Piper Cheyenne IIIA Airplane Maintenance Manual

AIRPLANE MAINTENANCE MANUAL
PA-42-720 (Advanced Trainer)
Cheyenne IIIA
PIPER AIRCRAFT CORPORATION
PART NUMBER 761-852
March 10, 2004
Published by
Technical Publications
© The New Piper Aircraft, Inc.
2926 Piper Drive
Vero Beach, Florida 32960
U.S.A.
Member
General Aviation
Manufacturers Association
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
0
RECORD OF REVISIONS
Revision Revision
No.
Date
Date
Inserted
By
Revision Revision
No.
Date
Date
Inserted
By
PAGE 1
Nov 1/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
RECORDOF REVISIONS(continued)
Revision Revision
No.
Date
PAGE 2
Nov 1/90
Date
Inserted
By
Revision Revision
No.
Date
Date
Inserted
By
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
LIST OF EFFECTIVE REVISIONS
(Always destroy superceded pages when you insert the revised pages.)
Revisions to this Maintenance Manual 761-852 issued January 10, 1990 are as follows:
Revision *
Publication Date
Chapters Affected
761-852
January 10, 1990
Original
761-852A
November 1, 1990
Record of Revisions and 5, 27
761-852A1
April 15, 1991
5, 23, 51, 71, 91
761-852A2
February 1, 1998
5, 7, 27, 30, 35, 51, 56, 77, 91
761-852A3
March 10, 2004
5
NOTE: A List of Effective Pages is found at the front of each chapter.
* Basic publications are assigned a part number which appears on the title page with the date of the issue.
Subsequent revisions are identified by the addition of a revision code after the part number. An "A" followed
by a number indicates the revision to the basic publication. Periodically it will be necessary to reissue the
entire manual, this will be indicated by the next successive letter of the alphabet.
1
LOG OF REVISIONS MarPAGE
10/04
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
THIS PAGE INTENTIONALLY BLANK
PAGE 2
Mar 10/04
LOG OF REVISIONS
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
INTRODUCTION
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
PAGE
OriginalIssue
All
DATE
CHAPTER
SECTION
PAGE
DATE
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LISTOF EFFECTIVE
PAGESan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
INTRODUCTION
LIST OF EFFECTIVEPAGES(continued)
CCHAPTER
SECTION
Jan0/9
PAGE
DATE
CHAPTER
SECTION
PAGE
LIST OF EFFECTIVE PAGES
DATE
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
INTRODUCTION
TABLE OF CONTENTS
SUBJECT
Introduction
General
Assignmentof SubjectMaterial
Application
Effectivity
Aerofiche
IdentifyingRevisedMaterial
AlphabeticalIndex
List of EffectivePages
SerialNumberExplanation
System/ChapterIndexGuide
Warnings,Cautions,and Notes
SupplementaryPublications
VendorPublications
PAGE
1
1
2
2
2
3
3
3
3
3
4
10
10
10
EFFECTIVITY:
040-999
CONTENTS
PAGE
1
CONTENTS
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Introduction
A. General
withtheAir
Manualis preparedin accordance
Trainer)Maintenance
(Advanced
The PiperPA-42-720
and
arrangement
the
to
respect
with
No.100
Specification
(ATA)
America
of
Association
Transport
system.
chapter-numbering
designated
the
within
System/Chapters
the
of
content
canceland/ordeclare
expresslyreservestherightto supersede,
NOTE: PiperAircraftCorporation
in thismanual
thatmaybe referenced
kitsor publication
obsoleteanypart,partnumbers,
withoutpriornotice.
WARNING: USE ONLYGENUINEPIPERAIRCRAFTPARTSOR PIPERAIRCRAFTAPPROVED
PARTSOBTAINEDFROM PIPERAPPROVEDSOURCES,IN CONNECTIONWITH
THE MAINTENANCEAND REPAIROF PIPERAIRPLANES.
to insureairworthiness
underrigorousprocedures
andinspected
GenuinePIPERpartsareproduced
otherthan
sources
from
purchased
Parts
for usein PIPERairplaneapplications.
andsuitability
inspections
and
tests
required
the
had
have
not
may
appearance,
PIPER,eventhoughidenticalin
when
dangerous
be
may
and
materials,
and
techniques
maybe differentin fabrication
performed,
installedin an airplane.
sources,whichtheservice
approved
salvagedor thosepartsobtainedfromnon-PIPER
Reworked,
stressesor
to unacceptable
subjected
been
have
may
authenticated,
be
cannot
or
unknown
historyis
usual
or
visual
routine
through
discernible
not
damage,
hidden
other
have
or
temperatures
eventhough
or structuralassembly,
testing. Thismayrenderthepart,component
nondestructive
unsuitableandunsafefor airplaneuse.
by PIPERAIRCRAFT
originallymanufactured
PIPERAIRCRAFTexpresslydisclaimsany responsibilityfor malfunctions,failures, damageor injury
causedby use of non-PIPERapprovedparts.
thecareof yourairplane,besureto includetheairplaneserialnumberin any
Anyquestionconcerning
correspondence.
EFFECTIVITY:
10/90
NTRODUCTIONJan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
of SubjectMaterial
B. Assignment
sectionto the manual,are markedwith a yellowplasticized
Eachchapter,includingthe Introduction
thesedividersshallbe staggered.
tabdivider.Foreaseof reference,
is organizedatthreelevels.Thethreelevelsare:
Thecontentof thispublication
- Thevariousgroupsarebrokendownintomajorsystemssuchas Environmental
1. System/Chapter
Systems,ElectricalPower,LandingGear,etc. Thesystemsarearrangedmoreor less
or importance.Theyareassigneda number,which
ratherthanbyprecedence
alphabetically
system.Thus,theelement"28"of the
numbering
becomesthefirst elementof thestandardized
thefuelsystemwillbe
concerning
number28-40-01refersto thechapter"Fuel".Everything
coveredin thischapter.
of an airplaneare brokendowninto
- Themajorsystems/chapters
2. Sub-System/Section
areidentifiedbythe secondelementof thestandardnumbering
subsystems.Thesesub-systems
system.Theelement"40"ofthe number28-40-01concernsitselfwiththeindicatingsectionof the
fuelsystem.
bythethird
maybe identified
unitswithina sub-system/section
- Theindividual
3. Unit/Subject
system.Theelement"01"of the number28-40-01is a subject
elementof thestandardnumbering
andmayor maynotbe
at theoptionof the manufacturer
designator.Thiselementis assigned
used.
C. Application
system.A person
to theATAformatwillusethesamebasicnumbering
conforming
Anypublication
the indicationportionof thefuelsystem,wouldreferto the
concerning
wishinginformation
Tab28-Fuel.Thetableof contentsin thefrontof thischapterwillprovidea listof subSystem/Chapter
systemscoveredin thischapter.Forexample,thefuelsystemchapterwitha full indexwouldcontain:
28-00
28-10
28-20
28-30
28-40
General
Storage(Tanks,
cells,necks,caps,etc.)
(Fuellines,pumps,valves,controls,etc.)
Distribution
Dump(If in-flightdumpingsystemis installed)
pressure,etc.)
temperature,
Indicating(Quantity,
Thematerial
andlistof theSystem/Chapters.
Referto thetableof contentsfor a completebreakdown
isarrangedin ascending
numerical
sequence.
D. Effectivity
followingthetitlepageof the manualliststherevisionscurrently
TheLogof EffectiveRevisions
effectivefor themanual.
EFFECTIVITY:
040-999
Jan 10/90INTRODUCTION
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
E. Aerofiche
for microfiche
a specification
of America(ATA)hasdeveloped
Association
TheAirTransport
compiledin this
foruseby allATAmembers.Theinformation
of aircraftpublications,
reproduction
periodically.These
Manualwillbe keptcurrentbyrevisionsdistributed
AeroficheMaintenance
and
all previousrevisionsandwillbe completeAerofichecardreplacements
revisionswillsupersede
Aerofichecardsof thesamenumberin theset.
shallsupersede
codenumbers:
of Aerofichealpha/numeric
Conversion
2J16 = Aerofichecardnumbertwoof a givenset andgridlocationJ16.
Example:
Firstnumber"2"istheAerofichecardnumber.
linereferencepercard.
Letter"J"isthe horizontal
percard.
is
the
verticallinereference
"16"
Secondnumber
RevisedMaterial
F. Identifying
A revisionto a pageis definedasanychangeto the printedmatterthatexistedpreviously.Revisions,
by a verticalblacklinealongthe left-handmarginofthe
anddeletionsshallbe identified
additions
pageoppositeonlythatportionof the printedmatterthatwaschanged.
pagenumberanddate,will
A blacklinein theleft-handmarginoppositethechapter/section/subject,
to a differentpage.
butthematerialwasrelocated
indicatethatthetextwasunchanged
Forpartslistingsan individualcodeletter"R"shallbe usedon eachlineto identifyrevisions.
Index
G. Alphabetical
is providedasan assistancein locating
indexfollowingthisportionof theintroduction
Thealphabetical
in whichany
andsub-chapter
the
chapter
index
provides
alphabetical
thedesiredinformation.The
to theTableof contentsin thefrontof the indicated
maybe found. Reference
giveninformation
canbe found.
chapterwillprovidethespecificpage(s)onwhichtheinformation
Pages
H. Listof Effective
liststheissuedateof eachpagethatis
Thelistof effectivepagesfollowingeachChapterDivider-Tab,
effectiveforthatchapter.
I. SerialNumberExplanation
blocksandcodesandit is a three
systemusedpertainsto theeffectivity
Theserialnumbering
system.Thesystemusesthelastthreedigitsof theaircraft'sserialnumber.
alpha-numeric
character
and
aircraftarereferenced
Thenumber999representtheterm"andup". In somecasesindividual
seriesof serialnumberare
thoseserialnumberswillbe separatedbya comma.Sequential
bya dashandthe lastserialnumberof thesequence.
bythefirstserialnumberseparated
represented
EFFECTIVITY:
040-999
10/90
INTRODUCTIONJan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
IndexGuide
J. System/Chapter
ThefollowingSystem/Chapter,SubsystemSectionIndexGuide is preparedin accordancewith ATA
SpecificationNo. 100 for usewith MaintenanceManuals,IllustratedPartsCatalogsand Wiring
DiagramManuals. The followingchaptersare not applicableto this MaintenanceManual: 18, 22, 38,
41,45, 49, 60, 62, 63, 64, 65, 66, 67, 70, 78, 80, 81,82, 83, and 84.
SYSTEM/
CHAPTER
SUB-SYSTEM/
SECTION
TITLE
INTRODUCTION
5
TIME LIMITS/MAINTENANCE
CHECKS
00
10
20
50
6
DIMENSIONSAND AREAS
00
7
10
20
10
Weighingand Balancing
Leveling
TOWINGAND TAXING
00
10
20
10
General
Jacking
Shoring
LEVELINGAND WEIGHING
20
9
General
LIFTINGAND SHORING
00
8
General
TimeLimits
Checks
Maintenance
Scheduled
Checks
Maintenance
Unscheduled
General
Towing
Taxiing
PARKINGAND MOORING
20
General
Parking
Mooring
11
REQUIREDPLACARDS
20
ExteriorPlacardsandMarkings
12
SERVICING
00
10
20
30
General
Replenishing
ScheduledServicing
Servicing
Unscheduled
00
10
EFFECTIVITY:
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INTRODUCTION
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
IndexGuide(continued)
J. System/Chapter
TITLE
SYSTEM/
CHAPTER
SUB-SYSTEM/
SECTION
20
STANDARDPRACTICESAIRFRAME
00
10
General
CorrosionInhibitingCompound
21
AIR CONDITIONING
00
20
30
40
60
70
General
Distribution
PressurizationControl
Heatingand Cooling
TemperatureControl
Moisture/AirContaminantControl
23
COMMUNICATIONS
00
20
60
70
General
DataTransmission&
AutomaticCalling
Static Discharging
Audio& Video Monitoring
24
ELECTRICALPOWER
00
30
40
60
General
DC Generation
ExternalPower
DC ElectricalLoad Distribution
25
EQUIPMENT/FURNISHINGS
00
10
20
30
40
50
60
70
General
FlightCompartment
Compartment
Passenger
Buffet/Galley
Lavatories
CargoCompartments
Emergency
Compartments
Accessory
26
FIREPROTECTION
00
10
20
General
Detection
Extinguishing
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INTRODUCTIONJan
INTRODUCTION
PIPERAIRCRAFT
PA-42-720(AdvancedTralner)
MAINTENANCEMANUAL
J. System/Chapter
IndexGuide(continued)
SYSTEM/
CHAPTER
SUB-SYSTEM/
SECTION
27
FLIGHTCONTROLS
00
10
20
30
50
70
General
AileronandTab
RudderandTab
ElevatorandTab
Flaps
GustLockandDamper
FUEL
00
10
20
40
General
Storage
Distribution
Indicating
HYDRAULICPOWER
00
10
30
General
Main
Indicating
ICEAND RAIN PROTECTION
00
10
20
30
40
60
General
Airfoil
Air Intakes
Pitot and Static
Windows,Windshieldsand Doors
Propellers/Rotors
28
29
30
TITLE
31
INDICATING/RECORDING
SYSTEMS
00
General
50
Central Warningsystems
32
LANDINGGEAR
00
10
20
30
40
50
60
General
Main Gear and Doors
Nose Gear and Doors
Extensionand Retraction
Wheelsand Brakes
Steering
Positionand Warning
LIGHTS
00
10
20
40
50
GeneralCompartment
Flight Compartment
PassengerCompartment
Exterior
EmergencyLighting
33
EFFECTIVITY:
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Jan 10/90INTRODUCTION
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
I. System/ChapterIndexGuide (continued)
TITLE
SYSTEM/
CHAPTER
SUB-SYSTEM/
SECTION
34
NAVIGATION
00
10
20
30
40
50
60
General
Data
FlightEnvironment
Direction
&
Attitude
LandingandTaxiingAids
PositionDetermining
Independent
Determining
Position
Dependent
Computing
FlightManagement
35
OXYGEN
00
10
20
General
Crew
Passenger
36
PNEUMATIC
00
10
20
General
Distribution
Indicating
VACUUM
00
10
20
General
Distribution
Indicating
37
51
STRUCTURES
00
10
20
40
70
52
53
54
DOORS
00
10
30
40
70
General
CleanupandAerodynamic
Investigation,
Smoothness
Processes
Fastners
Repairs
General
Passenger/Crew
Cargo
Service
DoorWarning
FUSELAGE
00
10
General
FuselageStations
NACELLES/PYLONS
00
General
EFFECTIVITY:
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INTRODUCTION
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
IndexGuide(continued)
J. System/Chapter
TITLE
SYSTEM/
CHAPTER
SUB-SYSTEM/
SECTION
55
STABILIZERS
00
10
20
30
40
General
Stabilizers
Horizontal
Elevator
VerticalStabilizer
Rudder
56
WINDOWS
00
10
20
General
FlightCompartment
Compartment
Passenger
57
WINGS
00
10
60
General
CenterWing
AileronsandElevons
61
PROPELLERS
00
10
20
General
Assembly
Propeller
Controlling
71
POWER PLANT
00
10
20
30
General
Cowling
Mounts
Fireseals
73
ENGINEFUELAND CONTROL
00
10
20
30
General
Distribution
Controlling
Indicating
74
IGNITION
00
10
20
General
ElectricalPowerSupply
Distribution
EFFECTIVITY:
040-999
Jan 10/9INTRODUCTION
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
J. System/ChapterIndexGuide (continued)
TITLE
SYSTEM/
CHAPTER
SUB-SYSTEM/
SECTION
76
ENGINECONTROLS
00
10
General
PowerControl
77
ENGINEINDICATING
00
10
20
30
General
Power
Temperature
Analyzers
79
OIL
00
10
20
30
General
Storage
Distribution
Indicating
91
CHARTS
EFFECTIVITY:
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PAGE
INTRODUCTION
10/90
Jan
INTRODUCTION
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CautionsandNotes
K. Warnings,
pointswhennecessary.
important
Theseadjunctsto thetextshallbe usedto highlightor emphasize
or limitswhichmustbe
procedures
methods,
processes,
Warningscallattentionto useof materials,
to methodsand
attention
call
Cautions
followedpreciselyto avoidinjuryor deathto persons.
attentionto methods
call
Notes
to
equipment.
damage
whichmustbefollowedto avoid
procedures
andnotesdirectly
above
directly
be
located
shall
caution
and
Warning
easier.
job
whichmakethe
apply.
they
which
to
paragraphs
the
with
in
line
be
and
beneaththetext
Publications
L. Supplementary
on various
providingservicing,overhaulandpartsinformation
Thefollowingisa listof publications
the
Trainer)airplane,whichyou maysupplement
(Advanced
on thePA-42-720
components
manual.
maintenance
PiperPublications:
(1) PartsCatalog- P/N 761 818
InspectionManual(50hour)- P/N761820
(2) Progressive
InspectionManual(100hour)- P/N761819
(3) Progressive
- P/N761853
(4) WiringDiagramManual(BasicElectrical)
- P/N761854
(5) WiringDiagramManual(Avionics)
M. VendorPublications
Thefollowing is a list of the vendor publications,usedin conjunctionwith the servicing,overhauland
parts informationon variouscomponents.
WARNING: WHEN SERVICINGOR INSPECTINGVENDOREQUIPMENTINSTALLEDIN PIPER
AIRCRAFT,IT IS THE USER'SRESPONSIBILITYTO REFERTO THE APPLICABLE
VENDORPUBLICATION.
1. ENGINE:
MaintenanceManual:
OperatorsHandbook:
PartsCatalog:
VendorAddress:
2. PROPELLER:
Overhaul Instructions:
VendorAddress:
3. VOLTAGECONTROL:
Vendor Address:
TURBOPROPGASTURBINEENGINE
PT6A-61:P/N 3034342
PT6A-61TURBOPROPENGINE,
SPECIFICOPERATINGINSTRUCTIONS
P/N 3033741
PT6A-61:P/N 3034344
Pratt & WhitneyAircraftCanada Inc.
Box 10, Longueuil,Quebec,CanadaJ4K 4X9
OVERHAULINSTRUCTION(FORTURBOPROP
APPLICATIONS)
Manual#118D
HartzellPropellerInc.
Piqua,Ohio 45356
LEARSIEGLERINC.
POWEREQUIPMENTDIVISION
OverhaulManualand IllustratedPartsCatalog
17600BroadwayAvenue
Maple Heights, Ohio 44137
EFFECTIVITY:
040-999
INTRODUCTION
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
M. VendorPublications(continued)
4. AUTOFLITE:
FlightControl:
VendorAddress:
FlightControl:
MaintenanceManual:
SystemManual:
SystemManual:
VendorAddress:
FlightControl:
SystemsManual:
SystemsManual:
VendorAddress:
FlightControl:
SystemsManual:
VendorAddress:
CollinsAP106/APS-65
AP106InstructionBook523-0764802-30111A
APS-65InstructionBook 523-0771868-00211A
FIS-84InstructionBook523-0768867-00111A
EFIS-85AInstructionBook523-077337-00311A
EFIS-85B2/12InstructionBook 523-0773940-00111A
EFIS-85B4/14InstructionBook 523CollinsGeneralAviationDivision
AvionicsGroup
RockwellInternationalCorporation
CedarRapids, Iowa 52498
Bendix/King
SystemFlightLine KNS 300
P/N 006-5091-01
KNS 660
P/N 006-5596-00
EFIS 10
P/N 006-5992-03
Bendix/KingRadioCorporation
400 N. RogersRoad
Olathe, Kansas 66062
GlobalSeries 2 GNS500A
P/N 34-56-00
GlobalSeries 3 GNS500A
P/N 34-56-15
GlobalNavigation/Sundstrand
2144 MichelsonDrive
Irvine, California 92715
UNS1
UNS-1A
UniversalNavigationCorporation
3260 E. LerdoRoad
Tucson, Arizona 85706
5. WHEELSAND BRAKES:
Installation,Maintenance
and OverhaulManual: B.F.Goodrich
3-1392Wheeland 2-1435-2Brake
6. KEVLAR:
A Guide to Cuttingand MachiningKevlarAramid:
KEVLARSpecialProducts
VendorAddress:
E.I. DuPontDe Nemours& Co. Inc.
TextileFibers Department
CentreRoadBuilding
Wilmington, Delaware 19898
EFFECTIVITY:
040-999
10/90
INTRODUCTIONan
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
(continued)
M. VendorPublications
7. CORROSIONINHIBITINGCOMPOUND:
DINOLInternational
VendorAddress:
Box 149, S-28101
OR
(GMBH)Wilhelm- Stein- Weg2
Hassleholm,Sweden
D-2000
Hamburg63, WestGermany 40-538-2061 46-451-80000
8. OXYGENSYSTEM
VendorAddress:
ScottAviation
225ErieStreet
Lancaster,NewYork 14086
9. COCKPITVOICERECORDER
FairchildAviationRecorders
VendorAddress:
P.O.Box3041
Sarasota, Florida 33578
10. FIRE EXTINGUISHER(PORTABLE)
GeneralFire ExtinguisherCorporation
VendorAddress:
1688 ShermerRoad
Northbrook, Illinois 60062
EFFECTIVITY:
040-999
10
Jan 10/90
INTRODUCTION
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 5
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SECTION
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DATE
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MAINTENANCE MANUAL
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PAGE 2
Mar 10/04
5 - LIST OF EFFECTIVE PAGES
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 5 - TIME LIMITS / MAINTENANCE CHECKS
TABLE OF CONTENTS
SUBJECT
SECTION
PAGE
GENERAL
5-00-00
1
TIME LIMITS
5-10-00
1
Airworthiness Limitations
Inspections
Life Limited Parts Marking and Disposition
SCHEDULED MAINTENANCE
1
2
2
5-20-00
General Purpose Description
Definitions
Away From Home Requirements
Program Responsibility
Event 1
Propellers, Detailed
Engine(s), Detailed
Left Wing, Detailed
Fuselage Forward, Detailed
Fuselage Main, Detailed
Cabin and Cockpit, Detailed
Fuselage Aft and Empennage, Detailed
Right Wing, Routine
Landing Gear, Routine
Special and General Section
Inspection Completed Statement
Event 1 Inspection Discrepancy Sheet
Event 2
Propellers, Detailed
Engine(s), Detailed
Right Wing, Detailed
Landing Gear, Detailed
Left Wing, Routine
Fuselage Forward, Routine
Fuselage Main, Routine
Cabin and Cockpit, Routine
Fuselage Aft and Empennage, Routine
Special and General Section
Inspection Completed Statement
Event 2 Inspection Discrepancy Sheet
Forms
Event Inspection Record and Sign Off Sheet
Progressive Cycle Inspection Record and Sign Off Sheet
Nicad Battery Form
Discrepancy Record Form
Service Publication Compliance Record
1
1
5
6
7
9
9
9
12
13
14
15
17
18
19
19
20
21
22
22
22
25
26
27
27
28
28
29
29
30
31
32
32
33
34
35
36
EFFECTIVITY:
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5 - CONTENTS MarPAGE
10/04
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 5 - TIME LIMITS / MAINTENANCE CHECKS
TABLE OF CONTENTS (cont.)
SUBJECT
SECTION
PAGE
SCHEDULED MAINTENANCE (cont.)
5-20-00
1
Forms (cont.)
Equipment Change Record Form
FAA Airworthiness Directives Compliance Record Form
Operational Inspections and Checks
100 Hour
37
38
39
39
SPECIAL INSPECTIONS
1
5-50-00
General
Engine Oil
100 Hours
300 Hours
400 Hours
500 Hours
600 Hours
700 Hours
1,000 Hours
1,200 Hours
1,400 Hours
1,500 Hours
2,000 Hours or Two Years
2,800 Hours
3,000 Hours
3,100 Hours
4,500 Hours
7,500 Hours
Three Years
Five Years
Seven Years
Eight Years
Ten Years
Twelve Years
Special or Unusual Condition Inspection
General
Operation in High Dust or Industrial Pollution
Operation in High Salt or Humidity Environment
Soft or Unusual Terrain
Operation in Extreme Cold
Lightning Strike
Engine Overspeed, Overtorque or Sudden Stoppage
Battery Overtemperature
Severe Turbulence, Hard or Overweight Landing
1
1
1
1
2
2
2
2
2
3
3
3
4
4
4
4
4
5
5
5
5
5
6
6
6
6
6
7
8
8
8
9
9
10
EFFECTIVITY:
040-999
PAGE 2
Mar 10/04
5 - CONTENTS
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Time Limits/Maintenance
Checks
A. General
PiperAircraftCorporationtakesa continuinginterestin havingthe ownerget the most efficientuse
from his airplaneand keepingit in the best mechanicalcondition. Consequently,PiperAircraft,from
time to time,issues servicebulletins,servicelettersand servicespares lettersrelatingto the aircraft.
(1) PiperServiceBulletinsare of specialimportanceand Piperconsiderscompliancemandatory.
These are sentto the latestregisteredownersand PiperCheyenneServiceCenters.
(2) ServiceLettersdeal with productimprovementsand servicehints pertainingto the aircraft.
They are sentto PiperCheyenneServiceCenters and sometimesdirectlyto ownersso they
can properlyservicethe aircraft and keep it up to datewith the latest changes. Owners
shouldgive carefulattentionto the serviceletter information.
(3) Servicesparesletters,which are usuallysentto PiperCheyenneServiceCenters,offer
improvedparts, kits and optionalequipmentwhich were not availableoriginallyand which
maybe of interestto the owner.
Aircraftoperatedfor otherthan normaloperation,such as air taxi or operatingin extremeclimates,
mayneed morefrequentinspectionto detectwear,corrosion,or lack of lubrication. Underthese
conditions,inspectionsshould be conductedmorefrequently,until operatorscan set their own
schedulesbasedon findings.
An ownershouldperiodicallycheckwith a PiperCheyenneServiceCenterto findout the latest
informationto keep his aircraftup to date.
PiperAircraftCorporationhasa subscriptionservicefor the servicebulletins,servicelettersand
servicesparesletters. This serviceis offeredto owners,pilots and mechanicsat a nominalfee and
may be obtainedthrough PiperCheyenneServiceCenters. Ownersresidingoutsideof the United
Statesare urgedto subscribeto this servicesince Pipercan seldomotherwiseobtainthe addressesof
foreign owners. Serviceproductsupportmanualsand revisionsare availablethrough PiperCheyenne
ServiceCenters.
The first overhaulor replacementof componentsshould be performedat the given periods. The
conditionof variouscomponentscan then be usedas criteriafor determiningsubsequentperiods
applicableto the individualairplane,dependingon usage,providingthe operatorhas an approved
monitoringsystem.
The time periodsgivenfor inspectionsof variouscomponentsis basedon averageusageand
environmentalconditions.
NOTE: Thelisted inspection,overhauland replacementschedulesdo not guaranteethat particular
itemwill reachthe listedtime withoutmalfunction,as the abovestatedconditionscannotbe
controlledby the manufacturer.
EFFECTIVITY:
040-999
5-00-00 PAGE
1
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A.
Time Limits
NOTE: The Airworthiness Limitations section is FAA approved and specifies maintenance required
under §§ 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.
1.
Airworthiness Limitations
The following limitations, related to fatigue life of the airplane and its components, have been
established for the PA-42-720 (Advanced Trainer):
(a) Refer to Chart 1 for Structural Inspection and Replacement.
(b) Refer to Chart 2 for Overhaul and Replacement Schedule.
(c) The safe life limit of propeller blades is unlimited.
NOTE: Refer to the LIMITATIONS section in the Pilot’s Operating Handbook for a detailed
delineation of the flight limitations of the airplane.
CHART 1
STRUCTURAL INSPECTION AND REPLACEMENT
Component
Life Limit
(Flight Hours)
Inspection Interval
(Flight Hours)
Effectivity
Code
Wing and Associated Structure
25,000
7,800 and 10,000
C
Cabin and Pressurized Structure
15,000
34,333
36,848
12,300 and 13,900
28,044 and 31,692
30,258 and 34,184
B
D
A
Empennage and Associated Structure
25,000
11,600 and 13,300
C
CHART 2 (Sheet 1 of 2)
OVERHAUL AND REPLACEMENT SCHEDULE
Component
Life Limit
(Flight Hours)
Inspection
Time
(Flight Hours)
Engine Mount Bolts (F.S. 106.0)
7,500
7,500
Inspection
Interval
(Flight Hours)
Effectivity
Code
Engine:
C
Main Landing Gear:
Top Cylinder Bolts (P/N 401-195)
1,400
C
Main Landing Gear Brace,
Pivot Shaft Assembly (P/N 43286-02)
1,500
C
Main Gear Retraction Arm (P/N 42042-02)
2,800
Link Bolt (P/N 400-209)
2,800
C
Link Assembly (P/N 85165-2 Rev B)
3,100
C
EFFECTIVITY:
A: 040-044, 053, 055, 057, 059
B: 048-052, 054, 056, 058, 060-999
C: 040-999
D: 045-047
700
100
C
1
5-10-00 MarPAGE
10/04
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A.
Time Limits (continued)
CHART 2 (Sheet 2 of 2)
OVERHAUL AND REPLACEMENT SCHEDULE
Life Limit
(Flight Hours)
Component
Inspection
Time
(Flight Hours)
Inspection
Interval
(Flight Hours)
Effectivity
Code
Main Landing Gear: (continued)
Actuator (P/N 451-814)
10,000 *
C
Hydraulic Cylinder (P/N 455-961)
10,000 *
C
Hydraulic Power Pack (P/N 481-171)
10,000 *
C
Hand Pump (P/N 481-771)
10,000 *
C
Shuttle Valve (P/N 491-948)
10,000 *
C
Unlock Actuator (P/N 551-968)
10,000 *
C
* 10,000 Hours or Ten (10) Years, whichever comes first.
Nose Landing Gear:
Actuator (P/N 451-825)
10,000 *
C
Shuttle Valve (P/N 491-949)
10,000 *
C
* 10,000 Hours or Ten (10) Years, whichever comes first.
2.
Inspections
Refer to 5-20-00 for Piper’s recommended Inspection Program.
3.
Life Limited Parts Marking and Disposition
14 CFR Part 43.10, Disposition of Life-Limited Aircraft Parts requires that proper procedures are
followed when removing life limited parts with time and/or cycles remaining on them as well as the
disposition of life limited parts with no time and/or cycles left. Life limited parts defined by Type
Certificate (TC) are listed in paragraph 1, above. Other parts which are replaced or rebuilt at
specified intervals are listed in Chart 2, above, and in 5-20-00 and 5-50-00.
A.
Parts that are removed prior to accumulating their life limit, are to be marked with indelible ink
or marker with the part number, serial number and accumulated life status as defined in 14
CFR Part 43.10 in a manner that does not affect part structural integrity, i.e. - no surface
deformation such as vibration/etching allowed.
B.
Parts that have accumulated the life limit shall be disposed of in accordance with the
applicable FARs. Piper recommends life limited parts with no time and/or cycles remaining be
completely destroyed.
PAGE 2
Mar 10/04
5-10-00
EFFECTIVITY:
A: 040-044, 053, 055, 057, 059
B: 048-052, 054, 056, 058, 060-999
C: 040-999
D: 045-047
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance
1. GeneralPurposeDescription
The PiperProgressiveInspectionprogramcomplieswith the F.A.A.FederalAviationRegulations
Parts43, 91 and 135 for progressiveinspections.The owner/operatoris primarily responsiblefor
maintainingthe airplanein an airworthycondition,includingcompliancewith all applicable
AirworthinessDirectivesand conformitywith the requirementsin FAR91.169,91.171 and91.172.
The completecycleinspectionconsistsof two (2) 100 hourevents,which providesfor a complete
aircraftinspectionin 200 aircraftflying hours. The completeinspection,events one andtwo must
be compliedwithintwelve (12) calendarmonths.
Late compliancewith the inspectionintervalof 100 hour may be extendedby not morethan ten
(10) hourswhile enrouteand for changingan inspectionintervalbecauseof serviceexperience.
The timeusedto reachthe nextinspectionfacility mustbe deductedfrom the next inspectiontime.
The inspectionprogramsare setup in manualform and are availablefrom the PiperCheyenne
ServiceCentersunder Part Numbers761 819 (100 HourEvents)and 761 820 (50 HourEvents).
Factsyoushould know:
ServiceBulletins,ServiceLetters,and Instructionsare sent to the registeredownerof the
affectedaircraft.
The registeredowners nameand addressare receivedby the FederalAviationAdministration
and usedon the AircraftRegistrationCertificateis the name and addressthat PiperAircraft
usesto mail ServiceBulletins,ServiceLetters,and Instructions.
If the aircraft is basedand/oroperatedat a differentlocationand/orby personsotherthan
thoserecordedon the aircraftregistration,then it is the responsibilityof the bonafideowner(s)
to forwardthe above Bulletinsand Lettersto those locationsor personsor to providea
separatesubscriptionserviceavailablefrom PiperAircraftCorporation.
Changesin aircraft registrationmaytake a substantialamountof time to be recordedon the
FederalAviationAdministrationcomputerand receivedby PiperAircraftto changethe mailing
address. Ownersand operatorsshouldmake arrangementsto keep abreastof service
releasesin this interimperiodthroughtheir PiperServiceCenter.
Everytwo weeksthe FederalAviationAdministration(FAA)publishesAirworthinessDirectives
(AD's)that applyto specificgroupsof aircraft. They are mandatorychangesand areto be
compliedwithin a time limit set by the FAA. Whenan AD is issued,it is sent to the latest
registeredownerof the affectedaircraftand also to subscribersof the service. The owner
shouldperiodicallycheckwith his PiperServiceCenteror A & P mechanicto seewhetherhe
hasthe latest issuedAD againsthis airplane. The owneris solelyresponsiblefor beingaware
of andcomplyingwith airworthinessdirectives.
PiperAircraftCorporationtakesa continuinginterestin havingthe ownerget the mostefficient
usefrom his airplaneand keepingit in the best mechanicalcondition. Consequently,Piper
AircraftperiodicallyissuesServiceBulletins,ServiceLetters,and ServiceSparesLetters
relatingto the Aircraft.
EFFECTIVITY:
040-999
PAGE
5-20 00 Nov
1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance
(continued)
1. GeneralPurposeDescription
(continued)
Facts you shouldknow: (continued)
PiperServiceBulletinsare of specialimportanceand PiperConsidersCompliancemandatory.
These are sent to the latest registeredownersand PiperServiceCenters.
ServiceLettersdealwith productimprovementsand servicehints pertainingto the aircraft.
They are sentto the PiperServiceCenterand directlyto the owners so they can properly
servicethe aircraftand keepit up to date with the latestchanges. Ownersshouldgive careful
attentionto the ServiceLetterinformation.
ServiceSpareLetterswhich are usuallysentto Piper ServiceCenters,offer improvedparts kits
and optional equipmentwhichwere not availableoriginallyand which maybe of interestto the
owner.
Anownershouldperiodically
checkwitha PiperServiceCenterto findoutthe latest
information
to keephisaircraftupto date.
PiperAircraftCorporationhasa subscriptionservicefor the ServiceBulletins,ServiceLetters,
and ServiceSparesLetters. This serviceis offeredto interestedpersonssuch as owners,
pilots, and mechanicsat a nominalfee and may be obtainedthroughPiperServiceCenters.
Ownersresidingoutside of the UnitedStatesare urgedto subscribeto this servicesince Piper
cannotobtain the addressesof foreign owners. ServiceProductSupportManualsand
revisionsare availablethroughPiperServiceCenters.
WARNING: WHEN SERVICING OR INSPECTING VENDOR EQUIPMENT INSTALLED IN
PIPER AIRCRAFT, IT IS THE USERS RESPONSIBILITY TO REFER TO THE
APPLICABLE VENDOR PUBLICATIONS.
Eachevent inspectioncomprisesa predeterminednumberof locationinspectionsas indicatedon
each event sample. The event inspectionis conductedeach 100 hours and mustbe done in
sequence. The event inspectionsare so arrangedso that the 200 flying hour cycle resultsin a
complete inspection. Eacheventwill be recordedin the Event InspectionRecordand Sign Off
Sheet,which are a runninglog or the currentstaus of the aircraftinspection.
ThePiperProgressive
100HourInspection
hasthefollowingbasicfeatures:
(a) TheTwo(2) EventInspections
at 100HourIntervals
(b) InspectionCompleted
Statements
(c) CompleteAircraftInspectionCycleat 200Hours
(d) InspectionDiscrepancy
Sheet
(e) EventInspectionRecordandSignOffSheet
(f) Progessive
CycleInspectionRecordandSignoffSheet
(g) NicadBatteryForm
(h) Discrepancy
RecordForm
(i) ServicePublication
Compliance
Record
(j) Equipment
ChangeRecordForm
(k) FAAAirworthiness
DirectivesCompliance
RecordForm
(I) Operational
Inspections
andChecks
(m) Special Inspections
(n) Specialor UnusualConditionInpsections
EFFECTIVITY:
040-999
PAGE 2
Nov1/90 5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
1. GeneralPurposeDescription(continued)
The progressiveinspectionis recommendedby PiperAircraftCorporationand meetsthe
requirementsoutlinedin FederalAviationRegulationsPart 43 and Part 91 SubpartC, paragraph
91.169(d).
The purposeof the progressiveinspectionis to allow maximumutilizationof the aircraft,reduce
maintenanceinspectioncost and maintaina maximumstandardof continuousairworthiness.
Ownersand operatorsof the Piper CheyenneIIIA are remindedthat certain requirementsmustbe
met beforethe progressiveinspectionprocedurescan be utilized. These requirementsare
containedin the FederalAviationRegulationsPart43 - Maintenance,PreventiveInspection,
Rebuildingand Alterationand Part 91 - GeneralOperatingand FlightRules.
The inspectionfrequencyused in the progressiveinspectionis basedon previousturbo propeller
operatingexperience.However,adjustmentsto the inspectionintervalscan be made only by Piper
AircraftCorporation.Any changesto this procedureby the owneror operatormust be approved
by the local FederalAviationAdministration.
The inspectionfrequencymay also vary for trainingaircraftwhosesole purposeis flight training,
and whereexperienceinformationhas been submittedand evaluatedby Piperand the applicable
aviationauthority(ex. FAA,JCAB,etc.). (SeeChart1, InspectionIntervalVariance,Section5-20-00.)
Discrepanciesfound during inspectionswill be enteredon the DiscrepancyRecord. The person
conductingthe inspectionwill advisethe ownerand/oroperatorof the discrepanciesfound during
the inspectionand enteredon the DiscrepancyRecord. Discrepancieswhich affectthe
airworthinessof the airplanewill requirethe necessarycorrectiveactionto be accomplishedbefore
the airplaneis returnedto service.
Event#1
To be performedat the 100 - 300 - 500 - 700 - 900flying hour intervals.
Consistof:
(a) Propellers,Detailed
(b) Engines,Detailed
(c) Left Wing, Detailed
(d) FuselageForward,Detailed
(e) FuselageMain,Detailed
(f) Cabinand Cockpit,Detailed
(g) FuselageAft and Empennage,Detailed
(h) RightWing, Routine
(i) LandingGear,Routine
(j) Specialand GeneralSection
(k) InspectionCompletedStatement
(I) Event1 InspectionDiscrepancySheet
EFFECTIVITY:
040-999
5-20-00 Feb
Feb 1/98
1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
1. GeneralPurposeDescription(continued)
Event #2
To be performedat the 200 - 400 - 600 - 800 - 1000flyinghour intervals.
Consistof:
(a) Propellers,Detailed
(b) Engines,Detailed
(c) RightWing, Detailed
(d) LandingGear,Detailed
(e) Left Wing, Routine
(f) FuselageForward,Routine
(g) FuselageMain, Routine
(h) Cabinand Cockpit,Routine
(i) FuselageAft and Empennage,Routine
(j) Specialand GeneralSection
(k) InspectionCompletedStatement
(I) Event 2 InspectionDiscrepancySheet
Event InspectionWork Sheet- used in conjunctionwith the eventinspectionto providea list of
discrepanciesand their correctiveaction.
Special Inspections- are inspectionsto be performedand recordedwith the appropriateEvent
Inspection.
Specialor UnusualConditionsInspections- these inspectionsshould be performedin conjunction
with the normal and specialevent inspectionswhenoperatingin extremeconditions(i.e. sand,
saltwater,etc.) or in the chanceof some unforeseenincidentsuchas lightningstrike,extreme
turbulence,etc.
OperationalInspection- to be performedupon completionof each Event Inspection.
Event InspectionRecordand SignOff Sheet- is a permanentrecordand containsthe following:
(a) Event InspectionNumber
(b) AircraftHours
(c) DateAccomplished
(d) Work Order Number- FAAapprovedrepairstationsonly
(e) Signatureand CertificateNumberof personconductinginspection.
(f) The followingCertificationstatement:
I have inspectedthis aircraft in accordancewith PiperAircraftCorporation'sProgressive
Programand found it to be in airworthycondition.
EFFECTIVITY:
040-999
Nov 1/90
5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
1. GeneralPurposeDescription(continued)
ProgressiveCycle InspectionRecordand Sign Off Sheet- is usedupon completionof the two
eventinspections(200flight hours). The cycle recordincludesthe aircraft registrationnumber,
serial number,and columnsfor recordingeach cycle inspection. It also containsa list so that the
personconductingthe inspectionscan ascertainthat all paperworkand inspectionrecordsare in
orderbeforestartingthe nextcycle.
DiscrepancyRecord- is a logof discrepancieswhich mayor may not requirecorrectiveaction.
FAAAirworthinessDirectivesand/or manufacturer'sservicepublications,and itemsdiscovered
awayfrom stationor on the eventinspection,not requiringimmediateaction,may be enteredon
the discrepancyrecordform providingcompliancewith the AD or servicepublicationat the next
eventwill be withinthe time allowancepermitted. Certain FAAor manufacturer'smandatory
inspectionsmay haveto be accomplishedbeforefurtherflight, in whichcase, their compliance
shouldbe recordedon the appropriaterecord.
ServicePublicationComplianceRecord- is usedto recordthe complianceof all manufacturer's
servicepublications.
FAAAirworthinessDirectivesComplianceRecord- is used to recordthe complianceof applicable
AD notes.
EquipmentChangeRecord- is a form to recordequipmentchangesand overhaultimes which
allowsthe controlof equipmenttimesfor inspectionor overhaulreplacement. By use of this record
the out-of-sequenceequipmentcan be reviewedto permit a projectionof equipmentduetimes in
relationto the aircraftflight hours.
2. Definitions:
(a) Inspections- Mustbe performedonly by CertifiedMechanicswho are qualifiedon this aircraft,
utilizingacceptablemethods,techniquesand practicesto determinephysicalconditionand
detectdefects.
(b) Checks- Can be performedby pilotsand/or mechanicswho arequalifiedon this aircraftand
consistsof examinationsin the form of comparisonswith statedstandardsfor the purposeof
verifyingcondition,accuracyand tolerances.
(c) DetailedInspections- Consistsof a thoroughexaminationof the appliances,the aircraftand
the componentsand systemswith such disassemblyas is necessaryto determinecondition.
(d) ApprovedInspection- Meansa continuingairworthinessinspectionof an airplaneand its
variouscomponentand systemsat scheduledintervalin accordancewith proceduresapproved
by the Administratorof the FederalAviationAdministration.
(e) InspectionTime Limitations- Late compliancewith the inspectionintervalof 100 hourmay be
extendedby not more thanten (10) hourswhile enrouteand for changingan inspectioninterval
becauseof serviceexperience.The time usedto reachthe nextinspectionfacility mustbe
deductedfrom the next inspectiontime.
(f) Tests- Operationof aircraftcomponents,appliancesor systemsto evaluatefunctional
performance.
(g) OperationTest- This test is used to ascertainthat a systemcomponentis in operablecondition
and can be performedwith the equipmentinstalledin the aircraft. In addition,eachoperational
test must be performedby an FAACertifiedRepairStationappropriatelyrated or by a Certified
Mechanicwho is qualifiedon this aircraft. The recordingof the abovefunction mustbe made
in the permanentaircraft recordsby the authorizedindividualperformingthe test.
EFFECTIVITY:
040-999
5-20-00
N
1/90
Nov 1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance
(continued)
2. Definitions
(continued):
(h) Functional
Test- Thistestis usedto ascertainthatsystemor component
is functioning
properly
andis in conformance
withminimumacceptable
designspecifications.
Thistest mayrequire
theuseof supplemental
benchtest equipment.In addition,eachfunctionaltest mustbe
performedbyan FAACertifiedrepairStationwithappropriate
ratingsor by a Certified
Mechanic
whois qualifiedonthis aircraft.Therecording
of theabovefunctionmustbe made
inthe permanent
aircraftrecordsbytheauthorized
individual
performing
thetest.
(i) BenchCheck- Meansremovalof component
fromtheaircraftto inspectfor cleanliness,
impending
failure,needfor lubrication,
repairor replacement
of partsandcalibration
to at least
the manufacturers
specifications
usingthemanufacturers
recommended
testequipment
or
standardsortheequivalent.
Eachbenchtestwill be performed
bya CheyenneServiceCenter,FAACertifiedRepairStation
withappropriate
ratingor bya certifiedmechanic.Thistestwillbe performedat thescheduled
intervalregardless
of anybenchtestperformed
on a particular
component
whilebeing
repaired/overhauled
beforescheduledintervalbenchtest. Afterthecomponent
is installedinto
theaircraft,an operational
testof thecomponent
andits relatedsystemshouldbe performed
to
ensureproperfunction.Serviceable
partsthatwereissuedto thecomponent
willbe filedin the
aircraftpermanent
records.Thepersonperforming
thecheckmustmakeappropriate
entriesin
theaircraft'spermanent
maintenance
record.
(j) Maintenance
- Thewordmaintenance
asdefinedby FARPart1, means"inspection,
overhaul,
repair,preservation
andthereplacement
of parts,butexcludespreventivemaintenance."
However,wherereferencein thisinspection
programthe word"maintenance"
means
inspectionandthereplacement
of timelife limitedparts.
(k) RoutineInspections
- Consistsof a visualexamination
orcheckofthe aircraftandits
components
andsystemswithoutdisassembly.
(I) SpecialInspections
- Involvethosecomponents,
systemsor structurewhichbytheirapplication
or intendeduserequirean inspection
peculiarto, moreextensivein scopeor at a timeperiod
otherthanbeyondthatwhichisnormallyaccomplished
duringthe50 houreventinspection.
(m)Timein Service- As usedin thisprocedure
isthetimefromthemomentthe aircraftleavesthe
grounduntilit touchesthegroundatthenextpointof landing.
(n) OnCondition- Maintenance
conceptwherebysomecomponents
of theengineremainin
serviceas longastheyappearairworthyat eachinspection.Thereplace-on-condition
concept
is asopposedto replaceaftera "life-limited"
timeinterval.Inthecaseof enginesthemselves
this meansno TBOis required.
3. Away From Home Requirements
If the airplane is to be awayfromthe homelocationat the time an inspectionis due, the Pilot-inCommandof the flight will takewith him all sign off sheetswhichwill be requiredfor the inspection
and a copy of this manual. The inspectionwill be conductedor supervisedby one of the following:
(a) Anappropriately
certifiedrepairstation.
(b) Anappropriately
certifiedmechanic,
qualifiedon thistypeof aircraft.
of PiperAircraftCorporation.
(c) A qualifiedrepresentative
Theresultsof the inspection
willbe notedon the properSignOffSheetswhicharethenbrought
backto the homebase. Thepilotwillbe responsible
forall inspection
formsandworksheet
entrieswithmechanicsand/orinspector's
signatureandidentification.
Discrepancies
affectingtheairworthiness
of theairplane,whentheairplaneis awayfromthelocal
station,willbe correctedbyeithera, b or c above.Thepilotwillbe responsible
for allworksheet
entrieswithmechanics
and/orinspector's
signatureandidentification.
ThePilot-in-Command
is responsible
for assuringthattheappropriate
entrieshavebeenmadein
theaircraftandenginelogbooks.
EFFECTIVITY:
PAGE 6
Nov 1/90
5-20-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
4. ProgramResponsibility
Any changein personnelresponsibleforthis programwill be added with the appropriate
informationon a separatesheetand the originalcopy sentto the local FederalAviation
Administration- GeneralAviationDistrictOfficewhile a duplicatecopy is attachedbehindthat
page in the booklet. The previousinformationsheetwill be left in the bookletand the word
"changed"will be written acrossthe altered information.
NOTE: The titles and/or positionslistedbelowmay be changedor combinedas desired,but the
responsibilitiesshouldbe maintainedto assureprogramintegrity.
ProgramManager
Name (Printor Type)
(Signature)
It will be the ProgramManager'sresponsibility:
(a) To assurethat all flight discrepanciesare correctlyrecordedand coordinatedwith the
maintenancedepartment.
(b) To schedulethe aircraft into maintenancein accordancewith the inspectionprogramand
aircrafttimes.
(c) To maintaina recordof aircraftdata such as equipmentchangedates and times, airframe,
engineand accessoryserialnumbers,time changeitems, etc..
(d) To assurethat all AD's, Bulletinsand Lettersare relayedto the appropriatepersonsfor
execution.
(e) To assurethat equipment,trainingand safetyitems are availableto properlyand safely
performthe inspectionand maintenanceprogram.
MaintenanceForeman
Name (Printor Type)
(Signature)
It will be the responsibilityof the MaintenanceForeman:
(a) To see that all inspectionformsand maintenanceinstructionsare properlycompliedwith.
(b) To providetechnicaldata, maintenancemanuals,instructionsand AD notesfor the aircraft
inspection.
(c) To providetrainingand assistanceto maintenancepersonnelproceduresand methodsin
accomplishingmaintenanceand inspectionon the aircraft.
(d) to assignthe personnelnecessaryto inspectand maintainthe aircraft in a safe and
correct manner.
(e) Toinform the managerif discrepanciesin parts,equipmentand personnelaffectingthe
program.
Chief
Mechanic/Inspector/Crew
Name(Printor Type)
(Signature)
It will be the responsibilityof the above:
(a) Toconductor supervisethe InspectionProgram.
(b) Toassurethat OperatingTimes,SerialNumbers,AirworthinessDirectives,Bulletins,
Instructionsand Discrepancies,etc. are properlynoted,recorded,completedand
forwardedto the Foreman.
(c) To preparethe necessaryEvent Inspection,SpecialInspectionand DiscrepancyForms.
(d) To informthe Foremanof lack of equipment,personnelor parts to properlyperformthe
Inspectionand MaintenanceProgram.
EFFECTIVITY:
040-999
5-20-00
FEB
5-20-00 PAGE
Feb 1/98
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
4. ProgramResponsibility(continued)
Pilot
Name(Printor Type)
(Signature)
It will be the responsibilityof the Pilot:
(a) To assurethat all flight discrepanciesare properlyand as completeas possible,recorded.
(b) To assurethat "Away FromStation"inspectionsand maintenanceare properlycomplied
with and all forms and recordsare correctlycompleted.
(c) To assurethat all forms, manualsand items neededfor "AwayFrom Station"inspections
are on boardthe aircraftwhen required.
(d) To assurethat all forms and informationrelativeto the aircraft inspectionand maintenance
are forwardedto the maintenancemanagerand/orforeman immediatelyupon returnto
home station.
The person responsiblefor schedulingand maintainingthe aircraftunderthis inspectionprocedure
must enter their namebelowwith the requiredinformationand forwardthe originalcopy of this form
to the local FAA GeneralAviationDistrictOffice. A duplicatecopy should be maintainedin this
manual.
Name:
Address:
Street
City
State
Zip
Telephone
Date ProgramInitiated
Signature
EFFECTIVITY:
040-999
Nov 1/90
5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event1
(a) Propellers,Detailed(Refer to 61-10-00)
Left Right
(1) Removeand inspectspinnerfor cracks,corrosionand damage.
(2) Inspectbladesfor nicks,cracks,erosionand evidenceof strikes.
(3) Checkfor greaseand oil leaks.
(4) Inspectbulkheadfor cracks,securityand corrosion.
(5) Inspectpropellermountingbolts for conditionand propersafety. Checktorque if safety
is broken.
(6) Inspect hub parts for cracks,corrosionand security.
(7) Rotate bladesand inspectfor tightness.
(8) Inspectbetafeedback ring for runout (0.010inch max.) and no metalto metalcontact
with reverseleverand carbonblockholder.
(9) Inspectcarbon blockfor wear limit and freedomof movement.
(10) Inspectlow pitch stop rods, returnspringsand beta feedbackring for damage,
corrosionand freedomof movement.
(11) Inspectconditionof propellerdeicerslip ring and brush blockor modularbrush
assembly.
(12) Inspectpropellerdeicebootsfor securityof attachmentand condition.
(13) Inspectpropellerdeicewiringand junctionblocksfor security,cracks,chafingand
damage.
(14) If installed,inspectconditionand securityof synchrophaserwiring.
(15) Lubricatepropeller.(Referto 12-10-00)
(16) Installspinner.
(b) Engine(s),Detailed (Referto 71-00-00)
NOTE: Referto Pratt& WhitneyPT6A-61MaintenanceManualP/N 3034342and 71-0000 in the PA-42-720(AdvancedTrainer)MaintenanceManualas requiredfor
details.
Left Right
]
(1) Removeenginecowling.
(2) Removeupperand lowerfirewallaccesscovers.
(3) Clean and inspectcowlingand coversfor cracks,distortionand loose or missing
fasteners.
(4) Inspectoil temperaturesenderunitfor leaksand security.
(5) Inspectoil linesand fittingsfor leaks,security,chafing,dents,cracksand routing.
(6) Cleanand inspectoil coolerfor conditionand attachment.
CAUTION: REFERTO APPROPRIATEPRATT& WHITNEYMAINTENANCE
MANUALAND SERVICEBULLETINSAND 5-50-00IN THE PA-42-720
(ADVANCEDTRAINER)MAINTENANCEMANUAL.
(7) Removeand inspectoil filterfor damageand contamination Cleanor replaceas
required.
EFFECTIVITY:
040-999
5-20-00
PAGE9
l5-20-00
Nov1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event 1 (continued)
(b) Engines,Detailed (continued)
Left Right
AND CLEANINGPRECAUTIONS
CAUTION: ALL ENGINECLEANINGPROCEDURES
MUST BEOBTAINEDFROMTHE APPROPRIATESECTIONSOF THE
PRATT& WHITNEYMAINTENANCEMANUAL( PT6A-61)P/N 3034342.
(8) Clean exteriorof engine.(Referto Pratt& WhitneyMaintenanceManual)
(9) Inspectconditionof igniterplugs. (Referto 74-00-00)
(10) Inspect ignition harnessand insulatorsfor high tension leakage, continuity,damage
and attachment.
(11) Inspectelectricalconnectionson ignitionexciter for safetyand security.
(12) Removeair inlet screen; inspectfirst stage compressorblades for ingestiondamage
and corrosion. Inspectscreenfor damageand cleanliness. Installscreen.
(13) Clean and inspectfuel pump inlet screenfor foreign material. Replaceoutletfilter.
(14) Inspect gas generatorcase drain valvesfor securityand leaks. (Checkafter engine
run)
(15) Inspect magnetic chip detector and jump pins "A & B", operational check of
annunciator.
(16) Inspectconditionof inlet air ducts and ice protectionsystemfor operationand fit. (See
latest PiperServiceLetterNo. 983.)
(17) Inspect condition of actuators and linkage for ice protection system and oil cooler
doors.
CAUTION: WHEN ENGINEIS NOT RUNNING,ANY ATTEMPTTO MOVEPOWER
LEVERSINTO REVERSEPOSITION,WITHOUTDISCONNECTING
PROPELLERPUSH-PULLWIRE ROPECLEVISFROMPROPELLER
CONTROLCAM,WILL RESULTIN BENDINGOR KINKINGOF WIRE
ROPE
(18) Inspect power lever,start control, propellergovernorand propellerreversing linkage
for condition,traveland operation.
(19) Inspectgas generatorcase for cracks,distortionand evidenceof overheating.
(20) Inspectexhauststacksand exhaustductsfor cracks,distortionand security.
(21) Inspectpropellergovernorfor leaksand security.
(22) Inspect propeller shaft for oil leaks.
(23) Removedrain; clean and inspectfuel filter bowl and element. (Firewallmounted)
(24) Inspect all flexible lines (fuel, hydraulic,pneumaticand oil) for leaks, abrasions,cuts
and secureconnections. Replaceupon conditionor as per SpecialInspection. (See
latest PiperServiceBulletinNo. 822 and 5-50-00.)
(25) Inspectfuel control, fuel pumps,fuel manifold,fuel flow transmitterand fuel pressure
transmitterfor leaks, securityand condition. Checkwiring for security and condition.
(See latest revisionof PiperServiceBulletin957.)
(26) Replace hydraulic filter and inspect for contamination. If filter shows evidence of
contamination,inspectentire hydraulicsystem.
(27) Inspecthydraulicpumpand hydrauliclinesfor securityand leaks.
(28) Inspectenginefiresealsfor cracks,damageand security.
(29) Inspectfirewallsfor cracks,stressand condition.
(30) Inspectfirewallsealsfor condition.
I
EFFECTIVITY:
040-999
PAGE 5-20-00
Feb 1/98
5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event1 (continued)
(b) Engine(s),Detailed (continued)
Left Right
(31) Inspectoil breathertube for obstructionand security.
(32) Inspectoil filler capseal for damageand condition.
(33) Check properlockingfeatureof oil filler cap.
(34) Inspectoil pressuretransmitterfor securityand leaks. Checkwires for connectionand
damage.
(35) Inspect torque transmitter for leaks and security. Check wiring for damage and
security. Check conditionof shockmounts.
(36) Inspectoil manifoldfor leaksand security.
(37) Inspect autoignitionswitch and manifoldfor securityand condition. Check wiringfor
damageand secureconnection.
(38) Inspect P3 air filter for contamination.Replaceif evidenceof contamination.(Referto
5-50-00)
(39) Inspect fire extinguisherfor damageand security of wiring. Test fire extinguishing
systemfor propercylinderpressure(Referto 26-20-00)
(40) Inspectfire warningsensorsandwiringfor securityand condition.
(41) Inspectcompressorwash ringfor damageand security.
(42) Inspectcompressorwashvalve assemblyfor securityand operation.(if installed)
(43) Inspectengine mountsfor cracks,damageand loose mountingbolts.
(44) Inspectrubber Lordmountsfor deteriorationand condition.
(45) Checksecurity,wiringand operationof bladeanglesensoror beta lights,if installed.
(46) Check security,wiringand operationof beta limiter system.
(47) Inspectfront and rear tachometergeneratorsfor securityand wiring.
(48) Inspect starter generator quick attachment device (QAD) ring and mount pad for
security,cracksand damage.
(49) Inspectconditionof starter-generatorcables.
(50) Inspectconditionof starter-generatorcoolingair ducts.
(51) Cleandual drive lubefilter.
(52) Inspectgeneratorcontrol units (GCU)for security,damageand wiring integrity.
(53) Inspect bleed air lines, flexiblelines and couplingsfor security,damageand leakage.
(Also see latest PiperServiceBulletinNo.914).
(54) Check bleed air shutoffvalve and mixing regulatorfor security,damage,leakageand
correct operation. Checkwiringfor attachmentand damage.
(55) Inspect bleed air intercoolerfor cleannessand blockage. Check intercoolerinlet and
outletfor blockage,securityand leakageof duct couplings.
(56) Inspect and checkall enginewiring and ITT harnessand connectorsfor securityand
condition.
(57) Lubricatepower plantper LubricationChart.(Referto 12-10-00)
(58) Installupper and lowerfirewallaccesscovers.
(59) Installenginecowling.
Y:
EFFECTIVIT
040-999
11
5 20 00 PAGE
NOV1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event 1 (continued)
(c) Left Wing, Detailed(Referto 57-00-00)
CAUTION: THE FLUXDETECTORCOVERON THE OUTBOARDWING SURFACEIS
SECUREDWITH BRASSSCREWS. ONLYBRASSSCREWSWILL BE
USEDWHEN INSTALLINGTHIS COVER.
(1) Removeinspection
platesandpanels.
(2) Inspectstaticdischargewicksfor securityof attachmentand condition.
(3) Inspectflux detectorplug connectionsand wiring for corrosion,securityand condition.
(4) Inspectwing and control surfaceskins and fairingsfor cracks,looseor missingrivets
and damage.
(5) Inspectaileronfor securityof attachmentand freedomof movement.
(6) Inspectinteriorstructurefor cracks,loose and missingrivetsor concealeddamage.
(7) Inspectaileroncables,pulleysand bellcrankfor damage,full travel, alignment,
clearanceand propercable tension.
(8) Inspectaileronbalanceweightsand ailerongap seal for conditionand security.
(9) Inspectflaps,actuators,limitswitches,
wiringandpotsfor corrosion,damage,operation
and full travel.
NOTE: An approachflap extensionof 10° will not activatethe Flap/LandingGear
WarningHorn sincethis flap setting is intendedfor extendedapproachuse.
Normallandingsare made using30° flaps and the Flap/LandingGearWarning
Hornwill activateif the landinggear is not extendedwhen the flaps are
extendedmorethan 10°.
(10) Inspectflap tracks and rollersfor condition. Checkrollersfor freedomof movement
and binding.
(11) Inspectflap track bolts and aileronhingeboltsfor wear,securityand corrosion.
(12) Inspectall controlsurfacebearingsfor attachment,wearand freedom of movement.
(13) Checkoperationof left fuel shutoffvalveand crossfeedvalve.
(14) Inspectwing attachmentbolts for stripealignmentand bracketsfor cracksand
corrosion.
(15) Inspectenginemount bracketsfor conditionand security.
(16) Inspectbladderfuel cells for attachment,leaksand contamination.
(17) Inspectintegralfueltanks for leaks,corrosion,contaminationand damage.
(18) Inspectfuel lines for attachment,chafingand leaks.
(19) Checkfiller neckanti-siphonvalvesand fuel caps for damageand properseal. Inspect
quickdrainsfor properoperation.
(20) Checkfuel tanks for correctoperatingfuel. Check conditionof fuel type placards.
(21) Inspectfuel ventsfor obstructionsand damage. Checkvalvesfor operationand seal.
(22) Inspectfuel capacityprobesfor security,corrosionand leaks.
(23) Inspectelectrical
wiringharnessandconnections
for chafing,damageandsecurity.
(24) Inspecthydrauliclines for leaks,damageor chafingand attachment.
(25) Inspectpneumaticlines,flexible lines and componentsfor leaks,cuts, abrasionsand
secureconnections. Replaceupon conditionor per SpecialInspection.
(26) Inspectbleedairwarningductswitchesfor leaksandsecurityandwiringfordamage
and attachment.(Engine,intercoolerand wing root).
(27) Inspectbleed air duct couplingfor leakage,damageand security. Checkduct
insulationfor conditionand security. Checkductingfor securityand chafing.
EFFECTIVITY:
040-999
PAGE 12
Nov 1/90 5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event 1 (continued)
(c) LeftWing,Detailed(continued)
deicerbootsfor conditionanddamage.
(28)Inspectpneumatic
springcenteringof switchbladeand
for securityof attachment,
(29)Inspectlifttransducer
corrosion.checkheatelementfor operation.
boltsfor security.
(30)Inspectwingtip tankattachment
(31)Inspectwingtip navigationandstrobelightsfor brokenlenses,security,wiringand
attachment.
lightfor brokenlens,security,wiringandattachment.
(32)Checkwinginspection
for
condition,leaksanddamage.
lockers
wing
(33)Inspect
(34)Inspectwinglockerdoorfor securityanddamage.
(35)Checkwinglockerdoorcylinderandlockfor security,damageandoperation.
Chart.(Referto 12-10-00)
per Lubrication
(36)Lubricate
CAUTION: ONLYBRASSSCREWSARE TO BE USED FOR INSTALLINGFLUX
DETECTORACCESSDOOR.
(37) Installinspectionplates and panels.
(d) FuselageForward,Detailed(Refer to 35-00-00and 53-00-00)
platesandpanelsandopenbaggagedoorandradome.
(1) Removeinspection
(2) Inspectbaggagedoor surface,door latch,hinges,air cylinders,door ajar switch,
compartmentlightand door sealfor damage,wear,properriggingand operation.
(3) Checkbrake reservoirand brake lines for leaks,securityand properfluid level in
reservoir.
(4) Inspectelectronicsinstallation,wire harnessplugs,ground bus bar,triplexerand radios
for condition,corrosionand security.
(5) Inspectantennamountsand electricalwiringfor securityand corrosion.
(6) Inspectradioand ECS accesspanelsfor damage,looseor missingfastenersand
conditionof rain gutteron accessopening.
(7) Inspectbatteryboxand cablesfor security,damageand corrosion.
(8) Inspectconditionof battery,batteryover temperaturesensors and fuse. (Referto
5-50-00)
(9) Inspectradomelightningdiverterstripsfor damageand security.
(10) Withinthe radomeinspectthe radar,glide slope antenna,wave guideand
for conditionand securityof mounting.
receiver/transmitter
(11) Inspectflap amplifierfor damageand security.
(12) Removeaccesspanels withinthe nosebaggagecompartment. Inspectavionicsplugs,
harnessand connectionsfor security,corrosionand condition.
(13) Inspectbulkheads,stringersand skin for damage,conditionand corrosion.
(14) Inspectleft and rightpitot mastfor obstructions,damage,securityand operation.
(15) Checkradar,environmentalcontrolunit (ECU),batterycoolingair inletsand vents for
obstructions,damageand security.
(16) Inspect ECUram air and groundair checkvalvesfor damageand properoperation.
Check ECUgroundfan for damageand operation.
EFFECTIVITY:
040-999
5-20-00 Nov 1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Scheduled
Maintenance
(continued)
5. Event1 (continued)
(d) FuselageForward,Detailed(continued)
WARNING:DONOTPERMITOIL,GREASE
OROTHERPETROLEUM
PRODUCTS
TO COME
IN CONTACT
WITHANYLINESORFITTINGSUTILIZEDINTHEOXYGEN
SYSTEM.BESURESKINANDCLOTHING
AREFREEOFOIL,GREASEOR
OTHERPETROLEUM
PRODUCTS
BEFOREWORKING
ONANYCOMPONENT
OFTHEOXYGEN
SYSTEM.
NOTE: Dateof lasthydrostatic
test is stamped
on cylinder.
(17)Inspectrefrigeration
unitfordamage,securityandflexiblecouplingleakage.Inspect
waterseparatorcoalescent
bagfor dirt,washeach300hoursmaximum.InspectECU
overtemperature
andoverpressure
switchesforsecurityandleakageandwiringfor
damageandattachment.Inspectwaterasperatorplumbingfor blockage,leakageand
condition.
(18)Inspectoxygencylinder,regulatorandlinesfor securityandcondition.Check
connections
andlinesfor leaks.Checkcontrolforoperation.Checkrupturedisc
conditionandsystemfor properpressure.(Referto SpecialInspection
300& 3500
Hour.)
(19)Inspecthydraulic
powerpackfor leaks,securityandproperfluidlevel.
(20)Inspecthydraulic
powerpackflexiblecontrolcablesandlinefor damage,security,
operationandleaks.
(21)Inspectall hydrauliclinesfor leaksandsecurity.
(22)Drainandinspectstaticdrainpumps.
(23)Inspectlandingandtaxi lightsfor brokenlensesandsecurity.
(24)Checkelectricaloutsideairtemerature
probe(OAT)for corrosion,damage,conditionof
wiringandsecuremounting.
(25)Inspectexternalelectricalconnection
(GPU)andaccessdoorfor damageandsecurity.
(26)Inspectconditionof outerskin;checkfor looseor missingrivets,damageandcondition.
(27)LubricateperLubrication
Chart.(Referto 12-10-00)
(28)Reinstallaccessplates,panelsandcloseradomeandbaggagedoor.
(e) FuselageMain,Detailed(Referto 35-00-00and53-00-00)
(1) Removeinspection
plates,panelsandfloorpanels.
(2) Inspectexternalskinsfor condition,looseor missingrivets,damageandcorrosion.
(3) Inspectwindshield
andwindowsfor cracks,distortion,
leaksandsecurity.
(4) Checkbimetallicoutsideair temperature
probe(OAT)for corrosion,damageand
condition.
(5) Removeemergency
exitwindow;checkwindowandsealfor cracks,distortionandleaks.
Installwindowandcheckforsecurityof latchingmechanism.
(6) Inspectwindshield
wipersfor securityof mounting,conditionandoperation.(DoNot
Operateon DryWindshield)
(7) Inspectfuel,hydraulicandpressurization
linesfordamage,leaks,routingandsecurity.
(8) Inspectall controlcablesandpulleysfordamage,full travel,alignment,clearance
and
propertension.
(9) Inspectantennamountsandconnections
for tightness,securityandcorrosion.
(10)Inspectall electricalwiringfordamage,routing,attachment
andsecurity.
EFFECTIVITY:
PAGE140
Nov1/90 5-20-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance
(continued)
5. Event1 (continued)
(e) Fuselage
Main,Detailed(continued)
(11) Inspectautopilotpitchandrollservosfor security.Inspectconditionof bridlecables
andwiring.(Referto 22-10-00)
(12) Inspectmaincabindoorandif installed,inspectcargodoorfor damage,conditionof
doorseal,properrig andoperation
of latchingmechanisms.Checkdoorajarswitches
for mechanical
operation;anaudibleclickshouldbe heardwhenswitchopensor
closes.
(13) Inspectdoorsnubberfor leaksandattachment.
(14) Inspectdoorrestraintcablesfor condition
andsecurityof attachment.
(15) Inspectdeicevalvesandpneumatic
systemregulators
for security,damageandleaks;
electricalconnections
for securityandcondition.
(16) Inspectpneumatic
lines,flexiblelinesandcomponents
for leaks,cuts,abrasions
and
secureconnections.Replaceuponconditionorper SpecialInspection.
(17) Checkupholstery
for damage.
(18) Checkseatsandseatbeltsfor securityof bracketsandbolts.
(19) Checkall lightsandair ventsfor damageandoperation.
WARNING:BESURESKINANDCLOTHING
AREFREEOFGREASE,
OILOR
OTHERPETROLEUM
PRODUCTS
BEFORECHECKING
OR
PERFORMING
MAINTENANCE
ONANYCOMPONENT
OFTHE
OXYGENSYSTEM.
(20) Inspectoxygenoutletsandmasksfordefects,corrosionandattachment
of masksto
outlets.
and
(21)Checkoperationof oxygensystem.(Referto 300/3500HourSpecialInspection
Pilot'sOperatingHandbook)
(22)Checkportablefireextinguisher
forchargeandservicetime. (Referto b0).
(23) If applicable,
checkservicetimeandconditionof eachlifepreserver.Checkthatlocate
lightis securelyattachedandoperative.
(24)Checkoutflowandoutflow/safety
coverscreenfor obstructions.Checkoutflowand
safetyvalvepopitfor cleanliness.(Referto 21-10-00)
(25)Checkall electricoptionsfor security,
damage,wiringintegrityandcondition.
(26)Checkreturnairfiltersin airboxfor cleanliness.
Cleanor replaceas required.
(27)Checkrecirculation
doorsconditionandfreedomof movement.Checkactuatorcables
andsolenoidsfor operation.
(28)Checkcabinventfansforoperation,
securityandattachment.
(29)Checkovertemperature
andrecirculation
switchesfor securityandwiringattachment.
(30)Lubricateper Lubrication
Chart.(Referto 12-10-00)
(31) Replaceinspection
plates,panelsandfloorpanels.
(f) CabinandCockpit,Detailed
NOTE:SomeitemsincludedunderFuselage
Main,Detailedare alsorequiredfor Cabin
andCockpit,Detailed.
plates,panelsandfloorpanels.
(1) Removeinspection
(2) Inspectcabincockpitentranceanddividersfordamage.
for damage.
(3) Inspectupholstery
beltsfor damage,securityandoperation.
(4) Inspectpilotandcopilotseats/seat
EFFECTIVITY:
040-999
15
5-20-00
5-20-00 PAGE
Nov 1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event 1 (continued)
(f) Cabinand Cockpit,Detailed(continued)
(5) Inspecttrim operationand indicatorsfor full travel, binding,damageand correct control
deflection.
(6) Checkrudderpedalsfor travel, bindingand security. Inspectbrake cylindersfor leaks
andoperation.
(7) Inspectparkingbrake and parkingbrakecable for condition,securityand operation.
(8) Inspectcontrolwheels,column, pulleysand cablesfor damageoperationand full travel.
(9) Inspectinstrumentsand attachmentsfor security,damage,propermarkingsand
placards.(Referto Pilot'sOperatingHandbook).
(10) Inspectcompasscorrectioncard for correctdata. Calibrateas required.
(11) Inspectavionicsand electricalsystemsfor conditionand securityof switchesand
knobs.
(12) Inspectcircuitbreakersfor conditionand securityof installation.
(13) Performmain bustie circuitbreakerand distributiondiodecheck. (Referto 24-60-00)
(14) Checkcabin pressurecontrollerfilter and instrumentair filter for contaminationand
damage.
(15) Inspectpitotand staticlines for conditionand security.
(16) Checkthat altimetersand transponderarein accordancewith latest revisionof AC
43.13-1and certifiedin accordancewith FAR23 to complywith FAR91.171 and
91.172.
(17) Check securityand operationof crossfeedvalve handles.
(18) Check securityand operationof emergencyshutoffvalve handles.
(19) Checkoperationof recirculationblowers.
(20) Inspectconditionand operationof heaterducts and air conditioningductsand outlets.
WARNING: BESURE SKINAND CLOTHINGARE FREEOF GREASE,OILOR
OTHERPETROLEUMPRODUCTSBEFORECHECKINGOR
PERFORMINGMAINTENANCEON ANY COMPONENTOF THE
OXYGENSYSTEM.
(21) Inspectoxygenoutletsfor defectsand corrosion.
NOTE: Operationof oxygenshutoffvalvewill deploy all oxygenmasks.
(23) Inspectand checkoperationof passengeroxygen shutoffvalve.
(24) Inspectoxygenmasksfor properattachmentand condition.
(25) Testcockpitvoicerecorder,if installed.
(26) Lubricateper LubricationChart. (Referto 12-10-00)
(27) Installinspectionplates,panelsand floor panels. Inspectpneumaticlines,flexiblelines
and componentsfor overall conditionand operation. Replaceon condition. (Referto 550-00)
(28) Checkportablefire extinguishersfor properservice,conditionand inspectiondate.
(Referto 26-10-00)
(29) If applicable,checkthe servicetime and conditionof each life preserver. Checkthat
the locatelight is securelyattachedand operable.
(30) Turn battery masterswitcheson. Inspectand checkoperationof all electrically
operatedinstruments.Overhaulor replaceas required.
(31) Check all instrument,cockpit,navigation,strobe and recognitionlightingfor operation.
(32) Check pilot'sstormwindowfor condition,operationand properseal. (If installed)
EFFECTIVITY:
040-999
PAGE 16
5-20-00
Nov1/90 5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event1 (continued)
(f) CabinandCockpit,Detailed(continued)
(33) Performoperationaltest of microphonesand cabin speakers.
(34) Checkglareshieldand eyebrowpanelsfor condition,cracksand security.
(g) FuselageAft and Empennage,Detailed(Referto 27-00-00)
(1) Removeall inspectionplates,accesspanelsand fairings.
(2) Inspectconditionof skin, interiorbulkheads,formers and stringersfor damage,looseor
missingrivetsand corrosion.
(3) Inspectstaticdischargewicksfor securityof attachmentand condition.
(4) Inspectverticalfin and ruddersurfacesfor securityof attachment,damageand
corrosion.
(5) Inspectrudderandtab hinges,bolts and attachmentsfor damage,operation,wear and
security.
(6) Inspectrudderand ruddertrim mechanismfor operationand full travel.
(7) Inspectruddercove seal for damageand securityof attachment.
(8) Inspecthorizontalstabilizerand elevatorsurfacesfor damage,looseor missingrivets
and corrosion.
(9) Inspectlightningdiverteranddiverterstripson bulletassemblyfor damageand
security.
(10) Inspecttail navigationlightsand strobe lightsfor broken lensesand security.
(11) Inspectelevatorand tab hinges,horns and attachmentsfor damage,securityand
operation.
(12) Inspecthorizontalstabilizerattachmentsfor security,damage,cracks and corrosion.
(13) Inspectelevatorand tab hingebolts and bearingsfor securityof attachments,damage,
wear and corrosion.
(14) Inspectelevatortrim mechanismfor operationand full travel.
(15) Inspectrudder,elevatorandtrim mechanismcables,tumbuckles,guides,torquetubes
and pulleysfor safety,cable tension,damage,corrosion,operationand condition.
(16) Inspectelevatordown springfor damage,corrosion,attachmentand tension.
(17) Inspectrudderand elevatorbalanceweightsfor security.
(18) Inspectautopilotcomponentsfor condition,securityof mounting,conditionof
shockmountsand evidenceof moistureor corrosionin plugs.
(19) Inspectautopilotservosbridlecablesfor condition,securityand tension.
(20) InspectELTbatteryfor replacementdate and unitfor corrosion,operationand damage.
(21) InspectELTantennafor attachment,securityand for properconnectionto ELTunit.
(Referto latest PiperServiceLetter935.)
(22) InspectVOR antennaand connectionsfor corrosion,securityof mountingand
condition.
(23) Inspectantennamounting(s)for security,corrosionand condition.
(24) Inspectpneumaticdeice bootsand plumbingfor condition,leaksand damage. Replace
upon condition. (Referto 5-50-00)
(25) Inspectstatic portsand lines for obstructions,leaksand condition.
EFFECTIVITY:
040-999
17
PAGE
5-20-00
5-20-00
Nov 1/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
5. Event1 (continued)
(g) FuselageAft and Empennage,Detailed(continued)
(26) Checkoutflowand safetyvalvestaticopeningsfor obstructions.
CAUTION: TO PREVENT WATER DAMAGE TO VENTRAL FIN KEVLAR MATERIAL,
THE EDGE OF EACH VENTRAL FIN DRAIN HOLE IS SEALED WITH
EPOXY RESIN. IF NECESSARY TO OPEN VENTRAL FIN DRAIN
HOLES, CARE SHOULD BE TAKEN NOT TO BREAK SEAL. IF SEAL IS
BROKEN, REFER TO 51-10-00 FOR PROCEDURE UTILIZED TO
APPLY EPOXY RESIN.
(27) Checkthat fuselage, elevatortrim drum and ventralfin drain holesare open and free of
foreign matter(See latest PiperServiceBulletinNo. 857).
(28) Lubricateper LubricationChart. (Refer 12-10-00)
(29) Installinspectionplates and accesspanels.
(h) RightWing, Routine(Referto 57-00-00)
(1) Checksurfaces,skins,tip tank andfairings for damage,condition,loose or missing
rivets.
(2) Inspectaileronand trim tab attachmentsfor security,damageand operation.
(3) Inspectaileronbalanceweightfor damageand security.
(4) Inspectflap and flap tracks for securityof attachment,damage,conditionand corrosion.
(5) Checkthat fuel tanks containcorrecttype fuel. Check fuel caps and anti-syphonvalves
for seal,damageand operation. Inspectconditionof fuel type and fuel capacity
placards. Replaceif illegible.
(6) Inspectpneumaticdeice bootsfor condition,leaksand operation.(Refer to 30-10-00)
(7) Inspectlift transducerfor securityof attachment,springcenteringof switch blade and
corrosion. Check heat elementfor operation.
(8) Inspectwing tip navigation,strobeand wing inspectionlightsfor broken lenses,wiring
and security.
(9) Lubricateper LubricationChart 12-20-00.
EFFECTIVITY:
040-999
PAGE1
8
Nov1/90
5-20-00
5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
5. Event 1 (continued)
I
(i) LandingGear, Routine(Referto 32-00-00and latest PiperServiceBulletin822)
Nose Left Right
(1) Placeairplaneon jacks. Jack airplane. (Referto 7-10-00)
(2) Checkoleo struts for leaks,scoring,damage,cleanliness,proper extensionand
pressure.
(3) Inspecttires for cuts, unevenor excessivewear and slippage.
(4) Removewheels;clean, inspectand repackbearings.
(5) Cleanand inspectwheelsfor cracks,corrosionand brokenor loose bolts.
(6) Checktires for properpressure. (Referto 12-10-00)
(7) Checkbrakesand lines for damage,attachment,securityand wear limits.
(8) Checkgear legsand bracesfor security,damage,corrosionand condition.
(9) Inspect gear doors for securityof attachment,cracks, damage and corrosion.
(See 100 Hourand 1000HourSpecialInspections.)
(10) Inspectactuatingcylinders,lines and fittingsfor attachment,leaksand damage.
(11) Inspectall hydraulicand pneumaticlines for chafing.
(12) Inspect landing gear, emergency gear extension and pneumatic bottles for
securityof mountingand properpressure.
(13) Check emergencygear extensionpneumaticsystem lines, fittings and shuttle
valvesfor security,leakageanddamage.
(14) Inspectconditionof up and down lock hooks, springs and cables for damage,
binding, operationand corrosion. Inspect up and down lock actuating cables
antirotationclips.
(15) Inspectmaingear retractionarm for cracks,security,and damage.
(16) Inspectall wiringand wiringharnessfor condition,security,damage,chafing and
corrosion. Checkswitchesfor adjustment,securityand operation.
(17) Lubricateper LubricationChart. (Refer to 12-10-00)
WARNING: DO NOT REMOVEJACKS UNTILIT HAS BEEN DETERMINED
THATTHE LANDINGGEAR IS DOWNAND LOCKEDAND ANTIRETRACTIONSYSTEMHAS BEENCHECKED.
(18) Placeweightof aircrafton landinggear.(Do Not RemoveJacks.)
(19)Checkanti-retractionsystemfor properoperation.
(20) Ensureall gears are downand locked,then removejacks.
(j) Specialand GeneralSection
(1) Special Inspectionscompletedas required.(Referto 5-50-00).
(2) OperationalInspectionand run-upcompleted.(Referto 5-50-00).
(3) Aircraftcleanedand lubricatedafterwash(as required).
(4) All AirworthinessDirectives,ServiceBulletins,Letters and Instructionscompliedwith.
(5) Event Record,DiscrepancyRecord,ComplianceRecordand EquipmentChange
Recordscompleted.
EFFECTIVITY:
040-999
19
PAGE
5-20-00
5-20-00
Feb 1/98
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
5. Event 1 (continued)
(k) InspectionCompletedStatement
INSPECTION COMPLETED
I certify that this aircraft has been inspected in accordance with
PiperAircraft Corporation100 Hour ProgressiveInspectionEvent 1,
and is approved for return to service. Pertinent details of this
inspectionare on file at this facility underRepairOrder No.
Total Time:
Signed:
Date:
Repair Station No.:
EFFECTIVITY:
040-999
PAGE 20
Nov 1/90
5-20-00
5-20-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
5. Event1 (continued)
(I) InspectionDiscrepancySheet
AircraftTime:
Engine Time - Left:
EngineTime - Right:
Work Order No.:
Date:
Iem No.
Discrepancy
Corrective Action
Mechanic / Crew Chief Signature
EFFECTIVITY:
040-999
5-20-00
5-20-00
Nov1/90
Nov
1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event2
(a) Propellers,Detailed (Referto 61-10-00)
Left Right
(1) Removeand inspectspinnerfor cracks,corrosionand damage.
(2) Inspectbladesfor nicks,cracks,corrosionand evidenceof strikes.
(3) Check for greaseand oil leaks.
(4) Inspectbulkheadfor cracks,securityand corrosion.
(5) Inspect propeller mounting bolts for condition and proper safety. Check torque if
safety is broken.
(6) Inspecthub partsfor cracks,corrosionand security.
(7) Rotateblades and inspectfor tightness.
(8) Inspect beta feedbackring for runout (0.010 inch max.) and no metalto metal contact
with reverseleverand carbonblock holder.
(9) Inspectcarbon blockfor wear limit and freedomof movement.
(10) Inspect low pitch stop rods, return springs and beta feedback ring for damage,
corrosionand freedomof movement.
(11) Inspectconditionof propellerdeicerslip ring and brushblockor modularassembly.
(12) Inspectconditionof propellerdeiceboots and securityof attachment.
(13) Inspect propeller deice wiring and junction blocks for security, cracks, chafing and
damage.
(14) If installed,inspectconditionand securityof synchrophaserwiring.
(15) Lubricatepropellerper LubricationChart. (Referto 12-10-00)
(16) Installspinner.
(b) Engine(s),Detailed (Referto 71-00-00)
Left Right
NOTE: Referto Pratt& WhitneyPT6A-61MaintenanceManualP/N 3034342.
(1) Removeenginecowling.
(2) Removeupper and lowerfirewall accesscovers.
(3) Clean and inspect cowling and covers for cracks, distortion and loose or missing
fasteners.
(4) Inspectoil temperaturesenderunit for leaksand security.
(5) Inspectoil linesand fittingsfor leaks,security,chafing,dents,cracksand routing.
(6) Clean and inspectoil cooler for conditionand attachment.
CAUTION: REFERTO APPROPRIATEPRATT& WHITNEYMAINTENANCE
MANUAL,SERVICEBULLETINSAND5-50-00.
(7) Remove and inspect oil filter for damage and contamination Clean or replace as
required.
EFFECTIVITY:
040-999
PAGE
22
5-20-00
Nov1/90 5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(b) Engine(s),Detailed (continued)
Left Right
CAUTION: ALL ENGINECLEANINGPROCEDURESAND CLEANINGPRECAUTIONS
MUSTBEOBTAINEDFROMTHE APPROPRIATESECTIONSOF THE
PRATT& WHITNEYMAINTENANCEMANUAL( PT6A-61)P/N 3034342.
(8) Cleanexteriorof engine.(Referto Pratt& WhitneyMaintenanceManual)
(9) Inspectconditionof igniterplugs. (Referto Chapter74-10-00)
(10) Inspect ignition harnessand insulatorsfor high tension leakage, continuity,damage
and attachment.
(11) Inspectelectricalconnectionson ignitionexciterfor safety and security.
(12) Removeair inlet screen; inspectfirst stage compressorblades for ingestiondamage
and corrosion. Inspectscreenfor damageand cleanliness. Installscreen.
(13) Cleanand inspectfuel pump inletscreenfor foreign material. Replaceoutletfilter.
(14) Inspect gas generatorcase drain valves for securityand leaks. (Check after engine
run)
(15) Inspect magnetic chip detector and jump pins "A & B", operational check of
annunciator.
(16) Inspectconditionof inlet air ducts and ice protectionsystemfor operationand fit. (See
latest PiperServiceLetterNo. 983.)
(17) Inspect condition of actuators and linkage for ice protection system and oil cooler
doors.
]
[
]
D
CAUTION: WHEN ENGINEIS NOT RUNNING,ANY ATTEMPTTO MOVEPOWER
LEVERSINTOREVERSEPOSITION,WITHOUTDISCONNECTING
PROPELLERPUSH-PULLWIREROPECLEVISFROMPROPELLER
CONTROLCAM,WILLRESULTIN BENDINGOR KINKINGOF WIRE
ROPE.
a (18) Inspect power lever, start control, propellergovernor and propellerreversinglinkage
for condition,travel and operation.
D
] (19) Inspectgas generatorcasefor cracks,distortionand evidenceof overheating.
(20) Inspectexhauststacksand exhaustductsfor cracks,distortionand security.
(21) Inspectpropellergovernorfor leaksand security.
(22) Inspectpropellershaftfor oil leaks.
(23) Removedrain;clean and inspectfuel filter bowl and element. (Firewallmounted)
(24) Inspect all flexible lines (fuel, hydraulic,pneumaticand oil) for leaks, abrasions,cuts
and secure connections. Replaceupon conditionor as per Special Inspection. (See
latestPiperServiceBulletinNo. 822 and 5-50-00,3500 Hr.)
(25) Inspectfuel control,fuel pumps,fuel manifold,fuel flow transmitterand fuel pressure
transmitterfor leaks,securityand condition. Check wiring for securityand condition.
(See latestrevisionof PiperServiceBulletin957.)
(26) Replace hydraulic filter and inspect for contamination. If filter shows evidence of
contamination,inspectentirehydraulicsystem.
(27) Inspecthydraulicpump and hydrauliclines for securityand leaks.
(28) Inspectenginefiresealsfor cracks,damageand security.
EFFECTIVITY:
040-999
23
5-2000PAGE
5-20-00
Feb 1/98
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event 2 (continued)
(b) Engine(s),Detailed (continued)
Left Right
]
[
(29) Inspectfirewallsfor cracks,stressand condition.
(30) Inspectfirewallsealsfor condition.
(31) Inspectoil breathertube for obstructionand security.
(32) Inspectoil filler cap seal for damageand condition.
(33) Checkproperlockingfeatureof oil filler cap.
(34) Inspectoil pressuretransmitterfor securityand leaks. Checkwires for connectionand
damage.
(35) Inspect torque transmitter for leaks and security. Check wiring for damage and
security. Checkconditionof shock mounts.
(36) Inspectoil manifoldfor leaksand security.
(37) Inspect autoignitionswitch and manifoldfor security and condition. Check wiring for
damageand secureconnection.
(38) Inspect P3 air filter for contamination. Replaceif evidenceof contamination.(5-50-00,
1,000Hr.)
(39) Inspect fire extinguisherfor damage and security of wiring. Test fire extinguishing
systemfor propercylinderpressure(Referto 26-10-00)
(40) Inspectfire warningsensorsand wiringfor securityand condition.
(41) Inspectcompressorwash ringfor damageand security.
(42) Inspectcompressorwashvalveassemblyfor securityand operation.(if installed)
(43) Inspectenginemountsfor cracks,damageand loose mountingbolts.
(44) InspectrubberLord mountsfor deteriorationand condition.
(45) Checksecurity,wiringand operationof bladeangle sensoror beta lights,if installed.
(46) Checksecurity,wiringand operationof beta limiter system.
(47) Inspectfront and rear tachometergeneratorsfor securityand wiring.
(48) Inspect starter generator quick attachment device (QAD) ring and mount pad for
security,cracksand damage.
(49) Inspectconditionof starter-generatorcables.
(50) Inspectconditionof starter-generatorcoolingair ducts.
(51) Cleandual drivelube filter.
(52) Inspectgeneratorcontrolunits(GCU)for security,damageand wiringintegrity.
(53) Inspect bleed air lines,flexible lines and couplingsfor security,damageand leakage.
(Also see PiperServiceBulletinNo. 914).
(54) Check bleed air shutoffvalve and mixing regulatorfor security,damage,leakage and
correct operation. Checkwiringfor attachmentand damage.
(55) Inspect bleed air intercoolerfor cleannessand blockage. Check intercoolerinlet and
outletfor blockage,securityand leakageof duct couplings.
] (56) Inspect and check all enginewiring and ITT harness and connectorsfor securityand
condition.
(57) Lubricatepowerplant per LubricationChart. (Refer 12-10-00)
(58) Installupper and lowerfirewallaccesscovers.
(59) Installenginecowling.
EFFECTIVITY:
040-999
Nov 1/90
5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(c) RightWing, Detailed (Referto 57-00-00)
CAUTION: THE FLUX DETECTORCOVERON THE OUTBOARDWING SURFACEIS
SECUREDWITHBRASSSCREWS. ONLYBRASSSCREWSWILLBE
USEDWHEN INSTALLINGTHIS COVER.
(1) Removeinspectionplatesand panels.
(2) Inspectstaticdischargewicksfor securityof attachmentand condition.
] (3) Inspectflux detectorplug connectionsand wiringfor corrosion,securityand condition.
(4) Inspectwing and controlsurfaceskinsand fairings for cracks, looseor missingrivets
and damage.
(5) Inspectaileronfor securityof attachmentand freedomof movement.
(6) Inspectinterior structurefor cracks,looseand missingrivetsor concealeddamage.
(7) Inspectaileroncables,pulleysand bellcrankfor damage,full travel,alignment,
clearanceand propercabletension.
(8) Inspectaileronbalanceweightsand ailerongap seal for conditionand security.
(9) Inspectflaps, actuators,limit switches,wiringand potsfor corrosion,damage,operation
and full travel.
NOTE: An approachflap extensionof 10° will not activatethe Flap/LandingGear
WarningHorn sincethis flapsetting is intendedfor extendedapproachuse.
Normal landingsare madeusing 30 flaps and the Flap/LandingGear Warning
Horn will activateif the landinggear is not extendedwhen the flaps are
extendedmore than 10°.
(10) Inspectflaptracks and rollersfor condition. Checkrollersfor freedomof movement
and binding.
(11) Inspectflap track bolts and aileronhinge boltsfor wear,securityand corrosion.
(12) Inspectall controlsurfacebearingsfor attachment,wear and freedomof movement.
(13) Checkoperationof right fuel shutoffvalve and crossfeedvalve.
(14) Inspectwing attachmentboltsfor stripealignmentand bracketsfor cracksand
corrosion.
(15) Inspectenginemount bracketsfor conditionand security.
(16) Inspectbladderfuel cells for attachment,leaks and contamination.
(17) Inspectintegralfuel tanksfor leaks,corrosion,contaminationand damage.
(18) Inspectfuel lines for attachment,chafing and leaks.
(19) Checkfiller neck anti-siphonvalvesand fuel caps for damageand properseal. Inspect
quick drainsfor properoperation.
(20) Checkfuel tanks for correctoperatingfuel. Checkconditionof fueltype placards.
(21) Inspectfuel vents for obstructionsand damage. Checkvalvesfor operationand seal.
(22) Inspectfuel capacityprobesfor security,corrosionand leaks.
(23) Inspectelectricalwiring harnessand connectionsfor chafing,damageand security.
(24) Inspecthydrauliclinesfor leaks,damageor chafingand attachment.
(25) Inspectpneumaticlines,flexiblelines and componentsfor leaks,cuts, abrasionsand
secureconnections. Replaceupon conditionor per Special Inspection.
(26) Inspectbleed air warningduct switchesfor leaksand securityand wiringfor damage
and attachment. (Engine,intercoolerand wing root).
(27) Inspectbleed air duct couplingfor leakage,damageand security. Checkduct
insulationfor conditionand security. Checkductingfor securityand chafing.
(28) Inspectpneumaticdeicerbootsfor conditionand damage.
(29) Inspectlift transducerfor securityof attachment,springcenteringof switch bladeand
corrosion. check heat elementfor operation.
(30) Inspectwing tip tank attachmentbolts for security.
EFFECTIVITY:
040-999
25
5-20-00 PAGE
Nov 1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(c) RightWing, Detailed (continue)
(31) Inspectwing tip navigationand strobelightsfor brokenlenses,security,wiring and
attachment.
(32) Checkwing inspectionlight for brokenlenses,security,wiringand attachment.
(33) Inspectwing lockersfor condition,leaksand damage.
(34) Inspectwing lockerdoor for securityand damage.
1 (35) Checkwing lockerdoor cylinderand lockfor security,damageand operation.
(36) Inspectnacellefuel tank for condition,leaksand damage. Check conditionof fueltype
and capacityplacards. Replaceif illegible.
(37) Lubricateper LubricationChart. (Referto 12-10-00)
CAUTION: ONLYBRASSSCREWSARE TO BE USED FOR INSTALLINGFLUX
DETECTORACCESSDOOR.
(38) Installinspectionplatesand panels.
(d) LandingGear, Detailed (Referto 32-00-00and latest PiperServiceBulletinNo.822)
Nose Left Right
(1) Placeairplaneon jacks. Jack airplane. (Referto 7-10-00)
(2) Checkoleostrutsfor leaks,scoring,damage,cleanliness,properextensionand
pressure.
Inspecttires for cuts, unevenor excessivewear and slippage.
Removewheels;clean, inspectand repackbearings.
Cleanand inspectwheelsfor cracks,corrosionand broken or loosebolts.
Checktires for properpressure.
Clean and inspect gear legs, nose gear fork and axles for security, damage,
2(7)
cracks, nicks,corrosionand condition.
(8) Clean and inspectgear struts, attachments,side braces, retractionlinks/arms
and bolts for condition,damage,corrosionand security.
(9) Inspectactuatingcylinders,lines and fittingsfor attachment,leaksand damage.
(10) Inspectall hydraulicand pneumaticlines for chafing.
(11) Inspect emergencygear extensionpneumaticbottles for security of mounting
and properpressure.
(12) Checkemergencygear extensionpneumaticsystemlines,fittings,shuttlevalves
and linkagefor security,leakage,damageand proper adjustment.
(3)
(4)
(5)
(6)
O
WARNING: WIRES MUSTBE REMOVEDFROMSQUIB PRIORTO
CONTINUITYCHECK.
(13) Checkemergencyair bottlesquibwiring for continuity.
(14)Inspect condition of up and down lock hooks, springs and cables for damage,
binding, operationand corrosion. Inspect up and down lock actuating cables
antirotationclips.
(15) Inspectbrake housingsfor cracks,leaks,attachmentand damage.
(16) Inspect brake linings and discs for cracks, uneven wear, distortion and wear
limits.
(17)Inspectbrakehydrauliclinesfor security,chafing,damageand leaks.
(18)Inspectshimmydampenerfor security,damage,corrosionand leaks.
(19)Check nose gear steering and mechanism for wear, binding, freedom of
operationand full travel.
EFFECTIVITY:
040-999
PAGE26
Nov1/90 5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(d) LandingGear,Detailed (continued)
Nose Left Right
cracks,looseor missingrivets,condition,
forsecurity,
(20) Inspectgeardoorsandattachments
damage,properoperationandfit. (See100Hourand 1000HourSpecialInspections.)
(21) Inspect actuatingcylindersand lines for leaks, damage,corrosion,scoring and
security.
]
(22) Inspectall wiring and wiringharnessfor condition,security,damage,chafingand
corrosion. Checkswitchesfor adjustment,securityand operation.
(23) Checkgear retractionand extensionoperations.
(24) Lubricateper LubricationChart. (Referto 12-10-00).
WARNING: DO NOT REMOVEJACKS UNTILIT HAS BEENDETERMINED
THATTHE LANDINGGEAR IS DOWNAND LOCKEDAND ANTIRETRACTIONSYSTEMHAS BEENCHECKED.
(25) Placeweightof aircrafton landinggear. (Do Not RemoveJacks.)
(26) Check anti-retraction system for proper operation.
(27) Ensureall gearsare down and locked,then removejacks.
(28) Check wheel alignment.
(e) Left Wing, Routine (Referto 57-00-00)
(1) Checksurfaces,skins,tip tank and fairingsfor damage,condition,looseor missing
rivets.
(2) Inspectaileronand trim tab attachmentsfor security,damageand operation.
(3) Inspectaileronbalanceweightfor damageand security.
(4) Inspectflap and flap tracksfor securityof attachment,damage,conditionand corrosion.
(5) Checkthat fuel tanks containcorrecttype fuel. Checkfuel caps and anti-syphonvalves
for seal, damageand operation. Inspectconditionof fuel type and fuel capacity
placards. Replaceif illegible.
(6) Inspectpneumaticdeice bootsfor condition,leaksand operation.(Refer to 30-10-00).
(7) Inspect lift transducerfor securityof attachment,springcenteringof switch bladeand
corrosion. Checkheat elementfor operation.
(8) Inspectwing tip navigation,strobeand wing inspectionlightsfor broken lenses,wiring
and security.
(9) Lubricateper LubricationChart. (Referto 12-10-00)
(f) FuselageForward,Routine (Referto 53-00-00)
(1) Inspectbaggagedoor surface,door latchmechanism,door ajar switches,lightswitches
and door seal for damage,conditionand operation.
(2) Check radomefor condition,securityand latchingmechanismfor operation.
(3) Check batteryand batterycase for damageand corrosion. Checkbattery contactors,
cables,fuses, solenoidsand wiringfor condition,corrosion,securityand damage.
(4) Check avionicsinstallationfor securityand condition.
(5) If applicable,checkelectricaloutsideair temperatureprobe for corrosion,damageand
securemounting. Inspectconditionand securityof wiring.
EFFECTIVITY:
040-999
5-20-00 PAGE
27
Feb 1/98
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
6. Event 2 (continued)
(f) FuselageForward,Routine (continued)
(6) Checkbrake reservoirand hydraulicpowerpackfor leaks,condition,damageand fluid
level. Serviceas required.
(7) Inspectsurfaces,skins and panelsfor looseor missingrivets,conditionand damage.
(8) Lubricateper LubricationChart. (Referto 12-10-00)
(g) FuselageMain, Routine (Referto 53-00-00)
(1) Inspectexternalskins and fairingsfor missingrivets,damage,conditionand corrosion.
(2) Checkall windowsfor cracks,distortionand condition.
(3) Inspectcabin entrancedoor and emergencyexit for damage,conditionand operation.
If applicable,inspectcargodoor for damage,conditionand operation.
] (4) Checkbimetallicoutside air temperatureprobe (OAT)for corrosion,damageand
securemounting.
(5) Inspectstrobe lightsfor broken lensesand security.
(6) Checkupholsteryfor damageand seatsfor operation,conditionand damage.
(7) Checkseat beltsfor condition,securityand operation.
WARNING: BE SURE SKIN AND CLOTHING ARE FREE OF GREASE, OIL,
GASOLINE OR OTHER PETROLEUM PRODUCTS BEFORE
CHECKING OR PERFORMING MAINTENANCE ON ANY COMPONENT
OF THE OXYGEN SYSTEM.
] (8) Check oxygen masks for condition and damage, that masks are properly connected to
outlets.
(9) Check outflow and safety valve screen for damage and obstruction.
(10)Check cabinetry, consoles and dividers for damage and security.
] (11) Check all lights and air vents for damage and operation.
(12) Lubricate per Lubrication Chart. (Refer to 12-10-00)
(h) Cabin and Cockpit,Routine
(1) Inspectcockpitseats, seatbelts and shoulderharness,upholsteryand curtainsfor
tears, damageand operation.
(2) Inspectinstruments,instrumentpaneland circuitbreakersfor damage,conditionand
operation.
(3) Inspectcockpit,navigation,strobeand recognitionlightingfor damage,corrosionand
operation.
(4) Testcockpitvoice recorder,if installed.(Referto 23-70-00)
] (5) Performmainbus tie circuitbreakerand distributiondiodescheck. (Referto 24-60-00)
WARNING: BE SURE SKIN AND CLOTHING ARE FREE OF GREASE, OIL,
GASOLINE OR OTHER PETROLEUM PRODUCTS BEFORE
CHECKING OR PERFORMING MAINTENANCE ON ANY COMPONENT
OF THE OXYGEN SYSTEM.
(6.) Check oxygenmasksfor damage,conditionand properattachmentto outlets.
NOTE: Operationof oxygenshutoffvalvewill deploy all oxygenmasks.
EFFECTIVITY:
040-999
Nov 1/90
5-20-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(h) Cabinand Cockpit,Routine (continued)
(7) Checkrudderpedals,controlcolumnand controlwheelfor damageand operation.
(8) Lubricateper LubricationChart. (Referto 12-10-00)
(i) FuselageAft and Empennage,Routine (Referto 27-00-00)
(1) Inspectskins,fairings,verticalfin, rudder,horizontalstabilizer,elevatorand tabsfor
damage,loose or missingrivets,corrosionand condition.
CAUTION: TO PREVENT WATER DAMAGE TO VENTRAL FIN KEVLAR MATERIAL,
THE EDGE OF EACH VENTRAL FIN DRAIN HOLE IS SEALED WITH
EPOXY RESIN. IF NECESSARY TO OPEN VENTRAL FIN DRAIN
HOLES, CARE SHOULD BE TAKEN NOT TO BREAK SEAL. IF SEAL IS
BROKEN, REFER TO CHAPTER 51-10-00 FOR PROCEDURE
UTILIZED TO APPLY EPOXY RESIN.
(2) Checkventralfin drain holesare open and free of foreign matter. (See latestPiper
ServiceBulletin857)
(3) Inspectrudder,ruddertab, elevator,elevatortabs, hinges,bolts and attachmentsfor
damage,wear,securityand operation.
(4) Inspectpneumaticdeice bootsfor damage,securityand condition.
(5) Check antennasfor securityand condition.
(6) Inspectstatic portsfor obstructionsand condition.
(7) Inspecttail navigationlights,strobe lightsand logo lightsfor broken lenses,corrosion
and security.
(8) Lubricateper LubricationChart. (Referto 12-10-00)
(9) Installinspectionplates and accesspanels.
(j) Specialand GeneralSection
(1) SpecialInspectionscompleteas required. (Referto 5-50-00).
(2) OperationalInspectionand run-upcompleted. (Referto 5-50-00).
(3) Aircraftcleanedand lubricatedafterwash.(As Required).
(4) All AirworthinessDirectives,ServiceBulletins,Letters and Instructionscompliedwith.
(5) Event Record,DiscrepancyRecord,ComplianceRecordand EquipmentChange
Recordscompleted.
EFFECTIVITY:
040-999
190
5-20-00 Nov
NOV1/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(k) InspectionCompletedStatement
INSPECTION COMPLETED
I certify that this aircraft has been inspected in accordance with
PiperAircraftCorporation100 Hour ProgressiveInspectionEvent2,
and is approved for return to service. Pertinent details of this
inspectionare on file at this facility under RepairOrderNo.
TotalTime:
Signed:
PAGE 30
Nov 1/90
Date:
RepairStation No.:
EFFECTIVITY:
040-999
5-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
6. Event2 (continued)
(I) InspectionDiscrepancySheet
EngineTime- Left:
AircraftTime:
EngineTime- Right:
Work Order No.:
Date:
Item No.
EFFECTIVITY:
040-999
Discrepancy
Corrective Action
Mechanic / Crew Chief Signature
31
e00PAGE Nov 1/90
5-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance
(continued)
7. Forms
(a) Event InspectionRecordand Sign OffSheet
NOTES:
(1) Proper inspection proceduresare the responsibilityof the individuals performingthe
inspectionand mustbe made in accordancewith all applicablecurrentFederalAviation
Regulationsand PiperMaintenanceManualsand Publications.
(2) Workorder columnis applicableonly to FAAapprovedrepair stations.
(3) Alwayscheckand useonly current information.
(4) The signatures signify that this aircraft has been thoroughly inspected and found
airworthy in accordance with all current FAR's, Piper Maintenance Manuals,
Publications,in addition ServiceBulletins and MandatoryService Letters have been
compliedwith. The signaturesare verificationthat the appropriateentries have been
made in the Aircraft and Engine Logbooks, Event Inspection Record, Discrepancy
Record, Publication Record, Equipment Change Record and FAA Airworthiness
Recordsectionsof this manual.
EVENTNo.
INSP
1
2
1
2
1
100
A/C TIME
DATE
W.O.No.
SIGNATURE- CERTIFICATENo.
200
300
400
0
500
600
700
800
2
1
2
1
900
2
1000
1
1100
2
1200
1300
1400
1500
1
2
1
2
1
1600
1700
2
1800
1
1900
2
2000
0
EFFECTIVITY:
PAGE
1/90
32ov52000
Nov 1/90
5 2000U
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
7. Forms(continued)
(b) ProgressiveCycle InspectionRecordand SignoffSheet
CurrentFAA Pilot'sOperatingHandbookis in the aircraft.
Appropriateentriesmade in the Aircraftand Enginelogbooks.
Registrationcertificateis in the aircraftand properlydisplayed.
Airworthinesscertificatein aircraftand properlydisplayed.
RadioStation FCCLicensesis in the aircraft and properlydisplayed.
Aircraft EquipmentList, Weightand Balanceand FAA Form 337 (if applicable)are in
the aircraftand in properorder.
(7) All ServiceBulletinsand mandatoryServiceLetters havebeen compliedwith.
(8) ApplicableFAAAirworthinessDirectivesare compliedwith.
(9) PiperProgressiveInspectionRecordsin order and properlysigned off.
(10) Outstandingconditionshavebeen correctedas listedon conditionrecord.
(1)
(2)
(3)
(4)
(5)
(6)
CYCLENo.
DATE
TACH
REMARKS
SIGNATURE - CERTIFICATE No.
EFFECTIVITY:
040-999
5-20-00 Nov 1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
7. Forms (continued)
(c) Nicad BatteryForm
NICKEL-CADMIUM BATTERY SERVICE RECORD
BATTERYTYPE
RATEDCAPACTY(C):
SERIAL NO.
MINIMUMALLOWABLECELL
INSTALLATION
DATE
AMPS
AIRCRAFT
Ah
CHARGERATES
CAPACITY(0.85x C):
Ah
C/2
ALLOWABLE WATER CONSUMPTION
Cm
3
AMPS
C/10
SERVICEIN ACCORDANCEWITHAIRFRAMESERVICE/MAINTENANCE
MANUAL
ConditionFromArcraft
Removal
Dates
Reason
for
Hours
Since
Removal
Serviced
Visual
Chargeand WaterConsumptionData
CellEndof
DistilledWater
Minimum
ChargeVoltage
Addedto Cells
Cell
Banery
Capacty Capacity
(CA)
Max/Cell MinJCell AVG MaxJCell Min/Cell
(CB)
AVG
No.
No.
No.
Cell
to
Case
Insul.
Remarks
No.
NOTE:
Numbercallsby startingwith the cell connected
to the negativebatteryterminal andproceeding
sequentially
as the cellsare connectedin series
to the positivebatery terminal.
PAGE34 5-20-00
Nov 1/90
If the quantityofwateraddedduringmaintenance
is greaterthanthat indicated.
it isrecommended
that a checkbe madeof chargevoltagewith reference
to
temperature.If necessary,
shortenintervalbetweenmaintenance.
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Scheduled Maintenance (continued)
7.
Forms (continued)
(d) Discrepancy Record Form
DISCREPANCY
A/C
HOURS
DISCREPANCY RECORD
SIGNATURE DATE CORRECTIVE W.O.
No.
ACTION
SIGNATUREAND
CERTIFICATENo.
DATE
EFFECTIVITY:
040-999
35
PAGE
5-20-00 Nov
1/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
7. Forms(continued)
(e) ServicePublicationComplianceRecord
SERVICE PUBLICATION COMPLIANCE RECORD
MANUFACTURER PUBUCATION NUMBER COMPLIANCE
DATE A/C HOURS
PAGE36 5
20 00
Nov 1/90 5-20-00
W.O.No.
SIGNATURE
AND
CERTIFICATE
No.
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ScheduledMaintenance(continued)
7. Forms(continued)
(f) EquipmentChange RecordForm
EQUIPMENT CHANGE RECORD
DATE
A/C
HOURS
REMOVEDPART No.
SERIALNo. INSTALLPARTNo.
SERIALNo.
SIGNATUREAND
CERTIFICATENo.
EFFECTIVITY:
040-999
37
5-20-00 PAGE
Nov 1/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
7. Forms (continued)
(g) FAA AirworthinessDirectivesComplianceRecordForm
FAA AIRWORTHINESSDIRECTIVESCOMPLIANCERECORD
A.D.
A/C
METHODOF ONE
A.D
NUMBER DATE HOURS COMPLIANCETIME
RECUR-RING
HOURS
NEXTDUE WORK SIGNATURE
AND
DATEOR ORDER
CERTIFICATE
No.
No.
EFFECTIVITY:
040-999
PAGE38
Nov 1/90
20
00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
8. OperationalInspectionsand Checks
(a) 100 Hour
(1) Operationalgroundfunctionaltest of ECS. (Referto 21-00-00)
EFFECTIVITY:
040-999
5-20-00
v 1/90
1/90
Nov
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ScheduledMaintenance(continued)
8. OperationalInspectionsand Checks
CHART1
INSPECTIONINTERVALVARIANCE
INTERVALVARIANCE
200 HOUR
TRAININGFACILITY
AIRPLANES/N'S
All NipponAirways
ANAM
048, 049, 050, 055, 058
NOTE: The trainingfacilities listedin Chart 1 havesubmittedinformationbasedon experiencewhichallows
the original inspectionintervalto be varied. Any reductionin usage or change in experiencewhich
will reduce inspectioninterval time will require returningto the original inspectioninterval until new
information has been submittedto Piper and the applicableaviation authority (FAA, JCAB, etc.).
Airplane serial numbers listed in Chart 1 which no longer operate under the listed trainingfacility
mustalso revertto the originalstandardinterval.
EFFECTIVITY:
PAGE40 5-24-00
Feb1/98
5-20-00
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. SpecialInspections
1. General
Specialinspectionsare performedat the appropriatetimes indicatedin conjunctionwith the normal
event inspection.They are also repeatedat eachspecifiedinterval,for example: at 100 hours
performthe 100 hour specialinspection,at 200 hours performboth the 100 hour and 200 hour
specialinspection,etc.
2. EngineOil
Regularoil changesare not necessary.Oil contaminationfrom extraneousmatter,such as
hydraulicfluid, sand,etc.,will requirethat the oil systemto be drained,flushed and refilledwith oil
of an approvedbrand. Shoulda switchto anotherbrand be made or shouldoils of differentbrand
be mixed,drain and flush the completeoil system. Refill in accordancewith Pratt & Whitney
MaintenanceManual(PT6A-61P/N 3034342). Any programestablishedto monitoroil quality
should be done in collaborationwith the oil supplieror manufacturer.Referto latest Pratt &
WhitneyCanadaServiceBulletin(PT6A-61)No. 13001for additionalinstructions.
3. 100 Hour
(a) NICADBattery
(1) Regulardeep cyclesare not necessary.electrolytelevel adjustmentswill dependupon
operatingconditions. Adjustlevel in accordancewith SAFT MaintenanceManual,P/N:
DC-3-01-78-3176-5A>
NOTE: A batterylog is providedfor recordingbattery condition.
(b) FuelNozzles
Left Right
(1) At first 100 hoursafter receiptof newaircraft and newor overhauledenginesa flow
check of the fuel nozzlesis recommended.After this first check refer to the 300 hour
SpecialInspection.
(c) FlapTransmission(See 500 hour SpecialInspection.)
(d) Engines(PT6A)
Left Right
(1) At first 100hours after receiptof new aircraftand new or overhauledengines,retorque
enginemountbolts (F.S.106.00)is recommended.After this first checkrefer to the 300
hour SpecialInspection.
(e) LandingGear
Nose Left Right
(1) Inspectmaingear retractionarm. (Referto SpecialInspection,700 and 2,800
Houritems.)
(2) Inspectmainlandinggear inboarddoor hingesfor cracks,with a 10X magnifying
glass.
(f) Starter Generator
(1) Inspect starter generator brushes and commutator for wear, condition and security.
4. 300 Hour
(a) Fuel Nozzles
(1) Inspectand checkfuel nozzlesfor flow, leaks,damageand condition. (Referto Pratt&
WhitneyMaintenanceManual(PT6A-61)P/N 3034342.
EFFECTIVITY:
040-999
5-50-00Feb
PAGE
1
1/98
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. SpecialInspections(continued)
4. 300 Hour (continued)
WARNING: DO NOT PERMIT OIL, GREASE OR OTHER PETROLEUM PRODUCTS TO COME
IN CONTACT WITH ANY LINES OR FITTINGS UTILIZED IN THE OXYGEN
SYSTEM. BE SURE SKIN AND CLOTHING ARE FREE OF OIL, GREASE,
GASOLINE OR OTHER PETROLEUM PRODUCTS BEFORE WORKING ON ANY
COMPONENTS OF THE OXYGEN SYSTEM.
(b) Oxygen System
(1) Inspect pressure regulator for condition and operation. Overhaul or replace after each
5 years in service.
(c) Environmental
(1) Clean water separator coalescer.
(d) Engines(PT6A)
Left Right
(1) Retorqueenginemount bolts.
5. 400 Hour
(a) Oil Drain
NOTE: Referto latest Pratt& WhitneyCanadaServiceBulletinNo. 13001 (PT6A-61).
Regularoil changesare not necessary.Operatorsshouldbe aware of the dangerof
oil contamination,whichwould requirethe oil systemto be drained,flushed and
replenishedwith new oil of an approvedbrand.
6. 500 Hour
(a) Static System
(1) Inspectstaticsystemdrain assemblyfor corrosion. (Referto 34-10-00)
(b) Environmental
(1) Inspectwater aspiratornozzleand hosefor condition.
(c) Oil System
(1) Inspectand clean engineoil scavengescreenon reductiongear box.
(d) FlapTransmission
(1) Inspectflap transmissionto determineuseful servicelife at first 500 hoursof operation
and every 100 hoursthereafter. (Referto 27-50-00)
7. 600 Hour
(a) Engine
Left Right
(1) Functionaltest of MagneticChip Detector. (referto Pratt& WhitneyManual3034342)
8. 700 Hour
(a) LandingGear
Nose Left Right
(1) Performfirst inspectionof the main landinggear retractionarm, P/N 42042-02,
then every 100 Hours. (SeeSpecialInspection2,800 Hour Item)
9. 1,000 Hour
(a) Engines(PT6A)
Left Right
(1) Overhaulor replacestarter generators.
(2) ReplacecompressorP3 air filter.
(3) Replaceenginemainoil filter element.
EFFECTIVITY:
040-999
Feb198 5-50-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Special Inspections(continued)
9. 1,000 Hour(continued)
(b) RudderPedals
(1) Inspectrudderpedaltorquetube bracketsfor cracks. Replaceupon condition. (Not
requiredif ServiceBulletinNo. 888 has been compliedwith.)
(c) FlexibleLines/Hoses
Toassurecontinuedhose integrity,it is suggestedthe followinginspectionproceduresbe
accomplishedafter each 1,000hoursof operation:
(1) Pressurizethe flexiblefuel lines with the fuel boostpump operating.
NOTE: Place the conditionleverstop positionprior to using the boostpump for fuel
systempressurization.
(2)
(3)
(4)
(5)
Examinethe hoseexteriorfor evidenceof leakageor wetness.
Inspectfor discolorationof the hoses and/orcolor bleachingof the end fittings.
Checkthe hosesfor evidenceof stiffness.
Replaceanyflexiblehoseswhicharefoundleakingorwhichshowa notableamountofstiffness.
Duringinstallationof flexible hoseassemblies,considerthe followingprecautions:
(1)
(2)
Assurethe hoseis not twisted. High pressuresappliedto a twistedhose can cause
failure of the hoseor looseningof the B-nut.
Do not attemptto straightena hose havinga bend in it as this could resultin damageto
the hose. Rubberhoseswill take a permanentset during extendedserviceperiods.
Care should also be taken during removaland reinstallationof such hosesto assure
they are not bent excessivelyand that theyare returnedto their original position.
(d) AcrylicWindows
(1) Performinspectionper Chapter56 of the MaintenanceManual(p/n 761-852).
(e) LandingGear
(1) Inspectmain landinggear inboarddoor hingesfor cracks, usinga dye penetrant
methodof inspection.
10. 1,200 Hour
(a) LandingGear
Nose Left Right
(1) Inspectnoseand mainlandinggear upperbearingblock retainingpins.
11. 1,400 Hours
(a) LandingGear
Nose Left Right
(1) Replace top cylinder bolts, P/N 401 195.
12. 1,500 Hour
(a) Engines(PT6A-61)
Left Right
(1) Perform Hot Section Inspection(HSI) in accordancewith the latest Pratt & Whitney
ServiceBulletinNo. 13303.
NOTE: All PT6Aenginesmaybeoperatedto a scheduled
hotsectioninspection
intervalor
alterantively,
the HSIfrequency
maybe basedon engineperformance
trend
monitoring.If trendmonitoring
is introduced
partwaythroughenginelife,compressor
washandhotsectioninspection
mustbe accomplished
to established
performance
baseline. Referto Pratt& WhitneyAgtoil23 fordetailson trendmonitoring.
EFFECTIVITY:
040-999
5-50-00
5-50-00
PAGE
Feb
1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. SpecialInspections (continued)
12. 1,500Hour (continued)
(b) LandingGear
Nose Left Right
(1) Replacemain landinggearbrace, pivotshaft assembly,P/N 43286-02.
13. 2,000 Hours or Two Years,(whichevercomesfirst)
(a) Fuel System
(1) Inspectoperationof fuel cell baffles,checkvalves,and fuel tanks. (Referto 28-10-00)
(2) Inspectinteriorof nacelleand tip tank for contamination,corrosion,and evidenceof
leaks.
14. 2,800 Hours
(a) LandingGear
Nose Left Right
(1) Replacemain gear retractionarm, P/N 42042-02.
(2) Replacemain gear link bolts, P/N 400 209.
15. 3,000 Hours
(a) Propellers
Left Right
(1) Overhaulpropellersevery 3,000 hours or five (5) years, whichevercomes first. Refer
to latest HartzellServiceLetterNo. 61.
(b) LandingGear
Nose Left Right
2. Replacepivotshaft, P/N 43286-02.
16. 3,000Hoursor at escalatedtimebetweenoverhaulsas authorizedby Pratt& WhitneyAircraftCanada
(a) Engines(PT6A-61)
Left Right
(1) Overhaulengines.
(2) Replacerubberenginemounts.
(3) Overhaulor replacefuel crossfeedand shutoffvalves.
NOTE: Referto the latest Pratt & WhitneyCanadaServiceBulletin13303 for criterion
for escalatingtime betweenoverhaulson PT6A-61engines.
17. 3,100 Hours
(a) LandingGear
Nose Left Right
(1) Replacemaingear link assembly,P/N85165-2Rev. B.
18. 4,500 Hour
(a) CockpitVoiceRecorder
(1) Replacecockpitvoice recorder (if installed).
(b) Engines(PT6A)
Left Right
(1) Overhaulor replaceoverspeed
governors.
EFFECTIVITY:
040-999
Feb 1/98
5-50-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Special Inspections(continued)
19. 7,500 Hour
(a) Engines(PT6A)
Left Right
(1) Replaceenginemount boltslocatedat the firewall (Station106.00).
20. Three (3) Years
(a) OxygenCylinderand Regulator
WARNING: DO NOT PERMITOIL, GREASEOR OTHER PETROLEUMPRODUCTS
TO COME IN CONTACT WITH ANY LINES OR FITTINGS USED IN
OXYGENSYSTEM.
WARNING: BE SURE SKIN AND CLOTHING ARE FREE OF GREASE, OIL,
GASOLINE OR OTHER PETROLEUM PRODUCTS BEFORE
PERFORMING
ANY WORKON THE OXYGENSYSTEM.
(1) Oxygen cylinders (DOT 3HT - Steel, thin wall): Hydrostatic test to 5/3 their working
pressure and retire from service at 24 years or 4,380 filling cycles (partial or full
pressurization) after date of manufacture, whichever comes first. Oxygen cylinders
(DOT E-8162 or E-8391 - composite): Hydrostatic test to 5/3 their working pressure
and retire from service at 15 years.
(2) Regulators on oxygen cylinders (DOT 3HT - Steel, thin wall) and on oxygen
cylinders (DOT E-8162 or E-8391 - composite): Perform a functional check, and
overhaul every 6 years.
21. Five (5) Years
(a) EngineFire ExtinguisherBottle
Left Right
(1) Hydrostatictest.
(2) Replacesquib.
(b) OxygenCylinderand Regulator
WARNING: DO NOT PERMITOIL, GREASEOR OTHER PETROLEUMPRODUCTSTO
COME IN CONTACTWITH ANY LINESOR FITTINGSUSED IN OXYGEN
SYSTEM.
WARNING: BE SURE SKINAND CLOTHINGARE FREE OF GREASE,OIL, GASOLINE
OR OTHER PETROLEUM PRODUCTS BEFORE PERFORMING ANY
WORKON THEOXYGENSYSTEM.
(1) Oxygen cylinders (DOT 3AA - Steel): Hydrostatic test to 5/3 their working pressure.
(2) Regulators on oxygen cylinders (DOT 3AA - Steel): Overhaul.
(c) LandingGear EmergencyExtensionNitrogenBottle
Nose Left Right
(1) Replace squib.
22. Seven(7) Years
Replaceflexible pneumaticlines in wings and fuselage.
(a)
(b)
Flexiblebleedair lines(hightemp)to be replacedat 1500hoursor 7 years,whichever
occursfirst (at pneumaticpressureregulatorand at pneumaticboot deice injectors).
23. Eight (8) Years
(a) Engines(PT6A)
Left Right
(1) Replaceall flexiblefuel, oil, pneumatic,and hydraulichoses,forwardof the firewall.
EFFECTIVITY:
040-999
5-50-00 Feb 1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Special Inspections(continued)
24. Ten(10) Years
(1) Pressurizeall fluid hosesto systempressuresand visuallycheckfor leaksor a notable
amountof stiffness. If foundfree of leaks,returnto servicefor an additional5 years
and pressurecheck per above. Recheckevery5 years after initialten year inspection.
Replacehoses as necessary.
NOTE: The hoses are to be checkedin the aircraftwithoutdisturbingthe hoses.
25. Twelve(12) Years
(a) Fire Extinguisher(PortableUnit)
(1) HydrostaticTest
B. Specialor UnusualConditionInspection
1. General
This sectioncontainsinspectionsrequiredin additionto the normal eventschedule;when the
aircraft is operatedcontinuouslyin adverseenvironmentalconditionsor subjectedto unusual
incidents.
The special inspectionsrequiredunderadverseenvironmentaloperatingconditionsshould be
repeatedin accordancewith the time intervalsspecified.
The unusual incidentinspectionis normallyaccomplishedon a one time basisassociatedwith
each condition.
Itemsindicatedin this procedureare guidelinesbasedon past operatingexperience. Each
operatorshould reviewhis own operatingconditionsand react accordinglyto keephis aircraft
airworthy.
NOTE: A log bookentry shouldbe made upon completionof these inspections.
2. Operationin High Dust or IndustrialPollution
Item
Inspection
InspectionInterval
P3 Air filter
Remove,inspectand clean.
100 Hours
Replaceas required.
Air Intake Screens
Cleanand inspectfor damage.
100 Hours
EngineOil Filter
Cleanand inspectcondition.
100 Hours
EngineOil
Drain and replace.
200 Hours
Compressor
Inspectand completeperformance
recoverywash.
Weeklyor more
often as required.
Propellers.
Referto latest HartzellServiceLetter.
1,500 Hours
Three (3) years.
Cowling.
Snugfit of firesealsand ice doors.
Water SeparatorCoalescer Remove,inspectand wash.
CabinEnvironmentaland
InstrumentAir Filters.
Inspectand replaceif necessary.
100 hours.
100 Hours or
as required.
100 Hours.
EFFECTIVITY:
040-999
Feb 1/98
5-50-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Specialor UnusualConditionInspection(continued)
2. Operationin High Dust or IndustrialPollution(continued)
Item
Inspection
Interval
Inspection
CAUTION: CHECKTHATLINESARE DISCONNECTEDFROMSYSTEM.
Pitot/Static
system
Checkfor obstruction.Reverse
flowto lines.
100 Hoursor
as required.
LandingGear Up and
Down LockAssemblies.
Clean,inspectand lubricate(Refertol2-10-00)
100 Hours.
LandingGear Actuators
and Oleos.
Inspectand clean.
100 Hours.
LandingGear wheel
Bearings.
Clean,inspectand repack.
100 Hours.
Windows.
Inspectfor cracks,erosion,visibility
and cleanliness.
Daily.
3. Operationin High Saltor HumidityEnvironment
Item
Inspection
nspectlonInterval
Fuselage,Empennage
and Wings.
Removefloor panels and exterior
accessplates; inspectfor corrosion.
200 Hours.
LandingGear.
Inspectfor corrosionand lubrication;
switchesand wiringfor condition.
200 Hours.
Engines.
Performdesalinizationand wash. (Referto
latestPratt & WhitneyField Note No. 956).
Instrumentsand Wiring.
Inspectfor properseal of cases and
corrosion.
100 Hours.
Interior.
Inspectupholstery,seat belts,seats and
rugs for corrosionand integrity.
100 Hours.
EFFECTIVITY:
040-999
DDailyor as required.
5-50-00 PAGE7
5-50-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Specialor UnusualConditionIrInspection(continued)
3. Soft or UnusualTerrain
Item
Inspection
Inspection
Interval
LandingGear.
Inspectfor cracks,attachment,
damage,cleanlinessand lubrication.
100Hours.
Wheels.
Inspectfor cracks,damage,chipped
rims;bearingsfordamage,corrosion
andlubrication.
100Hours.
Tires.
Inspectfor cuts,wear, inflationand
deterioration.
Daily.
WheelWells.
Inspectfor foreignmaterial,damage
and corrosion.
100Hours.
Brakes.
Inspectfor damage,foreign material,
cracksand overheating.
Daily.
Flaps,Lower Fuselage
and Wing.
Inspectfor damage,cracksand
corrosion.
100Hours.
Tip Tanks.
Inspectfor proper attachment.
100Hours.
4. Operationin ExtremeCold
Item
Hydraulic,Pneumatic
and Environmental.
Inspection
Checkall fittingsand attachmentsfor
securityand leaks.
Interval
Inspection
First100Hour,then
asrequired.
5. LightningStrike
Item
Inspection
Inspection
Interval
Overhaulpriorto
returnto service.
Propellers.
Referto latest HartzellServiceLetter..
EngineOil filter.
Inspectfor contamination.
Referto P& W
PT6A-61Engine
Maintenance
Manual.
Electricaland Avionics
Systems.
Inspectand checkfor high voltage
damageand operation.
Replaceandoverhaul
eachoccurrence.
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B. Specialor UnusualConditionInspection(continued)
5. LightningStrike(continued)
Item
Inspection
All exteriorsurfacesand
bearings.
Inspectfor burns, evidenceof arcing
and damageon surfacesand bearings.
StaticWicks.
Replace.
InspectionInterval
Replaceor repair
affectedareas each
occurrence.
Replaceeachoccurrence.
6. EngineOverspeed,Overtorqueor SuddenStopage
Item
Inspection
InspectionInterval
Engine.
See P&W PT6A-61
MaintenanceManual,Chapter72,
Table603.
Immediately
followingincident.
Propeller.
Propelleroverspeedof morethan 10%.
Referto latestHartzellServiceLetter.
Removeand
overhaulbefore
returnto service.
EngineMount and
Attachments.
Inspectfor distortionand
damage.
Replaceor repair
as required.
EngineOil Filter.
Inspectfor contamination.
Referto Pratt &
WhitneyPT6A-61
MaintenanceManual.
I
7. BatteryOvertemperature
Item
Inspection
Interval
Inspection
Battery.
Deepcyclebattery.
Batteryovertemperature
warningor indication.
Electrical.
Inspectwiringandchargingcircuit
for damage.Checkfor proper
opensandshorts.
Batteryovertemperature
warningor indication.
Checkcrossfeeddiodefor
opensand shorts.
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B. Specialor UnusualConditionInspection(continued)
8. SevereTurbulence,Hardor OverweightLanding
Item
Inspection
Inspection
Interval
CAUTION: MINOR SUPERFICIALDAMAGEMAY INDICATEA MORE SEVERE CONDITION
SOMEWHEREELSEIN THE STRUCTURE.
(a) Place aircraft in a normallevel attitude.
(b) Makea preliminaryinspectionof checkingalignmentand out-of-trackconditionof nacelles,
engines,wings, tail, tip tanks, landinggear and doors.
(c) FollowPiperand Pratt & WhitneyMaintenanceManualprocedures. If there are anyquestions
regardingrepairs or procedures,contactthe PiperAircraftCorporationServiceDepartment.
(d) Inspectthe followingitems closelyto determinethe extentof damage:
LandingGear Struts.
Cracks,signsof overstress
deformation,looseor damaged
trunnionmounts. Axles for cracks,
bendingor flat spots. Damagedoleos
and seals,hydraulicleaksand landing
gear alignment.
Hard or overweight
landing.
Wheels,Tires, Brakes.
Cracks,chips,looseor cracked
mountingbolts, alignmentof slippage
marks,sidewalldistress,hydraulicor
air leaks. Dyecheckor magnaflux
wheelsand bolts.
Hard or overweight
landing.
Wheel Wellsand Landing Buckling,cracks,overstress,wing skin
Gear attachpoints.
buckling,actuatorand side brace
damageand condition. Magnaflux
landing,gear attachmentand drag
link bolts.
Hardor overweight
landing.
Wings.
Hardor overweight
landing. Severe
turbulence.
Wing attachboltsfor slippage,damage
and overstress. Upperand lowerwing
skinsfor wrinkles,cracks,poppedor
loose rivets.
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B. Specialor UnusualConditionInspection(continued)
8. SevereTurbulence,Hardor OverweightLanding(continued)
I
Item
Inspection
InspectionInterval
Wings(continued)
Removeaccessplatesandinspectfor
internaldamageto ribs,stringersand
sparwebs;
fueltanks,linersandtip
tanksfor damageattachment
andleaks.
Hardor overweight
landing,severe
turbulence.
EnginesandNacelles.
Inspectengineoil filtersfor contamination. Hardor overweight
Accessories
for mountinganddamage.Gas landing,severe
generator
casefor buckling.Oil hydraulic
turbulence.
andairlinesfor attachment
andleaks.
Enginemountsfor distortionanddamage
to elastomeric
parts.Propeller
for evidence
of groundstrike(hardor overweight
landing).
Nacelles
for bucklingor fuelleaks.
Fuselage.
Looseor missingrivets,door alignment,
windowsand attachmentsfor overstress,
cracksor damage. Wing carrythrough
memberfor overstressdamage. Stringers,
bulkheads,keel beamsfor buckling,cracks
or damage. Forwardand aft pressurebulkheadsforbuckling,cracksand damage.
Avionics,instruments
and accessories
installationfor securityand operation.
Hardor overweight
landing,severe
turbulence.
Empennage.
Skinsfor bucklingwrinkles,looseor
missingrivets. Elevator,rudder,vertical
fins and horizontalstabilizerfor security
of attachmentand overstressof bolts.
Ribs,stringersfor buckling,cracks
and damage.
Hardor overweight
landing,severe
turbulence.
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PIPER AIRCRAFT
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MAINTENANCE MANUAL
CHAPTER 6
LIST OF EFFECTIVE PAGES
CHAPTER
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PAGE
6-EFFECTIVITY
6-CONTENTS
6-00-00
6-00-00
6-00-00
6-00-00
6-00-00
6-00-00
6-00-00
6-00-00
6-00-00
6-00-00
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1
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2
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4
5
6
7
8
9
10
DATE
CHAPTER
SECTION
PAGE
DATE
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
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10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 6 - DIMENSIONS AND AREAS
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
6-00-00
General
Station Reference
LeadingParticularsand PrincipalDimensions
Access and InspectionProvisions
1
2
5
6
EFFECTIVITY:
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CONTENTSJan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Dimensionsand Areas
A. General
The principalairplanedimensionsare shownin Figure 1 and the leadingparticulars/principal
dimensionsare listedin Chart 1. The airplaneserial numberis locatedon the ManufacturersAircraft
Association(MAA)plate,which is locatedbelowand to the right of the cabin door. The engineserial
numberplatesare locatedon the left rear side of the engineaccessorycase.
21' - 10"
-1
DIHEDRAL
43' - 4.7"
14'-9'
10'-7"
1'- 3'
ThreeView
Figure1
EFFECTIVITY:
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
B. Station References
To locate variousairplanecomponentsthat requireImaintenanceand servicing,a methodusingwing
fuselage station,wing station,buttock line and waterlinedesignationsis frequentlyused in this manual.
Fuselagestations(F.S.),buttocklines (B.L.),and waaterlines(W. L.) are referencepoints measuredby
inchesin the verticalor horizontaldirectionfrom a given referenceline. These points indicatestation
locationsof airplanestru ctural members.
FUSELAGE
STATIONS
STA
STA
STA
00
STA
Station References
Figure 2 (Sheet1 of 3)
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B. Station References(continued)
WINGSTATIONS
Station References
Figure 2 (Sheet2 of 3)
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MAINTENANCEMANUAL
B. Station References (continued)
HORIZONTALSTABILIZERSTATIONS
.98
0.00
58.77
33.30
100.09
O84.03
10.
38.5
NACELLESTATIONS
TA
STA
28 17
STA
66.11
105
Station References
Figure 2 (Sheet3 of 3)
Jan 10/9
6-00-00
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MAINTENANCEMANUAL
andPrincipalDimensions
C. LeadingParticulars
Chart 1
and PrincipalDimensions
LeadingParticulars
PA-42-720 (AT)
MODEL
ENGINE
Manufacturer
Model
EngineType
Flat RatedHorsepower(AirframeLimit)
Rated rpm
Dry Weight(lb.)
Fuel Specification
Oil Specification
Oil Tank Capacity
Pratt & Whitneyof Canada
PT6A-61
FreeTurbine
720
2000
428
Referto ServiceBulletinBook Section3026522-72-44,Service
BulletinNo. 13044 ( Latest
Revision)
Referto ServiceBulletinBook Section3026522-72-1,Service
BulletinNo. 13001( Latest
Revision)
2.3 Gal.
PROPELLER
Manufacturer
Type
Hub
Blade
Diameter(Inches)
OverspeedGovernorModel
Hartzell
ConstantSpeed- Featheringand
Reversing
HC-B3TN-3K
T10173AB-6Q
95
Woodward- P/N 210620
FUEL SYSTEM CAPACITY
TotalSystemCapacity(Gal.)
585
UnusableFuel(Gal.)
2
LANDING GEAR
Type
Shock Strut Design
Wheel, Nose
Wheel, Main
Brake
Tire, Main
Tire, Nose
TirePressures
EFFECTIVITY:
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Retractable- Hydraulic
CombinationAir and Oil
B.F.Goodrich3-1076
Cleveland40-140
B.F.Goodrich3-1392
B.F.Goodrich2-1435-2
6.50 x 10, 12 ply Rating,Type III,
ribbedthread, tubeless
17.50x 6.25 - 6, 8 ply rating,
Main- 100 psi
Nose- 70 psi
6-00-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
D. AccessandInspectionProvisions
Airplaneaccessandinspection
provisions
areshownin Figure's3 through5. Components
to be
servicedor inspected
througheachopeningareidentifiedin theillustration
byan assignedindex
referencenumber.All accessplatesandpanelsaresecuredby metalfastenersor screws.
NOTE: Beforeremovinganyaccessplatesorpanelsin thepressurized
portionof the fuselage,refer
to 51-00-00to determinethesealingrequirements.
Gainaccessto floorpanelattachment
screwsby removingseatsandcarpeting.To enteraft sectionof
fuselage,removeaccesspanelson eithersideof fuselage,aft of station332.00.
12
11
NACELLE
1.
2.
3.
4.
5.
6.
WASHRINGFITTING
AFT NACELLEPANEL- INSPECTION
NACELLEPANEL- INSPECTION
FORWARDNACELLEPANEL- INSPECTION
NACELLEFUEL SENSOR
INTERCOOLERAIR INLET
7.
8.
9.
10.
11.
12.
FUEL FILTERDRAINHANDLE
FUEL FILTERDRAIN
OIL FILL ANDDIPSTICK
ICEDEFLECTION
DOORCONTROLCONNECTONS
ICE DEFLECTIONDOOR
OIL COOLERDOOR
AccessPlatesandPanels- EngineNacelle
Figure3
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D. Access and Inspection Provisions (continued)
23
56 55
5451
5352
5250
28
25
48 47
4238
4645
31
30
4137
57
58
49
44
43
40 39
36
34
NOTE: Call outsfor Figure 4 can be
found on 6-00-00Page8.
AccessPlatesand Panels- Wings
Figure 4
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MAINTENANCEMANUAL
A. Accessand InspectionProvisions (continued)
Figure 4. (Wing) Call outs
13. FUELQUANTITYSENSOR- AFT INBOARDCELL
14. INSPECTIONAND ACCESSTO AFT CELL COVERAND MOUNTINGPLATE
15. INSPECTIONAND ACCESSTO MAIN CELL,COVERAND MOUNTINGPLATEAND SUBMERGED
FUELPUMP
16. FUELQUANTITYSENSOR- MAIN FUELCELL
17. MAIN CELL - ACCESS,INSPECTION,MOUNTING
18. MAIN CELL - ACCESS,INSPECTION,MOUNTING,AFT CELL CONNECTION
19. FUELQUANTITYSENSOR- MAIN CELL OUTBOARD
20. MAIN CELL - ACCESS,INSPECTION,NACELLEAND OUTBOARDCELL INTERCONNECT
21. INTERCONNECTOF MAIN AND NACELLEFUELCELLS
22. FUELVENT INTERCONNECT,FLOATVALVESYSTEM- FUEL VENT INTERCONNECT
23. FUELQUANTITYSENSOR- OUT BOARDFUELCELL
24. FUELCELL
25. FUELCELL
26. FUELQUANTITYSENSOR
27. INSPECTIONACCESS
28. FUELQUANTITYSENSOR
29. INSPECTIONACCESS
30. INSPECTIONACCESS
31. FLUXDETECTOR
32. FUELVENT LINE INTERCONNECT,
TIP TANKVENT FLOATVALVE
33. ACCESSTO FUELLINESAND TIP TANKSTRAINERSCREEN
34. STROBELIGHTTRANSFORMER
35. FUEL LINE SUPPORTAND FUELVENT CONNECTION
36. FLUX DETECTORCOMPENSATOR
37. FUEL LINE SUPPORT
38. FUEL LINEAND FUELVENT LINE
39. AILERONBELLCRANKAND CONNECTIONS
40. AILERONBELLCRANKAND CONNECTIONS- RIGHTWINGONLY
41. FUELVENT
42. FUELVENT CAN
43. AILERONCABLES
44. FUEL CELL VENT - RIGHTWINGONLY
45. FUEL CELL VENT
46. FUEL LINE AND FUEL VENT LINE
47. QUICKDEFUELDRAINACCESS
48. JACK PAD
49. INSPECTION,FLAPACTUATOR
50. INSPECTION,FLAP ACTUATOR
51 FUEL DRAIN - OUTBOARD FUEL CELL
52. AILERONCABLESAND MAIN LANDINGGEARTRUNNIONBOLT
53. AILERONCABLESAND MAIN LANDINGGEARLINK BOLT
54. FUEL LINE AND MAIN LANDINGGEARTRUNNIONBOLT
55. FUEL LINE
56. BLEEDAIR LINE COUPLINGAND MAIN LANDINGGEARLINK BOLT
57. FUEL DRAIN- MAINCELL (INBOARD)
58. FUEL DRAIN - AFT INBOARD CELL
EFFECTIVITY:
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MAINTENANCEMANUAL
D. Access and InspectionProvisions (continued)
64
65
n
n
73 76
78 77
74
EXTERNAL
INTERNAL
75
80
81
NOTE: Call outsfor Figure5 can be
found on 6-00-00Page10.
Access Platesand Panels- Fuselageand Stabilizer
Figure 5
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MAINTENANCEMANUAL
A. Access and InspectionProvisions (continued)
Figure 5. (Fuselageand Stabilizer)Call outs
59. TAIL RECOGNITIONLIGHTS,ELEVATORCONTROLS,STABILIZERATTACHMENTAND
ELEVATORPUSHROD
60. ELEVATORSECTOR,RUDDERAND ELEVATORCABLE
61. PRESSURIZATION
OUTFLOWVALVE
62. E.L.T.
63. EMERGENCYEXIT
64. ECU,HYDRAULICRESERVOIRAND HYDRAULICPOWERPACK
65. RADARAND BATTERY
66. ANTENNAAND CABLE
67. RUDDERTRIM
68. DINITROLSPRAYACCESS
69. RUDDERSECTORCONTROLCABLES
70. NOSE BAGGAGECOMPARTMENT,OXYGENBOTTLES,ECU GROUNDCOOLINGFANAND
ELECTRICCONTROLPANELS
71. BRAKERESERVOIRFILL
72. AVIONICSBAY AND NOSEGEAR STEERINGCONNECTIONS
73. q-SENSORRELAYS
74. BELOWFLOORACCESS,RUDDERCABLES,ECS LINESAND MISCELLANEOUS
75. GPU RECEPTACLE
76. NOSEGEAR DOORS
77. ELEVATOR,RUDDER,ELEVATORTRIMAND RUDDERTRIM CABLES
78. ELEVATOR,RUDDER,ELEVATORTRIMAND RUDDERTRIM CABLES
79. DINITROLSPRAYACCESS
80. ELEVATORTRIMCABLES PULLEY
81. ELEVATOROUTBOARDHINGEBOLTACCESS
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-60
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MAINTENANCE MANUAL
CHAPTER 7
LIST OF EFFECTIVE PAGES
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7-CONTENTS
7-10-00
7-10-00
7-20-00
7-20-00
7-20-00
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2
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3
DATE
CHAPTER
SECTION
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DATE
Feb 1/98
Jan 10/90
Feb 1/98
Feb 1/98
Jan 10/90
Jan 10/90
Jan 10/90
LISTOF EFFECTIVEPAGES
PAGE 1
Feb 1/98
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER7 - LIFTINGAND SHORING
TABLEOF CONTENTS
SUBJECT
CHAPTER
PAGE
7-10-00
General
Jacking
1
1
7-20-00
Shoring
1
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CONTENTS an109
PIPERAIRCRAFT
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MAINTENANCEMANUAL
Lifting and Shoring
A. General
The airplaneis lifted with the use of conventionaltripodjacks. In an emergencysituation,it may be
necessaryto useslings or airbagsfor the initial liftingprocedure.
If wing and fuselageshoringis required,be sure supportis contouredto conformto the surfaceit
upholds.
B. Jacking (Figures 1 and 2)
NOTE: Jackingmustbe done in a wind protectedarea on a level surface.
The liftingarrangementfor the PA-42-720(AdvancedTrainer)consistsof a jacking pad on eachwing,
outboardof the nacells,a nosepad forwardof the nosegear and a removabletail jacking pad which
attaches in front of the tail tie-down ring (Figure 1). Adjustable25 inch tripod jacks must be used.
Eightton capacitywing jacks and two ton capacitynoseand tail jacks are recommendedfor the
followingprocedure:
(1) Mounttail jacking pad (shownin Figure 1).
(2) Temporarilyalignjacks undertheir respectivejack pads.
(3) Pumpjacks up to pads. Whilejacking, realignjacks as necessary. Ensurejackheadsfit properly
with their pads and jacks are not slanted.
(4) Carefullyraisewing and nosejacks until all wheelsclear the surface;maintaina level airplane.
CAUTION: CARE MUSTBE USED IN APPLYINGPRESSUREAT THETAILJACKINGPAD.
EXCESSIVELOADSCAN DAMAGETHE AIRCRAFTSTRUCTURE.
(5) Raisetail jack to maintaincontactwith tail jackingpad.
JACK PAD
ATTACH SCREWS
(4 REQ'D)
VENTRAL FIN
TAIL JACK PAD
P/N 72246-10
TAIL TIE DOWN
RING
JACK CENTERING
CONE (INTEGRAL TO
TAIL JACK PAD)
JACK
Use of TailJackingPad
Figure 1
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B. Jacking (continued)
TOOL
P/N 72246-10
I
DISTANCESTO JACKPOINTS(Ground to Structure)
DISTANCESWHEN STRUTSAT:
JACKPOINTAND
STRUTAFFECTED MIN. EXTENSION MAX.COLLAPSED
WING/MAING.
51 IN.
32 IN.
NOSE/NOSEG.
44 IN.
25 IN.
JackingArrangements
Figure 2
7-10-00
Feb 1/98
7-1
0
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A. Shoring
Whensupportingthe aircraft at pointsother than jackingpads, loads mustbe carefullydistributedto
avoid overstressinglocal structures. Toshore fuselageand wings, usewoodencontourblocksas
shownin Figure7-3. The fuselageis supportedby a singleblock at FuselageStation(F.S.)93.0. A
pair of blocksat F.S.297.38and 310.0 are mountedtogetheron a transversepivot at F.S.304.0 to
equallydistributeweightof the aft fuselage. The wing is supportedby singleblocksas WingStation
(W.S.)30.0 and W.S. 109.5. All blocksare made of 2 x 10's,and are linedwith carpet or heavyfoam
rubberalongcontact faces.
ShoringArrangements
Figure 1
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A. Shoring(continued)
- 1INCHGRID
CONTOUR
FUSELAGE
NOTE:ALLOWFORCOMPRESSED
WHEN
OF PADDING
THICKNESS
PLOTTINGCONTOURBOARDS.
FUSELAGE
SKINCONTOUR
CENTERLINE
OF AIRPLANE
STATION93.0
FUSELAGE
FUSELAGE
SKINCONTOUR
FUSELAGE
SKINCONTOUR
CENTERLINE
OF AIRPLAN
CENTERLINE
OF AIRPLANE
/
STATION297.38
FUSELAGE
STATION310.0
FUSELAGE
WINGCONTOUR- 1INCHGRID
WINGSTATION30.0
WINGBOTTOMSKINCONTOUR
WINGSTATION109.5
FuselageandWingShoring
Figure2
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
A. Shoring(continued)
The centerlinelocations,loadson and strap widthsare shownin the tablebelow. The forwardstrap
can be no less than 12 incheswide and the aft strap 15 incheswide. (See Figure 3)
LOCATIONF.S.
FrontF.S. 40.0
STRAPWIDTH IN
LOAD PSI
(1)
12
24
138.06
69
15
30
100.54
50.3
(2)
Aft F.S. 230
(1)
(2)
Guide wireswill be neededon wing tips, nose,and tail. To facilitatethe attachmentof the guidewires
the tip tank fairingsand noseradomewill needto be removed. The tail guidewire can be attachedto
the tail tie down. These guidewires are to be usedfor stabilityonly. The guidewires will needone
person per wire to guidethe liftingand movingof the aircraft.
a = NOT TO EXCEED45°
138.50
13.81"
GUIDEWIRE
GUIDEWIRE
F.S.
4000
FS
GUIDEWIRE
GUIDEWIRE
GUIDEWIRE
Sling LocationF.S.
Figure 3
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MAINTENANCEMANUAL
CHAPTER8
LIST OF EFFECTIVEPAGES
CHAPTER
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8-EFFECTIVITY
8-CONTENTS
8-10-00
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1
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1
DATE
CHAPTER
SECTION
PAGE
DATE
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
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CHAPTER 8 - LEVELING AND WEIGHING
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
8-10-00
Weighing
1
8-20-00
Leveling
1
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Levelingand Weighing
A. Weighing
The airplaneis weighedas follows:
(1) Positiona scaleand rampin front of all three wheels.
(2) Securescalesfrom rollingforwardand tow airplaneup onto scales. (Referto 9-10-00.)
(3) Removerampsto avoid interferencewith scales.
(4) Toweighor balanceairplane,level airplaneusinginstructionsgiven in previoussub-system
section.
Weighing
Figure 1
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A. Leveling
andlateralleveling.Theairplanecanbe
withlongitudinal
are provided
All airplaneconfigurations
whilewheelsare on scales,or on theground.To
leveledwhileon jacks,duringweighingprocedure,
levelairplanefor weighingor rigging,proceedas follows:
screwsfromrightsideof aircraftat Fuselage
withdrawtoolattachment
Tolevelairplanelongitudinally,
Placeaircraftlevelingtool (P/N71587-3)in positionagainst
Station87.5and66.5(approximately).
andplacespiritlevelon levelingtool. Deflate
removed,
aircraftskin,securewithscrewspreviously
nosewheelor adjustjacksuntilbubblein levelis centered.
/
C
LEVEL
0
F.S.87.5
I
F.S.66.5
Leveling
Figure 1
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MAINTENANCE MANUAL
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CHAPTER 9 - TOWING AND TAXIING
TABLE OF CONTENTS
SUBJECT
PAGE
CHAPTER
9-00-00
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General
9-10-00
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Towing
9-20-00
Taxiing
1
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Towingand Taxiing
A. General
Beforetowingor taxiingairplane,ground personnelmustbe informedby a qualifiedpilot or other
personnelabouttow turning limitsof nosegear,enginestartingand shutdownprocedures,and any
other systemfunctionsrequiredto properlyand safely movethe airplane. (Refer to Figure 1)
TurningRadiusand Limits
Figure 1
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A. Towing
CAUTION: Whentowing,do not turn nosegear in either directionbeyondits 40 degree arc from
center. This results in damageto nose gear and steeringmechanism. A placardis
installedon nosegear strut to indicateturn limits.
Theairplanecan be movedby usingpowerequipment
whichwill notdamageor causeexcessstrain
to nosegearsteeringassembly.Towinglugsareusedaspartof the nosegearfork.
Topulltheairplaneon a hardlevelsurface,approximately
100poundsof pullis requiredto startits roll
andapproximately
60 poundsto maintainroll.
Whentowinglinesarenecessary,
linesare attached
to bothmaingearstrutsbelowthesidebracelink
attachments.Linesmustbe longenoughto clearnoseor tail bynotlessthan15feet anda qualified
personmustridein thepilot'sseatandusethebrakesandnosewheelsteeringto maintaincontrol.
A collapsible
towbar,locatedin the nosebaggagecompartment
fastenedto therearbulkhead,
is
removedbypullingit fromfrictionretainers.
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A. Taxiing
Whenthe propellerpropwash, exhaustblast, and taxi areas are clear,start engines. Apply power
slowlyto starttaxi roll and performthe followingchecks:
(1) Taxiforwarda few feet and applybrakesto determineeffectiveness.
(2) Taxiwith propellersset in low pitch and high rpm setting. Checkfor evenprop reversing.
(3) Whiletaxiing,makeslight turns to determinethe effectivenessof the steering.
(4) Checkwing clearancewhen taxiingnear buildingsor otherstationaryobjects. If possible,place
guides at eachwing tip.
(5) Whentaxiingon unevenground,avoid holesand nuts.
(6) Do notoperate enginesat high rpmwhen runningor taxiingover groundcontainingloosestones,
gravel,or any other loose materialthat can cause damageto propellerblades.
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CHAPTER 10
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PIPER AIRCRAFT
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MAINTENANCE MANUAL
CHAPTER 10- PARKING AND MOORING
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
10-10-00
Parking
1
10-20-00
Mooring
1
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Parkingand Mooring
A. Parking
Whenparkingthe airplane,ensure it is sufficientlyprotectedagainstadverseweatherconditionsand
presentsnodangerto other aircraft. Whenparkingthe airplanefor any lengthof time or overnight,it
mustbe mooredaccordingto sub-systemsectionon mooringbelow.
(1) Whenparkingairplane,headit intothewindif possible.
CAUTION:Usecarewhensettingbrakesthat areveryhotduringcoldweather.Extremeheator
accumulated
moisturecanfreezebrakes.Priorto settingbrakes,if eitherof the
aboveconditions
exist,chocksmustbe usedto blockwheels.
(2) Set parkingbrake by applyingtoe pressureagainsttop of rudderpedalswhilepullingout on brake
handle. To releaseparkingbrake, applytoe pressureon pedals and push in on parkingbrake
handle.
(3) Installprotectivecovers on enginesand pitot tubes;securepropellers.
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A. Mooring
Theairplaneis mooredfor protectionandsecurityundervariousweatherconditions.Thefollowing
procedure
mustbe usedfor mooringthisairplane:
(1) Headairplaneintothewindif possible.
(2) Blockwheelswithwheelchocks.
CAUTION: Use square or bowlineknots. Do not useslip knots.
NOTE: Additionalpreparations
for highwindsincludeusingtie-downropesfromthe landinggear
forksandsecuringtherudder.
(3) Securetie-downropesto wingtie-downringsandtail skidat approximately
45 degreesto the
ground.Whenusingropeconstructed
of non-synthetic
material,leavesufficientslackto avoid
damagingaircraftwhenropescontractdueto moisture.
(4) Installpitottubecovers,engineinletexhaustcovers,generator
coolinginlet,andexhaustoutlet
covers.Restrainpropellersto preventwindmilling.
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CHAPTER11
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CHAPTER 11 - REQUIRED PLACARDS
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
11-20-00
ExteriorPlacardsand Markings
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RequiredPlacards
A. ExteriorPlacardsand Markings
The airplanenameplateplacard is locatedbelowthe entrancedoor of the airplane. The placard
identifiesthe airplane by its modelnumberand serial number. Should a questionariseconcerningthe
careof theairplane,it is important
to includetheairplaneserialnumberin anycorrespondence
to
PiperAircraftCorporation.
As requiredinteriorplacardsandmarkingsarelistedin SectionII Limitations
of the Pilot'sOperating
Handbook
andFAAApprovedAirplaneFlightManual.
Exteriormaintenance
placardsareshownin thischapter.
NOTE: Anytimean airplaneis repainted
or touchedup,inspectall placardsto ensurethattheyare
notcoveredwithpaint,arelegible,andsecurelyattached.
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A. ExteriorPlacardsandMarkings(continued)
C
%
4
4
5
6
7
7
TOP VIEW
19
17
18
9
16
0
14
15
SIDEVIEW
12& 13
ExteriorPlacardsandDecals
Figure1 (Sheet1 of 6)
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A. ExteriorPlacardsand Markings(continued)
20
21
21
22
25
20
20
24
23
BOTTOMVIEW
FRONTVIEW
ExteriorPlacardsand Decals
Figure 1 (Sheet2 of 6)
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A. ExteriorPlacardsand Markings(continued)
BRAKE
RESERVOIR
LEVELPOINT
LEVEL POINT
PLACARD2
PLACARD1
CUTHEREIN EMERGENCY
CUTHEREIN EMERGENCY
PLACARD3
ENGINEOIL SPECIFICATION
DO NOT MIX DIFFERENTBRANDS
OIL CAPACITY:9.2 QTS.
DO NOT OVERFILL
FILL WITH APPROVEDOIL TO MAXIMUM
MARK ON DIP STICK. SEE CURRENTISSUE
OF UNITEDAIRCRAFTOF CANADA LTD.
ENGINESERVICEBULLETINNO. 1 FOR LIST
OF APPROVEDLUBRICATINGOILS.
PLACARD4
JET FUEL ONLY
PLACARD5
ExteriorPlacardsandDecals
Figure 1 (Sheet3 of 6)
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A. ExteriorPlacardsand Markings(continued)
FUEL
USEAVIATIONKEROSENE
SEE AIRCRAFT FLIGHT
MANUAL
FORALTERNATE FUEL
NO STEP
PLACARD 7
PLACARD 6
TIE DOWN ONLY
NO JACKING
DO NOT PUSH
PLACARD 8
PLACARD 9
PIPER PC
STATICVENTS
KEEP CLEAN
PLACARD10
MANUFACTUREDBY
PIPERAIRCRAFT
CORPORATION
VERO BEACH, FLORIDA
MODEL
SERIAL NO.
PUSH
PLATENO.
PLACARD13
PIPERPART NO.79644-2
PLACARD11
ExteriorPlacardsand Decals
Figure 1 (Sheet4 of 6)
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A. ExteriorPlacardsand Markings(continued)
FORSERVICE
WIREINFLATION- MAIN 100 PSI INSTRUCTIONS
(SEEMAINTENANCE
MANUALFOR
PLACARD15
SERVICINGWITH MIL - H - 5606
(RED)HYDRAULICFLUID). WITH
TIRE INFLATION- NOSE 70 PSI NO LOADONSTRUT,INFLATETO
435 psi.
PLACARD15a
PLACARD14
INSTRUCTIONS
FORSERVICE
(SEEMAINTENANCE
MANUALFOR
SERVICINGWITH MIL - H - 5606
(RED)HYDRAULICFLUID). WITH
NO LOADON STRUT,INFLATETO
330 psi (350psi on PA-42-720).
PLACARD16
OXYGEN
FILL
PLACARD19
PLACARD17
JACK PAD
E. L. T.
PLACARD20
LOCATEDBEHINDPANEL
PLACARD18
ExteriorPlacardsandDecals
Figure1 (Sheet5 of 6)
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A. ExteriorPlacardsand Markings(continued)
FILL PORT - DRY NITROGEN ONLY
SEE SERVICE MANUAL
FOR INSTRUCTIONS
TEMP-PRESSURE RANGE
°F
PSIG
°F
PSIG
-40
-20
0
+20
FUNCTIONALTEST PORT
SEE SERVICEMANUAL
FOR INSRUCTIONS
+40
1585 1660 1735 1815 1890
+60 +70 +80 +100 +120
1960 2000 2035 2110 2185
WARNING
COMPRESSEDGAS
PLACARD 21
FUEL SUMP
DRAIN
PLACARD 22
OXYGENSYSTEM
OVERPRESSURE
DISCHARGEDISC
PLACARD 23
FUEL SHUTOFF
DRAIN
PLACARD 24
FUEL
CROSSFEED
DRAIN
EXTERNAL
POWER
28 VOLTS DC
PLACARD 25
STATICSYST. DRAINS
PLACARD 26
PLACARD 27
ExteriorPlacardsand Decals
Figure 1 (Sheet6 of 6)
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MAINTENANCE MANUAL
CHAPTER 12
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
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CHAPTER 12 - SERVICING
TABLE OF CONTENTS
SUBJECT
General
Engine/Compressor
Washing
FieldCleaningEngine
Aircraft FinishCare
Cleaning
CleaningExteriorSurfaces
CleaningWindshieldand Windows
CleaningInterior
CleaningCarpets
CleaningToilet
CleaningSurfaceDeicingEquipment
CleaningLandingGear
CHAPTER
PAGE
12-00-00
12-10-00
Replenishing
Fuel HandlingPractices
FillingFuel Cells
Jet Fuel Additives
MIL-1-27686Jet Fuel Anti-IcingInhibitors
BioborJF (Biocide)
DrainingMoistureFrom Fuel System
DrainingFuel System- Complete
ProcedureFor RemovingBiologicalFuel Contamination
BrakeSystem
FillingBrakeSystemReservoir
DrainingBrakeSystem
LandingGear OleoStruts
FillingOleo Struts
InflatingOleo Struts
Tires
HydraulicPowerPack
Propellers
EngineLubrication
EngineOil LevelCheck
EngineOil Chip Detector
RemovalOf Chip Detector
Inspectionof Chip Detector
Installationof Chip Detector
DrainingEngineOil
ServicingOil FilterElements
1
1
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CHAPTER12 - SERVICING
TABLE OF CONTENTS(continued)
SUBJECT
CHAPTER
PAGE
12-10-00
13
13
13
14
Recommendationsfor ChangingOil
OxygenSystem
OxygenSystemSafety Precautions
FillingOxygenCylinder
12-20-00
1
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1
1
2
ScheduledServicing
AirframeLubrication
Applicationof Grease
Applicationof Oil
LubricationCharts
12-30-00
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EngineAccessoryDrive Shafts- Lubrication
1
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CONTENTS
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
Servicing
A. General
This chaptercovers all routineservicingof airplane,scheduledand non-scheduled,including
replenishmentof fuel, oil, hydraulicfluid, oxygen,tire pressure,lubricationrequirements,servicingof
oleo strutswith air and oil, etc. Pay specialattentionto all WARNINGSor CAUTIONS.
B. Engine/CompressorWash
Due to accumulatedenvironmentalairbornechlorideswhichcause deteriorationof compressorblades
by a processknown as sulphidation,Pratt & WhitneyAircraftrecommendsa compressorwashbe
carriedout weekly regardlessof apparentatmosphericconditions. Pratt & WhitneyMaintenance
Manual,P/N 3034342for PT6A-61engine,givesfull, detailed instructionsto wash of engineand
compressor.For specificPiperinstallationsinstructions,usefollowingadditionalinstructions:
CAUTION: BEFORECLEANING,CABLESMUSTBE PROPERLYSEALEDTO PREVENT
WATERFROMENTERINGCABLEHOUSINGS.DO NOT DIRECTANY WATER
PRESSUREAT THESESEALS. WATERCOULDFREEZEAND BIND CABLES
UNDERCERTAINCONDITIONS.
CAUTION: DO NOT USE TAPWATERAS INHERENTCHEMICALSCAN CAUSEDEPOSITS
ON COMPRESSORBLADES.
CAUTION: BE CAREFULWHENWASHINGEXTERIOROF FCU. DO NOTALLOWWASH
SOLUTIONTO ENTERVENTHOLESOF FCU, WHICHCOULDGIVE FALSE
INDICATIONOF FUELPUMPLEAK.
CAUTION: OBSERVESTARTEROPERATINGLIMITSOF 30 SECONDSON, 60 SECONDS
OFF,30 SECONDSON, 60 SECONDSOFF,30 SECONDSON, AND30 MINUTES
OFF.
CAUTION: RUN ENGINEWITH STARTERONLY. ENSUREIGNITIONIS OFF AND
APPROPRIATEFUELFIREWALLSHUTOFFVALVEIS CLOSED.
1. Allow engineto cool for at least30 minutesbeforeperformingcompressorwash.
2. With top cowlingremoved,disconnectbleedair line at unionbelowT-connection.Securecap
lines.
3. Close bleedair shutoffvalve and installground runcowl. Disconnectand cap HI and LO stage
bleed lines. Do not wash enginewith bleedmixingvalveconnectedto bleed lines as valvecontrol
passagewaysbecomepluggedor fouled,renderingvalve inoperativeand uncontrollable.
4. Open accessdoor on side of bottomcowl;clean mechanismattachedto wash ring fitting and
clean accordingto Pratt & WhitneyMaintenanceManual.
5. Soak for about 15 minutesafterwash.
C. Field CleaningEngine
Field cleaningconsistsof internalwashingof enginecompressorand externalwashingof engine.
Referto Pratt& WhitneyMaintenanceManual,P/N 3034342,Chapter71, for approvedprocedures
and precautions.
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D. AircraftFinish Care
1. Cleaning
WARNING: DO NOT USEGASOLINE,KEROSENE,ALCOHOL,BENZENE,CARBON
TETRACHLORIDE,THINNER,ACETONEOR WINDOWCLEANINGSPRAYSTO
CLEANAIRPLANE.
The entire airplaneis carefullyfinished insideand out to assuremaximumservicelife. All parts
are alodinetreated and sprayedwith zinc chromateprimeron both sides. The externalsurfaces
are coatedwith durablepolyurethaneenamel.
2. Cleaning ExteriorSurfaces
The airplaneshould be washedwith a mild soap andwater solution. Harshabrasivesor alkaline
soaps or detergentscould scratchpaintedor plasticsurfacesor corrodemetal. Cover areas
where a cleaningsolutioncould cause damage. Towash the airplaneusethe followingprocedure:
(a) Flushaway loosedirt with water.
(b) Apply cleaningsolutionwith a soft cloth,a spongeor a soft brush.
(c) To removeexhauststains,allow the solutionto remainon the surfacelonger.
(d) To removestubbornoil and grease stains,usea softcloth dampenedwith naphtha.
(e) Rinseall surfacesthoroughly.
(f) Any good automotivewax may be usedto protectand preservepaintedsurfaces. Soft
cleaningclothsor a chamoisshouldbe usedto preventscratcheswhen cleaningor polishing.
A heaviercoat of wax on leadingsurfaceswill reducethe abrasionproblemsin theseareas.
Referto surfacede-ice cleaningprocedures.
3. CleaningWindshieldand Windows
CAUTION: USE ONLYWATERAND MILDSOAP WHEN CLEANINGTHE HEATED
WINDSHIELD. USE OF ANY OTHERCLEANINGAGENTOR MATERIALMAY
CAUSEDISTORTIONOR DAMAGETO WINDSHIELDCOATINGS.
(a) Removedirt, mud and other loose particlesfrom exteriorsurfaceswith clean water.
(b) Washinterior and exteriorwindowsurfaceswith mild soap andwarm water. Use a softcloth or
spongein a straightback and forth motion. Do not rub harshly.
(c) Removeoil and greasewith a cloth dampenedwith PlexiglasPolishand Cleaner,P/N 403D or
similarsubstanceconformingto FederalSpecification(P-P-560)or kerosene.
(d) Rinsewindowsthoroughlyand dry with soft lint-freecloth.
WARNING: DO NOT USE GASOLINE,ALCOHOL,BENZENE,CARBONTETRACHLORIDE,
THINNER,ACETONE,STRONGSOLVENTSOR WINDOWCLEANING
SPRAYS. DO NOT USE PLASTICCLEANERON HEATEDGLASS
WINDSHIELDS.
(e) A superficialscratch or marin plasticcan be removedby polishingout the scratchwith
jeweler'srouge.
(f) Whenwindowsare clean, apply a thin coat of polishingwax. Rub lightlywith a softcloth. Do
not apply wax to heatedwindshieldswith electricalheatingelements.
(g) Apply REPCONrepellentor equivalentto windowsand windshieldto improvevisibilityduring
flightsthrough rain. Apply only accordingto manufacturer'sinstructions. (Referto 91-00-00,
ConsumableMaterials.)
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D. AircraftFinishCare (continued)
4. CleaningInterior
(a) Vinylinteriorsurfaces maybe cleanedwith a damp cloth and mild soapand water solution.
(b) Leathermaybe cleanedwith a mild handsoap and water solutionor with a saddlesoap.
Followthe precautionswhich applyto the cleaningof any fine leather product. Avoid saturation
and never use detergentsor harsh cleaningsolutionson leather.
CAUTION: USE OF COMMONHOUSEHOLDCLEANERSAND POLISHESON WOOD
LAMINATEDSURFACESCOULDBE VERYHARMFUL.
(c) Woodlaminatedsurfacesshould be maintainedusingonly a highgradefurniturewax.
(d) All upholsteryfabrics are Scotchguardtreatedand may be cleanedas follows:
(1.) Spilledoily and wateryliquidswill generallybead up on the fabric and can be blottedaway
leavinglittle or no stain. Blot spills up as quicklyas possiblewith an absorbentcloth,
tissue or sponge. If the materialis a solid or semi-solid,such as butter,removethe
excessby gently scrapingwith a tableknife. Often,blottingwill removeall tracesof stain
but if the stainingagent is not completelyremovedby blotting,the followingtechniques
are suggested:
(e) Water-basedstainssuch s ketchup,milk, ice cream,coffee:
(1.) Wipethe stain with a cloth wet with watercontaininga detergentor ammonia(4 fluid
ounces of ammoniato one gallon of water). Repeatif necessary.
(2.) Oil basedstainssuch as saladdressing,butteror mayonnaisemaybe removedby either
of the followingprocedures:
(3.) Apply "Texize K-2RSpot Remover"by sprayingor rubbinginto the fabric and let dry.
Vacuumoff the residualpowder. Repeatif necessaryor wet a clothwith a solventtype
spot cleanersuch as "Energine"or "Renuzit"and wipe or gently rubthe stained area.
Turn cloth and rewetwith solventoften. Repeatuntil staindisappears.
(4.) To removeresidualdetergentleft on the fabric,wipe the entirefabric surfacewith a cloth
dampenedwith water. The cloth shouldbe rinsedin cleanwater severaltimes. This
procedurewill ensurethat the treatmentwill continueto function.
NOTE: It is best to test the cleaneron an inconspicuousportionof the fabric to test for
discoloration.Also avoid soakingor harsh rubbing.
5. CleaningCarpets
WARNING: SOLVENTCLEANERSREQUIREADEQUATEVENTILATION.
Use a small whisk broom or vacuumcleanerto removedirt. For soiledspots,use a nonflammable
dry cleaningfluid. Floorcarpets maybe removedand cleaned like any householdcarpet.
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D. Aircraft FinishCare (continued)
6. CleaningToilet
(a) Dry Toilet
(1.) Todisposeof the sanitarybag, pull the top of the bag from the pail and closewith a wire
tie. Removeit from the airplanein the coveredpail and disposeof accordingto field
facilities. Do not attemptto flush the bag in a toilet.
(2.) Toclean and deodorizethe airplane'stoilet, mix a solutionof disinfectanttypecleaner.
Usinga soft bristlebrush, rag and solution,washthe toilet pail and seat. The toilet may
be removedfor cleaningby disconnectingthe two fastenersat the insideforwardend of
the unit. Slide it back and lift from the floor.
(3.) Whenoffensiveodor remains,use a strongersolutionand reclean.
(4.) Rinsewith fresh water and dry.
(5.) To installa new sanitarybag, place it over the top edge of the pail and push it intothe
bottomof the pail.
(b) FlushingToilet
(1.) Toclean, disconnectthe electricalplug. Unlockthe toilet assemblyby turning the wing
head fastenersone-halfturn counter-clockwise.Removethe toilet assemblyand clean.
Serviceperthe instructionslocatedon the toilet wastetank.
7. CleaningSurfaceDeicingEquipment
The deice bootsshouldbe cleanedwhen the aircraft is washedusing a mild soap and water
solution.
In cold weather,wash the bootswith the airplaneinsidea warm hangarif possible. If the cleaning
is to be done outdoors,heat the soap and water solutionbeforetaking it out to the airplane. If
difficultyis encounteredwith the waterfreezingon boots,direct a flow of warm air alongthe region
beingcleaned, using a portabletype ground heater.
As an alternatecleaningsolvent,use benzol or non-leadedgasoline. Moistenthe cleaningcloth in
the solvent,scrub lightlyand then with a clean dry cloth, wipe dry so that the cleanerdoes not
have time to soak intothe rubber.
CAUTION: PETROLEUMPRODUCTSSUCHAS THESEARE INJURIOUSTO RUBBERAND
THEREFORESHOULDBE USEDSPARINGLYIF AT ALL.
When deice bootsare clean,a coatingof B.F. GoodrichIcex shouldbe applied. Icexis
compoundedto lowerthe strengthof adhesionbetweenice and rubbersurfaceof the deiceboots.
8. CleaningLandingGear
Beforecleaninglandinggear, placeplasticcover or similarmaterialover wheeland brake
assembly.
NOTE: Inboardgear doors can be loweredby actuatingemergencyhand pump handlewith
master switch OFF.
(a) Place can undergear to catch waste.
(b) Sprayor brush gear area, as required,with solventor mixtureof solventand degreaser.
(c) Allow solventto remainon gear for 5 to 10 minutes. Rinsegear with additionalsolventand
allow to dry.
(d) Removecover fromwheel and removecatchcan.
(e) Lubricategear per lubricationchart. (Refer to 12-20-00)
EFFECTIVITY:
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Jan 10/9
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Replenishing
1
26
25
24
14 18
13
19
28
1. TIP TANK FUELFILL
2. DRAINFOR TIP TANK (ON FAIRING)
3. ENGINEOIL FILTER(OUTBOARD)
4. OIL DRAIN(LINEFROM ENGINE)
5. HYDRAULICFILTER
6. FUEL FILTER
20. MAINFUELTANKDRAIN- RIGHT& LEFT
21. OXYGENPRESSUREGAUGE
22. PRESSURIZATION
CONTROLLERFILTER
BLEEDAIR
23. OXYGENFILL
24. NOSEGEARTIRE
7. NACELLE FUEL FILL - RIGHT
25. APU COUPLING
8. SUBMERGEDFUELPUMP- RIGHT& LEFT
26. BATTERY
9. INBOARDAFTCELLDRAIN- RIGHT& LEFT
27. OXYGENBOTTLE(BEHINDROYALITEPANEL)
10. SHOCKSTRUTVALVEAND FILL - RIGHT& LEFT
28. NOSEGEAR SHOCKSTRUT FILLVALVE
11. OUTBOARDCELL DRAIN- RIGHT & LEFT
29. HYDRAULICBRAKERESERVOIRAND
12. RIGHT& LEFTMAINTIRES
POWERPACK
FILL
13. DUALDRIVEOIL LINEFILTER30. ECUAIR WATERSEPARATOR
LEFTENGINE(OUTBOARD
31. HYDRAULICPOWERPACK
14. WASHRINGCONNECTIONAND CAP - LEFTENGINE 32. VACUUMSYSTEMFILTER
15. FUEL FILTER
33. WASHRINGCONNECTIONAND CAP
16. NACELLEFUELFILL - LEFT ENGINE
RIGHTENGINE(INBOARD)
17. HYDRAULIC FILTER
34. DUALDRIVEOIL LINE FILTER
18. OIL DRAIN - LEFT ENGINE (INBOARD)
RIGHTENGINE(INBOARD)
19. ENGINE OIL FILTER (INBOARD)
35. ENGINEGEARBOXOIL STRAINER
Service Points
Figure 301
EFFECTIVITY:
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12-10-00 JanPAGE
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12-10-00
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. FuelHandlingPractices
Thehandlingof turbinefuelas usedinthisairplanerequiressomespecialattentionandsafety
precautions
whichcannotbe overlystated.Thereareseveralproblemswhichare notnormally
associated
with aviationgasoline.Oneis wateror microscopic
particlesof freewatersuspended
in
thefuel,anotheris microbiological
contaminants
or micro-organisms
whichliveandmultiplyinthe
waterinterfaceswithturbinefuel. Dueto theseproblems,
turbinefuelrequiresgoodfuel handling
practicesto assurethattheairplaneis servicedwithcleanfuel. Thefollowingstepsshouldbe usedto
minimizethepossibleintroduction
of contaminants
intothefuel systemandmaintaina cleancondition
withinthefuelcells:
1. Knowthesource(supplier)
of thefuelto be used,ascertainthatit is properlystoredandfilteredas
it is passedfromthe storageareato theairplane.
2. Performregularfuelfilterinspections
to determineif anysludgeis present.(Microbiological
contamination
is visibleas a slimeor sludgewhichmayvaryin color,i.e.red,brown,grayor
black.) Micro-organisms
havea tendencyto matandcauseinterference
withfuelflow. Reference
to FAAManualA.C.65-9,Chapter4 givescompleteexplanation
on fuelsandrelatedproblems.
3. It isveryimportantto maintaina cleanfuel systemby periodically
flushingthefuel cellsto remove
anycontaminants
within.
C. FillingFuel Cells
WARNING: DO NOT OPEN OPTIONALNACELLEFUELCELL FILLEROR WINGFILLERCAPS
WITH MORETHAN2 INCHESOF FUEL IN TIP TANKS.
WARNING: ALWAYSCONNECTSTATICGROUNDCABLEFROM REFUELERTO AIRPLANE.
KEEP ALL GROUNDINGCONNECTIONSCLEANAND CORROSIONFREE.
The fuel cells in eachwing are filled throughwing filler cap. Optionalnacellefuelcells contain
individualfiller neckson top of each nacelleinsteadof wing fillers.
Afterrefuelingairplane,allow3 to 4 hourssettlingperiodwhenever
possible,thendrainsmallamounts
of fuel fromeachdrain. thebenefitsof a settlingperiodwillbe lost,unlesstheaccumulated
contaminants
withinthefuel cellsaredrainedbeforetheairplaneis movedor thefuel is disturbedby
theoperationof theinternalfuelpumps.Toreduceaccumulation
of condensation
withinthefuelcells,
it is suggested
thatthecellsbe maintained
in a full conditionas oftenaspossible.
At intervalsof 100 hours or 90 days,whichevercomesfirst, clean the filter elementsin eachfuel filter
unit locatedon the inboardside of eachenginemount. Removeand cleanthe filters in accordance
with instructionoutlined in 28-00-00. Inspectionintervalsof the variousfuel systemcomponentsmay
be found in the Piper ProgressiveInspectionManual,P/N 761 819 (100 Hour) and P/N 761 820 (50
Hour).
D. Jet FuelAdditives
Condensationof water in the fuel tanks increasesthe possibilityof microbiologicalgrowth
contaminationof the fuel. This contaminationcan damageskins,coatingsand sealantsin the tanks.
Fuel additivesconformingto MIL-I-27686and/ora biocidalagent manufacturedundersuch trade
name'sas BioborJF are compoundswhichcontain anti-fungicidalagents. Use of either of these
additivesin the fuel tanks will reducethe possibilityof contaminationof fuel and fuel filters/lines.
NOTE: Referto latestPratt& WhitneyCanadaServiceBulletin13044(PT6A-61
engine)for
instructions
on useof fuel additives.
EFFECTIVITY:
040-999
Jan 10/90
12-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
E. MIL-1-27686Jet Fuel Anti-icingInhibitors
The MIL-1-27686
Jet Fuel Anti-IcingInhibitor,primarilyis an anti-icingagent, howeverit also has
excellentmicrobiologicalsludgedeterrentcharacteristics.It is very solublein water, and only slightly
solublein fuel,which mandatesthat the blendingwith fuel be accomplishedin a precisemanner.
Such a devicepermitsinjectionof the agent intoa flowingstreamof fuel to ensureeven disbursement.
Whenblendingthe additive,the concentrationshould not be less than 0.10 percentor morethan 0.15
percentby volume. Exceptfor the informationcontainedherein and in the Pilot'sOperating
Handbook,the manufacturer'smixingor blendinginstructionsshouldbe carefullyfollowed.
CAUTION: ASSURETHATTHE ADDITIVEIS DIRECTEDINTOTHE FLOWINGFUELSTREAM.
THE ADDITIVEFLOWSHOULDSTARTAFTERAND STOPBEFORETHE FUEL
FLOW. DO NOT PERMITTHE CONCENTRATED
ADDITIVETO COMEIN CONTACT
WITH THE AIRCRAFTPAINTEDSURFACESOR THE INTERIORSURFACESOF THE
FUELTANKS.
CAUTION: SOME FUELSHAVEANTI-ICINGADDITIVESPREBLENDEDIN THE FUELAT THE
REFINERY,SO NO FURTHERBLENDINGSHOULDBE PERFORMED.
CAUTION: THIS ADDITIVESHOULDNOT BE USEDAS A REPLACEMENTFOR PREFLIGHT
DRAININGOF THE FUELSYSTEMDRAINS.
F. BioborJF (Biocide)
BioborJF is not an anti-icingagent and is intendedto be usedspecificallyas a fuel biocide. The
compoundis an extremelyefficientbiocidalagent and is solublein the fuel as well as water. BioborJF
dispersesthroughoutthe entirefuel systemto eventhe mostremote areas soonafter introductioninto
the fuel system. This compoundis usedas a periodictreatmentin concentrationsof 135 ppmwhen
the airplanehas been operatedin an environmentconductiveto contaminationor when evidenceof
such contaminationis found. BioborJF may alsobe used in maximumconcentrationsof 270 ppm as
a singledose shocktreatmentto clean out and sterilizea very contaminatedsystem. BioborJF is not
volatileand may remainin the tank until the fuel is used.
The preferredmethodof introducingBioborJF intothe fuel is by injectionthrough a meteringdevice.
If no meteringdeviceis available,blendingmaybe accomplishedby batchblendingor by over-thewing blendingwhile fillingthe tanks. Whenone halfthe requiredquantityof fuel has been added,
graduallyintroducethe compounddirectlyintothe streamof fuel whilethe remainingone half of fuel is
added. Completemixingis necessarydependingon the severityof the contamination. It mustbe
used at a high enoughconcentrationto kill, not controlthe infestation.When usedonly periodically,it
must be usedoften enoughto contactthe entire surfaceof the fuel tank interiorsand remainin contact
up to 72 hoursto effectthe kill. An airplanewhich hasbeen treatedand flown, should be retreatedat
consecutivefills so that a 72 hour contacttime is accomplished.
CAUTION: IT IS IMPERATIVETHATALL MANUFACTURER'S
INSTRUCTIONSBE FOLLOWED
WHEN USINGTHESEPRODUCTS
EFFECTIVITY:
040-999
12-10-00 Jan
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
G. DrainingMoistureFrom Fuel System
Tofacilitatedrainingfuel systemfilterbowls,lines,andfuelcellsof moistureandforeignmatter,drains
in bottomof eachfilterbowl,wingtiptank,mainoutboardandinboardfuelcell,aft
areincorporated
inboardfuelcells,andcrossfeedlines. Thenacellefuelcellsdrainintomainfuelcellsanddo nothave
individual
externaldrains.
AND POSSIBLEFIRE
WARNING: TO PREVENTRAMPSURFACECONTAMINATION
DAMAGE,ANY FUELSPILLEDON RAMPAREA,ETC, MUSTBE REMOVED
IMMEDIATELY.
1. To drain eitherfilter bowl,open accessdoor on left rear side of each enginecowl and momentarily
pushdown on the drain valvearm. Allowenoughfuel to flow to clear filter bowl.
NOTE: Ensurenacelletankisfull to drainfilterbowl.
2. Todrainoffwaterinfuel cells,pushup on eachcelldrainarmandallowfuel to flowmomentarily.
Fivedrains;oneforeachtiptank,onefor eachmainoutboardcell,onefor eachmaininboardcell,
andonein inboardafttankandcrossfeedlinedrainonbottomof eachwing.
NOTE: To ensureremovalof moisturefrom eachfuel drain, allowfuel to settle for three to four
hours if possible.
H. DrainingFuel System- Complete
Thebulkof fuel is drainedfromsystemby placinghosedownthroughwingfillerfor standardsystems
or nacellefillerneckforoptionalsystems.Thefuelis drainedfromfuelfilterbowlsbyactivating
valvesarein off position.
providingcrossfeed
filterdrains.Eachwingis drainedseparately,
individual
1. Procedure
ForRemoving
BiologicalFuelContamination
Fuelsystemcontaminationpresentsa bigger potentialproblemin turbine fuel systemsthan in fuel
systemsusing aviationgasolinebecauseof turbinefuels greateraffinityfor water. Microorganisms
thrivewhen water dropletsand fuel are mixedsinceby-productscreatedby this form of contamination
attackfuel cell bladdersand metalcomponents;fuel systemmust be keptclean and periodically
inspectedto ensure it is free of water and otherforeign matter. If biologicalcontaminationexists,
evidencedby presenceof red, brown,gray,or blackslime in fuel tanks, lines,pumpsand filters,
thoroughlyclean all systemcomponentswith lowestoctaneaviationgasolineavailable.
Proceedasfollows:
WARNING: PROPERGROUNDINGPROCEDURES
AND SAFETYPRECAUTIONSMUST BE
FOLLOWED.
1. Levelaircraft.
2. Defuelaffectedwings,nacelles,andtiptanks.
fuel.
NOTE: Onlyusecontainerdesignedfor usewithcontaminated
3. Removeallsumpdrainson effectedsidesandensureallfuel is removed.
4. Removebottomwingrootfairing.
5. Removefuelcell andtankaccesscoverson winguppersurface.
6. Removeboostpump.
7. Removecowlingof affectedengines.
8. Removefirewallmountedfuelfilterandenginedrivenfuelpumpinletandoutletfilters. Cleanor
replaceas required.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
1. Procedure
ForRemovingBiological
FuelContamination
(continued)
9. Removeallfingerscreensandfloator checkvalves.
10. Cleanallfuelfilterbowlsandhousings
withaviationgasolineandinspectcomponents
for etching.
If etchingexists,replaceaffectedcomponent.
CAUTION: BRUSHMUSTHAVELANYARDATTACHEDTO PREVENTBRUSHFROM
FALLINGWITHINCELL.
11. Removeaccess coversfrom fuel cellswhich requirecleaning. Use Stoddardsolventand soft
bristle brushto scrubaffectedcells. Removeany particlesof contaminationin fuel cell with tack
rag. Whenfuel cell cleaningis completed,ensureno equipmentis left in fuel cells and reinstallall
accesscovers.
NOTE:Nacelletankaccesscoverrequiressealing.
12. Use lowestoctane aviationgasolineavailable. Thoroughlyflush all fuel cells,tanks, connecting
fuel lines,and boostpump.
13. Inspectall fuel cells, tanks, pumps,and lines for deterioration. The microorganismby-products
attachfuel bladders,harmfuel tank coatings,and etch underlyingmetals.
14. Reinstallboost pump and safety.
15. Reinstallall sump drains.
16. Reinstallfirewall mountedfuel filter bowlswithoutfilter elements.
17. Reinstallboth filter elementsand bowlson enginedrivenfuel pumpsand safety.
18. Flushsystemas follows:
(a) Disconnectfuel line betweenfuel pressuresnubberand fuel pump.
(b) Add eightgallonsof aviationgasolineto affectedsides.
(c) Pullall circuit breakersexceptthose controllingfuel boost pump.
(d) Placemaster switch in on positionand actuateboostpump.
(e) Afterpumpingtwo gallonsof aviationgasolineusingpump, observefuel comingfrom fuel line.
Actuatecrossfeedvalve;ensurecrossfeedline is clean.
NOTE: If rightwingisonlycontaminated
portion,ensurecrossfeedvalveandlineis
adequately
flushedbydisconnecting
crossfeedlineat crossfeed
valveon leftwing
side. Drainfuel intocontaminated
fuel container.
19. Checkall linesandfittingsforleaks.
20. Continueto pump aviationgasolinethroughsystemuntil cleanfuel flows intocontaminated
container.
21. Reinstall
filterelementsin firewallmountedfuelfiltersandsafety.
22. Reconnect
fuel linesbetweenfuelflowtransmitters
andenginedrivenfuel pumps.
23. Checksystemfor leaks.
24. Reinstall
bottomwingrootfairings,fuelcell,andtankaccesscovers.
25. Reinstall
enginecowlings.
26. Fillaffectedfuel cellswith30gallonsof lowestoctaneaviationgasolineavailable.(Add
onequartof
120aviationgrademineraloil to every100gallonsof fuel) Runengines.Observeall cautions
whenoperatingengines.
NOTE: Makelogbookentryeachtimeengineis runon aviationgasoline.Referto Pratt&
WhitneyServiceBulletinNo.13044,EngineFuelsandAdditives.
27. Inspectfirewallmountedfuelfiltersafteroperating
engines.Lookfor evidenceof microbiological
contamination.
If contamination
exists,repeatcleaningprocedure.
28. Cleanfuelfilters;reinstallandsafety.
EFFECTIVITY:
040-999
12-Jan
PAGE5
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
J. BrakeSystem
The brake systemcontainsa hydraulicfluid reservoirthroughwhichthe brake systemis periodically
serviced. Fluid is drawnfrom the reservoirby the brake mastercylindersto maintainthe volumeof
fluid requiredfor maximumbrakingefficiency.Spongybrake pedalactionsis often an indicationthat
the brake fluid reservoiris runninglow on fluid or air. Whenrepairsto brake systemcomponentsor
bleedingthe systemare required,refer to instructionsin 32-40-00.
K. FillingBrakeSystemReservoir
The brake systemreservoirmust be filled with hydraulicfluid to the level markedon the dipstick(MILH-5606). The reservoirin the upper nosesectionabovethe powerpack mustbe checkedat every50
hour inspectionand replenishedas necessary.Accessto the reservoiris throughthe dooron the
upper right portion of the nose section. If fluid level is low, it mustbe filled with filtered hydraulicfluid
(MIL-H-5606). No adjustmentto the brakesis necessary,but they mustbe checkedperiodicallyper
instructionsgiven in 32-40-00.
L. DrainingBrake System
Todrain brake system,connect hoseto bleederfitting on brake housing. Placeother hoseend in
suitablecontainer. Open bleedervalveand slowlypump brakepedal until fluid stops flowing. Toclean
system,flush with denaturedalcohol.
NOTE: If brake systemis drained,parts replaced,or line connectionsbroken,pressurefill and bleed
systemper procedurein 32-40-00. Procedureassuresair is not trapped in system.
M. LandingGear Oleo Struts(Referto Figure 12-2)
WARNING: DO NOT RELEASEAIR BY REMOVINGSTRUTVALVECOREOR FILLERPLUG.
DEPRESSVALVECOREPIN OR OPENAIR VALVESLOWLYTO RELEASESTRUT
PRESSURE(AS APPLICABLE).
Air-oilshock struts,incorporatedin each landinggear oleo assembly,absorb shockfrom wheel impact
on runwayduring landing.
NOTE: Serviceand adjuststruts per placardon strut.
N. FillingOleo Struts
Fill oleo strut completelyas follows:
1. Place airplaneon jacks (Referto 7-10-00).
2. Place pan under gearto catch spillage.
3. Openair valve slowlyor depressvalvecore pin (as applicable)to releasestrut pressure.
4. Removevalvecore pin.
5. Attach clear plastictube to valvestem. Place oppositeend of tube in hydraulicfluid filled
container.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
N. FillingOleo Struts (continued)
NOTE: An airtightconnectionis necessarybetweenplastictube and valvestem. Withoutan
airtightconnection,a small amountof air is drawn intooleo strutduring eachsequence,
resultingin inordinateamountof air bubblesand prolongedfilling operation.
6. Extendoleo strut by pullingdownon wheeland drawingfluid into oleostrut. Continue
compressingand extendingoleo strut until it is full of fluid and air bubblesceaseto appearin
plastictube.
7. Slowlycompressstrut to fully compressedposition.
8. Removeplastic tube. Reinstallvalvecore (if applicable).
9. Inflateoleo strutsaccordingto informationin Figure 12-2.
10. Tightenair valve (if applicable).
NOTE: For accurateoleo strut inflation,the aircraft mustbe placed on jackswith the weightof
the aircraftoff of the wheels.
O. InflatingOleo Struts
Ensureoleo strut containssufficientfluid (describedin LandingGear Oleo Struts). Attachstrut pump
to air valveand pump up oleo strut. Beforecappingvalve,checkfor valvecore leakage.
MAINGEAR
FORSERVICE
INSTRUCTIONS
MANUALFOR
(SEEMAINTENANCE
SERVICINGWITH MIL - H - 5606
(RED)HYDRAULICFLUID).WITH
NO LOADON STRUT,INFLATETO
435 psi.
NOSEGEAR
FORSERVICE
INSTRUCTIONS
MANUALFOR
(SEEMAINTENANCE
SERVICINGWITH MIL - H - 5606
FLUID).WITH
(RED)HYDRAULIC
NO LOADON STRUT,INFLATETO
350psi.
ServicingLandingGearShockStruts
Figure 302
EFFECTIVITY:
040-999
12-10-00 Jan 0/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
P. Tires
Tubelesstiresare designedto permitanyair or nitrogenthatis trappedin thecordsorthat diffuses
throughthe linerto escapethroughspecialsidewallvents.Thisventingpreventspressurebuild-up
withinthecordbodywhichmightcausetread,sidewallor plyseparation.Discounting
tire growthafter
initialinflation,oncethetire hasbeeninflated,themaximumpermissible
pressuredropdueto diffusion
is5% in any24 hourperiod.
Vent holes penetratethe sidewallrubberto, or into,the cord bodyand may vary in size, depth and
angle. Therefore,the amountof diffusionthroughthese holeswill vary.
Whenwater or a soapsolution is brushedover the outsideof an inflatedtubelesstire, bubblesform.
Somevents may emit a continuousstreamof bubbles. Othersmayproduceintermittentbubbles. And
some maynot bubbleat all. This variety is normal and doesnot mean that there is anythingwrong
with the tire. In fact, as long as a tubelesstire is inflated,there will be some diffusionfrom the vents.
Whenthe loss rate exceeds5% in 24 hours, recheckfor possibleinjuries. Ventsshould remainopen,
so check periodicallyto make sure they havenot been coveredover or closedby tire paintor spilled
solvent. And since vents may be coveredduring retreading,checkfor evidencethat your retreads
havebeen revented.
Severalbasiccharacteristicsof tubelessaircrafttires may be mistakenfor problems:
1. Tire growthin the first 12 to 24 hours after inflationwill resultin a seeminglyseverepressuredrop.
Simply inflate,wait for another24 hours,then checkpressure. It will probablybe within specs.
2. Make sure that initial inflationis to recommendedoperatingpressureto ensurefull tire growth.
3. It is normalfor tubelesstires to showa small amountof pressureleakagethroughoutthe life of the
tires.
Maintaintires at pressurespecifiedin Chart601, 6-00-00. Whencheckingtire pressure,examinetires
for wear,cuts, bruises, and slippage. Apply Age-Master#1 to tires to protectagainstozone attackand
weatheringas follows:
1. Cleanoil and grease from all tire surfaces.
2. Apply singleheavycoat usingbrush at 0.4 - 0.5 fluid ouncesper square foot. Cover surface
completelyand evenly;allow to dry for 5 - 10 minutes.
3. Apply secondcoat per step2; allow to dry for 20 - 30 minutesbefore handling.
4. Removeagent on wheel assemblywith cleaningsolvent.
5. Apply as conditionsdictate.
Q. HydraulicPowerPack
Checkhydraulicpowerpackreservoirfluidlevelevery50 hoursandfill asrequired.Specialfillingand
drainingservicehookupis installedinsiderightfuselageaccesspanelof nosesection.A pressurepot
component
by removing
panel,openingaccessin hydraulic
or hydraulictestunit canbe connected
coversandprotective
capon suction;fill anddrainfitting. Connectfluidsupplylinefromsupplysource
supporthydraulic
fluid
to fitting. Raiseleverto openvalveandfill reservoir.Togravityfill reservoir,
isfull whenfluidreachesfull
supplycontainerhigherthanfluidlevelin powerpackreservoir.Reservoir
lineon transparentreservoirs.Besureto closesuction;fill anddrainvalvebyplacingleverin down
positionbeforedisconnecting
supplylinefromfitting. Reinstallprotective
caponfitting,closeaccess
in hydrauliccomponents
cover,andinstallaccesspanel.
EFFECTIVITY:
040-999
Jan 10/90
12-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
R. Propellers
Checkblades periodicallyfor damage. Minor nicksin blade leading edgesmustbe filed out and all
edges rounded. Daily inspectionmustincludeexaminationof blades and spinnerfor visible damage
and greaseleakage. For furtherinformationon servicingpropeller,refer to Chapter61 / AC 43.13-1A,
SectionIII on propellerrepairing.
S. EngineLubrication
CAUTION: DO NOT MIX DIFFERENTBRANDSOR SPECIFICATIONS
OF OIL. CHEMICAL
STRUCTURESCAN DIFFER,MAKINGOILS INCOMPATIBLE.
Checkengineoil level within ten minutesafter engineshutdown. If engineis stationaryfor 12 hoursor
more; start it, run at idle for minimum2 minutes,shutdown,and checkoil not morethan 10 minutes
later. For enginesoperatedin corporateor utilityaircraftwith typical usageof 50 hoursper monthor
less, changeoil every400 hours of 9 months,whicheveroccurs first. For enginesoperatedin high
utilizationcommuterairlines,basicoil changeperiodsare 800 hoursfor 7 1/2 centistokeoil, or 1200
hours for a 5 centistokeoil, or 9 months. Extensionsbeyondbasicoil change periodare considered
providedoil is monitoredby spectrometricoil analysisand a written requestis submittedto Pratt &
WhitneyCanadaLimitedServiceDepartment.Whenoperationresults in frequentcold soakingat
ambienttemperaturesof 0°F (-18°C)or lower,use 5 centistokeoil. For further information,consult
latest Pratt& WhitneyServiceBulletin13001.
Whenchangingbrandor type of engineoil, flush lubricationsystem. Referto drainingengineoil
sectionfor properprocedure.
T. EngineOil Level Check
CAUTION: IF OIL LEVELIN TANK IS BELOWBOTTOMOF DIPSTICK,DETERMINECAUSETO
TROUBLESHOOT.IF NEITHERFLUCTUATINGOR LOW OIL PRESSURE
READINGSARE NOTICED,CHECKFOR EXTERNALLEAKSAND OIL FILTER
CONTAMINATION.CLEANOIL FILTERAND FILL OILTANK TO RECOMMENDED
LEVEL. RECORDOIL QUANTITYADDED,COMPLETE15 MINUTEENGINERUN,
AND RECHECKOIL QUANTITYAND CONDITIONOF OIL FILTER. IF BOTHARE
SATISFACTORY,
NO FURTHERACTIONIS NECESSARY.OTHERWISE,REFERTO
ENGINEMAINTENANCEMANUAL.
Within 10 minutesfollowingengineshutdown,unlockfiller cap at 11o'clock positionon accessory
gearboxhousing. Checkcontentsof tank againstmarkson dipstickand fill to requiredlevel.
NOTE: Normaloil level is one quart belowmaximumlevel. Do not fill oil tank morethan one quart
below maximummark.
EFFECTIVITY:
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12-10-00
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
U. EngineOil Chip Detector
The magneticchip detector,locatedin the same place as the drain plugon the reductiongearbox,is
connectedelectricallyto the annunciatorpanel lights. Illuminationof chip detectlight on annunciator
indicatesmetalcontaminationin oil system. If chip detectlight illuminates,removechip detectorand
inspectmagneticpole piecesfor contaminate. Referto Pratt& WhitneyPT6A-61Maintenance
Manual,P/N 3034342,Chapter79.
NOTE: When chip detectoris removedfor inspection,also inspectoil filter.
1. Removalof Chip Detector
(a) Removewiring from chip detector.
(b) Removechip detectorfrom gearboxand discardpreformedpacking.
2. Inspectionof Chip Detector
(a) If a singlechain of magneticparticlesbridgesgap across detectorpoles and particlesconsists
of small slivers,clean chip detectorby wipingwith lint-freecloth and reinstall.
(b) If more than 10 piecesof small, nuggetshapedmagneticmaterialsexist on detector,send
engineto overhaulfacility for inspection.
(c) If small amountof fuzz (poweredmaterial)exists,clean detectorand reinstall. Recheckfor
continuityafter 10 hours of operation.
(d) If same amountof fuzz is found again,cleandetector,reinstall,and makeanothercontinuity
check after another10 hoursof operation.
(e) If fuzz is found a third time with similaror greaterquantities,ship engineto overhaulfacilityfor
inspection.
3. Installationof Chip Detector
(a) Installchip detectorwith newpreformedpackingin boss on reductiongearbox.
(b) Tightenand torque the detectorto 45 - 55 inch-pounds.
(c) Connectplug and safety.
V. DrainingEngine Oil
1.
2.
3.
4.
Removeenginecowlingand placesuitablecontaineror drip pan under engine.
Removechip detectorat 6 o'clock positionon frontcase of reductiongearbox.
Removedrain plug at 6 o'clockpositionon accessorydrive gearbox.
Removedrain plug from oil tank drain line.
NOTE: Whenoperatingengineon oil which differsfrom that previouslyused,or if oil systemis
contaminatedby other metallicmatter,proceedwith steps5 through 18. If using sameoil
and no contaminationexists,proceedonly with steps7, 8, 17, and 18.
EFFECTIVITY:
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Jan
PIPERAIRCRAFT
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MAINTENANCEMANUAL
V. DrainingEngineOil (continued)
5. Removedrain plug from oil-to-fuelheater.
CAUTION: LIMIT ENGINEROTATIONTO MINIMUMTIME REQUIREDTO ACCOMPLISH
COMPLETEDRAINING. DO NOT EXCEEDSTARTERTIME LIMITS (30SECONDS
ON, 1 MINUTEOFF,30 SECONDSON, 1 MINUTEOFF,30 SECONDSON, 30
MINUTESOFF).
6. With drainsopen and ignitionand conditionleveroff, motor enginewith starteronly; allow
scavengerpumpsto clear all lubricatingoil.
7. Installnewpreformedpackingson chip detectorand plugs.
8. Reinstallchip detectorand drain plugs. (Referto t00-00for torquevalues.)
9. Refilloil tankwith specifiedoil. (See latestrevisionof Pratt & WhitneyServiceBulletin13001.)
Normaloil lever is one quart below maximumlevel (hot). Overfilling causesexcess oil to flow
throughaccessorygearboxbreather.
10. Start engineand run at idle speedfor minimum2 minutes.
11. Featherpropellerand shut down engine.
12. Repeatsteps 1 through 6.
13. Removeand clean mainoil filter.
14. Removeand clean reductiongearboxoil strainer.
15. Reinstallall enginedrain plugs and chip detector;tighten,torque, and lockwire. (Referto 91-0000 for torque values.)
16. Repeatsteps 7 through 10.
17. Checkoil level; replenishas required.
18. Installfiller cap and dipstickassemblyin filler tube. Ensurecap is correctlyinstalledand locked
securely.
W. ServicingOil Filter Elements
CAUTION: PLUGBOTH ENDS OF FILTERELEMENTBEFORESUBMERGINGIN VARSOL
CLEANED,
CLEANER. THE ELEMENTMUSTNEVERBE ULTRASONICALLY
PRESSUREFLUSHED,OR DRIEDWITHCOMPRESSEDAIR CAUSINGDAMAGETO
FILTERMEDIA.
Oil filter elementsmust be cleanedevery100 hours. Removeand inspectfor foreign materialand
handflush in petroleumsolvent(AMS3160 Varsol)bath to removelight contaminantscollectedon
externalprotectivescreening. Servicelife of filter elementis 1000 hours.
If cleaningmethodpreviouslydescribedprovesineffective,clean filter elementelectrosonically.
1. Plug openingsat eachend of filter elementwith suitableplasticor rubberplugs.
2. Place filterelement in electrosoniccleanertank.
3. Add sufficientquantityof cleaningsolventto tank. (Approximately1/4 inch belowtop edgeof
tank.)
4. Operateunit for 10 minutes.
5. Rotateelement(end-to-end)180° in cleaningtank and operateunit for additional10 minutes.
NOTE: Adjust cleaningdurationdependingon conditionof element. For best results,replace
cleaningsolventevery20 minutes.
6. Removeelementfromtank usingclean, lint-freegloves; removeplugs.
7. Placeelementin clean locationand allowto dry.
8. After elementis cleaned,inspectwith magnifyingglassfor clogged passagesand brokenwires. If
more thanfive percentof visible passagesare clogged,return elementto overhaulfacility. If dents
or brokenwires are found, replaceelement.
9. InstallnewO-ringson filter elementwhetherelementis cleanedor new.
10. Insertfilter element(perforatedflangefirst) intofilter housing in compressorinlet case.
EFFECTIVITY:
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W. ServicingOil Filter Elements(continued)
11. Install new O-ring on filter cover.
NOTE: Ensureteflon spaceris in positionon filter coverstuds.
12. Installfilter cover and securewith four plainwashersand self-lockingnuts. Tightennuts and
torque to 24 - 36 inch-pounds.
13. Cleandual drive oil filter every 100 hours.
(1/4
Plug
CleaningTank
NOTE: ElectrosonicCleanerTankmay be procuredfrom:
AerosupportInternational,Inc.
75 de la Moselle
St. Lamber, Quebec
J45 1W3 Canada
P/N Sonac S-2
ElectrosonicCleaningTank
Figure 303
12-10-00
Jan
10/90
Jan 10/90
12-10-00
EFFECTIVITY:
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X. Recommendations
For ChangingOil
NOTE: Referto Pratt & WhitneyServiceBulletinNo. 13001.
1. Major factorsconcerningoil changefrequencyare enginemechanicalcondition,spectrometer
analysisof used oil, climaticconditions,dust and sand ingestionduringtakeoff and landingroll,
engineusage,and shelf life limitationsof syntheticlubricants.
2. Wheneveroil is changed,removeand check oil filter elementfor metalparticles. Clean,reinstall,
or replacedependingon time in service. (SeeServicingOil Filter Elements.)
3. Only useoils listedin Pratt& WhitneyServiceBulletinNo. 13001.
CHART 1
THREADLUBRICANTS
TYPE OF LINE
TYPE OF LUBRICANT
Brake
Deicer(Air)
MIL-H-5606
TT-A-580(JAN-A-669),Anti-SeizeCompound
(White Lead Base)
MIL-T-5544,Anti-Seize,GraphitePetrolatum
MIL-G-6032,LubricatingGrease(Gasolineand
Oil Resistant)
MIL-T-5542,ThreadCompound,Anti-Seizeand Sealing,
OxygenSystem
TT-A-580(JAN-A-669),Anti-SeizeCompound
(WhiteLead Base)
C5-AHigh TemperatureAnti-SeizeCompound
Fuel
Oil
Oxygen
Pitot and Static
Engine- BleedAir
NOTE: Lubricateenginefittingsonly with fluid containedin particularlines.
Y. OxygenSystem
Breathingsystemoxygen is furnishedfrom a stationarycylinderin the aft sectionof the forward
compartment.Serviceand maintenanceinstructionsfor the oxygen systemis found in 35-00-00.
1. OxygenSystemSafety Precautions
WARNING: FOREIGNMATTERIN HIGH PRESSURELINESCAN CAUSEAN EXPLOSION.
WHEN COMINGIN CONTACTWITH OXYGENEQUIPMENT,KEEP HANDS,TOOLS,
AND CLOTHINGCLEAN.
Use extremecautionwhen servicing,handling,and inspectingthe oxygen system. Complywith
the followingprecautions:
(a) Keepoxygen regulator,cylinder,gauge, valve,fittings,masks,and all otheroxygensystem
componentsfree of oil, grease,fuel, and other readilycombustiblesubstances.
(b) Do not allowforeign matterto enteroxygen lines.
(c) Neverattemptto repairor repaintoxygen equipment.
(d) Keepfire and heat awayfrom oxygenequipment. Do not smokewhen workingwith or near
oxygenequipment. Do not generatesparkswhen usingtools.
(e) Neverallow electricalequipmentto contactoxygen cylinder.
(f) Useonly thread compoundapprovedunderMIL-T-5542on oxygensystems. Applyonly to first
threadof malefittingsto preventthread seizure.
EFFECTIVITY:
040-999
12-10-00 PAGE13
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Y. OxygenSystem(continued)
2. FillingOxygenCylinder
The oxygen systemfiller valve is accessiblethrougha door on left side of nosesection.
NOTE: If airplaneoxygen pressureis below50 psi, purgesystemas describedin 35-10-00.
(a) To fill oxygen cylinder,open accessdoor,removecap from filler valve, and attachfiller hoseof
oxygen rechargeunit to filler valve. Ensureall fittingsare free of oil, grease,dirt, etc.
(b) When using rechargeunit containingone supplycylinder,slowlyopen supplyunit valve and
allowoxygen to transferuntil cylinderservicepressureis reached. Ambienttemperaturemust
be consideredwhenfilling oxygencylinders. See Chart 2, IndicatedOxygenCylinder
Pressuresvs. AmbientTemperature.
(c) When using rechargeunit containingtwo or more supplycylinders(cascadestoragesystem),
proceedas follows:
(1.) Beforeopeningany valves,check remainingpressurein airplaneoxygencylinder. If partly
charged,note pressureindicatedon cylindergauge. Openand close eachvalve on
cascadestoragesystemand determinewhichcylinderhas lowestpressure. If this
cylinderhas pressurelowerthan oxygencylinderin airplane,do not attemptto fill it. Use
storagecylinderwith pressurehigherthan airplanecylinder,but lower than all others.
(2.) Openvalve only on storagecylinderwith lowestpressure. When indicatedpressureon
airplaneoxygengauge and charginggauge is equal,closestoragecylindervalve.
Proceedto storagecylinderwith next higherpressureand repeat procedure.
(3.) After adjustinglast storagecylinder,if oxygensystemis still not fully chargedthen place
full storagecylinderin place of cylinderwith lowestpressure.
(4.) Oxygenwill remainin large cylindersused in cascadesystemsafterfilling only one
cylinder. Suchremainingoxygen is at a pressureless than 1800 pounds,which is not
sufficientto completelyrefill anotheraircraftcylinder.
(5.) Do not rechargethree or four-cylindercascadesystemswith oxygen at lessthan 300 psi
pressurein 300 cubicfoot bank of cylinders. Use 300 cubicfoot cylindersto
approximately300 psi and returnfor refilling. In two-cylindersystems,useto
approximately600 psi and returnfor filling. (See Chart 2, indicatedOxygenCylinder
Pressuresvs. AmbientTemperatures.)
WARNING: BLEEDPRESSUREFROMFILLERHOSE BEFOREDISCONNECTING
FROM FILLERVALVE.
(d) Whenpressuregaugeon rechargeunit or in airplanereachesappropriateservicepressure
(Chart 3), close pressurevalveon rechargeunit. Disconnectfiller hosefrom filler valve;
replaceprotectivecap on filler valveand closeaccessdoor.
NOTE: This table accountsfor about 25° raise in temperaturedue to heat of compressionand
presumescylindersare filled at maximumrate.
EFFECTIVITY:
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Page
14 12-10-00
12-10-00
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
Y. OxygenSystem(continued)
2. FillingOxygenCylinder(continued)
CHART 2
OXYGEN CYLINDER FILLING PRESSURES VS. AMBIENT TEMPERATURE
- °F
AmbientTemperature
Filling Pressures - Psig
0
10
20
30
40
50
60
70
80
90
100
110
120
130
1650
1700
1725
1775
1825
1875
1925
1975
2000
2050
2100
2150
2200
2250
NOTE: Pressuresare not exact, but accurateenoughfor workingpressuresbetween1800 to 2400
psig cylinders.
CHART 3
INDICATED OXYGEN CYLINDER PRESSURES VS. AMBIENT TEMPERATURE
Ambient Temperature- °F
Indicated Cylinder Pressure - Psig
110
100
90
80
70
60
50
40
1980
1935
1890
1845
1800
1755
1710
1665
EFFECTIVITY:
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A. Scheduled
Servicing
1. AirframeLubrication
Properlubricationproceduresare valuablefor prolongingthe service life of the airplaneand as a
meansof reducingthe frequencyof extensiveand expensiverepairs. The periodicapplicationof
recommendedlubricantsto relevantbearingsurfacescombinedwith cleanliness,as detailedin the
followingparagraphs,ensuresmaximumefficiencyand utmost serviceof all movingparts.
Lubricationinstructionregardinglocations,time intervals,and type of lubricantsusedare found in
properlubricationcharts. Toensurethe best possibleresultsfrom lubricantapplication,observe
the followingprecautions:
(a) Useonlyrecommended
lubricants.Wheregeneralpurposelubricating
oil isspecified,but
unavailable,
cleanreciprocating
engineoil is a satisfactory
substitute.
(b) Checkcomponents
for evidence
of excessive
wearandreplaceas necessary.
(c) Removal
all excesslubricants
fromcomponents
to preventcollectingdirtandsandin quantities
capableof causingexcessive
wearordamageto bearingsurfaces.
2. Applicationof Grease
Whenlubricatingbearingsand bearingsurfaceswith a grease gun, ensuregun is filled with new,
clean greasespecifiedfor the particularapplicationbeforeapplyinglubricantto greasefittings.
(a) If a reservoiris not providedarounda bearing,apply lubricantsparinglyand wipe off excess.
(b) Removewheel bearingsfromwheelhub and clean thoroughlywith suitablesolvent. When
repackingwith grease,ensurelubricantenters spacebetweenrollers in retainerring. Do not
packgrease intowheel hub.
(c) Use extra care when greasingHartzellpropellerhub to avoid blowingclampgaskets. Remove
one greasefitting while applyinggreaseto otherfitting. Unevengreasingeffectspropeller
balance.
3. Applicationof Oil
If specificlubricationinstructionsfor certaincomponentsare not available,observethe following
precautions:
CAUTION: AFTERTHOROUGHLY
WASHINGAIRPLANE,ENSURELANDINGGEAR,
FLIGHTSURFACEWINGS,FLAPTRACKS,ELEVATORTRIM SCREW,AND
ENGINECOMPARTMENT
ARE STILL PROPERLYLUBRICATED.
(a) Applyoil sparingly.Neverapplymorethanenoughto coatbearingsurfaces.
(b) Sincecontrolcablesaresufficiently
coatedby manufacturer,
additionalprotectionforcorrosion
prevention
is unnecessary.
EFFECTIVITY:
040-999
PAGE1
12-20-00
12-20-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. LubricationCharts
WARNING: KEEPJET FUELSAND LUBRICATINGOILS OFF OF SKIN.
CAUTION: DO NOT USE HYDRAULICFLUIDWITH CASTOROIL OR ESTERBASE.
CAUTION: DO NOT APPLY LUBRICANTTO RUBBERPARTS.
Lubricationchartsconsistsof individualillustrationsfor variousaircraftsystemswith components
referencedby numbersand by type of lubricationand frequencyof lubricationin hours. Special
instructionsare listedat the beginningof lubricationchart and are referencedon each particularchart.
NOTE: Lubricatepilot and passengerseatstrack rollersand stoppins as requiredusing general
purpose,low temperaturelubricatingoil (MIL-L-7870).
NOTE: Wheel bearingsrequirecleaningand repackingafterexposureto excessivequantityof water.
CHART 1
SPECIALINSTRUCTIONS
(1) Cleanexteriorof bearingsand bushingswith dry solventbeforerelubricating.
(2) Disassembleoil coolerdoor, ice protectiontransmission,and screws. Trim screws
and wheel bearings; clean with dry solvent. When reassemblingtransmission,
lubricateand apply thin coating to screw.
(3) Fill oleo struts, powerpack reservoir,and brake reservoirper instructionson unit or
containeror containeror refer to 12-10-00.
(4) Removeone of two propellergrease fitting for each blade. Apply grease through
fitting until fresh grease appearsat holeof removedfitting.
(5) Wipe all lubricationpointsclean of old grease,oil, dirt, etc, beforerelubricating.
(6) Clean or replace oil filter element (refer to 12-10-00)after usage of 50 hours or
less. Change engine oil every 400 hours or 9 months, whichever comes first.
(Refer to latest Pratt & WhitneyCanada Service Bulletin No. 13001 for a list of
approvedoils.)
(7) Loosenboot from gear lock assemblyand greasecable.
EFFECTIVITY:
040-999
12-2O-00
PAGE22-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. LubricationCharts(continued)
CHART 2
LUBRICATIONCHART(LANDINGGEAR, MAIN)
COMPONENT
LUBRICANT
FREQUENCY
1. GEARDOOR,OUTBOARD,HINGESANDCONTROLRODS,RIGHTAND LEFT
MIL-L-7870
100HRS
2. GEAROLEOSTRUTFILLER,RIGHTANDLEFT;COATPISTONTUBEAS NECESSARY
MIL-H-5606
AS REQUIRED
3. GEARCONTROLROD ENDSAND BELLCRANK
BOLTS,RIGHTANDLEFT
MIL-L-7870
100HRS
4. WHEELBEARINGS.RIGHTANDLEFT
MIL-G81322
100HRS
5. GEARDOWNLOCKANDUP LOCKHOOKS,GEARTORQUELINKFITTINGS,
RIGHTAND LEFT
MIL-G81322
100HRS
6. GEARSIDE BRACELINKBUSHINGANDHOUSINGBUSHING,MAINGEARDRAG
LINKASSY,TORQUE LINEASSY,RIGHTAND LEFT
MIL-G-83122
100HRS
7. GEARCONTROLROD ENDS,CYLINDEREND HOOK,RIGHTANDLEFT
MIL-L-7870
100 HRS
8. GEARDOOR,INBOARD,HINGESAND CYLINDERENDS,RIGHTAND LEFT
MIL-L-7870
100HRS
9. BRAKEAND POWERPACKRESERVOIR
MIL-H-5606
AS REQUIRED
10. GEARLOCKCABLEASSEMBLY(Referto SpecialInstructions#7,12-20-00, Page2)
MIL-G-81322
100HRS
5
5
10
6
8
1
2
5
4
MainLandingGear
Figure 301
EFFECTIVITY:
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12-20-00
PAGE
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PA-42-720(AdvancedTrainer)
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B. LubricationCharts(continued)
CHART 3
LUBRICATIONCHART(LANDINGGEAR,NOSE)
COMPONENT
LUBRICANT
FREQUENCY
1. NOSEGEAROLEOSTRUTFILLER
MIL-H-5606
AS REQUIRED
2. STEERINGARM ROLLERSBELLCRANKRETRACTION
ROD ENDSANDSTEERINGROD ENDS
MIL-L-7870
100HRS
3. NOSEGEAR DOORACTUATOR,RETRACTIONROD
ENDAND CYLINDERROD END
MIL-L-7870
100HRS
4. UP LOCKHOOKAND UP LOCK ROD
MIL-L-7870
100HRS
5. DOORHINGEBOLT
MIL-L-7870
100HRS
6. DRAGLINKASSEMBLYAND IDLERLINK
MIL-G-23827,
MIL-G-7711A
100 HRS
MIL-G-3545C,
MIL-G-7711A
100HRS
MIL-G-23827,
MIL-G-7711A
100 HRS
9. UPPERAND LOWERTORQUELINKCONNECTING
BOLTANDSHIMMYDAMPENER
MIL-G-23827,
MIL-G-7711A
100 HRS
10. GEARHOUSINGBUSHINGS
MOLYKOTENO.33 100HRS
11. NOSEGEARSTEERINGCONTROLROD ENDS
MIL-L-7870
100 HRS
12. NOSEGEARUP LOCKCABLEASSEMBLY
(Referto SpecialInstructions#7, 12-20-00,Page2)
MIL-G-81322
100 HRS
13. NOSEGEARSTEERINGGREASEFITTING
MIL-G-23827
100 HRS
7. WHEELBEARINGS
8. UPPERAND LOWERTORQUELINKS
11
2
4
6
9
11
NoseLandingGear
Figure 302
EFFECTIVITY:
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B. Lubrication
Charts(continued)
CHART 4
CHART(CONTROLSYSTEM) (Sheet1 of 3)
LUBRICATION
FREQUENCY
LUBRICAN
COMPONENT
1. AILERONTRIMSCREW
MIL-G-7711A
MIL-G-23827,
500 HRS
2. AILERONTRIMTABHINGSANDCONTROLRODENDS
MIL-L-7870
100 HRS
3. RUDDERTRIMSCREW
MIL-G-23827,
MIL-G-7711A
500 HRS
4. RUDDERANDRUDDERTRIMTAB HINGESANDCONTROLRODENDS
MIL-L-7870
100HRS
5. ELEVATORANDELEVATOR
TRIMTABHINGESANDCONTROLRODENDS
MIL-L-7870
100 HRS
6. AILERONHINGES,RIGHTANDLEFT
MIL-L-7870
100 HRS
7. FLAPTRANSMISSION
PIVOTBOLTSANDSENDERARM
MIL-L-7870
100 HRS
8. FLAPTRACKS,RIGHTANDLEFT
ALL PURPOSESLIPSPRAY
50 HRS
9. FLAPTRACKROLLERS,RIGHTANDLEFT
(DUPONTNO.6611)
MIL-L-7870
100 HRS
10.AILERONBELLCRANK
CABLEENDS,PIVOT
BEARINGANDCONTROLRODENDSRIGHTANDLEFT
MIL-L-7870
100 HRS
11.TRIM SCREWS
MIL-G-3278ORMIL-G-23827
500 HRS
12.TRANSMISSIONSCREWS,RIGHTANDLEFT
MIL-G-23827
100 HRS
13. ELEVATOR
TRIM SCREW
MIL-S-8660B
OR
(DOWCORNING4 COMPOUND
100 HRS
14. ELEVATORDOWNSPRING
MIL-C-16173D
CorrosionRetardant
(Referto 91-00-00)
100 HRS
ControlSystem
Figure 303 (Sheet 1 of 3)
EFFECTIVITY:
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PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. LubricationCharts (continued)
CHART 4
LUBRICATIONCHART(CONTROLSYSTEM) (Sheet2 of 3)
View A
View B
13
View E
14
View F
ControlSystem
Figure303 (Sheet2 of 3)
EFFECTIVITY:
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Jan 10/90 122
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PIPER AIRCRAFT
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MAINTENANCE MANUAL
B. Lubrication
Charts(continued)
CHART 4
LUBRICATIONCHART(CONTROLSYSTEM) (Sheet3 of 3)
COMPONENT
LUBRICANT
FREQUENCY
1. AILERONBELLCRANK
ASSEMBLYBUSHING
MIL-L-7870
100 HRS
2. CONTROLWHEELCHAIN,VERTICALANDHORIZONTAL
MIL-L-7870
500 HRS
3. RUDDERPEDALS,TORQUETUBEBEARINGSANDBLOCK,CONTROL
CABLEENDS,BRAKECYLINDERENDS,ANDPULLEYS
MIL-L-7870
100 HRS
2
View G
View H
ControlSystem
Figure 303 (Sheet3 of 3)
EFFECTIVITY:
040-999
12-2
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PAGE
7
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. LubricationCharts(continued)
CHART 5
LUBRICATION CHART (POWERPLANT, PROPELLER & REVERSING LINKAGE)
LUBRICANT
FREQUENCY
1. ZERKFITTINGS,BLADEHUB(2 PERBLADE)
COMPONENT
MIL-G-23827
100 HRS
2. FUELCONTROLUNIT INTERCONNECT
RODENDS
MIL-G-23827
100HRS
3. CONTROLCAMAND PINS
130A
LUBRIPLATE
100HRS
MIL-G-23827
100 HRS
4. PROPELLERCONTROLRODENDS
5. OIL FILTERELEMENT
REFERTO SPECIAL
12-20-00Page2
INSTRUCTION
6. OILTANK
REFERTO SPECIAL
INSTRUCTION
12-20-00Page2
7. PUSHPULLCONTROL- WIREROPE
MIL-G-21164
100HRS
NOTE:
Referto HartzellService
Letter No. 61A
1
PROPELLER
NOTE
SPECIALINSTRUCTIONS
Cleanor replaceoil filter elementat eachoil drainperiodas described
in 79-00-00. In aircraftwith a typicalutilizationof 50 hours/monthsor
less, changeengineoil every 400 hoursor 9 months,whichevercomes
first. Referto Prattand WhitneyServiceBulletinNo. 13001for a list
of approvedoils.
4
4
3
CARBON
BLOCK
WIPE CLEAN
VIEW A
Power Plant,Propeller,and ReversingLinkage
Figure 304
EFFECTIVITY:
040-999
Jan
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Jan 10/12-20-00
PIPERAIRCRAFT
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MAINTENANCEMANUAL
B. LubricationCharts (continued)
CHART 6
LUBRICATIONCHART(AIR INLETICE PROTECTIONAND OIL COOLERDOORS)
COMPONENT
LUBRICANT
FREQUENCY
1. TRANSMISSION
ASSEMBLY
DUKES2196-74-1
500 HRS
2. TRANSMISSION
SCREW
MIL-G-23827
500 HRS
3. SLEEVEAND BOLTASSEMBLY
MIL-L-7870
100HRS
4. OIL COOLEREXHAUSTDOORHINGE
MIL-L-7870
100HRS
5. ICEDEFLECTORDOORHINGE
MIL-L-7870
100HRS
6. BYPASSDOORHINGE
MIL-L-7870
100 HRS
7. BEARINGBLOCKS
MIL-G-23827
100HRS
8. TRANSMISSION
SCREW
MIL-G-23827
500 HRS
9. TRANSMISSION
ASSEMBLY
DUKES2196-74-1
500 HRS
10.TRANSMISSION
MOUNTINGBUSHINGS
MIL-G-23827
500 HRS
11.CLEVISPIN
MIL-L-7870
100HRS
12. ICEDEFLECTORDOORRODENDS
MIL-L-7870
100HRS
13.CLEVISPINSANDBOLTASSEMBLIES
MIL-L-7870
100HRS
10
Air InletIce Protectionand Oil CoolerDoors
Figure 305
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B. LubricationCharts(continued)
CHART 7
LUBRICATION CHART (CABIN DOOR, BAGGAGE DOOR, AND SEATS)
COMPONENT
LUBRICANT
FREQUENCY
1. CABINDOORLATCHHINGESANDSTEPMECHANISM
MIL-L-7870
100 HRS
2. CARGODOORLATCHANDHINGES
MIL-L-7870
100 HRS
3. NOSECONEANDFORWARDBAGGAGEDOORHINGESANDLATCHES
MIL-L-7870
100 HRS
4. NACELLELOCKERAND ENGINECOWLDOORLATCHANDHINGES
MIL-L-7870
100 HRS
5. SEATTRACKS(ALL)
MIL-L-7870
100 HRS
4.
5
2
4
4
3
CabinDoor,BaggageDoor,and Seats
Figure 306
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PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. UnscheduledServicing
1. EngineAccessoryDriveShafts - Lubrication
Lubricateaccessorydrive shaftsaccordingto Pratt & WhitneyMaintenanceManual,P/N 3021442,
page 204.
Chapter70, StandardPractices,GeneralTorqueRecommendations,
Specificaccessoriesare:
(a) Tachgenerators.
(b) Hydraulicpumps,fuel pump.
Do not apply lubricantto the followingaccessories:
(a) Fuel pumps(P&W).
(b) Propgovernors(CSU).
(c) Fuelcontrol units.
Installoverspeedgovernorwith dry shaftor lubricatewith cleanturbine engineoil.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER 20
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER 20 - STANDARD PRACTICES / AIRFRAME
TABLE OF CONTENTS
SUBJECT
CHAPTER
20-00-00
General
StandardPractices- Airframe
TorqueWrenches
FlarelessTube Assemblies
CorrosionInhibitingCompound
ApplicationSafety
ApplicationTips
Access Locations(Elevator)
Access Locations(Wing and Fuel CellArea)
Access Locations(WingFlap and Aileron)
Access Locations(EngineNacelle)
Access Locations(Rudderand RudderTrimTab)
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CONTENTSan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
StandardPractices- Airframe
A. General
This chaptercontainsgeneralinformationpertainingto standardaircraft hardwareinstallationand
removalpractices.
includedwillbe veryhelpfulif it is referredto on a regularbasis.
Theinformation
method.
testingis neededafterrepairof 4130steel,usethe magnaflux
Ifnon-destructive
aluminumpartsmaybe donebythe dye
castingsandmachined
of aluminum
Testingandinspecting
penetrantmethod.
Usually,a goodvisual inspectionwith a 10X magnifyingglass will showany damageor defectin a
repairthat is of a significantnature.
B. StandardPractices- Airframe
1. TorqueWrenches
Torquewrenchesshould be checkedand calibrateddaily with weightsand, a measuredleverarm
to ensurethat inaccuraciesare not present. Checkingone torque wrenchagainstanotheris not
sufficientand not recommended.Somewrenchesare quite sensitiveto the way they are
supportedduring a tighteningoperation. Any instructionsfurnishedby the manufacturermustbe
followed.
2. FlaredTubeAssemblies
Whenanyfitting containingconicalsealsis disconnectedthe followingsteps must be performed
when reconnectingthe fitting.
(a) Lubricatethreadsof nut with a substancecompatiblewith the fluid that is to be containedin the
line
(b) Installnew conicalseals
is brokenthesealsmustbe
NOTE: Conicalsealsareneverto be reused.If a connection
replaced.
NOTE: Applytorque on back portionof nut next to shoulderto minimizedistortionof thread.
CAUTION: ANGULAR MISALIGNMENT BETWEEN TUBE AND FITTING WILL OVERSTRAIN SLEEVE AND NUT DURING TORQUE -UP. APPLY TORQUE ONLY
AFTER TUBE CENTER LINE IS SQUARELY MATED TO THE FITTING CENTER
LINE.
(c) Tightenfitting one (1) to one and one half (1 1/2) hexflats from positionof sharp torquerise
(fingertight).
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B. StandardPractices- Airframe (continued)
37° FLAREDFITTING
CONICAL
SEAL
TUBE
NUT
SLEEVE
ConicalSeals
Figure 1
C. CorrosionInhibitingCompound
This sectioncontainsinformationnecessaryfor the applicationof corrosioninhibitingcompoundsto
the interior of the aircraft structure. Corrosioninhibitingcompoundis usedto supplementthe corrosion
protectionof primers,sealants,etc.
CAUTION: TO ENSUREPROPERAPPLICATION,MAINTENANCEPERSONNELMUST
THOROUGHLYFAMILIARIZETHEMSELVESWITH THE INFORMATIONAND
PROCEDURESFOUNDIN THE DINITROLA AVIATIONTECHNICALMANUAL
AND THE DINITROLAVIATIONTRAININGVIDEO.
1. ApplicationSafety
WARNING: CHARCOALFILTERBREATHINGMASKSSHOULDBE WORNWHENSPRAYING
IN ENCLOSEDAREAS.
CAUTION: PROTECTALL ELECTRICALEQUIPMENT,COMPONENTSAND CONNECTORS
FROMSPRAY.
CAUTION: PROTECTALL TUBINGANDOXYGENLINE FITTINGSAND ENDS FROM SPRAY.
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MAINTENANCEMANUAL
C. CorrosionInhibitingCompound(continued)
1. ApplicationSafety (continued)
CAUTION: PROTECTPLASTICS,CABLES,CABLE PULLEYS,DUCTING,TAPEAND OTHER
MISCELLANEOUS
EQUIPMENTFROM DIRECTSPRAY.
CAUTION: PROTECTOPENTYPE INSULATIONFROMSPRAYOR INSTALLAFTER
APPLICATION.
CAUTION: PROTECTALL AREASREQUIRINGADDITIONALFINISH,SEALING,BONDING
OR OTHEROPERATIONSREQUIRINGADHESIONTO SKIN, FROMSPRAY.
CAUTION: DO NOT REUSEOLD PLUGSAND OLD TAPE. REPLACEWITHNEW PLUGS
AND NEW TAPE.
CAUTION: WHEN INSTALLINGFUELBLADDERS,BE SURETHEREARE NO SHARPEDGES
THATCOULDPUNCTUREBLADDER.
2. ApplicationTips
(a) Removeinterioras requiredto accesssprayareas.
(b) Be sure surfacesto be coatedaredry and free of dust,dirt, debrisand excessivebuildupof oil
or grease.
(c) Use specialtool (Piper P/N 89123-02)to spray areasthat cannotbe reachedwith Dinitrol
accessories.
(d) Sounddampingtape, primerand sealantsmay be appliedbeforespraying.
(e) Applycompoundbeforecomponentssuch as radios,systems,rigging,lines,wiring, etc. have
beeninstalled.
(f) Applycompoundto joints,faying surfaces,fastenersand any other metalsurfacesof the
interiorof the aircraftstructurewherecorrosioncouldoccur.
(g) Applycompoundas receivedfromthe vendorwithoutthinning.
(h) Applycompoundto a thicknessof 0.8 mils. Avoid puddlingand thick or thin spotsas muchas
possible.
(i) The compoundwill dry tackfree in 1 to 1 1/2 hours. Completedryingwill require6 to 8 hours.
The compoundwill never set up hardlike paintor primer.
(j) Removecompoundwith naptha,chlorinatedhydrocarbonsor alkalinedegreasers.
CAUTION: DO NOT REUSEOLD PLUGSAND OLD TAPE. REPLACEWITHNEW PLUGS
AND NEW TAPE.
(k) Replaceall plugs,patch plates,tape, and accesscovers.
NOTE: Figures1 through5 on the followingspages showparticularsprayaccesslocationson
the aircraft that mayotherwisebe difficultto find.
NOTE: For further informationor to obtaina copy of the DinitrolAviationTechnicalManualor
the DinitrolAviationTrainingVideo,please contact DINOLInternationalat one of the
addresslisted in the vendorpublicationssection,of the Introduction.
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C. CorrosionInhibitingCompound(continued)
3. Access Locations
TRIMTAB
ELEVATOR
ELEVATOR
CorrosionInhibitingCompoundAccess Locations(Elevator)
Figure 1
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C. CorrosionInhibitingCompound(continued)
3. Access Locations(continued)
PANELSON
THROUGH
ACCESS
RECESS
AREA
SURFACE
CONTROL
MAINWINGINTERIOR
ACCESS
PANELS
INSPECTION
THROUGH
MAINFUEL
CELLLINER
ACCESS THROUGH PANELSON TOP
OF WING REMOVEFUELBLADDER.
AFT INBOARD
FUEL CELLLINER
CorrosionInhibitingCompoundAccessLocations(Wingand Fuel Cell Area)
Figure 2
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C. CorrosionInhibitingCompound(continued)
3. AccessLocations(continued)
WINGFLAP
TRIMTAB
AILERON
AILERON
CorrosionInhibitingCompoundAccessLocations(WingFlapand Aileron)
Figure 3
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C. CorrosionInhibitingCompound(continued)
3. Access Locations(continued)
NACELLE
BULKHEAD
ASSEMBLY
INTERIOR
REMOVE
AS NECESSARY
ACCESSFROM
UNDERNEATH
NACELLE
NACELLE
FLOOR
PAN
CorrosionInhibitingCompoundAccessLocations(EngineNacelle)
Figure 4
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C. CorrosionInhibitingCompound(continued)
3. Access Locations(continued)
RUDDERTRIMTAB
RUDDER
CorrosionInhibitingCompoundAccessLocations(Rudderand RudderTrim Tab)
Figure 5
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MAINTENANCEMANUAL
CHAPTER 21
LIST OF EFFECTIVE PAGES
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1
PA9PAGE
LIST OF
LISTOFEFFECTIVE
EFFECTIVE
PAGESJan
10/90
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PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER 21 - AIR CONDITIONING
TABLEOF CONTENTS
SUBJECT
CHAPTER
PAGE
21-00-00
Air Conditioning
General
1
1
21-20-00
1
1
5
5
5
5
Distribution
Descriptionand Operation
Removalof GroundCoolingFan
Installationof GroundCoolingFan
Removalof CheckValve Assembly
Installationof CheckValveAssembly
21-30-00
PressurizationControl
Descriptionand Operation
Troubleshooting(PressurizationSystem)
ComponentDetailedDescriptions
CabinPressureDump
PressurizationCheckwith Test Unit
PressurizationSystemCheckoutProcedure
GroundOperationCheck
Safety Precautions
PressurizationSystemFlightCheck
AbsolutePressureRegulatorRemoval
AbsolutePressureRegulatorInstallation
Outflowand/or SafetyValveRemoval
Outflowand/or SafetyValve Installation
Outflowand SafetyValveCleaning
Removalof Controller
Installationof Controller
ControllerFilter Replacement
1
1
2
9
13
13
17
17
19
20
24
24
25
25
25
26
26
26
21-40-00
Heatingand Cooling
General
Troubleshooting(EnvironmentalControlSystem)
ComponentDetailedDescriptions
Removalof PressureRegulatorand ShutoffValve
Installationof PressureRegulatorand ShutoffValve
Removalof Hot Air BypassValve
Installationof HotAir BypassValve
Removalof BleedAir Supply OverpressureSwitch
Installationof BleedAir SupplyOverpressureSwitch
Removalof CompressorDischargeSensingSwitch
Installationof CompressorDischargeSensingSwitch
1
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3
4
4
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5
5
5
5
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CHAPTER21 - AIR CONDITIONING
TABLEOF CONTENTS(continued)
CHAPTER
PAGE
21-60-00
TemperatureControl
Removalof Duct TemperatureSensor
Installationof Duct TemperatureSensor
Removalof CabinTemperatureSensorand Controller
Installationof CabinTemperatureSensorand Controller
1
1
1
1
1
21-70-00
Moisture/AirContaminantControl
Removalof Water Separator
Installationof WaterSeparator
Cleaning,Inspectionand Repairsof Water Separator
1
1
1
1
SUBJECT
EFFECTIVITY:
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CONTENTS
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
Air Conditioning
A. General
The cabinis pressurizedby enginebleed air that is conditionedby an environmentalcontrolsystem
(ECS). The bleed air is cooled as requiredfor heating,air conditioning,ventilationand pressurizing
the air in the cabin.
CAUTION: PERFORMPITOTAND STATICSYSTEMLEAKCHECKSBEFOREPERFORMING
ANY PNEUMATICFUNCTIONALTESTS. CONDUCTINGCABIN PRESSURETESTS
WITH LEAKINGSTATICSYSTEMSCOULDDAMAGEDELICATEINSTRUMENTS.
The environmentalcontrolunit (ECU)uses bleedair from both enginesas the prime sourceof energy.
This bleedair systemhasthree parts:
1. The ECUbleed air supply
2. The auxiliarybleed air supplyfor deicer bootsand gyros
3. The emergencybleed air cabin pressurizationsystem.
NOTE: To cap isobaricvalveambientlines,removeaccesscovers in the tail of the aircraft
and cap fittings(adapters)on aft pressurebulkhead.
(a) Thecompressorand interstageturbinebleed air from eachengineis suppliedthrougha
variableejector mixingvalvedirectlyto the ECU. A pressureregulatorand shutoffvalve
controlspressureand flow of bleedair intothe ECU, locatedin the right hand equipment
compartmentand forwardof fuselage station57.00 pressurebulkhead. Referto Heatingand
Coolingsectionsfor a more detaileddescriptionof variouscomponents.
(b) Auxiliarybleedair supplysystemis usedto operatethe cabin pressurecontrolsystem,
inflatablecabin door seals,surfacedeicerboots and vacuumgyro system. This bleed air is
takenoff the enginebleedair ductingupstreamof each bleedair shutoffvalve and cannotbe
shutoff unlessthat particularengineis shutdown. A ram air-bleedair intercooleris installedat
the firewallof each enginenacelleto cool the bleed air supplyto the auxiliarysystembelow
250°F,prior to enteringthe fuel tank area aft of the firewall. A bleedair overtemperature
°
switch,installedin the bleedair duct downstreamof the intercooler,closesat 425 ±5°F and
illuminatesthe BLEEDAIR HOT light on the pilot annunciatorpanel. Duringnormaloperation,
bleedair to the auxiliarysystemvaries between10 and 85 psi and/or 150°Fand 500F.
Temperatureis reducedto below250°F by the intercooler. Referto pressurizationcontrolfor
moredetail, 30-00-00for detailon the deicersystemand 37-00-00on the vacuumsystem.
(c) The emergencybleedair cabin pressurizationsystemconsistsof a solenoidshutoffvalve,jet
pumpand pressureswitch. The emergencybleedair is suppliedfrom the right hand auxiliary
bleedair supplyline and activatedby the pilot with the ECS SELECTORswitchon the comfort
controlpanel. With the ECSSELECTORswitchedintothe EMERposition,the emergency
pressurizationvalvein the right handwing root is opened. At the sametime,the pressure
regulatorand shutoffvalvede-energizes,shuttingoff bleed air flow to the ECU. The
emergencypressurizationair serves as motiveflow to the jet pump in the right handwing root,
whichpulls in ambientair from a port in the wing rootfairing. A total pressurizationflow up to 9
poundsper minuteis providedintothe right hand heaterduct,within the cabin,dependingon
the right hand enginepowersetting and altitude.
The emergencypressurizationvalveis automaticallyopenedwhen the cabin altitudeexceeds
12,000- 12,500feet, regardlessof the positionof the ECS SELECTORswitch. An absolute
pressureswitch in the cabin, set to activateat 12,000- 12,500feet, providesthis control. The
emergencypressurizationvalve is automaticallyopenedwhen the ECU is automaticallyshut
downdue to overtemperatureor overpressure.Referto PressurizationControl for more detail.
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A. Distribution
Bleedair isductedfromthe nacellefirewallto the ECUin theaircraftnose. Thecoolingair ventin the
wingrootfairingprovidesaflow pathoverboard
whena bleedcouplingO-ringfails. Thebleedmixing
capability
of thebleedair controlvalveassumesa lowerbleedair temperature
in theductingsystem
andeliminates
the needfor bleedductingcoolingflow.
Afterbleedair linespenetratethefuselageon eitherside,theyjoinat a Y-ductdownstream
froma
checkvalveinstalledin eachlegof the Y. Thesecheckvalvespreventreverseflow intoa nonoperatingengineor non-pressurized
ductsystemandpreventlossof cabinpressurization.
Theduct
fromthe Y-ductforwardto theforwardpressurebulkhead,
fuselagestation57.00,isshroudedand
ventedoverboard
at thebottomofthefuselage,withtheinletin the righthandequipment
compartment
at fuselagestation57.00bulkhead.
A ramair-bleedair intercooler
is installedatthefirewallto coolthe bleedair supplyauxiliarysystems
below250°F,priorto enteringthefueltankareaaftof thefirewall.Whenthe ramairinletto the
intercooler
is blocked,a bleedair overtemperature
switchis installedinthe bleedair duct downstream
of theintercooler.Thisswitchis setto closeat 425°F±50 F,whichwill illuminate
the BLEEDAIRHOT
lighton thepilotannunciator
panel.If thisoccurs,thefollowingstepsmustbe taken:
1. Shut off the ECU bleedair from that engineby usingthe ON-OFFswitch on the overheadengine
switchpanel.
2. If the lightremainson after shuttingoff the ECUbleed air,the 425°F switch could havecausedthe
light to illuminate. Sincethis air cannotbe shutoff, powerto that enginemustbe reduced.
3. If the lightremainson after completingsteps 1 and 2, makea precautionarylandingas soonas
practical,using minimumenginepoweron the affectedside.
4. Inspectenginebleed air ductsystemand makethe necessaryrepairs.
Thecabinair distribution
systemusesbleedair fromtheenginesandair enteringthe ECUfrom
outsidetheairplaneto operatetheECS.TheECSin turnproducescabinheatingor coolingand
air to defrostthewindshield
andsidewindows.Hotbleedair is usedto supplyheat,when
required,
througha bypassvalveon theECU.Thebypassvalvecontrolstheamountof hotair
mixedwithcoldair priorto theair enteringthecabin.
Air is distributed
throughoutthecabinthrougha systemof ducts,blowermotors,louversand
outlets.Theair boxes,locatedforwardof thesparboxes,houseblowermotorswhichhelp
distributethe propervolumeof air to eachoutlet.A divertervalve,locatedbelowthejunctionof
thewindshield
andsidewindowdefrosterlines,is installed
to operatethedistribution
of defroster
airfor thesewindows.
TheECScabinselectorpanel,locatedat thelowerportionof thecopilot'sinstrument
panel,allows
for operationof cabinair distribution
withtheuseof electrically
operatedtemperature
andpressure
controls.
ABINAIR
CABINCOMFORT
ECS SELECTOR
HEAT
ECSSELECTORL
HEAT
ECS CabinSelectorPanel
Figure 1
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Jan
1
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Distribution(continued)
CREWANDPASSENGER
'OVERHEADAIROUTLET(COLDAIR)
CREWFOOT FS
WARMER
FROM
-ECS
\
VALVE
WINDSHIELD
DEFOGCONTROL
VALVE
SIDEWINDOW
DEFOGOUTLET
'
|
LJ
COLDAIR
AAIR
DIST SELECTOR'OVHD'
FANS'OFF'
'ON"OR 'OFF'
MAY BESELECTED
DEFROSTER
CabinAir DistributionSchematic- ConditionedAir
Figure 2
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A. Distribution(continued)
CREWFOOT
WARMER
CREWANDPASSENGER
OVERHEAD
AIR OUTLET(COLDAIR)
FROM
ECS
WINDSHIELD
DEFOGCONTROL
VALVE
SIDEWINDOW
DEFOGOUTLET
WARMAIR
'AIR DIST SELECTOR"FLOOR"
RECIRCULATED
AIR
WITHFANS"LO"OR "HI"
MAYBESELECTED"ON"OR "OFF"
DEFROSTER
Schematic
- HeatedAir
CabinAirDistribution
Figure3
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A. Distribution(continued)
6
7
11
16
11
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
Fresh Air Valve
11.
Degog Vent Valve
12.
ConditionedAir Duct
13.
CrossoverDuct
14.
Footwarmerand Side WindowDefog Duct 15.
Heat Duct Plenum
16.
Defog Duct
17.
Side WindowDefog Outlet
18.
OverheadAir Outlets
19.
Defog Outlet
20
FootwarmerPlenum
CrewSide Outlet
FilteredRecirculatedAir Inlet
CabinAir Lever
WindshieldDefogLever
DuctTemperatureSensor
RecirculationCut Switch
OvertemperatureLightSwitch
CabinAir DistributionBoxand Blower Housing
CabinHeat Duct
Air DistributionSystem
Figure 4
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PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
5. Removalof GroundCoolingFan
(a) Gainaccessto baggagecompartmentareaand removehardwaresecuringpartitionbetween
baggagecompartmentand fan.
(b) Removeaccess panelon right sideof nosesection.
(c) Loosenand removeclampssecuringfan to flexiblerubbercuffs and refrigerationunit.
(d) Disconnectelectricalleadsto fan motor.
(e) Slidecuffs from refrigerationunit so fan motorcan be removedfrom refrigerationunit.
(f) Removefan.
6. Installationof GroundCoolingFan
(a) Withfan in position,slide rubbercuffs over ends of fan.
(b) Connectelectricalleadsto fan motor.
(c) Tightenclampssecuringfan in position.
(d) Replaceaccesspanel removedfrom right side of nose section.
(e) Replacepartitionremovedfrom baggagecompartment.
7. Removalof CheckValve Assembly
(a) Removeclampssecuringhose betweenwaterseparatorand checkvalveassembly.
(b) Removebolts and washersthat attachcheckvalve to pressurebulkhead.
(c) Removecheckvalvewith gasket.
8. Installationof CheckValve Assembly
(a) Installnew valveand gasketto pressurebulkhead.
NOTE: Checkvalve mustbe installedwith flapper shaft in verticalposition.
(b) Securevalve in positionwith washersand bolts.
(c) Installhose betweenwater separatorand checkvalve.
(d) Securehosewith clamps.
EFFECTIVITY:
040-999
21-20-00 PAGE5
21-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl
Pressurizedair for the airplanecabin is obtainedby mixinglow pressureand highpressurebleed air
from the enginecompressor.The bleedair is controlledby a solenoidshutoffvalve, operatedby an
ON-OFFswitchon the overheadengineswitch panel. This bleedair is routedthrough shrouded
annularducts,checkvalves and insulatedducts to the inletof the ECU,which conditionsthe bleedair.
The cabin pressurecontrolsystemconsistsof the cabin outflowvalve,cabin safetyvalve,cabin
pressurecontroller,auxiliaryvolumetank, absolutepressureregulator,filter, vacuumsolenoidrelief
valve,vacuum regulator,manualtest valve,cabin pressuretest/dumpswitch,cabin differential
pressureswitch,cabin absolutepressureswitches,plumbingand wiring. These items are given a
detailedoperationaldescriptionlater in this chapter.
The cabin safety valveis left open on the groundwith enginesoperatedby a vacuumappliedto the
controlchamberof the safetyvalve. The vacuumregulatorof the vacuumsystemprovidesa vacuum
of 4.0 to 6.0 inchesof mercury,referencedto cabin pressure. Enginebleedair is suppliedto the
ejectorto producethe requiredvacuum. This vacuum holdsthe safetyvalve openwhile on the ground
through the action of the landinggear squatswitch and "q" sensorsystemwhichenergizesand opens
the vacuumrelief solenoidvalve. The cabin pressurecontrolswitch on the lowercenter instrument
panelcontrolsthe vacuumreliefsolenoidvalve. Whenplaced in the DUMPpositionit energizesthe
vacuum solenoidand opensthe safetyvalve. The TEST position,(FORTEST PURPOSESONLY),
bypassesthe safety switch on the left mainlandinggear and "q" sensorsystems,which preventsthe
cabin from pressurizingon the ground. The normalpositionis CABIN PRESS,which allowsthe
systemto pressurizeaftertakeoff.
The cabin pressurecontrolleris mountedon the lowercenter instrumentpaneland the auxiliary
volume tankand filter are locatedbehindthe instrumentpanel. The volumetank providesadditional
volume for the rate pressurechamberin the controllerto give greateraccuracyof the cabin rate-ofchangecontrol. The air filter eliminatesentry of tobaccotar and dust particlesgreaterthan 0.3
microns intothe pneumaticcontrolelementsof the controller.
The cabin outflowand safetyvalves,cabin absolutepressureswitches,cabin differentialpressure
switch, absolutepressureregulator,and vacuum reliefsolenoidvalveare mountedon the aft pressure
bulkhead. The vacuumregulatoris locatedbehindthe copilot'sinstrumentpanel. (Referto 37-00-00)
The cabin air control, locateddirectlyabovethe cabin comfortcontrols,has two positionsmarked
PRESSandOUTSIDE. Whenthe controlis in the PRESSposition,the outsideair inlet is closedand
the cabin can be pressurized.Whenthe cabin air controlis set to the OUTSIDEposition,the outside
air inlet is open to allowfresh air to be drawn intothe cabinwhen the cabin is not pressurized.
A CABIN PRESSannunciatorlighton the annunciatorpanelwarnsthe pilot if the cabin altitudegoes
above 11,500feet or if the cabindifferentialpressureexceeds6.45 psi. Cabinpressureis
automaticallyregulatedto a maximumof 6.4 psi. If the cabinoutflowvalvemalfunctions,the cabin
safety valvereleasespressure. The CABIN PRESS/TEST/DUMP
switch is designedto prevent
inadvertentdumpingof cabin pressureand mustbe pulledout before actuationto the DUMPor TEST
positions.
EFFECTIVITY:
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00PAGE
1
21-30-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
CHART 1
FAULT ISOLATION (PRESSURIZATION SYSTEM) (Sheet 1-of5)
Fault
Cause
Remedy
Cabinwillnotpressurize.
Blockedsafetyvalvecabin
airfilteror orifice.
Replacefilter and check
orifice.
Blockedcontrollercabinair
filterwithorifice.
Cleanfilter and check
orificeon controller.
in the
Internalmalfunction
isobaricvalve.
Removeand replaceisobaric
valve.
Internalmalfunction
in the
safetyvalve.
Removeandreplacesafety
valve.
inthe
Internalmalfunction
controller.
Removeand replace
controller.
Defective
"q"switchand/or
landinggearsafetyswitch.
Removeandreplaceswitch.
Defective
dump/testswitch.
Replaceswitch.
No pressureto doorseal.
Checkand repairdoor
seal or door seal valve.
Excessive
leakagein
pressurization
ducts.
Locateleak and tighten
connections.
Excessive
cabinleakage.
Locateandrepairleak.
Solenoidvalve malfunctions
in the open position.
Replacevalve.
Valveon outside air control
boxwon't close.
Adjustor lubricatevalve
or controllinkage.
Malfunctionof ECS control
switch.
Repairor replaceswitch.
Malfunctionof ECU pressure
regulatorand shut off valve.
Repairor replacevalve.
PAGE
2 1-30-00
Jan 10/90 21-30
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. PressurizationControl(continued)
CHART 1
FAULT ISOLATION (PRESSURIZATION SYSTEM) (Sheet2 of 5)
Fault
Cause
Remedy
Cabinpressurizesto full
Vacuumtube not connected
to controller.
Connectvacuumtube.
Malfunctionin aircraft
vacuumsupply.
Checkaircraftvacuum
supply.
Rupturein volumetank.
Replacetank.
Internalmalfunction
in the
outflowisobaricvalve.
Removeand replacevalve.
Internalmalfunction
in the
controller.
Removeand replace
controller.
Low aircraftvacuumsupply.
Checkaircraftvacuum
supply.
Minor leak in tube between
controllerand volumetank
or in volumetank.
Removeand replacetube
or volumetank.
Minor leak in tube between
controllerand isobaricvalve
or in isobaricvalve.
Removeand replacetube
or isobaricvalve.
Minorleak in the controller.
Removeand replace
controller.
Minor leak in tube between
controllerand volumetank
or in volumetank.
Removeor replacetube
or volumetank.
Minor leak in the controller.
Removeand replace
controller.
Solenoidvalvemalfunction
in the closedposition.
Replacevalve.
"q" switch, landinggear
squatswitchor test/dump
switch malfunctionin the
open position.
Removeand replace
switch.
positivedifferential
pressureaftertakeoff.
Cabinaltitudedecreases
belowselectedaltitude.
Minimumratesunbalanced.
Downrate fasterthan up
rate.
Pressurizedoperation
before takeoffand
after landing.
EFFECTIVITY:
040-999
21-30-00
PAGE
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Pressurization
Control(continued)
CHART 1
SYSTEM) (Sheet 3 of 5)
FAULTISOLATION(PRESSURIZATION
Remedy
Fault
Cause
Pressurized
operation
beforetakeoffand
afterlanding.(continued)
Brokenwiringto the
vacuum reliefsolenoid.
Repairwiring.
Looseordamagedpneumatic
tubebetweensolenoidvalve
andsafetyvalve.
or
Checktubeconnections
replacedamagedtube.
in the
Internalmalfunction
safetyvalve.
Removeandreplacevalve.
True staticatmospheretube
blockedor not connectedon
isobaricvalve and safety
valve.
Securelyconnector remove
blockagefromthetruestatic
tubeon isobaric
atmosphere
valveandsafetyvalve.
pneumatic
Looseor damaged
tubingfromport 1" of
safetyandisobaricvalveto
atmosphere.
Repairor replacetubing.
Internalmalfunctionin
Removeand replace
controller.
Cabinexceedsfull positive
differentialcalibrated
setting.
Cabinclimbsanddescends
at a fixedrateregardless
of rateselection.
Cabinrateexceedsselected
ratevalveduringaircraft
climbto cruisealtitude.
Cabinpressurerapidly
increasesor decreases
of cabin
with reselection
altitude.
controller.
in controller.
Malfunction
Removeandreplace
controller.
Defective
cabinrateof
climbindicator.
Removeandreplace
indicator.
in controller.
Malfunction
Removeand replace
controller.
EFFECTIVITY:
040-999
21-30-00
Jan
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Jan 10
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
^
CHART1
FAULTISOLATION(PRESSURIZATION
SYSTEM) (Sheet4 of 5)
Fault
Cause
Remedy
Cabinaltitudeexceeds
selectedvalue.
Lossof airflowintocabin.
Repairbleedairsupply
of ECUsystem.
Internalmalfunction
in
isobaricvalve.
Removeand replacevalve.
Internalmalfunction
in
safetyvalve.
Removeandreplacevalve.
Internalmalfunctionin
controller.
Removeand replace
controller.
Excessive
cabinleakrate.
Sealleaks.
Dumpvalvepartiallyopen.
Closevalve; adjustvalve
controlcables.
Defective
isobariccontrol
valve.
Removeandreplacevalve.
Defectivesafetyvalve.
Removeand replacevalve.
Defective
pressurized
air
dumpvalve.
Removeor repairvalve.
Defectivecabin altitude
controller.
Removeand replacecabin
altitudecontroller.
Pressurizationduct leakage.
Locateleak and tighten
connection.
Cabinleakage
Defective
cabinaltitude
pressuregauge.
Locateandrepairleak.
Removeandreplacegauge.
Foreignmatteron isobaric
outflowcontrolvalve or
safetyvalveseats.
Cleanvalve seats.
Leakin outflowisobaric
valvecontrolline.
Locateleak and tighten
connection.
Cabinpressurewill not
maintaincontrolsetting.
EFFECTIVITY:
040-999
21-30-00 PAGE5
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
CHART 1
FAULT ISOLATION (PRESSURIZATION SYSTEM) (Sheet5 of 5)
Fault
Cabinpressureexcessively
high.
Cabindoor unsafe light
will not go out.
Cabindoor unsafelight
will not come on.
Nopressureto doorseal.
Cause
Remedy
Isobaricoutflowvalvestatic
line clogged.
Clean staticline.
cabinoverpressure
Defective
switch.
Removeand replaceswitch.
Defective
cabinaltitude
pressuregauge.
Removeand replacegauge.
Safetyvalvestaticvent
clogged.
Cleanvent line.
Defectivesafetyvalve.
Removeandreplacevalve.
Latchingrelaystickingin
the open position.
Lubricatethe mechanicalparts
(sparingly)with "GlideAir" or
equivalent.
Switch or switchesin door
frame out of adjustment.
Adjust.
Defectivepressureswitch.
Replaceswitch.
Shortto ground.
Checkwiring and repair.
Circuitbreakeropen.
Resetcircuit breaker.
Brokenwire or loose
connection.
Checkwiring and repair.
Leakin doorsealpressure
system.
Checkand repairdoor
seal pressuresystem.
EFFECTIVITY:
040-999
Jan
21-30-00
10/90 21-30-00
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. PressurizationControl (continued)
FROM
ECU
COALESCER
WATER
SEPERATOR
AMBIENTPRESSURE
CABINPRESSURE
P
FILTER
AUXILLARY
VOLUME
TANK
CABINPRESSURE
REFERENCE
PRESSURE
DISCHARGE
PRESSURE
RATEPRESSURE
AIRCRAFT
VACUUMPRESSURE
TRUESTATIC
PRESSURE
SOLENOID
AIR VALVE
CONTROL
CHAMBER
/ PORT
FILTER
CABINRATE
CONTROL
SELECTOR
KNOB
PORT "1"
ABSOLUTE
PRESSURE
REGULATOR
TRUESTATIC
ATMOSPHERE
SAFETYVALVE
VESSELBOUNDARY
TRUESTATIC
ATMOSPHERE
CABIN
DISCHARGE
CabinPressureControlSystemSchematic
Figure 1
EFFECTIVITY:
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21-30-00
Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
...
IgnitionTorque
GroundBleed
Air Switch
PressSwitchAutofeather
P3-13 PSI
P25-37 PSI
BleedAir
BLEEDAIR
SHUTOFF
VALVE
ON/OFFSolenoid
HI/LO
Solenoid
BLEEDAIR
SHUTOFF
VA
ON/OFF
ToECU
Valve
425 F
425 F
475
475
Bleed AirHot Warning
:..........................................
EmergencyPressValve
I
BleedAir Controland Cabin PressurizationSchematic (Sheet1 of 2)
Figure 2
EFFECTIVITY:
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10/902
30-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
Control(continued)
A. Pressurization
STA 57.00
STATION57.00
18 PSI
FILTER
AUX
VOLUME
TANK
PRESSURE
REGULATOR
RELIEFVALVE
REGULATOR
SHUTOFF
VALVE
VALVE
S
CABINDOOR SEAL
SOLENOID
VALVE
EJECTOR
SAFETYVALVE
ABSULUTEPRESSURE
REGULATOR(13.500)
VALVE
SAFETY
ABSOLUTELY
CABIN ALTITUDESWITCH(11,700)
(ABSOLUTEPRESSURESWITCH)
OUTFLOWVALVE
STA 3320
PRESSURE
CABIN ALTITUDESWITCH(12,000)
EMERGENCYPRESSURE
CABIN DIFFERENTIALPRESSURE
SWITCH (6.4-6.5 PSI)
BleedAir ControlandCabin PressurizationSchematic (Sheet 2 of 2)
Figure 2
EFFECTIVITY:
040-999
10/90
21-30-00 Jan
SUCTION
GAGE
-5 PSI
REGULATED
SUCTION
TO
VACUUM
RELIEF
SOLENOID
UNREGULATED
SUCTION
TO
EJECTOR
CONTROLLED
SUCTION
TO
ABSOLUTE
PRESSURE
REGULATOR
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Pressurization
Control(continued)
1. Component
DetailedDescriptions
(a) CabinOutflowValve(Figure3)
Theoutflowvalvecontainsa headandbasesection.Theheadsectioncontainsport2
(controller
connection)
anda pluggedcabinair port. Mountedon theheadisthedifferential
control,containingport1 (truestaticatmosphere
connection
withorifice).Thebaseassembly
enclosesa poppetoutflowvalvewhichsitson a baseassemblysurfacewhenin theclosed
position.
(b) CabinSafetyValve(Figure3)
Thesafetyvalvecontainsa headandbasesection.Theheadsectioncontainsport2
depressurization
connection
anda cabinairfilterwithorifice. Mountedon theheadis a
differential
control,containingport1 (truestaticatmosphere
connection
withorifice).Thebase
assemblyenclosesa poppetoutflowvalvewhichsitson a baseassemblysurfacewhenin the
closedposition.
(c) Cabin PressureController(Figure 4)
Thecontrollerbodyconsistsof threeelements:
(1.) Thelowerelementformsa chamberopento cabinpressureandhousestheabsolute
bellows.It is alsothefaceof the controller
thatcontainscabinaltitudeselectorknoband
cabinratecontrolknob.
(2.) Themiddleelement,whenassembled
to thelowerelement,completesandsealsthe
cabinpressurechamberfromtherestof thecontrollerwitha sealingdiaphragm.The
oppositesidesof themiddleelementformsa ratepressurechamberwhichhousesthe
ratespring.
(3.) Theupperelement,whenassembled
to theratediaphragm
andtheothertwoelements,
formsa referencepressurechamberwhichhousesthe reference
pressuremeteringvalve
andmeteringvalvefollowerspring.Thiselementalsocontainsthevariousair
connections
to installthecontrollerintothecabinpressurecontrolsystem.
(d) AuxiliaryVolumeTank
Thetankis a smallsealedchambernextto thecontroller.Whenconnected
to thecontroller,it
providesadditionalvolumeto theratepressurechamberin thecontrollerandprovidesgreater
accuracyof the cabinrate-of-control.
(e) AbsolutePressureRegulator(Figure502)
Theabsolutepressureregulatorcontainsa spring-loaded,
closedballmeteringvalveandan
aneroidbellows.Thebellowssensecabinpressureandoverridespringclosingforcewhen
cabinpressurereducesto approximately
13,500+ 1,000feet. Theunit isportedsothat
openingthe ball-metering
valveallowscabinpressureto entertheoutflowvalveheadwith
sufficientflowcapacityto fullyclosetheoutflowvalveandshutoff thepneumaticcontrol
pressurefromthecontroller.
EFFECTIVITY:
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Jan 10/90
Jan
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
1. ComponentDetailedDescriptions(continued)
(f) Air Filter
Thefilter elementis a cylindricalplug made of treated paperfabric, completelyenclosedin a
thin aluminumcase,with perforationsaroundits circumference.The filter effectivelyeliminates
entryof tobaccotar and dust particlesgreaterthan 0.3 micronin diameterintothe pneumatic
controlelementsof the outflowvalvecontroller.
(g) VacuumReliefSolenoidValve
Thisvalve,normallyclosed,is locatedbetweenthe vacuumregulatorvacuumport and the
controlline from the cabin pressurecontrollerto the safety valve. Whenenergized,the
vacuumprovidedby the vacuum regulatorejectoris appliedto the diaphragmof the safety
valveto holdit open. The vacuumreliefsolenoidvalve is open under eitherof the following
conditions:
(1.) On the groundwith the "q" sensorsystemor landinggear squatswitch energized.
(2.) In flight wheneverthe cabin pressurecontrolswitch is in the DUMPposition.
(h) VacuumRegulator
Vacuumto operatethe safetyvalveand controlleris obtainedfrom the vacuumsystem,which
uses its own regulator. The regulator,set to provide4.5 to 5.4 inchesof mercury(relativeto
cabin pressure),is placed in the systembetweenthe vacuumdriven instrumentsand the
ejector.
(i) Ejector
The ejectoris usedby the vacuumsystemto providea vacuumsource. Locatedunderthe
right side floor panelsnear F.S 151.30,it is connectedto the pneumaticlines from the
intercoolers.Bleed air flows throughthe ejectorto create the necessaryvacuum. (Referto 3600-00and 37-00-00)
(j) ManualTest Valves
The manualshutoffvalve is locatedbelowthe instrumentpanel,to the right of center,alongthe
brakesupportchannel. Whenused,the valveallows for systemgroundcheckoutand is
lockwiredin the open positionexceptwhenthe system is tested. The valveis installedin the
vacuumline goingto the controllerand is usedduringthe system positivedifferentialpressure
reliefcheck.
(k) CabinPressureSwitches
(1.) Cabindifferentialswitch,locatedon aft pressurebulkhead,providesa warningto the pilot
if cabin differentialpressureexceeds6.45 + 0.05 psid, by lightingthe CABIN PRESS
caution lighton the mastercautionpanel.
(2.) Cabinabsoluteswitch, locatedon aft pressurebulkhead,providesa warningto the pilot if
the cabin altitudeexceeds11,500feet, by lightingthe CABIN PRESScautionlight on the
pilot annunciatorpanel.
(3.) Cabinabsoluteswitchfor emergencypressurization,locatedon aft pressurebulkhead,
turns on the emergencypressurizationvalve if cabin altitude exceeds12,000to 12,500
feet.
EFFECTIVITY:
040-999
21-30-00Jan
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
PORT"2"DEPRESSURIZATION
CONNECTION
POPPETOUTFLOWVALVE
CONTROLCHAMBER
INNERDIAPHRAGM
BASEASSEMBLY
POPPETVALVERETURN
SPRING
METERINGVALVE DIFFERENTIAL
CONTROL
DIAPHRAGMASSEMBLY
NOISESUPPRESSION
SCREEN
PORT "1"TRUESTATICATMOSPHERE
CONNECTION
WITHORIFICE
CABINAIR FILTERWITHORIFICE
ONSAFETYVALVEONLY
DISCHARGE
PRESSURE
TRUESTATICATMOSPHERE
REFERENCEPRESSURE
CABINPRESSURE
GASKETINSTALLATION
DIMENSIONS
NOTE: THISPORT
PLUGGEDON
OUTFLOWVALVE
ONLY.
21NUT
SHIM(ASREQ)3 3 PLACES
0.385 IN.
0.485
HOLDTHISDIMENSION_
__
0.085
TYPICALDIMENSION
AFTER
INSTALLATION
OF SHIM
_
_
_
_
_
Safetyand OutflowValves
Figure 3
PAGE
12 21-30-00
Jan 10/9021-30-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
AUXILIARYVOLUME
TANKCONNECTION
REFERENCE
PRESSURE
METERINGVALVE
RATEDIAPHRAGM
METERINGVALVE
FOLLOWER
SPRING
RATESPRING
RATECONTROLVALVE
SEALINGDIAPHRAGM
CHECKVALVE
ABSOLUTEBELLOWS
RATECONTROLVALVE
POSITIONACTUATOR
CABINAIRSENSEPORT
ACTUATOR
CABINALTITUDE
SELECTOR
KNOB
CABINPRESSURE
CABINCONTROL
SELECTORKNOB
3
RATEPRESSURE
REFERENCE
PRESSURE
AIRCRAFTVACUUMPRESSURE
FACEVIEWOF CONTROLLER
CabinAir PressureOutflowValveController
Figure 4
EFFECTIVITY:
040-999
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13
21-30-00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl(continued)
2. Cabin PressureDump
In case of an emergencyrequiringthe cabin pressureto be dumpedin flight, placethe cabin
pressureswitch in the DUMPposition,placethe ECS selectorswitch to OFF positionand pull the
circuit breakerfor the DOORSEAL.
3. PressurizationCheck with Test Unit
NOTE: Theambientlineson theisobaricvalvesarecappedbycappingtheiradapterfittingson
theexternalsideof theaft pressurebulkhead.Thesefittingsare accessible
by removing
theaccesspanelin thetail.
Use the followingpressurizationtest procedureto determineif the aircraftfuselagehas an
acceptableleakagerate. A pressurizationtest unit (Figures501, 502, 503) is requiredto perform
thetest.
(a) AircraftPreparation
(1.) Removeaccesspanelon therightsideof thenosesection,to permitaccessto forward
pressurebulkheadat fuselagestation57.00.
(2.) Removeaccesspanelson therightandleftsideof thefuselagetail sectionat station
346.00.
(3.) Removethe trim panel at fuselagestation 296.00,in front of the outflowand safetyvalves.
Removethe cotter pin and cap ambientlinesfrom the outflowand safetyvalves.
(4.) Placecabin air controlin pressurizedposition. Close pressurizationtest valve underthe
instrumentpanel.
(5.) Placethe cabin air controlin the pressurizedposition. Closethe pressurizationtest valve
underthe instrumentpanel.
(6.) Positionall circuitbreakersexceptthe cabin pressurecontrol,door seal and
annunciator/warninglights in the OFF position.
NOTE: If airplaneis not on jacks, disconnectelectricalpowerto vacuum relief solenoid.
(7.) disconnectand plug gyro inlet lines at the filter.(Referto 37-00-00)
(b) Test Unit Hookup
(1.) Onthe right side of the forwardpressurebulkhead,removethe cabin pressuretest fitting
protectivecap. Connectthe cabin referenceline fromthe test unitto the fitting.
(2.) Removeair supplyline from the water separatorinletand installtest adapteras shownin
Figure 503. Connectair prssurelinefrom the cart to the adapter.
NOTE:Besurethatconnections
do notleak.
(3.) The door sealcan either be set up with shopair regulatedto 18 psi or throughthe test
cart. Proceedas follows:
(a.) Disconnectthe linefrom inlet side of the solenoidvalve(left side of fuselage,under
floor, F.S.203.00).
(b.) Connectthe line (hose)to the inlet side of the valveand routeit back to the fitting on
the upper middlepart of rear pressurebulkhead. Attachhoseto adapterwith
tightenedhose clampto preventleakage.
(c.) Removeaccesspanels on the tail of the aircraft and rach intothe tail to unscrewcap
from externalside of fitting.
(d.) Attach the line from the test cart or shopair sourceto externalside of fitting.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl(continued)
3. PressurizationCheckwith Test Unit (continued)
3.75
2.50
1.25 DIA
DIA
FabricatedReducerPressureTestAdapter
Figure 501
NOTE: Thisunit must be purchased
from Piper. This unit is
designatedwith a PiperPart
Number756344.
NOTE: The flowrate valve mustbe
set in full pump bypass
before startingor stopping
unit.
PneumaticAir or
PresssureAir
CabinReference -
Cabin Differential
Pressure Indicator
IInstrumentAir
Rate of Flow
Indicator
PressureIndicator
Fill Port
InstrumentAir
0
Indicator
Rateof
Climb Indicator
Circuit Breaker
-S tart Button
Stop Button
Flow Rate
Valve2
ElectricalConnection
ShopAir Air Regulator
Valve
FRONTVIEW
BACK VIEW
Cabin PressureTestUnit (Typical)
Figure 502
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
3. PressurizationCheckwith Test Unit (continued)
1 1/4 INCHSUPPLY
HOSEFROMTESTCART
-
CABINPRESSURE
IN
PressurizationTestHookup
Figure 503
EFFECTIVITY:
040-999
21-30-00
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10/90 21-30-00
Jan
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
3. PressurizationCheckwith TestUnit (continued)
(c) TestUnit Operation
TO AVOIDHARMING
WARNING: EXERCISECAUTIONDURINGDEPRESSURIZATION
UNIT CANNOTBE
TEST
THE
PERSONNEL.
OR
UNIT
TEST
AIRCRAFT,
IN THE CABIN.
EXISTS
DIFFERENTIAL
PRESSURE
WHEN
OFF
TURNED
RESULTS
DEPRESSURIZATION
RAPID
UNPLUGGED,
IS
IF MACHINE
CAUSINGSERIOUSDISCOMFORTTO ANYONE IN THE CABIN.
(1.) Turnon electricalpowerto activatedoorsealsystem.
(2.) Closecabindoorandensureit is closedsecurely.
systempressureon testunit usingregulatorcontrolknobso at least
(3.) Engagepneumatic
18 psigappearson thetest unitdoorsealpressuregauge.If shopair is hookedup,apply
equalpressure.
(4.) Connecttestunitto propervoltagesourceandturnflowratevalveknobto full bypass
positionto allowmachineto turnon.
CAUTION: TO PREVENTDAMAGETO RATEOF CLIMB INDICATOR,DO NOT
EXCEED4,000 FEETPER MINUTERATESOF CHANGE.
(5.) Turn cabin pressurizationflow controlvalveso a 2,000to 4,000 feet per minuterateof
descent is maintainedon the rate of climb indicator. Allow cabindifferentialpressureto
riseto 6.0 psi on the cabin differentialpressuregauge (CDP).
(6.) When 6.0 psi is indicatedon CDP gauge,rotate flow controlvalve and decreaseair flow
rate until the cabin rate of climb gauge indicateszero.
(7.) Maintain6.0 psi cabin differentialpressureand zero rate of change.
(8.) Observeleak rateon test unitflow meter. The actual leakagerate mustnot exceed60
CFM.
(9) If allowableleakagerate is exceeded,locateleak usingsoap bubbles,mechanic
stethoscopeor otherappropriatemethod;repair leak and re-pressurizeby followingthe
above procedures.
light systemas follows:
(10.)Aftercompletionof leak rate test, checkannunciator/warning
are capped.
valves
safety
and
outflow
from
line
sense
(a.) Ensureambient
pressureto a 6.45 ± 0.05
cabin
increase
slowly
openings;
other
any
(b.) Securedoor and
gauge.
pressure
differential
cabin
the
psig readingon
light systemand ensure cabin pressuredoes
(c.) Noteactivationof annunciator/warming
on at 6.45± 0.05 psig.
come
must
light
The
6.5
psig.
not exceed
CAUTION: AFTERCOMPLETIONOF PRECEDINGTESTS, ENSURECAPSARE
REMOVEDFROMAMBIENTSENSELINESTO OUTFLOWAND
SAFETYVALVESAND ENSURECOTTERPONSARE REPLACED.
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
3. PressurizationCheckwith Test Unit (continued)
(c)TestUnit Operation(continued)
(11.)Prior to anyengine runuptest, checkbleedair, cabin pressurizationsystem,safetyand
outflowvalvesas follows:
(a.) Safety valvecheck- Ensureambientsenseline for safety valveis open. Cap
outflowvalveambientsense line.
(b.) With cabin pressurestabilized,slowlyincreasecabin pressureto a 6.2 to 6.4 psi
readingon cabin differentialpressuregauge to permitopeningof safety valve.
The test unit cabin rate of climb indicatorwill indicatea climb when safetyvalve
opens.
(c.) Outflowvalvecheck- Cap ambientsense line for safety valveand open ambient
senseline for outflowvalve. Repeatprecedingstepfor outflowvalve.
(12.)Aftercompletingsafety and outflowvalveopeningchecks,rotateflow control to
depressurizecabin and bring pressureto ambient,by observingcabin differential
pressuregauge. Secureambientsense lines in open positionsby removingcaps and
replacingcotter pins.
(13.)Shutdown and turn off shopair to test to test unit. Bleedoff air pressurein doorseal
and open cabin door.
(14.)De-energizeairplaneelectricalsystemand disconnecttest unit pneumaticlinesfrom
airplane. Connectelectricallines to vacuumrelief solenoid,if disconnectedand all
aircraft pneumaticlines.
(15.)Replaceaccess and trim panels.
4. PressurizationSystemCheckoutProcedure
The followingproceduresare establishedto sytematicallycheckthe functionof eachcabin
pressurecontrol systemelement,so that any singleor combinationor componentmalfunctionis
safelydetectedand corrected. If a malfunctionis detected,it must be correctedimmediately.
5. GroundOperationalCheck
WARNING: THE FOLLOWINGOPERATIONALCHECKREQUIRESENGINERUNUPANDALL
SAFETYPRECAUTIONSMUSTBE STRICTLYOBSERVED.ALL PERSONNEL
WORKINGON THIS CHECKMUSTHAVECOMPLETEOPERATIONAL
KNOWLEDGEOF POWERPLANTSAND BE FAMILIARWITH ALL EMERGENCY
PROCEDURESOUTLINEDIN THE AIRPLANEFLIGHTMANUAL.
(a) Verifythatthe cabindoorandpilotwindowareclosedandlocked.
(b) Openmanualtest valve.
NOTE: Makecertainthatthe capsareremovedfromtheoutflowandsafetyvalveambient
senselines.
(c) Positionthe right and left bleed air switchesON.
(d) Verifythat the cabin air selectorswitch is in the CABIN PRESSposition.
(e) Rotatethe rate of changecontrolknob to the NOM position.
(f) Rotatethe cabin altitudecontrollerknob until the indicatoris at approximately500 feet above
field elevation.
EFFECTIVITY:
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Jan
10/90
21-30-00
21-30-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl(continued)
5. GroundOperationalCheck(continued)
(g) PA-42-720
(1.) Depresstoe brakesand set parkingbrake valve.
(2.) Start engines.
(3.) Place left and right bleedair switchesto the LO position.
(4.) Place ECS selectorto GND position.
(5.) Set enginepowerleversto GROUNDIDLE.
(6.) Verifythat the GROUNDBLEEDAIR annunciatorlightsare on.
(7.) Slowlyadvancethe powerlevers and verify that the GROUNDBLEEDAIR lights
extinguishat 70 to 75% Ng speed.
(8.) Retardthrottlesslowlyand ensurelightsilluminateagainat 65 to 70% Ng speed.
NOTE: Ensurethat the BLEED AIR OFF light illuminateswhen each engine is started
and when bleed air switch and ECS switch are in the OFFposition.
(h) Placecabin pressurization/test/dump
switch in the TEST position. Note that the safetyvalve
closes.
(i) Rotatethe cabin altitudecontrollerknob until either the cabin altitudeindicatesapproximately
1,500feet belowfield elevationor to full counterclockwisestopposition(belowsea level),
whicheveris applicable. Cabinpressurewill increaseduring rate of changeoperations.
(j) Rotaterate of changecontrolknobcounterclockwise.Note reductionin cabin pressurerate of
change.
(k) Rotaterate of changecontrolknobclockwise. Note increasein cabin rateof change.
(l) Allowcabin pressureto stabilizeat the selectedvalue.
(m) Rotatecabin altitudeselectorknobuntil CABIN ALTindicatesapproximately500 feet above
field altitude.
(n) Rotatecabin rate controlselectorknob counterclockwise.Note reductionin cabin pressure
rate-of-change.
(o) Rotatecabin ratecontrol selectorknob clockwise. Note increasein cabin pressurerate-ofchange. Allowcabin pressureto returnto field altitude.
(p) Monitorcabin rateof climb,cabin differentialpressureand the cabin altitudegaugesduring
test. Checkfor systemmalfunctionif gauge readingsare not acceptable.
(q) Placecabin pressureswitchto cabinpressurepositionand permitcabin to depressurize.Note
safetyvalveand outflowvalve arefully open.
(r) For positivedifferentialpressurereliefcheck,establishsteadycabin air inflow (outlinedabove)
and proceedas follows:
(1.) Rotate cabin rate of changecontrolknobfully clockwise. Thisallows pressurein rate
chamberto remainequalwith cabin pressureduring checkoutprocedure.
(2.) Rotate cabin altitudeselectorknob until CABINALT indicatesapproximately500 feet
abovefield altitude.
(3.) Place cabin pressureswitchin TEST positionto simulateflight condition. Ensuresafety
valvecloses and outflowvalvemovestowardOPENposition.
(4.) Behind instrumentpanel,locatemanualtest valvein controllervacuumline and cut safety
wire to handle.
(5.) Slowlymovetest valve handletowardclosedpositionuntil cabin pressurestartsto
increase(indicatedon cabin altimeterand rateof changeindicator).
(6.) Adjust neutraltest valveuntil comfortablecabin rateof change is established.Allow cabin
pressureto increaseuntil positivedifferentialpressurecontroloperationis achieved
(shownon cabin-to-atmosphere
differentialpressuregauge).
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21-30-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl(continued)
5. GroundOperationalCheck (continued)
(r) continued
NOTE: Whenworkingwith manualtest valve,openingvalvedecreasescabin pressurerate of
change and closing valve increasescabin pressurerate of change.
to zero,closemanualtest valveto shutoff
decreases
(7.) Whenpressurerate-of-change
vacuumto controller.Thecabinpressurecontrolsystemmustcontrolcabinpressure
pressureoperation.
duringnormalpositivedifferential
(8.) Capoutflowvalveambientlineto ensurepropertransferof differentialpressurecontrolto
safetyvalve. Thesystemnowexhibitscontrolat maximumpositivedifferentialpressure
of outflowandsafetyvalves.
verifyingoperation
operation,
pressurecontrolto returnto outflow
(9.) Uncapoutflowvalveambientline,allowingdifferential
valve.
cabinpressurerate-of-change
openmanualtestvalveto establishcomfortable
(10.)Slowly
to fieldaltitude.
whileascending
cabinpressurereturnsto fieldaltitude,shutenginesdown.
(11.)When
manualtest valvein OPENpositionandensureadapterfittingsareuncapped
(12.)Lockwire
andsecuredopenwithcotterpins.
6. SafetyPrecautions
Thefollowingsafetyprecautionsmustbe observed:
(a) UncontrolledPressurization:
(1.) Duringflight testingof system,continuouslymonitorcabin pressurizationinstrumentsfor
overpressurization.
(2.) In case of uncontrolledpressurization,the pilot muststop pressurizationor depressurize
aircraftas follows:
(a.) Movecabin pressuremodeswitchto DUMPposition.
(b.) Pull circuit breakerto deactivateinflationof cabindoor seal.
(c.) Close right and left enginebleedair valvesby placingboth bleed air switchesin OFF
position.
(d.) Rotate ECUcontrol to OFF position.
(e.) Openpilot storm window.
(b) ControlledDepressurization:
(1.) At altitudesabove 10,000feet, if an unpressurizedconditionis requiredfor an emergency
(such as smoke in cabin),depressurizeas follows:
(a.) Apply oxygen masks(all personson board).
(b.) Place cabin pressuremodeswitch in DUMPposition.
(c.) PositionECS selectorswitchto EMERGENCYposition.
NOTE: If smokepersistsor if cabinbecomestoowarm,positionECSselectorswitch
to OFFpositionandmovemanualcabinair leverto OUTSIDEAIR.
reduceaircraftaltitudeto lessthan10,000feet.
(d.) Immediately
conditioniscorrected,placecabinpressuremodeswitchin
(e.) Whenemergency
position,ECSselectorswitchin HI or LOposition,manualcabinair
PRESSURIZE
leverto PRESSposition,andreturnto aircraftcruisealtitude.Thecabinpressurewill
control.
settingon rate-of-change
returnto preselected
automatically
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
7. PressurizationSystemFlightCheck
The followinginstructionsexplainhowto performa pressurizationsystemflight check:
(a) Pre-FlightProcedure
(1.) Ensurecabin door and pilot windoware closedand locked.
(2.) Set cabin altitude selectorknob so cabin altitudeindicatesapproximately500 feet above
field altitude.
(3.) Turn cabin rate controlknobto NORMposition.
(4.) Move cabin air manualcontrol handleto PRESSURIZEposition.
CAUTION: CHECKFOR BROKENOR DISCONNECTEDCONTROLCABLEIF LITTLE
EFFORTIS REQUIREDTO MOVECONTROLHANDLE. DO NOT
CONTINUEFLIGHTCHECKUNTILINSPECTIONOR REPAIRSARE
COMPLETED.
(5.) Set cabin pressuremode switchto CABIN PRESSposition.
(6.) Start engines,setboth right and left enginebleedair switchesto ON position,ECS
selector switchto HI or LO, as desired,and establishsteadycabin air flow.
(7.) Ensurecabin door seal is inflated.
(b) Ascent Procedure
(1.) After lift-off,when selectedcabin altitude is attainedand cockpitwork load permits,select
aircraft cruise altitudeplug, 1,000feet on aircraftaltitudedial. Note when safetyvalve
closes on lift-off,no appreciableincreasein cabin pressureexists. The cabin rate of
descent must not exceed500 FPMfrom safety valveto outflowvalveduringtransitionof
cabin altitudecontrol.
(2.) Cabin altitudeautomaticallyclimbsto altitude indicatedon controllerat rate setwith cabin
rate controlselectorknob.
(3.) Monitordifferentialpressuregauge, cabin altitudegauge,and otherpressurization
controlsduring climb.
(c) CruiseProcedure
(1.) Annunciator/Warning
Light EmergencyPressurizationSystemCheck:
(a.) With airplanecruisingat 10,000feet, positioncabin pressureswitch to DUMPposition
and allowcabin pressureto stabilize.
(b.) Initiateclimb to 11,700+ 200 feet and ensurecabin pressurizationwarninglight and
annunciatorhaveactivated. Continueclimb to 12,500feet and ensure emergency
pressurizationcomes on.
(c.) Repressurizecabin by positioningcabin pressureswitchto CABIN PRESSURE
position.
(d) MaximumPositiveDifferentialReliefTestProcedure
(1.) Monitorcabin differentialpressuregaugecontinuouslyduring test so maximumoutflow
valve setting is not exceeded.
(2.) Stabilizecabin altitudeat 10,500feet and initiateclimb to 16,000feet at climb power.
NOTE: Leavepressurizationcontrolsat 10,000feet and ratefull clockwise.
(3.) When 16,000feet is reached,establishcruisepower. The cabin altitudemuststay at
10,000feet with zero rate of change.
(4.) Performthe followingstepswhile maintainingcruise powerat 16,000feet:
(a) Turn rate knobcounterclockwise(decrease).
(b) Select 7,500feet cabin altitude(outerknob).
(c) Turn rate knobslowly clockwiseuntil comfortablerateof descent is obtained. When
cabin altitudenears 7,500,turn rate knobcounterclockwiseuntil 300 FPMdescentis
obtained.
(d) Waituntil cabin stabilizes.
EFFECTIVITY:
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21-30-00 Jan
PAGE
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21- 30-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
(d) MaximumPositive DifferentialReliefTest Procedure(continued)
(4.) Performthe followingstepswhile maintainingcruise powerat 16,000feet: (continued)
(e.) Turn rateknob fully counterclockwise(decrease).
(f.) Select 800 feet cabin altitude.
(g.) Continueto monitordifferentialpressuregauge and test altimeterto ensurecabin
altitude doesnot drop below800 feet or cabin differentialpressuredoes not exceed
6.4 psi.
(h.) After cabin stabilizesat 800 + 500 feet, monitorpressurizationinstruments. Apply
climb powerand ensurecabin does not descentbelow800 feet or exceed 6.4 psi
differentialpressureon gauge. Climbto 18,000feet.
NOTE: If at start of climb cabin differentialpressurewas not at 6.3 psi, a rise in
differentialpressurewill occur. It must not exceed 6.4 psi and cabin rate of
climb must be identicalas aircraftrate of climb.
(5.) At 18,000foot altitude,set up cruise powerand recordthe followingdata:
(a.) Aircraftaltimeterreadingin feet.
(b.) Cabin test altimeterreadingin feet.
testaltimeterisrequiredto checkcabinaltitude
NOTE: A calibrated,hand-held
gauge.
(c.) Differentialpressurereadingin psid.
NOTE: Cabindifferentialpressuremust not exceed6.4 psi and cabin altitude must
not be less than 2,000 feet.
(6.) If systemis operatingsatisfactorily,proceedto nexttest procedure.
(e) Descentand NegativeReliefCheck Procedure
(1.) While maintaining18,000feet and cruise,proceedwith the followingsteps:
(a.) Set cabin rate controlfully counterclockwise(decrease).
(b.) Set cabin altitudecontrolknobto 10,000feet.
(c.) Set slowlyrotate cabin rate controlclockwiseto maximumrate (no climb will be
observedfor approximately1 minute). Whencabin stabilizesat 10,000feet, proceed
to next step.
(2.) Initiatenormal descent,maintainingsufficientpowerto maintainpressurization(untilbelow
10,000feet) and observethe following:
(a.) At 18,000feet, the cabin mustbe at 10,000feet and remain constantuntil aircraft
reaches10,000foot altitude.
(b.) Below 10,000feet, cabin rate of descentmust be approximatelythe same as
airplane.
NOTE: Whenairplanegoesthrough 10,000feet, differentialbetweencabin altitude
and aircraft altitudemust not exceed± 1,000feet.
NOTE: Do not land with morethan 0.3 psi cabindifferential. Dump pressureand
control airplanedescentto airplanealtitudedoes not catch up with cabin
altitudeduring rate operation.
(3.) Priorto landing,performthe followingsteps:
(a) Resetcabin altitude selectorto field elevationplus 500 feet, descentposition.
(b.) Adjust rateof changecontrolto comfortablerateof descent.
(c.) Observecabin differentialpressureindicator. Whenairplanereachespatternaltitude,
cabin differentialpressuremustbe nearlyequalized.
EFFECTIVITY:
040-999
21-30-00
10/90
Jan
Jan 21-30-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. PressurizationControl (continued)
CHART 2
CABIN ALTITUDE VS. AIRPLANE ALTITUDE
16,000
14,000
12,000
uJ 10,000
U
LL
0
m
8,000
6,000
4,000
2,000
SEA LEVEL
0
4
8
12
16
24
32333435
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl (continued)
WindshieldDefog
ControlLever
ManualTemperature
Control
Rateof
Change
Control
Altitude
Controller
Pressurization/
Test/Dump
Switch
CabinFan
Control
ECS Mode
Control
Automatic
Temperature
Selector
Cabin Pressurizationand ECS Control Panel
Figure 5
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl(continued)
8. AbsolutePressureRegulatorRemoval
(a) Removetrim panelin front of pressureregulator(locatedon rear pressurebulkhead).
(b) Disconnectlinesfrom regulator.
(c) Removethree attachingscrewsfrom regulator.
(d) Removeregulatorfrom mountingbracket.
9. AbsolutePressureRegulatorInstallation
(a) Installregulatorinto mountingbracket.
(b) Installthree attachingscrewsand tighten.
(c) Connectlines removedfrom regulator.
(d) Installtrim panelon rear pressurebulkhead.
BELLOW
CABIN
INBLEED
CONTROL
PORT
AbsolutePressureRegulator
Figure 6
EFFECTIVITY:
040-999
21-30-00
Jan
10/90
21-30-00
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Pressurization
Control(continued)
10. OutflowandSafetyValveRemoval
(a) Removetrimpanelin frontof safetyandoutflowvalves(locatedin rearpressurebulkhead).
(b) Removeaccesspanelon leftsideof tail section,justaftof entrancedoor,if safetyvalveis
beingremoved,
or removeaccesspanelon rightsideif outflowvalveis beingremoved.
(c) Disconnect
linesto valvebeingremoved.
(d) Workingthroughtail sectionaccesshole,removethreelocknutssecuringvalve.
(e) Removevalvefrompressurebulkhead.
11. OutflowandSafetyValveInstallation
(a) Placevalveontoshelfin rearpressurebulkhead.
(b) Whenreinstalling
safetyandoutflowvalve,seegasketinstallation
dimensions,
Figure3,to
insurepropergasketsealingrequirements.
for properclearance
betweennutsandgasket
face,adjustclearanceasfollows:
(1.) Removenutsusingdeepsocketandsufficientshimsto meetdimensional
requirements.
A minimumof oneshimis requiredfor installation
of eachnut.
(2.) Installnutsandtighten.
(3.) Applydropof lockingcompound(MIL-S-22473-EV)
to topof nuts,betweennutsand
studs.
(c) Throughtail sectionaccessopening,installthreelocknutsholdingvalvein place;tightento
metalcontactthenbackoff 1/4turn.
(d) Installaccessplateremovedfromsideof tail section.
(e) Connectlinesremovedfromvalve.
(f) Installtrimpanelin frontof valvesto ensureacousticalmaterialis in goodcondition.
12. Outflowand SafetyValveCleaning
Routinemaintenance
forcabinpressurecontrolsystemcomponents
islimitedto filterreplacement
in cabinair pressuresafetyvalveandcleaningof seatsin outflowandsafetyvalves.Cleanoutflow
andsafetyvalveseatsthoroughly
usingdetergentorisopropylalcohol.
WARNING: DRY CLEANINGSOLVENTMUSTBE USED IN A WELLVENTILATEDAREA.
AVOIDBREATHINGFUMESAND KEEPAWAYFROMFLAME.
Cleansafetyvalvefilterasfollows:
(a) Removeretainingring,onescreen,copperribbon,andremainingscreenfromfilterhousing.
(b) Washbothscreens,copperribbon,andfilterhousingin drycleaningsolvent.Ensureorifice
holeinfilterhousingis freeof foreignmaterial.
(c) Installonescreenin filterhousing.
(d) Instalcopperribbonin filterhousing.
NOTE: Donotovercompress
copperribbonin filterhousing.
(e) Installremianingscreenandinstallretainingring.
NOTE: Donotcleanfilteroncontroller.Removeandreplacecomponent
as required.
EFFECTIVITY:
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040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PressurizationControl(continued)
13. Removalof Controller
(a) Disconnectlinesfrom rear of cabin altitudecontrollerassembly. Cap open parts of lines and
fittingsto preventdust from enteringsystem.
panel to faceof instrumentpanel.
(b) Removescrewssecuringelectroluminescent
(c) Removethree screwssecuringselectorto instrumentpanels.
(d) Removecontrollerby liftingassemblyfrom rear of instrumentpanel.
14 Installationof Controller
(a) Fromfront sideof panel,positioncontrollerintoinstrumentpanelcutout.
(b) Securecontrollerto instrumentpanelwith threescrews.
panelto instrumentpanel and securewith screwspreviously
(c) Positionelectroluminescent
removed.
(d) Removeprotectivecapsfrom selectorlines and fittings. Connectlines to fittingson rear of
controller.
15. ControllerFilter Replacement
A disposabletobaccofilter, installedin the pressurizationsystemmust be replacedevery500
hoursof normaloperation. (Refer to the parts catalogfor replacementfilter part number.) More
frequentfilter changeand cleaningof the outflowand safety valveseats couldbe required
dependingon the amountof smokingin the cabin.
Replacecontrollerfilter as follows:
(a) Removefilter,accessiblefrom underneathinstrumentpanel,from behindand discard.
(b) Installnew filter.
EFFECTIVITY:
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PAGE
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21-30-00
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10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. HeatingandCooling
The heatingand coolingsystemuses enginebleed air to operatethe environmentalcontrolsystem
(ECS),whichin turn producesheatingor coolingto supplythe cabin. Hot bleed air is usedto supply
heat througha bypassvalveon the environmentalcontrol unit. The valvecontrolsthe amountof hot
air mixed with cold air prior to enteringthe cabin.
1. Fault Isolation(EnvironmentalControlSystem)
CHART 1
FAULT ISOLATION (ENVIRONMENTAL CONTROL SYSTEM) (Sheet 1 of 2)
Fault
Cause
Remedy
Bleedair leakagein primary
or secondaryheat exchanger.
Ruptureor corrosion.
Replaceheat exchanger.
Coolingturbinewill not start.
Excessiveair leakage.
Replaceseals.
Frozenbearingdue
to contaminationor
impropershimming.
Replacecoolingturbine.
Coolingturbinestops when
requiredto run.
Excessiveair leakage.
Repairleaks.
Waterseparatorblockage.
Coalescercloth is iced.
Checkanti-ice system.
Dirt contamination.
Cleancoalescercloth.
Water separatorcoalescer
cloth is damaged.
Overtemperature.
Replacecoalescercloth.
Excessivemoistureentering
cabin.
clothistorn
Coalescer
or dirty.
Cleancoalescercloth.
If torn, replace.
Conditionedair temperature
too high.
Ramair ductobstructed
or faceof heatexchanger
clogged.
Removeobstructionor
debris.
Heat exchangerleaking.
Replaceheat exchanger.
Coolingturbine rotating
torque unsatisfactory.
(See Note.)
Replacecoolingturbine.
Bypassvalve inoperative.
Checkvalvewiringand
operation. Replaceas
required.
MalfunctioningVariable
EjectorMixingValve
Removeand replacevalve.
EFFECTIVITY:
040-999
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21-40-00 PAGE
10/90
21-40-00Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. HeatingandCooling(continued)
1. FaultIsolation(Environmental
ControlSystem)(continued)
CHART 1
FAULTISOLATION(ENVIRONMENTALCONTROLSYSTEM) (Sheet2 of 2)
Fault
Insufficientconditionedairflow.
Remedy
Cause
BleedairON/OFFvalve
notfullopen.
Checkwiring.
Leaksin jointsorconnections.
Repairleakingjoints and
connections.
Coolingturbine rotating
torque unsatisfactory.
(See Note.)
Replacecoolingturbine.
Heatexchanger
leaking.
Replaceheatexchanger.
MalfunctioningVariable
EjectorMixingValve
Removeandreplacevalve.
NOTE: Referto label on coolingturbinefor maximumacceptabletorque value.
EFFECTIVITY:
040-999
Jan 10/90 21-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Heatingand Cooling(continued)
2. ComponentDetailedDescriptions
Thissystem,operatedbyenginebleedair,is controlled
by a pressureregulatorandflow limiting
venturi,alongwithvariouscomponents
whichcomprisetheenvironmental
controlsystem.The
followingis a description
ofthesevariouscomponents:
(a) PressureRegulatingand ShutoffValve
The pressureregulatingand shutoffvalveis installedin the bleedair line upstreamfrom the
refrigerationunit. This is a solenoidoperatedvalvewhich regulatesthe bleedair supply
pressureto the refrigerationunit and includesmeansfor shuttingoff all bleedair to the
refrigerationunit.
(b) BleedAir Supply OverpressureSwitch
Thisswitch, locatedat the inlet to the refrigerationunit, monitorsbleed air pressureto the unit
and signalsthe regulatingand shutoffvalveto shutoff air flow if pressureexceeds40 + 3 psig.
(c) VariableEjectorMixingValve
The PA-42-720uses a variableejectormixingvalve. The PT6A-61engineproducesa higher
compressorbleedair pressureand a resultinghigher bleedair temperature. The variable
ejectormixingvalve mixesthis higher press/temp.compressorbleedair with interstageturbine
bleedair and controlsboth temperatureand pressureof the bleed air supply.
(d) PrimaryHeat Exchanger
Thisheat exchanger,locatedin the refrigerationunit, is usedto lowerthe high bleedair
temperatureprior to beingroutedto the compressor.
(e) Compressor
Thecompressor
in therefrigeration
unit isbootstrappedto theturbineandcompresses
the
bleedair to a higherpressurewhichraisesthetemperature.
(f) CompressorDischargeOvertemperatureSensingSwitch
Thisswitch, installedat the compressordischargeport, sensesdischargetemperature. The
switch,normallyclosed,mustopen when temperaturesreach425°F ± 5°F and mustsignalthe
pressureregulatorand shutoffvalveto closeand shut off the bleedair supplyto the
refrigerationunit.
(g) SecondaryHeat Exchanger
Thisheat exchanger,locatedin the refrigerationunit, is usedto lowerthe air temperature(still
highdue to flow throughthe compressor).
(h) CoolingTurbine
Thecoolingturbine,installedon the commonshaftwith the compressor,receivesthe precooled
air from the secondaryheat exchanger.This air, still at highpressurewhen passingthrough
the turbine,is loweredby expansion. The turbineabsorbsenergyfrom the high pressurebleed
air and drivesthe compressor.The expansionof the bleedair, plus its loss of energy,causesa
temperaturereductionat the turbine discharge.
(i) MixingMuff
Thismixingdevice,locatedimmediatelydownstreamfrom the coolingturbine (1) mixescold
turbineoutlet air with hot bleed air from the hot air bypassvalveand (2) preventsicingof the
turbinerotor and dischargeducting.
(j) HotAir BypassValve
Thisvalve is installedbetweenthe turbine mixingmuff and the bleedair line to the primaryheat
exchanger. its function is to modulatethe flow of hot bleedair into the mixingmuffaccordingto
signalssent to the valvefrom the cabin temperaturesensorand controller. This valveuse an
electricactuatormotor.
EFFECTIVITY:
040-999
21-40-00
PAGE
3
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Heatingand Cooling(continued)
2. ComponentDetailedDescriptions(continued)
(k) Water SeparatorAssembly
This assemblyconsistsof a coalescer,water collector,and drain. The drain consistsof a line,
routedto the wateraspiratoron the air inlet side of the refrigerationunit, aheadof the heat
exchangers. A small portion of bleedair is extractedfrom the heat exchangerand is routed
throughthe aspirator,causinghigh velocityair flow throughthe aspiratorand creatinga
vacuum on the drain line which removesany waterfrom the water separatorcollector. This
moistureis sprayedinto the ambientair aheadof the heat exchangerto provideadditional
coolingcapacity.
(I) Duct TemperatureSensor
This sensor,locatedin the cabin air supplyduct downstreamof the water separator,senses
cabin air temperature. This unit, capableof monitoringtemperaturesbetween+30°Fto 200°F,
suppliessensordata to the cabintemperaturesensorand controller.
(m)CabinTemperatureSensorand Controller
This unit works in conjunctionwith the ducttemperaturesensorand cabin temperatureselector
to controlthe hot air bypassvalve and maintainsthe desiredcabin temperature. It is centrally
mountedin the aircraftcabin. The controllerrangeof operationis +30°Fto 160°F.
The ECS must maintainthe averagecabin and cockpittemperaturesof 75°F for coolingand
80°F for heating. Duringground operation,the systemmust maintainthe cabin at an average
temperatureof 75°F or less. Duringa hot day,the systemmustpull the cabintemperature
below80°F in 20 minutesor less from the timethe systemis turnedon. The cabin temperature
control automaticallymaintainsthe temperatureat the sensorwithin± 3°F of the selected
setting.
(n) CoolingFan
The coolingfan is energizedby the landinggear squatswitch only when the aircraft is on the
ground. It providesram air coolingfor both the primaryand secondaryheat exchangers
througha 28-voltvane axial fan.
3. Removalof PressureRegulatorand ShutoffValve
(a) Removewater separatoraccordingto instructionsin this chapter.
(b) Disengagebleedair circuit breaker.
(c) Disconnectpressureregulatorsensingtube from pressureregulatingand shutoffvalve.
(d) Disconnectelectricalplug from pressureregulatingand shutoffvalve.
(e) Removecouplingssecuringpressureregulatorand shutoffvalveassemblyin position.
(f) Removepressureregulatorand shutoffvalvefrom airplane.
4. Installationof PressureRegulatorand ShutoffValve
(a) Ensurepressureregulatorand shutoffvalveare in positionand securedwith couplings. Torque
couplingsto 35 - 45 inch-pounds.
(b) Connectpressureregulatorsensingtubeto pressureregulatingand shutoffvalve.
(c) Connectelectricalplug to pressureregulatingand shutoffvalve.
(d) Engagebleedair circuit breaker.
(e) Installwater separatoraccordingto instructionsin this chapter.
5. Removalof Hot Air BypassValve
circuitbreaker.
cabintemperature
(a) Disengage
electricalplugfrombypassvalve.
(b) Disconnect
(c) Removecouplingssecuringbypassvalveto ductflange.
(d) Removebypassvalveand seals.
EFFECTIVITY:
040-999
Jan 10/9021-40-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Heatingand Cooling(continued)
6. Installationof Hot Air BypassValve
(a) Securebypassvalveand new sealsto ductflange usingpreviouslyremovedcouplings.
Torquecouplingsto 35 ± 3.5 inch-pounds.
(b) Connectelectricalconnectorto bypassvalve.
(c) Engagecabin temperaturecircuitbreaker.
7. Removalof BleedAir Supply OverpressureSwitch
(a) Gainaccess to overpressureswitch. (Figure 401)
(b) Disconnectelectricalconnectorfromswitch.
(c) Cutsafetywire and unscrewswitchfrom receptacle.
(d) Removeswitch and O-ring.
8. Installationof Bleed Air SupplyOverpressureSwitch
(a) Installnew switch and O-ring into receptacle.
NOTE: EnsureproperhightemperatureO-ring is usedby referringto PartsCatalog.
(b) Secureswitch with safetywire.
(c) Reconnectelectricalconnectorswitch.
9. Removalof CompressorDischargeOvertemperatureSensingSwitch
(a) Gainaccessto overtemperatureswitch. (Figure 401)
NOTE: Note locationof eachwire to facilitate reinstallation.
(b) Disconnectelectricalleadsfrom switch.
(c) Loosennut and unscrewswitch from receptacle.
(d) Removeswitch and O-ring.
10. Installationof CompressorDischargeOvertemperatureSensingSwitch
(a) Installnew switchand O-ring intoreceptacle.
NOTE: EnsureproperhightemperatureO-ringis usedby referringto PartsCatalog.
(b) Screwswitch into receptacle.
(c) Connectwires to switch.
EFFECTIVITY:
040-999
21-40-00
PAGE
5
21-40-00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. HeatingandCooling(continued)
NOTE: Thisunit is locatedin the nose
section,right side, between
stations57.00 and 25.60.
GROUNDAIRFAN
(SERVICE- 500HR)
ERSEPARATOR
COALESCER
(SERVICE-500HR)
UNIT
REFRIGERATION
LEGEND
ELECTRICAL
INLET
OVERPRESS
SWITCH
OPEN= 40 ± 3 psig
REFRIGERATION
UNITBOUNDARY
Environmental
ControlSystem
Figure401
EFFECTIVITY:
040-999
PAGE
Jan 10/90 21-40-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. TemperatureControl
1. Removalof Duct TemperatureSensor
(a) Gainaccess to ducttemperaturesensorunderthe floor on right hand side of fuselage,
immediatelyaft of F.S.57.00 forwardpressurebulkhead.
(b) Removefour screws securingsensorin position.
(c) Removesensorwith gasket.
2. Installationof Duct TemperatureSensor
(a) Installnew sensorand gasket. Securewith four screws.
3. Removalof CabinTemperatureSensorand Controller
(a) Gain accessto cabin temperaturesensorand controller. Removescrews andwashersto
secureunit in position. Pull unit out so electricalconnectorcan be disconnected.
(b) Removecabin temperatureand controller.
4. Installationof CabinTemperatureSensorand Controller
(a) Installnew sensorand connectelectricalconnector.
(b) Secureunitwith washersand screws.
EFFECTIVITY:
040-999
21-60-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Moisture/AirContaminantControl
1. Removalof WaterSeparator
(a) Disconnectwater line, inlet, and outlet air connectionsfrom water separator.
(b) Removeclampssecuringwaterseparator.
(c) Removewater separator.
2. Installationof WaterSeparator
(a) Securewater separatorto hoseswith clamps. Torque30 to 35 inch-pounds.
(b) Connectwater line to waterseparator.
3. Cleaning,Inspectionand Repairsof Water Separator
The coalescercloth must be cleanedor replacedat 500 flight hours or less, exceptwhen operated
in abnormallydusty or contaminatingconditions.
(a) Removeband and coverfrom waterseparator.
(b) Removecoalescercloth from insidewater separator.
(c) Washcoalescercloth with warmwater and mild detergent;rinsewith cleanwater.
CAUTION: DO NOT WRINGCOALESCERCLOTH.
(d) Replacecoalescercloth on inner housingwith nap insideagainstthe screenand rubberbands
flat and firmly in place.
(e) Installcover and band on water separator.
EFFECTIVITY:
040-999
21-70-00 JanPAGE
10/90 1
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 23
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SECTION
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15/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 23- COMMUNICATIONS
TABLE OF CONTENTS
SUBJECT
I
CHAPTER
PAGE
23-60-00
Static Discharging
1
Inspectionand Testing
1
23-70-00
Audio & Video Monitoring
CockpitVoice Recorder(CVR)
Removalof CVR Unit
Installationof CVR Unit
Testing
EFFECTIVITY:
040-999
1
1
1
1
1
CONTENTSPAGE1
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Static Discharging
1. Inspectionand Testing
for thefollowing:
wicksmustbe inspectedat eachannualinspection
Staticdischarging
(a) Generalappearance
andphysicalcondition.
(b) Securityof attachment
to airframe.
(c) Discharge
pointsvisible.
(d) Resistance
(1.0to 100megohms,
500to 1,000voltmegohmmeter).
(e) Baseresistance
to airframe(100milliohmsmaximum).
EFFECTIVITY:
040-999
23-60-00PAGE
1
23-60-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Audio & Video Monitoring
1. CockpitVoice Recorder(CVR)
The FairchildCockpitVoiceRecorderSystem(CVR)providesa recordof four separatevoice
inputs. These inputsmay be eithertransmittedor receivedsignalsoriginatingfrom the following
stations:Pilot, Copilot, PublicAddressor Third Crew Memberand CockpitArea Microphone.
The CVR is a modularsystemcomposedof a minimumof two essentialmodules,the recorderand
the controlunit. The recorder,modelA100A,is housedin an internationalorange, 1/2 ATRshort
case. It containsthe recorderassemblyand associatedelectronics,locatedin the aft baggage
compartment.The controlunit is a standardARINCcharacteristic306 panelformat. ModelA152B
housemicrophonepre-amplifier,microphone,test switch,erase switch and meter,locatedon the
center instrumentpanel.
The erasefeature is a bulk erasefunction. Whenactivatedon the ground,this functionwill
completelyerase all datafrom the tape. The units normalmode of operationis self erasingwhile it
is recording.
2. Removalof CVR Unit
The CVR controlunit is mountedon the center instrumentpanel utilizingfour dzus fasteners.
(a) Unlockthe fastenersand lift the controlhead free of the panel.
(b) Removethe electricalconnection.
The CVR recorderunit locatedbehindthe aft baggagecompartmentwithin the pressurizedvessel,
maybe removedby:
(a) Removingthe recordercover.
(b) Loosenthe wing lock nutsand removeunit.
3. Installationof CVR Unit
The CVR recorderunit
(a) Insertunit and tightenwing lock nuts.
(b) Replacerecordercover.
The CVRcontrol unit
(a) Reconnectelectricalconnections.
(b) Placecontrol head in paneland lock fasteners.
4. Testing
Functionaltest of the CVR unit:
(a) Pushand hold "TEST"button locatedon the CockpitControlUnit for a minimumof five
seconds. A 600 hertzgeneratoris keyed and sequentiallyswitchedthroughthe four channels
of the recorder. Eachchannel receivesthe testtone for approximately0.8 seconds. The meter
circuitreceivesthese signalsand drives the meter,a "GO-NO-GO"indicatingdevice,located
on the CockpitControlUnit. The meter needlerises and comesto rest in the "GO"(green)
sectionof the meterscale.
EFFECTIVITY:
23-70-00 Janan1090
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Audio& VideoMonitoring
(continued)
4. Testing(continued)
Becauseof theshorttimeintervalbetweeneachchannelbeingfedthetesttone,the meterneedle
risesto an indicationbut doesnotcompletely
fallto a zeroindicationbetweensignals,givingmore
of an oscillatingactionor a slightditheringaction.In theeventof a channelfailure,the meter
needlewill returnto zeroandgivea definite"NO-GO"indication.
(b) Auralmonitoring
of the600hertztesttoneandchannelswitchingcanbe accomplished
with a
600ohmheadsetinsertedintothejacklocatedon theCockpitcontrolUnit.
Withthe headsetinsertedintothejacklocatedon theCockpitcontrolUnit,speakin a normal
voice6 inchesawayfromtheCockpitControlUnitmicrophone
andnotethatyou canhearwhat
youspeakwithapproximately
a 1/2seconddelaywithoutanysignificant
distortion.Thistest
ensuresthe microphone
isoperating.
Thetest procedureshouldbe performed
duringtheEventinspection
cyclesandreplacedat
4,500hourintervals.(Referto 5-50-00)
MICROPHONE
METER
SWITCHES
MATINGCONNECTOR
HEADSE
COCKP
COCKPITVOICE
VOICERECORDERHMS
RECORDER
0
CockpitVoice RecorderControl Unit
Figure 1
EFFECTIVITY:
048-050
Jan 10/90 23-70-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER24
LIST OF EFFECTIVEPAGES
CHAPTER
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LIST OF
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EFFECTIVE
PAGESJan
10/90
1
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER24 - ELECTRICALPOWER
TABLEOF CONTENTS
SUBJECT
CHAPTER
PAGE
24-00-00
General
24-30-00
DC Generation
Descriptionand Operationof StarterGeneratorSystem
Fault Isolation(StarterGenerator)
MaintenancePractices
Removalof StarterGenerator
Installationof StarterGenerator
Adjustmentsof StarterGenerator
StarterGeneratorServiceTestSpecifications
CheckStarterGeneratorSystem
GeneratorBrushInspection
CleaningGenerator(Assembled)
Descriptionand Operationof GeneratorControlUnit
Removalof GeneratorControl Unit
Installationof GeneratorControlUnit
CheckingGeneratorControlUnit
Removalof CrossStart Relays
Installationof CrossStart Relays
Descriptionand Operationof Battery
Fault Isolation (Battery)
ChargingBattery
ConstantCurrentCharging
ConstantPotentialCharging
BatteryCell Replacement
Removalof Battery
Installationof Battery
TestingBatteryTemperatureSensor
Adjustmentof ElectrolyteLevel
Battery Inspection
BatteryDisconnectand ReceptacleInspection
PeriodicBatteryCheck
Cell VoltageCheck
BatteryCleaning
OverheadMeterand Switch PanelAssembly
Removalof EngineControl PanelSwitch
Installationof EngineControl PanelSwitch
Removalof RockerSwitch
Installationof RockerSwitch
Removalof ElectricalGauge
Installationof ElectricalGauge
1
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2
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5
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EFFECTIVITY:
040-999
CONTENTSPAGE1
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER24 - ELECTRICALPOWER
TABLE OF CONTENTS(continued)
SUBJECT
CHAPTER
24-60-00
DC ElectricalLoad Distribution
Main CircuitBreaker Panel
Removalof Main Circuit Breakers
Installationof Main CircuitBreakers
ElectricalPower DistributionSystemTest
Main Bus Tie CircuitBreaker and CrossfeedDiodeCheck
Left and RightCircuit Breaker Panels
Removalof Plug-in Type CircuitBreakers
Installationof Plug-inType CircuitBreakers
Removalof Screw ConnectType CircuitBreakers
Installationof Screw ConnectType Circuit Breakers
PAGE
1
1
1
1
2
4
5
6
6
6
6
EFFECTIVITY:
040-999
CONTENTS
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
ElectricalPower
A. Descriptionand Operation
Electricalpoweris suppliedby a 28-volt,directcurrent,negativegroundelectricalsystemincorporating
a 24-voltnickel-cadmiumbattery furnishingpowerfor starting,and as a reservepower sourcein case
of generatorfailure. An externalpowerreceptacleis also providedin the nose of the airplanefor
auxiliarypowerduring cold weatheroperationsor wheneverexternalpower is requiredto start the
engines.
The electricalsystemis controlledby three rockertype switches: the battery master switch,right
starter generatorswitch, and left startergeneratorswitch. These switchesare locatedon an overhead
panel just abovethe windshieldbetweenthe pilot and copilotseats. The battery master switch
controlsa mastercontactorwhich connectsthe batteryto the tie bus. Both generatorsprovidepower
to this busand can be switchedindividuallyon or off the system.
The PA-42-720hastwo 300-amp,28-voltgenerators,whichprovidethe startingfunctionfor the
engines. Overvoltageand overloadprotectionis providedwithinthe system,with two circuitbreaker
panels locatedon the right and left side panelsof the cockpit.
EFFECTIVITY:
24-00-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation
CAUTION: THE SELECTORSWITCHSHOULDNOT BE LEFTIN THE STARTPOSITIONANY
LONGERTHANTHE TIME REQUIREDFORA NORMALENGINESTART;
OTHERWISE,THE UNIT MAYBE DAMAGEDBY EXCESSIVETEMPERATURES
CAUSEDBY THE LARGESTARTINGCURRENTSIF A NORMALSTARTIS NOT
EFFECTED.
1. Description
andOperation
of StarterGenerator
System
Thestartergeneratoris locatedon theupperpartof theengineaccessory
section.Thepurposeof
theunitisto providetorquefor enginestartingandto generatedc electricalpower.Whenthisunit
is beingutilizedasa starter,it maybe energizedbyaircraftbatteryor throughthe useof an
externalpowersourcefor firstenginestart.Alsoincorporated
is a crossstartsystemto provide
generated
powerto assistthe batteryin startingthe secondengine.Thecrossstartrelaysconnect
thefunctioning
generator
to thebatteryandthestartsolenoidto startthesecondengine,
bypassing
themainbusbreakers.Forcrossstarting,theseconditionsmustbe met: operating
enginegeneratorswitchon,engineat highidle,andsecondenginestartswitchto STARTposition.
Whenthe unit is beingutilizedas a generator,it will providerateddc output when operatedat rated
speeds.This generatedelectricalpoweris then utilizedas requiredto operatethe variouselectrical
systemsof the aircraft.
Thisunitincorporates
itsowncoolingsystemwhichconsistsof an air inletduct,exhaustduct,and
a fourbladedfanwhichis partof theunit. Coolingisobtainedbyroutingtheoutsideramair
throughtheair inletductwhichis thendriventhroughtheunitbythefourbladedfanandoverboard
throughtheexhaustduct.
Eachunit is controlledby its own independentthreepositionswitch: DNfor START,UP for
GENERATOR,center positionOFF. The switchesare locatedon the overheadswitch panel (refer
to Figure 1). With the battery masterswitchon, placingthe right or left startergeneratorswitch in
the STARTpositioncloses the appropriatestartersolenoidfor the particularengine. Poweris then
suppliedthroughthe mastercontactorto the fieldwindingsand the armaturewindingsof the
starterunit creatinga strong magneticfield. The magneticfield now existingin the armature
combineswith that existing in the field windingsof the starterunit driving the armatureas required
to start the engine.
Whentheswitchis placedin theGENposition,theunitprovidesrateddc outputto theaircraft
electricalsystemthroughthevoltagecontrolpanelandtheovervoltage
control.Placingtheswitch
in thecenterorOFFpositiondisconnects
theunitfromtheelectricalsystemof theaircraft.
NOTE: Referto PA-42-720(AdvancedTrainer)WiringDiagramManual,P/N 761 853, for the
electricalschematicsapplicableto these aircraft.
EFFECTIVITY:
24-30-00 Jan
Jan
1
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
2. Fault Isolation
After the malfunctioningsystemor componenthasbeen repairedor adjusted,it is recommended
that the entire systembe inspectedfor securityand operationof its components.The wiring
diagrammanualprovideselectricalschematicsto be used alongwith conventionaltroubleshooting
methods.
CHART 1
FAULT ISOLATION (STARTER - GENERATOR) (Sheet 1 of 3)
Remedy
Fault
Cause
Unit fails to operateor does
not attain normal speed.
Low voltagepowersource.
Checkthe powersourceto
makecertainthat full voltage
is beingappliedto the starter
terminals.
Defectiveswitchin power
supply
Defectivestartersolenoid.
Replaceswitch.
Damagedarmature.
Replacethe armature
assembly.
Shortcircuitedor open
statorwindings.
Replacethe stator and
housingassembly.
Improperlyseated
brushes.
Checkbrush seatsand
increasebrush run-intime.
Eccentriccommutator.
Refinishcommutator.
Short circuitedor grounded
field windings.
Replacestator and housing
assembly.
Excessiveclearancein
bearingsor rough
bearingraces.
Replacebearings.
Eccentriccommutator.
Refinishcommutator.
Short circuitin armature
windings.
Replacearmatureassembly.
Brushesincorrectly
installedwith top
bevel reversed.
Reverseand reset
Armatureout of balance.
Balanceor replace
armature.
Insufficientbrush run-in;
improperseating.
Runin brushesuntil
seated.
Excessivesparkingat
brushes.
Replacesolenoid.
EFFECTIVITY:
040-999
PAGE
2 24-30-00
24-30-00
Jan10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. DC Generation (continued)
2. Fault Isolation
CHART 1
FAULT ISOLATION (STARTER - GENERATOR) (She et 2 of 3)
Fault
Cause
Remedy
Excessivesparkingat
brushes.(continued)
Severeoverloador short
circuit in aircraftelectrical
system.
Locate and correctfault.
Brushesstickingin holders.
Free up brushes.
Weak brush springs.
Replacebrush holders.
Brushesloose in holder.
Replacebrushes. If still
loose, replacebrush holder
assemblies.
Roughbearings.
Replacebearings.
Scoredor worndrive
splines.
Replacedrive shaft.
Armaturerubbingin stator.
Repairor replacedefective
parts.
Fan blades bentand
rubbing.
Straightenor replacefan.
Unbalancedarmature
assembly.
Balanceor replace
armatureassembly.
Excessiverun-outof
armaturebearings.
Replacearmaturebearings.
Fandamagedor out
of balance.
Rebalanceor replacefan.
Voltmeterleadsreversed.
Connectvoltmeter
correctly.
Residualmagnetismin field
poles createswrongpolarity.
Flashthe field.
Continuousoverloador
restrictedair inlet.
Check aircraftelectrical
systemfor grounds,etc.
Makecorrectionas
necessary.
Noisy operation.
Unit vibrates.
Generatorproducesfull
voltage, but with reversed
polarity.
Generatoroverheats.
EFFECTIVITY:
4 9924-30-009
PAGE
3
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DCGeneration(continued)
2. FaultIsolation
CHART 1
FAULTISOLATION(STARTER- GENERATOR)(Sheet 3 of 3)
Fault
Cause
D to E parallelingvoltage
notwithinlimits.
Insufficient
coolingair.
Checkfor air inlet
temperature.
Air flow obstruction;dirt
accumulationin generator
ducting.
Checkductingandgenerator
air inlet.
Wrongloadappliedduring
testing.
Checktestingprocedure
andcorrectcondition.
Short circuitedor open
stator winding.
Replacestator and housing
assembly.
Opencircuitin armature.
Replacearmature.
Startergeneratorfails
startingtest.
Remedy
Figure1
EFFECTIVITY:
PAGE 4 24-30-00
Jan 10/90
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
3. MaintenancePractices
CAUTION: DO NOT EXCEED1000 HOURSBETWEENOVERHAULSUNLESSOTHERWISE
SPECIFIED.
As a precautionarymeasurebetweenoverhaulperiods,it is recommendedthat the starter
generatorsbe given a periodicinspection. (referto 5-50-00) Normallyit will be necessaryto
removethe starter generatorfromthe enginefor a thoroughinspectionof brushesand
commutator.Such removalalso affordsthe opportunityto inspectfor splineor dampenerwear, and
other details.
The instructionscontainedin this manualprovidea guidefor line maintenance,inspection,and
brushreplacementonly. Replacementof brushesat this level is made possibleby the use of
instantfilming brushes.
NOTE: No specialtools are requiredto accomplishline maintenanceof the startergenerators.
4. Removalof StarterGenerator
After enginecowlinghasbeen removed:
(a) Disconnectand mark electricalwiringat terminalblock.
(b) Disconnectcoolingair inlet and exhausthosesor ducts.
CAUTION: THE STARTERGENERATORMUSTBE SUPPORTEDBEFORELOOSENING
THE HOLDINGCLAMPAS DAMAGETO THE SPLINEMAYOCCUR.CARE
SHOULDALSO BE EXERCISEDIN THATTHE UNIT DOESNOT HITTHE
LOWERENGINEMOUNTWHEN REMOVINGIT FROMTHE ENGINE
ACCESSORYCOMPARTMENT.
(c) Supportstarter generatorand loosenclampbetweenQADand starter generator.
(d) Removestarter generatorby slidingaft and lift out of engineaccessorycompartment.
5. Installationof StarterGenerator
(a) Installstarter generatorby lift up and slidingforwardof the engineaccessorycompartment.
(b) Supportstartergeneratorand tightenclamp betweenQADand starter generator.
(c) Connectcooling air inletand exhausthosesor ducts.
(d) Connectelectricalwiringat terminalblock.
(e) Installengine cowling.
EFFECTIVITY:
24-30-00an
10/90
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DCGeneration (continued)
TerminalCover
Quick-Attach-Detach(QAD)
MountingKit
CorrectBrush
Torsion
Fan
Damper
Ring
V-BandAssembly
ExhaustAir Holes
CrossSectionof StarterGenerator
Figure 401
6. Adjustmentsof Starter Generator
The only adjustmentnecessaryto maintainthe propergeneratoroutput is locatedon the generator
control unit. A voltage of 28.5 volts mustbe maintained. All other control adjustmentsare made at
time of installationand need not be reset.
Since the starter generatorand regulatorunitsare designedfor use on a singlepolaritytype
electricalsystem,the followinglisted precautionsmust be observedwhen servicingthe charging
circuits.
CAUTION: FAILURETO OBSERVETHESEPRECAUTIONSCOULD RESULTIN SERIOUS
DAMAGETO THE ELECTRICALEQUIPMENT.
(a) Wheninstallinga battery,ensure that the groundpolarityof the battery and the ground polarity
of the startergeneratoris the same.
(b) Whenconnectinga boosterbattery,makecertainto connectthe negativebatteryterminals
togetherand the positivebattery terminalstogether.
(c) Whenconnectinga chargerto the battery,connectthe chargerpositiveleadto the battery
positiveterminal and the chargernegativeleadto the battery negativeterminal.
(d) Neveroperate the startergeneratoron an open circuit. Makeabsolutelycertainall connections
in the circuit are secure.
(e) Do not short acrossor ground anyof the terminalson the starter generatoror generatorcontrol
unit.
EFFECTIVITY:
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24-30-00
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040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
6. Adjustmentsof StarterGenerator (continued)
(f) A startergeneratorwith reversedpolarityin the output voltagemay be correctedby flashingthe
field as in the procedurebelow:
CAUTION: DO NOT FLASHTHE FIELDWHILESTARTERGENERATORIS IN
OPERATION.
(1.) Disconnectthe leadsto the propergeneratorcontrolunit.
(2.) Connectthe negativeterminalof a small battery (1.5to 6 volts), or an equivalentdc power
supply,to terminal E of affectedstartergenerator.
(3.) Connecta jumperwire from positiveterminalof samebatteryto terminalA of samestarter
generator.
NOTE: If flashingthe field fails to correctgeneratorpolarity,checkfor incorrect
connectionsor defectivefield circuit.
7. StarterGeneratorServiceTestSpecifications
Lear Sieglerleadingparticularsfor the 28-voltstartergeneratorsinstalledas standardequipment
are as follows:
CHART 2
STARTERGENERATORTESTSPECIFICATIONS
Rating(MinimumContinuous)
175amperes,28 volts at groundidle speedof 6,720 rpm.
300amperes,28 volts at 6,950 rpm.
300amperes,30.0 volts to maximumratedspeedof 12,000rpm.
ExternalStartingPowerLimitations:
1,700amperes maximum,self-limitingwith 30 volts maximumat start receptacleand 0.004
ohmaircraft circuitresistancewhenpowersupplyis connectedto terminalB (shuntstart).
Cooling......
....................................
CombinationSelf-Cooled& BlastAir
3.00 inches
Air Inlet OpeningDiameter.......................................................................................................
00 inches
Overall Length(Less Spline Drive)........................................................................................
HousingDiameter...............................................................................................................
86 inches
Weight (IncludingQADKit)* (Approx)...................................................................................
55 pounds
inch-pounds
OverhungMoment(Approx).............................................................................................153
Counterclockwise
Directionof Rotation(ViewingDrive End)......................................................................
Drive Spline& MountingFlange...............................................................................
Numberof Teethin Drive Spline..............................................
Drive Spline Pitch Diameter...............................................
Drive ShaftShear Torque(Nom.).................................................................
MS3331-1P
12
....
.... 0.600 inch
...
1,600inch-pounds
TerminalDesignations
Positive....................................................................................B+
Negative........................................................................................
PositiveField.....................................................................
...........
Equalizer........................................................
EA+
..D
EFFECTIVITY:
040-999
24-30-00
PAGE
7
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
8. CheckingStarter GeneratorSystem
The starter generatorsystemincorporatestwo ammeterswhich providean independentoutput
checkof eachgeneratorand a voltmeterwhich monitorsthe electricalbus voltage. Shouldeither
ammeterfail to indicatean outputfrom its associatedgenerator,checkthe appropriatecircuit
breaker (referto 24-61-02wiring diagrammanual). If the circuit breakersare in their normal
operatingposition,a furthercheckof the systemshouldbe accomplished.
(a) Ensurethat the ammetersare operatingproperly.
(b) Ensurethat all electricalunits are off and batteryis fully charged.
(c) Disconnectelectricallead at terminalstud B+on startergeneratorbeingtested(L or R).
(d) Turn on battery master switchand turn selectorswitch (L or R) for the unit beingtested to the
STARTposition.
(e) Usinga voltmeter,attachpositive leadto the electricallead removedfrom terminalstudB+ on
starter generatorand the other voltmeterleadto airframeground. Voltmetershould readthe
battery voltage of 24 volts.
(f) Turn battery masterswitch off.
(g) Disconnectthe voltmeterpositive leadfrom wire removedfrom startergeneratorterminalstud
B+.
(h) Connectelectricallead previouslyremovedto B+terminalstud on starter generator.
9. GeneratorBrush Inspection
Generatorbrush inspectionis recommendedat 100 hour intervals. Bymeansof the diagonalwear
groove on the side of each brush,which shows 100%usefullife when new,the percentageof
remaininguseful life is easilyestimatedat eachinspection. Inspectgeneratorbrushesas follows
to determinecontinuedairworthiness:
(a) Removebrush coverfrom unit.
(b) Removescrewssecuringbrush leadsto brush holders. With a stiffwire hook,lift springsfrom
brushesand removebrushes.
NOTE: If brusheswill be reused,markeach brushto allowthat the brush will be installedinto
brush holderthat it was removedfrom.
(c) Determineremaininglife of each brush (referto Figure 601). If any one brushis estimatedto
be worn out beforethe nextinspectionor overhaul,replaceall brushes.
(d) After inspection,replacebrushcover. Ensurethat coveris seatedin housingrecessand that
exhaustair holesare locatedadjacentto terminalblock.
(e) Installgeneratoron aircraft.
(f) After inspection,replacebrushcover. Ensurethat coveris seatedin housingrecessand that
exhaustair holesare locatedadjacentto terminalblock.
(g) Installgeneratoron aircraft.
NOTE: Instantfilming brusheswhich do not havecoresor visible particlesare identifiedby
markingI/F,in additionto anygrade numbersand date codeletters.
NOTE: If new brusheshave been installed,it is not necessaryto conduct seatingor run-in
operationsdue to the ability of instant-filmingbrushesto carry full startingand
generatingcurrentswithoutsuch run-in. If the specifiedbrush is NOTone of these
types, the unit mustbe returnedto an overhaulshopfor brush replacement,run-in,
andtest.
EFFECTIVITY:
PAGE8
Jan10/90
24 3000
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. DC Generation (continued)
WEAR
GROOVE 1/2LIFE
REMAINING
NEWBRUSH
1/4 LIFE
REMAINING
Brush Wear Stages
Figure 601
SOLID STYLE
SPLIT STYLE
CORE TYPE
ALTITUDE
TREATMENT
RANDOMPARTICLE
TREATMENT
ALTITUDE
Instant Filming Brushes
Figure 602
EFFECTIVITY:
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10/90
9
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
Brush must be installedwithtop bevelas shownfor the
clockwisearmaturerotationindicated.(For reverserotation
units,top bevelwill be oppositeto that shown.
RECONNECT
NEGATIVE
FIELDLEAD
LAYBRUSHLEADSOVER
BRUSHSPRINGCLIPS
CorrectPositionof Brushes,Leads,and Springs
Figure 603
PAGE
10
Jan 10/90
24-30-00
EFFECTIVITY:
040-999
"
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DCGeneration (continued)
10. CleaningGenerator(Assembled)
(a) Removegeneratorfrom aircraft.
(b) Removebrush inspectioncover. Do not removebrushesduring internalcleaningand
resistancecheckprocedures.
(c) Internalcleaning:
WARNING: WHILE USING COMPRESSED AIR, WEAR GOGGLES OR FACE SHIELD TO
PROTECT EYES. DO NOT AIM AIR JET AT EXPOSED SKIN. USE A DUST
FILTER RESPIRATOR.
CAUTION: TO PREVENT DAMAGE TO BEARING SEALS AND TO AVOID FORCING
CONTAMINANTS INTO BEARINGS, DO NOT AIM AIR JET AT BEARINGS
(1.) Removecarbon and copperdust from armatureand stator windingsusing a low pressure
(40 psi) air supplyand nozzle. Startat the drive end of unit and work towardthe brushes
and commutatorarea.
WARNING: STODDARD SOLVENT IS TOXIC AND COMBUSTIBLE. DO NOT
BREATHE VAPORS. USE IN WELL VENTILATED AREA FREE FROM
SPARKS, FLAME, AND HOT SURFACES. WEAR SPLASH GOGGLES,
SOLVENT RESISTANT GLOVES, AND OTHER PROTECTIVE GEAR. IN
CASE OF SKIN CONTACT, WASH WITH SOAP AND WATER; IN CASE OF
EYE CONTACT, FLUSH EYES WITH WATER AND SEEK MEDICAL
ATTENTION.
CAUTION:
DO NOT USE LUBRICANTS OR UNAUTHORIZED SOLVENTS, WHICH
CAN REDUCE BRUSH LIFE.
(2.) Inspect interiorof unit for oil and other contaminants.Wipecontaminantswith cleancloth
moistenedwith Stoddardsolvent(FederalSpecificationP-D-680,Type 1).
(3.) Performan insulationcheckusing a volt-ohmmeteror equivalent(50-voltmaximum)
sourcetester. The dc resistancebetweenpositiveterminalB and the machineframe must
measureat least 10,000ohms. If resistanceagainmeasuresless than 10,000ohms,
return unitto an authorizedoverhaulcenterfor repair.
(4.) Inspect air intakeand exhaustscreensfor foreign material. Carefullyremoveforeign
materialand checkfor possibleinternaldamageto unit.
(d) Exteriorcleaning:
(1.) Ensurethat brush inspectioncover is installedto unit.
WARNING: REFER TO WARNING UNDER INTERNAL CLEANING STEP (C) BEFORE
PERFORMING NEXT STEP.
(2.) Thoroughlyclean exteriorof unitwith soft,clean cloth moistenedwith Stoddardsolvent
(FederalSpecificationP-D-680,Type 1). Wipedry with a clean, lint-freecloth.
(e) Inspectgeneratorbrushesusing procedurein GeneratorBrushInspectionsection.
EFFECTIVITY:
PAGE2
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
11. Descriptionand Operationof GeneratorControl Unit
The generatorcontrolunit is designedto incorporateall the normalfeaturesof a directcurrent28volt controlsystemin one compactunit havingthree printed circuitboards. By usinga comparator
amplifierwith a regulatedreferencevoltage,any differencebetweenthe referencevoltage and the
generatoroutput, as seen by the sensingline, is amplifiedand suppliedto the comparatorcircuit,
which controlsthe shunt field excitationof the generator.
The parallelingportionof the generatorcontrolunit (one on each engine)incorporatesthe
advantagesprovidedby integratedcircuitry. The differencebetweenthe interpolevoltageof the
local generatorand interpoleof the other generatoris amplified,inverted,and filtered. Any
resultantdifferenceis then coupledto the summingjunctionof the voltageregulatingcircuit. The
equalizingcircuitcontinuouslysumsthe differencebetweenthe interpolevoltagesof both
generatorsto zero.
The line contactorand reversecurrentcontrolcircuitryconsistsof two integratedcircuits and
differentialvoltage sensingoperations. Whenthe generatorhas attainedan output voltage equal
to the tie bus voltage,thesecircuits allowthe line contactorto close. They also monitorthe
differencein voltage acrossthe interpoleterminalsof each generator. Whenthis potentialreaches
a positivevoltageof 0.2 volts or more,the integratedcircuits,after a time delay inversely
proportionalto the magnitudeof the voltage,causethe line contactorto open. Whenthis happens,
the circuit automaticallyshifts backto differentialvoltage sensing.
12. Removalof GeneratorControl Unit
Locationof generatorcontrolunit is on the aft engine nacelleelectricalaccessorypanel, aft of
enginefirewallat station 108.50on respectiveengine.
(a) Removethe aft upper enginepanelfor accessto generatorcontrolunit.
(b) Disconnectelectricalplugfrom control unit.
(c) Removemountingscrewsand lift unitfrom airplane.
13. Installationof GeneratorControlUnits
(a) Positiongeneratorcontrol uniton aft enginenacellepaneland securewith appropriatescrews.
(b) Reconnectelectricalplug.
(c) Replaceaft engineaccesspaneland securewith appropriatescrews.
NOTE: The replacementof generatorcontrolunits requirea functionalcheckfor proper
operation(refer to CheckingGeneratorControlUnit paragraph).
14. CheckingGeneratorControl Unit
(a) Start enginesand set to a gas generatorrpm of 60%. Turn on all electricalequipmentavailable
in aircraft;systemvoltage mustremainat 28 + 1 volts.
NOTE: Voltageadjustmentscrewis locatedaboveconnectorof generatorcontrolunit,
betweenthe two test jacks.
(b) Turn the left startergeneratorswitchto the OFF position. This will transferthe full electrical
load to the right generatorand generatorcontrolunit. Systemvoltagemustremain at 28 ± 1
volts.
EFFECTIVITY:
040-999
Jan10/9024-30-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. DC Generation (continued)
14. CheckingGeneratorControl Unit (continued)
(c) Turn left startergeneratorswitchto the ON positionand turn the right startergeneratorswitch
off. This will transferthe full electricalload to the left startergeneratorand generatorcontrol
unit. The systemvoltage mustremain28 ± 1 volts.
(d) If the voltagedoes not remainat 28 ± 1 volts, checkthe generatorand battery,makingsure
they are in good condition.Checkall circuitconnectionsand all wiringin the startergenerator
systemfor unwantedresistance. Wiringconnectionsshouldbe cleanedand solderedas
necessary.Checkvoltmeterfor accuracyand repeattest. If systemvoltage still is not within 28
± 1 volts, referto performancetest.
of CrossStartRelays
15. Removal
The cross start relaysare locatedunderthe floorboards,aft of fuselage station99.00, betweenthe
crew seats.
(a) Determinethat electricalpoweris disconnected(batteryand externalpower).
(b) Removecenter avionicsconsoleand centerfloorboardsto gain accessto the contactors.
(c) Disconnectelectricalcables,bus bars and markto facilitate reinstallation.
(d) Disconnect20 gauge jumper betweencontactorcoils.
(e) Disconnectannunciatorwire (withfuse holder).
(f) Removescrewsto contactorand removeunit.
16. Installationof CrossStart Relays
(a) Positioncontactorson mountingplateand securewith appropriatescrews.
(b) Connectannunciatorwire, 20 gaugejumper,bus bars and all markedelectricalcablesto their
appropriateterminalsand securewith lockwashersand nuts.
(c) Reconnectbattery or externalpowerand performoperationalcheck.
17. Descriptionand Operationof Battery
The nickelcadmiumbatteriesmustbe keptclean and chargedto remainairworthy. Serviceis
requiredevery 100 hours or 60 days,whicheveroccurs first. Water consumptionis directly
proportionalto the overchargecurrentsexperienced.Servicefrequencydependson operating
conditions.
Importantprecautions:
WARNING: SERIOUS INJURY CAN RESULT WHEN THE FOLLOWING PROCEDURES FOR
CLEANING OR SERVICING A NICAD BATTERY ARE NOT FOLLOWED.
(a) Removeall metaljewelry,i.e. rings,watchbands,and bracelets. Dueto very highcurrent
capabilities,the batterycan quicklymeltor fuse metaland cause severeburns.
(b) Use only insulatedtools. Never usetools previouslyusedon leadacid batteries.
(c) Thepotassiumhydroxideand waterbatteryelectrolyteis causticand can cause severebums.
Wearprotectiveclothing(rubbergloves,apron,eye protection,etc.) while handlingthe
electrolyte. If contactoccurs,flush immediatelywith water and neutralizewith aceticacid,
vinegar,lemonjuice or a 10%solutionof boric acid. Flusheyeswith water continuouslyand
contactphysicianimmediately.
(d) Hydrogenand oxygengasesdo generateand are highlyexplosive. Vent thesegases to the
outsideair when charging. In caseof chargingindoorswith centralair conditioningpresent,
thesegases can be circulatedvia the duct work throughoutthe building. Outsideventingof the
batteryservice area is mandatory.
(e) ;Makesure all electricalconnectionsare tight and secureto preventelectricalarcswhich could
triggerand explosion.
(f) Keepcell vent plugs in placeat all times exceptwhen inspectingor adjustingelectrolytelevels.
EFFECTIVITY:
040-999
24-30-00
PAGE
13
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DCGeneration(continued)
18. Fault Isolation
CHART 3
FAULTISOLATION(BATTERY) (Sheet 1 of 3)
Fault
Batterydisconnectsolenoid
doesnotoperate.
Batterydisconnectsolenoid
intermittentoperation.
electrolyte
Excessive
spewage.
Cause
Remedy
Open circuit.
Repairwiring.
Dirty contacton
connectorplug.
Cleancontacts.
solenoid
Open-circuited
coil.
Replaceunit.
Plungerbinding.
Removeand wash plunger
and housingthoroughlywith
stoddardsolution. Change
springcompressiononly as
a last resort.
Short-circuitedcoil.
Looseelectrical
connection.
Replacecoil. Clean
andtightenelectrical
connections.
Plungerbinding.
See remedypertainingto
"Plungerbinding"under
"Does not operate."
Badly burnedpoints.
If pointscannotbe dressed
down,replacetheunit.
leveltoohigh.
Electrolyte
Cleanand adjustelectrolyte
level.
Ventcapslooseor damaged.
Replaceortightencaps,
recharge,andcheck
electrolyteleveland
clean.
cellcase.
Damaged
Shortoutall cellsto 0 volts
andclean,recharge,and
checkelectrolytelevel.
Replacedefectivecell.
Chargingvoltagetoo high.
check
Cleanandrecharge,
electrolytelevel,andcheck
batterychargesystem.
EFFECTIVITY:
040-999
PAGE14 24-30-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC Generation(continued)
18. Fault Isolation(continued)
CHART 3
FAULTISOLATION(BATTERY)(Sheet2 of 3)
Remedy
Fault
Cause
Excessuseof waterby
oneor morecells.
Leakyor defectivecellor
vent.
Inspectfor electrolyteleakage
andremoveandreplacedefectivecellsor vents.
Highchargevoltage.
Adjustgeneratorcontrolunit
voltageto 28 + 1 Vdc.
Formingduringcharge
afterwateraddition.
Lowconcentration
electrolyte.
Discharge;constant-current
charge. Replacedefective
cells.
foamingduring
Continued
Oilandgreasecontamination
in theelectrolyte.
Replacedefectivecells.
No batteryoutput.
Brokenor disconnected
links. Loosebattery
connector.Cellopen
internally.
Replaceor tighten links
and connector. Replace
defectivecell.
Lossof capacity.
leveltoo low.
Electrolyte
Charge,adjustelectrolyte
level, and capacitytest.
Chargingratetoolowin
service.
Chargeand capacitytest.
Check chargingsystem.
Toolittleusageor shallow
discharges.
Do a reconditioningcycle
per periodicbatterycheck
paragraph.
Batteryleft on load.
andcapacitytest.
Recharge
Chargernotoperating
properly.
andcapacitytest
Recharge
battery.Checkcharger
operation.
Internalconnectinglinks
loose.
Tightento propertorque
value; rechargeand capacity
connectorburned
External
or pitted.
Cleanor replace;recharge
andcapacitytest.
charging.
Belownormaloutput
voltage.
test.
EFFECTIVITY:
24-30-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC Generation(continued)
18. Fault Isolation(continued)
CHART 3
FAULTISOLATION(BATTERY) (Sheet 3 of 3)
Fault
Cause
Remedy
Terminallinks discolored
Looseterminalhardware.
Cleanor replacelinks
andtightenall terminal
to specified
hardware
torquevalues.
Burnedor pitted terminals.
Foreignmetallicobjectsin
thebattery;toolsdropped
intothe openbattery.
Locateandremoveforeign
objectsandreplacedefective
parts.
Burnedor pittedoutput
receptacle
terminals.
Improperly
fittingor loose
matingoutputconnections.
Replaceboth mating
connectors.
Distortionof cellcase
andcover.
Cellwithinternalshort.
and
disassemble,
Discharge,
replacedefective
cells.
Chargerfailure.
and
disassembly,
Discharge,
cells.
replacedefective
Pluggedventcaps, minor
explosion.
Discharge,disassemble,and
replacedefectivecells, and
replacevents.
Overheated
battery,
impropercooling.
and
disassemble,
Discharge,
replacedefectiveparts.
Majorexplosion:
Looselinks
Drycells
and
disassemble,
Discharge,
replacedefectivecells,link,
and
ventcaps,hardware,
or burned.
Distortionof batterycase
or cover.
case.
Highchargevoltage
Chargerfailure
Replacebatterycaseand
cover.
EFFECTIVITY:
040-999
Jan10/9024-30-00
10/90
24-30-00
Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
CHART 4
NICKEL CADMIUM BATTERY SPECIFICATIONS
BatteryType: 40776
Capacity: 40 AH at the 1 hour rate
Numberof seriesconnectedcells - 20 - NominalVoltage- 24
ConstantCurrentCharging:
Startingrate(Is) - 8.5 to 22 amperes- - Control Point30.5 volts
FinishingRate(If) - 4.0 to 10 amperes- - Trickle Rate215 to 430 milliamps
ConstantPotentialCharging:
Voltage(Ec)(See ConstantPotentialChargingV/T Table)43 amperesmin.
Inrushcurrentat abovevoltage:350 amperesmax.
FloatingVoltages:
0°F 29.0 to 31.0 volts
75°F 28.0 to 30.0 volts
100°F 27.4 to 29.4 volts
Cutoff Voltage:
DischargeRates:
Max. ShortTime:
10 sec. 1720 amperes
30 sec. 860 amperes
Max. Continuous:
430 amperes
1 hour rate: 43 amperes
5 hour rate: 9 amperes
20 hour rate: 2.25 amperes
15.0
20.0
21.0
22.0
(Cell) TerminalType: Screw - - ThreadSize: 10/32- - Torque: 34-38 in. Ibs
Depthin Baffle:
20 mm
ElectrolyteLevel:
During last 20 minutesof charge
CHART 5
CONSTANT POTENTIAL CHARGING V/T TABLE
BatteryTemp.(°F)
Volts/Cell
Voltage
0°
1.565
1.545
1.525
1.505
1.485
1.460
1.440
1.420
31.3 ± 0.5
30.9 ± 0.4
30.5 ± 0.3
30.1 ± 0.2
29.7 ± 0.2
29.2 ±0.2
28.8 ± 0.1
28.4 ± 0.1
°
20
40 °
60°
80°
1000
120°
140°
EFFECTIVITY:
040-999
17
PAGE
24-30 00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
Circuit Diagram No. 1
Ammeter
Load
Resistor
Load
Resistor
Shunt
DischargeCircuit (Preferred)
DischargeCircuit (Alternate)
Circuit DiagramNo.2
Ammeter
TemperatureProbe
Ammeter
Temperature
Probe
I
Shunt
Knife Switch
ChargingCircuit(Preferred)
ChargingCircuit (Alternate)
Charge/ DischargeSchematics(TypicalService)
Figure 301
EFFECTIVITY:
040-999
Jan 10/9024-30-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
19. ChargingBattery
A battery'scapacity is measuredin amperehours (AH), which is the productof the numberof
ampsflowingand the hours this currentflows. The chargerequiredis also measuredin ampere
hoursand is always somewhatlargerthan the dischargeobtainable. The amountof recharge
requiredat normal rates and temperaturesis 140%of the dischargeobtainable.
Voltagesvalues,currents,etc, refer to Chart 4. Chargingis most efficientwhen performedat
batterytemperaturesbetween+40°Fand +80°F. Do not start charging,exceptwhen necessary,if
the batterytemperatureis above100°F.
Do not charge a nickelcadmiumbattery in the proximityof leadacid batteries. Fumesor acid
spillagecan exist to contaminatethe nickelcadmiumbattery. If the sameequipmentis usedto
charge both types of batteries.cleanthoroughlywith a sodiumbicarbonatesolutionbeforeusing it
on nickelcadmiumbatteries. Thereare several methodsusedto chargethis type of battery. The
preferredmethodand an alternatemethodare presentedin Figure301.
20. ConstantCurrentCharging
If batterycharge is unknown,completelydischargethe batterybeforecharging.
(a) Chargebattery at 13.3 ampsuntil batteryvoltagereachescontrol point(30.5 volts).
(b) Thefinishingcharge rate will be 4 amps. Todeterminetime to fully chargebattery at finishing
rate,use the followingformula:
Tf = Is x Ts
3 x If
Tf - Time, in hoursrequiredfor finishingcharge.
Is - Startingcharge rate, in amps.
Ts - Time, in hours,of chargeat the startinguntil "ControlPoint"voltageis
reached.
If - Rate, in amps,of finishingcharge.
NOTE: For furtherinformationon battery referto SAFToperatingand maintenancemanual,
P/N DC 3-01-78-3176-5A.
21. ConstantPotentialCharging
(a) Chargethe batteryfor 4 hours at propervoltage(referto Chart 4). The chargershouldbe able
to delivera minimumof 43 amps.
(b) A nearlyfull charge may be restoredin one hour if the chargeris capableof delivering86
amps.
(c) A batteryin a dischargedstate will acceptvery high currents,for a few minutes,at the
beginningof the charge (350amps maximumin rush current). This currentdoes not damage
the battery,but the chargershould haveinherentcurrent limitingor be otherwiseprotected
againstoverload.
EFFECTIVITY:
19
24-30-00PAGE
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
22. BatteryCell Replacement
WARNING: TO AVOIDPERSONALINJURYOR BATTERYDAMAGE,DO NOT REMOVEA
CELL OR TERMINALLUGSFROMA CHARGEDBATTERY.WEARSAFETY
GOGGLESAND PROTECTIVECLOTHINGTO PROTECTEYESAND BODY
FROMANY ELECTROLYTESPRAYSQUEEZEDFROM REPLACEMENTCELL
WHEN IT IS PUSHEDINTO PLACE.
CAUTION:
DO NOT REMOVEDEFECTIVECELL FROMBATTERYUNTILA PROPER
REPLACEMENTCELL IS AVAILABLE(REFERTO PARTSCATALOGFOR
CORRECTPARTNUMBER).
(a) Dischargebattery at 20 ampsfor 2 hours.
(b) With clip leads,short acrosseachcell as voltagegoesbelow 1/2 volt.
(c) After all cells are shorted,removeconnectingstrapsfrom defectivecell.
(d) Lift defectivecell from battery by liftingat terminalsusing a speciallyfabricatedtool (referto
Figure 302).
(e) Installnew cell ensuringit is dischargedand polaritysymbolsare properlypositioned.
NOTE: To aid insertion,be sure ventson all cells in the same row,includingreplacementcell,
are loosened.
(f) If cell is difficultto install,apply vaselineor Shell Dorina2 on sidesof replacementcell.
(g) Reassembleattachinghardware.
NOTE: These parts are specificallydesignedto providean adequateelectricalconnection.
Neveruse homemadehardware.
Socket screwterminals
(2 required)
Appropriate
thread (5/16)
FabricatedCell PullerTool
Figure 302
EFFECTIVITY:
Jan 10/90
Jan 10/90
24-30 00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. DC Generation (continued)
THERMOSTAT
FUSEHOLDER
I
Cell Layout- NickelCadmiumBattery
Figure 303
23. Removalof Battery
The batteryis locatedbehindthe nosecone.
(a) Openforwardbaggagecompartmentdoor.
(b) Releasenosecone latch locatedimmediatelyto the left, insidethe baggagecompartmentdoor.
(c) Swingopen nosecone,cut safetywire on large Elcon electricalconnectorand unplug
connector.
(d) Locatesinglewire (in lineconnector)to batterytemperatureprobeand disconnectthe wire
ends.
(e) Turn camlocksloose at bottomfront of batteryand removebattery supportangle.
(f) Slidebattery forwardon tracks andwithdrawfrom nosesection. Be careful,batteryweightis
considerable.
24. Installation
of Battery
(a) Placebattery on mountingbracketand reconnectvent lines previouslyremoved.
(b) Slidebattery intoplace and securewith two camlockson bottom front of battery.
(c) Connectbatterytemperatureprobewire from top of battery,at in-lineconnector.
(d) Put electricalconnectoron batterywith (+) symbolson connectoron top and (-) symbolson
connectoron bottom. Secureby tighteningknobon connector.
(e) Secureknobby placingsafetywire throughtwo holes on knobto two nutson each side of
knob.
(f) Close nosecone and securewith latch. Closesmall accessdoor to latchingmechanismand
securewith screwtype fastener.
EFFECTIVITY:
040-999
24-30-00
PAGE
21
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
25. TestingBatteryTemperatureSensor
Use the followinginformationto checkthe temperaturesensoroperation:
(a) Set up a hot oil bath at 130°F and obtainan ohmmeter.
(b) Removethe temperaturesensorunitfrom the batteryand disconnectthe wire at the fuse
holder.
(c) Connectthe probes of the ohmmeterto the temperaturesensor;there shouldbe no reading.
(d) Submergethe temperaturesensorintothe hot oil and observethe ohmmeter;a readingshould
be indicated. The sensorshould resetwhen removedfrom the hot oil, after beingallowedto
cool down to 110°F.
(e) With testcompleted,reinstallthe temperaturesensorto the battery and connectthe fuse
holder. Ensurethat the fuse is installedand in goodcondition.
26. Adjustmentof ElectrolyteLevel
WARNING: WEAR PROPERPROTECTIVEGEARWHEN PERFORMINGBATTERY
MAINTENANCE.ELECTROLYTE(POTASSIUMHYDROXIDE)IS VERYCAUSTIC
AND MAYCAUSEPERSONALINJURYOR AIRCRAFTSTRUCTURALDAMAGE.
IF INJURED,NEUTRALIZEWITH3% BORICACID SOLUTIONIN WATER,AND
SEEK MEDICALATTENTION.
The liquidlevel in battery varies with the stateof charge. It must be visible abovebaffletop when
the battery is fully charged.
(a) Adjust level after battery is fully chargedand is at rest for 2 to 4 hours disconnectedfrom any
circuit.
(b) Removeventplugfromeachcell.oneat atime,to adjustelectrolytelevel.
tubeopenat bothends,aboutsixincheslong,and0.025inchin diameter.
(c) Usea transparent
Insertit perpendicular
to bafflesintofillerwelluntilendrestslightlyon cellbaffle.Thenplace
indexfingerovertopendof tubeandwithdraw.
(d) Tubeliquidlevelmustbe between0.375- 0.5inch. If liquidlevelis above0.5inch,remove
excesswith a syringeor squeezebottle.If liquidlevelis below0.375inch,addonlydistilled
water.
(e) Rechargebatteryat 4 ampsfor 1 hourafteraddingdistilledwaterto preventdamagefrom
freezingduringcoldweather.Removebatteryfromaircraftfor charging.
27. BatteryInspection
wear,corrosion,cracks,bent
of arcing,mechanical
(a) InspectElconconnectorfor evidence
especiallyaroundthe
terminals,andgeneralphysicalcondition.Lookfor signsof overheating,
connectorscancausedangerousoverheating
positiveand negativeconnectorpins. Defective
of thenicadbattery.Usingan ohmmeterseton highest
dueto thehighcurrentcapabilities
scale,verifytheresistanceofthe insulationis infinitebetweentheconnectorpins.
NOTE: Referto BatteryDisconnect
andReceptacle
Inspection
paragraphin thischapterfor
completeinspection
procedure.
PAGE22
24-30-00
24-30-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
28. BatteryDisconnectand ReceptacleInspection
The purposeof this inspectionis to detectwornor weakenedbatteryquick disconnectsthereby
reducingthe possibilityof the existenceof a potentiallyhazardouscondition.
(a) Disengagethe batterydisconnectfrom the matingreceptacleand inspectfor the following:
(1.) Corrosionor pitting of the helix.
(2.) Excessivefree play in the handwheel-wormassembly.
(3.) Evidenceof arcingor bum markson the helix.
(b) Insertthe 0.385 inch diameterend of the inspectiongauge (Elcon InspectionGaugeNo. 029)
intoeach helix to a depth of 0.437 inches. The fit shall be snugwith a force to removegreater
than one pound. This is to test the resiliencyof the helix to an oversizedpin.
(c) Insertthe 0.370 inch diameterend of the inspectiongauge into each helixto a depth of 0.437
inches.The fit shall be snugwith a nominalforceto removeof one pound. Thiswill ensure
propercontactto a worn or undersizedcontactpin.
(d) Withthe matingdisconnectremoved,inspectthe battery receptacleas follows:
(1.) Inspectthe contact pinsfor evidenceof corrosionor pitting.
(2.) Inspectthe contact pinsfor evidenceof arcingor burn marks.
29. PeriodicBatteryCheck
The conditionof the batteryshould be determinedevery 50 to 100 hours initially. Periodicbattery
checkintervalsmaybe variedas serviceexperiencedictatesby referringto BatteryService
Recordin chapter5. If the temperaturesare above100°Ffor an extendedperiod,or if battery
problemsarise,the batteryshouldbe checkedmorefrequently. This checkwill also equalizethe
cell voltages.
(a) Dischargethe battery.
(b) Rechargebattery.
(c) Checkthe electrolytelevel;adjust if necessary.
(d) Restbattery for 24 hours.
NOTE: The batterycells mustbe at roomtemperature.
(e) Dischargethe battery at 40 amps; at one hourthe battery voltageshould be 20 volts.
(f) If the battery voltageis below20 volts,rest batteryfor 4 hours and repeat steps2 thru 5.
(g) Duringthis discharge,checkthe individualcell voltages. If the batteryvoltage is againbelow
20 volts, replaceeach cell that fell below1 volt before 1 hour. Consultbatterymanufacturer's
serviceand repairliterature.
30. Cell VoltageCheck
The cell voltagecheck requiresthe use of a 0-50 Vdc rangevoltmeterwith at least2% accuracy;a
digitalreadouttype is suggested.
(a) Connectthe negativeleadof the voltmeterto the negativeterminalof the Elconconnector.
(b) Withthe positiveprobe, startingat the positiveterminalof cell number20, measureand record
voltagereadingsof all cells in reverseorderof numericalsequence(referto Figure24-10).
(c) Disconnectthe negativelead of voltmeterfrom negativeterminalof Elconconnectorand
connectpositiveleadof voltmeterto negativeterminalof Elconconnector.
(d) Withthe negativeprobe, startingat the negativeterminalof cell number1, measureand record
voltage readingsof all cells in numericsequence(referto Figure24-10).
(e) The defectivecell may be found by monitoringthe voltage readingsobtainedbetweeneach cell
terminaland the batterycase. The lowestvoltageswill occur at the terminalconnectorson
eachside of the defectivecell. Replacedefectivecell.
EFFECTIVITY:
040-999
24-30PAGE
23
24-30-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC Generation (continued)
31. BatteryCleaning
WARNING: DO NOT CLEANBATTERYWITH CHEMICALOR PETROLEUMBASELIQUIDS.
DO NOT USE SOLVENTSOF ANY KIND.
Nickelcadmiumbatteriesmustbe kept clean to maintainan airworthycondition. Contamination
can cause conductivepaths leadingto self-discharge.The battery shouldbe cleanedand serviced
every 100 operatinghours or 60 days, whicheveroccurs first. Chargerates determinewater
consumption,thus operatingconditionsmustdetermineservicefrequency. Nicadbatteriesshould
never be servicedin a lead acid batteryservicearea. Even smalltraces of sulfuricacid enteringa
nicad battery can cause permanentdamage.
(a) Wipe down all surfaceswith a cleandry cloth.
(b) Loosenstubborndepositswith a plasticscraperand usingfiltereddry low pressureair, with a
nonmetallicnozzle,blow awaycontamination(dust, salts,etc) from aroundthe tops of the cells
and case. Use eye protection.
EFFECTIVITY:
040-999
Jan10/9024-30-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. OverheadMeterand Switch PanelAssembly
switchpanelsmadeof
meterandswitchpanelassemblycontainsfourremovable
Theoverhead
plastic,threebezelmountedelectricalgauges,a seatbelt lightswitch,a domelight
electroluminescent
wipercontrolswitch.
switch,a no smokinglightswitch,anda windshield
panels in royalitetrim panels. They are located
The switchesare locatedon the electroluminescent
centrallyabovethe windshieldand on the cockpitceiling. The switchesare of the rockertype.
1. Removalof EngineControl PanelSwitch
(a) Removescrews securingcoverpanelto switchpanel. Removecover panel.
(b) Removescrewssecuringswitchto panelassembly.
(c) Removewire connectorfrom switch.
2. Installationof EngineControl PanelSwitch
(a) Attachwireconnectorto switch.
(b) Placeswitchin panelassembly.Securewithtwoscrews.
(c) Placecoverpanelon switchpanel.Securewithscrews.
3. Removalof RockerSwitch
(a) Removefour screwssecuringface panel. Pull panel awayfrom panelassembly.
(b) Removewires fromterminalson back of switch.
markwiresandlocationon switch.
NOTE: Tofacilitateinstallation,
(c) Removeswitchfromfacepanel.
of RockerSwitch
4. Installation
(a) Positionswitchin facepanelandpressintoplace.
(b) Connectwiresto terminalson rearof switch.
(c) Positionfacepanelon panelassembly.Securewithscrewspreviouslyremoved.
5. Removalof ElectricalGauge
andlowerassemblyuntil
(a) Removescrewssecuringoverheadmeter,switchpanelassembly,
electricalgaugesareaccessible.
wiringfrombackof gauge.
(b) Disconnect
(c) Removescrewssecuringgaugeto panel;removegauge.
of ElectricalGauge
6. Installation
(a) Placegaugein positionon backof panelassembly.Securewithscrews.
(b) Connectwiringto backof gauge.
andsecurewithscrews.
(c) Positionpanelassembly
EFFECTIVITY:
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. OverheadMeter and Switch PanelAssembly (continued)
THIS PAGEINTENTIONALLY
LEFT BLANK
PAGE
26 XX
Jan 10/90
XX XX
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. OverheadMeterand Switch PanelAssembly(continued)
SEATBELTS
NOSMOKING(a)
DIMMING
PUSHON
BATTERY
MASTER
EXT
PWR
ONON
RECOG
LO
RED
ON
OFF
STARTERDISENGAGE
ON
CLOSE
OFF
AISLE
STROBE POSITION LNDG/TAXI EXIT
LTS LTS
EXTERNALLIGHTS
LEFTENGINE
ON
HI
GEN
GEN
CLOSE
MANUAL
PLACARDS
DIM BRT
CENTER
DIM BRT
CO-PILOT
PILOT
MID
Fight ENGINE
RIGHT
LEFT
MANUAL
STARTERDISENGAGE
PANEL- UGHTS
-
WIPER
WINDSHEILD
HTG RESET LOCKOUT FEATHER
Q
I
lJLR0
IR
OiLCOOLERDOOR
ICE
PtTOPEN
PROTECTION
NOMAL
AIR
BLEED
AUTO
PUP
FUEL.
AUTO
IGNITION
STARTER
DIM BRT
DIM BRT
ROURESCENT
PANELIGHTS
OverheadSwitch Panel
Figure 2
EFFECTIVITY:
040-999
24-30-00 PAGE27
24-30-00 Jan
10/90
STARTER
IGNITION
AU
PROTECTION
OIL COOLERDOOR
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution
1. Main CircuitBreakerPanel
The maincircuit breakerpanelis locatedon the pedestalat the center of the flight compartment.It
contains50, 100, 200 amp circuitprotectorsprovidingoverloadprotectionfor variousaircraft
circuits.
2. Removalof Main CircuitBreakers
(a) Verifymasterbattery switch is off and battery is disconnected.
(b) Removecover assemblyfrom circuitbreakerpanelat base of pedestal. (Figure 401)
(c) Removescrewsecuringcircuitbreakerto circuitbreakerpanel. Removecircuit breakerfrom
panel.
(d) Removescrewsecuringelectricalwire to circuitbreaker.
3. Installationof MainCircuit Breakers
(a) Verifybattery master switchis off and batteryis disconnected.
(b) Positionrequiredwires at circuitbreakerterminals. Securewith screws.
(c) Positioncircuit breakerin circuitbreakerpanel and securewith screw.
(d) Installcover assembly.
CHART 1
CIRCUITBREAKERFUNCTION- MAIN BREAKERPANEL
CIRCUIT
BREAKER
BREAKER
VALUE(AMPS)
CIRCUIT
PROTECTED
BAT BUS TIE
200
BatteryBus to Batteryand CrossStart
NON ESSEN
100
BatteryBus to NonessentialBus
R GEN BUS TIE
200
BatteryBus to RightDistributionBus
L GEN BUS TIE
200
BatteryBusto Left DistributionBus
L MAIN
100
Left DistributionBusto Left MainBus
R MAIN
100
Left DistributionBus to RightMain Bus
ESSEN
100
Left DistributionBus to EssentialBus
AVIONICSNO. 1
50
Left DistributionBus to Number1 AvionicsBus
L MAIN
100
RightDistributionBusto Left MainBus
R MAIN
100
RightDistributionBusto RightMain Bus
ESSEN
100
RightDistributionBus to EssentialBus
AVIONICSNO. 2
50
RightDistributionBus to Number2 AvionicsBus
EFFECTIVITY:
040-999
1
24-60-00 JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
TerminalScrew
CoverAsserhbly
CircuitBreaker
AttachmentScrew
CircuitBreakerPanel
MainCircuitBreakerPanel
Figure401
NOTE: Referto 24-50-00and 24-60-00in the PA-42-720(AdvancedTrainer)Wiring Diagram
Manualfor schematics
of theACandDCDistribution.
4. ElectricalPower DistributionSystemTest
The followingtests of the electricalpowerdistributionsystem(diodes and circuitbreakerwiring)
are requiredat each100hourinspection.
(a) Testfor an open circuitin bus diodeand wiring interconnectas follows:
(7.)
Push
in
essential
breaker.
Pull
outesseial
breaker
on
right
side
of main
breaker
panel.
If
esse
ttial
bus
power
is lost,
diode
or
circuit
breaker
onpower.
wireP1
F-6
isopen
and
must
be
(1.)
Apply
dc
power
using
either
aircraft
engines
or
external
(1.)
Apply
dcleft
power
using
either
aircraft
engines
or
external
power.
(2.)
Pull
out
main
circuit
sreaker
. Check
that
equipment
Panel
(2.) Pullout leftmain circuitbreaker on leftside of mainbreaker panel. Checkthat equipment
poweredbyleftmainbuscontinues
to function.If left mainbuspoweris lost,diodeor
circuit
breaker
on
wire
P1
B-6
is
open
circuitbreaker on wire PIB-6 is open and
and must
must be
be replaced
replacedor
or reset.
reset.
(3.)
Push
in
left
main
circuit
breaker.
Pull
out
left
main
circuit
breaker
(3.) Push in leftmain circuitbreaker. Pullout left maincircuitbreaker on
on right
rightside
side of
of main
main
breakerpanel.Checkthatequipment
poweredbyleftmainbuscontinues
to function.If
leftmain
mainbus
buspower
left
power is
is lost,
lost, diode
diodeor
or circuit
circuitbreaker
breaker on
on connecting
connectingwire
wire P1A-6
P1A-6is
is open
open and
and
mustbe replacedor reset.
(4.) Pushin leftmaincircuitbreaker.Pulloutrightmaincircuitbreakeron leftsideof main
breakerpanel.Checkthatequipment
poweredbyrightmainbuscontinues
to function.If
right mainbus power is lost, diode or circuitbreakeron connectingwire P1D-6is open
andmustbe replacedor reset.
(5.) Pushin rightmaincircuitbreaker.Pulloutrightmaincircuitbreakeron rightsideof main
breakerpanel.Checkthatequipment
poweredbyrightmainbuscontinues
to function.If
right
main
bus
power
is
lost,
diode
or
circuit
breaker
on
wire
P1
C-6
is
open
and
mustbe
or reset.circuit
Pushbreaker
in rightmain
breaker.
(6.) replaced
Puefll
outdiode
esseial
left
breaker
panel.
If essential
buspower
is lost,
or circu breaker
on on
wire
Pside
-6ofismain
open
andmust
be replaced
or reset.
replacedorreset. Pushin essentialbreaker.
EFFECTIVITY:
(4.) Push
in left
circuit
and must
bemain
replaced
orbreaker.
reset. Pull out right main circuit breaker on left side of main040999
Jan
24-60-00
10/90PAG
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
4. ElectricalPowerDistribution
SystemTest (continued)
(b) Testfor shorteddiodesasfollows,referto Chart 2:
(1.) Placethebatterymasterswitchin theONposition.
68%N1 withall circuitbreakerspushedin.
(2.) Startleftengineonlyandrunat approximately
(3.) Placetheleft generator
switchin theONposition.
(4.) Pullouttherightgeneratorbustiecircuitbreakeron the maincircuitbreakerpanel.
(5.) Pulloutbothrightmainandbothessentialbuscircuitbreakerson maincircuitbreaker
panel.
(6.) Checkthattheequipment
poweredbyessentialandrightmainbusesareinoperative.
wireP1B-6of
(7.) If essentialandrightmainbuspoweris stallpresent,diodeon connecting
leftmainbus is shorted.
(8.) Pushin essentialbuscircuitbreaker,andpulloutleftmainbuscircuitbreakeron leftside
of mainbreakerpanel.
on leftandrightmainbusesareinoperative.
(9.) Checkthattheequipment
(10.)If leftandrightmainbuspowerisstill present,diodeon connecting
wireP1G-6of
essentialbus isshorted.
(11.)Pushin rightmaincircuitbreakerandpulloutleftmainandessentialcircuitbreakeron left
sideof mainbreakerpanel.
(12.)Checkthattheequipment
on leftmainandessentialbusesare inoperative.
wireP1D-6of
(13.)If left mainandessentialbuspowerisstill present,diodeonconnecting
rightmainbusis shorted.
(14.)Pushin all breakersandstartrightengine;shutdownleftengine.
(15.)Repeattheaboveprocedure
forthe rightgeneratorbypullingoutleftgeneratorbustie
breakeron maincircuitbreakerpanel.Withrightgeneratorswitchon,repeatsteps(5.)
through(13.),pullingtherightmain,essentialbus,andleftmaincircuitbreakerson right
sideof mainbreakerpanel.PUllingthesebreakerswilltest forshortsin diodeson
connecting
wiresP1A-6,P1F-6,andP1C-6respectively.
(16.)Pushallbreakersin andshutdownrightengine.
CHART 2
ELECTRICALPOWERDISTRIBUTIONDIODEOPERATIONALCHECK (Sheet 1 of 2)
L GEN DISTRIBUTION CIRCUITBREAKER CIRCUITBREAKER COMPONENTS
MALFUNTION
CIRCUIT BREAKERS
PULLED
ACTIVATED
Essential(100A)
L Main(100A)
R Main(100A)
R Gen Tie Bus (200A)
Yes
Yes
Yes
Yes
Essential(100A)
L Main (100A)
R Main(100A)
R GenTie Bus (200A)
Yes
Essential(100A)
L Main(100A)
R Main(100A)
R Gen Tie Bus (200A)
Yes
Yes
EFFECTIVITY:
Yes
Yes
Yes
Yes
Yes
REMARKS
Shorteddiode
on essentialbus
from RightDist.
Bus
Nopower
shouldbe
observed
on L & R
Mainbus
Shorteddiode
on L Mainbus
fromRightDist.
Bus
No power
shouldbe
observed
on Essen &
R Mainbus
Shorteddiode
on R Mainbus
fromRightDist.
Bus
Nopower
shouldbe
observed
on Essen&
L Mainbus
24-60-00Jan
1090
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC ElectricalLoadDistribution(continued)
CHART 2
ELECTRICALPOWERDISTRIBUTIONDIODEOPERATIONALCHECK (Sheet 2 of 2)
R GEN DISTRIBUTION CIRCUIT BREAKER CIRCUITBREAKER COMPONENTS
CIRCUIT BREAKERS
ACTIVATED
MALFUNTION
PULLED
REMARKS
Shorteddiode
on essentialbus
fromLeftDist.
Bus
No power
shouldbe
observed
on L & R
Mainbus
Shorteddiode
on L Mainbus
from Left Dist.
Bus
No power
shouldbe
observed
on Essen&
R Mainbus
Shorteddiode
on R Mainbus
from Left Dist.
Bus
No power
shouldbe
observed
on Essen&
L Mainbus
Essential(1OOA)
L Main (100A)
R Main (100A)
L GenTie Bus (200A)
Yes
Yes
Yes
Yes
Essential(100A)
L Main (100A)
R Main (100A)
L Gen Tie Bus (200A)
Yes
Essential(100A)
L Main(100A)
R Main (100A)
L GenTie Bus (200A)
Yes
Yes
Yes
Yes
Yes
Yes
Yes
5. MainBusTie CircuitBreakerandCrossfeedDiodeCheck
poweris routedthroughthe leftandrightdistribution
Thischeckensuresthatgenerator(electrical)
busesto the leftmain,rightmain,andessentialbuses.(referto Chart 3)
NOTE: All 200Atie busbreakersmustbe activatedduringthischeck.
CHART 3
MAIN TIE BUS CIRCUITBREAKERAND CROSSFEEDDIODECHECK (Sheet 1 of 2)
LEFT DIODE/ CIRCUITBRAKER OPERATIONCHECK
R GEN DISTRIBUTION CIRCUIT BREAKER CIRCUITBREAKER COMPONENTS
CIRCUITBREAKERS
CHECKED
ACTIVATED
PULLED
Essential(100A)
L Main (100A)
R Main (100A)
REMARKS
Observethe
Feederdiodes
equipment
and circuit
breakersattached operated
to L Gen Dist Bus bythe
Yes
Yes
Yes
appropbus
is powered
L GenDistribution
CircuitBreakers
Essential(100A)
L Main(100A)
R Main(100A)
Yes
Yes
Yes
EFFECTIVITY:
040-999
Jan 109024-60-00
PIPERAIRCRAFT
PA-42-720(AdvancedTralner)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
CHART 3
MAINTIE BUS CIRCUITBREAKERANDCROSSFEEDDIODECHECK (Sheet2 of 2)
RIGHTDIODE/ CIRCUITBREAKEROPERATIONCHECK
L GEN DISTRIBUTION CIRCUITBREAKER CIRCUITBREAKER COMPONENTS
CIRCUIT BREAKERS
PULLED
ACTIVATED
CHECKED
Essential(100A)
L Main(100A)
R Main (100A)
REMARKS
Observethe
Feederdiodes
equipment
and circuit
breakersattached operated
to R Gen Dist Bus bythe
Yes
Yes
Yes
appropbus
ispowered
R Gen Distribution
Circuit Breakers
Essential(100A)
L Main (100A)
R Main (100A)
Yes
Yes
Yes
6. Left and RightCircuitBreakerPanels
Theleftand rightcircuitbreakerpanelsareattachedto mountingbracketsto theleftandrightof
electricalsystemsin
panel.Thecircuitbreakersallowthecrewto isolateindividual
theinstrument
theeventof trouble.
panels.Thetoppanelcontains
Theleftcircuitbreakerpanelassemblyconsistsof threeindividual
indicatorlightsfor left pitotheat,rightpitothead,andstallwarningheat,prop/inletdeiceswitch,
ammeter,
andthe leftmaincircuitbreakers.Thecentercontainsessentialbuscircuitbreakers,
andthelowerpanelcontainstheaccircuitbreakers.
The right circuitbreakerpanel assemblyconsistsof three individualpanels. The top panel
containsan enginehour meter,wing and tail surfacedeice indicatorlights,and the right main
circuitbreakers. The center panelcontainsthe nonessentialbus circuitbreakers,andthe bottom
panelcontainsthe avionicscircuitbreakers.
plastic,andcircuitbreakersareWoodElectric,plug-intype.
All panelsare electroluminescent
usedin theaccircuitbreakerpanelareWoodElectriccircuitbreakerswiththreaded
Breakers
terminals.
EFFECTIVITY:
040-999
24-60-00
5
JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
7. Removalof Plug-inType CircuitBreakers
WARNING: ENSURETHATBATTERYMASTERSWITCHAND THE GENERATOR
SWITCHESARE IN THE OFF POSITIONWHEN WORKINGON THE CIRCUIT
BREAKERPANEL.
(a) Removedesiredcover panelfrom auxiliarycircuit breakerpanel.
(b) Unplugdesiredcircuit breakerfrom bus bar.
8. Installationof Plug-inTypeCircuit Breakers
WARNING: ENSURETHATBATTERYMASTERSWITCHAND THE GENERATOR
SWITCHESARE IN THE OFF POSITIONWHEN WORKINGON THE CIRCUIT
BREAKERPANEL.
(a) Verifythe circuitbreakeris of the correctamperage.
(b) Plug circuitbreaker intobus bar.
(c) Repalcecover panel.
9. Removalof Screw ConnectType Circuit Breakers
WARNING: ENSURETHATBATTERYMASTERSWITCHAND THE GENERATOR
SWITCHESARE IN THE OFF POSITIONWHEN WORKINGON THE CIRCUIT
BREAKERPANEL.
(a) Removepanelcoverfrom ac circuitbreakerpanel.
(b) Removetwo screwssecuringcircuit breakersupportbracket. Withdrawsupportbracketfrom
panel assemblywith circuitbrakersattached.
(c) Removescrewsecuringbus bar to circuit breaker.
(d) Removescrewsecuringwire to circuitbreaker.
(e) Removelocknust securingcircuitbreakerto supportbracket. Removecircuit breakerfrom
bracket.
10. Installationof ScrewConnectType Circuit Breakers
WARNING: ENSURETHATBATTERYMASTERSWITCHAND THE GENERATOR
SWITCHESARE IN THE OFF POSITIONWHENWORKINGON THE CIRCUIT
BREAKERPANEL.
(a) Placecircuit breakerinto supportbracket. Securewith locknut.
(b) Attach wire to circuitbreakerterminalwith screw.
(c) Attach bus bar to circuitbreakerterminalwith screw.
(d) Postionsupportbracketto panelassemblywith screws.
(e) Positioncover panel and securewith screws.
EFFECTIVITY:
040-999
Jan
10/90
24-60-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
CircuitBreakerTerminal
- Screw Attachment
Electroluminescent
Panel
0
Insulator
Plate
Insulator /AC Bus
Mounting Hardware
MountingPlate for AC Circuit
Breakers
Breaker
Locknutand
Washer
LeftAuxiliaryCircuitBreakerPanel
CircuitBreakerInstallation
Figure402
EFFECTIVITY:
040-999
7
PAGE
Jan
24-60-00
24-60
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
CHART 4
BREAKERFUNCTION- LEFT BREAKERPANEL (Sheet1 of 3)
USED
ON CODE
CIRCUIT
BREAKER
BREAKER
VALUE(AMPS)
FUELPUMP
INVERTERNO. 2
FUELTEMP SENSE
FUELFLOW
FUELPRESS
OIL PRESS
OIL TEMP
OIL COOLER
TORQUEMETER
BLEEDAIR CONT
PROPDEICE
10
15
5
AIR INTAKEDEICE
30
ICE VANECONT
7.5
HTG RESET
5
IGNITION
5
STARTCONT
ITT
EMER PRESS
SPK AMPLI
MAP LIGHTS
5
5
3
3
5
BETASOL
PRESSCONT
3
Jan10/90
24-60-00
5
5
3
3
5
3
3
30
5
CIRCUIT
PROTECTED
LeftEngineElectricFuelPump
Number2 dcto ac PowerInverter
FuelTemperature
Monitor
LeftEngineFuelFlowIndicating
LeftEngineFuelPressureIndicating
System
LeftEngineOilPressureIndicating
System
LeftEngineOilTemperature
Indicating
System
LeftEngineOilCoolerDoor
LeftEngineTorqueIndicatingSystem
LeftEngineBleedAirValve
LeftPropellerDeicerandDeiceTimer
LeftPropellerInboardHeatingElement
LeftPropeller
OutboardHeatingElement
LeftEngineAirIntakePartingStrip
LeftEngineLipDeicerShedAreaI
LeftEngineLipDeicerShedAreaII
LeftEngineIceDeflectorDoor,Relays,and
Indicator
LeftHydraulic
ToppingGeneratorReset
Switches
andSolenoid
LeftEngineIgnitor
LeftengineIgnitionMonitorRelay
LeftEngineAutomaticIgnitionTorqueSwitch
LeftEngineStartContactor
System
Temperature
LeftEngineInterturbine
Emergency
CabinPressureValve
SpeakerAmplifier
Leftand RightCockpitMapLights
No SmokingLight
FastenSeatBeltLight
PublicAddressChimeAmplifier
Leftand RightEngineLockPitchSolenoids
CabinDoorSolenoidValveVacuumRelief
Solenoid
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DCElectricalLoadDistribution(continued)
CHART 4
BREAKERFUNCTION- LEFT BREAKERPANEL (Sheet2 of 3)
USED
ON CODE
CIRCUIT
BREAKER
BREAKER
VALUE(AMPS)
B
B
B
B
B
LEFTPITOTHEAT
L. WINDSHIELDHEAT
L. WINDSHIELDCONT
FUELQUANTITY
SURFACEDEICE
5
35
5
5
5
B
B
B
A
B
B
B
PANELLIGHTSLEFT
PANELLIGHTSCENTEF
PANELLIGHTSRIGHT
LOGOLIGHTS
LANDINGLIGHT
TAXILIGHT
POSITIONLIGHTS
5
5
B
B
STROBELIGHTS
GEAR POS IND
10
5
B
GEARWARN
5
B
B
B
B
B
B
B
B
B
B
B
B
INVERTERNO. 2
ELECTTRIM
PHONEAMP 1
LEFTALTIMETERENC
ANNUNMALF
ANNUN
L. GEN RESET
R. GEN RESET
VOLTAGECONT
VOLTAGECONT
STALLCONT
STALLHEAT
15
3
2
3
5
5
EFFECTIVITY:
A: 040, 045-050
B: 040-999
5
15
10
10
5
5
5
10
10
5
15
CIRCUIT
PROTECTED
andSolenoid
LeftPitotTubeHeatContactor
HeatingElements
LeftWindshield
HeatingSolenoid
LeftWindshield
System
FuelQuantityIndicating
WingandTailDeiceEngageValve
WingandTailDeiceIndicator
WingandTailDeiceTimer
CockpitLeftPanelLights
CockpitCenterPanelLights
CockpitRightPanelLights
LogoLights
LandingLights
TaxiLight
LeftWing(Red),RightWing(Green),and
TailBullet(White)Lights
LeftandRightWingStrobeLights
GearLockedDownIndicatorLights
GearNotLockedWarningLight
GearDoorSwitch
GearSelectorSolenoidLock
GearDoorSolenoid
GearWarningHorn
GearWarningMuteSwitch
Number1 dcto ac PowerInverter
ElectricTrimServoPower
Pilot'sAudioSelectorBoxPower
Pilot'sAltimeterservoPower
WarningLight
Malfunction
Annunciator
MasterWarningandTestCircuit
Annunciator
LeftStarterGeneratorReset
Reset
RightStarterGenerator
VoltageControl
LeftStarterGenerator
VoltageControl
RightStarterGenerator
LeftSideLeftComputerPower
Heat
LeftSideLeftTransducer
9
24-60-00JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
CHART 4
BREAKER FUNCTION- LEFT BREAKERPANEL (Sheet3 of 3)
USED
ON CODE
C
C
C
C
CIRCUIT
BREAKER
BREAKER
VALUE (AMPS)
5
C
C
C
A
A
C
C
WING INSPECTION
RECOGLIGHTS
q-SENSOR
FLUORESCENTLIGHTS
GLARESHIELD
FLUORESCENTLIGHTS
BRIT/DIM
VG1
RADAR
VG2
GPWS
VOICE RECORD
AIR SPD 1
EHSIHDG
C
EADIATTD
1
C
C
AP
NAV1
1
1
C
C
COMP 1
RMI 1
1
A
B
UNS1
FCS
1
C
Jan10/9024-60-00
10
3
5
5
1
1
1
2
1
1
1
1
1
CIRCUIT
PROTECTED
WingInspectionLight
LeftandRightRecognition
Lights
DynamicPressureSensorSwitch
Pilot'sandCopilot'sFluorescent
FloodLights
Pilot'sandCopilot'sFluorescent
FloodLightsIntensity
Pilot'sAttitudeGyroand FlightDirector
RadarAntenna
Copilot'sAttitudeGyroand FlightDirector
GroundProximityWarningSystem
FairchildCockpitVoiceRecorderUnit
Number1 AirspeedIndicator
Horizontal
SituationIndicatorHeadingFlag
Unit
PRocessing
Number1 Multifunction
Number1 DisplayProcessing
Unit
Electronic
AttitudeDisplayUnitFlag
Processing
Unit
Number1 Multifunction
Number1 DisplayProcessing
Unit
AutopilotComputer,
YawRateGyro
Number1VeryHighFrequency
NavigationReceiverac Power
Number1 CompassSystem
Number1 RadioMagneticIndicator
Number1 VORon RMI1
Universal
Navigation
System
FlightControlSystemPower
Unit
Processing
Multifunction
Unit
DisplayProcessing
EFFECTIVITY:
A: 048-050
B: 040-047
C: 040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution(continued)
CHART 5
BREAKERFUNCTION- RIGHTBREAKERPANEL (Sheet1 of 4)
USED
ON CODE
CIRCUIT
BREAKER
BREAKER
VALUE(AMPS)
BLEEDAIR CONT
TORQUEMETER
OIL COOLER
OILTEMP
OIL PRESS
FUELPRESS
FUELFLOW
OXYGENCONTROL
EMERGGEAREXT
3
3
5
3
3
FUELPUMP
STALLCONT
STALLHEAT
ITT
STARTCONT
IGNITION
10
5
15
3
5
5
HTGRESET
5
ICEVANEAND CONT
7.5
5
5
3
7.5
AIR INTAKEDEICE
30
PROP DEICE
30
WINDSHIELDWIPER
R.WINDSHIELDHEAT
R.WINDSHIELDCONT
R. PITOT HEAT
HOURMETER
10
35
5
5
3
CIRCUIT
PROTECTED
Right EngineBleed Air Valve
Right EngineTorqueIndicatingSystem
Right EngineOil Cooler Door
Right EngineOil TemperatureIndicatingSystem
Right EngineOil PressureIndicatingSystem
Right EngineFuel PressureIndicatingSystem
RightEngineFuel Flow IndicatingSystem
EmergencyOxygenMask DeploymentSolenoid
EmergencyLandingGear Extension(NOTE:
7 and 7.5 amp breakersare rated equally)
RightEngineElectricFuel Pump
RightSide Lift ComputerPower
RightSide LiftTransducerHeat
Right EngineInterturbineTemperatureSystem
Right EngineStart Contactor
Right EngineIgnitor
RightEngineIgnition MonitorRelay
RightEngineAutomaticIgnition
TorqueSwitch
RightEngineHydraulicToppingGenerator
ResetSwitchand Solenoid
RightEngineIce DeflectorDoor Motor,Relays,
and Indicator.
RightEngineAir IntakePartingStrip
Right EngineShedArea I
Right EngineShedArea II
Right PropellerLip Deicerand DeicerTimer
RightPropellerInboardHeatingElements
RightPropellerOutboardHeatingElements
WindshieldWiperMotor
RightWindshieldHeatingElements
RightWindshieldHeat Solenoid
RightPitotTube Heat Elementand Contactor
HourMeter Instrument
EFFECTIVITY:
040-999P24-60-00
AGE11
24-60-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
CHART 5
BREAKERFUNCTION- RIGHTBREAKERPANEL (Sheet2 of 4)
USED
ON CODE
CIRCUIT
BREAKER
BREAKER
VALUE(AMPS)
A
CABIN COMFORT
5
A
A
RECIRFAN
ECS
15
5
A
A
A
A
READINGLIGHTS
CABIN LIGHTS
FLAP MOTOR
FLAP CONTROL
5
5
35
A
A
A
A
B
C
3
5
A
A
A
PROPSYNC
AUTO FEATHER
COMMODEPUMP
BEV UNIT
FUELTOTALIZER
FUEL REMAINING
TOTALIZER
AUDIOAMP 2
AUDIO2
COMM1
A
A
D
A
COMP1
XPNDER1
EMERGYRO
NAV1
3
2
5
2
D
UHF COMM
5
A
DME1
3
PAGE12
Jan
10/90
24-60-00
3
7
10
5
5
2
2
7.5
CIRCUIT
PROTECTED
CabinTemperature
Controller
CabinTemperature
Thermostat
HotAir BypassValveSwitch
Recirculating
FanMotors
ThermalSwitch
CabinOvertemperature
Switch
CabinOverpressure
Recirculating
DoorSolenoids
OverheadReadingandConsoleLights
Leftand RightCabinAisleLights
FlapMotor,DownSolenoid,UpSolenoid
PositionIndicator
PositionControlRheostat
Differential
ControlRheostat
TestSwitch
Propeller
Synchrophaser
System
System
AutomaticPropellerFeathering
CommodePumpPower
BeverageUnitandRazorInverter
FuelTotalizer
Totalizer
FuelRemaining
Copilot'sAudioPanelandAudioPanelLighting
AudioPanel
Observer
Number1 VeryHighFrequency
Communications
RadioPower
Number1 CompassSystem
Pilot'sRadarTransponder
Power
Gyro
Emergency
PilotandCopilot
Number1 VeryHighFrequency
dc Power
NavigationReceiver
UltraHighFrequency
Communications
Power
Transmitter/Receiver
Equipment
Pilot"sDistanceMeasuring
Radiodc Power
EFFECTIVITY:
A: 040-999
B: 045-047
040
D: 048-050
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoadDistribution(continued)
CHART 5
BREAKERFUNCTION- RIGHTBREAKERPANEL (Sheet3 of 4)
USED
ON CODE
CIRCUIT
BREAKER
BREAKER
VALUE(AMPS)
A
A
A
A
A
A
A
A
A
B
C
A
EADI1
DCP1
DPU1
MPU1
MFD
RADALRT
ADF
RADAR
RNAV
VOLTMON
VLF
NAV2
5
1
7.5
7.5
5
3
2
5
7.5
3
3
2
A
A
AIR DATA
DME2
1
3
A
A
A
A
A
A
A
A
EADI2
EHSI2
DCP2
DPU2
MPU2
ENCALT
ALTALRT
COMM2
5
5
A
C
D
A
D
A
A
A
COMP2
TAS COMP
XPNDER2
RMI 1
STNDBYGYRO
EMERBATT
AP
SERVO
3
1
2
1
1
15
5
10
EFFECTIVITY:
A: 040-999
B: 040-047
C: 048-050
D: 040-047,051-999
1
7.5
7.5
3
3
7.5
CIRCUIT
PROTECTED
Pilot'sHorizontalSituationIndicator
Pilot's DisplayControl Panel Power
Pilot's DisplayProcessingUnit Power
Pilot'sMultifunctionProcessingUnit Power
MultifunctionDisplayand DisplayFan Power
RadarAltimeterPower
AutomaticDirectionFinderReceiverPower
WeatherRadarControl Panel
Area NavigationComputerPower
VoltageMonitor
Very Low FrequencyPower
Number2 Very High Frequency
NavigationReceiverPower
Air DataSensorController
Copilot'sDistanceMeasuringEquipment
RadioPower
Copilot'sElectronicAttitudeDisplayIndicator
Copilot'sElectronicHorizontalSituationIndicator
Copilot'sDisplayControl PanelPower
Copilot'sDisplayProcessingUnit Power
Copilot'sMultifunctionProcessingUnit Power
Number2 EncodingAltimeterPower
AltimeterAlerter Power
Number2 Very High FrequencyNavigation
ReceiverPower
Number2 CompassSystem
True AirspeedComputer
Number2 RadarTransponderPower
Pilot'sRMIdc Power
Copilot'sStandbyGyro
EmergencyBatteryChargingUnit
AutopilotServo Power
AutopilotComputerPowerand Autopilot
SwitchingUnit
10/90
2460-00Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. DC ElectricalLoad Distribution (continued)
CHART 5
BREAKERFUNCTION- RIGHTBREAKERPANEL (Sheet4 of 4)
USED
ON CODE
CIRCUIT
BREAKER
BREAKER
VALUE (AMPS)
FCS
1
AIRSPD2
EADI2
1
1
EHSI2
1
COMP2
NAV2
1
1
RMI2
1
CIRCUIT
PROTECTED
FlightControlSystemPower
Unit
Processing
Multifunction
DisplayProcessUnit
Number2 AirspeedIndicator
AttitudeDisplayIndicatorFlag
Electronic
Unit
Processing
Number2 Multifunction
Number2 DisplayControlUnit
SituationIndicator
ElectronicHorizontal
HeadingFlag
Unit
Processing
Number2 Multifunction
Number2 DisplayControlUnit
Number2 CompassSystem
Number1 VeryHighFrequency
ReceiveracPower
Navigation
Number2 RadioMagneticIndicator
Number2 VORon RMI2
0
EFFECTIVITY:
040-999
Jan 10/9024-60-00
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
CHAPTER 25
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
25-EFFECTIVITY
25-CONTENTS
25-10-00
25-20-00
25-20-00
25-20-00
25-20-00
25-20-00
25-20-00
25-20-00
25-40-00
25-60-00
25-60-00
25-60-00
25-60-00
25-60-00
25-70-00
25-70-00
25-70-00
25-70-00
25-70-00
PAGE
DATE
1
1
1
1
2
3
4
5
6
7
1
1
2
3
4
5
1
2
3
4
5
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
CHAPTER
SECTION
PAGE
DATE
PAGES Jan
LIST OF
LISTOF EFFECTIVE
EFFECTIVE
PAGES
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER 25 - EQUIPMENT / FURNISHINGS
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
25-10-00
1
1
1
Flight Compartment
Removalof Crew Seats
Installationof CrewSeats
25-20-00
1
1
1
1
1
1
1
2
2
2
2
2
2
PassengerCompartment
Removalof PassengerSeats
Installationof PassengerSeats
Removalof Cabinets
Installationof Cabinets
Removalof Tables
Installationof Tables
Removalof Curtain
Installationof Curtain
Removalof Nav Kit Tie DownAssembly
Installationof NavKit Tie DownAssembly
Removalof ObserverConsoleCovers
Installationof ObserverConsoleCovers
25-40-00
1
1
1
Lavatories
Removalof ToiletSeat
Installationof ToiletSeat
25-60-00
1
1
1
3
3
4
5
Emergency
(ELT) EmergencyLocatorTransmitter
BatteryRemovaland Installation(Alkaline)
TestingEmergencyLocatorTransmitter
Pilot's RemoteSwitch
TestingPilot's RemoteSwitch
InadvertentActivation
25-70-00
AccessoryCompartments
EFFECTIVITY:
040-999
1
Jan
CONTENTS
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
/ Furnishings
Equipment
A. FlightCompartments
1. Removalof CrewSeats
as necessary.
(a.)Removeequipment
(b.)Removeseattrackendcoversandseatstops.
(c.)Moveseatto slotsin seattracksandlift seatofftracks.
of CrewSeats
2. Installation
(a.)Placeseatintoslotsin seattracks.
(b.)Moveseatto desiredposition.
(c.)Installseattrackendcoversandseatstops.
removed.
(d.)Reinstallotherequipment
SmokeGoggles
(IF INSTALLED)
-
Flashlight
Fire Extinguisher
(BEHINDPILOTSEATONLY)
Seat Recline
Handle
CrewSeatInstallation
Figure401
EFFECTIVITY:
040-999
1
25-10-00 JanPAGE
10/90
25-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Passenger
Compartment
1. Removalof Passenger
Seats
(a) Removetablesandotherequipment
asnecessary.
(b.)Removeseattrackendcoversandseatstops
(c.)Moveseatto slotsin seattracksandlift seatoff tracks.
2. Installation
of passenger
seats.
(a.)Placeseatintoslotsin seattracks.
(b.)Moveseatto desiredposition.
(c.)Installseattrackendcoversandseatstops.
(d.)Installtablesorotherequipment
thatmayhavebeenremoved.
3. Removal
of CabinetsandTables.
(a) Removecabinetsasfollows:
(1.) Turnoff electricalpower.
(2.) Slideseatsasnecessary
for easieraccess.
andtag electricalwiring.
(3.) Disconnect
to removedrawersandopentambor
(4.) Removeattachinghardware.(Itmaybe necessary
hardware.)
doorsto gainaccessto somemounting
(5.) Removecabinet.
(b) Installcabinetsasfollows:
(1.) Turnoff electricalpower.
for easieraccess.
(2.) Slideseatsas necessary
(3.) Positioncabinetto properlocation.
(4.) Connectelectricalwiring.
(5.) Attachmountinghardware.
(6.) Insertdrawersthat mayhavebeenremovedfor cabinetremoval.
(c) Removetablesasfollows:
(1.) Lifttableto openpositionor removetableleaffromtableframefor easieraccess.
tableplateassembly.
fromunderneath
(2.) Removeattachinghardware
(3.) Removetable.
(d) Installtablesasfollows:
(1.) Positiontableto properlocation.
(2.) Attachmountinghardware.
(3.) Installtableleaf if it wasremoved.
EFFECTIVITY:
25-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Passenger
Compartments
(continued)
4. Removaland Installation
of Curtain.
(a) Removecurtainasfollows:
(1.) Removecurtaintrackendcovers.
(2.) Slidecurtainfromtrack.
(b) Installcurtainasfollows:
(1.) Positioncurtainontotrack.
(2.) Installcurtaintrackendcovers.
5. Removalof NavKitTie DownAssembly.
(a.)Removemountingboltsattachingnavkit tiedownassemblyto seattrack.
(b.)Removeassembly.
6. Installation
of NavKit Tie DownAssembly.
(a.)Positionassemblyto properlocation.
(b.)Attachmountingboltsto secureassemblyto seattrack.
7. Removalof ObserverConsoleCovers
(a.)Turnoff electricalpower.
NOTE: Consolecoversareattachedto consoleframewithVelcromaterial.
(b.)Disconnect
communication
system.
(c.)Removetopcoverbypryingoff withhands.
(d.)Removebottomcoverby pryingoff withhands.
8. Installation
of ObserverConsoleCovers.
(a.)Turnoff electricalpower.
(b.)Positionandsecurebottomcoverintoproperlocation.
(c.)Positionandsecuretopcoverintoproperlocation.
(d.)Connectcommunication
system.
EFFECTIVITY:
040-999
Jan 109025-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Compartment(continued)
A. Passenger
Seat ReclineButton- Locatedon
insidesurfaceof leftarmrest
(RightSideForwardPassenger
SeatDoesNotRecline)
Seat Track Latch
ReleaseHandle
PassengerSeat Installation
Figure 401
EFFECTIVITY:
040-999
25-20-00 Jan 10/9
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PassengerCompartment (continued)
Seat Back -
AdjustLever
SeatTrackLatch
ReleaseHandle
ObserverSeats Installation
Figure 402
EFFECTIVITY:
040-999
Jan 10/90 25-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PassengerCompartment(continued)
VanityCabinet
RefreshmentCabinet
Table Plate
-
StorageCabinet
Table
TableLeaf
Cabinetsand TableInstallation
Figure 403
EFFECTIVITY:
040-999
252000
PAGE5
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. PassengerCompartment (continued)
0
TrackEnd
Cover
Curtain
Top Cover
Bottom
Cover
NavKit Tie DownAssembly
ObserverConsole
ObserverConsole,Nav Kit Tie Down,and Curtain Installation
Figure 404
EFFECTIVITY:
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MAINTENANCEMANUAL
A. PassengerCompartment(continued)
SEATINGARRANGEMENT
Seat Stops
Figure 405
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Lavatories
1. Removal
of ToiletSeat.
(a.)Liftup lid andremovepail.
(b.)Disconnect
relieftube hoseatfloorboard.
(c.) Releasewedjit fasteners.
(d.)Liftupframeandslideaft.
(e.)Removeseat.
2. Installation
of ToiletSeat.
(a.) Positionseatto properlocation.
(b.) Securebottomframeto wedjitfasteners.
(c.) Connectrelieftube hoseto floorboard.
(d.) Placepail intoposition.
(e.) Checkrelieftube operationby pouringcup of waterthrough hornwith buttondepressed. If
waterdoes not drain, checkhosefor pinchingor kinks.
Wedjit Fastener
ToiletSeat Installation
Figure 401
EFFECTIVITY:
040-999
25-40-00 Jan 10/901
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Emergency
locatortransmitter(ELT),thepilot's
checksof the emergency
Thischapterdescribestheoperational
for battery
instructions
installation
and
remoteswitchusedwiththe ELT,andincludesthe removal
replacement.
LocatorTransmitter
1. (ELT)Emergency
battery.Theuseablelifeof this
Theelectricalpowerfor theELTis suppliedby a self-contained
dateis marked
replacement
mandatory
The
batteryis19 monthsfromthedateof manufacture.
is installed.
battery
the
when
ELT
the
on
marked
be
must
date
on eachbattery.Thereplacement
usedin an
been
has
transmitter
the
if
replaced
be
must
battery
the
to FAAregulations,
According
to
is
necessary
It
time.
test
accumulated
of
hour
one
than
more
has
or
situation
emergency
battery.
the
replace
to
aircraft
the
from
removethe ELT
2. BatteryRemovaland Installation(Alkaline- 19 monthbattery)
CAUTION: Do not removethe insidelip sealantfrom the new battery pack. The sealantserves
as a watertight seal and mustnot be removed.
The ELTis locatedunderneaththe dorsalfin betweenstations310.00 and 327.00.
(a) Removethe accesspanelon the dorsalfin at station321.00.
(b) Disconnectthe antennacable fromthe transmitter. (Figure 1)
(c) To removethe ELT,releasethe latch on the strap and slide the ELToff the bracket.
(d) Disconnectthe pilots removeswitch harnessfromthe transmitter.
(e) Extendthe portableantenna. (Figure 2)
(f) Unscrewthe four screws holdingthe controlhead to the battery casing. (The controlheadbatterycase slides apart. Batteryconnectionleads are approximately3" long.)
(g) Disconnectbattery by unsnappingthe snapoff battery pigtailterminalsfrom the bottomof the
transmitterprinted circuitboard.
(h) Beforeinstallingthe new batterypack, checkreplacementdate printed on the battery. Mark
dateon theoutsideof the ELT.
(i) Connectnewbatterypackterminalsto thebottomof thetransmitterprintedcircuitboard.
(j) Reinsertthecontrolheadsectionintothebatterypack;be carefulnotto°pinchwires. Replace
fourscrews.If thefourholesdo notlineup,rotatethebatterypack180 andreinsert.
(k) Connectthepilot'sremoteswitchharnessto thetransmitter.
(I) Placetransmitterinto itsmountingbracketandlatchstrap.
(m)Connecttheantennacableto thetransmitter.Ensurecontactseparatoris insertedbetween
portableantennacontactfingerandportableantenna(seeFigure1).
NOTE: Testunitoperationbeforeinstallingthe accesspanel.
(n) Installaccesspanelon thedorsalfin. Enterthe newbatteryexpirationdateintotheaircraft
logbook.
EFFECTIVITY:
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Jan10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Emergency (continued)
NOTCH
ANTENNABLADE
TOUCHES
PORTABLE
FINGERCONTACT
PIN
PORTABLE
ANTENNA
OPERATIVE
BUTSTORED
ANTENNA
EXTENSION
TAB
VIEW A
ANTENNA
EXTENSION TAB
LATCH
SET
ON-OFF-ARM
SWITCH
TO "ON"
ANTENNA
POPSOUT
OFCHANNEL
ANDDOWN
VIEW B
/
\
PULLTAB
PIN
STOP
TO EXTENDTOFULLLENGTH
VIEW C
ELT Portable Folding Antenna
Figure 1
PORTABLE
ANTENNA
CONTACT
CONTACT
SEPARATOR
PORTABLE ANTENNABLADE
NOT MAKINGCONTACT
- FINGER
FIXEDANTENNA'S
CABLECONNECTORAND
CONTACTSEPARATOR
ELT UsingFixedAircraftAntenna
Figure 2
EFFECTIVITY:
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040-
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Emergency(continued)
LocatorTransmitter
3. TestingEmergency
of 121.5and243.0mHz. Bothfrequencies
frequencies
operateson emergency
Thetransmitter
tests,the
anyELToperational
Beforeperforming
byvariousFAAinstallations.
are monitored
mustbe observed:
followingprecautions
energyis not
to ensureelectromagnetic
ConductELTtestingin a screenroomor metalenclosure
mustbe adheredto:
radiated.If a shieldedenclosureis notavailable,thefollowingprecautions
NOTE: For detailedinformationconcerningELTtesting, consultFAA AdvisoryCircular,AC 20-81.
(a) Donottest longerthanthreeaudiosweeps.
(b) Usea dummyloadasa substituteif theantennais removed.
duringthefirstfiveminutesafterany hour.
(c) Testingof the ELTmustonlybe conducted
at
a timeotherthanfiveminutesafterthehour,the
be
conducted
testsmust
(d) Iftheoperational
withthe nearestFAAtowerorflightservicestation.
testmustbecoordinated
To conducttest, proceedas follows:
(a) Removeaccess panelor cover to gaintransmitteraccess.
(b) Turn master switch ON.
(c) Switch receiverON and tune to 121.5mHz. Deactivatesquelchand turn up volume until slight
backgroundnoisecan be heard.
NOTE: If the aircraft is not fittedwith a communicationreceiver,requestthat the tower listen
for your test.
switchto ONposition.KeepswitchONfor a few
settheON/ARM/OFF
(d) Ontransmitter,
thensetto OFF(orARMif OFFdoesnotexist). Returnto ARMposition.
seconds,
NOTE: Thetest transmissionshould be pickedup by the aircraftcommunicationsreceiveror
controltower. Duringcold weather,there could be a slightdelay beforetransmission
occurs.
downwardswepttone.
transmittermustemita characteristic
(e) A properlyfunctioning
switchis in theARMposition.
ON/ARM/OFF
be suretransmitter
(f) Whentest is completed,
(g) Placeaccesspanelondorsalfin at station321.0andsecurewithscrews.
switchfromARM
ON/ARM/OFF
thetransmitter
NOTE: Whencheckingthe ELTby alternating
to ON,theswitchmustbeputin theOFFpositionbeforegoingbackto ARM. Under
thetransmitterswitchmustbe setto ARM.
normalconditions,
NOTE: Inspectthe externalwhipantennafor anydamage.Avoidbendingthewhip. Any
sharplybentor kinkedwhipmustbe replaced.Antennadamagemaycausestructural
failureof whipin flight.
4. Pilot'sRemoteSwitch
NOTE: Undernormalconditions,the remoteswitch must be set to ARM.
Thepilot'sremoteswitch,locatedon theoverheadswitchpanel,is providedso thetransmittercan
frominsidethecabin.Theswitchis lockedintoeachposition.Tomovetheswitch,
be controlled
the togglemustbe pulledoutandmovedto thenewposition.Thepilot'sremoteswitchis
POSITION).Theswitchis normallyleftin thedownor ARM
to ONandARM(NORMAL
positioned
off, movetheswitchto theONpositionforonesecondandthen
position.Toturnthetransmitter
returnit to the ARMposition.Toactuatethetransmitterfortestsorotherreasons,movethe switch
is desired.
upwardto theONposition.Leaveit in thatpositionas longastransmission
EFFECTIVITY:
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JanPAGE
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Emergency(continued)
5. TestingPilot'sRemoteSwitch
Beforeperforming
any pilot'sremoteswitchoperational
test,thefollowingprecautions
mustbe
observed:
NOTE: Thetransmitteroperateson the emergency
frequencies
of 121.5and243.0mHz,bothof
whichare monitored
by thevariousFAAinstallations.Permission
mustbe obtainedfrom
the FAA/FCCrepresentative
(or other authorizedauthority)priorto testing. Keepyour
testtransmission
to a minimalduration.
(a) SwitchthereceiverONandturncommunications
receiverto 121.5mHz. Deactivate
squelch
andturnup volumeuntilslightbackground
noiseis heard.
NOTE: If the aircraft is not fitted with a communicationsreceiver,requestthat the tower listen
for your test.
(b) Set the pilot's remoteswitchto ON and holdswitch in this positionfor a few seconds.
NOTE: The test transmission
mustbe pickedup by the aircraftcommunications
receiveror
controltower. Duringcoldweather,therecouldbe a slightdelaybeforetransmission
occurs.
(c) Setthe pilot'sremoteswitchto ONforonesecond;selectARMposition.
EMERGENCY
LOCATOR
TRANSMITTER
ANTENNA
I
GBA
ELTANTENNA
ELTARMSWITCH
A327
I
WHT/BLU-
I
REMOTE
AFTPRESSURE
BULHEAD
EmergencyLocatorTransmitterSchematic
Figure 501
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Emergency (continued)
6. InadvertentActivation
CAUTION: Undernormalconditions,the pilot'sremoteswitch mustbe set to ARM position.
In the eventthe ELTis inadvertentlyactivated,setthe pilot's remoteswitchto ON, then returnit to
ARM position.
thattheELTbe replacedat theearliestchance
it is recommended
As a routineprecaution,
theproblemmaynotbe in thetransmitter.Checkthe
activation.However,
followinginadvertent
following:
(a) Properspacingof antennasto minimizeantennaconductedRF.
(b) Rigidityof the transmitterinstallation.
EFFECTIVITY:
040-999
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. AccessoryCompartments
and
compartment,
Theavionicsshelvesare installedin thenoseof theairplanein theaccessory
facilitiesfor avionicsandelectricalequipment.LocatedbetweenF.S.24.60andF.S.
providemounting
angles,brackets,andclips.
57.00,theseshelvesare madeof 2024-T3aluminum,
of damageto theavionics
blanket,installedin theavionicsbay,reducesthepossibility
A protective
of trimstrip.
causedbywaterleakage.Theblanketis installedusingsixinchsegments
equipment
InverterMonitor
Assembly
VIEW
LOOKING
AFT
VHFComm#1 VHFComm#2
RadioAltimeterTransmitter
RadioAltimeterReceiver
Transponder#2
PRESSUREBULKHEADSTA. 57.0
AvionicsBayFeedThroughIdentificiations
Figure401
EFFECTIVITY:
040-999
1
25-70-00PAGE
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. AccessoryCompartments(continued)
- VIEW B
VIEW C -
Pitch
Servo
TOP VIEW
LOOKINGDOWN
VIEW
VIEW D
VIEW
Cockpit VoiceRecorder
VIEW C
VIEW E
_
Pitch
Servo
Yaw
Servo
Trim
Servo
LEFT, SIDE VIEW
Electricaland ElectronicEquipmentLocations
Figure 402 (Sheet 1 of 4)
EFFECTIVITY:
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25-70-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. AccessoryCompartments(continued)
VIEW A
Lighting
Inverter
Assembly
LeftStall
Computer
RightStall
Computer
Autofeather
Computer
0
0
LeftIgnitionSensor
Dimmer
Control
Assembly
Lighting
RightIgnitionSensor
Leftand Right LeftandRight
StallWarning
PilotHeat
CurrentSensors
Sensors
a
Electricaland ElectronicEquipmentLocations
Figure 402 (Sheet2 of 4)
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(AdvancedTralner)
MAINTENANCEMANUAL
A. AccessoryCompartments(continued)
VIEW B
Left and RightWindshieldHeat
Timers
Leftand RightJet Pump
DisengageRelays
Left and Right
Start
FlapWarningRelay
GearWarning
Relay
Flap Control Amplifier
Left andRightFuel
PumpRelays
DeiceTimer
LandingLight Solonold
Taxi Light Solonoid
LeftWindshield
Heat
Contactor
ElectricalandElectronicEquipment
Locations
Figure402 (Sheet3 of 4)
EFFECTIVITY:
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25-70-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. AccessoryCompartments(continued)
VIEW C
Avionics1 and2 Relays
VIEW D
VIEW E
Left and Right
StallWarning
CurrentSensors
and
Horn
Fuel FlowSignal
Conditioner
Locations
Equipment
ElectricalandElectronic
Figure402 (Sheet4 of 4)
EFFECTIVITY:
040-999
5
25-70-00PAGE
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER 26
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
26-EFFECTIVITY
26-CONTENTS
26-10-00
26-20-00
26-20-00
26-20-00
26-20-00
26-20-00
PAGE
1
1
1
1
2
3
4
5
DATE
CHAPTER
SECTION
PAGE
DATE
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
LISTOF EFFECTIVEPAGESJan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER26- FIREPROTECTION
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
26-10-00
1
1
General
Detection
Descriptionand Operation
1
26-20-00
Extinguishing
Descriptionand Operation
Removalof FireExtinguisherBottle
Installationof FireExtinguisher
ServicingFire ExtinguisherBottle
ReplacingFire ExtinguisherSquibAssembly
TestingExtinguishingSystem
PortableFire Extinguisher
EFFECTIVITY:
040-999
1
1
2
3
3
3
4
5
CONTENTSPAGE1
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
Fire Protection
A. General
A fire detectionand extinguishingsystemis providedfor eachengine;both are completely
independentfrom the other. Duringan enginecompartmentfire, thermaldetectorsinstalledin the
enginecompartmentactuateand completean electricalcircuitthat illuminatesthe master caution
warning light,soundsa warning horn,and illuminatesthe appropriateenginefire warning light on the
annunciatordisplay. Eachsystemhas a switch locatedon the lower left side of the instrumentpanel
which electricallydischargesthe fire extinguishingagent throughtubes into appropriateengine
compartmentareas.
B. Detection
1. Descriptionand Operation
Each enginefire detectionsystemconsistsof threefire detectingthermalunits and interconnecting
harness. Two of these unitsare locatedon eachside of the front fire seal in the hot section. One
is locatedat the bottomof the rear fire seal in the accessorysection. The thermalunits actuateat
a temperatureof 450°F. Whenevercontactsin one of the thermalunits is actuated(dueto a fire
condition),the circuitis completedand causesa master cautionlightto blink,a hornto blow,and
the enginefire warning lightto illuminateon the annunciatordisplay. The hornand flashinglight
can be deactivatedby pressingthe mastercaution light.
of eachenginesystemin
harnesses
Whentestswitchis pressed,it connectsinterconnecting
whichcheckscontinuityof
ground
to
display
annunciator
from
a
circuit
completes
it
and
series,
annunciator.
on
lights
warning
fire
engine
right
and
left
of
operation
and
system
EngineFireDetectors
Figure1
EFFECTIVITY:
040-999
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PAGE
26-10-00
10/90
Jan
26-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extinguishing
1. Descriptionand Operation
Eachenginefire extinguishingsystemconsistsof a sphericalcontainer(bottle)storinga fire
extinguishingagent (Halon 1301)chargedto 360 +25 -0 psig at 70°Fwith dry nitrogen. A pressure
gauge mountedon the side of the bottleindicatesthe internal(charged)pressure. Eachbottle is
mountedon the right side of each rear fire seal in the accessorysectionof the enginenacelles. A
maindischargepipe extendsfrom a valveon the bottomof the bottleforwardthrough rear and
front fire sealsto the hot sectionof the engine. An additionaltube extendsfrom the main
dischargepipe, passesaft throughthe rearfire seal, and terminatesat the top of the engine
accessorysection.
An electricallyoperatedcartridge(firingsquib),screwedintothe dischargevalve at the baseof the
bottle,providesa releasefor the extinguishingagent. Whenthe switchin the cockpit is actuated,
the firingsquib in the dischargevalveis detonatedand puncturesthe seal in the dischargevalve
that allowsthe releaseof extinguishingagentthroughpipes. The container(bottle)also has a
combinationfill fitting and safety reliefvalveassembly. If ambienttemperaturerises abnormally
(215°Fto 226°F), a fusible checkvalvewithin the fill fitting melts, relievingcontentsof container
(bottle)and avoidingpossibleburstingof container.
EngineFire ControlSystem
Figure 2
EFFECTIVITY:
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1
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Extinguishing(continued)
0
2. Removalof FireExtinguisher
Bottle
circuitbreakeris disengaged.
(a) Ensureaircraftmasterswitchisoff andfire extinguisher
(b) Removeupperandlowerenginecowling.
WARNING: FROSTBITEOR LOWTEMPERATUREBURNSWILL RESULTIF HALON1301
CBRF3)COMES IN CONTACTWITHSKIN.
(BAROMOTRIFLUOROMETHANE
squibunitwithaircraftharness.
threewiresconnecting
(c) Disconnect
WARNING: CHARGEDBOTTLESMUSTBE HANDLEDWITH CARETO AVOIDDAMAGING
THE SEAL. DO NOT BRINGELECTRICALCURRENTIN CONTACTWITH
TERMINALSON SQUIBASSEMBLYOF A LOADEDUNIT OR ACCIDENTAL
DETONATIONCOULDRESULT.
dischargepipeat fire sealfittingandremovenutandwasherfromfittingon forward
(d) Disconnect
sideof fireseal.
(e) Supportbottle;loosenmountingclampandremovebottle.Removefittingfromdischargeport
of squibhousing.
UpperCowlingSkin
FireExtinguisher
/
I
II
Pressure
Gauge
Clamp
EngineFireExtinguisher
Figure401
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
A. Extinguishing(continued)
of FireExtinguisher
3. Installation
(a) Installconnectorfittingintosquibhousingandtighten.
throughhole
tubeconnectorfittingprotruding
(b) Positionbottleintoproperpositionwithdischarge
in fireseal.
throughfire
clampandinstallingnutandwasheron fittingprotruding
(c) Securebottleby tightening
seal.
pipeto firesealfitting.
(d) Connectandsecuredischarge
as
of dischargenozzles(shownin Figure401). Nozzlesmustbe positioned
(e) Checkplacement
agent.
of extinguishing
shownto obtainproperdispersal
(f) Ensureall aircraftelectricalpowerisoff;connectwiresto properterminalson squibassembly.
(g) Installenginecowling.
testswitch,andverifyleftandrightengine
(h) Turnaircraftelectricalsystemon,pressannunciator
indicatorlightsareoperating.
inoperative
fireextinguisher
4. ServicingFire ExtinguisherBottle
(a) Checkfor leakageordamageto container.
weighit to be sureit iswithin0.25poundsof totalweight
(b) If bottleis notbeingreplaced,
stampedondataplate.
unit.
or damaged,replacewithserviceable
(c) If bottleisunderweight
givenin
is
withinspecification
bottle
fire
extinguisher
on
reading
pressure
indicated
(d) Ensure
Chart 1.
5. ReplacingFire ExtinguisherSquibAssembly
WARNING: DISPOSEOF REMOVEDSQUIBASSEMBLYIN A SAFEMANNERAS WITHANY
OTHEREXPLOSIVEDEVISE.
Thesquibassemblyhasatotallifeof 10years(Fiveyearsshelflifeandfiveyearstime- in service).Thesquibassemblymustbe replacedafterfiveyearstime- in - service.Todetermine
was installedin theaircraft,notthedatewhichthe
servicelife,checkthedatethesquibassembly
its five
squibassemblybeganits shelflife. Do notinstallanysquibassemblythathasexceeded
year lifeontoanyaircraft.
EFFECTIVITY:
040-999
PAGE3
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26-20-00 Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Extinguishing(continued)
6. TestingExtinguishingSystem
byturningaircraftmasterswitch
(a) A quickcheckof thesystemelectricalcircuitis accomplished
on,pressingannunciator
displaytest switch,andverifyingthatleft andrightenginefire
extinguisher
inoperative
indicatorlightsareoperating.A morethoroughcheckis asfollows:
(1.) Assureall aircraftelectricalpoweris off andall circuitbreakersaredisengaged.
(2.) Disconnect
electricalwiringharnessfromfireextinguisher
squibin oneengine
compartment
andconnecta testlampacrossdisconnected
wiresof harness.
(3.) Resetcircuitbreakersandturnmasterswitchon.
switchin cockpitandverifythattest lamp
enginefireextinguisher
(4.) Engageappropriate
illuminates.
(5.) Resetfire extinguisher
switch,turnmasterswitchoff,disengage
circuitbreakers,and
disconnect
test lamp.
WARNING: DO NOT USE A VOLT-OHMMETER,
BATTERYPOWEREDCONTINUITY
LIGHT,OR SIMILARDEVICEWHEN TESTINGSQUIBASSEMBLY.USE
OFTESTDEVICES
WHICHPASSMORETHAN30mA CAN DETONATE
SQUIB.
(6.) Connectsquib tester (Model 115squib test, AmericanStandard,Monrovia,California)to
squibterminalsand checkfor nominalresistanceof 1.15± 0.25 ohms. Disconnectsquib
tester.
(7.) Ensureaircraftelectricalsystemis deactivated;reconnectsystemwiringto squib
assemblyterminals,assuringgroundwire is connectedto groundterminal.
(8.) Repeatsteps a throughg for oppositeengine.
(9.) Pressurecheckfire extinguishercontainersperiodicallyto ensure pressureis between
minimumand maximumlimitsprescribedby manufacturer.(Referto pressure
temperaturecorrectiontable on container(bottle)or referto Chart 1.)
NOTE: Pressure
changeswithambientpressuremustfall withinprescribed
limits.If
container.
limits,replaceextinguisher
pressuresdo notfall withinprescribed
CHART 1
CORRECTION
PRESSURE-TEMPERATURE
Temperature -60
Farenhelt
-40
-20
0
+20
+40
+60
+80
+100 +120
Indicated
Pressure
127
155
148
180
174
212
207
251
249
299
304
354
367
417
442
492
110
134
532
582
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extinguishing(continued)
7. PortableFireExtinguisher
WARNING: AFTERDISCHARGEOF EXTINGUISHERAVOIDEXPOSURETO SMOKE,
VAPORSAND OTHERBY - PRODUCTSOF FIRE. DO NOT INCINERATE
EXTINGUISHER.
CAUTION: EXTINGUISHERIS A PRESSUREVESSEL. PROTECTFROMCORROSIVE
CONDITIONS.IF THEREIS ANY CORROSIONOR DAMAGE,EXTINGUISHER
SHOULDBE CAREFULLYEMPTIEDAND DISCARDED.USE ONLYAS
DIRECTED.
The portablefire extinguisherunit GeneralFire ExtinguisherCorporation(Model No. GH - 2 - 1/2),
contains2 1/2 poundsof Halon1211. It has a dischargerateof no less than 9.5 seconds. The
is 4 pounds12ounces
originalweightofthe extinguisher
willrechargeandreturnfora
NOTE: Thereare nofieldrechargefacilities.Themanufacturer
servicecharge.(Seelistof vendors)
removeit fromthequick- releasebracket,holdit uprightin either
Tooperatetheextinguisher,
withthespraynozzlepointingforward.Removethesafetypin,directthe
handbythe handgrip,
nozzletowardsthebaseof thefiresource,squeezethe leverwiththepalmofthe hand.Maximum
extinguishingeffectis obtainedif the fire - fighter uses sideto side motionand keeps moving in
theleverclosesa secondary
towardsthebaseof thefiresourceasit isextinguished.Releasing
seal insidethe operatinghead. This interruptsthe flow of extinguishant,thus retainingpart of the
charge,for dealingwith a flash back or re-ignitionshouldthey occur,withoutwasteor leakage.
of partialortotaldischarge.A partlyor
discprovidesa visualindication
Ejectionof the indicator
afteruse.
shouldbe replacedimmediately
assembly
extinguisher
totallydischarged
The extinguishershall be inspectedmonthlyor unlessotherwisespecified. The nozzleshall be
examinedto ascertainthat they are unobstructed.The tampertag or tamper indicatorshall be
intact. The extinguishershall be pressurizedas indicatedand the weightshall be withinthe
toleranceon the label
Therequiredservicechecksare asfollows:
(a) 12year hydro - statictest.
EFFECTIVITY:
26-20-00
Jan10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 27
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
27-EFFECTIVITY
27-CONTENTS
27-CONTENTS
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CHAPTER
SECTION
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LISTOFEFFECTIVE
PAGESFeb 1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER27 - FLIGHTCONTROLS
TABLEOF CONTENTS
SUBJECT
CHAPTER
PAGE
27-00-00
1
2
4
6
Descriptionand Operation
StandardProcedures
Wrappingof Trim Drums
SpecialTools
27-10-00
1
1
3
4
4
4
5
9
9
9
10
10
10
10
11
12
12
12
13
15
15
Aileronand Tab
Fault Isolation (AileronControlSystem)
Fault Isolation (AileronTrim ControlSystem)
Removalof Aileron
Installationof Aileron
Removalof AileronControlCables
Installationof AileronControlCables
Removalof ControlColumnSprockets
Installationof ControlColumnSprockets
Removalof AileronControlSection
Installationof AileronControlSection
Removalof AileronBellcrank
Installationof AileronBellcrank
Removalof AileronTrim (Fuselage)
Installationof AileronTrim(Fuselage)
Removalof AileronTrim (Wing)
Installationof AileronTrim (Wing)
Riggingof AileronControls
Riggingof AileronTrim
AileronControl SystemFrictionCheck
AileronTrim TabFree Play
27-20-00
Rudderand Tab
Removalof ForwardRudderCables
Installationof ForwardRudderCables
Removalof ForwardRudderControlSector
Installationof ForwardRudderControlSector
Removalof Aft RudderCables
Installationof Aft RudderCables
Removalof Aft RudderControlSector
Installationof Aft RudderControlSector
Riggingof the Rudderand its Controls
RudderControlSystemFrictionCheck
Removalof ForwardRudderTrim System
Installationof ForwardRudderTrim System
EFFECTIVITY:
040-999
1
1
1
1
1
4
4
4
5
5
8
8
9
CONTENTSFeb 1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER27 - FLIGHTCONTROLS
TABLEOF CONTENTS(continued)
SUBJECT
CHAPTER
PAGE
27-20-00
Rudderand Tab
Removalof Aft RudderTrim System
Installationof Aft RudderTrimSystem
Removalof Trim Tab
Installationof TrimTab
Riggingof RudderTrim
Removalof RudderPedalAssembly
Installationof the RudderPedalAssembly
9
9
10
10
10
11
12
27-30-00
Elevatorand Tab
Removalof ForwardElevatorControlSector
Installationof ForwardElevatorControl Sector
Removalof Aft ElevatorControlSector
Installationof Aft ElevatorControlSector
Removalof ElevatorControl Cables
Installationof ElevatorControlCables
Removalof ElevatorPushTube
Installationof ElevatorPushTube
Riggingthe ElevatorControlSystem
ElevatorControlSystemFrictionCheck
ElevatorTrim System
Removalof ForwardElevatorTrim System
Installationof ForwardElevatorTrim System
Removalof Aft ElevatorTrimActuator
Installationof Aft ElevatorTrim Actuator
Riggingof ElevatorTrim
ElevatorTrim SystemFrictionCheck
Free Play Check of ElevatorTabs
Inspectionof Aft ElevatorTrim Actuator
Trim Systems'Controlsand Indicators
Removalof Trim Controls
Installationof Trim Controls
Adjustmentof Trim Indicators
System
Stall Warning/Recognition
Stall WarningFunctionTest
ForceApplicationKit
1
1
1
1
2
2
3
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8
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27-50-00
Flaps
Descriptionand Operation
Removalof Flap
1
1
1
EFFECTIVITY:
040-999
Nov1/90 CONTENTS
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 27 - FLIGHT CONTROLS
TABLE OF CONTENTS (continued)
SUBJECT
PAGE
CHAPTER
27-50-00
Flaps
Installationof Flap
Removalof FlapActuatorMotor
Installationof FlapActuatorMotor
Removalof FlexibleActuatorShaft
Installationof FlexibleActuatorShaft
Removalof FlapTransmissions
Installationof FlapTransmissions
Disassemblyof FlapTransmission
Assemblyof FlapTransmission
Serviceand Inspectionof FlapTransmissionInternalComponents
Inspectionof OutboardWing Flap Transmission
Inspectionof InboardWing Flap Transmission
Removalof FlapControl Box (Selector)
Installationof FlapControl Box
Removalof FlapControl Amplifier
Installationof FlapControlAmplifier
Riggingand Adjustmentof Flaps
Preparationfor Rigging
MechanicalRiggingProcedure
ElectricalRiggingProcedure
ElectricalSystemFunctionTest Procedure
1
3
3
3
3
6
6
6
7
11
11
12
13
13
13
13
14
15
17
17
21
EFFECTIVITY:
040-999
CONTENTS
PAGE3
CONTENTS
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Flight Controls
A. Descriptionand Operation
The primaryflight controlsare conventionaltype operatedby dual controlcolumnsand rudderpedals.
Thecontrolcolumnsfunctionon a leverarmprincipleattachedto a crossovershaft(torquetube)
shaftactsasthe axisof rotationfor thetwocolumns
mountedunderthe cockpitfloor.Thecrossover
thetwocontrolwheels.Thecontrolcolumnscontain
andhousestherollerchainthatinterconnects
of controlwheelsandaileronprimarydrivemechanism.Thelinkagesto the
for adjustment
hardware
undertheleftsideof thefloor.
aileronandelevatorcontrolsectorsare contained
The aileronsare actuatedby the pilot and copilotcontrolwheelsthroughthe rollerchain which drives a
lever locatedin the pilot's controlcolumn. This levertransmitsthe controlwheelstravel to the aileron
controlsectorthrough the link, bellcrank,and anotherlink. Cablesrun from the sectorto aileron
bellcranksin the wings.
from
shaft. Anarm,extending
Theelevatorsarecontrolledbycontrolcolumnsthroughthecrossover
thepivotfittinglocatedon the leftsideofthecrossovershaft,transmitscontrolcolumntravelthrougha
linkto theforwardelevatorcontrolsector.Thecontrolcablesfortheelevatorcontrolsystemrunfrom
theforwardcontrolsectorat F.S.93.30to theaftcontrolsectorat F.S.373.10.Theaft controlsectoris
to a longpush-pulltubewhichreachesup throughto thetopof theverticalstabilizerwhere
connected
it boltsto theelevatorcontrolhorn.
Attachedto the left set of rudderpedalarms are tubesconnectedto a bellcrankwhich is attachedto
the pressurebulkheadat F.S.57.00. The ruddercontrol sectorat W.L. 18.00 is driven by a tube
runningfromthe bellcrank. Controlcablesrunfrom the controlsectorto the ruddersector,which is
attacheddirectlyto the rudder.
Theaileron,elevator,andruddertrimcontrolsaremountedon thepedestalalongwithposition
for eachsystem.As eachcontrolis moved,cablewrappeddrumsrotate,andin turnthey
indicators
the
actuate particulartrim systembeingoperated.
of thischapter.
in detailin the27-50-00
TheCalcotypeflap mechanismis described
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Standard Procedures
The followingtips are helpfulwhen removingand installingvarious assemblies:
1. Levelandplaceairplaneon jacksduringriggingandadjustment
of controls.
2. Removeturnbuckle
barrelsfromcableendsbeforewithdrawing
cablesthroughstructures.
3. Tiea cordto cableendbeforedrawingcablethroughstructuresto facilitatereinstallation
of cable.
4. Turnbuckle
stationsaregivenat neutralposition.
5. Beforedisconnecting,
usea feltmarkerto markcableends,etc.
6. Assembleandadjusttumbuckles
to ensureeachterminalis screwedin approximately
equal
distanceintobarrel. Duringadjustment,
do notturnterminalsso a permanent
twistis putin cables.
7. Whenturnbuckles
are setto correctcabletension,no morethanthreethreadsmustbeexposed
fromeitherendof turnbucklebarrel.Checklockingclipsfor properinstallation
by removingclips
usingfingersonly. Bothlockingclipscan be insertedin thesameturnbucklebarrelholeor
installedin oppositeholes. Lockingclipsinstalledandremovedmustbe scrapped.
8. Whenpushrodsor rodendsareprovidedwithan inspection
hole,thescrewmustbe screwedin
enoughto passthe inspection
hole. Thisis determined
visuallyor byinsertinga pieceof wireinto
theinspectionhole. Whereno inspection
holeis provided,a minimum3/8inchthreadmustbe
engaged.
9. Cabletensionmustbe measured
withappropriatesurfacecontrolin neutralposition.
NOTE: Performa frictioncheckof the systemwheneverelevator,rudder,or aileroncontrol
systemis serviced.
NOTE: Cableriggingtensionsspecifiedin the followingparagraphsmustbe correctedto ambient
temperaturein areawheretension is beingchecked(referto Chart 1).
10. Ensureall cable guard pins are installedproperlyand are not interferingwith controlcable travel.
CAUTION: WITH RIGGINGPINSINSTALLED,CLAMPTHE BELLCRANK,SECTOR,OR
ASSEMBLYSO WHENCABLESARE TIGHTENEDTHE LOAD IS NOTTAKENUP
BY THE PIN. ENSUREPIN IS FREE ATALL TIMES. IT IS RECOMMENDED
THAT
CABLESARE CLAMPEDNEARSECTOR,INSTEADOF CLAMPINGTHE
SECTOR.
11. After adjustingtrim tab travels,checkcable wraps on trim drums at eachend of travel. Minimum
allowableis 1 1/4wraps. Installfairleadsso they do not cause a changein directionof morethan
3° .
12. Installpulleys so they do not cause a changein cable directionof morethan 1 laterally(primary
controls)or 20 laterally(trimsystem).
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. Standard Procedures (continued)
CHART 1
CABLE RIGGING TENSION VS. TEMPERATURE
200
170
150
Z
50
20
POUNDS
RIGGINGLOADCORRECTION,
SUBTRACT
EFFECTIVITY:
040-999
ADD
3
27
27-00-00 JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
C. Wrappingof Trim Drums
NOTE: Thefollowinginstructions
providegeneralized
instructions.Forspecificrequirements
asto
numberandpositionof cablewrapson drum,referto appropriate
trimriggingprocedure.
Alltrimdrums,wrappedbasicallythesame,mustbe removedfromtheairplaneasfollows:
1. Forreference,markendof drumtowardbaseof housingbracketwhenlaterinstallingand
wrappingcableon drum.
2. Withdrumhousingbracketheldfirmly,removeoneof thecableguardboltsfromhousingbracket.
3. Removedrumscrewor drumshaftfromtrimscrewassembly.Removescrewbyremovingstop
locatedon endof screwoppositebaseof housingbracket.Turnscrewfromdrum. Removeshaft
by drivingrollpinfromcenterof drum. Pressshaftfromdrum.
4. Removedrumfromhousing.
5. Unwraptrimcableandremovecableandlockpinfromdrum. Ifoneendof cableis markedto
facilitatehookupof cableends,notelocationin relationto drumwheninstallingnewcableon
drum.
6. Checkconditionof bushingin housingbracketfor excesswear.
7. Toinstallandwraptrimcable,locatecenterof cable,measuring
fromendto end.
8. Insertcenterof cableintocableslotin drum;installlockpin.
9. Holddrumwithpreviously
markedor baseendof drumdown.
10. Lookingdownon drum,wrapcableleadingfrombaseendup in a counterclockwise
direction.
Wrapcablefromupperenddownin a clockwise
direction.
11. Insertdrumin housingbracket,positiondrum,androutecablesfromassembly
asshownin Figure1.
12. Installscrewandscrewstopor drumshaft. Securewithrollpin.
13. Blocktrimcablesin centerpositionusingmethodshownin Figure2.
14. Centerdrumbetweenstopson screwbyrotatingscrew.
ScrewStop
DrumScrew
Bushing
Drum
Housing
Bracket
Roll
Pin
Drum
Cable
Lock
Pin
Bushing
LockPin
Housing
BracketBase
Bolt
Guard
Cable
Attachment
Nuts
ScrewStop
Trim Screw Assembly
Figure 1
EFFECTIVITY:
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Jan
10/9027-00-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
C. WrappingofTrimDrums(continued)
Methodsof BlockingTrim Cables
Figure 2
EFFECTIVITY:
040-999
27-00-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
D. SpecialTools
Elevator RiggingTool
AileronRiggingTool
Tool
P/N 71505-2
P/N 71505-3
Rudderand RudderTrim RiggingTool
Flap RiggingTool
Tool
P/N L-72233
Rudder Pedal RiggingTool
SpecialTools
Figure 501
PAGE6 27-00-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
D. SpecialTools (continued)
0.500 AND0.562
Socketsneeded
to covertwo size
jam nutson dots
Cut throughthe
disc and socketto
permitit to slide
over the pot shaft
TOP VIEW
Weld Holes
0.250
0.187 OR 0.250
steeldisc
Holesdrilledin
discfor small
punchtypeobject
to assistin tightening
the jam nut on pot
FabricatedCalcoFlap Potentiometer
Installationand AdjustmentTool
SpecialToolsfor CalcoFlaps
Figure 502
EFFECTIVITY:
040-999
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27-00-00 JanPAGE
10/90
27-00-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
D. SpecialTools (continued)
3 lb movableweightwith
markedcenterline
as required o balance
toolitself
SurfaceChordLine
-Beambalancing
bolt (usedfor
balancingthe tool itselfonce
the trailingedge support
has beenset)
Hingecenterlineplaceddirectly
over hingeline of controlsurface
MarkGraduationsin inches
Horizontally
Adjustablefor
settingtoolto
widthof control
BubbleLevel
surface
SetScrew
Verticallyandhorizontally
adjustabletrailingedgesupport
Verticallyadjustablefor
setting beamparallel
chord lineof controlsurface
ControlSurfaceBalancingTool
Figure503
PAGE
8 27-00-00
27-00-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. AileronandTab
1. FaultIsolation-AileronControlSystem
CHART 1
FAULTISOLATION(AILERONCONTROLSYSTEM) (Sheet 1 of 2)
Fault
Cause
Lost motionbetween
controlwheeland
aileron.
Cabletensiontoo low.
Adjustcabletension.
Linkage looseor worn.
Checklinkageandtighten
or replace.
Brokenpulley.
Replacepulley.
Cablesnotin placeon
pulleys.
Installcables correctly.
Check cable guards.
Improperrigging.
Check riggingin the controlcolumn
and crossover(torquetube) shaft,
and at the bellcranksin the fuselage
and the wings.
Systemnot lubricated
properly.
Lubricatesystem.
Cabletensiontoo high.
Adjust cable tension.
Control columnchain
improperlyadjusted.
Adjust chain tension.
Pulleysbindingor
rubbing.
Replacebindingpulleysand/orprovide
clearancebetweenpulleys
and brackets.
Cablesnot in place on
pulleys.
Installcablescorrectly.
Checkcableguards.
Bentaileronand/orhinge.
Repairor replaceaileronand/or hinge.
Cablescrossedor
routedincorrectly.
Checkroutingof control
cables.
Interference
between
fittings.
Checkcontrolcolumnfittingsin pilot's
control column. Linkagesto
bellcrankfrom controlcolumn.
Incorrectcontrol
columnrigging.
Rig and check roller chainfirmness
betweenthe two controlwheels.
Resistanceto control
wheel rotation.
Controlwheelsnot
synchronized.
Remedy
EFFECTIVITY:
040-999
27-10-00Jan
10/90
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
1. Fault Isolation- Aileron ControlSystem (continued)
CHART 1
FAULTISOLATION (AILERONCONTROLSYSTEM) (Sheet 2 of 2)
Fault
Cause
Remedy
Controlwheels not
horizontalwhen
aileronsare neutral.
Incorrectriggingof
aileronsystem.
Rig.
Incorrectailerontravel.
Aileroncontrolrodsnot
adjustedproperly.
Adjust.
Aileronbellcrankstops
notadjustedproperly.
Adjust and checkall bellcranks
in the fuselageand wings.
Correct ailerontravel
cannotbe obtainedby
adjustingbellcrankstops.
Incorrectriggingof
aileroncables,control
wheelandcontrolrod.
Rig.
Controlwheel stops
beforecontrol surfaces
reach full travel.
Incorrectriggingbetween
controlwheelandcontrol
cables.
Rig.
EFFECTIVITY:
040999
Jan
10/90 27-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
2. Fault Isolation- AileronTrim ControlSystem
CHART 2
FAULTISOLATION (AILERONTRIM CONTROLSYSTEM)
Remedy
Fault
Cause
Lost motionbetween
trim controlwheel
and trim tab.
Cabletensiontoo low.
Adjust.
Cables not in placeon
pulleys.
Installcables correctly.
Checkcable guards.
Brokenpulley.
Replacepulley.
Linkagelooseor worn.
Checklinkageand
tightenor replace.
Systemnot lubricated
properly.
Lubricatesystem.
Cabletensiontoo high.
Adjust.
Pulleysbindingor
rubbing.
Replacebinding pulleys.
Provideclearancebetween
pulleysand brackets.
Cables not in placeon
pulleys.
Installcablescorrectly.
Checkcable guards.
Trim tab hingebinding.
Lubricatehinge. If
necessary,replace.
Cables crossedor
routedincorrectly.
Checkroutingof control
cables.
Systemincorrectly
rigged.
Checkand/or adjust
rigging.
Eitheror both trim drums
incorrectlywrapped.
Checkand/or adjust
rigging.
Trim indicatorunitnot
adjustedproperly.
Adjust.
Trimcontrolwheelmoves
with excessiveresistance
Trim tab fails to reach
full travel.
Trim indicatorfails to
indicatecorrecttrim
position.
EFFECTIVITY:
040-999
3
27-10-00 JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
3. Removalof Aileron (refer to 57-10-00Figure401)
(a) Removerear fairingbetweenwing and wing tip tank.
(b) Removewing tip aft attachmentrib.
(c) Disconnectaileroncontrol rod.
(d) At right aileron,disconnecttrim tab controlrod.
(e) Removehinge bolts and removeaileron.
4. Installationof Aileron (refer to 57-10-00Figure401)
(a) Place aileron in position. Installhingebolts.
(b) If right aileronwas removed,connecttrim tab control rod.
(c) Connectaileroncontrol rod.
(d) Attach wing tip attachmentrib.
(e) Install rear fairing betweenwing and wing tip tank
5. Removalof Aileron ControlCables (Figure 401)
(a) Removepilot and left passengerseats behindmainspar carry through.
(b) Removeleftfloor panels from behindcontrolcolumn backto Station174.0 or approximately34
inchesbehind mainspar carry through. If necessary,movethe affectedpassengerseat so
right floor panel and center panelscan be removedat same station.
(c) Removefairleadsfrom wings at Station 121.5and 58.5, and removefairleadsfrom where
aileron cablesgo throughfuselageat fairleadpan, Station 173.0.
(d) Removeaccess plates underwing alongfrontof rear spar at WingStations92.5, 121.0,and
183.0. Also removethree plates at rear of wheelwell and on undersideof wing fillet.
(e) To removeleft balancecable, proceedas follows:
(1.) In left wing at bellcrank,removesafety wire or clip from aft turnbuckle;disconnectcable.
(2.) Removefairleads at Wing Stations58.5 and 121.5 and removecable guard pins at Wing
Stations0.5, 30.9, and 147.5.
(3.) In fuselage, removesafetywire or clip from aft turnbuckleat Station172.0;disconnect
cables.
(4.) Markcable end to facilitateinstallation.
(5.) Pullcable end to facilitateinstallation.
(f) Removethe right balance cable as follows:
(1.) In right wing at bellcrank,removesafetywire from aft turnbuckleand disconnectcable.
(2.) Disconnectturnbuckleat FuselageStation 172.0.
(3.) Removefairleadsand cableguard pins as describedfor leftwing.
(4.) Mark cable to facilitateinstallation.
(5.) Carefullypull cable fromaircraft.
(g) Removeleft primarycable as follows:
NOTE: Whenremovinginboardsectionwhich leadsfrom controlsectorto turnbuckleat
Station 142.0or outboardsectionwhich leads to the bellcrankfrom turnbucklesonly
use directionsleadingto or from Station142.0.
(1.) In leftwing at bellcrank,removesafetywire or clip from turnbuckleand disconnectcable.
(2.) Removeprimarycontrolcable fairleadsat Wing Stations121.5and 58.5, cable guardpins
at Wing Stations0.5, 30.0, 147.5,and at FuselageStations164.51and 112.48.
(3.) Removesafetywire and screwsecuringretainerplateand cable end to sector;disconnect
cablefrom sector.
(4.) At Station 155.0, drawcablesfromwing and insidefuselage.
PAGE4
27-10-00
Jan10/90
27-10-00
Jan~
10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Aileron and Tab (continued)
5. Removalof AileronControlCables (continued)
(h) To removeright aileroncable, use basicallythe sameprocedureas the left. The only
differencefor the rightcable systemis that pulleylocationsaft of sectorare different. The right
system'sfirst pulleyfrom sectoris at Station101.07. One is at Station 164.51where cable
turns towardwing and goesunderanotherpulleyat Station 168.0. The inboardand outboard
sectionsare still dividedby a tumbuckleat Station 142.0.
6. Installationof AileronControlCables (Figure 401)
NOTE: Whenall fairleadsand cable guardpins are removed,and only the inboardor outboard
sectionof cable is to be installed,follow instructionsfor the specificsectionfrom either
side of turnbucklesat Station 142.0and on.
(a) Installleft primarycable as follows:
(1.) At bellcrankin left wing,fastentumbucklefork to forwardarm of bellcrank.
(2.) Carefullyfeed cablethroughpulleysin wiringat Stations147.5,30.0, and 0.5 and around
pulley at wing root (FuselageStation170.03,ButtockLine 28.58). Angleslightlyforward
throughforward holein fairleadpan assemblyand aroundport pulleyat FuselageStation
164.51.
(3.) If full cable is beingrigged,feed cable forwardaroundpulleyat FuselageStation112.48
and to left side of uppercontrolsector.
(4.) Fastencable end to aileroncontrolsectorby screwingon retainerand safetywiring.
(b) Installright primary cable as follows:
(1.) Connecttumbucklefork to forwardarm of bellcrankin right wing.
(2.) Route cablethrough pulleysin right wing as previouslydescribedfor left wing.
(3.) Again feed cable throughforwardhole in fairlead pan assembly,Waterline16.81.
(4.) At a slight angleforward,routecable frompan inboardto a pulleyat FuselageStation
168.0. Feedcable underand aroundpulleyto rear pulleyat Station 164.51and aroundit.
(5.) If both sectionsare being installed,routecableforwardto pulley at Station101.07,around
its left side,throughbulkheadat Station100 and onto right side of aileroncontrolsector.
(6.) Fastencable end to controlsectorby screwingon cable retainerplateand safetywiring
them to sector.
(c) Installleft and right balancecablesas follows:
(1.) Connectcablesto aft arm of individualbellcranks. Verify,if applicable,that red painted
cable terminalson aileronbalancecablesare installedto red paintedlugs on aileron
bellcranksin wings.
(2.) Routecablesthroughpulleysinstallingcable guardpins at Wing Stations147.5,30.0, and
0.5 and fairleadsat Stations121.5 and 58.5.
(3.) Check properangleof ailerons;connectand tightencables at turnbuckleaccordingly.
Verifytrailing edge of leftaileronmovesup and trailing edge of right aileronmovesdown
and vice-versawhen controlwheelis
when controlwheel is turned counterclockwise
turned clockwise.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
F.S.
112.49
F.S.
170.03
AileronandAileronTrimControls
Figure401 (Sheet1 of 3)
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PIPER AIRCRAFT
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MAINTENANCE MANUAL
A. Aileron and Tab (continued)
FuslageStation93.30
AileronTrimPulley
FuselageStation101.23
FuselageStation101.10
FuselageStation 164.51
FuselageStation142.0
FuselageStation170.03
Aileron andAileronTrim Controls
Figure 401 (Sheet2 of 3)
EFFECTIVITY:
040-999
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PAGE
27-10-00 Jan
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Aileron and Tab (continued)
AileronBalanceCable
FuselageStation 171.00
AileronTrimTab Cable
Wing Station 0.50
AileronTrim
Tab Cable
WingStation 30.00
Wing Station 174.50
AileronTrim Tab
Cable
WingStation 147.50
Wing Station 174.50 (rightwing only)
Aileronand AileronTrimControls
Figure 401 (Sheet3 of 3)
EFFECTIVITY:
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Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
7. Removalof ControlColumnSprockets
(a) Removeaccesspanels locatedonforwardside of controlcolumn approximately6.00 inches
belowcontrolwheels on pilot and copilotcontrolcolumns.
(b) Removecoverassemblyfrom top of both controlcolumns.
(c) Installriggingpins in lowerportionof pilot controlcolumn ensuringbellcrankis captured
betweentwo pins.
(d) Inserttwo piecesof 0.032 inch safetywire down copilotcontrol columnand one piece down
pilotcontrol column. Wrapone end of eachwire to a link in chain belowturnbuckles. Tie
oppositeendsof wires to holeswhichforwardaccesspanels are mountedto columns.
NOTE: Keepthe wires tight so chaindoes not fall off sprocketsunderfloorboards.
8. Installationof ControlColumnSprockets
(a) Placealignmentmark on new sprocketin sameplace as old sprocket.
(b) Mountnew sprocketon shaftwith sprockethub facing awayfrom controlwheel. Lineream
holein sprocketand shaftassemblyto 0.1635- 0.1640 inch diameter. InstallHy-LokHL 18-516 pin in holefor drivefit. InstallHy-LokHL-70-5collar on pin and tighten it until hex position
shearsoff. Hold pin headwith an Allen wrenchif necessary.
(c) Reassemblycontrolwheel assembliesintocontrolcolumnsby securingbearingblocksto each
columnwith ten AN3-3Abolts previouslyremoved.
(d) Installchainson sprocketsso previouslyinstalledty-raps alignwith sprocketalignmentmarks.
(e) Reconnectturnbucklesensuringproperplacement. Removesafetywire used to retain chains.
Levelpilot controlwheel by adjustingturnbucklesA and B and taking up slackwith turnbuckle
C (Figure402). Level copilotcontrolwheel by adjustingturnbucklesB and C. Tensionchain
enoughto removeslack,but not enoughto increasefriction. Throughaccesshole in copilot
column,deflectchainwith finger applyingapproximately5 poundsof pressure. Deflectionmust
be between 1/4 - 1/2 inch.
(f) Removeriggingpins and ty-raps. Checkaileronsystemfriction per 27-10-00page ??. Move
controlsthroughfull travel rangeand checkfor free movement.
(g) Installturnbucklesafety pins and accesscovers.
9. Removalof AileronControlSection (Figure401)
(a) Disconnectcablesand aileroncontrolpushrodfrom sector.
NOTE: Both aileron and elevatorsectorsare locatedat Station93.3. Thoughnot integrally
connected,a hingebolt maintainstheir axial position. If is necessary,therefore,to
removeaileroncablesfromtheir sectorand loosenelevatorcablesso hingebolt can
be pulled out. The forwardelevatorsectorwill not be unhingeddue to removalof
aileronsector.
(b) RemoveAN6-60Apivot bolt.
(c) Rotatesectorso groovesare facingfore and aft. Slide sectorto left of aircraft and out from
betweenbracketsupports.
EFFECTIVITY:
040-999
9
PAGE
Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. AileronandTab (continued)
10. Installation
of AileronControlSection(Figure401)
(a) Holdsectoron endwithgroovedendsforeandaft,androtateit downandbetweentoptwo
supports.
connectcontrolrodto mountingflange.
(b) Withsectorbetweenits supports,
(c) Ensureflangeisto leftsideof aircraft.Positionsectorbetweenits support.
(e) Ensureelevatorcontrolsectoris in position.DriveAN6-60Apivotboltdownthroughtwo
sectorsandtheirsupports.Screwboltintonutplate.
(f) Connectandtightenaileroncontrolcables.
(g) Tightenelevatorcontrolcables.
11. Removalof Aileron Bellcrank (Figure401)
(a) Removeaccessplateto bellcrankassembly.
(b) Relievecabletensionof controlsystemby rotatingonetumbuckleattachedto bellcrank.
tumbuckleendsfromforwardandaft bellcrankends.
(c) Disconnect
aileroncontrolrodat bellcrank.
(d) Disconnect
fromwing.
(e) Removepivotboltsecuringbellcrank.Removebellcrank
wing.
from
(f) Unboltstopblockandremove
of AileronBellcrank(Figure401)
12. Installation
(a) Placebellcrankin mountingbracketwithadjustablestopstowardoutboardendof wing.
(b) Installpivotboltandtorque.
(c) Installaileroncontrolrod;secureboltassemblyandsafety.
(d) Connecttumbuckleendsto bellcrank;secureandsafety.
NOTE: Thebellcrankaft endandbalancecableendis paintedredto facilitateproperhookup.
Do nottightenturnbuckleforkendson bellcranksoendscannotrotate.
(e) Installstopblockandtorquebolts.
(f) Checkaileroncontrolsriggingandadjustment.
(g) Installaccessplateandsecure.
13. Removalof AileronTrim(Fuselage)(Figure401)
(a) Togainaccessto trimcontrolactuator,cables,pulleys,andcontrolpedestal,removerightand
andaccesspanelsin andaroundpedestal.
left pilotseats,floorboards,
NOTE: Thefuselageailerontrimcablesare routeddownrightsideoffuselagefrompedestal
into rightwing. Afterenteringwing,cablesgo throughtwosetsof pulleysto Wing
Station92.5wheretheyattachto wingailerontrimcablewithtumbuckles.
(b) Toreleasetensionon theaileroncablesystem,loosenbalancecabletumbuckleat Fuselage
seatsandfloor
byremovingnecessary
Station171.3.Accessto tumbuckleis accomplished
panels.
in
(c) Cablesandpulleysin fuselageare reachedby removingrighthandandcentralfloorboards
to
135.0
Station
from
seats
Remove
to
163.0.
99.0
cockpitthroughcabinat FuselageStation
163.0asnecessary.
(d) Blocktrimcablesat screwdrumassemblyin wingat WingStation171.0andinfuselageat
pulleysunderpedestal.
(e) Underwingat WingStation92.5,removeaccesspanel,markcablesto ensureproper
fuselagetrimcablesfromtumbuckles.
disengage
reinstallation;
NOTE: Besureto notespecificroutingandhookupof eachcableto ensuretrimtaboperates
properlyafterreinstallation.
EFFECTIVITY:
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
A. Aileron andTab (continued)
13. Removalof AileronTrim (Fuselage) (continued)
(f) Removetwo small snap bushingssecuringtrim cablesto rib flange at Wing Station58.5 by
reachingthroughoutboardaccesshole in aft wheelwell bulkheadand under wing at Wing
Station65.0.
(g) On aft wheelwell bulkhead,removeinboardaccesspanel. Reachthroughaccess hole,
removenut from pulley bearingbolt,and carefullyslide bolt up throughpulleysfar enoughto
removetab pulleys.
(h) At Wing Station0.5, reachthroughbottom,aft accesshole in wing fillet, and remove tab
pulleys.
(i) Tabcablesare routedfrom last wing pulleygroup, througha doublerassembly,and into
fuselage.
(j) Removerequiredpulleyguidepins from specificpulleysin fuselage. Carefullydrawcables
fromwing intofuselage.
(k) Frompedestal in cockpit,carefullydrawcablesthroughfuselage.
(I) Removeaccesscovers on controlpedestal.
(m) Withtab cablesstill blockedat pulleysbelowpedestal,blockcablesat pedestaltrim screwand
removeclevis pinfasteninguniversaljoint to screwshaft.
(n) Unblockcablesat pulleys;removepulleys.
(o) Removefour bolts retainingscrewassemblyto supportbracket.
(p) Slide screwassemblyforwardfrom supportbracketuntil shaftclears supportbracket.
(q) Carefullyremovescrewassemblyfrom pedestal. Pull cablesout throughpedestal.
(r) Referto appropriatesectionon trim controlsand indicatorsfor removalof ailerontab control.
14. Installationof AileronTrim (Fuselage) (Figure401)
NOTE: Beforeinstallingcable, notewhichcable is routedto which turnbucklein wing.
(a) Ensureappropriatecable is centeredand evenlywrappedand blockedon trim drum to prevent
unwrapping.
(b) Removeall accesspanels,pulleys,and pins (explainedin previousparagraph).
(c) Carefullyfeed cablesthroughbottomaccesshole on left side of pedestalundertorquetube for
controlcolumn and back toward rightside of fuselagewherecablesgo thru pulleysat Fuselage
Station 101.23and RightButtline7.9.
(d) Fromcopilot side of pedestal,carefullypull and lay cable so screwdrum assemblycan be
installedwith as little cableslack in pedestalassemblyas possible.
(e) Carefullypositionscrewdrum assemblythroughaccesshole. Positionassemblyon mounting
bracketsso universaljoint, attachedto trim control driveshaft,can be attachedto drumdrive
shaft.
(f) Fastenuniversalto drumdrive shaft. Attachscrewdrum assemblyto supportbracket.
(g)Aligncables handingfrom screwdrum in first set of pulleysunder pedestal. Allow cableto go
throughpulleyson same sidesas they leavedrums.
(h) Reinstallpulleysin pulleybracketunder pedestal.
(i) Routecablesthroughpulleysat Station101.23and backthroughright side of fuselageto
Station163.38. Turn cablesthroughdoublerassemblyon fuselageand out throughwing by
pulleysat Wing Station31.0. Frompulleyat Station31.0, cablesgo throughholesfor snap
bushingsin rib at Station58.5, andtop cablefrom fuselagegoes in aft hole. Finally,cables
travel out wing to Station90.0 wherethey attachto wing ailerontab cables.
(j) Be sure to connectpropertrim cablesand tightento tension describedin Figure502.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
15. Removalof AileronTrim (Wing) (Figure401)
(a) Removeaccessplates locatedunderbottomtrailing edge of wing at Stations92.5,117.5,
128.0,151.5,171.0, and 176.0.
(b) Disconnecttrim control link locatedbetweentrim screwand tab push-pulltube.
(c) Block both sets of trim cablesto preventunwrappingfrom their drums and ease removal.
Blockfuselagecable systemat pedestaldrum and wing systemat tab screwassemblyWing
Station 171.0.
(d) Mark one set of cable ends at Wing Station90.0 to facilitateinstallationand disconnectcables
at tumbuckles.
NOTE: Note specificrouting and hookupof eachcable to ensureproperoperationafter
installation.
(e) Removefairleads in rib at Station 121.5by reachingthrough accessopeningsat WingStations
117.5and 128.0.
(f) Throughaccess openingat Wing Station150.0,removeappropriateguide pin.
(g) With screwdrum disconnectfrom tab link assembly,removebolts securingdrum assemblyto
rear spar.
(h) Carefullypull screwdrum assemblyand cablesfrom wing.
16. Installationof AileronTrim (Wing) (Figure401)
(a) Ensureappropriatecable assemblyis centeredand evenlywrappedon drum (see paragraph
titled Wrappingof Trim Drums). Centerdrum betweenstopson trim screw andblock cablesto
preventunwrapping.
(b) Feed cablesback throughwing so screwdrum is fed up intowing as cable slackbecomesless.
(c) Positionscrewdrum assemblyinsidewing, installattachmentbolts, and torque.
(d) Finish drawingcablesthroughwing. Connectto appropriatetumbuckles at WingStation90.0.
If fuselagecable systemis not installed,blockcablesat rib Wing Station 121.5by reaching
through accessopeningat Station 117.5.
(e) With cablesretained,removecable blocks.
(f) Connecttrim link to screwdrum shaft.
(g) Installcable guard pin at Wing Station 150.0.
(h) Installsnap bushingsat Station 121.5
(i) If both fuselage and wing cable systemare installedand engaged,set cable tensionwith
turnbucklesat Wing Station90 (Figure502). Checkriggingand adjustment.
(j) Installall access plates.
17. Riggingof AileronControls (Figures401,402, 501 through504))
NOTE: The followingprocedureassumessystemto be far enoughin rig to allow all rigging
pins to fit in their individualholesat sametime.
(a) Removeaccessplateto eachaileronbellcrankat Wing Station 178.
(b) Positionbellcranksin neutralpositionsusing riggingpins. (AN-3-20bolts with ribbons
attached.) Figure503)
(c) Removeaccessplates underpilot seatand insertriggingpin throughthe sectors. If pins will
not line up in both bellcranksand sectorsunderpilot seat, proceedas follows:
(1.) Align sectorsand installriggingpin.
(2.) Clampcables nearsectorsto preventany load on riggingpin.
(3.) Adjust cableswith tumbucklesat FuselageStation142 until both aileronbellcrank
pinholesalign.
(4.) Insert riggingpins and unclampcables.
(d) Installrigging pins in bottomof pilot controlcolumn. Adjust pushrodto sectorif necessary.
Adjust lengthof verticalpushrodin column as follows (referto Figure501).
EFFECTIVITY:
PAGE
12
Jan 10/90 27-10-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Aileron andTab (continued)
18. Riggingof AileronTrim
(a) To adjustailerontrim, ensurethe followingis accomplishedeither during installationor as a
preadjustmentcheck:
(1.) Trimcables are evenlywrapped(centered)on drums both belowcontrolpedestaland in
wing and both cabletumbucklesare locatedapproximatelyat Wing Station90.
(2.) Trimdrum in wing is centeredbetweenstops of trim screw.
(3.) The cabletension is set accordingto specificationsin Figure502.
(b) Removeaccessplates on undersideof right wing at Stations171.0 and 176.0.
(c) Withtrim screwheld from rotating,turn trim drum until 0.560 inchexists betweenforwardscrew
stopand drum housingmeasuredalongscrew. (This is neutralpositionof screw.)
(d) Withright wing riggingtool (P/N 72159-2)installedand aileronsin neutralposition,rotatetrim
wheelin cockpitto specificationsin figure 27-6 as indicatedon riggingtool. Ensurecable
tensionmeetsspecificationsin Figure502.
(e) Ensurerotationof wheelfrom stopto stop is smoothand free with no binding or chafing.
(f) Usingtool (L73035)and a dial type torquewrench,checktrim systemfriction at pedestalby
removingtrim wheel and attachingtool and torquewrench to splinedshaft. Frictionmust not
exceed9 inch-poundswhentested in either directionat any point betweenlimits.
CopilotControl
Cover
AdjustPush-PullRod
insidepilotscontrol
columnto positionrod
end (andbellcrank)at
W.L. -18.00.
Bellcrank
TurnbuckleC
VIE
Access
Cover
ControlColumn
(Right)
.1.50 + .12
FWD
InstrumentPanel
ControlColumnTravel and Limits
Figure 501
EFFECTIVITY:
040-999
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Jan 10/90
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTralner)
MAINTENANCEMANUAL
A. Aileronand Tab (continued)
Aileronand AileronTrim Tab
A- 18.5° +1 "-0
B-18.5 ° +1° -0
C -290 +1 -0"
D - 15 +1 -0°
CableTension
Aileron- 55 lbs.± 5 lbs.
AileronTrimTab- 14lbs.± 2 lbs.
CAUTION:
MAKESURETO SECURELY
CLAMPBELLCRANKS
ATQUADRANT
BEFORE
TIGHTENING
CABLES.
TrimTabtravelwith
Aileronin neutralposition
2° belowchordline
Chord Line Level
AileronControl Travelsand CableTension
Figure 502
b
Stop Bolt
-
RiggingHole
Bellcrank
Stop
Stop Bolt
Locationof BellcrankRiggingHole
Figure503
PAGE
14 27-10-00
Jan 10/90
0
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MANUAL
MAINTENANCE
A. Aileron and Tab (continued)
TOOL P/N 72025
Installationof AileronRiggingTool
Figure 504
19. Aileron ControLSystemFrictionCheck (Figure601)
Usinga spring scaleand pullingfrom pointon aileronshownin Figure503, take readingsin both
up and down directionsas aileronpassesthroughneutral position. Recordreadings,add them,
and ensure total doesnot exceed9 poundswithoutautopilotbridlecablesconnected,or 10
poundswith autopilotbridlecablesconnected.
20. AileronTrimTab Free Play
(a) Positiontrim tab in neutral position.Trailingedge of tab in neutral positionmust be in line with
trailingedge of mainsurface.
(b) Totalfree play mustnot exceed0.04 inch measuredfrom one extremeto other between
outboardend of tab trailingedge andtrailing edge of mainsurface.
(c) If excessiveplay exists, inspectailerontrim screwand hingeassembliesto determinelocation
of excessiveplay. Repairor replacewornparts as required.
EFFECTIVITY:
040-999
27-10-00Feb1/98
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Aileron and Tab (continued)
Flap
Aileron
.50
.50
Measurefrom here
Aileron FrictionCheck
Figure 601
PAGE
16 27-10-00
Jan
10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab
1. Removalof ForwardRudderCables (Figure401)
(a) Removepilot seatand floor panelsunderand in front of pressurebulkheadat FuselageStation
(F.S.)57.0.
(b) Ruddercable pulleysfor forwardsystemare locatedat F.S.77.2 (in front of controlcolumn),
161.35,212.96,248.96,and 281.5. Removeleft seats and floorboardsin these areas,only
wherenecessary. Removeleft sidefloor panelsaround F.S.303.5to makeaccessto rudder
cableturnbuckles.
(c) Beforedisconnectingforwardcables,block rearcables in front of bulkheadF.S.310.0, keeping
cablestensionedand preventingslippagefrom pulleysand sector.
(d) Markone cable and tumbuckleto facilitateinstallationand disconnectturnbucklesat F.S.
303.5.
(e) Removecableguard pins from pulleyclusters,disengagecable endsfrom forwardcontrol
sector,and removetop pulleyat F.S.77.2.
(f) Slowlyand carefullypull cablesfrom betweenF.S.110.37and F.S.117.88bulkheads.
2. Installationof ForwardRudderCables (Figure401)
(a) Withfloorboards,pulleys,and guidepins removed,installcable ball ends to forwardsector
underneathrudderpedals. (Removesector,if necessary.)
(b) Feedcables backthroughpulleysto F.S.303.5.
(c) If aft cables are not installed,ensurecablesare alignedon pulleysand sector,and put tension
on cableswhile blockingthem aft of bulkheadF.S.310.0.
(d) If aft cables are installed,attachcablesto turnbucklesat F.S.303.5.
(e) Rig rudderand set cabletension (referto Figure501). Ensurecablesare alignedon pulleys
and sector.
3. Removalof ForwardRudderControlSector
(a) Disengagecontroltubesfrom leftpedal arms. Tapetubes to pressurebulkheadF.S.57.0.
(b) Rotatepedalsand tie them out of way.
(c) Withfloorboardsunder pedals removed,disconnectcables.
(d) Reachdown throughaccesshole in floor and disconnectcontroltubes on sectorand tube,
disconnectingsectorbellcrankfrom rudderpedalcontrolbellcrank.
(e) Removebolt retainingsectorassemblyto two mounts.
(f) Carefullyremoveassemblyfrom underfloor.
4. Installationof ForwardRudderControlSector
(a) Installassemblyfrom underfloor.
(b) Installbolt retainingsectorassemblyto two mounts.
(c) Connectcontroltubes on sectorandtube, connectingsectorbellcrankto rudderpedalcontrol
bellcrank,via accesshole in floor.
(d) Connectcablesto pedalsand installfloor boards.
(e) Removepedalties and place pedalsintotheir properposition.
(f) Removetape from tubesat pressurebulkheadF.S.57.0. Engagecontroltubes from left pedal
arms.
EFFECTIVITY:
040-999
27-20-00 Jan
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
RudderTrim Pulleys
RudderTrim Cable
FuselageStation279.38
FuselageStation333.43
RudderControlSystemInstallation
Figure 401 Sheet (1 of 2)
PAGE
2 27-20-00
7-20-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTralner)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
RudderTrim
FuselageStation62.75
RudderTrimActuatorAssembly
FuselageStation387.00
FuselageStation380.61
FuselageStation402.40
RudderControlSystemInstallation
Figure 401 Sheet(2 of 2)
EFFECTIVITY:
040-999
27-20-00JanPAGE
10/90 3
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
5. Removalof Aft RudderCables (Figure401)
(a) Removeleft side floor panelson backtwo cargo decksfrom F.S.280.0 to F.S.332.0 and tail
cone (stinger).
(b) Removefairleads in bulkheadF.S.332.0.
(c) If forwardcable systemhas not been removed,block it at F.S.281.5 pulleysto preventcables
from slippingpulleys and sector.
(d) Disengageaft cablesfrom tumbucklesat F.S.303.5 and tie a 10 foot leader line to each cable
terminals end.
(e) Removeaccess panelson left side of tail.
(f) Removecable guide pins at F.S.334.00,354.67,and 379.5 (thoseon aft cantedbulkhead)
pulleys.
(g) Disconnectcable endsfrom aft sectorand carefullypull cablesout through back of aircraft
ensuringenoughleader line extendsfrom eachend.
6. Installationof Aft RudderCables (Figure401)
(a) Tie each cable terminal end to leader line and from cargo area insidecabin at F.S.303.5pull
each cablethrough fuselagetail.
(b) Attach cable ball endsto sectorand lock rudderin neutralposition.
NOTE: If forwardcable systemis not installed,ensure cablesare centeredin pulleysand
block them to bulkheadF.S.310.0.
(c) At F.S. 303.5 in cargo sectionof cabin,removeleader lines. After ensuringall cablesare 5.
properlypositionedon their pulleys,engagecableterminalends with properturnbucklesand
tighten to specificationsin Figure501.
(d) Installcabin fairleads into F.S.bulkhead332.0.
7. Removalof Aft RudderControlSector (Figure401)
(a) Removetail cone (stinger)and after looseningcables at F.S.303.51,disconnectcontrolcables
from ruddersector.
(b) Disconnectruddertrim actuatorrod end from trim shaft arm and removetrim shaft (explainedin
sectioncoveringthe ruddertrim system).
(c) Removesafety wire and four bolts fasteningruddertorquetube mountingplate (stud weldment
plate) to ruddersector.
(d) Removefive countersunkmachinescrewsby rotatingsectorfor access.
NOTE: It could be necessaryto rotate sector180° to gainaccessto two forwardscrews.
(e) Slide sectorassemblyoff supportbracket.
(f) To disassemblesectorassembly,removesnapring where adapterextendsthrough sectorand
carefullypull piecesapart notingwhereeach componentis installed.
PAGE4
Jan 10/9027-20-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. RudderandTab (continued)
8. Installationof Aft RudderControlSector (Figure401)
(a) Assemblypiecesof componentand install snapring where adapterextendsthroughsector.
(b) Slide sector assemblyonto supportbracket.
(c) Installfive countersunkmachinescrews.
(d) Installfour bolts fasteningruddertorquetube mountingplate (studweldmentplate)to rudder
sectorand safetywire.
(e) Installtrim shaftand connectruddertrim actuatorrod end to trim shaft arm.
(f) Connectcontrolcablesto ruddersectorat F.S.303.51 and installtail cone (stinger).
9
Riggingof the Rudderandits Controls(Figure501)
(a) Removepilotseatandfloorpanelson forwardsideof pressurebulkhead(FuselageStation
57.0).
(b) In backof cabinbetweenF.S.bulkheads298.38and310.00,removeleftsidefloorpanelsto
accesspulleysat F.S.303.5. Removetail cone(stinger)to accessruddersector.
(c) Adjustrudderpedalandrudderfor neutralpositionasfollows:
(1.) Install rudderriggingtool (P/N72260)on right side of verticalfin with markingson tool
facing down. Attachtool to fin with No. 10-32screwsand 3 rivnutsat W.L. 84.57.
(2.) Install ruddertrim tab riggingtool (P/N72266-2)on right sideof rudder. Attachtool to
rudder,markingsfacingdown,using 3 No. 8-32 screwsand 3 rivnutsat W.L. 35.42.
(3.) Since differentinstallationsof rudderpedalpushrodassembliesexist,referencepointfor
rudderpedals is determinedas follows:
(a.) For pedal pushrodsP/N 70752-19and P/N 70752-20,aircraft up to serial number42801038,positionand securerudderpedals 10.51± 0.25 inchesaft of pressure
bulkheadto pedalhingetube. Measurementto center after tube is 10.85± 0.25
inches.
(b.) For wing pedalpushrodsP/N 70752-23and P/N 70752-24,aircraft serial numbers428010038and up, installrudderpedal riggingtool P/N 72233 on pilot left and right
pedalsas follows:
(4.) Adjust lengthof pedalpushrodsto level bellcrankon pressurebulkheadand adjust
bellcrankto sectionpushrodso forwardruddersectoris vertical.
(5.) Positionrudderin neutral(± 1°).
(6.) Ensureruddercablesare properlyroutedaroundpulleys and are securedwith cable
guards. Rig cablesaccordingto specificationsin Figure501, or proceedwith following
step ifautopilotis installed.
CAUTION: CABLETENSIONMUSTBEADJUSTEDEVENLYSOAS NOTTO
DAMAGECLAMPEDRUDDER.
(7.) Since autopilotbridlesaffectprimarycabletension,do not readjustprimaryruddercable
tensions. Proceedas follows:
(a.) Set tensionto 55 pounds± 5 poundsand hookup bridle.
(b.) Tensionautopilotbridlecablesusingpropermanufacturersservicemanual. Primary
ruddercable tensionincreasesdownstreamof bridleand decreasesupstream.
(c.) Recordtensionsupstreamand downstreamof autopilotbridle cable hookupfor later
verification.
(d.) Duringverification,ensuretensionupstreamof autopilotbridlecable hookupis within
+ 5 poundsof previouslyrecordedvalues.
EFFECTIVITY:
27-20-00Jan
Jan 10/90
1090
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
9
0
Riggingof the Rudderand its Controls (continued)
(8.) Removerudderclamp and pedaltools. Smoothlyrotate rudder30° right and 20° left.
(9.) Adjust rudderstops at ruddersectorfor 30° right and 20° left.
(10.) With rudderin neutral,rotatetrim wheel in cockpitso tab travel is 10° rightand 20° left.
Trimcable tension to matchspecificationsin Figure501.
(11.) Removeriggingtools and reinstallaccesscovers.
Rudder and Rudder Trim Tab
A - 20° +1° -0
B 10° +1° -0
C 30° +1 -0
D 20 +1 -0°
CableTension
Rudder= 55 Ibs.± 5 Ibs.
RudderTrimTab = 14 Ibs.± 2 Ibs.
CAUTION:BEFORETENSIONINGCABLESMAKE
SURETO CLAMPTHE SECTOROR CABLES
TO PREVENTLOADON CLAMPEDRUDDER.
TrimTabtravelwith
ChordLine
(neutralPosition)
-
-
Rudderin neutralposition.
Fin, RudderandTrim Tab
Viewedas seed from above.
Rudderand Trim TabControlTravelsand CableTensions
Figure 501
PAGE
6 27-20-00
27-20-00
Jan10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
Tool P/N 72260
Rudder
RudderRiggingTool
Figure 502
TrimTab
Trim Tab Tool P/N 72266-2
RudderTrim RiggingTool
Figure 503
EFFECTIVITY:
040-999
2720-00
27-20-00
7
PAGE
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. RudderandTab (continued)
10. RudderControlSystemFrictionCheck (Figure601)
NOTE: Whenmeasuring
ruddercontrolsystemfriction,nosegearmustbe retractedorbungee
disconnected
in noselandinggearwheelwell.
Usinga springscaleplacedon rudder(Figure601),moverudderfromtwoinchestrailingedgeleft
to two inchestrailingedgerightandback. Measureforceneededto moveruddereachtime
trailingedgepassesthroughneutral.Bothreadingsmustnotexceed6 pounds.
NOTE: Frictionmeasurements
aretakenwithoutautopilotbridlecablesconnected.If bridle
cablesare connected,
frictionreadingmustnotexceedseven(7)pounds.
11. Removalof ForwardRudderTrimSystem(Figure401)
(a) Removecopilotseat and floor panelson same side,from spar carry throughto pressure
bulkhead F.S.57.0.
(b) Pulleysaft of forwardscrewdrum are locatedon right side of aircraft underfloor at F.S.101.23,
280.0, 332.0, and 376.0. Rub blocks are locatedat F.S. 162.3, 181.0, 174.0,and 251.0. To
gain accessto this cable hardware,removerequiredseats and floor panels. If fairleadsfor aft
cable systemin pressurebulkheadF.S.332.0 mustbe removed,removeright side floor panels.
Approachturnbucklesaround F.S.312 throughright side floor panelsbetweenbulkheadsat
F.S.310.0 and 321.0.
(c) Blockforwardcablesystemat trimscrewunderneath
controlpedestalandaft cablesystem(if
notremoved)at pressurebulkheadF.S.332.0. If alsoremovingaft ruddertrimsystem,block
cablesat aft screwdrumon aftcantedbulkheadat F.S.380.35.
(d) Markonesetof turnbucklecableendsto facilitateinstallation
of F.S.312.0. Removecable
guidepinsandrubblocksto easeremovalof cables.
(e) Disconnect
cablesfromtumbucklesandattachtwo23foot leaderlinesto eachcableterminal
end.
(f) From cockpitat F.S.78.0, carefullypull cablesthroughaircraft.
(g) Removefour bolts attachingscrewdrum assemblyto channel plate. Removepin linkingdrive
shaft to drum.
(h) Pullcablesupto drumanddisconnect
leaderlines.
(i) Removedrumandcableassemblyfromaircraft.
NOTE: Notecableroutingandwhichcables(respective
to screwdrum)areattachedto which
leaderlines.
Rudder
50
TAB
Measure
fromhere
.50
RudderFrictionCheck
Figure601
EFFECTIVITY:
Jan 10/9027-20-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
12. Installationof ForwardRudderTrim System (Figure401)
(a) Ensurecable is centeredand evenlywrappedon trim drum (see paragraphon Wrappingof
Trim Drums). Blockcablesto preventdrum from unwrapping.
(b) Laytrim drum on floor in front of pedestaland attach leader linesto propercables.
(c) Fromrear of cabin, carefullypull cablesthroughfuselageensuringcablesare alignedon
pulleys.
(d) Installcable guidepins and rub blocks.
(e) Installdrive shaftfrom controland mountthe drum assemblyon channelplate.
(f) Followcable back downfuselageand align in pulleyand rub blocks.
(g) If aft trim systemis not installed,pull cablestight and blockthem on aft side of F.S.310.0
bulkhead.
(h) If aft trim systemis installed,engagecableswith properturnbucklesand rig and tightencables
to specificationsin Figure501.
(i) Conducta final checkof all cable routing,pulleys,and rub blocks.
(j) Installall accessplates, carpeting,and seats.
13. Removalof Aft RudderTrim System (Figure401)
(a) Removeright side floor panels betweenbulkheadsF.S.310.0 to 332.0,two accessplateson
right side of tail and tail cone (stinger).
(b) Blockaft trim cables(usingone methodin 27-00-00,Figure 2) on front side of bulkheadF.S.
332.0to preventunwrappingfrom screwdrum assemblyon aft cantedbulkhead.
(c) Blockforwardcablesto rear of F.S.310.0 bulkhead.
(d) Mark one set of turnbucklecable endsand removefairleads in pressurebulkheadF.S.332.0.
(e) Disconnectcablesat turnbucklesand attach10 foot leaderline to two cableterminalends.
(f) At pulleys on bottomof pressurebulkheadand on aft cantedbulkhead,removecableguide
pins and blockcableson aft screwdrum.
(g) Removecable blocksat F.S.332.0 and bolts retainingscrewdrum to canted bulkhead.
Carefullyremovedrum.
(h) Carefullypull cablesout tail and disconnectleader lines,notingwhich lines are attachedto
which cables,respectiveto trim drumin its mountedposition.
14. Installationof Aft RudderTrim System (Figure401)
(a) Ensureappropriatecable is centered,evenlywrappedon drum (explainedon paragraph
entitledWrappingof Trim Drums),and blockedto preventunraveling.
(b) Positionscrewdrum assemblyon cantedbulkhead. Mountwith two bolts and required
washers.
(c) Attachcable terminalendsto leader lines and from insidecockpitat F.S.313.0. Carefullyand
slowlypull cablesthroughfuselage. Removeleader lines from cableswhen cablesare in
fuselage.
(d) Ensurecables are properlycenteredon pulleys.
(e) Attachecable to properturnbuckles.Tightenand rig systemto specificationsin Figure501.
EFFECTIVITY:
27-20-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
15. Removalof Trim Tab
(a) Removefairing/access
coverswherecablescomethroughrudder.
(b) Loosencabletumbucklesandremovecablesecuringfixturesontrimtabsectors.
(c) Removehingeboltsandtab.
16. Installationof Trim Tab
(a) Verifythatcablesarereriggedbeforeinstallingfairing/access
covers.Installhingeboltsand
tab
(b) Installcablesecuringfixtureson trimtabsectorsandtightencabletumbuckles.
(c) Installfairing/access
coverswherecablescomethroughrudder.
17. Riggingof RudderTrim (Figure501)
(a) Before adjustingruddertrim, proceedas follows:
(1.) Ensurecables are centeredand evenlywrappedon trim drums.
(2.) Removeright side floor panels betweenF.S.310.0 and 321.0. Ensurecable turnbuckles
are near F.S.312.3.
(3.) Check cable tension (Figure501).
(b) Removetail cone (stinger)and access plateon ruddernear WaterLine 45.0.
(c) Disconnectrod end from trim tube arm so trim screwis free to rotate.
(d) In cockpit,center control at neutraland ensuretrim drum underfloor is in neutral position.
Forwarddrum cable capacity is 18 1/2 turns, and when set with systemin neutral,2 1/4turns of
each side of cable mustbe wrappedon drum.
(e) With systemin neutral,ensure aft screwdrum in tail also has9 1/4 turns of cable wrappedon
each side of drum.
(f) On aft trim drum, measuredistancefrom machinedsurfaceof drum assemblyto stopwasher
on screw. (End of screwwith rod end attached.) Distancemustmeasure0.625 inches. Screw
rod assemblyin or out for propermeasurement.
(g) With trim screwand systemin neutral,align rod end with trim tube arm, and insertbolt to set
and holdtab position. Trailingedges of tab and ruddermust align. If control surfacesdo not
align, pull bolt out of arm and rod end and turn screwshaft in or out until tab aligns. For fine
adjustments,use turnbuckles.
(h) Installand secureattachmentbolt in rod end; trim tube arm.
(i) In cockpit,turn control to each stop and measureanglesof deflectionfrom centerlineof rudder.
Measurementsmustcompareto those in Figure501. Use riggingtool (Figure503) to check
tab angles.
(j) After adjustingsystem,turn controlto its stops and ensureno less than 1 1/4 turns of cable is
left on either drum.
(k) Using tool (L73035)and dial typetorque wrench,checktrim systemfriction at pedestalby
removingtrim wheel and attachingtool and torque wrenchto splinedshaft. Frictionmustnot
exceed 9 inch-poundswhen tested in either directionat any point betweenlimits.
PAGE10 27-20-00
Jan10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Rudderand Tab (continued)
18. Removalof RudderPedalAssembly (Figure402)
(a) Removepilotandcopilotseatsfor easieraccessto pedals.
NOTE: If bearingsupporthousingandbearingson endof tubesareonlyrequiredserviceable
items,proceedto step(f).
(b) Disconnect
brakecylindersfromrudderpedalclevisarmsandsupportbracketssobrake
cylinderassemblies
(brakecylinderandextension)
remainassembled.If removing
eitherof
copilotpedals,disconnect
brakecylinderfor leftpedalat rudderpedalclevisarmand
extension.Removeextensionwithrightrudderpedalorforwardtubeassembly.
(c) Usethefollowingprocedure
to removeleftpedals(afttube assembly)
on pilotandcopilotside:
(1.) Removeboltsattachingpillowblockcapsto housingsandremovetwoboltson rightside
of blockmounting
bracket.Afterremovingcaps,reinstallboltsin leftblock.
(2.) Removetwobolts,attachingtubesupportassemblyon pilotsideto bracket,mountedon
pressurebulkhead.
(3.) Removeboltssecuringleftpedalassemblies
to torquetube.
(4.) Supporting
aft tubewithyourhand,removeclevispin in leftendof tube,fasteningit to
bearingsupporthousing.
(5.) Withboltsremovedfromrightpillowblock,ensureitsfreemovement.Carefullysliderear
tuberight,slidingpillowblockwithit untiltubeis freeof bearing;layblockon floor.
(6.) Whentubeis clearof bearingsupporthousing,slidesubassemblies
off tube. If tube
needsto be replaced,
jockeyit outfromunderneath.
(d) Toremovepilotandcopilotrightpedalsor forwardtorquetube,proceedasfollows:
(1.) Removebothpillowblockcaps. Reinstallattachment
boltsin rightsideblockhousing.
Removeboltsin leftsideof blockhousingmountingbracket.
(2.) Disconnect
brakecylinderassemblies
(brakecylinderandextension)
fromforwardtube
supportandremoveboltssecuringtwotubesupportsto bracketsmountedon pressure
bulkhead.
(3.) Removeboltsmountingrudderpedalassemblies
to forwardtorquetube.
(4.) Onpilotside,disconnect
aft tubesupportfrombracketandrotateoutof way.After
removingboltsconnecting
pilotleftrudderpedalto pushrodandtorquetube,slidepedal
assemblyasfar to leftaspossible.
(5.) Removeclevispin in bearingsupporthousinganddisconnect
copilotleftbrakecylinder
fromits extension.
(6.) Whileholdingleftpillowblockhousing,carefullyslideforwardtubeleft,movingassemblies
outof wayuntiltubeclearsbearingsupporthousing.
(7.) Removenecessary
assemblies
fromtube. If rudderpedaltorquetube needto be
replaced,removeas manyassemblies
aspossiblefromtubebeforejockeyingit outfrom
underneath
panel.
(e) Sleevesandbearingssupporttubeson rubblocksconstitutea pressedfit. Todisconnect,
removerivets,heattube,coolsleeve,andbearing;slidesleeveandbearingfromtube.
(f) Removebearingsupporthousingsandbearingsasfollows:
NOTE: If previousinstructions
havebeenfollowed,proceedto Step(g)(5.).
EFFECTIVITY:
040-999
27-20-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. RudderandTab (continued)
(g) Toremovepilotandcopilotrightpedalsorforwardtorquetube,proceedasfollows:
(1.)Removeclevispin mountingspecificbearingsupporthousingto tube.
(2.)Withreferenceto aft tubeassembly(thatclosestto pilotandcopilot),removeboltsretaining
pedalsto torquetubeandboltsin rightpillowblock.
(3.)Withreferenceto forwardtubeassembly,
removeboltsretainingpedalsto torquetubeand
boltsin leftpillowblock. Afterdisconnecting
pilotleftbrakecylinderassembly(brakecylinder
and extension)
fromforwardtubesupport,disconnect
supportfrombracketon pressure
bulkheadandswingit outof waysoforwardtubecanslideto left.
(4.)Whilesupporting
unconnected
pillowblockhousing,slideaffectedtorquetubeandblock
housingsotheyclearbearingsupportsleeve.A socketwrenchcanbe usedto removebolt
mountingbearingsupportsleeveto fuselagesupportskin. Whenpilotblockclearsmounting
pad, layit onfloor.
(5.)Withtorquetuberemovedawayfrombearingsupporthousing,removebearingandhousingby
ratchetingboltoutof sleeve.Noteplacement
of hardware.
(6.)Afterremovinghousing,removebearingpressedintohousing.
19. Installation
of the RudderPedalAssemblies(Figure402)
(a) If rudderpedaltorquetubeandpillowblockbearingsupportsleevefromtubeisto be removed,
proceedasfollows:
(1.) Fillbucketwithice cubesandplaceendof tubeso it acceptssleevein ice.
(2.) Heat supportsleevein oven at 350° for 15 minutes.
(3.) Removetorquetubefromiceandimmediately
slideheatedsleeveovertube. Besureto
alignholesin twoassemblies
solongersleeveend,relativeto rivetholes,facestoward
tubeendto be supportedin bearingsupporthousingon fuselageside.
(4.) Withsleeveproperlypositionedon tube,installtwoNAS1738Bblindrivets.
(5.) If bearingsupporthousingon sideof fuselageis removed,replacein reverseorderof
removal.
(6.) Withbearingsupporthousinginstalled,
properlyinsertandaligntubein supporthousing
andalignpillowblockin properposition.
(7.) MarksupportsleevewhereKP21Bpillowblockbearingis to be positioned.
(8.) Removetorquetubefromunderneath
panel.Installbearingon sleeve.
(b) Withtorquetubepositionedunderpanel,proceedasfollows:
(1.) Positiontube in bearingsupporthousingsoit is properlyplacedin rightpillowblock,
forwardopening.
(2.) Withrightpedalandforwardtubesupporton pilotsideslideon torquetube,looselymount
tubesupportto bracketon pressurebulkhead.
(3.) Completesameprocedureon copilotside.
(4.) Withtube looselymountedon supportbrackets,slideit leftuntilbearingon bearing
supportsleeveis hangingoverfloor. Pushbearingintoproperpillowblockhousingby
aligninghousingbearingslotwithbearingandpushinghousingup ontobearing.If fit is
tootight,ensurebearingis properlyalignedandappropriate
bearingis used. Finally,
rotatehousingaroundtubeandcarefullypushhousingon withsoft mallet.
NOTE: For RudderBalancingProcedure,
referto 55-40-00.
EFFECTIVITY:
Jan 10/90 27-2000
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. RudderandTab (continued)
(b) Withtorquetubepositionedunderpanel,proceedasfollows:(continued)
(5.) With bearingpositionedin pillow blockhousing,place housingundertube and align aft
tube with openingin pillowblock. Slide forwardtube right and into bearingsupport
housing,ensuringthe pillow block alsoslides into properpositionon mountingbracket. To
ensure properalignmentof pillow blockhousing,installcap bolts withoutblockcap.
(6.) Installclevis pin, washer,and cotter pin throughbearingsupporthousingand torquetube.
(7.) Bolt on rudderpedals and brake cylinderswhere required.
(8.) Installand connectall hardwareand assemblies.
(c) Slideremovedassemblies
to aft ruddertorquetubein propersequence.
(1.) Positiontube in bearingsupporthousingon left side of fuselage so it is properlyplaced in
left pillow block,aft opening.
(2.) Connectaft tube supporton pilot side to bracketon pressurebulkhead.
(3.) With tube supportedby supportbracketand left pillow block,reinstallbearingin pillow
block housing.
(4.) Reinstalltube and reconnectall hardware.
(d) Checkrigging.
EFFECTIVITY:
27-20-00 PAGE
13
=
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. RudderandTab (continued)
Bearing
TorqueTube
End Bearina
RudderPedalsInstallation
Figure 402
EFFECTIVITY:
PAGE 14 27-20-00
Jan 10/90
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ElevatorandTab
NOTE: Anytimethe elevatorcontrolsystemis serviced,conducta frictioncheckto ensure system
frictionis within limits.
of ForwardElevatorControlSector(Figure401)
1. Removal
(a) Removepilotseatandallcentralfloorpanelsat F.S.270.0and322.5,andthosein frontand
behindthem.
(F.S.270.0or322.5)anddecrease
(b) Removesafetyclipfromproperelevatorcableturnbuckle
oneof turnbuckleeyes.
cabletensionby partiallyunscrewing
seatson leftsideof cabinsofloor panelbehindsparcarrythrough
(c) Moveor removeappropriate
sectioncanbe removed.
at F.S.142.0anddecreasecable
(d) Removesafetyclipon oneof aileroncableturnbuckles
tensionon aileronsector.
controlcolumnelevatorpushrodandcontrolcablesfromforwardelevatorsector.
(e) Disconnect
(f) Removetensionfromtwocablesystems,unscrewpivotbolt,andcarefullyslideoutboltuntil
fromunderaileronsector.If controlcolumnpushrodof aileron
elevatorsectorcanbe removed
pushrodfromaileronsector.
disconnect
controlsectorimpedesremoval,
of ForwardElevatorControlSector(Figure401)
2. Installation
(a) Positionsector,under aileronsectorcontainingpushrodmountingflange,to right and on
bottom.
(b) Align sectorto fit pivot boltand pushbolt throughsectors.
(c) ScrewAN6-60Apivot bolt into nut plate using standardtorque designatedin AC43-13.
NOTE:Tofacilitaterigging,ensuretorquetubedrivingforwardsectormeasures12.31inches
betweendefinedcentersof tworodendbearings(Figure401).
(d) Attachpushrodto mountingflangeextendingfrom bottomof sector.
(e) Installright elevatorcable in starboardgroove of sector,retainingplatewith retainingscrew,
and safetywire.
(f) Installleft elevatorcable in groove.
(g) Tightenaileroncables (Figure401) and rig elevatorcables(Figure501).
of Aft ElevatorControlSector(Figure401)
3. Removal
(a) Removerearwardmostaccessplateson bothsideof fuselagetailandbulletassembly
fromtail.
extending
linkagewith
tubefromsector,gainaccessto tube/sector
NOTE: Whenremovingaft push-pull
elevatorin up position.Maintaina firmgripor clampsupporton elevatorto prevent
release.
(b) Rotateelevatorto pullup position.
(c) Withtwo peoplereachingthrougheachtail sectionaccesshole,removelocknutandboltand
carefullyreleasetube.
(d) Removefirst three accessplatesin centerof raisedfloor and disconnectelevatorcablesat F.S.
270.0and F.S.322.5 to relievetensionin system.
(e) Withone person reachingthroughaccessand lighteningholes and holdingbolt, and another
holdingnut, unscrewand removepivot bolt.
(f) Pullsectorforwardthroughslottedbulkheadand disconnectcablesby removingsafetywire
and retainingscrews.
(g) Removesectorfrom fuselage.
EFFECTIVITY:
040999
27-30-00JanPAGE1
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
4. Installation
of Aft ElevatorControlSector(Figure401)
(a) Withaft cablesystemdisconnected
at oneturnbuckle,eitherat F.S.270.0or 322.5,connect
cablesasfollows:
(1.) Insertup cablein groovebetweenarmandsector,fastencableto sectorby screwingon
retainingplace,andsafetywireplateandscrewto sector.
(2.) Repeatprocedure
to fastenothercable.
(b) With an assistantreachingthroughaft controlbulkhead,slide sector(tube armforward)through
slot in bulkheadF.S.368.0 until it can be held in aligned position. While holdingsector in
position,insert AN5-25pivot bolt.
(c) With an assistantreachingthroughstarboardaccessand lighteningholes holdingnut, reach
throughon other side and tighten pivotbolt.
(d) Reconnecttumbucklesand pushtube to sectorarm.
5. Removalof ElevatorControlCables(Figure401)
Thecablesystemfor elevatorprimarycontrolsrunsfromtheforwardcontrolsectorat F.S.93.3,
underpilotseat,to aft sectorat F.S.373.10.Theforwardupcable,attachedto rightsideof sector,
is routedto left sideof aircraftandaroundpulleyat F.S.101.07.Thecableis thenroutedthrough
leftsideof fuselageandsparcarrythroughto a secondpulleyat F.S.153.35,whereit turnstoward
pulleyat F.S.193.72at centerof aircraft.Fromthirdpulley,it travelsstraightthroughfuselage
centerto fourthpulleyat F.S.278.0,whereit anglesupto turnbuckle
at F.S.322.5.Theaft up
cableis routedthroughfairleadin aft pressurebulkheadthroughpulleysat F.S.355.75and366.0
andto aft controlsector.Theforwarddowncable,attachedto leftsideof forwardcontrolsector,is
mountedsimilarto up cablewithpulleysat F.S.112.47,160.2,and200.98,andturnbuckleat F.S.
270.0. Theaft downcabletravelsfromturnbuckle
throughpulleyat F.S.278.0,fairleadin aft
pressurebulkhead,andpulleyon bulkheadaheadof aft controlsector.Toremovecables,proceed
asfollows:
(a) Thefollowingproceduremustbe usedto removeforwardelevatorcables:
(1.) Removepilotseatandleftpassenger
seatsfromF.S.135.to 203.0andfloorpanels
necessaryto gainaccessto pulleysandturnbuckles.
(2.) Markendof cableto be removedto facilitateinstallation.Disconnect
cablefrom
tumbuckle.
(3.) Afterdetachingcablefromturnbuckle,
attach20 footleaderlineto cableend.
(4.) Removecableguardpinsfromrequiredpulleys.Disconnect
cablesfromforwardsector.
(5.) Frombehindpulleysat F.S.101.07,carefullypullcablesinsideaircraftsoenoughleader
lineexistsfor reinstallation.
(b) Toremoveaft elevatorcontrolcables,proceedasfollows:
(1.) RemovecenterflooraccesspanelsfromF.S.265.0backto aft pressurebulkhead.
Accesspanelson tail andtail cone(stinger).
(2.) Followsteps(a)(2.),(a)(3.),and (a)(4.)to removecablesfromaft sector.
(3.) Reachthroughaft accessopeningon fuselage,workcablesforwardthroughslotted
bulkhead,andpullcablesfromaircraftensuringleaderlinelaysin pathof removedcable.
(4.) Disconnect
leaderlines.
EFFECTIVITY:
PAGE
2
Jan 10/90 2730-00
27-30-00
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
ControlCables(Figure401)
6. Installation
of Elevator
of
NOTE: Usecablesandsectorsmarkedwithred paintto facilitateandassureproperinstallation
redcorner
elevatorup cables.Verifythatredballendof cableis attachedto appropriate
withadjoiningup cable
to turnbuckle
of sectorandredterminalendof cableis attached
alsohavingredterminalend.
(a) Forwardcontrolcables,runningfromforwardcontrolsectorto tumbucklesat FuselageStation
270.0and 322.5, are installedas follows:
(1.) Behindforwardsector,tie leaderlineontocableswagedterminalend,an from(aftcable)
turnbucklepositionor endof leaderline,pullleaderandcablethroughaircraftensuring
the cableis routedcorrectly.
(2.) Referto sectionon elevatorriggingcontrolandtightenelevatorcontrolcablesat
turnbuckles.
(3.) Reinstallall cableguardpins,rubblocks,andotherhardware.
(b) Aft cables,runningfrom turnbucklepositionsto aft sector,are installedas follows:
holein aftcanted
(1.) Connectcablesto at controlsectorbyreachingthroughlightening
by
removing
aft
sector.
aft
access
opening
in
tail,
or
bulkheadand
(2.) Feedcablesthroughpulleyson F.S.368.0bulkhead(whereaft sectoris attached).Attach
cableterminalendsto leaderlines.
(3.) Withleaderlinestiedto cableends,haveassistantfeedcablesthroughpulleysat
turnbuckle
station,orwhereleaderlinesend.
(4.) Aftercablesare pulledthrough,ensurecablesareproperlyroutedwithrespectto sector
andseatedin pulleys.
in thissection.Tightencablesin turnbuckles.
(5.) Checkrigginginstructions
(6.) Reinstallall cableguardpins,fairleadsaccesspanels,andotherhardware.
(c) Checkproperoperationof elevatoraftercableriggingis completed.
EFFECTIVITY:
040-999
3
27-3000PAGE
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Elevatorand Tab (continued)
Shadedareasrepresent
the comersof the sectors
paintedred.
Elevatorupcable
FuselageStation93.90
ElevatorTrim
Pulley
F.S.
431.45
F.S.
417.76
F.S.
FuselageStation102.72
432.84
Referto Note
Note
NOTE: Applycorrosionretardant
compoundPiperP/N 197508 or
197509,with springin extended
condition.Referto 91-00-00for
Listof Consumable
Materials
F.S.
F.S.
27.38
162.80 F.S.
251.00
344.31
F.S.
332.50
F.S.
F.S.
373.37
r
F.S.
F.S. 365.96
355.75
F.S.
I
78.76
F.S.
93.30
F.S.
160.20
r-\
ElevatorSystemInstallation
Figure 401 Sheet (1 of 2)
EFFECTIVITY:
040-999
Jan
10/9027-30-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Elevator and Tab (continued)
ElevatorTrim
Cables
ElevatorTrimPulleys
FuselageStation162.60and 251.00
FuselageStation279.38
NOTE: Applycorrosionretardant
compoundPiperP/N 197 508or
197509, withspringin extended
condition.Referto 91-00-00for
Listof Consumable
Materials
FuselageStation332.50
See Note
Elevator
UpCable
FuselageStation431.45
FuselageStation373.37
ElevatorSystemInstallation
Figure 401 Sheet(2 of 2)
EFFECTIVITY:
040-999
27-3000
27-30-00
PAGE
5
Jan
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Elevator and Tab (continued)
ELEVATORAND ELEVATORTRIMTAB
A. 7°+ 1°-20
B. 30°+ 1°-0
C. 12° + 1/2° - 0°
D. 20° + 1° - 0
CABLETENSIONS
ELEVATOR= 55 LBS ± 5 LBS.
-
NOTE -
TRIM TABTRAVELWITH ELEVATORIN
NEUTRALPOSITION
ELEVATOR TRIM = 14 LBS. + 2 LBS.
CHORD LINE LEVEL (NEUTRAL POSITION)
D
- NOTES-
1.TRIM TAB NEUTRAL POSITION IS TAB
TRAILINGEDGE EVENWITH THE TRAILING
OR ITS NEUTRAL
EDGEOF THE ELEVATOR,
POSITION.
2. TRIM TAB FREE PLAY MUST NOT EXCEED
0.126MAX. AT THETRAILINGEDGEOFTHE
TAB.
3. RIG ELEVATORS WITH ELEVATORS IN
NEUTRAL POSITION (PINNED AT AFT
SECTOR). VERIFY THAT RIGHT HAND
ELEVATORTRAILING EDGE IS ALIGNED
WITH LEFT HAND ELEVATOR TRAILING
EDGE. ADJUST LENGTH OF ANTI-SERVO
RODS TO OBTAIN 0.12" ± 0.12" TRAILING
EDGE UP OF THE RIGHT HAND TAB AS
MEASURED ON THE INBOARD TRAILING
EDGEOF THETAB.
Elevator and Elevator Trim - Travels and Cable Tensions
Figure 501
Feb 1/98
27-3000
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
Tool P/N72046
ElevatorRiggingTool
Figure 502
ElevatorHornAssembly
ElevatorTorque
TubeCollar
VIEWA-A
ElevatorRiggingStops
Figure503
EFFECTIVITY:
040-999
27-30-00JanPAGE
10/90
PIPERAIRCRAFT
PA42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
7. Removalof ElevatorPushTube (Figure401)
(a) Removebullet,aft accessplateson tailandverticalstabilizer,
andbulletassemblyontopof
verticalstabilizer.
(b) Afterremovingbulletassemblyfromtopof verticalstabilizer,blockor tiecontrolhornso
elevatorremainsin mostupwardpositionwhentubeis releasedfromsector.
(c) Withelevatorin mostupwardposition,tubeandconnecting
armon aft sectormustprotrude
throughsloton bulkheadto whichthesectoris attached.Reachthroughaft accessholein tail
anddisconnect
tubefromsectorby removingAN4-13Abolt.
(d) Removerestraintfromcontrolhorn. Allowelevatorto moveto downstop.
(e) Withelevatorin downposition,tubeconnection
to controlarmis nowaccessible.Disconnect
tubefromelevatorhornandpulloutof tail.
(f) Disconnect
elevatordownspringandapplyretardant
withspringin extendedposition.(Refer
to Lubrication
Chartin 12-20-00for corrosionretardants
usedon elevatordownspring.)
8. Installation
of ElevatorPushTube (Figure401)
(a) Connectelevatordownspring.
(b) Withelevatorin downposition,tubeconnection
to controlarmis nowaccessible,
insertintotail.
Connecttubeto elevatorhorn.
(c) Installrestraintto controlhorn. Moveelevatorto mostupwardposition.
(d) Withelevatorin mostupwardposition,tubeandconnecting
armon aft sectormustprotrude
throughsloton bulkheadto whichthesectoristo beattached.Reachthroughaft accesshole
in tail andconnecttubeto sectorbyinstallingAN4-13Abolt.
(e) Removerestraintfromcontrolhom. Allowelevatorto moveto downstop.
(f) Installbullet,aft accessplateson tail andverticalstabilizer,andbulletassemblyon topof
verticalstabilizer.
NOTE: Forrigging,ensurecontroltubemeasures120.5inchesfromcenterof endfitting
bearingto centerof rodendbearing.
9. Riggingthe ElevatorControlSystem(Figure501)
NOTE: Mostadjustments
to systemare madewithcabletumbuckles.Pushrodsandtubearea
specifiedlengthfromrodendto rodendbearingcenter,andcanonlybe usedfor minor
smalladjustments.If wholesystemmustbe rigged,followinstructions
asgiven.
Otherwise,
followinstructions
for specificareasonly,usingotherinstructions
as a check.
(a) Togainaccessto existingsystems,proceedasfollows:
(1.) Togainaccessto forwardcontrolsectors,removepilotseatandsurrounding
access
panels.
(2.) Togainaccessto aft elevatorcontrolsconsistingof hardwarecontrollingelevatorfromaft
sector,removelastlargeaccesspanelson eithersideof fuselage,tail cone,andbullet
assembly.
(b) Beforerigginganypartof elevatorcontrolsystem,setelevatorin neutralposition(± 1°) and
installriggingtool (P/N72046)andriggingpinsin aftfuselagesector,belowfin andsector,
underpilotseat(Figure502). Installriggingtooon left handstabilizer.
(c) Rigcontrolcablesto specifications
in Figure501,orfollowingstep,if autopilotis installed.
Ensurebothriggingpinsarein placewithoutcarryinga loadandclampsectorsor blockcables.
EFFECTIVITY:
040-999
Jan 10/90 27-30-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
9. Riggingthe ElevatorControlSystem(continued)
(d) Sinceautopilotbridlesaffectprimarycabletension,do notreadjustprimaryelevatorcable
tensions.Proceedasfollows:
(1.) Settensionto 55 ± 5 pounds.Hookupbridle.
(2.) Tensionautopilotbridlecablesusingmanufacturer
servicemanuals.Primaryelevator
cabletensionincreasesdownstream
of bridleanddecreases
upstream.
(3.) Recordtensionupstream
anddownstream
of autopilotbridlecablehookupfor later
verification.
(4.) Duringverification,
ensuretensionupstream
anddownstream
of autopilotbridlecable
hookupsarewithin± 5 poundsof previously
recordedvalues.
(e) Adjustpushrodin finto bringelevatorto neutral 1°.
(f) Removeriggingpinsfromsectorsandadjuststops(Figure503)at elevatorto obtainvalues
specifiedin Figure501.
NOTE:Alltravelsaretakenfromtailingedgeof controlsurface.
(g) Adjustpushrodgoingfromfrontsectorto controlcolumnfor 1.50± 0.12inchclearance
betweencolumnandinstrument
panelwhencolumnis fullforward.
(h) Checksystemtravelforsmoothoperation.
(i) Adjusttrimwheelin cockpitfor neutralwithelevatortabin neutral.
(j) Withelevatorin neutral,rotatetrimcontrolwheelin cockpitto obtainupanddowntabtravels
andminimumtrimcabletensionspecifiedin Figure501.
(k) Removeriggingtool. Installaccesscovers.
10. Elevator
ControlSystemFrictionCheck
CAUTION: DO NOT EXCEED60 POUNDSDURINGTHE FOLLOWINGPROCESS.IF SCALE
READINGAPPROACHESTHIS VALUE,STOPAND CHECKSYSTEMFOR
BINDING. ENSUREALL RIGGINGPINSARE REMOVED.
(a) Attachspringscaleto inboardtrailingedgeof elevator(Figure601).
(b) Withspringscaleattached,positionelevatortrailingedge2 inchesdownfromneutralposition.
NOTE:Toobtaineffectivereadingon springscale,rotateelevatorwithfirmandsteady
movement,
recordingforcereadingaselevatorpassesthruneutralposition.Do not
stoprotationwhiletakingreadingor exceed60 poundsof forcefor any measurement.
(c) Raiseelevatorwithattachedscalefromitsdownpositionto 2 inchesaboveneutralandrecord
forcerequiredto raiseelevator.
(d) Lowerelevatorwith attachedscalefrom2 inchup positionto 2 inchdownpositionandrecord
force.
(e) Repeatsteps(c) and(d)untilaverageforceis attained.
(f) Subtracttwoaverageforcesto verifytotalfrictionin system.Totalfrictionin elevatorcontrol
systemmustnotexceed10poundswithoutautopilotsysteminstalledor 11poundswith
autopilotsysteminstalled.
EFFECTIVITY:
27-30-00
27-30-00
PAGE
9
'
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
Elevator
ElevatorSystemFrictionCheck
Figure601
11. EvevatorTrim System
trimtabmountedon the leftelevator,a trimtab
Theelevatortrim systemconsistsof an adjustable
actuatormountedto the stabilizerrearspar,a controlwheelanddrummountedin thecockpit
trimcontrolcableandpulleys.
controlpedestal,andaccompanying
NOTE: Kit No. 764411Lis availablefor modificationof the trim actuatorto reducefriction and for
installationof an environmentalenclosurearoundtrim actuatorpreventingwater entry.
12. Removalof ForwardElevatorTrimSystem(Figure401)
seatsas necessary.
(a) Removepilotandcopilotseatsandrightsidepassenger
(b) Removefloorpanelaftof pedestal,thoseunderandleftof copilotseat,rightsidepassenger
to reachrequiredcablesandhardware,andrightsidefloor
seats,floorpanelsnecessary
panelson twoaft cargodecks.
(c) Blockforwardtrimcablesat leftsetof pulleysandunderpedestal.Blockaftcablesat aft drum
on stabilator(referto 27-00-00,Figure2).
anddisconnectcablesat
(d) Markonesetof cableendsat F.S.65.0to facilitateinstallation
tumbuckles.
(e) Removecableguardpinsat F.S.125.0and243.5.
(f) Removeone screwfromeachsetof rubblocksat F.S.140.0,162.0,174.0,and215.0. Open
themenoughto allowcableendsto passthrough.
(g) Slidebushingup shaftto separatetwohalvesof trimscrewassembly.
to mountingbracket.Drawassemblywith cablesfrom
(h) Removeboltsattachingscrewassembly
fuselage.
EFFECTIVITY:
040-999
PAGE10
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
13. Installation
of ForwardElevatorTrimSystem(Figure401)
(a) Ensurecableis evenlywrappedon trimdrum(centered)andblockedto preventunwrapping.
(Referto Wrapping
theTrimDrum.)
(b) Positionforwardtrimscrewon leftsideof mountingbracketbelowpedestalat F.S.100.0.
(c) Drawcablesaftthroughfuselage,backto F.S.65.0.
connectcableends. (If cablesfromelevatorare not
(d) If trimcablesfromelevatorare installed,
installed,pullcablestightandblockthemin fuselageat bulkhead274.0.)
installcableguardpinsat F.S.125.0and F.S.243.5.
(e) WithcablesInstalledandconnected,
Closeandsecurerubblocksat F.S.140.0,162.0,174.0,and215.0.
(f) Removecableblocks.
F.S.220.0.(Checkriggingof elevatortrim
(g) Setcabletensionwithturbucklesat approximately
forriggingandadjustments.)
(h) Installandsealaccessplatesandpanels.Installbulletassemblyon verticalstabilizerand
installseats.
14. Removal
of Aft ElevatorTrimActuator
fromstabilizerto gainaccessto actuatorassembly.
(a) Removetopandbottomcoverassemblies
to trim
(b) Removecotterpins,nuts,washers,andboltssecuringtwotrimtab rodassemblies
actuator.
(c) Removeelevator(referto 55-20-00,Removalof Elevator).Blocktrimcablesto actuator
(Figure402).
to gain
(d) Removeseats,cabinets,andcarpetat F.S.215.00to F.S.251.00.Removefloorboard
accessto rightsidefloorboard.
(e) Blocktrimcablesat aft sideof bulkheadlocatedat F.S.235.35(Figure402).
cablesat tumbuckles.
anddisconnect
(f) Markonesetof cableendsto facilitateinstallation
Attachleaderlinesto cableends.
(g) Removebulletassemblyfromtopof verticalstabilizerandelevatortrimcablepulleyaccess
panelson topandbottomof horizontal
stabilizer(B.L.36.10).
(h) Removetail coneassembly
to gainaccessto elevatortrimcablepulley,locatedon aft sideof
bulkheadat F.S.368.00.
(i) Removeaccesspanelon rightsideof rearfuselageat F.S.339.50.
418.00,andtwo
(j) Removecableguidepinsfrompulleysat F.S.280.00,332.00,344.31,368.94,
stabilizerat B.L.34.40and36.98.Removerub blocksat F.S.251.00.
pulleysin horizontal
stabilizer.
(k) Drawcablesaft throughfuselage,tail,andhorizontal
fromtrimcables.
(I) Markleaderlinesto facilitateinstallation.Disconnect
stabilizerrearspar;removeactuator.
(m)Removesixboltssecuringtrimactuatorto horizontal
EFFECTIVITY:
27-30-00 Jan
Jan10/9
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
15. Installation
of AftElevatorTrimActuator
NOTE: CompletetheInspection
of aft elevatortrimactuatorbeforeinstalling.
in Wrappingof TrimDrums).Block
(a) Ensurecableis properlywrappedon drum(explained
cablesto preventunraveling.
(b) Positiontrimactuatoron mountingbracket(L.B.L.42.84).Securewith 6 boltsandwashers.
(c) Attachleaderlinesto cableends. Infuselageat F.S.215.00,drawcablesthroughhorizontal
stabilizer,verticalfin, andfuselage.Removeleaderlinesandconnectcableendsto
turnbuckle.
appropriate
verticalfin, andfuselage.Installrub
(d) Installcableguidepinsat pulleysin horizontalstabilizer,
blocksat F.S.251.00.
(e) Removecableblocksfromcableat trimactuatorandaft sideof bulkheadat F.S. 235.35.
(f) Installelevator(referto 55-20-00,Installation
of Elevator).
bolts,washers,nuts,andcotter
to trimactuatorwithappropriate
(g) Attachtrimtabrod assemblies
pins.
(h) Adjustcabletensionandtrimtabtravelusingspecification
in Figure501.
16. Riggingof ElevatorTrim
(a) Completethe followingsteps during installationor as a preadjustmentcheckto adjust elevator
trim:
(1.) Removeaccesspanelson leftandrightsideof fuselageaft of pressurebulkheadat F.S.
339.50,accesspanelson verticalfin, andbulletassemblyon verticalstabilizer.Carefully
removeaccesspanelin controlpedestalfloor.
(2.) Ensuretrimcablesareproperlywrapped.
to specifications
in Figure501.
(3.) Ensuretrimcabletensionisset according
bushings
are at midpointof slots.
to anti-rotation
(4.) Ensureactuatingscrewsarepositioned
(b) Rotatetrimcontrolwheelin cockpitto full noseup position.Ensuretumbuckleterminaldoes
notstrikepulley.
NOTE: If turnbuckle
terminaldoesstrikecenterpulleybeforeactuatingscrewsareat their
trimtab rodsand rotatescrewsin drumsuntilscrewsare at stops
stops,disconnect
to backoff
beforeterminalof tumbucklestrikescenterpulley.It maybe necessary
bushings.
trimwheelto reinstalltrimtabrodsandanti-rotation
withelevatorsin neutral.
(c) Adjusttrimtabrodssotabsareproperlypositioned
NOTE: Rigelevatorswithelevatorsin neutral(pinnedat aft sector)andensureRHelevator
trailingedgeis alignedwith LHelevatortrailingedge.Adjustlengthof trimtabfor 0.12
on inboardtrailingedgeof tab.
± 0.12inchtrailingedgeup fromRHtab,as measured
(d) Checkrodendsfor properthreadengagement.
(e) Withelevatorriggingtool (P/N72046)installedon leftstabilizerandelevatorin neutral,rotate
trimwheelin cockpitfortabtravelsspecifiedin Figure501.
trimwheelindicatorwithtabposition.
(f) Coordinate
(g) Usetool L73035anda dialtorquewrenchto checktrim systemfrictionat pedestalbyremoving
trimwheelandattachingtoolandtorquewrenchto splinedshaft. Frictionmustnotexceed9
inch-pounds
whentestedin eitherdirection,at anypointbetweenlimits.
EFFECTIVITY:
040-999
PAGE
12 27-30-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
TrimSystemFrictionCheck
17. Elevator
(a) Removeelevatortrimcontrolwheelfromelevatortrimactuatorshaftin controlpedestal(Figure
601).
(b) AttachPACtool number73035anda dialtorquewrenchto splinedshaftof elevatortrim
actuator.
(c) Moveelevatortrimactuatorto itstravellimits,in bothup andthedowndirections,usingtorque
whentestedin eitherdirection,at anypoint
wrench.Frictionmustnotexceed9 inch-pounds
betweenlimits.
at any
(d) Locateproblemarea. Repairor replacedefectivepartsif frictionexceeds9 inch-pounds
point.
18. FreePlayCheckof ElevatorTabs
(a) Ensuretrimtabis in neutral.
(b) Ensuretotaltabfreeplay,withtabneutral,doesnotexceed0.126inchmaximummeasuredat
tabtrailingedge.
19. Inspectionof Aft ElevatorTrim Actuator
(a) Ensurebearingsinstalledin trimdrummovefreely.
(b) Ensureendplayon trimdrumis 0.001to 0.003inch. Useoneofthe followingmethodsto
ensureproperendplay:
(1.) Placewasher49981-9,orwasher59486-2,-3, or-4, as required,betweenbearingand
drum.
shim70153-2,as required,betweentrimdrumandtrimdrumbracket.
(2.) Placelaminated
betweenactuatorframe. Trimdrumbracketguide
(c) Ensure0.01inchminimumlooseness
assembly.
(60°Fto 850 F) doesnotexceed1.5
(d) Ensureforcerequiredto actuateunitat roomtemperature
stroke.At -40°F,these
forceor 1 poundpullon eithercablethroughout
poundsbreak-out
forcesmustnotexceed4.5poundsand3 pounds,respectively.
20. TrimSystems'Controlsand Indicators
Thetrimcontrolsfor aileron,rudder,andelevatortrimsystemsaremountedin thecontrolpedestal.
to cabledrumsbyshaftswithailerontrimdrum
Theaileronandruddertrimcontrolsareconnected
platemountedunderpedestal.The
on
a
channel
drum
trim
rudder
and
pedestal,
mountedin
controlassemblyandmustbe removed
elevator
to
directly
mounted
elevatortrimcontroldrumis
alongwiththe assembly.
21. Removalof Trim Controls (Figure402)
(a) Removeflushheadsetscrewretainingcontrolknoborwheelto splinedshaft. Carefullypull
wheel/knob
fromshaft.
(b) Removeandinstallelevatortrimcontrolasfollows:
(1.) Removecontrolwheelandremovesixretainingscrewsholdingindicatorplateto the
controlhubassembly.
in paragraph
andpullforwardcablesystemthroughaircraft(described
(2.) Block,disconnect,
on Removalof the ForwardElevatorTrimSystem).Removefourmountingscrewsand
pullcontrolassemblyfromcontrolpedestal.
(3.) Reinstall,in reverseorder,ensuringindicatoris alignedproperly.
EFFECTIVITY:
040-999
PAGE
13
27-30-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
21. Removalof TrimControls(continued)
(c) Removeandinstalltheaileronandruddertrimcontrolmechanism
asfollows:
(1.) Removepilotseatandtwoaccessplateson sideof pedestal.
(2.) Removeclevispinconnecting
controlmechanism
shaftto universaljoint.
(3.) Withcontrolwheelremoved,unscrewthreeindicatorretainingscrews.Removeindicator.
(4.) Removemountingscrewsandpullassemblyfrompedestal.
(5.) Reinstallremovedassemblyin reverseorder,ensuringindicatoris alignedin neutral.
22. Installation
of TrimControls(Figure402)
(a) Instalationof aileronandruddertrimcontrolmechanism
asfollows:
(1.) Installremovedassembly,
ensuringindicatoris alignedin neutral.
(2.) Layassemblyintopedestalandinstallmountingscrews.
(3.) Withcontrolwheelremoved,installthethreeindicatorretainingscrews,installingindicator.
(4.) Installclevispinconnecting
controlmechanism
shaftto universaljoint.
(5.) Installpilotseatandtwoaccessplateson sideof pedestal.
(b) Installelevatortrimcontrolasfollows:
(1.) Installindicator,ensuringindicatoris alignedproperly.
(2.) Installfourmountingscrewsandlaylcontrolassemblyintocontrolpedestal.Pullforward
cablesystemthroughaircraft,connect,and
block (described
in paragraphon Removalof
the ForwardElevatorTrimSystem).
(3.) Installsixretainingscrewsholdingindicatorplateto thecontrolhubassembly.Install
controlwheel.
(c) Carefullyplace wheel/knobonto shaft. Installflush head set screwretainingcontrol knobor
wheel to splined shaft.
23. Adjustment
of TrimIndicators
(a) Ensureindicatormechanismmovesfreely and is properlylubricatedaccordingto Lubrication
Charts in 12-20-00.
(b) Maintaintrim tabs at controlsurfacesin neutral.
(c) Ensuretrim drums are at neutral positions.
(d) Proceedas follows if trim indicatorsare not alignedwith neutral markeron pedestal:
(1.) Removetrimcontrolwheelfromshaft.
(2.) Loosenthreescrewsholdingindicatordiscsto indicatormechanism.
(3.) Rotatediscsrightor leftto alignneutralpositionof discswithmarkeron pedestal.
(4.) Tightenthreescrews.Replacetrimcontrolwheel.
NOTE: For ELEVATORBALANCINGPROCEDURE,refer to 55-20-00.
EFFECTIVITY:
PAGE14
Jan10/9027-30-00
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
RudderTrim
Control
NOTE: Safetywirerollpinthroughshaft.
Snugtie offagainstshaftusingcautionto
avoidinterference
withmechanism.
TrimPositionIndicator
Gear-
TrimControlInstallation
Figure402
EFFECTIVITY:
040-999
2727-3O
30-00PAGE
15
-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
24. StallWarning/Recognition
System
Thestallindicatingsystemin thePA-42-720
containstwo,identicalsafeflightSC-200stall
recognition
systems,independent
of eachother,power,or aircraftconfiguration.
Eachsystem,one
for thepilottheotherforthe copilot,usesa heatedwingmountedlifttransducer,
a remotelift
computer,a stallwarninghorn,a stallrecognition
horn,a lightedplacard,anda testswitch.
Theelectro-mechanical
lifttransducer,
mountedto the lowerleadingedgeofthewing,sensesthe
existingpositionof the leadingedgestagnation
pointthroughthespringloadedvane. The
appropriate
signalissentto thecomputersowhenthevaneisforcedaft,thestallwarninghornis
activated,andwhenthevaneis forcedforward,thestallrecognition
hornandlightedplacardare
activated.
Thelift computeris locatedin theavionicsbay,forwardof FuselageStation57.0pressure
bulkhead.Signalsfromthetransducerareconditioned
bythecomputerwhichactivatesthestall
warningor recognition
systemthrougha two-leveloutput.A selfmonitoring
circuitin thecomputer
activatesa warninglightif anyessentialinternalor externalpoweris lost.
Thestallwarningsystemcontainsa separatehornanda lightedplacard.Thestallrecognition
horn,alsomountedinthe headliner,
emitsa loud,pulsatingtonedifferentthanthe stallor gear
warninghorns. Thelightedplacard(STALL),
mountedin theedgeof theglareshield,
is keyed
simultaneously
withtherecognition
horn.
A singletest switchis mountedon the instrument
panelbelowthefirewarninglight/switches.
On
theground,activationof theswitchbypassesthe rightgearsquatswitch,turnson thecomputer,
andslewsthetransducervaneupward.Thisprovidesthe necessary
signalsto activatethe horns
andlightedplacard.If theswitchis activatedin flight,thecomputersensesthe inabilityofthe low
controlvoltageto movethevaneagainsttherelativewind,andit generatesa simulated
signal
activatingthesystems.
25. StallWarningFunctionTest
Establish28 Vdc on essentialbuss. Ensurestall warning,stall warningheat, "q"sensor,
annunciator,and annunciatormalfunctioncircuit breakersare pushedin.
26. StallWarningSystemSelfTest
(a) Activatestallwarningtestswitchon lowerleftinstrument
panel.
(b) Ensurelift transducervane,locatedin leadingedgeof outboardliftwing,movesforwardand
stallwarningandstallrecognition(stallwarningannunciator)
activate.Releasetest switch.
CAUTION: STALLWARN HEATMUSTBE OFF.
(c) Manuallymove lift transducerforward (up). Ensurehorn and lightdo not operate.
(1.) Withlifttransducerheldforward,placeleft maingearsquatswitchto IN-FLIGHT
position.
Ensurestallwarningandstall recognition
activate.
(2.) Releaseleft maingearsquatswitchandlifttransducer
vane.
(d) Performsametest for right wing installation.
(e) Activate left and right pitot/stallheat switcheslocatedon overheadswitch panel.
(1.) Ensurelifttransducervaneandmountingplateon bothwingsbecomewarmandensure
stallheatindicator(blue)locatedon upperportionof theleftcircuitprotectionpanel
illuminates.
CAUTION: DO NOT ACTIVATEQOVERRIDESWITCH.
(2.) Turn off both pitot and stall heat switches.
PAGE 16
27-30-00
Jan10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ElevatorandTab (continued)
27. ForceApplicator
KitTest
The lift computeradjustmentpotentiometersarefactory setto nominalvaluesfor activatingthe
pre-stallhorn, and the stall recognitionlight and horn. Actualvaluesfor these settingshavebeen
determinedduringflight test of the aircraftand are recordedin the aircraftflight logbookat the time
of certification.
Uponreplacementof the lift computeror lift transducer,the computersettingsmustbe adjusted,if
different,to the logbookvalues. To makethese adjustments,use Safe FlightInstruments
CorporationForceApplicationKit (P/N1952-3)as follows;
(a) Attachpositionbracketto lift transducercavity.
(b) Attachpropergaugeto positionerfor each of the nexttwo setups.
(c) Checktip gramsetting at which the pre-stallwarningoccurs. If differentthan the logbook
valve,adjust screw#1 (undertop coverof lift computer)for propervalue of tip grams.
(d) Checktip gramsetting at which the pre-stallrecognitionlight and horn activates. If different
than the logbookvalue, adjustscrew#2 (undertop coverof lift computer)for propervalueof tip
grams.
(e) Removeforce applicationkit.
(f) Reinstallall panels removedfor this test.
EFFECTIVITY:
040-999
27-30-00PAGE
Nov1/90
17
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps
1. Description
andOperation
The wing flap control systemprovidescontinuouscontroland monitoringof flap positionand
conditionover its full range. In additionto limitingboth up and down overtravel,the systemwill
shut off the driving mechanismin the eventof a 5° differentialbetweenright and left flap position,
and will self-monitorand react appropriatelyduringa critical componentfailure in the control
circuitry.
Preselectionof any desiredflap positionfrom full up (0° ) to full down (30° ) is possibleby
a frictiontypedragbraketo holdthe
the selectorcontrol.Theselectorincorporates
positioning
position,aswellasballlockdetenteat 0°,10° , and30° of flap
leverat anydesiredintermediate
by a singlemotordrivethruflexibleshaftsconnected
extension.Flapsaredeployedmechanically
to individual
ballscrewactuators.
Selectionof flap positionmovesthe controlrheostatrelativeto the leftwing flap rheostat,with a
resultantamplifieroutput whichoperatesflap motorthroughcontactorsK1 and K2, and movesthe
left and right flaps to the desiredposition. If at anytime,the amplifiersensesa differentialvoltage
in excessof 0.5 Vdc betweenleft wing rheostatand rightwing rheostat,the amplifierwill shut the
systemoff. This conditioncorrespondsto a maximumdifferentialof 5° of flap position.
A flap faulttest switch is providedto checkcontrolcircuitryfor asymmetricalflap protection,as well
as operationof the fault lamp switchingtransistor. Activationof this switch,while flaps are in
motion,gives a false signalto the right side followerpotentiometer,simulatingan out-of-sync
conditionand causingthe amplifierto shutthe systemoff and illuminatethe fault light. Releaseof
the switchclearsthe simulatedfault and allowsthe systemto respondnormallyto selectorposition
command.
2. Removal
of Flap
(a) Lowerflap within a few degreesof full extension.
(b) At leftflap, disconnectpositionsenderrod by removingcotter pin from forwardend of rod.
(c) Disconnectflap controltubes at flap. Do not rotatecontroltubes unlessto adjust flap.
(d) Removeupper roller assembliesfromflap brackets.
(e) Removelower rollerassembliesand removeflap.
3. Installation
of Flap
on flapbracketsandtorquebolts.
(a) Placeflap in position.Installlowerrollerassemblies
andtorquebolts.
(b) Installupperrollerassemblies
NOTE: With all rollersinstalled,but no actuatorhook-up,flap mustfree fall (dropfrom its own
weight),withoutbinding,throughits normalrange(0° to 30° down)from any point in
this range.
(c) Connectcontroltube.
(d) If leftflap was removed,connectpositionsenderrod.
(e) Checkflap for properoperation,riggingand adjustment.
EFFECTIVITY:
040-999
PAGE1
27-50-00 Jan
Jan
10/90
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps (continued)
VIEW B
- FWD
DOWN
FWDUP
LIMIT
SWITCH
VIEW C
VIEWD
A
A
A
B
C
D
Wing Flap Installation
Figure 401
EFFECTIVITY:
040-999
Jan
10/90
27-50-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps (continued)
4
Removalof Flap ActuatorMotor (Figure 402)
(a) Removecenterfloor panel in maincabin area. The flap actuatormotoris locatedon forward
side of bulkheadstation 174.00.
(b) Disconnectelectricalleads from motor.
(c) Cut safetywire and disconnectflexibledrive shaft endsfrom motor.
(d) Removeclamp holding motorunits mountingbracket. Removemotor.
(e) Replaceshockgrommetsfrom bulkheadby removingmotorwith mountingbracketfrom
bulkhead.
5. Installationof Flap ActuatorMotor (Figure 402)
(a) Installshockgrommetsin bulkheadat F.S. 174.00.
(b) Installflap actuatormotorand bracket,if previouslyremoved,on forwardside of bulkhead.
Ensureanti-rotationpin on motorfits in mountingbracketpinhole. Secureholdingclamp.
(c) Connectflexibledrive shaft endsto motor,attachnut finger tight, and securewith MS20995C41 safetywire.
(d) Connectelectricalleads.
(e) Checkflap riggingand adjustments(Figure 502).
(f) Installaccessplates and panels.
6. Removalof FlexibleActuatorShaft(Figure 402)
(a) Removethe centerfloor panel locatedin the maincabin area.
(b) Removethe right or left rowof seats and floor panelsaft of the main spar.
(c) Removethe aft access plateon the fairinglocated on the undersidebetweenthe fuselage and
wing.
(d) Removethe accessplates at the aft side of the wheelwell at wing stations40.00, 47.00, and
56.00, on the undersideof the wing at W.S. 34.50, 42.50, 82.75 and 92.50, and on the false
sparat W.S.42.50, 53.00, 92.50 and 101.00.
(e) Cutthe safetywire and disconnectthe shaftfrom the actuatormotorand flap transmission.
(f) Removethe supportclamp on the fuselagebulkheadand the supportgrommetswithinthe wing
andfuselage.
(g) Removethe actuatorshaft.
7. Installationof FlexibleActuatorShaft(Figure 402)
(a) Drawthe shaftthroughthe wing into the fuselage.
(b) Connectthe flexible drive shafts to the transmissions. Ensure that the splines are properly
engagedand run the shaft attachingnuts on finger tight. Safety the nuts with MS20995-C41
safetywire.
(c) Checkthe flap riggingand adjustments.
(d) Installthe accessplates,panels,clamps,grommets,and seats.
EFFECTIVITY:
040-999
27-50-00
27-50-00
PAGE3
10/90
Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
DownLmitSwitch
Potentiometer
Linkage
AmplifierAdjustmentand Test Points
ControlPotentiometer
Diagram
FlapSystemFunctional
Figure 1
PAGE 4 27-50-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
Right
Transmission
Assembly
ShaftAssembly
SelectorSwitch
Indicator,FlapPosition
Motor
LeftTransmission
Assembly
Bolt AN3-4A
FlapPosition
WasherAN960-1 L
GrommentMS35489-33 Sender
Nut MS20365-1032C
Postion
Sender
Assembly
Motor
SKETCH A
Assembly
SKETCH B
Flap SystemInstallation
Figure 402
EFFECTIVITY:
040-999
27-50-00
PAGE
Jan
10/90 5
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps(continued)
8. Removalof FlapTransmissions
(referto Figure1)
(a) Lowertheflap andremovetheaccessplateon theaft undersideof the wingandthefalsespar
area,bothof whichare atW.S.92.50and42.50.
(b) Disconnect
thetransmission
tubefromtheflaphornbracket.
(c) Removethe safetywireanddisconnect
theflexibleactuatorshaft.
(d) Removethe spreaderbushingand washersfrom betweenthe transmissionattachment
brackets.
(e) Removethe transmission
from its mountingbracketsanddrawthe unit throughthe access
openingin the wingfalsespar.
9. Installation
of FlapTransmissions
(referto Figure1)
Determinethat the correctflap transmission
assemblies
are beinginstalledby checkingthe part
numberson the assemblieswith informationIn the latest PA-42-720
(AdvancedTrainer)Parts
Catalog.
(a) Lubricatetheflap transmission
assemblyin accordance
withlubrication
chart,12-20-00.
(b) Insertthe transmissionthroughthe accessopeningin the wingfalse spar and attachto its
mountingbrackets.Toallowthetransmission
to rotate,tightentheattachment
bolts(onlyfinger
tight)andsafety.
(c) Installthe spreaderbushingwith one washerbetweeneachmountingbracketand bushing.
Installthethroughbolt andsecure.
(d) If workingwith the left transmission,connectthe flexible actuatorshaft and safetywith
MS20995C41
safetywire. Attachthe rightflexibleshaftduringriggingandadjustment.
(e) Safetywire(MS20995-C20)
protectivecapon outboardtransmission.
(f) Checktheflap riggingandadjustment.
(g) Installaccessplates.
10. Disassembly
of FlapTransmission(Referto Figure2)
CAUTION: CALCOFLAPTRANSMISSIONDISASSEMBLYANDASSEMBLYPROCEDURE
ARE INCLUDEDIN THIS MAINTENANCEMANUALFOR INSPECTION
PURPOSESONLY.CALCODOES NOT RECOMMENDOVERHAULIN THE
FIELD.
(a) Removesafetywire,bolts andrearhousing.
(b) RemoveO-ring.
(c) Straighten
tangon lockwasher
so thatlocknutandlockwirecanbe removed.
(d) Removeballscrewandtubeassembly.
(e) Removebearingassemblyandshim.
(f) Removewormgear,keyandshim.
(g) Removefrontbearingassemblyfromhousing.
(h) Removeprotectivecap if used.
(i) Removescrewsandbothoutputflanges.
(j) Pushwormshaftandbearingsoutof housing.
(k) RemoveO-ringfromhousing.
(I) Bumperwasheris attachedto the housingwithLocktiteadhesive.UseLocktitesolvent,if
necessary
to removewasher.
(m)Removesafetywire,screws,andwiperblockandwiperfromballscrewandtubeassembly.
(n) Placea containerortrayunderthe ballscrewandtubeassemblyandremovethetwoscrews
securingthe ballreturntubeto the ballnut.
EFFECTIVITY:
040-999
Jan 10/90 27-50-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
of FlapTransmission(continued)
10. Disassembly
CAUTION: DO NOT ATTEMPTTO REMOVETHE OUTPUTTUBE FROMTHE BALLNUT.
THE OUTPUTTUBE IS FORM ROLLEDTO THE BALLNUT DURING
MANUFACTUREAND MUSTBE SERVICEDAS AN ASSEMBLY.
(o) Carefullyremovetheballreturntubeandseparatethetwohalfsallowingthesteelballsto drop
intoacontainer.Turnthe ballnutoverandrotatethe ballscrewuntilall steelballs(67- 69
total)havedroppedout,allowingtheballscrewto be removedfromtheballnut.
(Referto Figure2)
of FlapTransmission
11. Assembly
(a) Assembleballscrewandtubeassemblyasfollows:
to entirethreadof ballscrew.
No.7 grease,or equivalent
(1.) Applyathincoatof Aeroshell
assembly.
tube
output
and
(2.) Insertballscrewpartwayintoballnut
(3.) Layonehalfof ballreturntubeflaton a tableandfill groovewithsteelballs. Placethe
balls.
otherhalfoftheballreturntubeon theassembled
NOTE: A lightcoatof AeroshellNo.7 or equivalentmaybe usedto holdtheballsin
place.
CAUTION: DO NOT ALLOWTHE BALLSTO ROLLOUT EITHEREND OF THE BALL
NUT.
(4.) Inserttheremainingsteelballsintotheballnutbyplacingthemin oneof thehalesand
turningthe ballshaftuntilalltheballsarein place.
(5.) Carefullyinstalltheballreturntubeontotheballnutandsecurewitclampandtwoscrews.
to the ballreturntubeto
or equivalent
Applya coatof DowComing732RTVadhesive,
sealexternalopenings.
of 20%AeroshellNo.7 greaseand80%MobileJetII Oilor an
(6.) Applya lubricantconsisting
Installwiperandwiperblockontotheballnutandsecure
wiper.
equivalentmixture,to the
with screws.
(7.) Safetywire (MS20995-C20)the screwson the ball nut.
andattachto housingwith athinfilmof
or equivalent
(b) Cleanbumperwasherwithchlorothane,
equivalent.
or
adhesive,
Locktite495
fromC.E.F.
and7801-T3canbe purchased
NOTE:Specialtools,P/n7801-T1,7801-T2
Road,Addison,Illinois
423Interstate
Industries,
(c) Inserttoolfixture77801-T1and7801-T2intowormshaftbearingbores. Insertpinthroughtool
withdepthgaugefrom
fixturesandbearingbores(referto Figure501). Takemeasurement
of pin andrecord
diameter
1/2
add
pin,
of
milledsurfaceof housingto outsidediameter(O.D.)
thisdimension(Z dimension).Removetoolfixtures.
(d) InstallnewO-ringsin wormshaftboreof housing.Applya thinfilmor 20%AeroshellNo.7
to O-rings.
greaseand80%MobilJet II Oillubricant,orequivalent
(e) Insertwormshaftinto housing.
(f) Insertbothballbearingsintohousing,makingsurebearingsareseated.
(g) Attachoneoutputflangeandsecurewithfourscrews.Onoppositesideattachoutputflange
withtwoscrews.Usinga dialindicator,checkendplayof wormshaftandaddshimas required
to obtain0.004to 0.010inchendplay. Securewith fourscrews.
(h) Inserttool7801-T3ontosplineofwormshaftandcheckthatshafttorquedoesnotexceed12
inches.
(i) Insertfrontbearingassemblyintofronthousingassembly.
NOTE: Shoulderof bearingisto be pressedintobumperwasher.
EFFECTIVITY:
040-999
PAGE
7
27-50-00
27-50-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps (continued)
11.Assemblyof FlapTransmission
(continued)
(j) Takemeasurement
frommilledsurfaceof housingto innerraceY dimension.SubtractZ
dimensiontakenin first measurement
fromY dimension(referto Figure501).
(k) Measurewidthof wormgearface. TakehalethethicknessandsubtractthisfromA dimension
obtainedin secondmeasurement.
Subtract0.001/0.002
inchfromresults.Thisis theshim
thicknessrequired(referto Figure501).
(l) Placeshimovertopof frontbearing.Placewormgearovershim,shoulderendup.
(m)Takemeasurement
frommilledsurfaceof housingto shoulderof wormgearW dimension(refer
to Figure501). Measurewidthof rearbearingK dimension.Subtractthetwomeasurements.
Subtract0.001/0.002
fromresults.Thisistheshimrequired.
NOTE: Do notinstalltheshimat thistime.
(n) Applyapproximately
1/8oz.of lubrication
consisting
of 20%AeroshellNo.7 greaseand80%
MobilJet II Oil,or equivalentmixture,to wormshaftandwormgear. Rotatewormshaftwhile
applying.
(o) Installball screwand tube assemblythroughbearingand worm gear in front housingand line
up keyways.
NOTE: Keepwormgearandwormshaftin meshwhileinserting.
(p) Insert key in keyway.
(q) Place shim,previouslydeterminedon top of worm gear.
(r) Place rear bearing,flange side up, in housing.
(s) Place lockwasher over ball screw. Threadlocknut(chamferedside down)onto screw.
CAUTION: MAKESURE BALL NUT ANDTUBE ASSEMBLYIS POSITIONEDAWAYFROM
HOUSINGBEFORETIGHTENINGLOCKNUT.
(t) Tightenlocknutto a torqueof 80 in. lbs.minimumto alignlockwashertangwithslotin nut.
Bendtanginto slot.
CAUTION: MAKESURE THATNO CHIPSARE FORMEDDURINGTIGHTENINGOF NUT.
(u) Aftertighteningnut,measuredistancefrommilledsurfaceof housingto outerraceof rear
bearing.Readingshouldbe between0.001/0.004
inch.
(v) PlaceO-ringintoO-ringgroovein housing.Installrearhousingandattachwithbolts. Tighten
boltsto a torqueof 35-40in. lbs.
EFFECTIVITY:
PAGE8
27-50-00
27-50-00
Jan10/90
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Flaps (continued)
Pin
0.328"O.D.
PinDia.
divide by 2 = 0.164"
(0.328"ref)
X
+0.164"
(Z) Firstreading
First Measurement
NOTE:Shouldread0.750"(ref)
(A)Secondreading
Front
Bearing
Bearing
SecondMeasurement
Third Measurement
Flap TransmissionMeasurements
Figure 501 (Sheet1 of 2)
EFFECTIVITY:
040-999
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps (continued)
FrontBearing
RearBearing
Measurerearbearing
"K"width,subtractfrom
dimension"W"
Subtract0.001/0.002" W
for shimrequirement -K
ANS
WormGear
FourthMeasurement
FlapTransmission
Measurements
Figure501(Sheet2 of 2)
Jan 10/90
275000
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
12. Serviceand Inspectionof Flap TransmissionInternalComponents(CALCO)
CAUTION: ALL DEFECTIVEOR WORN PARTSMUSTBE REPLACEDWITH NEW PARTS.
DO NOT ATTEMPTTO REPAIRDEFECTIVEPARTS.
(a) Washall disassembledparts in a suitabledry cleaningsolvent.
(b) Thoroughlyclean off old sealantand adhesive.
(c) Dryparts thoroughlyusing low pressurecompressedair,or wipe dry with a clean, lint-free
cloth.
(d) Examineall partsfor cracks,burrsand corrosion.
(e) Visuallyinspectballs and groovesin ball screwfor pitting, scoring,corrosionand flat spots.
NOTE: If any one part of the ball screwand/ortube assemblyappeardefective,the entireball
screwand tube assemblymustbe replaced.
(f) Discardand replaceall bearings,O-rings, wipersand bumperwasher.
(g) Inspectworm shaftand worm gearand wormshaftfor excessivewear. If wormgear is worn
morethan 0.015 inch the wormgear and worm shaftmustbe replacedas a set. (Referto
Figure602)
13. Inspectionof OutboardWing Flap Transmission(referto Figure601)
The flap transmissionsare inspectedat the first 500 hour inspectioncycle of the aircraft and each
100 hours thereafter. This is accomplishedwithout removalof the transmissionsby the following
procedures:
(a) Positionthe flaps in the extendedposition(DOWN).
(b) Removethe accesscovers on the lowerwing surfaceto gain accessto the flap transmissions.
(c) With the use of vise grip pliers, grip the exposed portion of the set screw close to the
transmissionas shown(referto views A and B).
(d) Gently move the pliers from side to side and measurethe amountof movementwith a 6 inch
ruler (see view B).
(e) Shouldthe dimensionexceed0.300 inch, replacethe transmissionassembly.
(f) Installthe accesspanels and makeappropriatelogbookentry.
(g) Continueinspectionat 100 hour intervals.
.30 Max
FWD
ViseGripPliers
ViseGripPliers
Transmission
Screw
FigureA
FigureB
Wing FlapTransmissionInspection
Figure 601
EFFECTIVITY:
27-50-00Jan
Jan10/90
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps (continued)
14. Inspection
of InboardWingFlapTransmission
This inspectionis performedat the sametimethe outboardwingflap transmission
inspectionis
performed.
Toperforminboardwingflaptransmission
inspection,
proceedasfollows:
(a) Usingappropriate
tools,checkandrecordflap positionat full up andfull downpositions.
(b) Extendflapsto full downposition.
(1.) Pullflap motorcontrolcircuitbreaker.Removepower(GPU,etc)fromaircraft.
(2.) Removeaccesspanelsto flaptransmissions.
(3.) Removenut,washer,andbolt fromboth inboardandoutboardflap transmissions
at flap
attachhornon rightflap.
(4.) Removenut retainingthe potentiometerarm and free arm from flap on the left flap.
Removenut.washer,andboltfrominboardandoutboardflaptransmission.9.Inspection
of IntboardWingFlapTransmission
(continued)
(c) Gently lower flaps by hand to their fully extendedposition. Ensurethat the right flap
potentiometer
armstraightens
outsmoothly.
(d) Mark outboardflap transmissionsand take care that housingis not movedin or out from
originalposition.
(e) Turninboardflap transmission
housingoutto its full extension.Keeptrackof the numberof
turnsto ensureturninghousingbackto originalposition.
(f) Attachlockingpliersto inboardtransmission
screwjack.Donotforcepliers.
(1.) Placea six-inchrulerperpendicular
to bottomwingskin.
(2.) Measurefreeplay from center of flap transmissiondown (approximately3 inches).
Freeplaymustnotexceed0.180inches.
(g) Turninboardflaptransmission
housingin numberof turnspreviously
counted.
(1.) Raiserightflap until bolt holesin inboardandoutboardflap transmissions
alignwith bolt
holesin flaphorn. Ensurethatflappotentiometer
armretractsproperly.
(2.) Greasetransmission
boltswithsmallamountof generalgrease. Installbothtransmission
bolts.washers.andnuts,andsafetyallwithcotterpins.
(3.) Performsteps a and b for the left flap. Whentransmissionsare connected,connect
potentiometer
armto flapandtightennut.
(h) Usingthe flap riggingtool, checkvalue in full down position. Valueshould matchvalue
determined
in step(a).
(i) Lubricatescrewjacksper 12-20-00in maintenance
manual.
(j) Installaccesscoversonwings.
(k) Checkthatflaphandleisin fulldownposition.
(I) Resetflapcontrolcircuitbreakerandturnmasterswitchon.Flapsshouldremainstationary.
NOTE: Flap motor may surge for one second if down limit switch was movedor not
completely
contacted.
(m)Whilehavingsomeoneoutsidetheaircraftto watch,raisetheflapsin smallincrements
untilthe
flaps arein full up position.Ensurethatbothflapsraisein a consistent
manner.
(n) Checkdegreeof flapsin full position.Ensurethat measurement
matchesmeasurement
in
step(a)
EFFECTIVITY:
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040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Flaps (continued)
MeasureStep
in tooth form
Checkingfor WornGear Wear
Figure 602
15. Removalof Flap Control Box (Selector)
(a) Removethe knobfrom the controlbox.
(b) Removethe electricalconnectorfrom the rear side of the controlbox.
(c) Removethe two screwsthat securethe controlbox to the instrumentpanel.
(d) Removethe controlbox from the instrumentpanel.
16. Installationof Flap ControlBox
(a) Installthe flap controlbox in the instrumentpanel.
(b) Installthe two screwsthat securethe controlbox.
(c) Connectthe electricalleads.
(d) Installthe knob.
17. Removalof Flap ControlAmplifier
(a) Openaccessdoor in noseof airplaneto gainaccessto amplifierat F.S.25.60.
(b) Disconnectthe electricalplug fromthe amplifier.
(c) Removethe attachingscrewsand removethe amplifierfrom the airplane.
18. Installationof Flap ControlAmplifier
(a) Installcontrolamplifierin airplaneand securewith attachingscrews.
(b) Connectthe electricalplugto the amplifier.
(c) Check riggingand adjustmentof flaps.
(d) Close and secureaccessdoor.
EFFECTIVITY:
040-999
27-50-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
19. Riggingand Adjustmentof Flaps
The riggingprocedurefor this wing flap systemis both mechanicaland electricaland requiresthat
the landinggear be raisedor squat switchesin the left maingear be madeto the in-flightposition.
The controlsystem,in additionto providingproportionalpreselect,also incorporatescircuitryfor
systemshut-downin the eventof any asymmetricalflap conditionof five degrees,and controlof
flap transmissionstroke lengthin both extendand retractpositions. The main componentsof the
control systemare: a controlamplifierthat suppliesvoltagefor and receivessignalsfrom three
separatereostatsused in the system. Two of three reostatsare linked(one to the left and one to
the right) wing flap assembliesin such a manoras to senseflap position. The third rheostatis
locatedin the wing flap positionselectorand is the controlfor flap positioning. The following
abbreviationsare used in descriptionand serviceinformationpresentedin the following
paragraphs:
RC- Control PotentiometerWiperat Selector.
RL- Left Wing Flap PotentiometerWiper.
RR- RightWing Flap PotentiometerWiper.
A VCL-Voltagedifferencefrom (RL to RC - .10).X2 in the up position.
A VCR-Voltagedifferencefrom (RC to RR - .10) x 2 in the up position.
Required Equipment
DigitalVoltmeter(10 milliampScale)
Rig Boardflap tools (P/N71505-16and 71505-17)
Work Sheet(Figure 603)
WARNING: ALL ADJUSTMENTSMUSTBE MADEWITH MOTORPOWEROFF.
All adjustmentsare madewith motorcircuit breakerpulled OFF and flaps in DOWNposition.
Adjustmentproceduresrequirespecialequipmentsuch as a digitalvoltmeterand flap riggingtool
(P/N 71505-16and -17).
CAUTION: ELECTRICALPOWERTO SYSTEMMUST BE OFF. PULLFLAP CONTROLAND
MOTORCIRCUITBREAKERS,SET BATTERYMASTERSWITCHOFF,AND
DISCONNECTEXTERNALPOWER.
The control potentiometeroperatedby the flap selectoris referredto throughoutthe rigging
procedureas RC (potentiometercontrol). The wing flap potentiometersare designatedas RL
(potentiometerleft) and RR (potentiometerright). The voltagesat the centertaps are referredto
as VC, VL, and VR respectively.
Properoperationafter riggingrequirespotentiometerRL on the left flap must respondto changes
in flap positionselector potentiometerRC in VL and VC. Amountof stroketravel and how it is
centeredwith respectto ends is determinedby how RL is adjustedrelativeto RC. Since VC is
fixed and cannotbe changed,trimmerpot RT2,providedin the controlamplifier,allows adjustment
of VL to agreewith VC.
Throughoutadjustmentprocedures,whateverchangesare made to RL and RT2mustalso be
madeto RRand RT3. RRtracks RL over entire strokerange and shuts systemoff if VL and VR
outputs deviateby morethan 0.5 volts. Thisvoltagedifferentialcorrespondsto a five-degree
asymmetricalflap condition. RR also providesa voltage inputto the controlamplifierto give an
output to the flap positionindicator.
NOTE: Adjustments
of RL,RR,RT2,andRT3are alwaysmadewithflapsdown. Themagnitude
of theseadjustments,
basedon valuesof VC,VL,andVR,aremeasuredwithflapsup.
EFFECTIVITY:
14
PAGE
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040-999
PIPER AIRGRAW
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Flaps (continued)
19. Riggingand Adjustmentof Flaps (continued)
Cut through the
disc and socketto
permit it to slide
over the pot shaft
0.500 AND 0.562
Sockets needed
to cover two size
jam nutson dots
Weld
TOP VIEW
-
Holes
SIDE
0.187 OR 0.250
steel disc
0
Holesdrilledin
discfor small
punch type object
to assist in tightening
the jam nut on pot
Special Socket for Calco Flap Rheoststs
Figure 604
20. Preparationfor Rigging
CAUTION: ELECTRICAL POWER TO FLAP CONTROL SYSTEM MUST BE OFF. PULL
FLAP CONTROL AND MOTOR CIRCUIT BREAKERS, SET BATTERY MASTER
SWITCH OFF, AND DISCONNECT EXTERNAL POWER.
(a) Removeaccess plates in false sparat wing stations42.50, 53.00,92.50, and 101.0 for both
rightand left wings.
(b) Removeaccess plates on bottom sideof wingsat wing stations34.50,42.50, 82.75, and 92.50.
(c) Ensureflap positionsenderarms rotatefreelyon potentiometershafts,with linkagerods set at
properlength (Figure 502, Sketch B).
(d) Withtransmissionassembliesnot attachedto flap and turned into ball nut seat,ensure flaps
are free to roll full travel (0° to 30° ) on flap tracks.
(e) Attachflap riggingtools to wing station147.50to measureflap deflectionangles.
EFFECTIVITY:
040-999
15
2750-00PAGE
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Flaps (continued)
ACTUATORARM
SKETCH B
TOOL P/N 71505-16, LH
TOOL P/N 71505-17, RH
SKETCH A
Flap Rigging
Figure 502
EFFECTIVITY:
040-999
Feb1/98 27-50-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Flaps (continued)
21. MechanicalRiggingProcedure
(a) Adjust up limit actuatingbolt by manuallymovingleftflap so switch is actuatedwith flaptrailing
edgeat 0° on riggingtools.
°
°
(b) Manuallymoveleft flap to full down (30 + 1 - 0°) positionon riggingtool. Turn transmission
sleevesout from forwardstops, recordnumberof turns, align attachmenthole in sleeves,with
holes in respectiveflap horns,and temporarilyinstallattachmentbolt. Adjust down limit
actuatingboltto actuateswitch.
NOTE: Differencein numberof turns betweeninboardand outboardtransmissionsmustnot
exceed 1/2 turn.
(c) Turn right flap transmissionsleevesout from forwardstops (usingequal numberof turns used
for leftflap transmissionsleeves),alignattachmentholein sleeveswith holes in respectiveflap
horns,and temporarilyinstallattachmentbolt.
(d) Ensureproperalignmentof sleeveand flap horn. If sleeveand horn do not align, loosenbolts
attachinghornto flap, and tap horn to achieveproperalignment. Retorquehorn attachment
bolts.
(e) With sleeveand horn properlyaligned,connectsleeveto horn with bolt and castellatednut.
Tightennut to allow 0.03 inch bolt thrustplay. Installcotter pin.
(f) Connectflexibledrive shaftsto transmissions.Ensuresplinesare properlyengagedand install
shaftattachingnut finger tight. Safetywith MS20995-C32wire.
22. ElectricalRiggingProcedure
(a) Removecoversfrom RT2and RT3on flap controlamplifier. Ensureboth trimmersare
positionedfully clockwise. Insert30 amp fuse (for test purposesonly) in flap motorelectrical
powerconnection.
(b) Apply externalpowerto aircraftand establishbusvoltageof 28 ± 0.5 volts.
(c) Placeflap selectorin DOWNposition.
(d) Engageflap controlcircuitbreaker,but do not engageflap motorcircuitbreaker. Allowfive
minutewarm-uptime.(Flapshouldstill be downfrom mechanicalrigging)
(e) Insert"PLUS"test leadfrom digitalvoltmeter,into RCtest point on controllerand "MINUS"test
leadinto RL. Adjust shaftof left wing potentiometerfor a readingof + 0.10 v. and lock actuator
armto pot shaft.Be sure that voltagehas not changedwhile lockingactuatorarm. (Record
voltageon work sheet.)
(f) Move"MINUS"test lead to RRtest pointand adjustright wing pot. to +0.10v. Lock actuator
armto pot. shaft. Checkthat voltagedoes not changewhile lockingactuatorarm. ( Record
voltageon work sheet)
NOTE: All measurementsmust be takenat controlamplifier.
(g) Depress(but do not engage)motorcircuitbreakerand moveflap selectorto UP; ensureflap
motoris wired correctly(flapsmoveup). If not, reversewiring; if correct,engagebreaker.
NOTE: If flaps will not moveto full up position,hooka jumper betweenRL and RR. When
flaps are up removejumper.
(h) Withflaps in full up position,ensure .010 minimumclearancebetweenactuatorsleevesand
rubberseals.
EFFECTIVITY:
040-999
PAGE 17
17
27-50-00 PAGE
Feb 1/98
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Flaps (continued)
22. Electrical RiggingProcedure(continued)
(i) With DVM "PLUS"lead in RC and "MINUS"lead in RL, measureRC/RLvoltage. This voltage
must be negative;if not, trimmersRT2and Rt3 were not fully adjustedcw in step (a).
(j) Usingthe work sheet,performthe followingcalculation: Changethe magnitudeof rc/rl by
0.10v and multiplythe remainderbe 2. The resultis definedas A VCL.
(k) Move "MINUS"leadto RR and repeatstep (j) for A VCR.
(I) Move flap selectordownand disengagemotor breaker.
(m) With DVM "PLUS"lead in RC and "MINUS"in RL, checkthat voltage has not changedfrom
that in step (e) (If voltage haschangedby more than 0.03V,repeatthe entire proceduretasking
specialcare when lockingactuatorarm to pot. shaft.)
(n) Adjust RT2so that RC/RLvoltagechangesby the amountof the A VCL Calculatedin step (i) then, adjust RL pot. shaftso that RC/RLchangesin the oppositedirectionby A VCL. RC/RL
voltage will now be the same as measuredin step (m).
(o) Move "MINUS"leadto RR and checkthat RC/RRvoltagehas not changedfrom that in step (f).
(p) Adjust RT3so that RC/RRvoltagechangesby the amountof A VCR calculatedin step (j) then, adjust RRpot. shaftso that RC/RRchangesin the oppositedirectionby A VCR. RC/RR
voltagewill now be the sameas measuredin step(o).
(q) Engageflap motorbreakerand moveflaps to UP.
(r) MeasureRC/RLas in step (h). Voltagemust be -0.05Vminimumand -0.15Vmaximum.
(s) MeasureRC/RR. Voltagemustbe -0.05Vminimumand -0.15Vmaximum.
(t) Moveflaps to the DOWNposition.
(u) MeasureRC/RL. Voltagemustbe +0.05Vminimumand +0.30V maximum.
(v) MeasureRC/RR. Voltagemustbe +0.05Vminimumand +0.30Vmaximum.
NOTE: If the requirementsof steps (q) and (t) are not met, repeatthe procedurefrom step (g)
withoutpre-settingRT2and RT3. The calculatedA VCL and A VCR will be smaller
and the entire riggingprocedurewill be easierwith each repetition.
(w) Insert DVMtest leads into RL and RR. Moveflaps UP and DOWNWhile observingvoltage
readingon DVM. The readingmust not exceed± 0.10V
(x) Run flaps throughfull cycle threetimes to ensure properoperation.
(y) Measureflap deflectionat full down (30 ± 1°) and approach(10 + 1°) positionon both leftand
right hand side.
(z) Check positionindicatorreadingsagainstflap selectorand flap deflectionas follows:
(1.) When measuringflap deflectionangles,lift flaptrailingedge to eliminateplay between
rollersand trackslot. If indicatordoes not correspondto flap position,placeflaps in
APPROACHposition.
(2.) Adjustflap indicatortrimmer,locatedon inboardend of flap amplifierbox (opposite
connectorend), so flap indicatorneedlefalls in center of approachgraduation.
(3.) Checklocationof flap indicatorneedlein UP and DOWNpositionsand adjust trimmerso
needlecenterlinefalls withinor tangentto upperand lower edge of graduationin UP,
APPROACH,and DOWNpositions.
NOTE: If trimmeris rotatedto raiseneedle,needlemust risean equalamountin all three
positions.
(4.) If unableto adjust indicatorneedlefor properindication(as in examplebelow),proceed
with steps (a.) thru (e.) below:
PAGE 18
27-50-00
Jan 10/90
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Flaps (continued)
22. ElectricalRiggingProcedure (continued)
EXAMPLE
Flap Position
NeedleIndicator
UP
APPROACH
DOWN
Centerof Graduation
Centerof Graduation
Below DOWNGraduation
(a.) Adjust indicatortrimmerso flap indicatorneedleis at uppertangentof graduationat
UP and APPROACHpositions.
(b.) Adjust RT3 so needlefalls with downgraduation.
(c.) Recheckindicatorat UP,APPROACH,and DOWNpositions. Readjusttrimmeras
required.
(d.) RecheckVLR and readjustas necessary.RT2could require readjustment.
(e.) EnsureVL and VR are stillwithin limitsof VC specifiedand ensurepositionindicator
agreeswith flap positionin UP,APPROACH,and DOWNpositions.
(aa) Locateflap systemtest switch on lower instrumentpanel. Moveflap selector handleto
approachposition,activatetest switch,and ensurewing flap cautionlight, locatedin
annunciatorpanel, illuminatesand flap travel stops. Releasetest switch and checkflaps for
properopperation.
(bb) Remove30 amp fuse installedin step (a). Installall accessplates and panels.
EFFECTIVITY:
040-999
27-50-00PAGE
19
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
FLAPRIGGINGWORKSHEET
FLAPSDOWN
FLAPS UP
STEP 1.
RC (+) to RL (-)
+
V
STEP 2.
RC (+)to RR (-)
+
V
STEP3.
RC (+) to RL (-) VOLTAGE -
V
( CHANGEBY )
V
(MULTIPLY)
x2
V
VCL=
STEP4.
V
RC (+) to RR (-) VOLTAGE
V
( CHANGEBY )
V
(MULTIPLY)
x2
-
VCR =
FLAPSDOWN
STEP5.
V
( SAMEAS STEP 1. ± 0.03)V
STEP6.
±
ADD VCL (STEP 2. )
ADJUSTRT2 POT.TO
CHECK
ADJUSTRL SHAFT
STEP7.
RC/RLVOLTAGE
STEP8.
+
±
±
ADD VCR (STEP 4. )
ADJUSTRT3 POT.TO
CHECK
ADJUSTRR SHAFT
RR/RCVOLTAGE
+
Flap RiggingWork Sheet
Figure 603
EFFECTIVITY:
040-999
Jan 10/90 27-50-00
Jan 10/90 27-50-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Flaps (continued)
23. ElectricalSystem FunctionalTest Procedure
NOTE: All J1 connectionsare airframeconn E410and K1 and K2 relaysare airframesupplied
reversingrelays.
(a) Place left enginebus tie switch,right enginebustie switch, and non-essentialbus tie switch in
OFF position. Pull all essentialbus circuitbreakersto OUTposition.
(b) Actuateflap motorand flap controlcircuitbreakers.
(c) Turn on battery master switchor connectexternalpowerto aircraft.
(d) Operateflap selectorhandlein controlbox. Observeup and down operationof wing flaps.
(e) Checkfault light if wing flaps fail to operate. If fault light is on, proceedto step (m). If fault light
is off, proceedto step (f).
(f) Ensure27.5 volts exist at motorcontactorand pin 1 of connectorJ1 (airframeconn E410)to
verify circuitbreakersandwiring are installedproperly.
(g) Checkfor 27.5 volts acrosspowerterminalsof both K1 and K2 (reversing)relays.
(h) Disconnectflex shafts from motor assembly.
(i) Removeelectricalharnessplugfrom connectorJ1 and ground relay K1 at pin 6 of connectoror
relay K2 at pin 4 of connector. Apply 27.5 volts to drive motorbe energizingup and down
relaysK1 and K2 locally.
(j) If drivemotor fails to operate,checkup and down limit switchesin 27.5 volt leg of coilsfor
relaysK1 and K2 for 27.5 volts at NCcontactson limit switches.
(k) Check27.5 volt powerat drive motorswhile an assistantenergizesrelays K1 and K2. If 27.5
volts does not exist at drivemotor,contactsof relays K1 or K2 are defective. Replacedefective
relays. If drive motor operateswhen energizingrelays K1 and K2 locally,problemexistsin
eithercontrol box, left wing potentiometerRL,right wing potentiometerRR,or in flap control
amplifier.
(I) Reconnectflex shaftsto motorassembly.Connectelectricalharnessplugto connectorJ1.
(m) Pull flap motor circuit breakerto preventflap motorfrom runningremainderof test procedure.
(n) Usingprecisionvoltmeter(10 volt range),connect negativelead to amplifier,and test jack
amplifierand positiveleadto RC testjack. Slowlyoperateflap selectorhandlein controlbox
through entire range. Voltagereadingsmustbe approximately9-volts in DOWNpositionand
approximately4-volts in UP position.
(o) If RCvoltage readingsare too highor too low,problemexists in either harnesswiringor control
box. Wring out harnesswiring and repairor replace,if defective. Replacecontrolboxonly if
harnesswiring is functional.
(p) Connectvoltmeterbetweentest jacksRR and RL on amplifier. If voltage exceeds0.5 volts,
shut down is due to flap asymmetry.Correctcauseof asymmetryand rerigflap system.
(q) Connectvoltmeterbetweentest jacksRR and GND on amplifier. Voltagemustbe within0.3
volts of RC voltage.
(r) Connectvoltmeterbetweentest jacks RL and GND on amplifier. Voltagemustbe within 0.3
volts of RC voltage.
(s) If voltage readingsin eitherstep (q)or (r) exceeds0.3 volts,shut down is still due to flap
asymmetry.Correctcauseof asymmetryand rerigflap system.
(t) If problemis not found, replaceamplifier.
(u) Turn battery master switchOFF or removeexternalpowerfrom aircraft.
EFFECTIVITY:
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER28
LISTOF EFFECTIVEPAGES
CHAPTER
SECTION
28-EFFECTIVITY
28-CONTENTS
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LISTOF EFFECTIVE
PAGESJan 1090
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER28 - FUEL
TABLEOF CONTENTS
SUBJECT
CHAPTER
PAGE
28-00-00
General
DescriptionandOperation
1
1
28-10-00
Storage
DescriptionandOperation
Fuel Vent System
Fault Isolation
Handlingand Storageof Fuel Cells
Fuel Cell Replacement
Removalof WingTip Tanks
Installationof WingTip Tanks
Removalof WingFuel Cells
MoldedNippleFittings
Installationof Inboard,Aft Inboard,and
OutboardFuelCells
Testingof Fuel Cells
Inspectionof Fuel Cells
Cleaningof FuelCells
Repairof Fuel Cells
Handlingof RepairMaterials
Repair Limitationsof Fuel Cells
Repair Patch (HeatCure Method)
Repair Patch (AirCure Method)
Repair Patch (QuickCure Method)
SealingMetalSurfaceFittings
Fuel Cell AccessoryReplacement
Repair of FuelCell Defects
1
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28-20-00
Distribution
DescriptionandOperation
Fuel Valves
Fuel Filter
Fuel Jet Pumps
Fault Isolation- Fuel System
Overhaulof FuelShutoffValves
ServicingJet ScavengerPump
Removalof FuelValves
Installationof FuelValves
Removalof FuelFilter Screen
Installationof Fuel Filter Screen
Installationof Fuel Filter
Removalof Jet TransferPump
Installationof Jet TransferPump
1
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EFFECTIVITY:
040-999
CONTENTSJaGE1
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER28 - FUEL
TABLEOF CONTENTS(continued)
SUBJECT
CHAPTER
PAGE
28-20-00
Distribution(continued)
Removalof SubmergedFuel Pump
Installationlof SubmergedFuel Pump
Adjustmentof Fuel Shutoffand
CrossfeedValve
LeakageTestof Fuel Shutoffand
CrossfeedValve
Fuel Flow and PressureTest
Jet PumpFlow Check
Cleaningof Fuel FilterScreen
10
10
11
12
12
14
15
28-40-00
Indicating
Descriptionand Operation
Fuel QuantityIndicatingSystem
AutomaticFuel PumpSystem
Fault Isolation- Fuel System
Overhaulof Tank SensorUnits
Overhaulof Fuel QuantityIndicator
Removalof Tank Sensor Units
Installationof Tank SensorUnits
Fuel QuantitySystemCalibrationTests
and Adjustments
Testof AutomaticFuel PumpSystem
1
1
1
1
3
5
5
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6
7
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EFFECTIVITY:
040-999
Jan 10/90CONTENTS
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Fuel
andOperation
A. Description
fuelsystems(referto 28-00-00Figure1) in eachwingforeach
containsindividual
ThePA-42-720
engine. Eachstandardfuel systemconsistsof a wingtip tank,threebladdertypetanks,anda nacelle
tankwhichprovide281gallonsoffuelfor eachengine.
byfeedandventlines,andincorporate
Thefuel vesselswithineachwingare interconnected
on eachsideto an individual
typeprobesin eachcell. Thefuelprobesareinterconnected
capacitance
indicatoron a commondualdisplaygauge,andgivea linearresponsefor eachindicator'scombined
flame
andnon-icingvents,incorporating
system.Toventthefuelsystems,twoNACAnon-siphoning
arrestorsareinstalledundereachwing.
Thecontrolsregulatingfuelflow,otherthanenginecontrols(startcontrolleverandpowercontrol
controlled
andfuel shutoffvalves,bothofwhichare manually
lever),areusedto controlthecrossfeed
left
side
of the
on
the
is
located
valve
The
crossfeed
fromthefuelcontrolpanelwithinthecockpit.
2)).
The
Figure
to
28-20-00
andleftenginemainfeedlines(refer
aircraftattachedtothe crossfeed
plates.
spar
reinforcement
fuel shutoffvalvesare in bothmainfeedlinesandmountedto front
fuelpump,main
Fuelis deliveredto eachenginefromthatwing'smainfueltankthrougha submerged
fuel
controlunit
pump,
and
supply
fuel
driven
main
engine
filter,
the
fuel
shutoff
valve,
feedline,fuel
main
inboardfuel
in
the
located
fuel
pump,
The
submerged
pump.
driven
engine
containinganother
backupto the enginedrivenpump,and
cellof eachwing,functionsasa primerpump,an emergency
fuel.A fuelfilter,mountedon thelefthandside(facingforward)of each
transfersandcrossfeeds
whenthefilterispartially
anda pressureswitchwhichdetermines
firewall,consistsof a filterassembly
bypasswarning.Themainenginedriven
cloggedandwill soonbypass.Thisis a requiredimpending
sectionofthe engineon a dual
fuelsupplypumpis an enginedrivenpumpmountedon theaccessory
drivepadwhichalsodrivesa hydraulicpump.
in eachfuelsystem,controlsventingof fuel intothe
A jet typescavengepump,incorporated
duringan engineshutdown.A jet pumpisactivatedwheneverfuelpressureexistsand
atmosphere
in idleshutoff.Duringstart,fuel is returnedto thetankbythejet pump
theconditionleveris positioned
to purgeanyvaporfromthefuelcontrolunitfuelpump.
Fueltankdrainsareprovidedatfuelcellortanklowpoints. Fuelfilters,mountedon theforwardside
of eachfirewall,alsocontaindrainvalves.Quickdefueldrains,locatedat W.S.112.90on eachwing,
areprovidedto rapidlydraintheleftandrightfuelsystemwith siphonpumps.Thesiphonpumps
attachto thedrainwithan adapterhose.
EFFECTIVITY:
28-00-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Description and Operation (continued)
FuelManifold
Fuel
Crossfeed Valve
SenderUnit
Inbd
FuelCell
NOTE: 1. Enginedrivenboostpumpoperatesanytimeenginegasgenerator(N1)
is turningandsuppliesfuelto thefuelcontrolunit.
2. Submergedfuel pumpis usedto operatethejet transferpump,an emergency
backupand for crossfeedoperation.
FuelSystemInstallation
Figure 1
EFFECTIVITY:
040-999
Jan 10/90 28-00-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage
1. Description
andOperation
(a) FuelVentSystem(referto 28-10-00,Figure1)
Themainfuelventlineextendsfromthe upperportionof the nacellefueltank,downthrough
thewing,outto thetiptank. A floatvalveis installedontheendof theventlinein thenacelle
tankto preventfuelfromescapingthroughtheventsystem.Thetwo NACAnon-icingtypevent
assemblies,
installedalongtheventline,arenon-siphoning
andincorporate
flamearrestors.
Thetiptankhasa ventwellassembly
containinga floatvalve,tip relieftube,andthemainvent
lineconnectedto it. Thisventwellis sealedfromthefuelstorageareain thetip tank,except
for thefloatvalveandrelieftube,whichextendsto theforwardtopportionofthetank. Thefloat
valveinstalledin thetip tankventwellpreventsfuelfromescapingthroughtheventline. The
relieftubeallowsthefuel systemto ventduringclimbto altitudewithfullfuelaboardandalso
allowsfuel to escapewhentanksarefull andfuel expansion
occursdueto heat(suchas
aircraftbeingparkedon rampandexposed
to highramptemperatures).
FuelVentSystem
Figure1
EFFECTIVITY:
040-999
28-10-00
1
10/90
28-10-00JanPAGE
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage(continued)
2. Fault Isolation- Fuel System
CHART 1
FAULTISOLATION(FUELSYSTEM)
Fault
Cause
Unidentified
leak.
Fuellinesdamaged
or
improperly
installed.
Locateandrepair.
O-ringsimproperly
installed.
Locateandrepairor tighten.
Tankleak.
Repairleak.
Fullfueltanksandfuel
expansion
dueto exposure
to heat.
Defuelaircraft or park in a shaded
or cooler location.
Floatvalve in nacelletank,
aft inboardtank or float
valve in tip tank sticking
open or leaking.
Defuelaircraft and
inspectvalvesfor
condition.
Fillercapsimproperly
adjustedandnot
sealingproperly.
Adjustfillercapsto obtaintightseal.
Fuel leakingfrom NACA
vents.
Fuelleakingfromfiller
caps.
Remedy
EFFECTIVITY:
PAGE
Jan 10/9028-10-00
2
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage(continued)
3. Handlingand Storageof Fuel Cells
whenhandling
(a) Topreventneedlessdamageto fuelcells,exercisethe followingprecautions
cells:
intoairframecavities.
(1.) Foldor collapsecellsfor storage,transport,or installation
(2.) Useprotectivecoversoverfittingsealto protectsealsurfacefromcontactwithcavities
duringremovalor installation.
(3.) Protectcellsfromtools,hotlights,etc.
(4.) Avoidsteppingon foldsor creases.
(5.) Donotcarrycellsbyfittings.
(6.) Maintainoriginalcellcontours
or foldswhenrefolding.
(7.) Whenrepairing,maintainnaturalcontoursof cells,placeon well-litandwell-ventilated
surfaces,andpreventcontactwithsharpedges,comers,anddirtyfloors.
priorto cellinstallation.
(8.) Inspectcavitiesandensurecleanliness
(9.) Donotstackcells.
WARNING: NO SMOKINGOR OPENFLAMEIS ALLOWEDWHEN REPAIRING
CELLS.
(b) Observethe followingrule when storingcells:
(1.) Cleanusedcellswithsoapandwarmwaterpriorto storage;dryandplacein container.
(2.) Foldcellssmoothlyandlightlyaspossiblewith minimumnumberoffolds. Place
waddingbetweenfolds.
protective
paperandplacein suitablecontainer.Donotcrowdcell in
(3.) Wrapcellin moisture-proof
container.Usewaddingto preventmovement.
(4.) Stackboxedcellsto allowaccessto oldestcellsfirst. Do notallowstacksto crushbottom
boxes. Leavecellsin boxesuntilused.
70°Fandfreeof exposureto sunlight,dirt,and
(5.) Storageareamustbe approximately
damage.
4. FuelCellCompartment
loosewashers,bolts,or nuts.
of allforeignmaterialsuchastrimmings,
(a) Clearcellcompartment
(b) Roundoff anysharpedgesin fuelcellcompartment.
priorto fuelcellinstallation.
(c) Inspectfuel cellcompartment
(d) Tapeover all sharpedgesandroughrivets.
5. Removalof WingTip Tanks (referto 28-10-00 Figure401)
(a) Draintank.
(b) Removefairing betweenwing tip and tip tank.
(c) Removesender unit.
(d) Disconnectelectricalwires to navigationlightsand strobes.
(e) Disconnectall plumbingfrom tip tank. Cover endsto preventfuelcontamination.
(f) Supporttank, removesix bolts holdingtankto the wing and removetank.
EFFECTIVITY:
040-999
28 10-00 JanPAGE
3
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Storage(continued)
BoltAssembly(6 Req.)
TorqueBolt50 to 70 in. lbs.
TipTank
Tip Tank
Assembly
Fitting
lbs.
-Plastic
Tubing
BondingStrap
VIEW A
VIEW B
TipTank Installation
Figure 401 (Sheet 1 of 2)
EFFECTIVITY:
040-999
Jan10/9028-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage(continued)
Adapter
Tip Tank
Skin
Sealant(PR1422- A 2) for
Dome Nut Sealing and
Lightning Protection
SECTIONALVIEW A - A
Cover Plate
Gasket
Tip Tank
Skin
Sealant(PR1422- A 2) for
Dome Nut Sealing and
Lightning Protection
SECTIONALVIEW B - B
NOTE: If necessary,the tip tankdomenutsmaybe sealedby coatingthe entire
surfaceof the nutswithwith PR1422- A 2 sealant.Thedomenutsmust
be coatedwithsealantonthe fuelside as shownabove.Thiswillassure
optimumlightningprotectionforthe tankas wellas a fuelsealfor the nuts.
Tip TankInstallation
Figure 401 (Sheet2 of 2)
EFFECTIVITY:
040-999
28-10-00
PAGE5
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
6. Installation
of WingTipTanks(referto 28-10-00Figure401)
(a) Connecttankto wingbyinstallingsixbolts.
(b) Connectall plumbingto tank.
(c) Installsenderunit andconnectelectricalleadsto navigationlightsandstrobes.
(d) Installfairingbetweenwingtip andtiptank.
7. Removalof WingFuelCells (referto 28-10-00Figures402,403,and404)
(a) Drainbothsystemswhenremoving
cellson bothsides. If onlyonesideis affected,orwhen
replacingor servicingmaininboardfuelcell,closecrossfeedvalveanddrainappropriate
tank
or system.
(b) Removenecessaryaccessplatesonwingto gainaccessto fuelcellandsenders.When
removinginboardmainfuelcell,removeforwardbottomwingrootandfuelcelldrainpanels
andplates.
(c) Inboardandoutboardmainfuelcellsinterconnect,
whereapplicable,
withnacelletank,wing,
andventsystemthroughfittingsmountedin wingskinlocatedundernacelle.Whenremoving
tanks,removetopcenterpanelon nacelleto makeaccessto fittings.Removeboltsattaching
fittingsto wingandall hardware
fromaffectedtank.
(d) Disconnect
wiresfromappropriate
senders,removescrewssecuringeachsenderto fitting,and
carefullywithdrawsenderwithitsgasketfromcell. Notepositionof eachgasketrelativeto
senderunitwhenremoving,
to facilitatereinstallation.
(e) Reachthroughappropriate
accesshole.Loosenanddisconnect
clampsfromnipplesand
interconnecting
tubes.If replacement
of tubesis necessary,
removefromwingby
disconnecting
eachtubegroundstrapfromsparandfromothertank.
(f) On undersideof wing,removescrewsmounting
quickdrainplatesto wing. Carefullydrawtwo
fuel celldrainsoutof wing. (Enoughto allowscrewdriver
to releaseclamps.)
CAUTION: TO PREVENTNYLONFITTINGFROMTURNINGWHENDISCONNECTING
ELECTRICALCONNECTIONON FUELPUMPS,A WRENCHMUSTBE USED
TO BACKUP EACHCONNECTIONON TANK. IF FITTINGTURNS,INTERNAL
WIRECONNECTIONSWILLBREAKAND PUMPMUSTBE REPLACED.
(g) Whenremovinginboardmainfuelcell,removeelectricalconnections
fromfuel pumpin celland
disconnectandcapfuel lines.
(1.) Withdrawpumpfromtankbyremovingfourboltsmountingpumpto tankandwingrib. Lift
pumpthroughaccessholein wing.
CAUTION: DO NOT DAMAGESMALLFLAPPERVALVEIN INTERIORBAFFLE,NEXTTO
FUELPUMPMOUNTINGLOCATIONS,
WHEN REMOVINGMAIN INBOARD
FUELCELLS.
(h) Reachthroughproperaccessholefor eachfuelcell. Untienyloncordsecuringeachcell.
(i) Removeallcap boltsat accessholesattachingcellsto skinbrackets.Pushcelldownandwork
nyloncordbackthroughcellhangersandrib bushingsto endsof cellcompartment.
(j) Removescrewsattachingmountingbracketsto wingskinin eachelongatedaccesshole.
Removebracketsfromholes.
(k) Placetapeor otherprotective
materialaroundcellaccessopening,preventing
damageto cell
duringremoval.
(I) Foldcell neatlyin wing;tapeortie. Removecellgentlythroughelongated
openingon topof
wing.
EFFECTIVITY:
PAGE 6 28-10-00
Jan 10/90
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage (continued)
Gasket
NOTE Lacingin this areato be pulled tight" and "tied off"
aftersenderunit installationhasbeen completed.
Inboard- Main95 GallonFuel Cell
Figure 402
EFFECTIVITY:
040-999
28-10-00
PAGE 7
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
FuelQuanititySensorAssembly
CoverPlate
Outboard40 GallonFuelCell
Figure403
EFFECTIVITY:
040-999
Jan 10/90 28-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage (continued)
FuelQuanititySensorAssembly
Bushing
Assembly
Aft Inboard33 GallonFuel Cell
Figure 404
EFFECTIVITY:
040-999
28-10-00
PAGE9
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage (continued)
8. Molded Nipple Fittings
For best servicefrom this typefitting, exercisethe followingprecautionsat time of installation.
(a) Applythinfilmof SimonizeWaxto metaltubesto facilitateinstallation
andremoval.
(b) Insertfuel linesintoeachnippleuntilendisflushwithinsideedgeof cell.
(c) Ensurehoseclampsclearendof fittingby0.25inch,wherepossible.
(d) Torquehoseclampsonce. Do notretightenunlesshoseclampis loosenedcompletely
and
allowedto setfor 15 minutesbeforeretightening.
(e) Do notusesealingpasteor gasketcompound.
9. Installation
of Inboard,Aft-Inboard,
andOutboardFuelCells (referto 28-10-00Figures402,403,
and404)
(a) Inspectcell compartment.
(b) Do not removecell from shippingcontaineruntil readyfor installation.
(c) Ensurecell is warm enoughto flex. Donot use sharp tools such as screwdrivers,files, etc,for
installationpurposes.
(d) Placetape or protectivematerialover edgesof elongatedaccessopeningto preventdamage
to cell.
(e) Rollcell into propershapeand size to insertthroughaccessopeningcell.
(f) After fitting cell into wing, unrollcell and establishpropersizingof cell to fit compartment.
(g) From eachend of cell compartment,feed cord throughcell hangersand rib bushingsuntil
cordscan be joinedat accessopenings. Do not tie cord but route as shownin 28-10-00
Figures402, 403, and 404.
NOTE: The nyloncord holdingfuel cells has a 0.125 inch diameterwith a minimumbreaking
strengthof 550 poundsand conformsto MIL-T-5040C,Type IIIspecifications.
(h) Connectfueldrainplateby insertingthreadedendof boltor rod(notunderthreeincheslong)
up throughplateandnipplefittingof fuelcell(referto 28-10-00Figure405). Reachthrough
fuel cellopeningandinstall2 or 2 1/2inchdiameterwasheron boltor rod;securewithnut.
Pullnippledownthroughopeningin wingpanelenoughto clampnipplefittingto plate.
(i) Removeboltor rod. Secureplatetowingpanelandinstalldrainvalve.
(j) On inboardmaincell,installsubmerged
fuelpumpthroughaccessopeningin wingtop. Secure
to inboardrib withfourboltsattachingpump.
(k) Connectelectricalwiresto inboardcell,checkvalveon submerged
fuel pump,andconnectfuel
linesto checkvalve.
(I) Installfuelcellflangemountingbracketsin elongatedaccessholeswithscrews.
EFFECTIVITY:
PAGE
10
Jan 10/90 28-10-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage(continued)
Fuel Valve - Drain Plate Installation
Figure 405
(m)Wipeinsideof cellcleanwithclean,soft,lint-freetackcloth;inspectcleanliness.
(n) Toattachfittingsin nacellewingskins,proceedasfollows:
(1.) Iffittingcanbe reachedthroughnearbyaccesshole,holdcellandgasketupagainst
bracketandinsertseveralbolts.
attachment
(2.) Iffittingcannotbe installedasabove,reachdownthroughremovedaccessplateon
nacelle,insertthreadedrodorboltthroughholein wingbracket,downintocorresponding
holein cellnutflangefitting,andpullcellup againstbracket.Installseveralcapboltsto
bolts,andtorqueto 35 ± 5 inchinstallremaining
holdfuelcelluntilrodis removed,
pounds.
(o) Connectfuellinesattachedto outboardendsof fuelcellsanddrainlinerunningfrominboard
endof mainoutboardfuelcellto inboardendof maininboardcell.
tubes
tubesbetweenmaininboardandoutboardfuelcellsby inserting
(p) Connecttwocrossover
intonipplesin eachcellandinstallingclampsfrominsidecell. Torqueclampsto 60 - 65 inchtubesis attachedto spar.
pounds.Ensuregroundstrapon crossover
(q) Installsenders,gaskets(oneoneachsideof bracket),andscrews.Tightennylonscrewsto 5
+2/-0inch-pounds.
(r) Connectsenderwires. Ensureinsulatorsleeveinsulatessowiresattachto sender.Install
senderaccessplates.
of tie cords
(s) Drawnylontiecordstightandhold. (Referto 28-10-00Figure403for positioning
correctlyin cell
onoutboardfuelsenderon mainfuel cell.) Ensurecell is positioned
drawcordtight,holdwithclamporpliers,andtie. (referto 28-10-00Figure
compartment,
406)
cellcoveraccessplateson topof wing. Torquecellcovercapboltsto 25 ± 5
(t) Installremaining
inch-pounds.
fuel.
(u) Checkforfittingleaksin cellby inserting
(v) Installremainingaccessplates,lowerwingrootfairing,andnacelletoppanel.
EFFECTIVITY:
040999
11
28-10-00PAGE
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
Step 1
Step2
Step5
Step 3
Step6
Step 4
Step7
FuelCellThreadingDetail
Figure406
EFFECTIVITY:
PAGE 12
Jan 10/90 28-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
10. Testingof Fuel Cells
NOTE: Eitherof the followingleaktests maybe usedto detect leaksin the bladdercells. The
chemicalleak test is the more sensitiveand preferredtest.
(a) Performthe soapsuds leaktest as follows:
(1.) Attachtest platesto all fittings.
WARNING: DO NOT EXCEED0.25 PSI WHEN INFLATINGFUELCELLS.
(2.) Inflatethe cell with air to a pressureof 0.25 psi maximum.
(3.) Apply a soap and water solutionto all repairedareas suspectedof leakage. Checkfor
bubblesto appearat any pointwhere leakageoccurs.
(4.) After testing,removeall plates and wipe soap residuefrom the exteriorof the cell.
(b) Performchemicaltest as follows:
(1.) Attachtest platesto all but one fitting opening.
crystalsin 1/2 gallon of ethyl alcohol. Add 1/2 gallon of
(2.) Mix 40 grams of Phenolphthalein
water after the crystalshavedissolved.
WARNING: AMMONIAGAS IS GIVENOFF BYAMMONIUMHYDROXIDE.USE
CAUTIONWHENOPENINGTHE CONTAINERAND WHEN USING
AMMONIUMHYDROXIDE.PROVIDEADEQUATEVENTILATIONTO
OF AMMONIABELOWACCEPTABLE
MAINTAINTHE CONCENTRATION
LEVELS.(REFERTO 28-10-00,CHART801.)
(3.) Pour ammoniaas suppliedon an absorbentcloth in the ratio of 3cc (1 teaspoon)per cubic
foot of cell capacity. Place a saturatedcloth insidethe cell and installthe remainingtest
plate.
WARNING: DO NOT EXCEED0.25 PSIWHEN INFLATINGCELL.
(4.) Inflatethe cell with air to a pressureof 0.25 psi maximum. Maintainpressurefor a
minimumof 15 minutes.
(5.) Soak a largeclean white clothin the phenolphthaleinsolution,wring it out thoroughly,and
spread it smoothlyon the outer surfaceof the cell. Pressthe cloth down to ensure
detectionof minuteleaks.
NOTE: Red spotson the cloth will indicateleakage.
(6.) Checkthe cloth for red spotswhich will indicateleak. Mark any leaksfound.
(7.) Repeatstepse. and f. for remainingouter surfaceof fuel cell.
NOTE: Phenolphthaleinsolutionand test cloth canbe reused only if they remainclean.
Storesolutionnot in immediateuse in a closed rust proofcontainerto prevent
evaporationand deterioration.
(8.) Repairfuelcell asnecessary.
(9.) Removeallplatesandtest equipment.Purgecellwithfreshair.
EFFECTIVITY:
28-10-00
28-10-00 Jan
Jan 10/90
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage (continued)
11. Inspectionof Fuel Cells
WARNING: A VAPOR-PROOFLIGHTMUSTBE USED DURINGINSPECTION.
(a) NewCells: Inspectcellsurfaceinsideandoutfor cuts,abraded(scuffed)areas,andaccessory
damage.Alsoinspectfittingsealsfor nicks,scratches,
andforeignmaterial.
(b) UsedCells: Inspectcellsremovedfromairframecavityfor repair,orbeingreturnedto service
for cuts,abraded(scuffed)areas,andaccessory
damageon insideandoutsideof cellsurface.
Reachthroughfuelcell accessplateandtakesectionof cell betweenthumbandforefinger.
WiperidgewithclothsoakedwithMethylethylketone.
Iffinecracksarefound,fuelcell isnot
repairable
andmustbe replaced.
(c) BaffledFuelCells: Conductthefollowinginspection
every2 yearsor after2000hoursin
service,whichever
comesfirst:
(1.) Defuelbothmaincells.
(2.) Removeaccessplateslocatedinboardof nacelle.Removebothwingandfuelcellaccess
plates.
(3.) Inspectfuel cellfittingsfor rubberdeterioration
byusingfingernailto attemptscraping
rubberoff metalor nipplefitting. If rubberis notdeteriorated,
fingernailwillglideacross
rubber.If deterioration,
fingernailwilldig intorubber.Deteriorated
rubberusuallychanges
fromlightyellowishtanto dark,reddishbrowncolor.
(4.) Checktensionandknotsof twonylonsupportcords.
(5.) Inspectinteriorof cellfor bafflesecurityandproperoperationof flappervalve. Inspect
bothsidesof baffle.
(6.) Inspectexteriorof cellsto ensureVelcrotapehasnotseparated
fromcellor linersurfaces.
(7.) Installall accessplatesonfuel cellsandwings. Fillcellsandcheckfor leaks.
NOTE: Referto 28-10-00Repairof FuelCellsforfuelcell repairprocedures.
12. Cleaningof FuelCells
(a) NewCells: Newcellsneednotbe cleanedafterremovalfromcontainers,
if promptlyinstalled
in airframecavities.If cellsarenotinstalledimmediately
andbecomedirty,cleanwithsoap
andwarmwaterpriorto installation
in cleancavity.
(b) UsedCells: Priorto removal,drainfuelfromcells,purgewithfreshair,andswaboutto remove
all tracesof fuel. Followingremoval,cleancellsinsideandoutwithsoapandwater.
EFFECTIVITY:
PAGE14
Jan 10/90
040-999
28-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage (continued)
13. Repairof Fuel Cells
CAUTION: THE REPAIROF LORALVITHANEFUELCELLSSHOULDBE RESTRICTEDTO
AUTHORIZEDPERSONNELWHO HAVEBEENCERTIFIEDAND TRAINEDBY
LORALREPRESENTATIVES,
OR WHO HAVERECEIVEDTHEIRTRAININGFROM
PERSONSWHO HAVEBEENCERTIFIEDANDTRAINEDBY LORAL
REPRESENTATIVES.
NOTE: The followingrepairproceduresare in accordancewith the cell manufacturersrepair
procedure.
The followingare recommendedfield repair proceduresfor fuel cells constructedof LoralBTC - 85
material. Any of three methodsmay be usedfor repairs: heat cure, air cure,or quickcure. All
repairsare neatand permanent. Heat cure repairingallowscells to be cured and readyfor
installationin two hours. Air cure repairingrequiresthat the cell not be movedfor 72 hoursor
longer. Quickcure repairingcan be usedon cells that haveminordamageand can be repairedin
six hours.
14. Handling
of RepairMaterials
CAUTION: REPAIRCEMENTFOR HEATANDAIR CURE REPAIRS(5923C)AND QUICK
CURE REPAIRS(82C32)REQUIRESTHOROUGHMIXINGTO OBTAINFULL
ADHESIVEVALUES.
CAUTION: ALL CONTAINERSFORCEMENTSAND SOLVENTSSHOULDBE PROPERLY
IDENTIFIED.
(a) Protectrepairmaterialsfromdirt, contamination,sunlight.and excessiveheat or cold during
storage. Containersareto be tightlycappedand storedbetween30°F and 85°F temperature.
(b) Mixrepair cementsimmediatelybeforeapplication.
(c) Referto each curingmethodfor pot life of mixedcement.
NOTE: Unmixedrepaircements havea shelf life designatedby Loralon the storage
containers.
EFFECTIVITY:
28-10-00PAGE
Jan 15
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
15. RepairLimitations
of FuelCells
NOTE: FT- 227fabricis usedto repairsimplecontoursonly. All patchesreferredto in repair
procedures
are ofthistype
(a) Lap insidepatchesoverdefectiveedges1.0inchminimumin eachdirection.
(b) Cutoutsidepatchesapproximately
0.25to 0.50inchlargerthaninsidepatches.
(c) Applyoutsidepatchesandallowto curebeforeapplyinginsidepatches
(d) ApplybothoutsideandInsidepatchesfor blistersbetweeninnerlinerandfabriclargerthan
0.25inchin diameter.
(e) Applybothoutsideandinsidepatchesto rerairholesandpunctures.Applybothoutsideand
insidepatchesto repairseperations
betweenouterplieslargerthan1.0inchesin diameter.
NOTE: Slitsortearsarelimitedto 6.0inchesmaximumin length.
(f) Applyoutsidepatchonlyto externalabradedor scuffedareaswithoutfabricdamage.
(g) Trimlooselapsas necessaryprovideda 5.0incheffectivebandremains.
CAUTION: FOR EACH10° DROPIN TEMPERATUREFROM70°F,ADD 20 HOURSCURE
TIME. DO NOT AIR CURE REPAIRSBELOW60°F.
(h) Clamprepairpatcheswhenperforming
aircurerepair.Cureat roomtemperature
of 70°F
undisturbed
for 72 hours.
(i) Limitfittingrepairsto looseflangeedges,sealsurfacerework,andcoatstock.
(j) Donotexceedfourheatcurerepairsin thesamearea.
NOTE: Anydamagenotcoveredbytheabovethecellshouldbe returnedfor repairto: Loral
Engineered
Fabrics,669GoodyearStreet,Rockmart,Georga.30153- 0548.
EFFECTIVITY:
PAGE16
Jan 10/90
28-10-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage (continued)
CHART801
FUEL CELL REPAIREQUIPMENTLISTS (Sheet1 of 2)
RepairKit, LoralPartNo.2F1-3-37813
GROUPI MINIMUMMATERIALS
ITEM/ DESCRIPTION
*5923CCement
(3 component,1/2 pintset.)
FT - 227 Repairfabric
(Sheet, 12 in x 12 in min.)
Methylethylketone(MEK)solvent
(Quartcan)
AP -368 manual
(latest issue)
*Shelf life limitedto one yearfrom date on container.
QUANTITY REQUIRED
8
2
1
1
GROUPII MINIMUMEQUIPMENT
ITEM/ DESCRIPTION
Measuringcup
Releasefilm (cellophane)
Foam rubber,cloth backed
Cementapplicationbrush
Aluminumpressureplate
CQUANTITYREQUIRED
(250 ml.)
(Sheet 6 in. x 24 in. min.)
(Sheet 1/4 in. x 12 in. x 12 in. min.)
(1 in. wide)
(1/4 in. x 6 in. x 6 in. min.)
1
2
2
2
4
GROUPIII MINIMUMLEAKTEST EQUIPMENT
ITEM/ DESCRIPTION
CQUANTITYREQUIRED
Phenolphthalein(analytical
4 btl.
I grade) (40 g in 2 oz bottle)
Ammonia(27%concentrate
1 pt.
(commercialgrade)
e)
Ethyl alcohol
8qt.
(commercialgrade)
Balloonor broadcloth
2 yd.
(white)
1
2F1 - 3 - 35721- 1 heat cure iron
(240°Ftemperaturesetting)
C - clamps
6
(6 inch)
1
Vaperprooflight
(with 25 foot cord)
1
Sheers
(8 to 10 inch long)
Electricmotor
(Blackand DeckerP/N 725, 2250 rpm,
1
1.9 amp, 115VACor equivalent)
Abrasivearmor
(DunemoreR421003,1/4 in. drive,
1
1 in. longx 1 in. dia.,or equivalent.)
6
Sandingsleeve
(80 grit)
2
Abrasivecloth
(120grit in sheets)
2
Abrasivecloth
(320grit in sheets)
1
Scale
(12 inch straightedge)
Manometer
(FisherScientificCo. P/N 11- 286,
1
water or mercury,12 in. long,or equivalent.)
A/R
Closureplates
(fabricatedlocally)
EFFECTIVITY:
28-10-00Jan
PAGE
10/907
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
CHART801
FUELCELL REPAIREQUIPMENTLISTS (Sheet2 of 2)
RepairKit, LoralPart No. 2F1-3-42215
GROUPI MATERIALS
ITEM / DESCRIPTION
QUANTITY REQUIRED
3604N nylonfabric (NSN8135-01-242-3515)3.5 oz
*82C32 CementNSN 8040-01-243-6624(2 componentset)
AP - 472 Manual
(latest issue)
*Shelf life limit 12 months.
2 sq. yds.
9 ea. 1/2 pt.
1 ea.
GROUPII MATERIALS
ITEM / DESCRIPTION
Cement applicationbrush
Scotch Brite pad
Toungedepressor
Curved scissors(4inch long)
China marker
QUANTITYREQUIRED
(1 inch wide)
(6 inch x 9 inch)
(wooden)
(white #164T)
4 ea.
2 ea.
9 ea.
1 pr.
1 ea.
NOTE: All materialsrequiredto performautorizedrepairsare includedin the group I and group II repair
kits exceptfor clean clothsand methylethyketone.Accessories
-Tobe orderedper individualcell
requirements.
NOTE: Order materialand equipmentfrom Aero Hardwareand PartsCo. if not avaialbleorderfrom
Loral EngineeredFabrics.
Aero Hardware& PartsCo.
Loral EngineeredFabrics
1037Boston Post Road
669 GoodyearStreet
Rye, NY 10580.
RockmartGeorga,30153 - 0548
NOTE: Repairfabric and cementcan be purchasedseperatlyby specifyingthe code numberor
nationalstocknumber (NSN)listed above
NOTE: Solventand clean cloth can be purchasedfrom Aero Hardwareor a local supplier.
PAGE18 28-10-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Storage(continued)
16. RepairPatch(HeatCureMethod)
CAUTION: DO NOT APPLYAN OUTSIDEAND INSIDEPATCHSIMULTANEOUSLY.
APPLY
OUTSIDEPATCHFIRST.
(a) Cut a patch from FT - 227 repair fabricto the size requiredto ensure a properlap over the
injuryin all directions.
(1.) Holdshearsat anangleto producea bevelededge(feather)on thepatch.
(2.) Roundcomersof patch.Ensuredullsideor gumcontactfaceof repairpatchisthe
largestsurfaceafterbeveling.
(b) Washone squarefootof cellwallbeyonddamagedareain alldirections.
solvent.
withMethylethylketone
(c) Washcontactsideof patchusinga cleanclothdampened
(d) Centerrepairpatchoverdamagedarea. Markcell0.50inchbeyondpatchin alldirections
CAUTION: BUFFCELL SURFACEWITH CARETO AVOIDFURTHERDAMAGE.
(e) Buffcell surfacesurroundingdamagedarea as markedand contactside of patchwith fine
emerycloth to removegloss.
(f) Washcell and patch surfacestwo moretimes using a clothdampenedwith MEK.
CAUTION: TO PREVENTCEMENTFROMSTICKINGCELL WALLSTOGETHER,ENSURE
CELLOPHANEPLACEDINSIDECELL REMAINSIN PLACE.
(g) Tapea piece of cellophaneinsidethe cell over the injury.
(h) Foldcell so repaircan be completedwithout repositioningcell.
WARNING: CEMENTSAND SOLVENTSARE FLAMMABLE.MIX ANDAPPLYCEMENTIN
WELLVENTILATEDAREA.
WARNING: REPAIRCEMENT5923CSHELFLIFE IS ONE YEAR FROMDATEON
CONTAINER.DO NOT USE OUT DATEDCEMENT.
of 70°F.Potlifeof mixedcementis20
NOTE: Mixandapplycementat minimumtemperature
minutesto onehour.
(i) Mixrepaircement5923Casfollows:
(1.) Shakecontentsof part2.
makingsureentirecontentsof both
(2.) Pourcontentsof part2 intopart1. Stirthoroughly,
containersareareblendedcompletely.
EFFECTIVITY:
28-10-00Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
NOTE: Rapidstirringor shakingwillcauseair bubblesto form. Airbubblesin cementcan
resultin repairvoids,pits,blisters,andleakpaths.
(j) Applyoneevencoatof 5923Ccementon buffedareaof cellto within1/4inchof edgeandon
buffedsideof patch.Allowto dryfor 15 minutes.
CAUTION: COVERCEMENTCONTAINERBETWEENAPPLICATIONSTO MAXIMIZEPOT
LIFE.
(k) Applysecondcoatof 5923Crepaircementto cellandpatch. If cementhasbecometoothick
to brush,mixnewbatchof cement.[Referto step(i).]
(I) Allowcementto dryfor 5 minutes.
(m)Centerrepairpatchoverdamagedarea. Laypatchcarefullyby rollingactionfromcenterof
patchto edgesto preventtrappingair. Whilesurfaceiswet,sliderepairpatchbyhandto
improvelap
CAUTION: BE SURE PIECEOF CELLOPHANEIS LARGERTHAN CEMENTEDAREAAND
REMAINSIN PLACE. ENSUREFILMOBTAINSCOMPLETECOVERAGE.
(n) Tapepieceof cellophaneover patch.
NOTE: Aluminumplates mustbe largerthan patch.
(o) Coveronesideof aluminumplatewith0.25inchfabric-backed
airfoam(fabricsideout). Tape
airfoamintoplace. Ensureairfoamcoversedgesof platefor protection.
(p) Cuttwobackupboardslargerthancementedareaandsmoothall edges.
CAUTION: ENSURECELL IS NOT FOLDEDBETWEENPRESSUREPLATEAND BOARDS
TO PREVENTPERMANENTCREASE.
CAUTION: ENSUREPATCHDOESNOT MOVEWHEN TIGHTENINGCLAMP.
(q) Foldcellnextto patch. Placeplatewithairfoamoverpatch.
(r) Place2F1-3-2572
repairironon centerof plate. Coverironwithotherbackupboard.Secure
assemblyin placewith Cclamp. Wipeoff anyexcesscementthatflowsfrompressureplates.
(s) Connectrepairironto 110/120Vac. Setironto 240°Fandallowto curefor twohours.
(t) Unplugironandallowassembly
to coolto thetouch.
(u) Dissemble
cureiron,plate,andboardsfromcell. Dampencellophane
andremovefromcell.
(v) Checkfor completesealof patchedges.
(1.) Trimlooseedgesif lessthan1/8inch.
(2.) Bondlooseedgeswithcementandcureif morethan1/8/inch.
(w)Repeatsteps(a)thru(v)for insidepatch,exceptcutpatch1/4inchto 1/2inchsmallerthan
outsidepatch.
EFFECTIVITY:
PAGE20
28-10-00
Jan10/90
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
17. RepairPatch(AirCureMethod)
CAUTION: DO NOT APPLYAN OUTSIDEAND INSIDEPATCHSIMULTANEOUSLY.
APPLY
OUTSIDEPATCHFIRST.
NOTE: A minimumof 72 hourscuringtimeat 70°Fis requiredper patch.A minimumof 144
hoursis requiredto installanoutsideandinsidepatch.Add20 hourscuretimefor
below
each10°Fdropintemperature.Neverattemptto air cureat temperatures
60°F.
(a) Cuta patchfromFT- 227repairfabricto thesizerequiredto ensurea properlapoverthe
injuryin all directions.
(1.) Holdshearsat an angleto producea bevelededge(feather)onthepatch.
(2.) Roundcomersof patch.Ensuredullsideor gumcontactfaceof repairpatchis the
largestsurfaceafterbeveling.
areain alldirections.
(b) Washonesquarefootof cellwallbeyonddamaged
solvent.
withMethylethylketone
(c) Washcontactsideof patchusinga cleanclothdampened
area. Markcell0.50inchbeyondpatchin all directions
(d) Centerrepairpatchoverdamaged
CAUTION: BUFFCELL SURFACEWITHCARETO AVOIDFURTHERDAMAGE.
damagedareaasmarkedandcontactsideof patchwithfine
(e) Buffcellsurfacesurrounding
emeryclothto removegloss.
withMEK.
(f) Washcellandpatchsurfacestwomoretimesusinga clothdampened
CAUTION: TO PREVENTCEMENTFROMSTICKINGCELL WALLSTOGETHER,ENSURE
CELLOPHANEPLACEDINSIDECELL REMAINSIN PLACE.
insidethecellovertheinjury.
(g) Tapea pieceof cellophane
cell.
withoutrepositioning
(h) Foldcellso repaircanbe completed
WARNING: CEMENTSAND SOLVENTSARE FLAMMABLE.MIX AND APPLYCEMENTIN
WELL VENTILATEDAREA.
WARNING: REPAIRCEMENT5923CSHELFLIFE IS ONE YEARFROM DATEON
CONTAINER.DO NOT USE OUT DATEDCEMENT.
of 70°F.Potlifeof mixedcementis 20
NOTE: Mixandapplycementat minimumtemperature
minutesto onehour.
(i) Mixrepaircement5923Casfollows:
(1.) Shakecontentsof part2.
makingsureentirecontentsof both
(2.) Pourcontentsof part2 intopart1. Stirthoroughly,
containersareare blendedcompletely.
EFFECTIVITY:
28-10-00Jan
PAGE210/9
10/90
PIPERAIRCRAFT
PA42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
17. RepairPatch(AirCureMethod)(continued)
NOTE: Rapidstirringor shakingwillcauseair bubblesto form. Air bubblesin cementcan
resultin repairvoids,pits,blisters,andleakpaths.
(j) Applyoneevencoatof 5923Ccementonbuffedareaof cellto within1/4inchof edgeandon
buffedsideof patch.Allowto dryfor 15 minutes.
CAUTION: COVERCEMENTCONTAINERBETWEENAPPLICATIONSTO MAXIMIZEPOT
LIFE.
(k) Applysecondcoatof 5923Crepaircementto cellandpatch.If cementhasbecometoothick
to brush,mixnewbatchof cement.[Referto step(i).]
(I) Allowcementto dryfor 5 minutes.
area. Laypatchcarefullyby rollingactionfromcenterof
(m)Centerrepairpatchoverdamaged
patchto edgesto preventtrappingair. Whilesurfaceiswet,sliderepairpatchby handto
improvelap
CAUTION: BE SURE PIECEOF CELLOPHANEIS LARGERTHANCEMENTEDAREAAND
REMAINSIN PLACE. ENSUREFILMOBTAINSCOMPLETECOVERAGE.
(n) Tapepieceof cellophane
overpatch.
NOTE: Aluminumplatesmustbe largerthanpatch.
airfoam(fabricsideout). Tape
(o) Coveronesideof aluminumplatewith0.25inchfabric-backed
airfoamintoplace. Ensureairfoamcoversedgesof platefor protection.
(p) Cuttwobackupboardslargerthancementedareaandsmoothall edges.
CAUTION: ENSURECELL IS NOT FOLDEDBETWEENPRESSUREPLATEAND BOARDS
TO PREVENTPERMANENTCREASE.
CAUTION: ENSUREPATCHDOESNOT MOVEWHENTIGHTENINGCLAMP.
(q) Foldcellnextto patch. Placeplatewithairfoamoverpatch.
(r) Secureassemblyin placewithC clamp.Wipeoff anyexcesscementthatflowsfrompressure
plates.
NOTE: A minimumof 72 hourscuringtimeat 70°Fis requiredperpatch.A minimumof 144
hoursis requiredto installan outsideandinsidepatch.Add20 hourscuretimefor
below
each10°Fdropin temperature.Neverattemptto air cureat temperatures
60°F.
andremovefromcell.
cellophane
(s) Removeplateandboardsfromcell. Dampen
patch
edges.
seal
of
complete
(t) Checkfor
(1.) Trimlooseedgesif lessthan1/8inch.
(2.) Bondlooseedgeswithcementandcureif morethan1/8/inch.
(u) Repeatsteps(a)thru (t)for insidepatch,exceptcutpatch1/4inchto 1/2inchsmallerthan
outsidepatch.
EFFECTIVITY:
28-10-00
10/90
PAGE 28-10-00
Jan
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
18. RepairPatch(QuickCureMethod)
WARNING: REMOVEFUELCELL FROMAIRCRAFTBEFOREPERFORMINGQUICK
CURE METHOD.
CAUTION: USE EITHERHEATCUREOR AIR CURE METHODIF DAMAGEIS WITHIN5/8
INCHFROMOUTSIDEDIAMETEROF METALFITTINGS
(a) Cutrepairpatchfrom3604Nfabricmaterialto sizethatextends1.0inchbeyondinjuryin all
directions
NOTE: It is recommended
thata roundpatch3 inchesin diameterbe used.
WARNING: MEK IS FLAMMABLE.TAKEALL NECESSARYPRE-CAUTIONSTO PREVENT
SERIOUSINJURYTO YOURSELFAND/ORFELLOWWORKERS.
(b) Washfuel cellapproximately
12inchesbeyondinjuryin alldirectionsusinga clothdampened
withMEK.
(c) Centerfabricpatchoverinjury.Markcell0.50inchbeyondpatchin alldirections.
CAUTION: BUFF FUELCELL WITH CARETO PREVENTDAMAGEBEYONDINJURYAND
TO PROTECTCELL FABRICREINFORCEMENT.
(d) Bufffuelcellinsidemarkedareawitha ScotchBriepadorfineemeryclothto remove
gloss/shine
fromcell.
(e) Washbuffedareausinga clean,lintfreeclothdampened
withMEK. Repeatwitha second
cleancloth.
CAUTION: DO NOT MIX CEMENTBATCHESSMALLERTHANAS SUPPLIEDAS
UNRELIABLECURE CONDITIONSCAN RESULT.
(f) Mix82C32cementas follows:
(1.) Pourcontentsof part2 intocontainerof part1.
(2.) Thoroughly
stircontentswitha tonguedepressor
for about5 minutes.
NOTE: Potlifeof mixed82C32cementis about20 to 30 minutesin andopencontainer.Pot
life canbe extendedupto 1 hourby recapping
containerbetweenapplications.
EFFECTIVITY:
040-999
28-10-00Jan
PAGE
23
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
18. RepairPatch(QuickCureMethod)(continued)
(g) Applyonebrushcoatof 82C32cementto cleanbuffedareaof cell. Donotnotapplybeyond
buffedarea. Allowto dryfrom10to 15 minutes.
(h) Repeatstep(g)withsecondcoat.
(i) Repeatstep(g)withthirdcoat.
(j) Whilethirdcoatof cementiswet,applyfabricpatchto damaged
areaasfollows:
(1.) Dippatchin cleanMEKandshakeoff excesssolvent.
(2.) Laypatchintowetcement.Makesurepatchis centeredoverdamagedarea.
(3.) Smoothoutpatchusinga relativelydrybrush.Workfromthe centerof thepatchto the
edgesto removeall trappedair.
(k) Apply final coat of 82C32 cementover patch. Spreadcementat least 1/8 inch beyondfabric
patch.but not beyondbuffedarea.
CAUTION: NEVERAPPLYA HEATCURETO 82C32CEMENT.
(I) Allowrepairto aircurefor a minimumof 6 hoursat a minimumtemperature
of 70°Fbefore
movingcellor exposingthecellto fuel.
(m)Checkrepairaftercuretimeto ensurecementis cured. If stickyproceedasfollows:
(1.) Removerepairpatchandall cement.
(2.) Repeatsteps1thru 12. Makesurecementis notoutof date.
(n) Checkedgesof repairfor looseness:
(1.) Trimlooseedgesif lessthan 1/8inchradially.
(2.) Bondlooseedgesif morethan 1/8inchradially.
NOTE: Channelsor voidsrunningfromcenterof patchto edgesareunacceptable.
(o) Performfuel cellleaktest(referto testingfuelcells).
19. SealingMetalSurfaceFittings
WARNING: DO NOT ALLOWALODINESOLUTIONTO COMEIN CONTACTWITH HANDS,
EYES,OR CLOTHING.
(a) Rubroughnessofftheaffectedareawitha finefile or fineemerycloth.
(b) Cleanmetalsurfaceusinga cleanclothdippedin Methylethylketone.
(c) Moistenthecleanedsurfacewitha cleanclothdippedin water.
(d) Applyundilutedalodine1200solutionto theaffectedareawitha smallnylonbrush.
(e) Allowthesolutionto dry untila lightgoldencolorappears.
(f) Aftera coatinghasbeenformed,removetheexcesssolutionbywipingthesurfacewitha clean
watermoistened
cloth.
(g) Wipedry.
EFFECTIVITY:
PAGE 24
28-10-00
Jan10/90
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
20. FuelCellAccessoryReplacement
(a) Obtaina curedrepairaccessory
fromthecellmanufacturer.
(b) Marklocationof old accessory
andpreservemarkingsfor guidelinesto locatethenewpart.
(c) Removetheoldaccessory
asfollows:
(1.) Graduallyloosening
an edgewitha bluntprobe-likeinstrument.
(2.) Grasptheaccessory
bythelooseedgewithpliersandgentlypeelthe accessory
off the
cell wallfromtheblindsideof a celllaptowardtheexposededge. Becarefulnotto pull
the celllapopenwhilepeelingaccessory
off.
NOTE: Removaloftheold accessory
willprobablyleavean unevencavityandsurface.
(d) Buffthe cellsurfaceundertheaccessory
withemeryclothto smoothroughness
andprepare
forcement.
(e) Buffandwashthecontactsurfaceof newaccessory.Washthecellsurface[referto repair
patchheatcuremethodsteps(b)thru(d)).
(f) Applymixed5923Crepaircementto bothsurfaces.Levelthecavityleftbytheremovalof the
oldaccessory.
(g) Rollthe newaccessory
intoplace.Placepaddedplatesin positionto ensureadequate
pressurewhenclamped.Usea cellophane
separator
to preventthecementfromstickingin
thewrongplace.
(h) Cureaccessory
witheitherair cureor heatcuremethod.
EFFECTIVITY:
28-10-00
Jan 10
28-10-00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Storage(continued)
21. Repairof FuelCellDefects
(a) Repairblistersasfollows:
(1.) Trimlooseor raggedmaterialfromaffectedarea.
(2.) Applyan outsideandinsiderepairpatch.
(b) Repairholes,punctures,
cuts,tearsanddeepabradedareasasfollows:
(1.) Trimlooseor raggedmaterialfromaffectedarea.
(2.) Applyan outsideandinsiderepairpatch.
(c) Repairlooseedgesasfollows:
(1.) Bufflooseedgesandcontactsurfaceswithemerycloth.
(2.) WashbuffedareathreetimeswithMethylethylketone.
(3.) Applytwocoatsof 5923Cmixedcementto eachsurface.
(4.) Clampandcure. Eithermethodmaybe used.(Seerepairpatch.).
(5.) Trimlooseedgesif lessthan1/8inchremains.
(d) Repairinsideloosefittingflangeas follows:
(1.) Buffthe edgeof theflangeandthecontactsurfaceundertheflange.
(2.) Apply5923Cmixedrepaircement,cellophane,
paddedplatesandclamp. (Referto repair
patchheatcuremethod.)
(e) Repairloosenessagainstmetalasfollows:
(1.) Preparemetal(referto sealingmetalfittingsurfaces).
(2.) Apply5923Cmixedrepaircementandcureby eithermethod.
(f) If patchedareaof fuelcelllacksrepaircementproceedasfollows:
(1.) Buffsurfacenextto missingsealantwithemerycloth.
(2.) Washsurfacethreetimeswith MEK.
(3.) Applyfourcoatsof 5923Cmixedrepaircement.
(4.) Clampandcureusingeithermethod.
EFFECTIVITY:
040-999
28-10-00
10/90
Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution
1. Descriptionand Operation
(a) FuelValves(referto 28-20-00 Figure301)
The PA-42-720containsthree majorfuel control valvesconsistingof two primaryfuel shutoff
valvesand a crossfeedvalve. Eachfuel shutoffvalve is mountedto a wing forwardspar
reinforcementplatewithin the wing rootcavity. Thecrossfeedvalve is mountedto a tee fitting
on the left wing rib in the left root cavityand is connectedin linewith the left fuel feed line.
(b) Fuel Filter (referto 28-20-00 Figure 1)
Fuelfilters on the PA-42-720,locatedon the left side of the enginefirewall,are reachedby
removingthe top enginecowling. Maintenanceto filterassemblyis limitedto removaland
cleaningof filter screen,repairof minordamageor corrosion,or total replacementof filter
assembly.
BypassValve
Assembly
O-Ring
Element
Fuel Filter Assembly
Figure 1
EFFECTIVITY:
040-999
28-20-00PAGE
1
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
Vent
VaporBleed
Line
SumpDrain
Valve
AntiSiphon
Fier Cap
NacelleFuel
Tank
FuelFeedandCrossfeedInstallation
Figure2
EFFECTIVITY:
28-20-00
PAGE
Jan 10/90 2
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution(continued)
CheckValveand
FuelCell
Connector
VIEW B
VIEW A
Wing Fuel System
Figure 3
EFFECTIVITY:
040-999
28-20-00
PAGE3
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
(c) FuelJet Pumps(referto 28-20-00Figures302and401)
ThePA-42-720
is equippedwitha jet scavenger
fuelpumpwhichreturnsunusedfuel at start
andshutdownanda jettransferfuelpumpwhichtransfersfuelfromthe inboardaft auxiliary
tankto the inboardmaintank.
Thejetscavenger
pump(Figure302)is mountedto theinletair ducton therightrearsideof
eachengine.
Thejettransferpump(Figure401)is locatedin thewingrootcavity8.5inchesinfrontof theaft
sparandclampedto the aft inboard(auxiliary)tanknipple.Thoughtheauxiliarytankis
withtheinboardmaintank,theauxiliarytankisthe lowestpartof thesystem
interconnected
andrequiresa meansof transferring
fuelto an enginefeedareaoncethefuel levelhas
decreasedbelowthe interconnecting
tubelevel. Thejettransferpumpdrawsallfuel fromthe
aft inboardfueltankto thefeedareain theinboardmaintank. Highpressurefilteredfuel is
deliveredto the pump,whichusesa venturiaffectto pullunusedfuel fromthe auxiliarytank
anddeliversit to the inboardmaintank.
2. Fault Isolation- Fuel System
CHART 1
FAULTISOLATION (FUELSYSTEM)
Fault
Cause
Remedy
Fuelvalvesleak,
pressurelowor
pressuresurges.
Obstruction
in inletsideof
pump.
Tracelinesandlocateobstruction.
Faultypump.
Replacepump.
Fuellinesdamagedor
improperly
installed.
Locateandrepair.
O-ringsimproperly
installed.
Locateandrepairor tighten.
Unidentified
leak.
EFFECTIVITY:
040-999
Jan 10/9028-20-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
3. Overhaulof Fuel ShutoffValves
NOTE: A kit (P/N 763-995)containingvalvefor replacementpartscan be obtainedfrom Piper.
Disassemblevalve and rebuildas follows:
(a) Firmlysecurevalve in vise betweentwo slabsof wood or thick sheetsof soft aluminum.
(b) Withscrewdriverthat fits securelyin screw heads,apply small amountof down pressureon
screwsand removescrewsfrom body. Screwsare securedwith LoctiteGrade A threadlock.
(c) Removesafetywire and screwin valve shaft. The screwis also securedwith Loctite.
(d) Ensurevalve is closedpositionand removehandleon valveshaft. Notepositionof valveshaft
and roll pins.
(e) Withpliers, removeroll pins.
(f) Pullfitting from valvebody and removeO-ring.
(g) Cleanfitting and apply DowComingLubricant(FS3451)or equivalentto O-ring flange.
(h) Installnew MS29513-019O-ring. Set fitting in clean area and coverwith clear plastic. (Saran
wrap,etc.)
(i) Removeand throw awayvalve(spring,washer,and spacer.
(j) Removeand disposeseal (2555-05,Dukes)and O-ring.
(k) Removevalvefrom vise. With soft,wood dowel,pushout ball from other end of valvebody.
Be carefulnot to nick or damageball. Cleanas necessary.
(I) With roll pin removedfrom shaft,pushcontrolshaft intovalve bodyand remove.
(m) RemoveO-ringfrom shaftand clean O-ring.
(n) Removeother seal, O-ring,wave washer,and spacer.
(o) Thoroughlyclean insideof valveand dry.
(p) Installnew valvewasher and spacer.
(q) UsingDow ComingLubricant(FS3451)or equivalent,lubricateone 2559-05seal and install
MS29513-016O-ring on seal.
(r) Carefullyinsertseal in bodyuntil it meetsspacer.
(s) With controlshaftclean and corrosionfree, lubricatewith DowComing Lubricant(FS3451)or
equivalent. InstallMS29513-008O-ring.
(t) Apply large amountof lubricanton bottomof shaft (28-20-00 Figure301) and installshaft in
valvebody.
(u) Replaceroll pins so shaftpin is positionedon sidewith open designation. Installgroovedpins
in bodywith groovedendsdown.
(v) Withshaft in closedposition,install handle.
(w) CoatAN500AD6-3screwthreadswith threadlockfrom kit. Installtwo AN960C6Lwashersand
screwon shaft. Safetywire handleand screw.
(x) Installball valve,ensuringball slidesinto bodywith openingstoward side of body. Also ensure
shaftflange is snug againstbodyflange (28-20-00Figure301).
(y) Installsecondseal per steps (q) and (r) above.
(z) Installother new spacerand washer.
(aa) Withfitting preparedper steps (g) and (h), install it on valvebodywith attachingscrews,
ensuringthreadsare coatedwith Loctite.
EFFECTIVITY:
28-20-00
PAGE
5
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
"On" Position
'Open" Position
"Closed"
Position
ShutOff
Valve(SeeNote)
andShutoff)
DukesFuelValve(Crossfeed
Figure301
EFFECTIVITY:
040-999
Jan 10/90 28-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
4. Servicing
Jet Scavenger
Pump (referto 28-20-00Figure302)
Thisjet pumpcanisteris basicallya replaceable,
nota repairable
item. However,if thejet, elbow,
or checkvalvebecomecloggedor fouled,removeandreplaceasfollows:
(a) Disconnect
inletlinefromelbow.
(b) Releaselocknutsecuringelbowin position.
(c) Carefullyremoveelbow,checkvalve,andreplaceO-ringif necessary.
(d) Slidea pieceof 0.02inchsafetywirethroughelbowendof canisterto othersideandputa
1/16inchor lessbendat endof wire.
(e) Carefullyslidewirebackthroughandpulloutjet andspringwasher.Replacewasher,if
necessary.
(f) Replacepartsin reverseorder.
LineConnector
to SolenoidValve
Hose to Fuel Divider
Spring Clamp
SpringClamp7
OverflowDrainLine
Modified
Elbow
Nozzle
ScavenageCan
O-Ring Seal
Drain
Check Valve
Jet ScavengerPump
Figure 302
EFFECTIVITY:
040-999
28-20-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
5. Removalof FuelValves
(a) Ensurecrossfeed
valveis offwhenremovingeitherof thetwoshutoffvalves.Proceedas
follows:
(1.) Drainallfuelfromsideof systemaffected.
(2.) Removebottomwingrootpanelto gainaccessto valveon forwardsparreinforcement
plate.
(3.) Disconnect
linesfromvalve. Caplinesandremovevalvebyunscrewing
screwsfromself
lockingnuts. Disconnect
controlcablefromactuatingarm.
(b) Toremovecrossfeedvalve,drainfuelfrombothsystems.In leftrootcavityin frontoffuel
pump,disconnect
valvefromits bracket,teefitting,andcrossfeedline.
6. Installation
of FuelValves
(a) Placevalvein properposition.Secureto mounting
bracketor withattachment
clamps,
depending
on valvebeinginstalled.
(b) Connectproperfuellinesto valve. Connectcontrolcableto actuatorarmwithattaching
hardware.
(c) Checkvalveandendfittingsfor leaksby fillingtankwithfuel.
(d) Installlowerwingrootfairing.
7. Removalof FuelFilterScreen
(a) Closefuelshutoffvalve.
(b) Drainfuelfromfilterassembly.Removedrainvalveleverfromfuelfilterassemblybyremoving
clampattached
to filterbowl.
(c) Unscrewdrainvalvefromfilterbowl.
(d) Unscrewfilterbowlfrombody.
(e) Removescreenandinspectsealson retainerandbodyassembly.If sealsare deteriorated
or
damaged,replaceby scrapingthemoff theirfixture(orreplaceretainer)andgluingon new
ones.
(f) RemoveoldO-ringin bodyassembly.
8. Installation
of FuelFilterScreen
(a) Ensurescreensealson bodyassemblyandretainerarein goodconditionandsolidlymounted.
(b) InstallnewO-ringin body.
(c) Insertscreenin bowlandinstallbowlon body.
(d) Attachdrainfittinganddrainlever.
EFFECTIVITY:
PAGE8
Jan 10/90
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
9. Installation
of FuelFilter
(a) Positionfilterhousingin properlocation;secureto mountingbracketwiththreecapboltsand
safety.
(b) Connecttwofuellinesto properfittings.
(c) Attachfuel bowlquickdrainactuatorhandleremovedto mountingclampon filterbowlwith
screw,washer,andnut.
(d) Connectfilterbowldrainhoseto fittingon bottomof bowl.
NOTE: Fuelcellsmustbe 90%full to getfuelflowfromfilter.
(e) Turnfuel shutoffvalve on and depressfuel filter bowl drain valve until steadyflow of fuel exists.
Releasehandleand checkfor leakswherefilter bowl assemblyscrews into head assembly,
and wheretwo fuel lines and filterbowl drain line attachto filter housing.
(f) Installtop enginecowl.
10. Removal
of Jet TransferPump (referto 28-20-00Figure401)
on.
(a) Withcrossfeedvalveoff,drainsystem.If bothsystemsmustbe drained,leavecrossfeed
(b) Removenecessary
wingrootfairings.
(c) Disconnect
fuellinesfrompump.
(d) Removeretainingclampsandslidepumpinletportoutof tanknipple.
4.50
Motive FittingPort
Outlet Port
InletPort 4 X 4 MeshScreen
Jet TransferPump
Figure 401
EFFECTIVITY:
040-999
28-20-00PAGE
9
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution(continued)
11. Installationof Jet TransferPump
(a) Slide pump inlet port intotank nippleand install retainingclamps.
(b) Connectfuel lines to pump.
(c) Installwing root fairings (if previouslyremoved).
12. Removalof SubmergedFuel Pump
(a) Drain entiresystemor ensurecrossfeedvalve is off so eitherwing can be drainedseparately
withoutdrainingfuelfrom oppositeside.
(b) Removelower wing root fairingfrom underside of wing wherepump is to be removed.
(c) Removeaccessplateon top of wing, aheadof mainspar, nextto fuselage. Removefuel cell
cover plateto gain accessto fuel pumps(referto 28-20-00 Figure402).
CAUTION: WHEN DISCONNECTING
ANY ELECTRICALCONNECTIONON FUELPUMPS,
A WRENCHMUSTBE USEDTO BACK UP EACHTANKCONNECTIONTO
PREVENTNYLONFITTINGFROMTURNING. IF FITTINGTURNS,INTERNAL
WIRECONNECTIONWILL BREAK,NECESSITATING
PUMP REPLACEMENT.
(d) In wing root cavity,back up and disconnectelectricalconnections,fuel, and drain lines from
pump.
(e) While holdingpump throughcell accessopeningin top of wing,an assistancemustremove
four pump mountingbolts in wing root cavityand pull pump up and out of fuel cell.
13. Installationof SubmergedFuel Pump
(a) Installnew gasket on fuel pump mountingboss, insertpump into cell, and hold in place while
assistantattachesit to wingbutribwithfourmountingbolts.
(b) Reconnect
electricalconnections,
fuel,anddrainlinesandensurevalvesarepositioned
properly.
(c) Installfuel cell coverplate and accessplate on top of wing. Fill fuel cell through nacellefiller
and checkall connectionsin the wing root cavityfor leaks.
(d) Installlowerwing root fairing.
PAGE10
040-999
Jan 10/90 28-20-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
Submerged
FuelPump
NylonConnectorAssembly--
FuelCell
CheckValve
SubmergedFuel BoostPump
Figure 402
14. Adjustment
of FuelShutoffandCrossfeedValve(referto 28-20-00Figure301)
(a) Removelowerwingrootfairingon siderequiringvalveadjustment.
(b) Placefuel shutoffcontrolleverto full ONposition.Confirmvalveactuatoris againststopon
valvebody.
(c) Gapbetweencontrolleverandstopmustbe0.10- 0.20inch. If not,proceedto step4.
(d) Disconnect
controlcableat actuatorarm. Loosenjam nutat clevisfitting.
(e) PlaceshutoffvalveactuatorarmfirmlyagainstOPENpositionstoppin. Placecockpitlever
againststopposition.
(f) Carefullymovelever0.10- 0.20inchoff stop.
(g) Alignclevisholewithmatingholein valveactuatorarm. Securewith attachinghardware.
(h) Operatecontrolleverseveraltimes,to ensureactuatorarmon valvecontactsstoppin,before
controlleverin cockpitcontactsstop.
(i) Reinstalllowerwingrootfairing.
EFFECTIVITY:
040 999
PAGE11
28-20-00 Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
15. LeakageTestof FuelShutoffandCrossfeed
Valve
(a) Connectvalveinletportto 50 psi air source.
(b) Closevalve,apply50 psi air pressure,andsubmergevalvein keroseneor similarpetroleum
basefluidfor 2 minutes.
(c) Ensureno evidenceof leakagethroughvalveportor aroundseat.
(d) Disconnect
air source.Wipefluidfromvalveexterior.
16. FuelFlowandPressure
Test(referto 28-20-00Figure501)
fuellinefromflow meterandconnectit to test rig inlet.
(a) At flow divider/dump
valve,disconnect
(b) Placereturnlineendontonacelleor tiptankfilleropening.Ensureresultingfuelpressure
doesn'tpushit outof opening.
(c) Connectelectricpowersupplyat APUconnector.Maintain28voltsfor alltests.
(d) Ensureallshutoffvalveshavefull travelandwingtankscontainenoughfuelto allowfuelto
flowfreelyto maininboardtank. At least10gallonsof fuelmustexistin eachmaininboard
tank.
(e) Forzerofuelflowcheck,proceedasfollows:
(1.) Turncrossfeedvalveandrightfirewallshutoffvalveoff. Turnleftfirewallshutoffvalveand
rightsubmerged
fuelpumpon.
(2.) Ensurebothaircraftfuelpressuregaugesread0 psi.
(3.) Turncrossfeedvalveoff,andleftandrightfirewallshutoffvalveson. Closetest rig
regulating
valveandturnrightsubmerged
fuelpumpon.
(4.) Ensurefuelpressuregaugereads0 psi for leftengineandmaximum35 psifor right
engine.
(5.) Comparereadingson aircraftgaugewith readingon testrig gauge.
(6.) Turncrossfeedvalveoff,andleftandrightfirewallshutoffvalveson. Closetest rig
regulatorvalveandturnleft submerged
fuel pumpon.
(7.) Ensurebothfuel pressuregaugesread0 psi.
(8.) Turncrossfeedvalveoff,andleftandrightfirewallshutoffvalveson. Closetest rig
regulatorvalveandturnleft submerged
fuel pumpon.
(9.) Ensureleftfuel pressuregaugereadsmaximum35 psi andrightfuelpressurereads0 psi.
(10.) Comparereadingson aircraftgaugeswiththoseon test rig.
(f) Forpositivepressurefuelflowtest,proceedasfollows:
(1.) Forleftengine:
fuel
valveoff,andturnleftfirewallshutoffvalveandleftsubmerged
(a.) Turncrossfeed
pumpon.
(b.) Adjustflow meterreadingto 500pph. Fuelpressuremustreadminimum17psig.
(c.) Ensureaircraftfuel gaugereadsminimum17psig.
(d.) Turncrossfeedvalveon andrightfirewallshutoffvalveoff. Turnleftfirewallshutoff
fuelpumpon.
valveandrightsubmerged
(e.) Adjustflowmeterreadingto 500pphandfuelpressuregaugereadingmustread
minimum17psig.
EFFECTIVITY:
PAGE 12
Jan 10/90
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Distribution
(continued)
RegulatingValve
1400SeriesGauge6" Dia.0-60 psi
1/4 of 1%Accuracyor Equiv.
HoseReturnto
TankBeing Used
-800
Fisherand Porter
Flowmeter
=
DisconnectLineat
EnginePumpInlet
and Connectto
Test Rig.
-0
MaxFlowRate800 PPH
Accuracy+ 1% of Reading
or EquivalentCalibratedfor
Jet A-1
FlowmeterShouldbe Mountedin a VerticalPosition.
The ElevationShouldbe no Higherthan InjectorInlet
and the Samefor All Test.
Fuel FlowTestApparatus
Figure 501
(2.) Forrightengine:
fuel
valveoff,andturnrightfirewallshutoffvalveandrightsubmerged
(a.) Turncrossfeed
pumpon.
(b.) Adjustflow meterreadingto 500pph. Fuelpressuremustreadminimum17 psig.
(c.) Ensureaircraftfuelgaugereadsminimum17psig.
valveon andleftfirewallshutoffvalveoff. Turnrightfirewallshutoff
(d.) Turncrossfeed
fuelpumpon.
valveandleft submerged
(e.) Adjustflow meterreadingto 500pphandfuelpressuregaugereadingmustread
minimum17psig.
NOTE:If flowmeteris notavailableandpositivepressurefuelflowtestcannotbe performed
or
usefuelweightpertimemethod.In thistest,500pphequals8.33pound/minute
watch.
stop
with
minutes
2-3
for
approximately
test
Perform
1.24gallon/minute.
EFFECTIVITY:
040-999
28-20-00
13
PAGE
Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution(continued)
17. Jet Pump Flow Check
WARNING: AREASURROUNDINGAND INSIDEOF AIRCRAFTMUSTBE WELL
VENTILATEDAND CLEAROF ANY SOURCEOF FLAMEOR SPARK.
(a) Drain affectedfuel system(if not alreadydrained).
(b) Disconnectand plugjet pump returnline from pump.
(c) When accumulatinganyfuel, ensureit is done outsideor as close as possibleto outsideof
aircraft. Obtainan eightfoot or longer piece of 1/2-inchhoseor tubing. Connectline to jet
pump, and while keepingfree end 24 inchesabovejet pumpoutlet, route line out or neardoor.
Connectcontrolon/offvalveto free end of line.
(d) With firewall shutoffvalveclosed (off), add at least 20 gallonsof fuel to system.
(e) Open firewallshutoffvalve,operateboostpump untilfuel flow clears,and closecontrolvalveto
check for leaks. Withcontrolvalve open, it musttake maximum4.3 minutesto accumulate5
gallons (466 PPH minimum).
18. Cleaningof Fuel FilterScreen
(a) Clean bowl and bodywith oil solventand checkfor damage. Replaceif necessary.
(b) Clean filterelectrosonicallyand inspectdamage. Replaceif necessary.
PAGE
14 28-20-00
28-20-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Indicating
1. Descriptionand Operation
(a) FuelQuantityIndicatingSystem
The fuel quantity indicating systemcontainstwo separatecapacitancesystems using dual
display indicators. Each identical probe system measuresits fuel capacity with two probes
in each inboard main cell (95 gal cap.), and one probe in all other cells and tanks (refer to
28-40-00 Figure 1). The probeunits have fixed tabular capacitor elements to matchthe
contour of the respective cell or tank position. This systemdisplays very accurate
indicationsdue to the linear responseof probes. With fixed electrodes,sensor capacitance
is about 2:1, or approximatelytwice as great with a full system. Any change in fuel quantity
betweenfull and empty producescorrespondingchanges in capacitance. These changes
are amplified within the dual indicator and continuouslydisplayed on the indicator face. The
dual indicator readout is a direct indicationof fuel weight on board the aircraft.
Thedual-needlefuel quantity indicator,mountedon the copilotside abovethe controlwheel,
has its own ac inverterto powerthe capacitanceprobesystems. Electricalpowerfor the entire
systemis suppliedfrom the 28 Vdcaircraft powersupply.
(b) AutomaticFuel PumpSystem(referto 28-10-00in PA-42-720(AdvancedTrainer)Wiring
DiagramManual)
The automaticfuel pump systemsuppliesthe appropriatesystemwith properfuel if fuel
pressurefalls belowan acceptablelevel. If fuel pressurestartsto fall, the fuel pressuregauge
mechanismsensesthe drop, and at 15 psi, completesa circuitto activatethe low fuel pressure
annunciatorand the fuel pump relay. The relay completesa circuit betweenthe auto position
of the fuel pump switch and the fuel pump.
This systemonly workswith the switchin auto,which in turn preventsthe submergedfuel
pumpfrom runningcontinuously.The annunciatorlight will still comeon at 15 psi. With both
the pump and light controlled,in this case by the gauge,the gauge also shuts them off when
pressurerises above33 psi.
Thefuel pump relays are locatedon a shelf mountedto bulkheadat FuselageStation25.6.
Accessto the shelf is made by removingthe royalitecoverat the rear of the nose baggage
compartment.
EFFECTIVITY:
040-999
28-40-00
PAGE
1
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating(continued)
Outboard
MainTank
ProbeInstallations
FuelCapacitance
Figure1
EFFECTIVITY:
Jan 10/90 28-40-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating
2. Fault Isolation- Fuel System
CHART 1
FAULTISOLATION(FUEL SYSTEM) (Sheet 1 of 2)
Fault
Remedy
Cause
Circuitbreakerout.
Checkand reset.
Brokenwire.
Checkand repair.
Gaugeinoperative.
Replace.
Incompleteground.
Checkgroundconnectionat gauge
and at fuel transmitterin the wings.
Vent holes in fuel transmitter
clogged.
Clear vent holes.
Fuelvalve stuck.
Check valve.
No fuel in tanks.
Check and fill.
Filtersdirty.
Cleanfilters.
Faultyfuel pressuregauge or
transducer.
Replacegauge or transducer.
Enginestopswith more
than 10 gallons(67 lbs.)
of fuel remainingand/or
a significantamountof
fuel still remainsin aft
inboard(aux)tank.
MotivePortin JetTransfer
pumpclogged.
ServiceJet TransferPump.
Removeand cleanaffecteditem.
Erraticmovementof
meterin Fuel Quantity
Indicator.
Frictionin metermovement
causedby dirt or improper
alignmentof meterpointer.
ReplaceFuel QuantityIndicator.
Fuel QuantityIndicator
inoperative.
Metermovementcoil is open.
ReplaceFuel QuantityIndicator.
Defectivecomponenton
printedcircuitboards.
Replaceindicator.
Aircraftconnectornot
connectedproperlyto
indicator.
Checkconnectorinstallation
at indicator.
Aircraftwiring defective.
Checkwiring, repairas required.
Fuel gauge fails to
indicatepropertank
level.
Lowfuel pressure.
EFFECTIVITY:
Inlet Port screenclogged.
040-999
2840-00
1090
Jan
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating(continued)
2. Fault Isolation- Fuel System(continued)
CHART 1
FAULTISOLATION (FUELSYSTEM) (Sheet 2 of 2)
Fault
Zeroindicationof Fuel
QuantityIndicatoris
out of tolerance.
Cause
Remedy
Meterpointeroutof
balance.
Replaceindicator.
Internalmechanical
adjustment
of meter
notsetproperly.
Replaceindicator.
Externaladjustment
incorrect.
Adjust.
EFFECTIVITY:
040-999
Jan 10/90
28-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating(continued)
3. Overhaulof TankSensorUnits
Do not overhaultank sensorunits. If unit is found defective,replaceit.
4. Overhaulof Fuel QuantityIndicator
Do notoverhaulfuel quantityindicator. Replace,if necessary.
5. Removalof Tank SensorUnits
CAUTION: HANDLESENSORUNITSCAREFULLY.DAMAGINGTUBES DESTROY
ACCURACYOF THE UNIT.
(a) NacelleTankSensor(mountedin upperportionof nacelletank, inboardof filler cap):
(1.) Ensureenoughfuel is drainedfrom systemto preventspillover.
(2.) Removeaccesscover nextto filler cap.
(3.) Disconnectand tag or mark leadsto facilitatereconnection.
(4.) Removescrewsattachingprobesensorto nacelle. Carefullyremoveprobesensorand
gasket.
(b) MainOutboardFuel Sensor(mountedat Wing Station102.0):
(1.) Removeaccesscover at WingStation 102.0.
(2.) Ensureenoughfuel is drainedfrom systemto preventspillover.
(3.) Removeaccesscover nextto filler cap.
(4.) Disconnectand tag or mark leadsto facilitatereconnection.
(5.) Removescrews attachingprobesensorto fuel cell. Carefullyremoveprobe sensorand
gasket.
(c) Aft InboardFuel Sensor(mountedat Wing Station 15.0):
(1.) Removeaccesscover at WingStation 15.0.
(2.) Ensureenoughfuel is drainedfrom systemto preventspillover.
(3.) Removeaccesscover nextto filler cap.
(4.) Disconnectand tag or mark leadsto facilitatereconnection.
(5.) Removescrewsattachingprobesensorto fuel cell. Carefullyremoveprobe sensorand
gasket.
(d) MainInboardFuel Sensors(mountedat WingStations13.3 and 36.0):
(1.) Removeaccesscoversat WingStations13.3 and 36.0.
(2.) Ensureenoughfuel is drainedfrom systemto preventspillover.
(3.) Removeaccesscovers nextto filler caps.
(4.) Disconnectand tag or mark leadsto facilitate reconnection.
(5.) Removescrewsattachingprobesensorsto fuel cell. Carefullyremoveprobesensorsand
gaskets.
EFFECTIVITY:
28-40-00
PAGE 5
28-40-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Indicating(continued)
(e) Wing Tip Tank Sensor:
(1) Removebottomtank-wingfairing.
(2) Ensureenoughfuel is drainedfromsystemto preventspillover.
(3.) Disconnect
andtagor markleadsto facilitatereconnection.
(4.) Removescrewsattachingprobesensorto wingtiptank. Carefullyremoveprobesensor
andgasket.
6. Installation
of TankSensorUnits
CAUTION: HANDLESENSORUNITSVERYCAREFULLY,
AS DAMAGINGTUBES
DESTROYSACCURACYOF UNITS.
(a) NacelleTankSensor(mountedin upperportionof nacelletank,inboardof fillercap):
(1.) Carefullyinstallprobesensorandgasket.Installscrewsattachingprobesensorto
nacelle.
(2.) Connectleadsto probesensor.Ensuremarkedor taggedleadsareconnectedproperly.
(3.) Installaccesscoverpreviously
removed.
(b) MainOutboardFuelSensor(mountedat WingStation102.0):
(1.) Carefullyinstallprobesensorandgasket.Installscrewsattachingprobesensorto fuel
cell.
(2.) Connectleadsto probesensor.Ensuremarkedor taggedleadsareconnectedproperly.
(3.) Installaccesscoverspreviously
removed.
(c) Aft InboardFuelSensor(mountedat WingStation15.0):
(1.) Carefullyinstallprobesensorandgasket.Installscrewsattachingprobesensorto fuel
cell.
(2.) Connectleadsto probesensor.Ensuremarkedor taggedleadsareconnectedproperly.
(3.) Installaccesscoverspreviously
removed.
(d) MainInboardFuelSensors(mountedatWingStations13.3and36.0):
(1.) Carefullyinstallprobesensorsandgaskets.Installscrewsattachingprobesensorsto fuel
cell.
(2.) Connectleadsto probesensors.Ensuremarkedortaggedleadsareconnectedproperly.
(3.) Installaccesscoverspreviously
removed.
(e) WingTipTankSensor:
(1.) Carefullyinstallprobesensorandgasket.Installscrewsattachingprobesensorto fuel
cell.
(2.) Connectleadsto probesensor.Ensuremarkedortaggedleadsareconnectedproperly.
(3.) Installbottomwingtankfairing.
EFFECTIVITY:
Jan 10/90 28-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating(continued)
7. FuelQuantitySystemCalibration
TestsandAdjustments
Thecompletecalibrationtestsrequirethattheaircraftbelevelbothlongitudinally
andlaterally,and
thatboththedryandwetcalibration
testsbe accomplished.
(a) DryCalibration
Procedure:
(1.) Completely
drainfuelsystem.
(2.) Ensurethatfuel quantitycircuitbreakerlocatedon theessentialbus is pushedin.
(3.) Ensurethatallfuel distribution
circuitbreakersarepushedin.
(4.) Ensurethatbatterymasterswitchis off. Ensurethatfuelcrossfeedswitchis off.
(5.) Connectexternalpowerunitto aircraft.Setvoltageon externalpowerunit27 ± 3 Vdc.
switchpanelto ONposition.
Turnexternalpowerswitchon overhead
leftfuel systemwiringharnessfromfuelquantityindicator.
(6.) Disconnect
(referto 28-40withadapterharnesses
(7.) Connectinterfaceharness(RagenP/N89-174-1)
areusedwith respecttotesting
00 Figure501). Ensurethatcorrectadapterharnesses
sectionof partscatalogfor
equipment
the leftandrightfuelsystems(seemiscellaneous
correctpartnumbers).
NOTE: Analternateinterfaceharness(RagenP/N89-2241)maybe usedforthis
as mentioned
above
calibrationcheckwithoutthe useof theadapterharnesses
(referto 28-40-00Figure501).
(8.) Connectrespectivecablesto fuel quantityindicator,main harness,and fuel calibrationtest
set (referto 28-40-00 Figure 501).
(9.) Set NORM/MEASswitchand NORM/SIMswitch on interfaceharnessto NORMposition.
This ensuresthat fuel quantitysystemwill operatenormally.
(10.) Set test switcheson fuel calibrationtest set as follows (refer to 28-40-00 Figure 502):
(a.) Set CAP/VOMswitch to CAP position.
(b.) Set AC/DCswitchto DC position.
(c.) Set MEAS/SIMswitchto MEASposition.
(d.) Set MEAS INT/MEASEXTswitch to MEAS INTposition.
(e.) Set TU/COMPswitch to TU position.
(f.) Set NORM/CALswitchto CAL position.
(g.) Set ADD/OFFswitchto OFFposition.
NOTE: DonottouchDCCALknobaftersettingvaluegivenin step(11.).AdjustingDC
CALknobwillcauseinaccuracy
with remainder
of calibrationprocedure
and
requirethattheprocedure
be repeated.
(11.)Letfuelcalibrationtest setwarmupfor 15minutes.SetcalibrationbyturningDCCAL
knobto valueon fuelcalibrationplacard(locatedinsidelidof fuelcalibrationtest set).
EFFECTIVITY:
28-40-00
28-40-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating
(continued)
FuelCalibrationTest Harness
(P/N89-174-1)
AdapterTest Harness
(L.Wing)or (R. Wing)
Fuel Calibration
Test Box
Adapter TestHarness
(L. Wing)
IndividualFuel Probe
Test Harness
E344
AdapterTest Harness
(R. Wing)
FuelQuanitity
Indicator
I
MainFuselage
Harness
E344
J2 J1
Fuel Calibration
Test Box
E344
FuelCalibrationTest Harness
(P/N 89-224-1)
- FuelQuanitity
Indicator
E3 44
FuelCalibrationTestSetup
Figure 501
EFFECTIVITY:
PAGE8
Jan
10/9028-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating(continued)
Fuel CalibrationTest Set
Figure502
7. FuelQuantitySystemCalibration
TestsandAdjustments
(continued)
(a) DryCalibration
Procedure
(continued)
(12.)Set NORM/MEAS
switchon interfaceharnessto MEASposition.
(13.)Set switchesonfuel calibration
testsetasfollows:
(a.) Set MEASINT/MEASEXTswitchto MEASEXT position.
(b.) Set NORM/CALswitchto NORMposition.
readingof 178.0± 17.8pF. If
test setfor capacitance
(14.)Checkgaugeon fuelcalibration
reading
capacitance
readingfallswithintheselimits,proceedto step16;if capacitance
doesnotfall withinthoselimits,proceedto step(15.).
EFFECTIVITY:
040-999
28-40-00 JanPAGE
9
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Indicating(continued)
7. Fuel QuantitySystemCalibrationTestsand Adjustments(continued)
(a) Dry CalibrationProcedure(continued)
(15.) Checkindividualfuel sensorsas follows:
(a.) Disconnectinterfaceharnessfrom fuel calibrationtest set.
(b.) Connectfuel sensortesting harnessto fuel calibrationtest set.
(c.) Disconnectwiringfrom tip tankfuel sensorand connectrespectivecoloredwiresfrom
fuel sensortesting harnessto wires protrudingfrom fuel sensor.
(d.) Checkgauge on fuel calibrationtest setfor capacitancereadingof 17.66± 1.76pF
(refer to 28-40-00 Chart 501). If readingis not within limits, replacefuel sensor.
(e.) Disconnecttest harnessand connect respectivewires of sensorto harness.
(f.) Repeatsteps c thru e for the other fuel sensors,exceptcheck gaugefor capacitance
readingsas shownin 28-40-00 Chart 501.
(g.) Disconnectfuel sensortesting harnessfromfuel calibrationtest set.
(h.) Connectinterfaceharnessto fuel calibrationtest set,fuel quantity indicator,and main
harness.
(16.) Add 3 gallonsof fuel at tip tank filler point. Wait 15 minutesfor fuel to settle in the wing.
(17.) Set both interfaceharnessswitchesto NORMposition.
(18.) Set fuel quantityindicatorto read 0 lbs by adjustingpot markedEMPTYLEFTon back of
indicator.
(19.) Set NORM/SIMswitch on interfaceharnessto SIM position. Set MEAS/SIMswitchon
fuel calibrationtest set to SIM position.
(20.) Determinecapacitancevalue necessaryto makefuel quantityindicatorread0 lbs as
follows:
NOTE: Do not adjust EMPTYLEFTpot on back of fuel quantityindicator.
(a.) Turn FINE SET knobon test set until fuel quantityindicatorreads 0 lbs. Set MAIN
CAPACITANCEswitch as required.
(b.) Set MEAS/SIMswitchto MEASposition.
(c.) Set MEASINT/MEASEXT switchto MEASINT position.
(d.) Recordcapacitancevalue (in pF) on test set gauge.
(21.) Add 118.0pF to capacitancevalueobtainedin step (20.)(d.).
(22.) Set MEAS/SIMswitchto MEASposition. Set MEASINT/MEASEXT switch to MEAS INT
position.
(a.) Turn FINETEST knobon test setuntil capacitancevalue on test set gauge equals
capacitancevalue obtainedin step (21.).
(b.) Set MEAS/SIMswitchto SIM position.
(c.) Set fuel quantity indicatorto read 1950 lbs by adjustingFULLLEFTpot on backof
fuel quantity indicator.
EFFECTIVITY:
Jan
Jan
10/90
28-40-00
28-40-00
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Indicating(continued)
CHART 501
TANK UNIT CAPACITANCE(DRY)
Piper Part No.
Ragen Part
Number
Capacitance (pF)
Tolerance (pF)
Tip
07545-07
76-161-6
17.66
±1.76
Main(Inbd)
07545-02
76-161-1
20.65
+ 2.06
Main (Outbd)
07545-03
76-161-2
18.42
± 1.84
Outboard
07545-04
76-161-3
31.60
±3.16
Nacelle
07545-06
76-161-5
59.63
± 5.96
Aft
07545-05
76-161-4
18.72
+ 1.87
Unit Location
Full Left
Full
-
EmptyRight-
Empty Left
Fuel GaugeAdjustment
Figure503
EFFECTIVITY:
040-999
11
PAGE
28-40-00Jan
10/90
28-40-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Indicating(continued)
7. Fuel QuantitySystemCalibrationTestsand Adjustments(continued)
(a) Dry CalibrationProcedure(continued)
(23.) Set NORM/MEASswitchand NORM/SIMswitch on interfaceharnessto NORM position.
Ensuretest set gauge reads 0.0 pF. If not, repeatsteps (17.) thru (22.). If readingof 0.0
pF is still not attained,replacefuelquantity indicator.
(24.) Disconnecttest set,interfaceharness,and adapterharnessesfrom left main harnessand
fuel quantityindicator. Connectleft main harnessto fuel quantity indicator.
(25.) Disconnectright main harnessfrom fuel quantityindicator.
(26.) Repeatsteps (7.) thru (23.) for right fuel systemcalibrationcheck.
(a.) In step (7.), replaceadapterharnesseswith adapterharnessesused for testing right
fuel system.
(b.) In step (18.) and note in step (20.),replaceEMPTYLEFTpot with EMPTYRIGHT
pot.
(c.) In step (22.),replaceFULLLEFTpot with FULLRIGHTpot.
(b) Wet CalibrationProcedure:
CAUTION ENSURETHATTHE WEIGHTOF THE FUEL IS ACCURATEBEFORE
ADJUSTINGFUELQUANTITYINDICATOR.(EXAMPLE:300 U.S. GALLONS
OF JET-A FUELAT 75°F WILLWEIGH2000 LBS.,WHILE305 U.S. GALLONS
OF JET-A AT 100°FWILLALSO WEIGH2000 LBS.
CAUTION: VERIFYEMPTYSETTINGAND REPLACEGAUGEIF FULLSETTINGMUSTBE
ADJUSTEDMORETHAN± 50 LBS.
(1.) Drain both fuel systems.
(2.) Add fuel to each wing and nacellein 500 lb incrementsuntil all tanks are full. Recordfuel
quantity gauge readingsfor each increment(500, 1000, 1500,and full).
(3.) Ensure readingsagreewith tolerancesas shownin Chart502. If a differencegreaterthan
the tolerancesshownoccurs, repeatthe wet calibrationprocedure.
(4.) If a differencein readingsstill persistsafterthe secondwet calibration,checkthe fuel
sensors per step (15.) of dry calibrationprocedurefor both fuel systems (if previouslynot
done). If step (15.) of dry calibrationprocedurehas been performed,replacefuel quantity
indicatorand calibratefuel quantitysystem.
CHART 502
WET CALIBRATIONTOLERANCEREADINGS
Amountof Fuel (lbs)
500
1000
1500
2000 (Full)
Tolerance (lbs)
± 50
± 50
± 75
±100
EFFECTIVITY:
040-999
Jan10/9028-40-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Indicating(continued)
CHART 503
FUELQUANTITYCALIBRATIONWORKSHEET
FUEL QUANTITY CALIBRATION DATA
DATE
AIRPLANES/N
TECHNICIAN(S)
TEST SET BARFIELD 2548 - G / - GA S/N
PROCEDURE
L.L.SIDE
pF.
pF.
DRY
3 GAL/SIDE
ADJ LOW
R. SIDE
(WAIT 15 MINUTES FOR SETTLING)
LB.
ZERO
FOR
ZERO
SIMULATE 1870 LBS.
FOR
110.0
pF.
1870
LB.
LB.
pF.
pF.
SYSTEM CAPACITANCE
ADJUST HIGH
FOR
FOR
110.0
pF.
1870
LB.
500 LB OF FUEL
LB.
LB.
1000 LB OF FUEL
LB.
LB.
1500 LB OF FUEL
LB.
LB.
EL
FULL OR 2000 LB OF FUEL
LB.
LB.
EFFECTIVITY:
040-999
28-40-00
PAGE
13
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating (continued)
GroundLead
SensorFlange-
I
- Ground Post
I
I
I
I
I
I
Sensor
I I
Test
36
I
II II
I
I
I
- Convenient
I
-Insulated
Surface
6"
1.70" Dia.
NOTE: 1. DimensionsApproximate
2. Boxhas Only 5 Sidesas Shown
3. UnderTest Conditions,Box Mustbe
Insulatedfrom GtoundwithGround
PostConnectedto Shieldof H1ZCoax
Test Cableand Flangeof Sensor
UnderTest.
Fabricationof Test Fixture for Tank Unit Testing
Figure 504
EFFECTIVITY:
040-999
Jan 10/90
28-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Indicating
(continued)
8. Testof AutomaticFuel PumpSystem
NOTE: Referto chapter73 for furtherinformationon test and adjustmentof fuel pressure
transmitterand gauge.
for accuracywitha Barfieldtesterbeforecontinuing.
(a) Checkgaugeandits pressuretransmitter
If gaugeisdefective,replacewithserviceable
unit.
isasfollows:
existto checkthissystem.Thecrossfeedprocedures
(b) Twoprocedures
valve.
(1.) Closefirewallshutoffvalveof systemnotbeingtested.Opencrossfeed
(2.) Turnon batterymasterswitch.Placepumpswitchof systembeingtestedin autoposition.
(3.) Turnon oppositefuelpumpuntilfuelpressurerisesabove20 psi andshutpumpoff. As
fuelpump
lightandsubmerged
fuel pressuredecreasesbelow15± 2 psi,annunciator
mustcomeon. Iftheycomeon beforeorafter15+ 2 psi,replacegauge.
(4.) Turnall switchesoff.
(c) Anothercheckprocedureis to start appropriateengineand proceedas follows:
(1.) Positionpump switchin auto and shutenginedown. As fuel pressuredecreases,
submergedfuel pump and annunciatorlight mustcomeon at 15 + 2 psi. If theycome on
beforeor after 15 + 2 psi, replaceinstrument.
EFFECTIVITY:
28-40-00Jan
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER29
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
29-EFFECTIVITY
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LISTOF EFFECTIVEPAGESJan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER29 - HYDRAULICPOWER
TABLEOF CONTENTS
SUBJECT
CHAPTER
PAGE
29-00-00
General
HydraulicSystemFailure
Fault Isolation
1
1
2
29-10-00
Main
FlushingHydraulicSystem
HydraulicSystemOperationalChecksUsingPiperTest Unit
HydraulicTest Unit (Optional)
ConnectingTestUnit
CyclingLandingGear
CheckingLandingGear CycleTime
CheckingTime DelayValve
CheckingHandleReleaseto Neutral
CheckingPriorityValve
CheckingMain ReliefValve
CheckingHand PumpReliefValve
CheckingFor SuctionAir Leakage
DisconnectingTest Unit
Removalof HydraulicPowerPack
Installationof HydraulicPowerPack
Disassemblyof Power Pack
Assemblyof Power Pack
Cleaning,Inspectionand Repairof PowerPack
Assemblyof Reservoir
TestingReservoirfor Leakage
Disassemblyof Manifold
Assemblyof Manifold
Installationof Manifold
Disassemblyof PowerPack HandleReleaseMechanism
Assemblyof PowerPack HandleReleaseMechanism
Adjustmentof Power Pack Handle-ReleaseMechanism
Operationof Gear SelectorHandleMechanism
Inspectionof GearSelector Handle
Adjustmentof Gear SelectorHandleMechanism
Disassemblyof SpringCartridgeAssembly
Disassemblyof Main ReliefValve
Assemblyof MainRelief Valve
Adjustmentof Main ReliefValve
Disassemblyof PriorityValve
Assemblyof PriorityValve
Adjustmentof PriorityValve
Disassemblyof Time DelayCheck Valve
Assemblyof Time Delay CheckValve
1
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EFFECTIVITY:
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CONTENTSJan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER29 - HYDRAULICPOWER
TABLEOF CONTENTS(continued)
SUBJECT
CHAPTER
PAGE
29-10-00 (continued)
Main (continued)
Disassembly
of DoorVentValve
Assembly
of DoorVentValve
Adjustment
of DoorVentValve
Disassembly
of VentFilter
Assemblyof VentFilter
Disassembly
of Standpipe-Filter
Assemblyof Standpipe-Filter
Disassembly
of HandPumpCheckValve
Assemblyof HandPumpCheckValve
Disassembly
of HandPumpReliefValve
Assemblyof HandPumpReliefValve
Adjustment
of HandPumpReliefValve
Disassembly
of HandPumpSuctionScreen
Assemblyof HandPumpSuctionScreen
Adjustment
of DoorSolenoidValve
Disassembly
of TimeDelayCheckValve
Assemblyof TimeDelayCheckValve
Installation
andAdjustment
of InboardGearDoorsSwitch
PowerPackBenchTestAdjustment
BleedingtheHydraulicSystem
Removaland Installation
of HydraulicLines
Removaland Installation
of HydraulicFilters
Replacement
of FilterElements
HydraulicPumpOperational
Check
Procedure
afterHydraulicPumpFailure
Removalof HydraulicPump
Disassembly
of HydraulicPump
Assemblyof HydraulicPump
Cleaning,Inspection,
Repairof HydraulicPump
Installation
of HydraulicPump
PrimingHydraulicPump
HandPump(Emergency)
Disassembly
of HandPump
Assemblyof HandPump
Cleaning,Inspection,
andRepairof HandPump
Installation
of HandPump
BleedingHandPump
HandPumpTest
23
23
23
24
24
24
24
24
24
24
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EFFECTIVITY:
040-999
Jan
10/9
0 CONTENTS
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
HydraulicPower
A. General
Thehydraulic
powerpackprovidesthe hydraulic
powerrequired
to operatethelandinggear. The
powerpackis locatedin the rightsideof thefuselagenosesectionat BulkheadStation57.00in front
of theforwardpressurebulkhead.Thepowerpackis operatedby a flexibleshaftwitha selectorlever
fashionedlikea wheelmountedon theinstrument
panelleftof theenginecontrolquadrant.Thepower
packcontainsthesystemreservoirandassortedvalveswhichcontrolthesystemoperation.The
withtheenginedrivenpumps,solenoidvalves,andhydraulic
powerpackworksin conjunction
cylindersto performthedesiredoperationsequence
selectedwiththecontrolleverin thecockpit.
WARNING: TO ENSURELANDINGGEAR DOESNOT MOVETO THE UP (RETRACTED)
POSITIONWHILEAIRCRAFTIS ON GROUND,THE FOLLOWINGCHECKMUST BE
PERFORMEDPRIORTO APPLYINGHYDRAULICPRESSURETO SYSTEM.
ATTEMPTTO MOVE SELECTORLEVERTO UP POSITION. IF LEVERCAN BE
MOVEDTO UP POSITION,AN IMPROPERLYADJUSTEDSELECTORMECHANISM
EXISTSOR ANTI-RETRACTION
SYSTEMIS INOPERATIVE.BE SURETO SELECT
GEAR DOWNPRIORTO APPLYINGSYSTEMPRESSUREOR STARTINGENGINE.
Duringan electricalfailure,thedoorsolenoidvalvein thepowerpackmoves(springpressure)
to
OPENdoorpositionandremainsin thatposition.Doorswillnotopenuntilselectorleveris movedto
geardownpositionandgearextensioncycleis started.
WARNING: PRIORTO ANY CHECK OF HYDRAULICSYSTEM,PLACEAIRPLANEON JACKS
(REFERTO 7-10-00).
B. HydraulicSystemFailure
without
Emergency
useof handpumpto extendgearsindicatesenginedrivenpumpsareoperating
sufficientfluid. Thisconditioncausesadditional
wearon enginedrivenpumps.Removeandcheck
filterelementsevenif pumpfailureis notapparent.
1. Remove
filterelements.Checkfor metalparticles.
2. If no metalparticlesexist,replacefilterelementandreplenish
fluid.
3. If metalparticlesareevidentin eitherfilter,proceedasfollows:
(a) Inspect,replace,or repairbothhydraulic
pumps.
(b) Primepumpsanddo notconnectpumpsto restof hydraulicsystemuntilsystemisflushed.
(c) Proceedto flushsystem.
SystemFailurefaultisolations,
placeairplaneon jacks(referto 7-10-00)andperforma
ForHydraulic
systemoperational
check.
NOTE: If hydraulicsystemis servicedproperly,hydrauliccomponentsused in this airplane
manufacturedby the Wieble ToolCompanydo not requireoverhauluntil 10,000 hoursof
serviceor 10 years,whichevercomesfirst. If any problemsarise during inspection,corrective
action mustbe taken regardlessof time in service
EFFECTIVITY:
29-00-00
29-00-00
29-00-00JanPAGE
10/90
1
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. HydraulicSystemFailure(continued)
CHART 1
FAULTISOLATION(HYDRAULICSYSTEM)
Fault
LandingGearsystem
failsto operate.
Cause
Remedy
Selectorleverdisconnected.
Connectlever.
Selectleveroutof
adjustment.
Adjust lever.
CAUTION: PULL CIRCUITBREAKERSOF THE ICE PROTECTIONCIRCUITAND THE STALL
WARNHEATCIRCUITBEFOREDEPRESSINGTHE "q" SENSOROVERRIDESWITCH
TO AVOIDDAMAGINGTHE HEATINGELEMENTS.
NOTE: A solenoidoperatedlock,locatedbehindtheinstrument
panelaspartof the selectorassembly,
preventsleverfrombeinginadvertently
movedto theup positionwhiletheairplaneis onthe
groundor in flightbelow100± 4 KIAS.Tocyclethegearwiththe airplaneon jacks,depressthe
q sensoroverrideswitchunlockingthegearselectorhandle.Thegearcannowbeoperatedas
required.
Hydraulicfluid reservoir
belowoperatinglevel.
Fill the power packwith
hydraulicfluid.
Leakor obstructionin
hydrauliclines.
Checkthe systemwith
hydraulictest unit or
hand pump.
Internalleakagein main
reliefvalve.
Checksystemoperation.
Internalleakagein hand
pump relief valve.
Checksystemoperation.
EFFECTIVITY:
040-999
Jan 10/90 29-00-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. HydraulicSystemFailure(continued)
CHART 1
FAULTISOLATION(HYDRAULICSYSTEM)(continued)
Fault
Gearoperatesabnorrmally
slowor partially.
Selectorhandleretunns
to neutralbeforecycle
is complete.
EFFECTIVITY:
040-999
Cause
Remedy
Low fluid level.
Fill p owerpack with
hydr aulicfluid.
Leakingor kinkedline.
Repl aceline.
Internalleak in cylinder.
airor replacecylinder.
Repa
Priorityvalveout of
adjustmentor leaking.
Check valve operation.
Slow leak in mainrelief
valve. (Enginepump)
Chec
ck systemoperation.
Slow leak in hand pump
reliefvalve.
Check systemoperation.
Extemalleakageat
selectorvalve.
ReplacedamagedO-rings.
One enginepump
inoperative.
Replacepump.
Lowpumppressure.
Replacepump.
Cable,line or obstruction
restrictingthe travel
requiredto fully select
gear up or down.
Check andremove
obstruction.
Selectorleverout of
adjustment.
Adju stcontrol.
cycle
Ifgearcompletes
(redlightout)doorsdo
notclose,batteryoutput
maybe low.
Check voltage.
Time relayvalveand/or
pistonreleaselock out
of adjustment.
Check operation.
Timedelayvalveair
locked.
Bleedair outby holding
selectordownfor 30
seconnds,then makethree
orfo r rapidmovements
to neutralandbackto
dowr.
29-00-00
29-00-00
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. HydraulicSystemFailure(continued)
CHART 1
FAULTISOLATION(HYDRAULICSYSTEM)(continued)
Fault
Gearretractsor extends
beforedoorsopen.
Doorscomeopenin
flight. (Note: Refer
to 32-00-00,
Cause
Priorityvalveleaks in
powerpack.
Checkvalvecracking
pressure.
Solenoidvalvestuck
in closedposition.
Turnoff powerandhand
pumpdoorsopen. (Note:
Withpoweroff solenoid
valveshuttlesto dooropen
andthedoorsmaybe opened
withoutselectinggearup or
down.)
Micro switchon power
pack out of adjustment.
Checkfor loosewire or
mounting,or bent bracket.
Microswitchon power
packoutof adjustment.
Adjust micro switch. (Door
solenoidshouldremain in
door close positionwhen
handlereturnsto neutral.)
Doorsadjustedtootight,
actuatorriotlocking.
Loosenadjustmenton
actuatorrod end.
Faulty limit switch.
Checkall indicatorlights.
Lowelectricpower
supply.
Checkbattery.
Cannonplugon power
packloose.
Tighten.
Solenoidvalvestuckin
dooropenposition.
Checkwiringto solenoid
valve.
Circuitbreakerout.
Checkbreaker.(Note:
Withoutelectricpower,
thegeardoorswillopen
butnotclose.)
Fault Isolation-
(LandingGear)
Chart1.)
Doorsfail to close.
PAGE4
Jan 10/90
29-00-00
Remedy
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. HydraulicSystemFailure(continued)
CHART 2
LEADING PARTICULARS, HYDRAULIC POWER PACK
NOMENCLATURE
OperatingPressure
Main ReliefValvePressure(Primary)
Hand PumpReliefValve Pressure(Secondary)
Hand PumpReliefValve ReseatPressure
Low PressureThermalReliefVent Valve'Open"
Low PressureThermal ReliefVent Valve"Closed"
PriorityValveCrackingPressure
Hand PumpCheckValve CrackingPressure
LandingGear PositionRelease
Time DelayValve
HydraulicFluidRequired
Weight Dry - Power Pack
HydraulicFluidFlow Rate (Both PumpsOperating)
ReservoirOperatingFluidLevel (EnginePump)
(Minimum- Maximum)
ReservoirFluidLevel (Emergency)
(Stand Pipe Level)
WTC 2135-1
(See Note Below)
1900 PSI
1900- 1950 PSI
2025 - 2100 PSI
1900- 1950 PSI
0 to 100 PSI
150 PSI Max.
600 - 650 PSI
1 to 3 PSI
1220- 1250 PSI
3 to 9 seconds
MIL-H-5606
10.00 pounds
1.6 G.P.M.
1.82 - 2.1 pints
1.22 pints
NOTE: Shouldthe values in the textdiffer from the chart values,the chart valuestake precedence.
EFFECTIVITY:
040-999
29-00-00 Jan 1090
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main
1. FlushingHydraulicSystem.
Whenhydraulicsystemis contaminated,drain and flush entire systemto removecontaminated
fluid. Determinecause and type of contaminationand proceedas follows:
(a) Removeenginecowlings(refer to 71-10-00).
(b) Disconnecthydrauliclines at enginedrivenpumps.
(c) Drainhydraulicfluid from powerpack reservoirusing suction,fill, and drain fittingon bracket
locatedat loweraft comer of noseaccesspanelopeningbehind hydraulicscomponentscover.
(d) Disconnecthydrauliclines at actuatingcylindersand drain fluid from all hydrauliclines.
(e) Removeand replacefilter elementslocatedon enginefirewall. Flushout filter bowls.
(f) Flushhydraulicsystemwith clean hydraulicfluid (MIL-H-5606). Examineseveralsealsand
cylinderbores for damage.
(g) Whenhydraulicsystemis completelyflushedand no indicationof contaminationexists,
reconnectpreviouslydisconnectedfittingsand replenishsystemwith clean hydraulicfluid.
(h) Bleed hydraulicsystem(describedin Bleedingthe HydraulicSystem)and checkfor leaks.
(i) Replaceenginecowlings(refer to 71-10-00).
2. HydraulicSystemOperationalChecksUsingPiperTest Unit.
Thetest unit (P/N 753 080) can be usedto checkhydraulicsystems,the hydraulicpowerpack
landinggear cyclingoperation,powerpackoperatingpressurechecks and adjustmentsetc, all
performedwithoutoperatingengines.
The unitconsistsof an electric,motor drivenhydraulicpump, bypassvalve,fluid reservoir,filter,
pressuregauge, hoses, and adapterfittingshousedin a metalcabinet and mountedon casters.
3. HydraulicTest Unit (Optional).
Multi-purposehydraulictest units can alsobe usedto providethe samefunctionsas the Piperunit.
The testunit mustbe capableof duplicatingand monitoringthe operatingpressuresand the flow
rate given in 29-00-00,Chart 2.
NOTE: The followingproceduresarewrittenfor Piperor optionalhydraulictest units. Use proper
operatingmanualfor specificunitbeing used.
4. ConnectingTest Unit.
(a) Removeaccesspanelon right sideof nosesection. Openaccess in hydraulicscomponents
cover.
(b) If systemrequiresfilling only, removeprotectivecap from suction;fill and drain valvemounted
on bracketon lower aft comer of noseaccesspanelopening. Connectpressurehosefrom test
unit. Open valveon suctionport,place controlleverin up position,and proceedto fill system
per instructionswith test unit. Observefill lines so not to overfillreservoir.
(c) If systemis to be operatedduring variousgroundchecks,overhaul,or inspectionof
components,removeprotectivecapsfrom suctionand pressureports, connecttest unit
pressurehoseto pressureport andtest unit suctionhoseto suctionport. Openvalveon
suctionport and operatetest unit accordingto suppliedinstructions.
EFFECTIVITY:
29-10-00
PAGE
1
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A
Main (continued)
Pump - Engine Driven
Filter
Pressure
PortValve
SuctionPort
Toggle Valve
Power Pack Assembly
A. MainReliefValve
B. Engine Pump Check Valve
C. PriorityValve
D. Door Solenoid Valve
E. Vent Valve
F. Time Delay Check Valve
G. Time DelayValve
H. Hand Pump Relief Valve
J. Selector Valve Detent
K. Selector Valve Spring Return
L
Cylinder
Valve
Actuator,Nose Gear
Shuttle Valve
Nose Gear
Shuttle Valve
Main Gear
Shuttle Valve
Main Gear
Un-Lock
Actuator
Un-LockActuator
Actuator Main
Gear Door
ActuatorMain
Gear Door
Actuator
Main
Gear
Cylinder Assembly
Cylinder Assembly
ShuttleValve, Main Gear
Bulkhead Tee & Cap (Test Port)
HydraulicSystem- SchematicDiagram
Figure1.
2
Jan
Jan 10GE
10/90
9-10-00
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main (continued)
GroundGear WarningHorn
Horn Relay
Limit Switch
Bus
Up
MainGear
LimitSwitch (Right)
MainGear
LimitSwitch(Left)
Down
Down
NOTES
1. Gear is showndownand locked,doorsclosed
and selectorhandlein down neutral,poweron.
2. Poweron - doorsclosed
Poweroff - doorsopen
Schematic of Power Pack Electronics System
Figure 2.
EFFECTIVITY:
040-999
29-10-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
2.
5. GearActuating
7. Hydraulic
Pump,Right
9.
HydraulicSystemInstallation
Figure3.
5. Cycling LandingGear.
(a) Connecthydraulictest unit (describedin ConnectingTest Unit) and jack airplane(referto 7-1000).
(b) Set hydraulictest unit bypassvalveopen.
(c) Start test unit pumpmotor.
(d) Place gear selectorhandlein UP or DOWNposition. Slowlyclose bypassvalveuntil system
pressurehas reachedthat specifiedin 29-00-00,Chart2.
(e) Operategear using landinggear controlhandle.
NOTE: If retractionmalfunctiondue to air in systemis expected,follow procedurefor
CheckingLandingGear CycleTime. Gear cyclingtime can be prolongedby slowly
openingthe test unit bypassvalve partway and bleedingoff part of pump flow.
EFFECTIVITY:
PAGE4
29-10-00
Jan 10/90 29-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
5. CyclingLandingGear. (continued)
(f) After completionof cycling,ensure landinggear selectorhandle is in DOWN,neutralposition,
and landinggear is down and locked.
(g) Disconnecthydraulictest unit.
(h) Removeairplanefrom jacks (referto 7-10-00).
6. CheckingLandingGear Cycle Time.
NOTE: The followingtimes, takenusing a singletest unit,can be considerablyreducedby using
two test units, one hookedto eachfirewallfitting. If times are within limitswhen operated
by test unit,but exceed limitswhen operatedby enginedriven pump,either internal
leakage in pump or suctionair leak throughsuctionplumbingsystemto either of the
enginedriven pumpscould exist. (Referto paragraphentitled CheckingFor SuctionAir
Leakage.) If tests indicatea defectivepump, repairor replacedefectivepump. If time
exceedslimit when operatedby eithertest unit or enginedrivenpump, internalleakage
exists in hydraulicsystem. Checkactuatorsfor internalleakageand repairor replace
actuatorsas required. If actuatorsare not defective,powerpack internalleakageexists,
and repairor replacepowerpack.
Whenmalfunctionin hydraulicsystemis suspected,due to slowgear cycle time, it could be
causedby low fluid in airplanereservoircausingsystemto be full of air. The followingprocedure
will purgeair from systemand fill reservoir:
(a) Placeairplaneon jacks (referto 7-10-00).
(b) Cycle landinggear throughtwo completecycles.
(c) Excessivefoam in reservoirindicatesa possibleleak in suctionplumbingwhereair is drawn
intosystem. Check all ground servicesuctionconnectionsfor leaks.
(d) With landinggear extended,placegear handlein full UP position,and recordtime requiredfor
gearto retract and doors to close. Time mustnot exceed9 ± 0.5 seconds,plus time required
for time delay valveto operate.
(e) With landinggear retracted,placegear handlein full DOWNposition,and recordtime required
for gear to extendand doors to close. Time mustnot exceed8 ± 0.5 seconds,plustime
requiredfor time delay valveto operate.
7. CheckingTime DelayValve.
(a) Connecthydraulictest unit (describedin ConnectingTest Unit).
(b) Withtest unit operationaland airplanemasterswitch ON, move landinggear selectorhandleto
DOWNposition. Note delay of handlereturningto NEUTRALposition.
NOTE: Timedelay betweenmovingselectorhandleto down position(with master switchon)
and automaticreleasingof selectorhandleto neutral,must be 3 to 9 secondsat room
temperature. Colder temperaturecausesa longerdelay.
(c) If time delay is not 3 to 9 seconds,ensurevalve is not air locked. Bleedair out by holding
selectordown for 30 secondsand completethree or four rapid movementsfrom neutralto
down.
(d) Replacetime delay valve,if defective.
(e) Disconnecthydraulictest unit.
EFFECTIVITY:
040-999
PAGE
5
29-10-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
8. CheckingHandleReleaseto Neutral.
NOTE: One releasevalvereleaseshandlefrom both gear down and gear up positions. If handle
returnspringsare adjustedproperly,releasevalve must releasehandlefrom both
positionsat samepressure. Thefollowingprocedurescheckreleasepressurefrom gear
down positionand releasepressurefrom gear up position. This is done to assure
satisfactoryoperationof other equipmentrelativeto handlereleaseoperations.
(a) Place airplaneon jacks (referto 7-10-00).
(b) Connecthydraulictest unit (describedin ConnectingTest Unit).
(c) Run landinggear throughtwo completecycles, endingwith gear down and lockedand doors
closed.
(d) Set hydraulictest unit bypassvalvefully open.
(e) Place landinggear selectorhandlefully down.
(f) Close bypassvalve very slowlyuntil handletrips back to neutral. Ensuregauge pressure
readingscomplywith thosein 29-00-00,Chart 2 when handletrips to neutral. Allow timefor
time delayvalve to open.
(g) Set hydraulictest unit bypassvalvefully open.
(h) Place landinggear selectorhandle in full up position.
(i) Close bypassvalve very slowlyuntil handletrips backto neutral. Ensuregauge pressure
readingscomplywith thosein 29-00-00,Chart2 when handleis tripped to neutral. Allow time
for timedelay valveto open.
(j) Adjust handlerelease,if required.
(k) Ensurelandinggear selectorhandleis in down neutralpositionand landinggear is down and
locked.
(I) Disconnecttest unit and removeairplanefrom jacks.
9. CheckingPriorityValve.
(a) Connecthydraulictest unit and place airplaneon jacks (refer to 7-10-00).
(b) Run landinggear throughtwo completecycles.
(c) With gear down and lockedand test unitoperational,turn master switchoff and movegear
handleto down positioncausingdoorsto open and handleto returnto neutral position. Keep
switch off, leavingdoors open,facilitatingcompletionof check.
(d) Open hydraulictest unit bypassvalve.
NOTE: As priority valveopens,nosegear down lock startsreleasing. Readpressuregauge
at that point.
(e) Place landinggear selectorhandlefully up. Closebypassvalvevery slowly,observepressure
gauge of test unit, and note at which pressurereadingpriorityvalveopens. Priorityvalve must
open at 600 - 650 psi, as indicatedin 29-00-00,Chart2.
(f) Make requiredpriority valveadjustments.
(g) Ensurelandinggear selectorhandle is in down, neutralposition,and landinggear is down and
locked.
(h) Disconnecttest unit and removeairplanefrom jacks.
EFFECTIVITY:
040-999
Jan 10/90 29-1
0-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
10. Checkingmain reliefvalve.
(a) Connecttest unit.
(b) Opentest unit bypassvalve.
(c) Hold landinggear selectorhandlein full downposition.
(d) Closebypassvalve slowlyand note pressurebuild-upand point where pressurestabilizeson
testunit gauge. Stabilizationindicatesreliefvalve settingas listedin 29-00-00,Chart 2.
(e) Adjustmentof power pack main reliefvalveis completedwith power pack installedin airplane.
Removetop cover and drain fluid to gain accessto adjustingscrew.
(f) Disconnecthydraulictest unit.
11. Checkhand pump reliefvalve.
(a) Placelandinggear selectorhandle,locatedright of pilot seat underfloor, in full down position.
Withmaster switchoff, extendhandleand operateemergencyhand pump to open landinggear
doors.
(b) Disconnectdooropen line (upperfitting)from maingear door cylinder. Connecthydraulictest
unitpressurehoseto door open line. Capactuatorfitting.
(c) Closebypassvalveon hydraulictest unit.
(d) Operateemergencyhand pump and note at which readingon hydraulictest unit pressure
gauge hand pump reliefvalveopen. Pressuremustbe between2025 - 2100psi (indicatedin
29-00-00,Chart2).
(e) Adjustmentof powerpack hand pump reliefvalve is completedwith power pack installedin
airplane. Removecoverand drain fluid to gain accessto adjustingscrew.
(f) Openbypassvalveon test unit to releasepressure. Disconnecttest unit pressurehosefrom
dooropen line. Removecap from actuatorfitting and reconnectdooropen line to maindoor
actuator.
(g) Replenishrequiredhydraulicreservoirfluid.
12. Checkingfor SuctionAir Leakage.
(a) Removeenginecowlingfor access.
(b) Disconnecthydraulicpump suctionhose from pump. Connecttest unit suctionhoseto airplane
suctionhosewith suitablefitting.
(c) Disconnecthydraulicpump pressurehosefrom pump. Connecttest unit pressurehoseto
airplanepressurehosewith suitablefitting.
(d) Connecttest unit electricalcable to electricalpowersource.
(e) Jack airplaneand cycle landinggearthroughfive completecycles.
(f) Checktest unit reservoirfor air bubblesindicatingleakagein suctionline, hose,or fittings.
Replacedefectiveparts.
NOTE: If replacementparts eliminatevisibleair in test unit reservoir,but air still enters
hydraulicsystem,enginedrivenpump maycontainsuctionleak.
(g) Ensurelandinggear selectorhandleis in down, neutralposition,and landinggear is down and
locked.
(h) Removeairplanefromjacks. Disconnecttest unit.
EFFECTIVITY:
040-999
29-10-00
PAGE
7
0 Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
13. DisconnectingTest Unit.
(a) Ensurelandinggear selectoris in the down,neutral position,and the landinggear is down and
locked.
(b) Shut off test unit per instructionsuppliedwith unit.
(c) Closesuction-fill-drainvalvein airplaneby placingcontrolleverin down positionand
disconnectingtest unit hosefrom fitting. Installprotectivecap over fitting. Disconnectand
removetest unit pressurehosefrom pressurefitting in airplane(if previouslyconnected).
Installthe protectivecap on the fitting.
(d) Checkfluid level in powerpack reservoir. Check systemfor leaks.
(e) Closeaccess in hydrauliccomponentscover. Installaccesspanelon right sideof nose
section.
14. Removalof HydraulicPower Pack. (Figure401)
(a) Removeright accesspanelat nosesectionbetweenStations25.60and 57.00. Completely
removehydrauliccomponentscoverby removingretainingstrips from outer edgesof cover.
(b) Drain powerpack by removingboth drain caps from end of suction;fill and drain plug installed
insideaccessopeningbehindhydrauliccomponentscover. Connectfluid linefrom fittingto
container;raise leverto open valve and drain reservoir.
(c) Disconnectelectricalconnectorat forwardend of powerpack.
(d) Disconnectvent line from powerpack.
(e) Disconnectgear selectorcontrolcable from power packcontrolarm on outboardside of power
pack.
(f) Disconnectvarious hydrauliclines from power pack. Cap open lines to preventcontamination.
(g) Cut safetywire and removeattachmentbolts securingpowerpackto mountingbrackets.
(h) Movepower packforwardand out accessopening.
15. Installationof HydraulicPowerPack. (Figure401)
(a) Positionpower pack in mountingbrackets. Ensurepowerpack controlarm is facing outboard;
securepower pack and bracketsupportsto mountingbracketswith bolts and safety.
(b) Uncapand connectvarious hydrauliclines to powerpack.
(c) Connectelectricalconnectorto forwardend of powerpack and connectlandinggear selector
cable to selectorarm.
(d) Fill power pack (referto 12-10-00).
(e) Bleedhydraulicsystem per instructionsin this chapter.
(f) Close hydrauliccomponentscover. Replaceaccesspanel on side of airplanenose section.
NOTE: Readjustgear selectorcable removedfrom support.
EFFECTIVITY:
040-999
Jan10/9029-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
5.
PowerPack Installation
Figure401.
EFFECTIVITY:
040-999
9
29-10-000 JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
1. DrainFitting
2. MainReliefValve
3. PriorityValve
4. Filter,Hand
PumpSuction
PumpReliefValve
TimeDelayCheckValve
Locationof PowerPack Components
Figure402
EFFECTIVITY:
040-999
Jan
1090 29-10-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
16. Disassemblyof Power Pack. (Figure403)
After powerpack is removedfrom airplaneand all ports are cappedor plugged,spraywith
cleaningsolvent(FederalSpecificationsP-S-661,or equivalent)to removeall accumulateddust or
dirt. Drywith filteredcompressedair. Todisassembleunit,proceedas follows:
(a) Removewire, nut, reservoircover,and O-ring. Sincecover is a snugfit on reservoir,use soft
malletand tap cover lightlyto remove.
(b) Removesnap ringfrom center stud. Removebaffleplatefrom reservoir. Drain remaining
hydraulicfluid from reservoir.
(c) Removereservoirand O-ring. Reservoiris a snugfit in body and requireshard pull to
disengage.
(d) Removecenter studand O-ring.
NOTE: All electricalwires are colorcoded. Ensurecoloredwires matchwhen wires are
reinstalled.
(e) Removescrews,washers,switchassembly,and insulatingplate. Switchwill remainhanging
from electricalwires (Figure404).
(f) Removeplasticstrap attachingelectricalwires to door solenoidvalve. Removesafety wire
from door solenoidvalve (Figure404).
(g) Disconnectswitch and door solenoidelectricalwires from terminalblock.
(h) Removefour bolts attachingmanifoldassembly. Separatemanifoldassemblyfrom power
pack,being sure not to lose transfersleevesbetweenmanifoldand power pack (Figure404).
(i) Removefive transfersleevesfrom manifold(Figure404).
NOTE: Whenmanifoldis separatedfrom powerpack body,teeth on landinggear selector
spoolbecomedisengagedfrom gear and permitselectorspool to move. Nevermove
selectorspoolto a positionmorethan flush with manifoldbody at end opposite
selectorspoolteeth. If movedbeyondthis position,an O-ring will get caughtand
selectorspoolwill be difficultto remove.
17. Assemblyof PowerPack.
(a) Referto Cleaning,Inspectionand Repairof PowerPack priorto assembly.
(b) Use new O-ringsand gasketsduring assembly.
(c) Lubricateall O-ringswith petrolatum(per W-P-236 or equivalent)duringassembly.
(d) Lubricateall threadedsurfacesof all valves in powerpack with MIL-G-7711grease or
equivalentbefore installing.
NOTE: Whenpositioningreservoircover,ensureventfitting points to right when powerpackis
installedin airplane. Also,when installingreservoircover,ensurelarge O-ringis not
beingpinched.
(e) Installreservoircover on reservoir,securewith nut, and torque to 35 inch-pounds. Safetynut
to reservoircover using safetywire.
EFFECTIVITY:
040-999
10/90
29-10-00Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
36
NOTE: Theshadedparts,poppet(6)andpoppet
seat(7)are matchedpartsandmustbe
replacedas an assembly.
0-55
56
--57
HydraulicPowerPack
Figure403(Sheet1 of 2)
PAGE12 29-10-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
1.
2.
3.
4.
5.
6.
7.
8.
9.
Main ReliefValve
AdjustingScrew
Spring
Button
Body,ReliefValve
Poppet
PoppetSeat
Backup
O-Ringl
10. Priority Valve
11. AdjustingScrew
12. Spring
13. Button
14. Body,PriorityValve
15. Backup
16. O-Ring
17. Backup
18. O-Ring
19. Poppet
20. PoppetSeat
21. O-Ring
22.
23.
24.
25.
Fitting
Nut
Backup
O-Ring
26.
27.
28.
29.
30.
31.
32.
33.
34.
35.
Door Vent Valve
AdjustingScrew
Spring
Stem
Retainer
O-Ring
Piston
Wire, Safety
Body,VentValve
O-Ring
36.
37.
38.
39.
40.
Nut
Cover, Reservoir
Wire, Safety
O-Ring
Fitting
41.
42.
43.
44.
45.
46.
47.
48.
49.
50.
DeflectorPlate
Filter,Vent
SnapRing
O-Ring
CenterStud
SnapRing
BafflePlate
O-Ring
Reservoir
O-Ring
51. Hand Pump Suction Filter
52. SnapRing
53. Filter,Hand Pump
79.
80.
81.
82.
83.
84.
BracketAssembly
Bracket
Plug, Electrical
Screw
Washer
TerminalBlock
85.
86.
87.
88.
89.
90.
91.
Spring Cartridge
Snap Ring
Button
Spring
Plunger
Body,HandleRelease
Screw,Stop
54. Hand Pump Relief Valve
92.
55. AdjustingScrew
93.
56. Spring
94.
57. Stem
95.
58. Body,SecondaryReliefValve 96.
59. Ball
97.
60. Seat
98.
61. O-Ring
99.
Hand PumpCheckValve
Fitting
O-Ring
Backup
O-Ring
Poppet
Spring
Guide
100. Snap Ring
62. Time Delay Check Valve
63. Snap Ring
64. O-Ring
65. Seat
66. Bal
67. Spring
68. Body,CheckValve
69. O-Ring
101. Fitting
102. O-Ring
103. Standpipe-Filter
104. Fitting
105. Nut
106. Backup
107. O-Ring
70. Body
71. O-Ring
72. Backup
73. Nut
74. Fitting
75. Bolt
76. Washer
77. Bolt
78. Washer
HydraulicPowerPack
Figure403 (Sheet2 of 2)
EFFECTIVITY:
040-999
29-10-00 Jan
PAGE
13
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
18. Cleaning,Inspectionand Repairof PowerPack.
(a) Discardall old O-ringsand gaskets.
(b) Removeline fittingscaps, wash all parts in dry cleaningsolvent(FederalSpecificationP-S-661,
or equivalent),and dry with filteredcompressedair.
NOTE: Duringinspectionand until power pack is reassembled,keepparts as clean as
possible. After cleaningparts, placeon clean surfaceand cover with clean cloth.
(c) Inspectall parts for scratches,scores,chips,cracks,and excesswear.
(d) Use partscatalogto obtain properreplacementparts for powerpack.
19. Assemblyof Reservoir. (Figure403)
(a) LubricateO-ring (MS28775-009).Installonto top center stud.
(b) Installcenter stud intobody (PPN 762-589).
(c) Lubricatetwo reservoirO-ringsand install.
(d) Push reservoirintobody.
(e) Dropbaffleplate into reservoir. Secureby placingsnap ring into center stud.
20. TestingReservoirfor Leakage. (Figure403)
(a) Removedrain fitting. Attachtest hand pump with 200 psi gauge to drain port.
(b) Removecapfrom reservoirvent fittingat top of reservoir.Operatehand pump until reservoiris
completelyfull. (Indicatedby fluid coming out of vent fitting.)
(c) Cap reservoirventfitting.
(d) Operatetest hand pump to raisepressurein reservoiruntil pressuregauge indicatesmaximum
50 psi.
(e) Checkfor leaksand ensure no externalleakageis found.
(f) Crackvent fitting to releasepressure,removetest equipment,drain reservoirand cap fittings.
(g) Installhydraulicpowerpack in airplane.
21. Disassemblyof Manifold. (Figure404)
(a) Unscrewdoor solenoidfrom manifold. Removeplungerreturnspring.
(b) Removepin; removeplungerfrom spool by carefullypullingit from manifold.
(c) With hookmade from a brassweldingrod, withdrawtransfersleevefrom manifoldby inserting
hook intooil hole in transfer sleeve.
NOTE: Ensureend of hookis not over 0.06 incheslong. Use hookcarefullyto prevent
scratchingbore in manifold. The sleeveis difficultto withdrawdue to O-ringfriction.
(d) Removescrew,spring, and time delayplungerby insertingsmall woodendowel in center of
plunger.
(e) Removelandinggear selectorspoolby graspingrack (teeth)end of spool and pulling it from
manifold.
NOTE: Do not bend but pull selectorspool straightout. The landinggear selectorspool,time
delay plungerand manifoldare matched,lappedparts and mustbe replacedas an
assemblyonly.
EFFECTIVITY:
040-999
PAGE
190 29-10-00
Jan 10/90
PIPER AIRCRAFT
PA42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main (continued)
NOTE: The shaded parts, time delay plunger (2), landing
gear selector spool (19) and manifold (35) are
matched, lapped parts. It it is necessary to
replace any of these parts, replace them with a
matched assembly containing (2), (19) and (35).
Shaded parts, transfer sleeve (7), and spool (10)
are also matched and lapped parts and must be
replaced by a matched assembly containing (7)
and (10).
12.
47
1314.
42
46
1.
2.
3.
4.
5.
Time Delay Valve
Plunger,TimeDelay
Spring
O-Ring
Screw
17.
18.
19.
20.
Landing GearSelector Spool
O-Ring
Spool,LandingGear Selector
O-Ring
9. Door Selector Spool
10. Spool, DoorSelector
21.
22.
23.
24.
25.
26.
HandleDetent Assembly
O-Ring
Plunger
O-Ring
Spring
Retainer
11. Door Solenoid ValveAssembly
12. Solenoid,Door
13. O-Ring,Solenoid
14. Spring, PlungerReturn
15. Plunger
16. Pin
27. O-Ring
28. Fitting
29. O-Ring
30. Backup
31. Nut
32. Fitting
6. Transfer Valve
7. Sleeve,Transfer
8. O-Ring,Sleeve
33. O-Ring
34. Fitting
35. ManifoldAssembly
36. Sleeve,Transfer
37. O-Ring
38.
39.
40.
41.
O-Ring
Backup
Nut
Fitting
42.
43.
44.
45.
46.
Bolt
InsulatingPlate
Switch Assembly
Washer
Screw
47. Wire, Safety
48. Strap, Plastic
PowerPack Manifold
Figure404
EFFECTIVITY:
040-999
29-10-00 Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
A. Main (continued)
21. Disassembly
of Manifold.(Figure404) (continued)
(f) Removelandinggearhandle-release
retainer,spring,andplungerfrommanifold.Theplunger
end hasa ballwhichmustremainin place.
PS-661or
(g) Removecapsandfittings;washmanifoldin cleaningsolvent(FederalSpecification
air. Ensureinternalpassagesareclean.
equivalent)anddrywithfiltered,compressed
Reinstallcapson fittings.
22.Assemblyof Manifold.(Figure404)
(a) LubricateandinstallO-ringon landinggearselectorspool. InstallO-ringintomanifoldat
oppositeend.
NOTE: Thelandinggearselectorspool,timedelayvalveplunger,andmanifoldare matched,
lappedparts,andmustbe replacedas an assemblyonly.
(b) Insertselectorspoolintomanifoldfromlandinggearhandleendof manifold.Insertonlyuntil
0.06inchoutmanifoldend.
approximately
selectorspooltaperis protruding
NOTE: If selectorspoolis notprotruding
approximately
0.06inchoutof manifold,opposite
rack,wheninstallingintobody(seeFigure405),gearwill notengagein proper
position.Donotmoveselectorspoolmorethan0.12inchoutof manifold,opposite
rack. TheO-ringcouldgetcaughtanddamaged,necessitating
replacement.
(c) Ensurelandinggearselectorspoolslidesfreely.
(d) Ensuredoorsolenoidspoolmovesfreelywithintransfersleeve.
NOTE: Thespoolandtransfersleeveare matched,lappedpartsandmustbe replacedas an
assemblyonly.
(e) LubricatefourO-ringsandinstallontransfersleeve.
(f) Installtransfersleeveintomanifold.
(g) Attachplungerto doorselectorspoolwithpinandinstallintotransfersleeve.
1. Manifold
2.Gear
3. ReturnCam
Indexingof SelectorSpool
Figure405
PAGE16 29-1000
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
22. Assembly
of Manifold.(Figure404) (continued)
andinstallon solenoid.
O-ring(MS28775-018)
(h) Lubricate
(i) Lubricate
doorsolenoidthreads,insertplungerreturnspringintoplungercavity,andscrew
assemblyintomanifold.Torqueto 70 inch-pounds.
(j) Installtimedelayplungerandspringintomanifold.
O-ring,installontoscrew,andmounttimedelayassemblyintomanifold.Screwmust
(k) Lubricate
beflushwithoutsideof manifold.
23. Installation
of Manifold.(Figure404)
(a) LubricateO-ringsandinstallon fivetransfersleeves.
(b) Inserttransfersleevesintomanifold.
(c) Matemanifoldto powerpackbody,beingsurenotto damageO-ringson transfersleeves.
NOTE: Whenmatingmanifoldwith powerpack body,index landinggear selectorspool rack
with inputshaftgear (Figure405). With landinggear selectorspool protruding0.06
inchfrom face A of manifoldand inputshaft returncam in horizontalposition,tooth of
inputshaft gear must matchwith tooth space in landinggear selectorspool rack.
(d) Installfour manifoldattachingbolts and torqueto 35 inch-pounds.Do not over torquebolts,
causingbindingof landinggear selector spool.
(e) Lubricateand install O-ring (MS 28775-010)on bottomof plungerand O-ring (MS 28775-008)
on top of plunger.
(f) Installplungerand lubricatedspringinto manifold.
(g) Lubricatethreadsof retainer,installinto manifold,torqueto 25 inch-pounds,and safetywire
retainerto manifold.
24. Disassembly
of PowerPackHandleReleaseMechanism(Figure406)
(a) Removelockwireretainingrollpinin inputshaftandarm.
(b) Usinga punch,driverollpin outof armandshaft. Removearm.
(c) Usinga punch,drivepinoutof returncam. Removereturncam.
frompowerpack.
(d) Pullinputshaftassembly
25. Assembly
of PowerPackHandleReleaseMechanism.(Figure406)
frominputshaft,partsmustbe assembled
(a) If switchcam,gear,anddetentcamwereremoved
andindexed(Figure406,ViewA).
(b) Lubricateinputshaft,slidedetentcamandgearintoplace,andsecuregearwith rollpin.
(c) Slideswitchcamontoinputshaft;securewithrollpin. Installassemblyintopowerpackbody.
(d) Installreturncamandsecurewithroll pin. Ensurelandinggearshaftmovesfreelyin power
packbody. Checkfor slightendplaybetweeninputshaftandpowerpackbody. If shaftbinds,
removereturncamlapfaceof returncamboss;reinstallreturncam.
(e) Installpowerpackcontrolarmon shaftendwitharmpointingdown.Alignholesbetweenshaft
andarmassemblyandinstallrollpin. Install0.041inchsafetywirethroughrollpin andaround
halfof arm. Pulltwistedendof safetywirearoundotherhalfof armassembly(Figures407).
EFFECTIVITY:
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main (continued)
3. Gear
5. Cam Detent
-11. Lockwire
-9. Arm
1. CamSwitch
-8. Pin
View A
— 6. Shaft Input
7. ReturnCam
Detent
Shaft InputAssembly
Power Pack Handle Release Mechanism
Figure 406
MS20995C41
SafetyWire-
SafetyingControlArms
Figure407
EFFECTIVITY:
040-999
Jan
29-10-00
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
26. Adjustmentof PowerPack HandleReleaseMechanism (Figure501)
The followingprocedureoutlinesadjustmentsfor setting handlereleasecartridges,stoppingthem
in correctpositionbefore installingpowerpack intoairplane.
(a) Rotateinputshaft into gear UP detent position. Adjust left stopscrewto allow slightovertravel
pastdetent position.
(b) Rotateinputshaft into gear DOWNdetent position. Adjust right stopscrewto allowslight
overtravelpast detent position.
(c) Rotateinputshaftto neutralposition,bringinginputshaft returncamto horizontalposition.
(d) Hold inputshaft returncam in horizontal(neutral)positionby inserting0.125 inch diameterdrill
or punchthroughhole in arm and into rigginghole in body. (Rigginghole A, Figure501.)
Adjusthandlereturncartridgesso returnplungerballs barelytouch surfaceof inputshaft return
cam.
CAUTION: REMOVEDRILLOR PUNCHFROMRIGGINGHOLEA.
(e) Ensuredetent holds in both detent positionsand returnswith a positivesnapwhen manually
releasedfrom either position.
9. Stop Screw
2.
Camin HorizontalPosition(Neutral)
8. ReturnPlungerBall
Hole"A'
7. HandleReturnCartridge
HandleReleaseAdjustment
Figure501
EFFECTIVITY:
040-999
29-10-0 Jan
PAGE
19
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main(continued)
27. Operationof GearSelectorHandleMechanism.(Figure408)
Operatinggearselectorhandlemustaccomplish
positiveengagement
withdetent.Withselector
handlein UPor DOWNpositionandin detent,a forceof 3 1/2to 6 pounds,appliedperpendicular
to handlecenterline
at knobcenterline,is requiredto movehandlefromdetentbackto neutral
position.Tocheckoperationof gearselectorhandlemechanism,
placeairplaneon jacks(referto
7-10-00)andoperategearselectorhandlethroughentireup anddowntravel.
15. Safety Wire
8. Pin, Washer and
Cotter Pin
7.
Terminal
.10. MountingBlock
r- 1 1. Solenoid
6. StopPin
5. Sleeve
4. ControlKnob
14 . Bracket
18. Grommet
Assembly
3. Plate Assembly
2. Light Assembly
17. Firewall Plate
1. Panel Assembly
15. Safety Wire
16. Bushing
LandingGear SelectorMechanismInstallation
Figure408
PAGE20 29-10-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
28. Inspection
of GearSelectorHandle
(a) Ensurehandledoesnotcontactslotendsin instrument
panelwhenactuatedto travel
extremes.
(b) Ensureadequate
clearanceexistsbetweenselectorgearmechanism
andwiringharnesswhich
runslaterallyacrossaircraft.
(c) Ensurelocknutsare securelytightenedandall grommets
areproperlyinstalled.
(d) Checkcontrolcableconnections
fromactuatorarmsto powerpackandselectorhandle.
29. Adjustment
of GearSelectorHandleMechanism
(a) Disconnect
landinggearselectorcontrolcablefromselectorhandleandpowerpackcontrol
arm.
(b) Connectspringscaleto controlarm,pullforeandaft perpendicular
to armcenterline,
and
determine
if detentisleftat a forceof 9 + 1 or 2 pounds.If not,releaseat required
forceand
adjustmechanism.
(c) Depressbuttonon solenoidlockto allowselectorhandleto travelfreely.Withselectorhandle
in upor downpositionandin detent,a forceof 3 1/2to 6 pounds,appliedperpendicular
to
handlecenterline
at knobcenterline,
is requiredto movehandlefromdetent.
(d) Positioncontrolarmon powerpackin NEUTRAL
by inserting0.125inchdiameterdrillinto
rigginghole(holeA, Figure501)in controlarmandpowerpackbody.
(e) Placeselectorhandlein NEUTRAL
positionandhold.
(f) Positioncontrolcableto allowequaltravelat bothends.
(g) Adjustterminalendsof controlcableto obtainneutralpositionon bothcontrolarmandselector
handle.
(h) Connectterminalendsof controlcableto powerpackcontrolarmandselectorhandle.
(i) Removedrillfromriggingholein (holeA, Figure501)powerpack.
NOTE:Whenevercableassemblyis removedfromairplaneandreinstalled,
seatcablewhere
it passesthroughpressurebulkheadat Station57.0andsealper51-20-00.
pin(Figure407).
(j) Safetypowerpackcontrolarmattachment
(k) Checkoperationof gearselectorhandlemechanism
asfollows:
(1) Placeairplaneonjacks.
(2) Connecthydraulic
test unit.
(3) Operategearselectorhandlethroughentiretravelandcyclegearbothup anddown.
EFFECTIVITY:
040-999
29-10-
PAGE
21
Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
30. Disassemblyof SpringCartridgeAssembly.(Figure403, Item 81)
(a) Removetwohandlereleasebodiesfrompowerpackbody.
(b) Removesnaprings,buttons,springs,andplungers.
CAUTION: USE CAUTIONWHEN REMOVINGSNAPRINGS;CARTRIDGESARE SPRING
LOADED.
31. Disassemblyof Main ReliefValve. (Figure403, Item 1)
(a) Carefullyremoveadjustingscrew at top of mainrelief valve.
(b) Removereliefvalvebody containingspringand button.
(c) Removepoppet from poppet seat.
(d) Use a brass hook,not over 0.125 inch long,and pull poppet seatup and out of powerpack
body. Hookthrough holes insideseatwhile not damagingbore in body.
(e) Reassemblepoppet intopoppet seat.
32. Assemblyof Main ReliefValve. (Figure403, Item 1)
(a) Inspectpoppet and poppet seatfor pittingor score marks. Two parts are matchedparts and
mustbe replacedas assemblyonly.
(b) Lubricateand installO-ring and back up ring on poppetseat. Insert poppet intoseat and install
assemblyinto body.
(c) Lubricatethreads,install reliefvalvebody into powerpack body,and torqueto 70 inch-pounds.
(d) Installbottom and springinto reliefvalve body. Securewith adjustingscrew. Adjustingscrew
providesadjustmentof main relief valveand must be installedflush.
33. Adjustmentof Main ReliefValve. (Figure403, Item 1)
(a) With inputshaft in gear UP or gear DOWNposition,apply pressureuntil fluid flows from main
reliefvalve.
(b) Adjustscrewon top of main reliefvalveuntil valvebegins to open at 1900 - 1950 psi (see 2900-00,Chart2). Bleedpressureaftereach adjustmentby crackingcap on door open fitting.
34. Disassemblyof PriorityValve. (Figure403, Item 10)
(a) Removeadjustingscrewat top of priorityvalve.
(b) Removepriorityvalve body containingspring,button, and poppet.
(c) Use brass hookto removepoppetseat from body. Be careful not to damagebore.
(d) CarefullyremoveO-ring from bottomof cavity.
35. Assemblyof PriorityValve. (Figure403, Item 10)
(a) Lubricateand installO-ring and poppetback up. Insertpoppet into priorityvalvebody.
(b) LubricateO-ring and installinto powerpack body.
(c) Ensurepoppet seat containssharp seatingedge. Lap as requiredto obtainsharp seating
edge. Pushpoppet seat into valvebody,installassemblyinto powerpack body,and torque to
70 inch-pounds.
(d) Installbutton; springand securewith adjustingscrew. Adjustingscrewprovidesadjustmentfor
priorityvalve and mustbe installedflush.
EFFECTIVITY:
PAGE22
Jan 10/90 29-10-00
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
36. Adjustmentof PriorityValve. (Figure403)
(a) Placeinput shaftin gear up position. Removecap fromgear up fitting.
(b) Applypressureand note priorityvalve crackingpressureby observingpressuregauge when
fluid first startsto flow from gear up port.
(c) Adjustscrew until priorityvalvecracksat 600 - 650 psi ( 29-00-00,Chart2). Bleedpressure
aftereachadjustmentby crackingcap on door openfitting.
(d) Disconnecttest unit and cap all open fittings.
37. Disassemblyof Time DelayCheckValve. (Figure403, Item59)
(a) Removecheckvalve bodyfrom powerpack body.
(b) Removesnap ring.
(c) Usinga brass hook,pull out ball seat.
(d) Removeball and spring.
38. Assemblyof Time DelayCheckValve. (Figure403, Item59)
(a) Installspringand ball intocheckvalve body.
(b) Lubricateand installO-ring in seat.
(c) Installseat into checkvalvebody. Securewith snapring.
(d) Lubricatethreads,installO-ringon valve body,mount intopowerpack body,and torqueto 45
inch-pounds.
39. Disassemblyof DoorVent Valve. (Figure403, Item 26)
(a) Removeadjustingscrewfrom top of retainer.
(b) Removevent valve bodyfrom powerpack body.
(c) Removespring and stem.
(d) Cutwire and removeretainerfrom vent valvebody.
(e) RemoveO-ringand piston.
40. Assemblyof DoorVent Valve. (Figure403, Item 26)
(a) Installpiston into vent valvebody.
(b) Lubricateand install O-ringon retainer. Screw retainerinto valvebody;tighten and securewith
0.032 inch safetywire.
(c) Installstem, spring,and adjustingscrewinto retainer,ensuringadjustingscrew is flush.
(d) Lubricatethreads,installO-ring on valve body,and installassemblyintopower packbody.
41. Adjustmentof DoorVent Valve. (Figure403, Item 26)
(a) Removecapfrom dooropen fitting on powerpack. Attachpressurehosefrom hand pump to
doorfitting with 200 psi pressuregauge.
(b) Slowlyapply pressureto ensurefluid seepsfrom door vent valve.
(c) Adjustscrewso fluid flowsfrom vent valveat 0 to 100 psi ( 29-00-00,Chart2).
(d) Increasepressureto 150psi maximum. Ensuredoor vent valveis shutoff. If pressurefalls
below100 psi, fluid mustresumeflowingfrom door vent valve( 29-00-00,Chart2).
(e) Relievepressureby crackinghosefitting from handpump.
(f) Disconnecttest unit. Cap all openfittings.
EFFECTIVITY:
29-10-00Jan
Jan1090
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
A. Main (continued)
42. Disassembly
of VentFilter.(Figure403)
(a) Removesnapringandpulloutfilter.
43. Assemblyof VentFilter.(Figure403)
(a) Installventfilterintoreservoircover.Securewithsnapring.
44. Disassembly
of Standpipe-Filter.
(Figure403)
(a) Removestandpipe-filter
frompowerpackbody.
45. Assemblyof Standpipe-Filter.
(Figure403)
(a) Installstandpipe-filter
intopowerpackbody.
46. Disassembly
of HandPumpCheckValve.(Figure403,Item88)
(a) Removefittingfrompowerpackbody.
(b) Removesnapringfromfitting.
(c) Removeguide,spring,andpoppet.
47. Assemblyof HandPumpCheckValve.(Figure403,Item88)
(a) Installpoppet,spring,andguideintofitting. Securewithsnapring.
(b) Lubricatethreadsonfittingvalve. InstallrequiredO-ringclosestto flangedend.
(c) Installbackup ringandO-ringon fitting.
(d) Installvalveassemblyin body.Torqueto 55 inch-pounds.
48. Disassembly
of HandPumpReliefValve.(Figure403,Item51)
(a) Removeadjustingscrewattop of handpumpreliefvalve.
(b) Removehandpumpreliefvalvebodyby unscrewing
it frompowerpackbody.
(c) Removespringandstemfromvalvebody.
(d) Removeball.
(e) Usebrasshookandcarefullyremoveseatfrombody.Becarefulnotto damagebore.
(f) RemoveO-ringfrombottomof cavity.
49. Assemblyof HandPumpReliefValve. (Figure403,Item51)
(a) LubricateandinstallO-ringintopowerpackbody.
(b) Inspectseatseatingsurface.Seatingedgemustbe sharp.Lapif necessary
to obtainclean,
sharpedge.
(c) Dropballintocavityof handpumpreliefvalvebody. Installballseatintobody,trappingball
betweentwoparts.
(d) Lubricatethreadsandinstallassemblyintopowerpackbody.Torqueto 70 inch-pounds.
(e) Insertstemandspringintovalvebody. Installadjustingscrew.Adjustingscrewprovides
adjustment
for handpumpreliefvalveandmustbe installedflush.
PAGE
24
0
Jan 10/9029-10-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
50. Adjustment
of HandPumpReliefValve(Figure403,Item51)
(a) With input shaftin gear UP or gear DOWNposition,apply hand pumppressurevery slowlyuntil
fluid flows from hand pump reliefvalve.
CAUTION: HANDPUMPMUSTBE OPERATEDSLOWLYWHILEINCREASING
PRESSURETO BLEEDHANDPUMPRELIEFVALVE.
(b) Bleedair frompowerpackbycrackingcapon dooropenfitting.
Chart2). Bleed
(c) Adjustscrewat topof valveuntilthevalvecracksat 2025- 2100psi (29-00-00,
pressurebycrackingcap ondooropenfittingaftereachadjustment.
51. Disassemblyof Hand PumpSuctionScreen. (Figure403, Item48)
(a) Removesuctionscreenby removingsnap ring.
52. Assemblyof Hand PumpSuctionScreen. (Figure403, Item 48)
(a) Installfilter into powerpack body. Securewith snap ring.
53. Adjustmentof Door SolenoidValve. (Figure404, Item 11)
(a) Removecaps from door open and doorclosefittingson powerpack.
(b) Connecttest harnessto powerpack electricalplug and to powersource. (Testharnesscan be
fabricatedas shownin Figure502.)
(c) Withtest harnessswitch in OFF positionand input shaft in UP NEUTRALor DOWNNEUTRAL
position,apply pressureand note fluid flowsfrom door open fitting.
(d) Withtest harnessswitch in gear UPor gear DOWNposition,inputshaft in UP NEUTRALor
DOWNNEUTRALposition,apply pressureand note fluid flowsfrom door closedfitting.
(e) Disconnecttest equipment. Cap all openfittings.
Switchor Equivalent
MS35058-21
GearUp
Plug
MS3106A-145-25
MS3057A-6AClamp
GearDown
Clamps
Wire:18 Gauge
HarnessLength:2 to 3 ft
Battery-
PowerPackTestHarnessSchematic
Figure502
EFFECTIVITY:
29-10-00Jan
10/90
PIPERAIRCRAFT
PA42-720 (AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
54. Disassembly
of TimeDelayCheckValve.(Figure403,Item59)
(a) Removecheckvalvebodyfrompowerpackbody.
(b) Removesnapring.
(c) Usingbrasshook,pullout seat.
(d) Removeballandspring.
55. Assemblyof TimeDelayCheckValve.(Figure403, Item59)
(a) Installspringandballintocheckvalvebody.
(b) LubricateandinstallO-ringon seat.
(c) Installseatintocheckvalvebodyandsecurewithsnapring.
(d) LubricatethreadsandinstallO-ringon valvebody. Installassemblyintopowerpackbodyand
torqueto 45 inch-pounds.
56. Installation
andAdjustment
of InboardGearDoorsSwitch.
(a) Installswitchassemblywithinsulatingplatebetweenthe switchandmanifold.Securelightly
with washersandscrews.
(b) Moveselectorspoolto gearup anddownpositiona fewtimesto ensureproperactuatingof
switchfromONto OFF. Torqueswitchscrewsto 20 inch-pounds.
(c) Safetywiresolenoidto bracket(Figure404)using0.032inchsafetywire.
(d) Connectelectricalwiresfromswitchto terminalblock(Figure403). Secureto solenoidwith
plasticstrap.
NOTE: Electricalwiresarecolorcodedandmustbe matchedwhenreinstalling
wires.
(e) Installplungers,springs,andbuttonintohandlereleasebodies.Retainwithsnaprings.
(f) Installhandlereleaseassemblies
looselyin body.
57. PowerPackBenchTestAdjustment.
Aftercompletion
of overhaul,benchtest powerpackpriorto installation
in airplaneusinghydraulic
testunitor similartest equipment.
(a) Useonlycleanhydraulic
fluidperMIL-H-5606.
(b) Equipmentneededis asfollows:
(1.) Testunitpumpandhandpumpwith2500psicapacity.
(2.) Onehydraulicpressuregaugewith2500psi capacity.
(3.) Onehydraulicpressuregaugewith200psicapacity.
(c) Connecttest pressurehoseto pressureinletportof powerpack.The2500psigaugemust
operateoff pressureline.
(d) Connectsuctionhoseto suctionportof powerpack.
(e) Connectventhose(if included)to ventportat topof reservoir-cover.
(f) Capallotherfittingswithhighpressurecaps.
NOTE: Forcontrolof doorvalvesolenoid,fabricatean electricharness(Figure502). This
harness,whenconnected
to 24-voltbattery,allowscontrolof electricalcurrentto door
valvesolenoidpermittinghydraulic
doorcircuitsto operate.
EFFECTIVITY:
040-999
Jan 10/9029-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
System.
58. Bleedingthe Hydraulic
(a) Jackairplane(referto 7-10-00).
(b) Ensurereservoiris full.
test unitto airplane.
(c) Connecthydraulic
(d) Cyclelandinggearsystemthroughseveralcycles.
(e) Ensurehydraulicreservoiris full.
hydraulictestunit.
(f) Disconnect
(g) Ensurelandinggearselectorhandleis in down,neutralposition,andlandinggearisdownand
locked.
(h) Removeairplanefromjacks.
of HydraulicLines
59. RemovalandInstallation
brackets
fittingsat eachendanddisconnecting
linebydisconnecting
Removedamagedhydraulic
fordrainingline. Installnewor replacedlinebyconnecting
(Figure3). Providesmallcontainer
fluid.
brackets.Refillpowerpackwith hydraulic
fittingsat eachendandconnecting
NOTE: When usingstraightthread typefittings,locknutsmustbe tightenedso O-ringsealsare on
non-threadedportionof fitting.
of HydraulicFilters.
60. RemovalandInstallation
filters,locatedon lowerrightforwardsideof eachenginefirewall,are removedas
Thehydraulic
follows:
(a) Removeturtlebackskinaftof cowlingsto gainaccessto forwardandaft sidesof firewall.
filterinlethoseandoutletlinefromfilter.
(b) Disconnect
(c) Removefilterfromfirewallbyholdingboltsat aft sideof firewallandremovingnutatfilter.
(d) Thefilteris installedin reverseorder.
(e) Afterrunningengine,checkfor leaks.
of FilterElements.(Figure409)
61. Replacement
(a) Removeturtlebackskinaft of cowlingsto gainaccessto forwardandaft sidesof firewall.
(b) Cutsafetywire,unscrewbowl,andremovefilterelement.
(c) Cleanfilterbowlwithsuitablecleaningsolventanddry.
(d) ReplacefilterelementandO-ringon bowl.
systemandreplacebowl.
(e) Halffill filterbowlto minimizetrappedair in hydraulic
andreplacecowl.
(f) Safetyfilterbowlwithsafetywire(MS20995C20)
(g) Afterrunningengine,checkfor leaks.
EFFECTIVITY:
040-999
29-10-00
Jan
29-10-00U
Jan 110/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
1.Body,
Filter
2. -RingSeal
10. O-RingSeal
9.Screw
Pressure
ScrewPressure
3.O-RingSeal
8.Spring
17.
Valve,By-Pass
4. Filter
5.Spring
6. Bowl
HydraulicFilter
Figure409
62. HydraulicPumpOperational
Check.
Todetermineoperational
conditionof eachhydraulicpump,conductfollowingcheck:
(a) Startoneengineandallowto stabilizeat idle.
(b) Withengineoperatingat 52% gasgeneratorspeed,movegearselectorhandleto geardown
position.Onepumpmustbuildup pressurein hydraulicsystemandreturnselectorhandleto
neutralpositionwithin3 to 9 seconds.Againselectdownpositionandcheckhandlereturn
time.
(c) Shutenginedownandrepeatprecedingstepsfor otherengine.
(d) Ifselectorhandledoesnotreturnto neutralduringoperation
checkfor onepump,butdoes
returnwithinrequiredtimeduringcheckof other,removepumpanddeterminecauseof
malfunction.
63. Procedure
afterHydraulicPumpFailure.
If pumpbreakageoccurs,metalparticlescouldexistin hydraulic
system.Torectifycondition,flush
hydraulicsystemasfollows:
(a) Replacedefectiveengine-driven
hydraulicpumpandprimeit. Donotconnectpumpto
hydraulicsystemuntilsystemis flushed.
(b) Flushsystem.
(c) Removefilterelementsandcheckfor metalparticles.If metalparticlesarefoundin filter,clean
filterbowlwithdrycleaningsolvent.Drywithcompressed
air andinstallnewfilterelements.
EFFECTIVITY:
PAGE28
Jan 10/90 29-10-00
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
64. Removalof HydraulicPump.
twohalves.
(a) Removeupperandlowerenginecowlsby releasingskinfastenersandseparating
(b) Placedrippanunderengineto catchspillage.
twohydraulichosesfromendof pump.Caphosesto preventcontamination.
(c) Disconnect
(d) Disconnect
drainhosefrombottomof pump.
(e) Removefournuts,lockwashers,andflatwashersfrombaseof pump.
(f) Removepumpfromenginehousing.
(g) Whenremovingpumpfromdrivegear;remove,destroy,or discardgasketfrompumpmounting
face. Replacegasketandall sealringswithnewpartsuponreassembly.Neverreinstallan old
gasketor sealring.
of HydraulicPump.(Figure410)
65. Disassembly
(a) Cleanoutsideof pumpthoroughly.
fromrearside,across
substance
(b) MarklinewithblueDykemor someequivalentremovable
to drivesidefor properreassembly.
centerplate
CAUTION: DO NOT USE SCREWDRIVEROR SHARPTOOL TO SEPARATEPARTS
DURINGDISASSEMBLY.
anddriveside. Screws
(c) Removefoursocketheadcap screwssecuringrearside,centerplate,
arethreadedintodriveside.
outofdrivesideflangewhichmateswith
(d) Removefourlocknutsfromstudsextending
centerplate.
(e) Removerearsidebyrockingit sideto sideandslidingin fromfourdowels.If it sticks,tap
gentlywithplasticor rubberhammer.
(f) Removefourstudsfromrearside. RemoveanddiscardlargeO-ringsealfromrearside. Pull
shaftsuntildrivepinscleargears. Removedrivepins.
driveandsecondary
shaftby pullingfromcenterplate.
gear,andsecondary
(g) Removedrivegear,secondary
anddowelsbyrocking
(h) Removedriveshaftbypushingit outof driveside. Removecenterplate
it fromsideto side.
(i) RemovelargeO-ringsealfromdriveside;discard.
(j) Removeretainerringsecuringsealin drivesidesealbore. Noteproperpositionof sealduring
disassembly.Removeanddiscardtwopartseal.
EFFECTIVITY:
040-999
29
29-10-00Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
10.CenterPlateAssembly
HydraulicPump
Figure410
PAGE
3029-10-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
of HydraulicPump.(Figure410)
66. Assembly
fluidfor minimum2 hoursbeforeinstallation.
Soaksealandsealringsin Hydraulic(MIL-H-5606)
Pumppriorto assembly.
Hydraulic
of
Repair
and
Inspection,
(a) Referto Cleaning,
to installdriveshaftsealbackto
sure
Be
bore.
seal
side
drive
into
seal
shaft
drive
(b) Replace
back.
(c) Replaceretainerringintodrivesidesealbore.
(d) InstallnewO-ringsealon driveside.
assemblywithdrivesideassembly.Aligndowelpins.
(e) Matecenterplate
(f) Installdriveshaftfromenginesideof drivesideassembly.
gearsontodriveand
shaftintocenterplate.Installdriveandsecondary
(g) Installsecondary
shafts.Ensuredrivepincounterboreon drivegearfacespumprearside. Install
secondary
drivepins.
(h) InstallfourstudsandnewO-ringsealon rearsideassembly.
assembly.
fluidbeforecompleting
(i) Lightlyoil gearteethwith hydraulic
aligningdriveandsecondaryshaftswithrespective
(j) Materearsideassemblywithcenterplate,
holesin rearsideassembly.
outof drivesideflangematingwithcenterplate.
(k) Replacefourlocknutson studsextending
anddriveside
(I) Replacefoursocketheadcapscrewssecuringrearside,centerplate,
assemblies.Torquesocketheadcapscrewsandlocknutto 60 inch-pounds.
turndriveshaftby handandensurepumpturnsfreely.If stickingor
(m)Whenpumpisassembled,
pumpanddetermineproblem.Do notapplypowerto pumpuntilit
bindingexist,disassemble
turnsfreelyby hand.
Pump.
andRepairof Hydraulic
67. Cleaning,Inspection,
or
MIL-T-7003)
(MilitarySpecification
(a) Immerseandwashall metallicpartsin trichlorethylene
brush
fiber
fine
with
passages
and
openings
all
cleaningsolvent.Clean
equivalentcommercial
dippedin solvent.Do notscrubsurfaceswithtoolthatwillcausescratches.
WARNING: GOGGLESAND RUBBERGLOVESMUST BEWORNAND ADEQUATE
OR
VENTILATIONPROVIDEDWHEN USINGTRICHLORETHYLENE
SKIN CAN
WITH
SOLVENT
OF
CONTACT
REPEATED
SOLVENTS.
CLEANING
CAN
DAMAGE
SERIOUS
INHALED,
ARE
VAPORS
IF
CAUSEIRRITATION.
RESULT.
air at maximum
withclean,lint-freecloth,ordry,filtered,compressed
(b) Dryall partsthoroughly
air.
compressed
with
passages
and
bores,
parts,
all
out
Blow
20 psi.
pitting,
inspectall partsforscoring,nicks,scratches,
(c) Understronglightandmagnification,
or
crossed,
chipped,
for
surfaces
threaded
all
Inspect
wear.
excessive
and
cracks,
corrosion,
601.
Chart
in
information
to
conform
parts
all
Ensure
threads.
stripped
wherepartsexceedwearlimits,pumpwillnot
NOTE: Whenpumpoperatesunderconditions
produceratedcapacityandsystemwillnotfunctionproperly.Repairor replaceparts
notwithinstatedlimits.
EFFECTIVITY:
040-999
PAGE31
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
CHART 601
INSPECTIONANDREPAIR,HYDRAULICPUMP
ITEM
(Figure410)
INSPECTION
REPAIR
RearSide
Visuallyinspectlappedface
forscratchesor scoring.
Lap surfaceto removeany
scratches.
Centerplate
Visuallyinspecttwolapped
facesfor scratchesorscoring.
Inspectgearpocketsfordeep
scratches.
Lightlystone any burrs around
gear pockets. Lapfaces, but
do not removemorethan 0.0001
inch total metalfrom both sides.
Drive Side
Visuallyinspectlapped
surfacefor scratchesor
scoring.
Lapsurfaceto removeany
scratches.If deepscratches
exist,replacepart.
SecondaryShaft
Inspectshaftfordeep
scratchesin bearingarea.
If deepscratchesexist,
replacesecondary
shaft.
Gears
Visuallyinspectgearsfor
chippedteeth or cracks
aroundbore. Measure
gear O.D.,which mustbe
1.1646-1.1644 inch.
Ifgearsare notwithin
tolerance,or if anycracked
teethexist,replacepump.
Bearings
Visuallyinspectbearing
boresfor scratchesor
scoring.
If badlyscored,replacepump.
NOTE: UsePA-42-720
(Advanced
Trainer)PartsCatalog,P/N761818,to obtainrepairkitsfor servicing
pump.
EFFECTIVITY:
040-999
Jan
Jan 10/9029-10-00
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
of HydraulicPump.
68. Installation
(a) Placenew gasketon baseof housing.
(b) Lubricatepump shaft splineswith MolybdenumDisulfidetypeG paste lubricant.
NOTE: Drainfitting mustface to lowerright in downwardpositionwhen installingpump.
(c) Installpump on housing.
(d) Lineup shaftsplineswithgearinsideenginehousing.
(e) Installflatwashers,lockwashers,andnutson baseof pump;tighten.
hookupto firewallfittings.
(f) Installtwohydraulichosesandprimepumpbeforecompleting
fluid.
of
clean
hydraulic
(g) Ensuresystemreservoircontainsproperamount
(h) Changesystemfluidfilters.
69. PrimingHydraulicPump.
Whenpump is servicedor replaced,prime hydraulicpumpto assure it does not operatein dry
conditionas follows:
(a) Removehydraulicsuctionand pressurelines fromfirewallfittings.
(b) Installcaps on suctionand pressurefitting at firewallto preventfluid loss priorto hookupof
hydrauliclines.
(c) Hold both lines higherthan pump. Pour hydraulicfluid (MIL-H-5606)into lines.
(d) Oneby one, removecaps from firewallfittingsand connectappropriateline to fitting. Do not
spill hydraulicfluid previouslyput in lines.
(e) Afteroperatingengine,checkhookupfor leaks.
70. HandPump(Emergency).
(a) Removalof handpump.
(1.) Removepumpaccesspanelaftof controlpedestal.
hydraulicpressureandsuctionlinesfromforwardendof pump.
(2.) Disconnect
bolts.
(3.) Removepumpfrommountingbracketbyremovingattachment
(4.) Removepumpfromairplane.
(5.) Coverpressureandsuctionlinesto preventcontamination.
71. Disassembly
of HandPump.(Figure411)
quickclickpin andfourscrews.Allow
partsbyremoving
(a) Removeplungerandcomponent
bracketto separatefrompumpbody.
NOTE:Toremovequickclickpins,usehollowsteelrodwithoutsidediameterof 0.186- 0.184
inchandinsidediameter(bore)of 0.166inch.
(b) Pullplungerassemblyfrompumpbody.
(c) Slidescraperandglandfromplunger.
snapringfromplungercavity. Inject
(d) Removecheckvalveassemblyfromplungerby removing
lowchargeof air intoholein plungersideto removeseat,ball,andspring.
(e) Removecheckvalveassemblyin pumpbodysuctionportby removingsnapring. Injectlow
chargeof air intopumpbodyplungerboreto removeseat,ball,andspring.
EFFECTIVITY:
29-10-00Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
HandleAssembly
30. Stop
26.
.
22. Screw
20.
1. SnapRing
Hand Pump
Figure411
PAGE
3429-10-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
of HandPump.(Figure411)
72. Assembly
priorto assemblyasfollows:
all partswith oil (MIL-H-5606)
Lubricate
andRepairof HandPumppriorto assembly.
(a) Referto Cleaning,Inspection,
(b) LubricateO-ringandinstallon seat.
seatintoplunger.Retainwith snapring.
(c) Installspring,ball,andlubricated
(d) InstallGT-ringon plunger.
(e) InstallO-ringandbackup intoinsidegrooveof gland.
(f) InstallO-ringandbackup ontooutsidegrooveof gland.
(g) Lubricateentireglandandslideit ontoplungerwith recessedendon outside.
(h) Lubricatepumpbodyboreandslideplungerandglandintopumpbody.
(i) Installscraperontoglandrecessbyslidingscraperoverplungerwithtaperedlip of scraper
facingoutward.
(j) Attachbracketto pumpbodywithfourscrews.Torqueto 70 inch-pounds.
(k) PositionlinkandInstallquickclickpin.
(I) LubricateO-ringandinstallon seat.
seatintopumpbodysuctionport. Securewithsnapring.
(m)Installspring,ball,andlubricated
andRepairof HandPump.
73. Cleaning,Inspection,
(a) Cleanpumppartswith suitablesolventanddrythoroughly.
burrs,etc,which
(b) Inspectplungerfor enlargedpinholesandinspectsurfaceareafor scratches,
coulddamageO-ring.
(c) Inspectcheckballsandseatsfordamagedseatingareasandcorrosion.
(d) Checkgeneralconditionof all otherparts.
burrs,etc. ReplacewornO-rings
(e) Repairsto pumparelimitedto polishingoutsmallscratches,
anddamagedparts.
of HandPump.
74. Installation
(a) Positionhandpumpon mountingbracketandsecurewithbolts.
(b) Connecthydraulicpressureandsuctionlinesto forwardendof pump.
(c) Bleedhandpumpandtest handpumpoperation.
(d) Installaccesspanel.
(e) Ensurereservoiris filledwith hydraulic
fluid.
75. BleedingHand Pump.
Purgehandpumpbyoperatingpumpuntilallair is expelledfrompump. Thisusuallyrequires
approximately
15pumpcycles.
EFFECTIVITY:
040-999
29-10-00 Jan10/90
PIPERAIRCRAFT
PA42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Main (continued)
76. Hand PumpTest.
(a) Ensurereservoirisfilledwithhydraulic
fluid.
(b) Removecapfromdoor-open
port. Operateemergency
handpumpuntilfluidflowsfromport
withno evidenceof air in system.Replenish
reservoirwithcleanhydraulicfluid.
(c) Removefittingandinstall2100psigaugeat door-openport.
(d) Operateemergency
handpumpveryslowlyuntilpressureon gaugestopsincreasing,
indicatinghandpumpreliefvalvehasopened.
CAUTION: WHENBLEEDINGHAND PUMPRELIEFVALVE,HANDPUMPMUST BE
OPERATEDVERYSLOWLYAS PRESSUREIS INCREASED.IF OPERATED
RAPIDLY,DAMAGETO VALVECAN OCCUR,AS AIR WILL SLAMPARTS
AGAINSTEACHOTHER.
(e) Ensuremaximumgaugecomplieswiththosein 29-00-00,Chart2. Duringpumpingoperation,
emergencyhandpumpmustnotfeel spongyduringup ordownstroke.
(f) Crackgaugein door-openportto releasepressure;removegauge.Reinstall
fittingat dooropenport.
NOTE: Aftercompleting
test,reinstalllineandcheckreservoirfluidlevel.
7. GT-Ring
8. O-Ring
9.BackUp
1.RodEnd
2.Locknut
5. SafetyWire
4. End Cap
3. GT-Ring
12 NutSafety
13.BackUp
\
14.O-Ring
10 Nut
6. Piston
Wire
15.Race
16. Ball
17. Plunger
GearDoorActuatingCylinder
Figure412
PAGE
3629-10-00
Jan10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Main (continued)
6. Rod End
-1. CylinderBody
SafetyWire
-3. GT-Ring
6. BackUp
—-7.End Cap
8. GT-Ring
Gear ActuatingCylinder(NoseGear)
Figure413
EFFECTIVITY:
040-999
29-10-00
PAGE
37
Jan
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 30
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
30-EFFECTIVITY
30-CONTENTS
30-CONTENTS
30-CONTENTS
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SECTION
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LISTOFEFFECTIVE
PAGES
Feb 1/98
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER30- ICE & RAIN PROTECTION
TABLEOF CONTENTS
SUBJECT
CHAPTER
30-10-00
Airfoil
Descriptionand Operation
Fault Isolation
OperationalCheck
ElectricalCheck
PressureLeakageTest
PneumaticRegulatorAdjustment
Timer Maintenance
Inspection
GroundTest Procedure
100 - Hour Inspection
Removalof Boots
Repairof Boots
Cold Repair
VulcanizedRepair
Materialsfor VulcanizedRepairs
Definitionof Terms
General Procedure
Curing
SurfaceScuffs
Deep ScuffThroughNeopreneSurface
Holesor TearsThroughSurfaceSideof TubeArea
Holesor TearsThroughBacksideof TubeArea
Holesor TearsThroughTwoSides
HolesThroughDeicerExtendingfrom OneTube Into Another
Hole ThroughDeicerOutsideof TubeArea
Installationof Boots
Preparationof LeadingEdges
Preparationof Deicer
MountingDeiceron Leading Edge
AdhesionTest
Maintenance
Icex Application
ResurfacingConductiveCement
PAGE
1
1
3
5
5
5
7
7
7
8
8
9
9
9
12
12
14
14
15
15
15
19
19
19
19
20
20
20
20
20
24
24
24
25
30-20-00
Air Intakes
Descriptionand Operation
Fault Isolation
Air Inlet DeicerSystem
OperationalCheck
Removalof Inlet Deicers
Installationof InletDeicers
ElectricalCheckof Inlet Deicers
1
1
1
5
5
6
6
6
EFFECTIVITY:
040-999
CONTENTSan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER30- ICE & RAIN PROTECTION
TABLE OF CONTENTS(continued)
SUBJECT
CHAPTER
30-20-00(continued)
System
EngineAir InletIceProtection
of Ice DeflectorDoorTransmission
Removal
Installation
of IceDeflectorDoorTransmission
Cleaning,InspectionandRepairof IceDeflectorDoorTransmission
System
of EngineIce Protection
Adjustment
30-40-00
WindowsandWindshields
HeatedWindshield
Check
Functional
Copilot'sHeatedWindshield
WindshieldWiperMechanism
Removalof WiperMechanism
of WiperMechanism
Installation
WiperBladeandArmRemoval
WiperBladeandArmInstallation
WiperBladeandArmAdjustment
PAGE
6
6
6
11
11
1
1
1
1
1
1
2
2
2
2
30-60-00
Propellers
andOperation
Description
Practices
Maintenance
Check
DeicerSystemOperational
UsingtheAmmeter
HelpfulTips
1
1
1
1
2
2
50 - HourInspection
3
100- HourInspection
Checkingfor BrushWear
of Brushes
Replacement
Alignmentof NewBrushes
BrushModuleReplacement
Slip Rings
Machiningof SlipRings
of SlipRings
Replacement
DeicerBoots
Checkof DeicerBoots
Resistance
of DeicerBoots
Replacement
Repairof PropellerDeicerLeadStrap
Removalof Deicers
of Deicer
of SurfacePriorto Installation
Preparation
of Cement
Application
of DeicersandRequiredMaterials
Installation
of Sealer
andApplication
Preparation
WrinkledDeicers
3
4
5
7
8
10
10
10
10
10
10
11
12
12
14
15
15
17
EFFECTIVITY:
040-999
Jan 10/9
0
CONTENTS
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 30- ICE & RAIN PROTECTION
TABLE OF CONTENTS (continued)
SUBJECT
CHAPTER
30-60-00 (continued)
Propellers (continued)
Installationof PropellerDeicerStrapsand Wire Harness
Balancing
Final ElectricalCheck
Other Components
PowerControland Relays
Removalof the PowerControl Relays
Installationof PowerControlRelay
Removalof DeicerTimer
Installationof DeicerTimer
Timer Test
PAGE
18
19
19
19
19
19
19
21
21
21
EFFECTIVITY:
040-999
CONTENTSan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
Ice and Rain Protection
A. Airfoil - Descriptionand Operation
The deicerand vacuum systemis operatedwith pressureobtainedby toppingoff bleed airfrom the
enginecompressors.This air is routedthrough a regulatorvalvethat is set to maintainthe pressure
requiredto inflate the deicerboots on the leadingedge of eachwing,the verticalstabilizer,and the
horizontalstabilizer. Toassureoperationof the systemshouldone enginefail, a checkvalve is
incorporatedin the bleed air linefrom eachengineto preventthe escapeof air pressureintothe
chamberof the inoperativecompressor.High pressureair flows through an intercoolerand check
valvesto the pressureregulator/reliefvalve. The intercoolercoolsthe bleed air temperatureto a
temperaturebelow 200°F. In the eventthe bleed air temperatureexceeds425°F,a bleedair
overtemperatureswitchclosesto illuminatethe respective(left or right) BLEEDAIR HOTannunciator
light on the annunciatorpanel. The pressureregulator/reliefvalveregulatesthe pressuredownstream
to 18 psi and protectsthe systemfrom overpressurizationif the regulatedpressureexceeds21 psi.
The bleedair from the engine is also routedthroughan ejectorthat employsthe venturi effectto
producevacuumfor deflationof the deicerboots and operationof the instruments.The inflationand
deflationphasesof operationare controlledby meansof a controllingdeice valve.
The deicersystemis actuatedby a switch locatedon the RHoverheadpanel. This switch is a
momentaryon switch. Deiceboot inflationis indicatedby blue WINGand TAIL indicatorlightson the
right circuitbreakerpanel. Deicepressurecanbe monitoredthroughthe pneumaticpressuregauge
located onthe lower left instrumentpanel. Normally,the gauge should registerin the green,but will
flicker slightlyduring pneumaticdeiceoperation.
The outboardwing deice bootswill be referredto as the A boots and their controllingdeicevalve as
the A deice valve. The inboardwing deice bootsand the horizontaland verticalstabilizerdeice boots
will be referredto as the B boots and their controllingdeice valve as the B valve.
Momentaryactuationof the SURFACEDEICEswitchprovidespowerto the timerwhich initiallyopens
the solenoidon the A deice valve. Airflowthen passesthroughthe A deice valveinto the A boots.
When A boot pressurereaches15 psi (plusor minus1 psi), a pressureswitch closesto illuminatethe
blue WINGindicator light. Whenthe bootshavebeen inflatedfor 6 seconds(plusor minus0.5
second),the A boots exhaustthroughthe deice valve,the indicatorlight extinguishes,and vacuumis
restoredintothe A bootsthroughthe deicevalve integralejector. Whenthe A circuit is deactivatedby
the timer,the B circuit is activatedto open the B deice valvesolenoidand begininflationof the B deice
boots. As systempressurereaches15 psi (plusor minus1 psi),the blue TAILindicatorlight
illuminates.After 6 seconds(plusor minus0.5 second)of inflation,the timer deactivatesthe B deice
circuit and the pressureis exhaustedthroughthe B deicevalve. The indicatorlight extinguishesand
vacuum is restoredto the B bootsthroughthe integralejectorof the B deice valve. The pneumatic
deice systemwill automaticallyshutdown upon completionof one cycle of the A and B deiceboots.
The deicersystemon this airplaneis equippedwith a combinationvacuumand pressureline from a
combinationvacuum and pressurelinefrom a centraldistributorvalveto providepressurefor inflation
and vacuumfor deflationof the boots.
The vacuumline for the instrumentsis routedthrougha suctionrelief valvethat is designedto admit
into the systemthe amountof air requiredto reduceventurivacuumsufficientlyfor properoperationof
the instruments.
CAUTION: DO NOT OPERATETHE DEICERBOOTSBELOW-40°F. EXCEEDINGTHIS LIMIT
CAN RESULTIN PERMANENTDAMAGETO THE DEICERS.
EFFECTIVITY:
049990-10-00
30-1 0-00
PAGE
1
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
DeiceSchematic
Surface
Figure1
andOperation(continued)
A. Airfoil- Description
Jan 10/90 30-10-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
CHART 1 (Sheet 1 of 2)
FAULTISOLATION(PNEUMATICAIRFOIL DEICERSYSTEM)
Fault
Deicersdo notinflate.
Pneumatic
pressure
gaugein green.
Deicersinflateslowly
(Inflationtime - 6 + .5
seconds.)
Systemdoesnotachieve
operatingpressure.(Leak
test showsnosign.)
Cause
Remedy
Opencircuitbreaker.
Pushcircuitbreakerto
reset.
looseor
Systemconnection
wirebroken.
Tightenor repair as
required.
Timernotfunctioning.
Testandreplaceif
required.
Deicervalvesnot
functioning.
Makeelectricaltest. Check
for stickingpoppet. Clean.
Lines blockedor
not connected.
Blowout lines and inspect
connections.Makeair
leakagetest.
Linespartiallyblockedor
securely.
notconnected
Blowout lines and inspect
connections.Makeair
leakagetest.
Deicervalve not
functioning.
Testor replaceas
required.
Systempressurenot
being reached.
Checkpneumaticsystem
performanceto manufacturersspecifications.
Deicerpuncture.
Repairperspecification
or replace.
Inflationtime inadequate;
timer not functioning
properly,solenoidvalve
not openfor six seconds.
Test and replaceas required.
Cleanor replacevalve.
EFFECTIVITY:
040-999
30-10-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil- Description
andOperation(continued)
CHART 1 (Sheet 2 of 2)
FAULT ISOLATION (PNEUMATIC AIRFOIL DEICER SYSTEM)
Fault
Cause
Deicersdeflateslowly.
Pressureregulator
settoo
low.
Readjustpressure
regulator.
Lines partiallyblocked.
Inspectand blow out
lines.
Overboardlinefrom
controlvalvepartially
blocked.
Inspectandblowout
lines.
Leakagein system
plumbing.
Leakcheckandcorrect
leaking.
Remedy
EFFECTIVITY:
040-999
Jan 10/90 30-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
1. Operational
check.
Checkpneumaticdeicingsystemon the groundat least every 100 hours includinga visual
inspectionof the deicerboots.
Withoneengineoperatingat 80%Ng,turnon deicingsystem.Thepressurewillfluctuateas tubes
inflateanddeflate.Checkpneumatic
pressuregauge.If pressureis satisfactory,
checkoperation
of deicersfor a malfunction
andlookfortubeswhichleakorfail to inflateanddeflateproperly.
Repeatprocedure
forotherengine.
2. Electrical
test.
Withenginesoff,turnairplanebatteryswitchon.
(a) DeicerValves. Checkvalves beneathcenter floorboardaft of FuselageStation154.00. Turn
systemswitch on. One valve mustactuateimmediatelyfor 6 ± 0.5 secondswith an audible
click which can be felt if a hand is placedon valve. The other valve mustactuate6 ± 0.5
secondsafterthe first and remainactuatefor 6 + 0.5 seconds. If either valvedoes not function,
follow instructionsbelow:
(1.) Disconnectwires at valve. Attachtest light or other suitabletest equipmentto connector
and reactuatesystemswitch. If test equipmentdoes not indicatecompletecircuit,
completethe followingchecks:
(a.) Checkcircuitfrom timer to valveconnectorto ground.
(b.) Replacetimer (referto PA-42-720(AdvancedTrainer) PartsCatalog).
(2.) Use an ohmmeterto check valvefor an open circuit. If valve circuitis open, replacevalve.
3. Pressureleakage test. (Figures1 and 501)
(a) Removeappropriatefloor panels to gain accessto deicer solenoidvalvesunderfloor at
FuselageStation 157.00,near centerof fuselage.
(b) Disconnectpressure/vacuumline from outboardbootsvalve. Connecttest apparatusto line
(shownin Figure501).
NOTE: Use only clean and oil-free shopair. Shopair sourcemustbe capableof applyingat
least 18 psig.
(c) Attachshopair to test apparatus
withcontrolvalveclosed.Adjustregulatoruntil19psig
registerspressuregauge(number1)aheadof controlvalve.
(d) Slowlyopencontrolvalveto inflateoutboardwingdeicerboots.
(e) Allowsystemto stabilizeandclosecontrolvalve. Withpressuretrappedin system,check
pressuregauge(number2) downstream
of controlvalve. Ensureleakageratedoesnot
exceed3 psigper minute.
(1.) If systemdoes not hold requiredpressure,use soapywater to find leaks.
(2.) If connectionsleak excessively,tightenas muchas possible. Replaceas necessary.Do
not use thread sealantson threadedfittings.
EFFECTIVITY:
040-999
30-10-00
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Airfoil - Description and Operation (continued)
3.
Pressure leakage test. (Figures 1 and 501) (continued)
(f) Relieve pressure in system by slowly opening fitting at test apparatus.
(g) Retighten fitting and turn on aircraft electrical power.
(h) Slowly open control valve and increase pressure to 14 - 16 psig. Ensure wing boot indicator
light on copilot circuit breaker panel comes on at 15 ± 1 psig. Replace pressure switch by
removing turtleback cowl on left nacelle.
(i) Release system pressure. Remove test apparatus.
(j) Reconnect system pressure line to solenoid valve.
(k) Complete same test for inboard wing and tail boots solenoid control valve.
Clean
Oil Free
Air Supply
Manual
Regulator
15-30psig
0-100psig
PressureGauge
(SystemPressure)
GaugeNo. 1
ControlValve
0-100 psig
PressureGauge
(LeakPressure)
GaugeNo. 2
To Aircraft
SystemConnection
Boots TestApparatus
Figure501
30-10-00
Jan
Jan
10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
4. PneumaticRegulatorAdjustment
Togain accessto the pneumaticpressureregulatoron the rightof the fuselagecenterline,remove
the floorboardaccesspanelat FuselageStation 156.00.
The adjustableregulatorprovidesappropriatepressurefor the pneumaticsystem. An adjustment
screwon the outboardend of the valvebody is accessibleby removingthe thermoplasticventcap
from the outboardend of the regulator. Proceedas followsto checkregulatoroperation:
WARNING: ALL SAFETYPRECAUTIONSMUSTBE OBSERVEDWHEN STARTINGAND
OPERATINGENGINES. ENSUREAIRCRAFTIS PROPERLYRESTRAINEDWHEN
USINGFULLPOWERSETTINGS. REFERTO PILOT'SOPERATINGHANDBOOK
FOR OPERATINGINFORMATION.
(a) Start both enginesand place both right and leftenginebleedair switchesin the ON position.
Establishsteady airflowin cabin. If door is closed,ensuredoor seal inflates.
(b) Cycledeicer bootsand observesystempressureon cockpitpneumaticgauge. With enginesat
maximumpower90% Ng, the pressuremust not exceed20 psig. Withone engineoperatingat
85% Ng, pressuremust not go below16 psig.
(c) Toadjust regulator,proceedas follows:
(1.) Removeappropriatefloor accesspanel.
(2.) Loosenclampand slide plasticventcap off outboardend of regulator,exposing
adjustmentscrew.
(3.) Loosenjam nut on screwand rotatescrewclockwiseto increasepressure,
counterclockwiseto decreasepressure.
(4.) Lock screwin positionwith jam nut.
(5.) Reinstallplasticvent capon regulatorand tightenclamp.
CAUTION: ENSUREVENT CAP IS REINSTALLEDPROPERLYON REGULATOR.
ENSUREHOSEFROMCAP TO FUSELAGEIS SECUREAND IN GOOD
CONDITION.IF CAP IS LEFTOFFOR NOT PROPERLYSECURED,
REGULATORIS REFERENCEDTO CABIN PRESSURE,NOT AMBIENT
PRESSURE,CAUSINGREGULATORTO ALLOW EXCESSIVE
PNEUMATICPRESSURETO BUILD UP IN DEICERSAND DOORSEAL.
NOTE: Newaircraft containa pressureregulatorincorporatingan overboardventfitting,
eliminatingthe vent cap usedon earlier aircraft. Regulatoradjustmentis
unaffected.
5. TimerMaintenance
No field maintenanceis recommended.See parts catalogfor replacementor vendorfor repairs.
6. Inspections
Completea groundcheckof entire deicersystemat leastevery 100 hours. To groundcheck
systemwithoutoperatingengine,disconnectpneumaticsystemline (3/4-inchbranch line upstream
of bleedair shutoffvalve)at engineand connecthosefrom shopair to pneumaticline with air
regulatedto 22 psig. The shop air supplymustbe capableof deliveringair 3 poundsper minuteat
22 psig.
Beforecheckingsystem,inspectall deicersfor damageand repairaccordingto cold patchor
vulcanizedrepair proceduresin this section. To checksystem,usedeicer pipingdiagramdrawing
to determinethe operatingpressureand inflationtime allottedfor deicers.
EFFECTIVITY:
040-999
30-10-00JaPAGE
Jan10/90
7
PIPERAIRCRAFT
PA42-720 (Advanced Trainer)
MAINTENANCEMANUAL
andOperation(continued)
A. Airfoil- Description
7. GroundTestProcedure
testpressurerange,connectan externalair pressuresourceto the3/4-inch
Afterestablishing
enginepneumaticline. A checkvalvein the linepreventsairfrombeingforcedbackthroughthe
oppositeenginebleedair ports. Activatesystemandcheckoperatingpressure.Thepressure
operatingpressurewitheachinflation.
mustbe within1 psigof the recommended
If deicersdo notreachoperatingpressure,checksolenoidvalves.If bootsdeflateslowly,linesor
6 + 0.5seconds.(See
ejectorscouldbe plugged.Ensuresysteminflatesin approximately
section.)
OutboardWings,InboardWingsandEmpennage
CHART 2
OPERATINGPRESSURES
RecommendedOperatingPressure
PSIG
18
TestPressure
PSIG
MIN.
16
MAX.
20
8. 100-HourInspection
inspectandoperatedeicerbootsasfollows:
At each100-hourinspection,
(a) Carefullyinspectdeicersfor damageor deterioration.Repairor replacedamagedboots.
wearordeterioration.
(b) Replacebootsshowingconsiderable
deicingsystem.Replacedeteriorated
thepneumatic
comprising
(c) Inspectall hoseconnections
sectionsof non-kinkhose.
(d) Checkoperationof bootsandoperatingpressureof system.
stemsareproperly
(e) If newbootsareinstalled,checktubeinflationto ensureair connection
connected.
(f) Checkon-offcontrolswitchfor properoperationandwiring.
Inflation
Area
DeicerBootsOperation
Pneumatic
Figure2
EFFECTIVITY:
040-999
Jan 10/90
30-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
9. Removalof Boots
WARNING: DEICERBOOTSMUSTBE REMOVEDIN A WELLVENTILATEDAREATO AVOID
INHALATIONOF TOXIC,SOLVENTFUMES. TO REMOVEBOOTS,USE TURCO
388 OR KELITE21; TO REMOVEDRIEDCEMENT,USE MEK
(METHYLETHYLKETONE)
IN SQUIRTCAN.
NOTE: Disconnect
linefittingsfrombootfittings.
(a) Startingat one comer of deiceruppertrailing edge, applyminimumamountof solventto seam
linewhile applyingtension to peel back comer of deicer.
(b) Separatedeicerboot from surfacefor 4 inchesalonguppertrailing edge using a pressure
handlesquirt canfilled with solvent.
(c) Pulldeicer down towardsleadingedge with uniformtension.
(d) Use pressurehandlesquirtcan from centerlineof leadingedge to lowertrailing edge of deicer
to softenbond betweendeicerand wing skin.
(e) Use Kelite 21 or Turco388 to clean dry cementoff exposedwing area. Cleanarea thoroughly
with MEK (Methylethylketone).
10. Repairof Boots
Deicerrepairsareclassifiedascoldwhenmadeon bootstillon airplaneor vulcanized
whenboot
is takenoff airplane.
(a) Cold Repair
NOTE: Materialsand suppliesrequiredfor cold repairsare listedin Chart3.
of
whenscuffissevereandentirethickness
(1.) ScuffDamage- Repairsare onlynecessary
surfaceply is removedin spots(brownnaturalrubberunderneathisexposed).Proceed
as follows:
withsolvent.Buffareaaround
(a.) Cleandamagedareawithclothslightlydampened
damagewithP/N74-451-75emerybuffingstick. Wipebuffedareawithcleancloth
dampened
slightlywith solventto removeall looseparticles.
area. Applyoneevencoatof cement(P/N
(b.) Selectamplesizepatchto coverdamaged
74-451-20)
to patchandcorrespond
damagedarea. Allowcementto seta few
minutesuntiltacky.
(c.) Applypatchto deicerwithan edgeor thecenteradheringfirst. Carefullypushdown
rollpatchwithstitcherremainder
of patchto avoidtrappingair pockets.Thoroughly
roller(P/N74-451-73)
andallowto setfor 10to 15minutes.
slightly
areafromcenteroutwardwithclothdampened
(d.) Wipepatchandsurrounding
to
cement(P/N74-45-11)
withsolvent.Applyonelightcoatof A-56-Bconductive
patchedarea.
(e.) Properadhesionof patchto deiceris reachedin 4 hours. Tocheckrepair,inflate
deicerafter20 minutes.
EFFECTIVITY:
040-999
PAGE9
30-10-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
andOperation(continued)
A. Airfoil- Description
(a) ColdRepair(continued)
patches.
(2.) TubeAreaDamage- Repaircuts, tears,or ruptureswith fabric reinforced
on sizeof damage.)
-17,-18,or -19,depending
(P/N74-451-16,
(a.) Selectpatchwhichextendsat least5/8-inchbeyondendsandedgesof cutor tear.
to stretchin onedirectiononly. Besureto cut
NOTE: Patchesaremanufactured
directionof the
it stretchesin thewidthwise
so
patch
andapplyselected
tubes.
inflatable
(b.) Buffareaarounddamagewithbuffingstick(P/N74-451-75).
(c.) Applypatchto deicerwithstretchwidthwiseof inflatabletubes.Withstickyedgeof
downwithslightpullingactionto closeinjury.Donot
patchin place,workremainder
trapair betweenpatchanddeicersurface.
Area)- Peelandtrimloosesurfaceplyfor
(3) LooseSurfacePlyin RearArea(Non-Inflatable
properadhesionof surfaceply to deicer.
areawheresurfaceplywasremovedwith steelwool. Ensure
(a.) Scrub(roughen)
scrubbingmotionisparallelto cutedgeof surfaceplyto preventloosening.Buff
edgesof adjoiningsurfaceply 1/2-inchwith P/N74-451-75buffingsticksandtaper
downto tanrubberply. Removelooseparticleswithsolventandrag.
to extendat least1 inchin all
(b.) Cutpieceof surfaceply material(P/N74-451-23)
directionspastdamage.
(c.) Maskoffdamagedbootarea1/2-inchlargerin lengthandwidththanthesizeof
to damagedareaand
surfaceply patch.Applyonecoatof cement(P/N74-451-11)
onecoatto patch.Allowcementto setuntiltacky. Rollsurfaceply to deicerwith2
(P/N74-451-73)
inchrubberroller(P/N74-451-74).Rolledgeswithstitcher-roller
andapplyenoughtensionon surfaceplyto preventwrinklingandtrappingof air. If air
needle.
blistersappearaftersurfaceplyis applied,removethemwithhypodermic
(d.) Cleanexcesscementfromdeicerwithsolvent.
(4) LooseSurfacePlyIn TubeArea- Loosesurfaceply in tubeareausuallyindicatesdeicer
startingto flexfail. Thisfailureis easilydetectedasa blisterunderthesurfaceplywhen
deiceris pressurized.Ifdetectedwhilestilla smallblister(about1/4to 3/8inchdiameter)
servicelifeof deicerwillbe extended.Applyrepairpatchas
andpatchedimmediately,
outlinedin paragraph(2) (a.).
(5) DamageToFabricBackPlyOfDeicerDuringRemoval- If cementhaspulledloosefrom
wingskinandadheredto thebacksurfaceof deicer,removewithcleanrag andMEK. In
spotswherecoatinghaspulledofffabric,leavingbarefabricexposed,applyat leasttwo
andalloweachcoatto drythoroughly.
additionalcoatsof cement(P/N74-451-24)
EFFECTIVITY:
040-999
Jan 10/9030-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
(a) Cold Repair (continued)
PartNo.
CHART3 (Sheet 1 of 2)
MATERIALAND SUPPLIESFOR COLD REPAIR
Quantity
74451-C
(FSN1650-856-7939)
74-451-11
1/1 pt. can
74-451-16
30 pcs.
74-451-17
30 pcs.
74-451-18
10 pcs.
74-451-19
74-451-20
3 pcs.
(2) 1/2 pt.
74-451-70
74-451-73
74-451-75
74-451-87
2
1
1
6
1
Description
Cold Patch RepairKit
(B. F.GoodrichCo.)
A-56-BConductive
Cement
Smalloval patch
1 1/4 x 2 1/2 in.
Mediumoval patch
2 1/2x 5 inch
Largeoval patch
5x10 in.
Patch5 x 19 inch.
*No. 4 Cement
(patchingonly)
Cement BrushI j2 in.
1/8 in. Steel Stitcher
EmeryBuffingSticks
BuffingShield
*This cementwillgivebestresultswiththe patchesin thiskit.
The followingitemsmay be procuredfrom the B. F.GoodrichCo.,
Akron, Ohio,or other manufacturer,as required:
74-451-21
74-451-22
6 ft. roll x 6 in. wide
15 ft. roll x 2 in. wide
74-451-23
74-451-24
(FSN 8040-628-4199 and/
or FSN8040-S141880)
74-451-74
4 ft. roll x 8 in. wide
1 quart
74-451-100
1
1
Type21 or 22 Fillet
Neoprenecoated splicing
tape
Neoprenesurfaceply
§ EC-1403cementand/or
EC-1300L
2 1/2 in. spongerubber
roller
2 in. dia. x 2 1/2 in. rubber
roller
§ EC-801filler compound
§ MinnesotaMiningand ManufacturingCompany,AdhesivesDivision,
411 PiquetteAve., Detroit,Michigan.
EFFECTIVITY:
040-999
PAGE
11
30-10-00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
andOperation(continued)
A. Airfoil- Description
(a) ColdRepair(continued)
CHART3 (Sheet2 of 2)
MATERIALAND SUPPLIESFOR COLD REPAIR
Quantity
PartNo.
Description
Thefollowingmaterialsmaybeobtainedfromlocalsupply:
As required
Rolls
1
6 ft. long
1
As required
As required
Toluol
Clean,Lint-FreeCloths
cheesecloth)
(preferably
1 in. MaskingTape
SharpKnife
Tape
SteelMeasuring
Stone
FineSharpening
SteelWoolPads
needles
Hypodermic
(22gaugeor smaller)
Methylethylketone(MEK) can be used instead of Toluol, however MEK causes very rapid drying and providesonly 10 secondsworkingtime comparedwith 40 secondsfor Toluol.
(b) VulcanizedRepair
station.Careful
deicerinstallation
Vulcanizedrepairsmustbe madeat an approved
mustbegivento overallconditionof deicer. f largepartsof deicerstretcharea
consideration
are crackedor checkedto a depthof over0.005inch,do notrepair.Deicerswithslightchecks
cement.If checkingisdeepbutrestrictedto
in stretchareacanbe coatedwithconductive
smallarea,repairdamagedarea. Deicersswelledor softenedby contactwithoil orother
upon
bydepending
if damageis repairable
harmfulagentsmustbe scrapped.Determine
andtrainingof workman.
carefuljudgmentof inspectorandexperience
(c) MaterialsForVulcanizedRepairs
of anyrepairdependson an analysisof damageandselectionof correct
The effectiveness
to resistsunlightandweather,andretainflexibility.
repairmaterial.Deicersarecompounded
Useonlymaterialslistedin Chart4 whenmakingvulcanizedrepairs.Selectmaterialsspecified
wash
for eachrepairandavoidsubstitution.Sincemanymaterialsaredustedwithsoapstone,
and
tools
lists
all materialscarefullywithwashingorcleaningsolventbeforeuse. Chart5
equipmentsuitablefor repairwork.
EFFECTIVITY:
040-999
Jan
09030-10-00
12 30-10-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
CHART4
MATERIALSFOR VULCANIZEDREPAIRS
Part No.
74-451-B
74-451-B-1
74-451-2
74-451-3
74-451-4
74-451-5
74-451-6
74-451-7
74-451-8
74-451-9
74-451-10
74-451-11
74-451-12
Qty.
Description
SUPPORTKIT,High pressureDeicervulcanizedrepairs..............
1
MATERIALSKIT ..........................................................................
1
. NON-STRETCHFABRIC,Uncurredrubbercoated...................
15 ft x 8 in.
.FABRIC TAPE,Uncuredrubbercoated....................................
15ftx 1 in.
. TUBE FABRIC,Uncured............................................................ 15ftx 8 in.
. GUM,0.005 Uncured.................................................................15 ft x 2 3/4 in.
.GUM, 0.020 Uncured................................................................. 15 ft x 8 in.
.TREATED PAPER,Hollandor silicone...................................... 30 ftx 8 in.
.VULCANIZINGCEMENT,No. 60...............................................
lqt
.VULCANIZINGCEMENT,No. 61...............................................
lqt
.. SOAPSTONE............................................................................. lqt
.CONDUCTIVECEMENT,*A-56-B.............................................
1/2 pt
1/2 pt
.. *NEPORENEPUTTY.................................................................
*Thesecementshave an extendedshelf life, if kept underrefrigeration,from 0° to 40°F.
CHART5
EQUIPMENTFORVULCANIZEDREPAIRS
Part No.
74-451-B
74-451-B-2
74-451-B-3
74-451-B-4
74-451-40
74-451-41
74-451-42
74-451-70
74-451-71
74-451-72
74-451-73
74-451-74
74-451-75
74451-76
74-451-77
74-451-78
74-451-79
74-451-80
74-451-81
74-451-82
74-451-83
74-451-84
74-451-85
EFFECTIVITY:
040-999
Qty.
Description
SUPPORTKIT,High pressureDeicervulcanizedrepairs..............
... Tool Kit, Complete....................................................................
... Tool Kit, Special........................................................................
... Tool Kit, Standard.....................................................................
... VULCANIZER,Large2 1/3 x 8 ................................................
. PADS,Spongerubber,3 1/2 x 11 ............................................
. CURINGMETAL,6x 10 ..........................................................
... BRUSH,Cement,1/2 in. .......................................................
... BRUSH,Cement(Artist)..........................................................
... SHEARS, 10 in.. .....................................................................
... STITCHER, 1/8 in. Steel..........................................................
... ROLL,Spongerubber2 1/2 in. ..............................................
... STICKS,Emerybuffing............................................................
... KNIFE HANDLE.......................................................................
... KNIFE BLADE..........................................................................
... WHETTING STONE.................................................................
... HYPODERMICNEEDLE.........................................................
... ELECTRICBUFFER................................................................
... MANDREL(for felt wheels)......................................................
... WHEELS(felt buffing)..............................................................
... STONE,Grinding,pointed.......................................................
... STONE,Grinding,flat ..............................................................
... NUT, Hex..................................................................................
1
1
1
1
1
3
2
2
2
1
1
1
6
1
3
1
6
1
3
24
3
4
3
30-10-00Jan
PAGE
13
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
andOperation(continued)
A. Airfoil- Description
(d) Definitionof Terms
below:
areexplained
Termsin thefollowinginstructions
withToluolor MEK. (Benzineor
(1.) Wash- Cleansurfacewithcleanclothmoistened
gascanbe usedin placeof cleaningsolvent.Donotpermitfreesolventsto
nonleaded
remainon surfaces.)
(2.) Route- Removerubbersurfaceswithhexnuton shaftattachedto electricbuffer.
buffingsticksor abrasivepaper.
(3.) Buff- Roughensurfaceswith Carborundum
(4.) Cement- Applytwolightcoatsof afifty-fiftymixtureof number60 and61 vulcanizing
cements,unlessotherwisespecified.Leteachcoatdrybeforeproceeding.
(5.) Gum- Uncuredrubberstock.
(6.) FaceSideof Deicer- Sideexposedwheninstalledorconductivesurfaceside.
Surface- Aftercuringrepairon surfaceside,applytwocoatsof A-56(7.) RestoreConductive
cement.
B conductive
NOTE: Do not apply A-56-Bconductivecementto any electricaltransmittingor receiving
equipment.
togetherwithmetalor rubberroller.Stitchfrom
(8.) Stitch- Forcefabricsor gumelements
centertowardedgesto preventtrappingair betweenelements.
(e) GeneralProcedure
andisfreeof dustandforeignmatter.Keepwork
Ensurerepairroomhasadequateventilation
cementandsolvents,or damagedeicers.
not
contaminate
do
objects
foreign
so
clean
bench
Performthe followingsteps:
damaged
cleanlargeareasurrounding
repair,thoroughly
(1.) Beforestartingvulcanized
portionanddamageportionof grease,dirt,or talc. Useneutralsoapandwatersolution,
rinseclean,anddrywithcleancloth.
in Toluolor Methylethylketone
(2.) Washrepairareacarefullywith cleanclothmoistened
TT-M-261.
(MEK),FederalSpecification
to prevent
(3.) Whenroutingarounddeicerinjury,removeorcoverallcementcontainers
cement.
particlesfromgrindingstonefromcontaminating
(4.) Afterbuffingor routinganarea,removeall dustfromdeicerandtablesurfaces.
(5.) Protectall completedrepairsfromdustanddirtwithcleanpieceof hollandcloth. Hold
clothin placewithmaskingtape. Removemaskingtapebeforecuring.
(6.) Releaseall air trappedbetweengum,fabric,anddeicersurfacesby insertinghypodermic
needlethroughplyto airpocket.
(7.) Removeall excesscementanddustparticlesbywashingwith solvent.
(8.) Usecleanbrusheswhenmakingrepairs.CleancementbrusheswithBenzineor nonleadedgasoline.
(9.) UseapprovedsafetycanforToluolor MEK. Removespringandscreenoutof solvent
cansbeforefilling.
cementsareappliedin athin smoothcoating.If partiallysetup or lumpy,addition
(10.)Ensure
of propersolventrestoresusablecharacteristics.
under40°F.
(11.)Do notattemptrepairsin temperature
cleanclothbefore
humidityis high,wipemoistureoffwitha solventdampened
(12.)When
with repair.
proceeding
andhandscleanat all times.
(13.)Whenrepairingdeicers,keepmaterial,tools,equipment,
EFFECTIVITY:
30-10-00
Jan 10/90
10/90
Jan
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
(f) Curing
The vulcanizerlisted in Chart5 is adjustedat the factoryto heat to 285° + 5°F, using line
voltagespecifiedon the name plate. All curingtimes in this manualare for 285°F. If line
voltageis low, the vulcanizerwill not heat to 285°Fand curingtimes are longerthan specified.
Sincecuringtime varieswith type and positionof repair,times are given for eachspecifiedtype
of repair.
Curerepair as follows:
NOTE: Over-curingdestroysthe flexibilityof deicer. Under-curingpreventsproperbonding.
Alwayswatchcure time andtemperaturecarefully.
(1.) Preheatvulcanizer.
(2.) Place spongepad over bottomof unheatedplate.
(3.) Place pieceof clean, unwrinkled(or siliconetreated)paper over spongepad and deicer
over hollandwith area to be curedcentrallylocatedover bottom platen. (Repairside up.)
(4.) Place anotherpiece of smooth,clean hollandover area.
NOTE: If hollandor siliconetreatedpaper is not available,spread thin coatof soapy
water over surfacesof metalcuringsheet and spongepad. Allowto dry
thoroughly.
(5.) Place metalcuring sheetover hollandand clamp heatingelementin place. Ensuremetal
curing plateis at least 1 inch largeroverallthan heatingplate. Handtightenheaterfirmly.
(6.) Cure full allottedtime for each repair.
(7.) Test each repairthoroughlyafter it hascured. Flexand stretcharea by hand several
times and in a tube; inflateto 25 psig.
(g) SurfaceScuffs
(1.) Wash surface,apply one coat of conductivecement,and allowto dry thoroughly.Add
anothercoat and allow to dry. Dip finger in conductivecementsolvent(IsopropylAcetate)
and rub down with light circularmovement.
(2.) Wipe surfacelightlywith IsopropylAcetatemoistenedcloth.
(3.) Allow to dry thoroughly. Dust lightlywith soapstone.
(h) DeepScuffThroughNeopreneSurface
(1.) Mark area and carefullycut 0.010 inch Neoprenesurfaceply with knife. Preventsurface
ply from peelingbeyondmarkedareawhen using buffer. Ensurearea includesfull width
of tube and approximately1/2-inchbeyondscuff.
(2.) Usingbuffer,routedown untilall pits are removed. Buff 1/8-incharoundouter edge of
routed area. Maskoff outsideof buffed area and cement.
(3.) Using mill or putty knife, applyNeopreneputty. Fillcavity flush with surfaceand ensure
cavity is completelyfilled. Removemaskingtape and cure for 20 minutes.
(4.) Restoreconductivesurface.
EFFECTIVITY:
040-999
30-10-00PAGE
Jan 10/9015
PIPERAIRCRAFT
PA42-720 (AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
Markingand CuttingScuff
Figure 801
RoutingScuff
Figure802
BuffingEdgeof Repair
Figure803
HoleThroughSurfaceof Tube
Figure804
EFFECTIVITY:
040-999
10/90
30-10-00
30-10-00
Jan 10/90
Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
Rotatingto Tube Fabric
Figure805
CuttingSurfaceof Tube
Figure806
BuffedAreaandPatch
Cementing
Figure807
Applyingand StitchingFabric
Figure808
EFFECTIVITY:
040-999
17
PAGE
30-10-00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Airfoil- Description
andOperation(continued)
Placingand StitchingGum
Figure809
RemovingTrappedAir
Figure810
MaskingRepair
Figure811
ApplyingNeoprenePutty
Figure812
EFFECTIVITY:
PAGE
Jan 10/90 30-10-00
18
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil- Description
andOperation(continued)
(i) Holesor TearsThroughSurfaceSideof TubeArea
(1.) Markoff areaandcarefullycut0.010inchsurfaceplywithknife. Preventsurfaceplyfrom
peelingbeyondmarkedareawhenusingbuffer.Ensureareaincludesfull widthof tube
andapproximately
1/2-inchbeyondcut.
(2.) Usingbuffer,routedownto tubefabric. Becarefulwhileusingbuffernotto loosensurface
ply beyondrepairareaandensurethattubefabricis notinjured.Washoutarea.
(3.) Cuttubefabricpatchslightlylargerthancavitysize,ensuringfabricstretchisacrosswidth
of tube.
(4.) Cementbuffedareaandcontactsurfaceoftubefabricpatch.Applytubefabricto entire
cavityandstitch. Removetrappedair usinghypodermic
needle.Rollup smallpieceof
0.005inchgum(about1/32-inchdiameterand3/4-inchlong)andworkin aroundedgeof
tubefabricusingsharppointedobject(shears,etc). Stitchgumandcurefor 20minutes.
(5.) ScratchshineoffgumusingCarborundum
stick. Buffsurfaceply 1/8-incharoundrepair.
Washrepairedareaandapplycement.
(6.) Maskoff 1/16-inchbeyondrepair.Usingmillor puttyknife,applyNeopreneputtyfilling
cavityflushwithsurface.Ensurecavityiscompletely
filled. Removemaskingtapeand
curefor 15to 20 minutes.
(7.) Restoreconductive
surface.
(j) Holesor TearsThroughBacksideof TubeArea
(1.) Routeoff coatingdown to fabric at least 3/4-inchbeyondcut,wash entire buffedarea and
cement.
(2.) Cut fabricpatch,wash,cement,apply fabricpatch,and stitch. Removetrappedare using
hypodermicneedle.
(3.) Wash and cementrepairedarea, applythin coat of Neopreneputtywith mill knife and cure
for 22 minutes.
(k) Holesor TearsThroughTwoSide
Repaironesideat a timereferringto paragraphs
titledHolesor TearsThroughSurfaceSideof
TubeAreaandHolesor TearsThroughBackside
of TubeAreain thischapter.
(I) HoleThroughDeicerExtendingfrom One Tube intoAnother
(1.) Routeandbuffonesideat a time.
(2.) Workingonsurfaceside,routein betweentubetape3/4-inchin eachdirectionfromtear.
Routeoutin betweentubefillet. Donotdamagetubefabricwall.
(3.) Slitfabricon backsideof deicer,in between
tubes,and3/4-inchbeyondtear.
(4.) Cuttwofabricpatchesto extend1/2-inchbeyondtear. Ensurestretchof fabricpatches
arewithwidthof tube.
(5.) Washandcemententirebuffedareaof deicerandonesideof fabricpatches.
(6.) Applypatchesfor eachtube,insertingeachpatchthroughslit,withuncemented
patches
sidesbackto back. Stitcheachpatchto surfacesidefirst. Tensionotherendsslightlyand
stitchon backside.
(7.) Washandcementexposedsurfacesof fabricpatches.
(8.) Replacegumin betweentubesandapplypatchto backside.
(9.) Maskofftherepairedareaon surfaceside. FillflushwithNeopreneputty.
(10.)Curesurfacesidefirstfor 22 minutesandbacksidefor 10 minutes.
(11.)Restoreconductive
surfaceon surfacesideof boot.
EFFECTIVITY:
040-999
30-10-00 Jan
PAGE
19
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
andOperation(continued)
A. Airfoil- Description
(m)HoleThroughDeicerOutsideof TubeArea
titledHolesorTearsThrough
(1.) Repairsurfacesideandpatchbackside(seeparagraph
Backsideof TubeArea). Curecompleterepairfor22 minutes.Restoreconductive
Cement).
Conductive
surface(seeparagraphtitledResurfacing
11. Installation
for air
for installingdeicersrequiresthatairplanehaveprovisions
Thefollowingprocedure
etc.
connections,
of LeadingEdges
(a) Preparation
primer.
If leadingedgesarepainted,removeallpaintincludingzincchromate
(1.) Withone inchmaskingtape,maskoff leadingedgebootarea,following1/2-inchmargin
cleaningoff
to eliminate
boots. Ensuretapeis maskedaccurately
for non-recessed
excesscementlater.
(2.) Cleanmetalsurfacesat leasttwicewithMEKor acetone.Forfinalcleaning,wipeoff
solventfilmquicklywithclean,dryclothbeforeit dries.
primeroverbareleadingedges.Whenhard,
NOTE: If desired,reapplyzincchromate
and
cleanbeforeapplyingcement.
surfaces
chromate
sand
scuff
Deicerscanbe installedon alodinedoranodizedsurfaces.
EC-801.
(3.) Fillgapsof skinsplicesthatleadunderdeicerswith sealingcompound
grommets.Removesectionsof dopedfabric
(4.) Removesumpplugsfromairconnection
holes,if necessary.Drawoutendsof non-kinkhose
usedto covertheair connection
holesin leadingedge. If holeis crackedor
sectionto protrudethroughconnection
replacehose.
deteriorated,
of Deicer
(b) Preparation
MoistencleanclothwithMEKor acetone.Carefullycleanrough,backsurfaceof bootat least
of cleanedareas.
twice. Changeclothsfrequentlyto avoidrecontamination
(c) MountingDeiceron LeadingEdge
cementbeforeusing.Brushononeevencoatto cleanedback
mixEC-1300L
Thoroughly
surfaceof bootandto cleanedmetalsurface.Allowcementto air dryfor a minimum1 hour.
Applysecondcoatto bothsurfacesandallowto airdry anotherhour. Keepambientinstallation
between40° and110°F. Longerdryingtimefor cementcoatsmaybe requiredas
temperature
99%. Deicerandleadingedgecanbecementeda maximum48 hours
humidityapproaches
beforeactualinstallationif cementedpartsarecoveredandkeptclean.
Snapa chalklinealongleadingedgeof airfoilsection.Darkenchalklineon leadingedgeand
whitereferencelineon bootwitha ballpointpen. Mostbootsaremadewithexcessmaterialat
inboardandoutboardedgesfor finaltrimmingafterinstallation.Somerecessedbootstrimon
upperandloweredges.
Jan
10/90
Jan 10/90
30-10-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
11. Installation (continued)
Usingclampsor safetywire, attachhoseto deicerconnectionsas follows:
1. Holdingbacksideof boot closeto leadingedge,fasten end of each non-kinkhoseto
correspondingair connectionstem. Use tinnermanor other suitablenon-kinkhose
clamps. Tighteneachclamp using slip joint pliers. Do not over squeezeclamp,damaging
hose.
2. Push hoseconnectionsintoeither leadingedge grommetsor seals. (Limithandling
cementedside of boot.) Reactivatecementalongcenterlineleadingedge surfaceand
boot in spanwisestrips,approximately6 incheswide. Rubberroll deicerfirmly against
leading edge,beingcareful not to trap air underdeicer. Alwaysroll parallelto inflatable
tubes. Positiondeicercenterlineto coincidewith leadingedge centerline. Hold boot in
positionwhile reactivatingabout 3 inchesaroundconnectionsand correspondingholesin
leading edge, usinga clean, lint-freecloth moistenedwith Toluol. Insertconnectionsin
leading edge holesafter cementhasdried to a tacky stateand rubberroll boot to leading
edge of tackyarea.
3. If deicer attachesoff line, use MEKto removeand repositionproperly. Avoid twistingor
sharp bendingof deicer.
4. Rubberroll,applyingpressureover entire deicersurfaceparallelto inflatabletubes. Roll
edgeswith narrowstitcher-roller.
CAUTION: AVOIDEXCESSIVESOAKINGOR RUBBINGOF CEMENT,WHICHCOULD
REMOVECEMENTFROMSURFACE.
Removeall maskingtape and clean surfacescarefullywith MEK. Preventsolventfrom
runningunderdeiceredges.
6. Apply maskingtape to deicer edgeswhere exposedtrimmedends or gaps between
sectionsmustbe filled with MMM EC-801sealingcompound.
7. Apply maskingtape to deicer approximately1/4-inchin from trailing edgesand to wing
skin approximately1/4-inchfromtrailing edges,both forminga neat,straightline.
8. Apply brush coat of A-56-Bcementto surfacesbetweentapesand to EC-801seams.
Ensureconductivecoating (A-56-B)is continuousfrom deicer surfaceto wing painted
surface.
9. Removetape immediatelyafter applyingA-56-Bcement (beforecementdries).
10. Installflow strips onto leadingedge using 3M EC1300Lcementas shownon Figure3.
5.
NOTE: Applicationof A-56-Bconductivecementis not necessaryon deicerscontaining
CONDUCTIVElabels.
WARNING: CEMENTSAND SOLVENTSUSED ARE FLAMMABLEANDTHEIR FUMES
TOXIC. CONDUCTALL WORKIN A WELLVENTILATEDAREAAWAY
FROMSPARKSOR FLAMES. (USE OF SOLVENTRESISTANTGLOVES
IS RECOMMENDED.)
If boots mustbe removedor loosened,use MEKto softenthe adhesionline. Applya minimum
of solventto seam linewhile applyingtensionto peel back boot. Removeslow enoughto allow
solventto undercutcementpreventingdamageto part. Avoid excessivequantitiesof solvent.
NOTE: Referto Figure3 for flow strip and deicerboots locations.
EFFECTIVITY:
040-999
30-10-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
andOperation(continued)
A. Airfoil- Description
BootandFlowStripLocations
Pneumatic
Figure3 (Sheet1 of 2)
EFFECTIVITY:
040-999
10/90 30-10-00
JanJan
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Airfoil - Descriptionand Operation (continued)
11. Installation (continued)
WingLeadingEdgeCenterline
FlowStrip
FlowStrip
± 0.060
Tolerance
Wing
LeadingEdge
BootandFlowStripLocations
Pneumatic
Figure3 (Sheet2 of 2) (continued)
EFFECTIVITY:
040-999
PAGE
23
30-10-0030-10-00
Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Airfoil- Description
andOperation(continued)
11. Installation(continued)
(d) AdhesionTest
Usingexcessbootmaterialtrimmedfromendsof wingandempennage
deicers,preparea test
specimenfor eachdeicerinstalled.Thespecimenmustbe a 1x 8 inchthickstripof boot
materialcementedto wingskinadjacentto installedboot. Leave1 inchof stripuncemented
to
attachclamp. Fourhoursor moreafterinstallation,
attachspringscaleto uncemented
endof
eachstripandmeasureforcerequiredto removestripat rateof 1 inchperminute.Applypull
180degreesto surface.
A minimumof 5 poundtension(pull)is requiredto removetest strip. If lessthan5 poundsis
required,acceptance
of bootadhesionis basedon thefollowingtests:
1. Carefullyliftonecomerof bootenoughto attachspringclamp.
2. Attachspringscaleto clamp. Pullup 180degreesto surfaceto bootis removed
diagonally.
3. If a forceof 5 poundsper inchof widthcanbe exerted,theinstallation
is considered
satisfactory.(Widthincreasesascornerpeelsback.)
4. Re-cement
comer.
NOTE: Reasons
for improperadhesionaredirtysurfacesandcementnotreactivated
properly
or mixedthoroughly.Corrosion
of metalskincanoccurif properadhesionis not
attained,especiallyaroundrivetheadsandmetalskinsplices.
If adhesionrequirementsare met, airplanecan be flown immediately.Do not inflate deicers
within 12 hours of installationor until adhesionstrengthof 8 - 10 poundsis obtained.
12. Maintenance
Cleandeicerswith mildsoapandwatersolution.In coldweather,washbootsin warmhanger,if
possible.If cleaningis doneoutdoors,useheatedsoapandwatersolution.If waterfreezeson
boots,use portablegroundheaterto thaw.
UseBenzolor non-leaded
gasolineas alternatives.Moistencleaningclothin solvent.Scrub
lightlyandwithclean,drycloth,wipebeforecleanersoaksintorubber.Sparingly
usepetroleum
productswhichdamagerubber.
13. IcexApplication
B.F.GoodrichIcesis a siliconebasematerialspecifically
compounded
to loweradhesionstrength
betweeniceandrubbersurfacesof deicers.Icexwillnotharmrubberandoffersaddedozone
protection.
Properlyappliedandrenewedat recommended
intervals,Icexprovidesa smoothpolishedfilm
alsohaveless
irregularities
on rubberpartssurfaces.Iceformations
whichevensout microscopic
chanceto clingandice is removedfasterandcleanerwhendeicersareoperated.
Icexwill notpreventor removeiceformations,
butkeepsit fromgettinga strongfoothold.
BeforeapplyingIcex,thoroughlycleandeicerorotherrubbersurfaceswithragdampenedwith
non-leaded
gasolinefollowedbyscrubwashof mildsoapandwater.Allowtimefor surfacesto
dry.
12 inchesfromsurfaceandspraysparingly.If
ShakeIcexcanwell. Holdnozzleapproximately
applicationistoo heavy,resultingstickysurfacepicksup runwaydustandinhibitsice removing
efficiency.
Dueto naturalabrasiveeffectson leadingedgesof deicersduringflight,reapplyIcexto wingsand
empennage
deicersevery150flighthours.
EFFECTIVITY:
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24 30-1
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Jan
0-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Airfoil- Description
andOperation(continued)
14. Resurfacing
Conductive
Cement
(a) Materials
Thefollowingmaterialsare required
to removeandreplacedamagedcoating:
(1.) Finegritsandpaper.
(2.) Twoinchpaintbrush.
(3.) Oneinchmaskingtape.
(4.) Conductive
Neoprene
cement(No.A-56B,B.F.GoodrichCo.).
(5.) IsopropylAcetate,FederalSpecification
TT-1-720.
(6.) Alternatesolvent- (ToluolorToluene).
CAUTION: CEMENTSAND SOLVENTSUSED FOR RESURFACINGARE FLAMMABLE
AND FUMESARE SLIGHTLYTOXIC. CONDUCTALL WORKIN A WELL
VENTILATEDAREAAWAYFROMSPARKSOR FLAMES.
(b) Procedure
Duringcoldweather,placeairplanein warmhangerandpositionbootsin linewithoneor more
blastheaters.Complete
resurfacing
beforeotherworkto allowtimefor newcoatto cure.
(1.) Cleandeicerthoroughly
withIsopropylAcetate.
(2.) Roughenentiresurfaceof bootwithfinegritsandpaper.
(3.) Cleansurfaceagainwithclean,lint-freeclothmoistened
withcleaningsolvent.
(4.) Applymaskingtapebeyondupperandlowertrailingedgesleaving1/4-inchgapof bare
metal.
(5.) Maskoff anylegibledeicerbrands.
(6.) Applyonebrushcoatof A-56-Bcementto deicer.Allowto dry at least1 hour.Apply
secondcoatandallowto dryat least4 hoursbeforeoperatingdeicers.Planecanbe
flownassoonascementis dry.
NOTE: IfA-56-Bcementis 3 monthsold or more,dilutecementwithIsopropylAcetateto
obtainproperbrushingconsistency.
Mixthoroughly
withapproximately
5 partscement
to 1partIsopropylAcetate.
EFFECTIVITY:
30-10-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Air Intakes- Descriptionand Operation
The PA-42-720containsan engineinlet Lip Deicesystemin the nacelle.
The lip deicersystemconsistsof two individualsystemsone for eachenginelinkedtogetheran
ammeterand a selectorswitchthat enablesit to monitoroperationof either leftor right system.
Each lip deicesystemconsistsof an electricallyheated lip, a timer shunt,circuitbreakers,and a switch
to controlsystemoperation.
To conserveelectricalpowerdrawnfrom aircraftelectricalsystem,currentis cycledto deicerheaters
at timed intervals,not continuously.
NOTE: Heatingcan beginat any phasein the cycle dependingon timer positionwhen switchwas
turnedoff from previoususe.
B. Fault Isolation
Problemspeculiarto deicingsystemare listedin Chart 1 alongwith probablecauses and suggested
remedies.
CHART 1 (Sheet 1 of 5)
FAULT ISOLATION (ENGINE DEICING SYSTEM)
Fault
Ammetershowszero
current. (All4 phases
of the 2 minutecycle.)
EFFECTIVITY:
040-999
Cause
Remedy
Trippedcircuitbreaker.
Locateand correct short
beforesetting circuit
breaker.
Defectivepowersource.
If no voltage intoswitch,
locate and correct break.
Ammeterselectswitch
faulty.
If no voltage at switchoutput
with voltageat switch input,
replacethe switch. If voltage
is satisfactoryat switchoutput,
go to next step.
Ammeterfaulty. (If some
or all deicers heatwith
ammeterat zero, replace
the ammeter.)
Testfor voltage up to and out
of ammeter. If low or zero
output and input satisfactory,
replaceammeter. If no voltage
to ammeter,locateand fix
break betweenswitchand
ammeter.
Breakbetweenammeter
and timer.
Disconnectharnessat timer
and checkvoltage at Pin B
(of harness)to ground. If
none, locate and correct
break.
30-20-00Jan
Jan10/90
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. FaultIsolation(continued)
CHART 1 (Sheet2 of 5)
FAULTISOLATION(ENGINEDEICINGSYSTEM)
Fault
Ammetershowsnormal
currentpartof cycle,
zerocurrentrestof
cycle.
Ammetershowsnormal
currentpartof cycle,
lowcurrentrestof cycle.
Cause
Remedy
Opencircuitbetweentimer
andheatingelement.
Useheattestto finddeicers
notheatingandtestfor
voltageon thatcontactof
wireharnessplug. (At
brushblockassemblyor
connector.)Ifzeroover2
minutes,locateandfix
breakin wiringfromtimer
to wireharnessplug.
Burnedoutlipdeicer.
Replace.
Breakbetweenbrushblock
assemblyandpropdeicer
leadstraps.
If thereis voltageto brush
blockwire harnessplug,
try voltageat junctionof
deicerleadandslipring
lead. If novoltage,find
andcorrectbreakin wiring
withinbrushblockor no
contactof brushto slipring.
No groundcircuit,one
engine.
If voltageis foundat deicer
leads,locateandfix break
fromdeicerto ground.
of differentphases
Elements
heatingin thesamephase.
Locateandrepairincorrect
connections.
Breakin deiceror slipring
leads.
deicersto
Disconnect
checkheaterresistance.
locateand
If satisfactory,
fix breakin slipringleads.
High resistancein circuit
with low current.
If notin contactof brush
to slipring(including
groundbrush),tracewiring
to deicerandtotimerto fix
partiallybrokenwire,loose
or corrodedconnection.
SheddingAreaI and/or
SheddingAreaIIphases
of lip deicerinoperative
butPartingStripheater
working.
ReplacedeicerIfcurrent
existsat all terminals
duringacycle.
EFFECTIVITY:
040-999
30-20-00
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. Fault Isolation (continued)
CHART 1 (Sheet3 of 5)
FAULTISOLATION(ENGINEDEICINGSYSTEM)
Fault
Ammetershowlow current
over entire cycle.
Ammeter showsexcess
current over entire cycle.
Ammeter showsnormal
current part of cycle,
excess currentrest of
cycle.
Cause
Remedy
Aircraftvoltage low.
Checkvoltage into switch.
Ammeterfaulty.
Testfor voltageup to and
outof ammeter.If low
or zerooutputandinput
replaceammeter.
satisfactory,
If novoltageor ammeter,
locateandfix breakbetween
switchandammeter.
High resistanceup to
timer.
Checkfor partiallybroken
wire, loose or corroded
connectionin wiringfrom
aircraftsupplyto timer
input.
Ammeterfaulty.
Test for voltageup to and
out of ammeter. If low or
zero output and input
satisfactory,replace
ammeter. If no voltage
to ammeter,locateand
fix break betweenswitch
and ammeter.
Groundbetweenammeter
and timer.
Disconnectharnessat timer
and with ohmmetercheck
from Pin B (or harness)
to ground. If groundis
indicated.locateand correct
short.
Groundbetweentimer and
brush block.
Disconnectleads at brush
block and, with ohmmeter,
checkfrom powerleadsto
ground. If ground is indicated, locateand correct
short.
Groundbetweenbrush
block and deicers.
(Excludingground
brush circuit.)
If no shortexistsat
brush-slipringcontact
checkfor groundfrom
slipringleadto propeller
assemblywhileflexing
slipringanddeicerleads.
If a groundis indicated,
locateandcorrectshort.
EFFECTIVITY:
040-999
30-20-00 JanPAGE
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10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Fault Isolation (continued)
CHART 1 (Sheet4 of 5)
FAULTISOLATION(ENGINEDEICINGSYSTEM)
Fault
Ammetershowsnormal
currentpartof cycle,
excesscurrentrestof
cycle. (continued)
Ammeterdoes not
"flick"approximately
every 34 seconds.
Ammeterflicks between
34 secondphase periods.
Cause
Remedy
Short betweentwo
adjacentcircuits.
Checkfor cuts or low
resistancebetweencircuits.
If any,locate and correct.
Timerfaulty.
Testtimer.
Timergroundopen.
Disconnectharnessat timer
and checkwith ohmmeter
from Pin G (of harness)to
ground. If no circuit,fix
break per schematicdiagram.
Timer contactsarewelded
(causedby shortcircuit
in system).
Testtimer. If timer does not
cyclewith voltage at Pin B,
replacetimer but be sure
short causingoriginalfailure
has been locateand corrected.
Looseconnectionbetween
aircraftpower supply
and timer output.
If trouble occursover entire
cycle,trace wiringfrom
power sourceto timer input
to locateand tighten loose
connection.
Looseor poor connection
timer to deicers.
If trouble occursin part of
cycle, find whichdeicers
are affectedand checkfor
roughor dirty slip rings
causingbrush to "skip" or
poorconnectionat plug.
If not this, trace circuits
to locate and fix loose or
poorconnection. (If all
heaterson one deicerare
affected,checkthe ground
circuit.) Flexdeicerstraps
for break in deicerstraps.
Timercycleserratically.
Testtimer.
0
EFFECTIVITY:
PAGE4 30-2000
Jan10/90
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Fault Isolation (continued)
CHART 1 (Sheet5 of 5)
FAULTISOLATION(ENGINEDEICINGSYSTEM)
Fault
Radio noiseor interference
with deicerson.
Cause
Remedy
Brushes"arching."
Checkbrush alignmentas
shownin 30-60-00,Figures
502 and 509. Lookfor
roughor dirty slip rings. If this
is the cause, clean machineor
replaceslip ring assembly,
as required. Checkslip ring
alignment.
Looseconnection.
Referto Ammeterflicks
between34 secondsphase
periods.
Switchfaulty.
Try jumperwire across
switch if radio noise
disappears,replacethe
switch.
Wiringlocatedwithin 8
inchesof radio equipment
wiring.
Relocateat least 8 inches
awayfrom inputwiringto
radio equipment.
Cyclingsequencenot
correct.
Crossedconnections.
Checksystemwiringcircuit
diagramfor improperconnections. (Referto 91-00-00)
Rapidbrushwear or
frequentbreakage.
Brushblockout
alignment.
Checkbrush alignment.
Slip ring wobbles.
Checkslip ring alignment
with dial indicatoras
shownin 30-60-00,
Figure501.
C. Air Inlet Lip DeicerSystem
1. OperationalCheck
(a) Removetop enginecowl. Unpluglip deicerboot at plugand ground dead disconnect.
(b) Withauxiliarypowerpluggedin and deicer switchon, checkfor properoperationof ice
deflectordoor underneathair inlet screenby lookingbackthroughair inlet and down around
eachengine side. Also checkoperationof bypassdooron undersideof bottomenginecowl at
rear of engine.
EFFECTIVITY:
040-999
30-20-00JanPAGE
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10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
C. Air InletLip DeicerSystem(continued)
1. Operational
Check(continued)
CAUTION: THE LIP CAN BE DESTROYEDWITHTHE COMBINATIONOF THE PARTING
AND THE HEATINTENSITYOF
STRIP ELEMENTBEINGON CONTINUOUSLY
THE LIP DEICERELEMENTS.OBSERVELIP CLOSELYWHILETESTINGFOR
OVERHEATING.
(c) Threewaysto safetycheckoperationof thelip deicerareasfollows:
for each
(1.) Disconnect
deicerplug. Usinga precisionmeter,checkthefollowingresistances
heatingelement.
1.10ohms.
is approximately
(a.) ShedAreaI Resistance
1.10ohms.
is approximately
(b.) ShedAreaII Resistance
1.00ohms.
is approximately
(c.) ThePartingStripResistance
(2.) Obtain28 Vdcpowersourcecapableof supplying30 amps.Connectnegativeleadto
to 3 terminalsof deicerplug.
deicergroundleadsandtouchpositiveleadindividually
(3.) Have1 personin thecockpitpositionmasterwithdeicerswitcheson. Activategroundtest
switchwhilean assistantconnectsdeicerplugto matingplug. Supplysystempowerlong
plugandwaituntilsecondlip deicerphase
enoughto completecheck.Finally,disconnect
begins.
CAUTION: DO NOT HOLDCONNECTIONSO DEICERBECOMESTOOHOT TO
TOUCH.
NOTE: Thetimeronlyoperatesas longasthegroundtest switchis activated.
riseof thebootsmustbe noticeable.If localhotspotsareapparent,bootis
(d) Temperature
damagedandmustbe replaced.
2. Removalof InletDeicers
If inletdeicerlipbecomesdamagedor defective,requiringremovalof unitfromlowercowl
proceedas follows:
assembly,
(a) Removeupperandlowerenginecowling(see71-10-00).
(b) Locateinletdeicercannonplugconnector.Removewiresfromconnector.
(c) Removeclampsecuringinletdeicerwireharnessto lowercowlassembly.
(d) Removemachinescrewsfrominnerandouteredgesof inletdeicer.
(e) Pullinletdeicerawayfromlowercowlassemblyfar enoughto allowaccessto wireharness.
(f) Gentlypullinletdeicerwireharnessthroughfireshieldtube. Removedeicerassemblyfrom
aircraft.
3. Installationof Inlet Deicers
(a) Whileholdinginletdeicerin position,runendof inletdeicerwireharnessthroughfireshield
tube.
machinescrews.
(b) Positioninletdeicerassemblyon cowlassembly.Securewithappropriate
(c) Securewireharnessto cowlassemblywithclamp.
(d) Reattachinletdeicerwireharnessto cannonplugconnector.
(see71-10-00).
(e) Installloweranduppercowlassemblies
630-20-00
30-20-00
10/90
Jan
Jan 10/90GE
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
4. ElectricalCheck of Inlet Deicers
Ammeter
(ForReferenceOnly)
Wiring Diagram,Left Propellerand EngineAir InletLip DeicingSystem
Figure 1
(ForReferenceOnly)
Ammeter
Wiring Diagram,RightPropellerand EngineAir Inlet Lip DeicingSystem
Figure 2
EFFECTIVITY:
040-999
7
PAGE
30-20-00
30-20-00
Jan
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
4. ElectricalCheckof Inlet Deicers
(a) Check air inlet deicersby disconnectingharnessplugand groundconnectioninsidelower
enginecowl and removinguppercowl.
(b) Check electricalresistanceof eachelementbetweeneach pin in plug and groundlead. Pin C
and E is the parting stripelement;Pin D and F is sheddingarea (I) elementand Pin B and F is
the sheddingarea (II) element. (See Figures1 & 2 and Chart2.)
(c) Check systempowercycle time and sequencewith a voltmeterand pins in connectoron
aircraft harnesswith systempoweron.
(d) Whenelectricalcheckis completed,reconnectcircuitand installenginecowl.
°.
°
(e) Lipdeice thermoswitch opensat 150° and resetsat 100 +/- 10
CHART 2
INLET DEICERS ELECTRICAL SPECIFICATIONS
TIMER
SEQUENCE
ELEMENT
HEATED ZONE
TIME
SEC.
LOAD AMPS
@ 28 VDC
RESISTANCE
OHM
Cont.
PartingStrip
Zone A
Cont.
28.0
1.0
SheddingArea I
SheddingArea
Zone B
34-ON
102-OFF
25.5
SheddingArea
34-ON
25.5
SheddingArea II
1.1
D. EngineAir Inlet Ice ProtectionSystem
1. Removalof IceDeflectorDoorTransmission (Figure401)
To removetransmissionfrom aircraft,proceedas follows:
(a) Removeenginecowling.
(b) Disconnectelectricalleadsfrom transmissionassembly.
(c) Disconnecttransmissionclevisend fromtorquetube assembly.
(d) Disconnecttransmissionfromengine mountingbracket. Removecompleteassemblyfrom
enginecompartment.
2. Installationof Ice DeflectorDoorTransmission(Figure401)
NOTE: To facilitateinstallation,ensureice door and transmissionare in closed position.
(a) Positiontransmissionassemblyon enginemountingbracket. Securewith properhardware.
Allow transmissionto rotate on mountingbolt.
(b) Attachtransmissionclevis to torqueboltwith clevis pin,washers,and cotter pin.
(c) Connectelectricalleadsto transmissionassembly.
(d) Check adjustmentsusing paragraphtitledAdjustmentof EngineIce ProtectionSystemin this
chapter.
EFFECTIVITY:
PAGE
8
Feb1/98
30-20-00
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
D. Engine Air Inlet Ice Protection System (continued)
VIEW A
Side View of
Ice DeflectorDoor(OPEN)
12. BypassDoor Assembly
11. Hinge
10. Bolt, Washer,Bushingand Nut
9. RodAssembly
8. Pin
7. LimitSwitches& MountingBracket
Shims73050-2or 73050-3maybe
addedhereto maintaincontour
with cowl.
.12
VIEWB
Side Viewof Bypass Door (OPEN)
Engine Air Inlet Ice Protection System
Figure 401
EFFECTIVITY:
040-999
9
30-2000PAGE
30-20-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
D. EngineAir Inlet Ice ProtectionSystem (continued)
1. PartingStrip
7. Urethane
ErosionCoat -
A-A
(ZoneB)
'
3. SheddingArea (ZoneC)
I
EngineAir Inlet LipAssembly
Figure402
EFFECTIVITY:
040-999
Jan 10/90 30-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
D. EngineAir Inlet Ice ProtectionSystem (continued)
3. Cleaning,InspectionAnd Repairof Ice DeflectorDoorTransmission(Figure401)
(a) Removeenginecowling(see 71-00-00).
(b) Cleantransmissionassemblywith suitablesolvent.
(c) Inspecttransmissionscrewshaftfor excessiveback lash as follows:
(1.) Disconnecttransmissionfrom ice deflectordoortorque tube lever.
(2.) Clamppliers (visegrips) to screwshaft using light pressureon transmissionscrew.
(3.) Move pliersto rotatescrewshaftand ensure slightmovementis felt (notto exceed0.312
inch on a 6 inch radiusfrom shaft).
(d) Checktransmissionsleeve,screwshaft,and rod endsfor distortion.
(e) Cleanand dry transmissionscrewshaft and sleeve. Applycoatingof AircraftActuatorGrease
(MIL-G-23827)to transmissionshaft.
(f) Repacktransmission,if disassembled,75 percentfull with Dukesgrease (P/N 2196-74-1).
4. Adjustmentof EngineIce ProtectionSystem (Figure401)
(a) Removeice deflectordoor interconnectrod.
(b) Adjust rear microswitch contactscrewto triggerswitchwhen linkageis lockedin DOWN
position. Turn screwout four full turns.
(c) Adjustforwardmicroswitchcontact screwto trigger switchat ice deflectordoor UP position(ice
deflectordoor paralleland flush with forwardduct). Turn screwout one full turn.
(d) Runextensionmotorto full ice deflectordoor UP position. Adjust bypassdoor to seal.
(e) Installcowl with ice deflectordoor in UP position(paralleland flush with forwardduct). Adjust
interconnectrod to allow retainingpin to slip into position.
(f) Testrun ice deflectordoor,bypassdoor system,and recheckup and down positions.
EFFECTIVITY:
040-999
30-20-00PAGE
11
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Windows,Windshieldsand Doors
1. HeatedWindshield
(a) FunctionCheck
Thefollowingsteps determineif windshieldheatingelementand timer are functioningproperly:
(1.) Connect24-volttest light to positiveand negativeterminalsof windshield.
(2.) Set switch markedWindshieldHeat to ON position. Test light mustindicatecurrentbeing
deliveredto windshield.
(3.) Place hand againstwindshieldto determineif windshieldheatingelementis operating.
(4.) Ensuretest lightextinguishesbeforewindshieldis too hot to hold hand againstit. This
indicatesthat temperaturesensingelementis operatingproperlyand has passedthrough
thermostaticon-offcycle.
CAUTION: USE CAUTIONDURINGGROUNDOPERATIONTO PREVENT
OVERHEATINGAND POSSIBLEDAMAGETO WINDSHIELD.
(5.) After completingcheck,set WindshieldHeatto OFFposition. Removetest light.
(6.) See 56-00-00for additionalservicedata.
(b) Copilot'sHeatedWindshield
Windshieldis identicalto pilot side and is servicedlike standardleftwindshield.
2. WindshieldWiperMechanism
Windshieldwipersare standardequipmenton left and rightwindshield. Tooperatewindshield
wipers,turn switch on lower right side of instrumentpanelto HIGH or LOWposition. Whenturning
wipersoff, turn switchto OFFor PARKposition. The OFF positionstops bladesin placewhile
PARKpositionreturnsbladesto center postposition.
WARNING: NEVEROPERATEWINDSHIELDWIPERON DRY WINDSHIELD.IT CAN
SCRATCHGLASSAND SHORTENLIFE OF WIPERBLADES.
The windshieldwiper motoris locatedforwardof bulkheadat Station57.00,on upper left portionof
fuselageskin. A flexibleshaft runs from electricmotorand transmissionto a converter(from which
wiper runs)on right side of same bulkhead.
(a) Removalof WiperMechanism (Figure401)
(1.) Removeaccesspanelon left and right sidesof nosesection.
(2.) Cut lockwire at bolt securingarm to serratedconvertershaft and removebolt.
(3.) Loosenadjustmentnut. Lift wiper arm off convertershaft.
(4.) Removetwo screwsfrom shaftcover aroundconvertershaft. Removecover and old
sealantfrom shaft.
(5.) Disconnectelectricalconnectionto wiper motorand flexibledrive shaftfrom converter.
(6.) Removeremainingscrewsholdingmotorand converterto airplane. Removecomplete
assembly.
EFFECTIVITY:
040-999
30-40-00 PAGE
1
Jan 10/90
PIPERAIRCRAFT
PA42-720 (Advanced Trainer)
MAINTENANCEMANUAL
A. Windows,
Windshields
and Doors(continued)
WiperMechanism(continued)
2. Windshield
(b) Installation
of WiperMechanism(Figure401)
(1.) Timewipermotorandconverterbeforeconnecting
twounitstogether,asfollows:
to endof travel(orparkposition)andat serrated
(a.) Rotatedriveshaftin converters
convertershaft.
(b.) Temporarily
connectelectricalconnectorto wipermotorandoperatemotoruntil
switchendsin PARKposition.Disconnect
electricalconnector.
(2.) Assemblewipermotorandconverterbyscrewingunitstogetherwithflexibledrive
assembly;backofffor bracketalignment.
(3.) Assembleunitsslowlyuntilflexibledriveassemblyengagesconverter
shaft. Alignment
mustbe automatic.If severebindingoccurs,backoff andreassemble.
unitsintoairplaneandsecureto mountingbrackets.Donotinstallseal
(4.) Installassembled
coversatthistime.
throughfuselage.Position
(5.) Applybeadof RTVsealeraroundconvertershaftsextending
andsecureshaftcoverin placewithretainingscrews.
(6.) Connectelectricalconnectorto wipermotorandreplaceaccesspanels.Turnwiperswitch
momentarily
to PARKposition.
(c) WiperBladeandArmRemoval(Figure401)
(1.) Cutlockwireat boltsecuringarmto serratedconvertershaft;removebolt.
nutto relievearmtension.Removewiperarmfromconvertershaft.
(2.) Loosenadjustment
(3.) Pullout lockon wiperbladeto removebladefromarmassembly.
(d) WiperBladeandArmInstallation(Figure401)
(1.) Installwiperbladeto assembly.Ensurebladeis lockedto arm.
to PARKposition.Placearmandbladeassemblyon
(2.) Turnwiperswitchmomentarily
by
centerpostcenterline
serratedconvertershaftsowiperbladeclearswindshield
2.00to 2.25inches.
approximately
(3.) Installboltthroughwiperarmintoconvertershaft. TightenandsafetywithMS20995-C41
lockwire.
(e) WiperBladeandArmAdjustment(Figure401)
cam.
byunlockingbladeheightadjustment
(1.) Adjustwiperbladeheighton windshield
collarby2.50±
sobottomof bladeclearswindshield
(2.) Adjustbladeheighton windshield
cam.
0.50inches.Lockadjustment
stud. Rotateblade
(3.) Adjustwiperbladeangleby looseningnuton wiperbladeattachment
untilit is parallelwithwindshieldcenterpost. Tightennuton stud.
studfortensionof 3 - 4 poundswithbladepivotpoint
(4.) Adjustnuton wiperarmadjustment
in PARKposition.
NOTE: Checkthatthe baseof theadjustmentstudis in the recessprovidedin thewiper
arm.
EFFECTIVITY:
040-999
Jan10/90
30-40-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Windows, Windshields and Doors (continued)
Wire WrappedAroundNut
Wire - P/N 151 295
(MS20995-C20)-
Twisted Wire Centered Under Arm
Wire WrappedAroundArm
Wiper Blade
TvoicalWindshieldWiperBlade
10.Bolt, Washer,Nut
12. Blade
7. WiperShaftCover
6. Converter
10.Bolt, Washer,Nut
9. Wiper
Mounting
Bracket -
4. DriveAssembly
3. Bolt,
7. Wiper
Shaft
Cover
5. DriveAssembly
2. Motor
1.
6. Converter
WindshieldWiperInstallation
Figure401
EFFECTIVITY:
040-999
PAGE30
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Propellers- Descriptionand Operation
The propellerdeicersystemconsistsof two individualsystems. Onefor each engineis linkedtogether
by an ammetercontaininga selector switchwhich enablesit to monitoroperationof the leftor right
system.
For propellerdeicercycling sequence,see cycle sequence(91-60-00). The systemcan be used
continuouslyin flight, if needed.
NOTE: Heatingcan beginat any phasein cycledependingon timer positionwhen switchwas turned
off previously.
B. MaintenancePractices
1. DeicerSystemOperationalCheck
CAUTION: THE LIP CAN BE DESTROYEDWITHTHE COMBINATIONOF THE PARTING
STRIP ELEMENTBEINGCONTINUOUSLYON THE HEATINTENSITYOF THE LIP
DEICERELEMENTS.OBSERVEBOOTCLOSELYWHILETESTINGFOR
OVERHEATING.
(a) Chockwheelsand operateengineat neartakeoffpower.
(b) Tum deicersystemswitchon for side beingchecked. Activategroundtest switch.
(c) With ammeterselectorswitch in properposition,observeammeterfor at least2 minutes.
(d) Ensureammeterneedleflickers approximatelyevery34 secondswhen operatingtimer step
switch. Ensureneedleis in green arc during all four cycle phases.
(e) Stop engine,removetop enginecowl, and unpluglip deicer boot at plugand ground lead
disconnect.
(f) Plugauxiliarypowerin, turn deicerswitchon, and checkoperationof ice deflectordoor
underneathair inlet screenby lookingback throughair inlet and down eachengineside. Also
checkoperationof bypassdoor on undersideof bottomenginecowl at rear of engine.
(g) Haveassistantactivategroundtest switch. Adjust propellerdeicer bootoutboardelements
followedby inboardelements.
NOTE: Becausethe lip deicer is inoperative,the ammeterdoes not readthroughtwo phases
of the two minutecycle and reads slightlylowerthan that observedwith engine
running,during two propdeicerphases.
(h) Twoways to safety checkoperationof lip deicerare as follows:
(1.) Obtain 28 Vdc powersourcecapableof supplying30 amps. Connectnegativelead to
deicerground leadand touchpositivelead individuallyto three terminalsof deicer plug.
(2.) Connectdeicergroundwire at quick-disconnectterminal,positioncockpitmasterand
deicer switcheson, and activategroundtest switch. Haveassistantconnect deicerplugto
matingplug supplyingsystempowerlong enoughto noticetemperaturerise in boots.
Finally,disconnectplug and wait until secondlip deicerphasebegins.
WARNING: DO NO HOLDCONNECTIONSO DEICERBECOMESTOO HOTTO
TOUCH.
NOTE: The timer only operatesas longas groundtest switch is activated.
riseof bootsmustbe noticeable.If localhotspotsareapparent,bootis damaged
(i) Temperature
andmustbe replaced.
EFFECTIVITY:
30-60-00JanPAGE
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10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
2. Usingthe Ammeter
In flight or during groundtesting, use ammeterto indicateconditionof most electricalproblems.
The troubleshootingchart is based on ammeterresults.
NOTE: Whentroubleshooting,
useammeterandheattestto determinecircuitsinvolved.Use
circuitdiagramto checkvoltagesor continuity.
3. HelpfulTips
(a) If ammeterreadingdrops to one-thirdnormalcurrent,one heatercircuitis open.
(b) Excesscurrentreadingon ammeteralwaysindicatespower lead is shortedto ground. Locate
and correctgroundedpower lead immediately.
NOTE: Manytimers are returnedfor repairand found fully workablewhen tested. Complete
test describedin TimerTest beforediscardingtimer.
1.
7. LeftCircuitBreakerPanel
DeicePowerControlRelays
2. PropellerDeicerBoot
Propellerand EngineAir Inlet Lip DeicerSystem
Figure 1
30-60-00
Jan 10/90
10/90
30-60-00
Jan
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
4. 50-HourInspection
checkfor eachengine.
(a) Performentiredeicersystemoperational
deicerammeterand
(b) Removespinnerdomeandupperenginecowl. Withassistantobserving
deicer
wiring.(particularly
flexall accessible
deicerswitchon andgroundtestswitchactivated,
andwiring.)If any
leadstraps,leadsfromslipringassemblyandfirewallelectricalconnectors
of ammeterneedle,otherthan34secondflickerof cyclingexists,locateandcorrect
movement
shortorbreakimmediately.Performtestfor leftandrightsystems.
5. 100-HourInspection
(a) Removeenginecowling.
(b) Conduct50-hourinspection.
byoperatingeachengineat neartakeoff
(c) Checkfor radionoiseor radiocompassinterference
powerwith radiogearon,whileturningeachdeiceswitchon andoff. If noiseor interference
whenswitchis off,see30-20-00,Chart1 for fault
occurswithdeicerswitchon anddisappears
isolation.
aretight. Checkfor loose,
andelectricalconnections
(d) Ensureallclamps,clips,mountings,
broken,or missingsafetywire.
(e) Checkdeicerbootsfor wrinkled,loose,torn,orcut areasaroundendsof boots,wherepropeller
alongleadingedgesandflat orthrustface
bootstrappassesunderstrapretainer,especially
propellerboots.If heaterwiresareexposedin damagedareas,or if rubberistacky,swollenor
deteriorated,
replacedamageddeicer.
areproperlypositioned
andsecured.Lookforcracksor other
NOTE: Ensurestraprestrainers
damage.Operatepropellerfromfullpitchto featheringandensuredeicerleadstraps
are nottensionedor pinchedbypropellerblade.
surface,cracks,burnedor discoloredareas,and
(f) Checkslipringsforgouges,roughened
depositsof oil, greaseordirtasfollows:
slipringswithCRC-2-26solvent.(See91-00-00,Listof
(1.) Cleangreasyor contaminated
for
vendor
information.)
Consumable
Materials
is noticed,setup dialindicator(Figure501)to checkslip
if
wobble
exists
or
wear
(2.) If uneven
ringto propellershaftalignment.
SuggestedUse of Dial Indicator
Figure501
EFFECTIVITY:
30-60-00JanPAGE
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10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Maintenance
Practices(continued)
5. 100-HourInspection(continued)
or otherphysical
(g) Examinebrushblockmountingbracketsandhousingfor cracks,deformation,
damage.
(1.) Ensureeachbrushridesfullyon itsslipringover360° (seeFigure502). If alignmentis
bracket.(Shimis a seriesof laminates
off,shimwherebrushblockattachesto mounting
andcan be peeledfor properalignment.)If oldshimis notthickenough,installnewone.
SlipRing
BrushLocated
SlipRing
NotchWornin Brush
Dueto Misalignment
Centeringof Brusheson Slip Rings
Figure502
(2.) Checkfor properbrush blockto slip ringsclearance(Figure509). If incorrect,loosen
mountingscrews,place in proper elongatedholes,and tightensecurely.
(3.) Checkbrushesfor wear limitation(Figure503).
(4.) Visuallycheckblockfor approximately2° angleof contact (Figure509). If incorrect,
loosen mountingscrews,twist block,and ensure properclearancelimitswhen tightening.
CAUTION: DO NOT HOLD GROUNDTEST SWITCHON FOR ANY LENGTHOF TIME
WHICHCOULD CAUSEOVERHEATING.
flex
(h) Operatedeicersystemsandwhileassistantobservesammeter,inspectandphysically
to switch,andto aircraftpower
wiringfrombrushblockthroughfirewall,to timer,to ammeter,
every34 secondsin cycle.
supply.Theammetermustflickeras timerswitchesapproximately
Jumpsorflickersat othertimeintervalsindicatelooseor brokenwiring. Checkcontinuityin
affectedharnesswhileflexingandproddingeachwirein areacausingproblem.UseWiring
Diagram,30-20-00,Figure2, to tracecircuitry.Performsameteston engineinletlip deicers
with systemsswitcheson andan assistantpressinggroundtest switch.
6. CheckingForBrushWear
Insertsmalldiameterwirethroughholein rearof brushretainerassembly(referto Figure503).
Replacebrushesif the lengthof theinsertedportionof wiremeasuresmorethan1 25/64inches.
EFFECTIVITY:
040-999
30-60-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
MeasuringBrushWear
NOTE:
Measurebrushwear as shown,
X-dimension(inches)
given indicateswhen
brushesmustbe replaced.
During measurementonly
1/16 inch of brush shouldbe
allowedto protrudefrom
modularbrush. This is the
normalpositionof the
brushwhen installedon the
/
aircraft.
ModularBrushAssembly
X-Dimension(Inches)
Must Replace
3E2044-1
BrushesWith Rods
BrushesWithoutRods
23/64
1 25/64
ModularBrushAssemblyand BrushWearCheck
Figure503
7. ReplacementOf Brushes
WARNING: USE ONLYB.F.GOODRICHBRUSHES.DO NOT SEPARATEUNITSWHEN
REPLACINGBRUSHES. FAILURETO FOLLOWTHESEINSTRUCTIONSMAY
RESULTIN FAILUREOF THE DEICERUNIT.
NOTE: It is not necessaryto removethe individualunitsfrom the modularbrush assemblyfor
brush replacementwhen this procedureis followed.
(a) Removeold brush.
(1.) Removescrewsecuringterminalto housingbase. Notebrush identificationA, B, or C.
(2.) Removeterminalfrom brush lead and removebrush throughbrushopeningof unit.
(3.) Inspect insideof moduleunitto ensure no foreign materialis present.
NOTE: If moduleunit housing is wornor damaged,replacethe entire module.
(4.) Cleanoutsideof brush openingto removeanycarbon deposits.
EFFECTIVITY:
040-999
30-60-00JanPAGE
5
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Maintenance
Practices(continued)
7. Replacement
Of Brushes(continued)
(b) Preparenewbrush(seeFigure504).
(1.) Slidetubingoverbrushleadso endof tubingalmostcontactsthebrush.
(2.) Formleadin an arcasshown.
(c) Installbrushin module(seeFigure505).
(1.) Insertleadintobrushopening.Slidebrushintobaseuntilleadprotrudesthroughleadexit
hole.
(2.) Compressbrushandpull leadto obtainmaximumavailablelengthof leadoutsidemodule
base.
(3.) Securebrushin compressed
stateusingrudderband(seeFigure506).
(d) Installterminal(seeFigure506).
(1.) Withbrushcompressed,
slidetubingto within3/16inchof theendof thebarewire(as
shown).
(2.) Installringterminalsotheendof the insulating
tubingis positionedinsidethe insulated
jacketof theterminalso no barewireis exposed.
(3.) Crimpterminalin placewithrecommended
crimpingdieandtool.
(e) Attachbrushlead(seeFigure507).
(1.) Replacescrewandwasher(andspacerif needed)as shown.
(2.) IdentifymoduleunitA, B, or C (asrequired)
withpermanent
ink orwiremarker.
(3.) Removerubberbandandcarefullypullbrushuntilall slackin leadisencasedinside
module.
(4.) Compressandreleasebrushto ensureit doesnotbindor hangup insidemodule.
InsulatingTubing
Leadwire
Lead ExitHole
ModuleBase
PreparingNew Brush
Figure504
InstallingBrush
Figure505
RubberBandting)
RingTerminal
AMP32442)
Insulating
Tubing
InstallingTerminal
Figure506
Screw
AttachingBrushLead
Figure507
EFFECTIVITY:
040-999
Jan
10/9030-60-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Maintenance
Practices(continued)
8. Alignment
Of Brushes(referto Figures508and509)
at installation
mustbe checkedanytimethemodularbrushassembly
NOTE: Thebrushalignment
is dismounted
or brushesarereplaced.
(a) Notedirectionof slipringrotation.
(b) Placetemplateagainstfaceof brushassembly.
(c) Slidebrushassemblyforwarduntiltemplatemeetssliprings.
CAUTION: SLIDELOADSON BRUSHESSHOULDBE AVOIDEDTO PREVENTBRUSH
DAMAGE.
(d) Tightenbrushassemblyandremovetemplate.
template.
sectionof partscatalogto orderbrushalignment
NOTE: Referto miscellaneous
SlipRing
Surface
SlipRingRotation
Brush
Assembly
O
O
Template
ModularBrushAlignmentTemplate
Figure508
EFFECTIVITY:
040-999
30-60-00
30-60-00 JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
8. AlignmentOf Brushes (referto Figures508 and 509) (continued)
100%OF Brush
ContactsSlip
Ring Surface
Slip Ring
Assembly
Brush
Assembly
ProperRadialAlignment
CenterBrushesOn Slip Rings
IncorrectRadialAlignment
The Full ThicknessOf EachBrushFace Must
Contact The Slip RingThroughout360° Rotation
Slip Ring Rotation
Spring
Pressure
On Brush
ResultsCausedBy
CockingAssemblyAt
Too GreatOf An Angle
BrushAssembly
CorrectFore & Aft Alignment
ResultsCausedBy
AllowingToo GreatOf
A DistanceBetween
BrushHousingAnd
Slip Rings
IncorrectAlignment
ModularBrushAssemblyAdjustment
Figure509
9. BrushModuleReplacement
Measurethe brushesas shown in Figure503. Replacebrush modulesas follows:
CAUTION: BRUSH AND RING SERVICE LIFE MAY BE REDUCED IF OIL IS PRESENT ON
BRUSH UNIT. REFER TO PRATT & WHITNEY PT6A-61 MAINTENANCE MANUAL
FOR FIXING OIL LEAKS.
NOTE: The entire brush moduleunit shouldbe replacedwhen considerablewear of the housing
is apparent.
(a) Removethe modularbrush assemblyfrom the aircraft by removingthe attachmenthardware
and disconnectingthe enginewire harness.
EFFECTIVITY:
Jan
10/90
30-60-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Practices(continued)
B. Maintenance
(continued)
9. BrushModuleReplacement
(b) Removeassemblyscrewsandseparatemodulesandspacers.
NOTE: Thepartnumberof eachmoduleis etchedintothesurfaceof theplastichousing.
withthesamepartnumbermodule.
Replace
between
(c) Restackmodulesandspacersasshownin Figure512. Ifthereisinterference
adjacentringterminals,reorientcentermoduleas shownin Figure511.
betweenstarwasherandhousing.
NOTE: Ensurethatflatwasheris positioned
aircraftwireharnessandensureadjacentringterminalsarenottouching.
(d) Reconnect
(e) Installassemblyon theaircraftandcheckalignment.
1. BrushModuleAssembly
2. NylonSpacer
3E2011-28-4Only
NOTE:
The AlternateStackingArrangement
Is UsedWhenThere Is Interference
BetweenAdjacentModuleRing
Terminals.
3. Wire Marker
A. -1 & -4 Assembly
B. -2 Assembly
C. -3 Assembly
BrushModuleAssembly(3E2011)
Figure510
4. Spacer
AlternateModuleStackingArrangement
Figure511
1. BrushModule
Assembly
3E2011-1
2. BrushModule
Assembly
3E2011-2
6. Washer
5. Screw
7.Lockwasher
8. Nut
P/N 3E2044
3. BrushModule
Assembly
3E2011-3
ModuleBrushAssembly(3E2044-1)
Figure512
EFFECTIVITY:
030-60-00 Jan
10/90
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
10. Slip Rings
(a) Machiningof the Slip Rings
Sliprings,with roughened
or damagedsurfaces,canbe machined
for prolongedservicelife as
follows:
(1.) Removeslip ringassemblyfrompropellerhub.
(2.) Mountassemblyin lathenotexceeding
0.002inchrun-outover360° rotation,withrespect
to mountingsurfaceof assembly.
(3.) Makelightcutto removesurfacedamage.
(4.) Ensurecontactsurfacesof threeslipringsareparallelandflatto within0.002inchoverall
of eachother. (Deviation
fromflatcannotexceed0.002inchoverfourincharc.)
(5.) If necessary,
undercutinsulationbetweensliprings0.02to 0.03inchbelowcontact
surfaceof sliprings.
(6.) Ensureminimumdistancefor refacingslip ringassemblies
is notlessthan1.160inch
betweencoppersurfacesandlegsof assembly.
NOTE: If solderor brazeconnection
on undersideof slipringis exposedwhile
machining,
replaceslipringassembly.
(b) Replacement
of SlipRings
Replaceslipringassemblies
that areopenor shortedelectrically,
crackedordamaged
structurally,
or whichhavesurfacesdamagedbeyondminorrepair.
11. DeicerBoots
(a) Resistance
Checkof DeicerBoots
Tocheckfor incorrectresistance,
shortor breakcircuitat brush-to-slip
ringcontact,disconnect
harnessat eachtimerandusean ohmmeter
to readresistance
fromeachdeicercircuitlead
(pinsA, B, andC of harnessplugor modularbrushblock)to ground.
(b) Replacement
of DeicerBoots
or are visibledamaged
If testshowsdeicerbootshavean opencircuit,incorrectresistance,
beyondrepair,replacedeicerboot.
EFFECTIVITY:
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Jan109030-60-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. MaintenancePractices (continued)
11. DeicerBoots (continued)
(c) Repairof PropellerDeicerLead Strap (Figure801)
For repairs,use B. F. GoodrichField RepairKit No. 77-802,which containsrubberpatch
materialfor several repairjobs. Cementsand solventsspecifiedin directionsare not included
in kit.
(1.) Cleanrepairarea with MEKor acetoneto removeall grease and dirt. After lastwipe with
cleaner,quicklywipe surfacewithclean,dry, lint-freecloth, removesolventfilm.
(2.) Applyone even coatof EC1300Lor EC1403cement(MinnesotaMiningand Mfg.Co.) to
repairarea. Allow to dry approximately1 hour above40°F. Apply secondevencoat of
cementand allow to dry.
(3.) Cut patch (0.020 inchthick rubberabout 1/4 inch larger on all sidesof repairarea).
Ensureprotectivepaper is on cementedside and apply maskingtape on open side to
preventpatchfrom curling as cementdries. Strip off protectivepaperand apply EC1300L
and EC1403cement in smooth,even coat; allowto air dry. After 1 hour,applysecond
coat and allowto air dry.
(4.) With cementsurfacesdry or slightlytacky,apply light coat of MEKor Toluolover surfaces
and quicklycompletecementingas specified. Allow 1 hourto air dry beforepeelingoff
maskingtape or mylarcoatingon air side. Rub edgesand centerof patch to ensure
properadhesion. (Approximately24 hours.)
NOTE: Do not touchcementedsurfacewith dirty or oily fingers.
Neoprene
Patch
1300L Cement
-
ViewA-A
DeicerLeadStrap
WoodenBlockor Bucking
Bar MayBe UsedWhen
NecessaryFor Support
NeoprenePatch
CementedOver
ExposedFabric
Repairof Lead Strap
Figure801
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"Jan
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Maintenance
Practices(continued)
11. DeicerBoots (continued)
(d) Removalof Deicers
(1.) Disconnect
propellerdeicerterminalsat studson spinnerbulkheadandlip deicer
terminalsat boot.
(2.) UseMEKorToluolto softenadhesionlinebetweenbootandmountingsurface.
(3.) Startingat onecomerof deicer,loosendeicerenoughto graspwithvisegripspliersor
similartool.
(4.) Applysteadypullon deicerto pullit off mountingsurface.ContinueusingMEKor Toluol
to softenadhesionlines. Unlessdeiceris damaged
beyondrepair,cushionjawsof pulling
toolto preventdamageto deicersurface.Removeslowlyandcarefully.
(5.) RemoveresidualcementfrombladeusingTurco3 or equivalent.
(e) Preparation
of SurfacePriorto Installation
of Deicer
Preparepropellerblade surfacefor properdeicerbootsinstallationas follows:
PropellerBlade Protection
(1.) Mark and cut maskingtape samesize as propellerdeicer includingfirst inch of leadstrip
(Figure401).
(2.) Place mark at blade hub end in linewith bladeleadingedge. (Locationof mark is
determinedby sightingalongleadingedge.) Startingat hub, centertape on mark and
stick tape leadingedge. Mark positionof deicer leadstrap where it crosseshub.
NOTE: All deicerson singlepropellermustbe equallydistantfromhuborrational
balance.
(3.) Removetape and paintin markedoff area downto bare metal. Cleanareathoroughly
with MEKor acetone. For final cleaning,wipe solventoff quicklywith clean, dry, lint-free
cloth to avoid leavingfilm.
CAUTION: METALAND RUBBERPARTSMUSTBE CLEANTO ASSUREMAXIMUM
ADHESION.
(4.) Markcenterlineat propellerbladehubandontapeat outboardedgeof markedarea.
EFFECTIVITY:
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040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. Maintenance
Practices(continued)
11. DeicerBoots (continued)
(e) Preparationof SurfacePriorto Installationof Deicer (continued)
CenterLine
r- Pattern
MaskingTape
PropellerDeicerInstallation
Figure401
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Maintenance
Practices(continued)
11. DeicerBoots(continued)
(f) Applicationof Cement
To applycementon bootsandmatingsurface,proceedasfollows:
(1.) Markcenterlineon glossysideof deicerwithsilverpencil.
(2.) Moistencleanclothwith MEKor acetoneandcleanunglazedsurfaceof deicer,changing
clothfrequentlyto avoidcontamination
of cleanarea.
mixEC1300Lor EC1403cementandapplyoneevenbrushcoatto unglazed
(3.) Thoroughly
backsurfaceof deicer.Cementoneinchof deicerleadstrap. Allowto airdryfor
minimum1 hourat 40°For abovewithrelativehumiditylessthan70%. If humidityis75%
to 90%,allow2 hoursdryingtime. Donotapplycementif relativehumidityis higherthan
90%. Applysecondevenbrushcoatof cement.
NOTE: If deiceredgescurl,applymaskingtapeto edgesof glazedsidebeforeapplying
cementto unglazedside. Removetapebeforeinstallingdeicer.
or EC1403cementon cleanedsurfaceof propeller
(4.) Applyevenbrushcoatof EC1300L
of secondcoatof cementof deicer.(Timingis
bladeimmediately
afterapplication
as cementon bothsurfacesmustreachtackstageat sametime.)
important
CHART 1
REQUIREDMATERIALSFOR REPAIROF DEICERS
The materials and tools listed below are commercially
available and are not suppliedby B. F.Goodrichin kit form.
Item
Cement EC-1300Lor EC-1403(3M Mfg. Co.)
SealerA56B (B. F.Goodrich)
CleaningSolventMEK (Methylethylketone)or Acetone
B. F.Goodrich Filler82-075Aand B or 3M Sealer
EC-801and EC-1031
B. F.Goodrich Sealer82-076-1and -2 or Lowe
Brothers'paint C-19861,C21871and C-16176
CleaningCloth - anyclean, lint-freecloth
2 inch RubberHandRoller
1/4 inch Metal HandStitcher
Scissors
Turco #3 (Turco ProductsCo.)
MaskingTape
Amount
1 1/2 pt. for six blades
1 pt. for six blades
1 1/2 pt. for six blades
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
11. DeicerBoots (continued)
(g) Installationof Deicersand RequiredMaterials
CAUTION: TO ENSUREMAXIMUMADHESIONTO MOUNTINGSURFACE,FOLLOW
INSTRUCTIONSPRECISELY.
Proceedas followswhen cementcoats are tackydry on both deicer and mountingsurfaces: (It
is recommendedtwo personsperformthe followingprocedures.)
(1.) Positiondeiceron propellerleadingedge (usingcenterlineswhich start from hub) after
tackifyingcementin areawith clean, lint-freecloth dampened(not saturated)with Toluol
(Figure401). Ensurestrap falls into positionpreviouslymarked. Workingtowardtip, tack
deicer centerlineto leading edgeof propellerblade. Tackifycementas necessary. If
deicer is off line, pull up with quickmotionand removedeicer. Replaceif necessary,
beforeproceeding. Roll firmly alongcenter line with rubberroller (Figure401).
(2.) Roll taperededges(especiallyinboardedge)of deicerwith narrow,steel stitcherroller.
CAUTION: DO NOT USE METALSTITCHERON DEICERBODYTO AVOID
DAMAGINGRESISTANCEWIRES.
(3.) Apply one even brush coat of sealeraroundedgesof installeddeicer.
(4.) Removemaskingtape from bladeimmediatelyafter applyingsealer.
(5.) Allow cementto cure 24 hours beforeturning up propeller.Allow 72 hours curingtime
beforeoperatingdeicers. Handlepropellercarefullyto preventdamagingdeicers.
(h) Preparationand Applicationof Sealer
Propellerdeicers looseneddue to adhesivebond breakdownby lubricantswill not recement
properly. Remove,clean,and reinstalldeicers as follows:
(1.) Clean 0.500inch wide area aroundcircumferenceof propellerdeicerdownto bare metal
using MEKor acetone.
(2.) Cleanouter 0.500 inch and 0.250 inchunder deicerson all sidespast loosenedareaswith
MEK or acetone. For final cleaning,quickly wipe off solventswith clean,dry, lint-freecloth
to avoid leavingfilm.
(3.) Recementlooseneddeicers surfaces.
(4.) Thoroughlymixfiller, sealer,or paint in properproportionsby weightas follows:
(a.) 82-075A/B:one part A/onepart B.
(b.) 82-076-1/2:twelve parts 1/one part 2.
(c.) EC-1031/EC-801:twelve parts 1031/onehundredparts 801.
one part 19861/sevenparts 21871/twoand two-thirds
(d.) C-19861/C21871/C-16176:
16171.
parts
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. MaintenancePractices (continued)
11. DeicerBoots (continued)
(h) Preparation
andApplication
of Sealer(continued)
(5.) Place maskingtape approximately0.125 inch beyondcementedarea aroundpropeller
deicerto allow applicationof filler directlyto metal. Apply one even brush coat of 82-075A
filler (or EC-801sealer)over 0.125 inch of bare metal,cementedarea, and boot for
propellerdeicers.
(6.) Ensurefillet filler completelycovers areabetweenpropellerdeicerstrap and blade (Figure
402). Immediatelyremovemarkingtape from propeller. Allowfiller to dry for 6 hours.
(7.) Apply new markingtape approximately0.125 inch beyondfiller to allow applicationof
sealerdirectlyto mountingsurface. Apply one even brush coatof 82-076-1/2sealer(or C19861/C16176paint) over 0.125 inch of mountingsurfaceand 0.250 inchof deicer(Figure
402).
(8.) Ensuresealercompletelycovers area betweendeicer strap and blade on propeller(Figure
403). Removemaskingtape immediately.Allow sealerto dry for 24 hours beforestarting
engine.
82-076-1/-2Sealer
or C-19861/21871/16176
Paint
1/8
Deicer
CementedArea
Filler82-075A/B or
SealerEC-801
SealerApplication(Prop Boot)
Figure402
SpecialAttentionShouldBe GivenTo This
DistanceWhen LocatingThe Boot For Final
BondingTo Propeller.
Seal
I
SealerApplication(LeadStrap)
Figure403
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. MaintenancePractices (continued)
11. DeicerBoots (continued)
(i) WrinkledDeicers (Figure404)
If deiceredge is wrinkledor loose, recementedge. Use MEKor Toluolto loosenbond 1/4 inch
beyondloose or wrinkledarea. Applyone coatof EC1300Lor EC1403cementto deicer and
bondingsurfacesand allowto air dry for 1 hour. Apply secondcoat of EC1300Lor EC1403
cementto both surfaces. Allow to dry. Retackifywith MEKor acetoneand pressdownwith
fingersto work out wrinklesor secureloose edges. If materialhas stretchedand will not
cementflap, replacedeicer.
WrinkledDeicer
Figure404
Whenperformingresistancecheck,electricallyisolatepropellerdeicer circuits(if prop is
installed)from rest of airplanewiringas follows:
(1.) Removebrush blockand disconnecttimer and enginewire harnessat convenientlocation
or retractbrushes. Slip sheet of paperbetweenbrushesand slip rings.
NOTE: Resistancevaluesbelowapply onlyto deicerscompletelydisconnectfrom
terminalstuds and electricalconnectors.
(2.) Checkelectricalresistanceof each elementwithin deicerby checkingbetweenterminals.
(See 30-20-00,Figures1 & 2 and resistancereadingsin Chart2 below.)
(3.) Checkelectricalresistanceof elementsin parallel,by chechingbetweenslip rings (See
30-20-00,Figures1 & 2 and Chart2 below).
NOTE: Electricalcontinuitychecksmustbe madewithoutrotatingpropellers,with boot
switchon.
CHART 2
PROPELLER DEICER ELECTRICAL SPECIFICATIONS
TIMER
SEQUENCE
ELEMENT
HEATED ZONE
TIME
SEC.
LOAD AMPS
@ 28 VDC
E
Outboard
34
13.7
F
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040-999
Inboard
34
13.7
RESISTANCE CHECK AND VALUES
MAX
MIN.
OHMS
OHMS
1 bladeeach
element
3 bladesin
parallel
5.26
4.58
1.78
1.55
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Maintenance
Practices(continued)
11. DeicerBoots (continued)
(i) WrinkledDeicers(Figure404) (continued)
opencircuitsbytensioningdeicerstrapslightlywhilemeasuring
(4.) Checkfor intermittent
resistance.Presslightlyon deicersurfaceadjacentto strapretainer.Ensureresistance
doesnotvary.
NOTE: Identifycircuits in elementby referringto resistancevalves (See30-20-00,
Figures1 & 2). Identificationis necessaryto cycle systemproperlyand obtain
correct amperagevaluesduringsystemoperation. Minimumand maximumohms
betweencommongroundand other terminalsis 4.58to 5.26 ohms.
(5.) Reconnectdisconnectedcircuitsand removeany paper shims.
(j) Installationof PropellerDeicerStrapsand Wire Harness
(1.) Fastendeicerleadstripto bulkhead.
(2.) Attachdeicerstrapto studson spinnerbulkhead.
CAUTION: NEVERUSE TYPEB STARWASHER(TEETHON OUTERDIAMETER)
ADJACENTTO TONGUEOF DEICERTERMINALS.
(3.) Ensureno slack exists in deicerlead strap betweenterminalsand clip. Conducttest on
each propellerdeicingsystemto ensuredeicer leadstrapsare installedso propellercan
be movedfrom full low pitch throughfeatheringpositionwithoutplacingtensionon straps.
NOTE: Deicersmust haveplastic bondedto air side (shiny side)of deicerstrap (Figure
405).
(4.) If damageoccursto slip ring wire harness,rubberspacers,or hoseclamps,replace
damagedparts.
Prop Deicer
PropellerLead Strap Installation
Figure405
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. MaintenancePractices (continued)
11. DeicerBoots (continued)
(k) Balancing
To assurea balancedpropellerassembly,reinstalloriginal balancingweights or equivalents.
Positionweights in originalpositionon propellerhub. Ensurerestrainerand weightsdo not
interferewith propellerassembly. If balanceweightsare removed,reinstallsafetywire on
screws.
(I) FinalElectricalCheck
(1.) Ensureall terminalsare tight, not over-torqued.
(2.) Ensureall wires are properlyinsulated,especiallyin enginecompartments.
(3.) Ensureall wire ties are tight and positionedto preventchafingor stoppageof moving
parts.
(4.) Ensureall wires are tightenedin connectorsand ensure no bare wires will short on nearby
objects.
(5.) Ensureinstalledwires are not sharplybent,pinched,or pulledtight.
(m) OtherComponents
Do not attemptinternalrepairs of timer,ammeter,or switches. If inoperative,replace
componentswith properparts. For other repairor maintenanceproblemsnot coveredin this
manual,inquireat Aerospaceand DefenseProductsDivisionof the B. F.GoodrichCompany,
Akron,Ohio 44318.
(n) PowerControl Relays (Figure406)
Bothleft and rightpowercontrol relaysset are mountedin the accessorysectionof engine
nacelles.
(o) Removalof the PowerControlRelays
(1.) Removetop cowlsfrom nacelle.
(2.) Relays are mountedin accessorycompartmenton bulkheadby motorcontrolrelay.
Identifywire codes and note attachmentpoints;disconnectthem from desiredrelay. (See
91-00-00for appropriatewiringdiagram.)
(3.) Removeappropriaterelaybe unscrewingtwo screwsfasteningunit to firewall.
(p) Installationof PowerControl Relay
(1.) Repositionrelayand securewith properscrews.
(2.) Reconnectwires to appropriateterminal.
(3.) Completefollowingtest to determineproperinstallationand operationof relay:
(a.) Turn on ice protectionswitch. Pushgroundtest switch.
(b.) Ensurerelayactuates,causingtimerto start cycling and deicersto heat.
EFFECTIVITY:
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30-60-00Jan
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10/90
PIPER AIRCRAFT
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MAINTENANCE MANUAL
B. Maintenance Practices (continued)
11. Deicer Boots (continued)
View A
ViewB
DeicerPowerControlRelays
LEACHRELAYCOMPANY
KC-D4A
PropellerDeicerTimer
B.F.GOODRICH
3E1150-12
(Aft Of Firewall)
(ForwardOf Firewall)
PowerControl Relaysand DeicerTimer Installation
Figure406
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. MaintenancePractices (continued)
11. DeicerBoots (continued)
(q) Removalof DeicerTimer (Figure406)
Removedeicertimers on forwardside of enginenacellefirewall as follows:
(1.) Removecowl.
(2.) Disconnectelectricalplug from top of timer.
(3.) Removefour screwssecuringtimer to firewall; removetimer.
(r) Installationof DeicerTimer
(1.) Positiondeicertimer on firewall. Securedeicertimerwith four screwspreviously
removed.
(2.) Connectelectricalplug to top of timer.
(3.) Check operationof newtimer to ensureproperinstallationand operation.
(4.) Installcowlsand securewith screwtype fasteners.
(s) Timer Test
Beforeremovingtimer,performthe followingtest:
(1.) Disconnectwire harnessat timer and with deicerswitchon, checkvoltagefrom pin B of
harnessplugto ground. If no systemvoltageexists,fault is not with timer. If system
voltage existsat pin B, checkgroundcircuitfrom pin G to groundusing ohmmeter. If no
continuityexists,fault is in ground leadnot timer. If ground connectionis open, timer step
switch will not change position.
(2.) Connectjumper wire from pin B of harnessto B contact of timer socketand from pin G of
harnessto G contactof timer socketto completepowercircuit. Hook-upvoltmeterfrom
groundto timer socketand ensuretimer is cycling and deliveringsystemvoltageto C, D,
E, and F contacts. (Startingpoint is not important,but sequencemust be as stated.) All
four contactsmustdeliver voltagefor approximately34 secondseachwith zero voltageon
three contactsnot energized.
(3.) If timer meetsall requirementsof test, problemexistselsewhere. If timer does not meet
test requirements,replaceit.
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MAINTENANCEMANUAL
CHAPTER31
LIST OF EFFECTIVEPAGES
CHAPTER
SECTION
31-EFFECTIVITY
31-CONTENTS
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DATE
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PAGE
DATE
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PAGESan
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PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER31- INDICATING/RECORDING
SYSTEMS
TABLE OF CONTENTS
SUBJECT
Annunciator
System
General
Annunciator
Panel
Removalof Annunciator
Panel
Installation
of Annuncitator
Panel
Removalof Annunciator
Controller
Installation
of Annunciator
Controller
CHAPTER
PAGE
31-50-00
1
1
2
3
3
3
4
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
Indicating/Recording
Systems
A. AnnunciationSystem
1. General
The systemused to provideannunciationof aircraftsystemsis of a two channeltype: Master
CautionWarningand AdvisoryAlert. As a monitoredsystemreachesa point wherecertainsensor
limitsare reached,a circuitis made or brokenthussignalingthe annunciatorcontrollerto activate
a specific;red annunciatorlight circuitand warninghorn if the systemis wired into the Master
WarningChannel;or amber annunciatorlight if the systemis tied intothe AdvisoryAlert Channel.
Brightnessof the lights is controlledvia the FixedDimmingCircuit. (See Schematic31-50-01in
PA-42-720(AdvancedTrainer)Wiring DiagramManual.)
The annunciatorcontrolleris designedto illuminatean annunciatorlight when a specificsignalis
received. Dependingon how specificcircuitswithin the computerare designed,threetypes of
inputsor signals are used to activatethe controller: GroundApply;28 Vdc Apply; or the openingof
a circuit(groundremoveor positive). See Chart1 for Indexof AnnunciatorControllerInputs.
The annunciatorsystemincorporatestwo annunciatinglight strings,enginefire indicatinglights,a
controller(computer),a horn, and actuatingcomponentsin the affectedsystemsof the aircraft.
Componentsare also incorporatedfor testingthe operationof the annunciatorlightsas well as the
lightsin the lighted switchesused on the instrumentpanel and in the overheadswitch panels.
Equipmentto operatethis part of the systemconsistsof an ANNUNTEST (annunciatorpress-totest) switch in the left side of the annunciatorpanel; and, a numberof diodearray connectors
installedbehindthe overheadswitch panels. Whenthe test switchis held depressed,a groundis
appliedto the annunciatorcontrollerandthe diode arrayconnectorsvia a groundapply relay. At
the sametime, 28 Vdc is also appliedto the controllertest circuit. Withthe groundand power
appliedto the controller,a circuitis madewhich shouldilluminateall the annunciatorlights. With
the groundappliedto the diode connectors,a circuitis completedto all of the lightedswitches
which shouldcause them to be illuminated.
NOTE: The FixedDimmingcircuit providesa continuousvoltage (5 Vdc in BRIGHT;3 Vdc in DIM)
to the lights insidethe lightedswitches. Whenthe "ANNUNTEST' switch is activated,the
appliedgroundcompletesthe circuitsto all the affectedlights,illuminatingthem as
selectedby the Fixed DimmingCircuit.
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B. AnnunciatorPanel
Theannunciator
panelmonitorsvariousfunctions
of theelectricalsystem.Theannunciator
panel
containsindicatorlightbulbsthataregroupedtogetherandextendacrossuppercenterportionof
instrument
panelbelowglareshield
(Figures1 and401). Theannunciator
controlleris securedto
instrument
panelsupportbracketdirectlybehindcenterpanelof instrument
panel. Foridentification
of
annunciator
lights,referto Chart1.
/
Annunciator
Panel
Figure1
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B. AnnunciatorPanel (continued)
1. Removalof AnnunciatorPanel(Figure401)
NOTE: Replacementof a bulbdoes not requireremovalof annunciatorpanel. To replacea
defectivebulb, pushin on appropriatelight cover assemblyuntil it clicks. Removethe
light cover assembly. Removeold bulb and replacewith new bulb. Place lightcover
assemblyin propercut out and push in until it clicks,lockingthe light cover assemblyin
place.
(a) Removescrews securingcover to glareshieldassembly;removecover.
(b) Removescrewssecuringcenter panelof instrumentpaneland pull back on panel to gain
accessto annunciatorcontrolbox. Disconnectannunciatorpanelconnectors.
(c) Removescrewssecuringannunciatorpanelto glareshield. Removeannunciatorpanel.
2. Installationof AnnunciatorPanel(Figure401)
(a) Placeannunciatorpanel into positionon glareshield. Securewith screws.
(b) Attachannunciatorpanel connectorsto annunciatorcontroller. Installcenter panelof
instrumentpanel. Securewith screws.
(c) Positioncover on glareshieldassembly. Securewith screws.
Skin
AnnunciatorPanel
Figure401
3. Removalof AnnunciatorController
(a) Ensurebattery master switchis off.
(b) Removescrewssecuringcenter panelof instrumentpanelassembly. Pull panelout to gain
accessto annunciatorcontroller.
(c) Removeelectricalconnectorsfrom annunciatorcontroller.
(d) Removescrewssecuringannunciatorcontrollerto instrumentpanel supportassembly.
Removecontrollerfrom supportassembly.
EFFECTIVITY:
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B. AnnunciatorPanel (continued)
Controller
of Annunciator
4. Installation
panelsupportassembly.Securewith
controllerin positionon instrument
(a) Holdannunciator
screws.
controller.
to annunciator
(b) Attachelectricalconnectors
(c) Placecenterpanelintoposition.Securewith screws.
RemoveFourScrews
ForAccessTo
A B C D E F
GrimesPartNumberFor
Annunciator
Box80-0372-7
G H J
K L M
CircuitCardInstallations
(TopViewOf Box)
ControllerInformation
Annunciator
Figure2 (Sheet1 of 2)
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B. AnnunciatorPanel (continued)
PA-42-720ANNUNCIATOR
(GRIMESP/N 80-0372-7)
CIRCUITCARD
LOCATION
ANNUNCIATOR
FUNCTION
A
BRT/DIMRelay
Flasher
Master Caution
Horn Driver
B
Annun.Malf
L. Oil Temp.
R. Oil Temp.
BatteryHOT
C
L. Fuel Press
R. Fuel Press
L. Oil Press
R. Oil Press
D
L. BleedAir Hot
R. BleedAir Hot
Cabin Press
BaggageDoor
E
CabinDoor
L. EngineFire
R. EngineFire
ECS Overtemp
F
L. Ice Door
R. Fire Ext. Inop.
L. Fire Ext. Inop.
R. Ice Door
CIRCUITCARD
LOCATION
ANNUNCIATOR
FUNCTION
G
L. Fuel Filter
R. Ign. On
L. Chip Detect
L. Grnd. Bleed
L. Ign. On
R. Chip Detect
R. Fuel Temp.Low
R. Ign. On
H
Elec.Trim
Inv.Inop.
Emer.Press
Wing Flap
J
R. BleedAir Off
R. Start Engage
L. BleedAir Off
L. Start Engage
K
Spare
Ext. Pwr.Attach
Spare
Gear Warn.
L
R. Gen. Off
L. Gen. Off
FAIL-STALLWN (L. Chan.)
FAIL-STALLWN (R. Chan.)
M
L. Fuel Temp.Low
R. Fuel Filter
A/P Servo
Q-SensorOverride
AnnunciatorControllerInformation
Figure2 (Sheet2 of 2)
EFFECTIVITY:
040-999
31-50-00
Jan
31-50-00 an
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Annunciator
Panel(continued)
CHART 1 (Sheet1 of 2)
ANNUNCIATORIDENTIFICATION
Annunciation
Color
TypeAnnunciation
AppliedSignal
L. EngineFire
Red
MasterWarning
GND Apply
R. EngineFire
Red
MasterWarning
GND Apply
L. OilTemp
Red
MasterWarning
GND Apply
R. OilTemp
Red
MasterWarning
GND Apply
L. FuelPress
Red
MasterWarning
PositiveApply
R. FuelPress
Red
MasterWarning
PositiveApply
L. OilPress
Red
MasterWarning
PositiveApply
R.Oil Press
Red
MasterWarning
PositiveApply
L. BleedAir Hot
Red
MasterWarning
GND Apply
R.BleedAir Hot
Red
MasterWarning
GND Apply
CabinPress
Red
MasterWarning
GND Apply
BatteryHot
Red
MasterWarning
+18V Removed
CabinDoor
Red
MasterWarning
GND Apply
TrimFail
Red
MasterWarning
PositiveRemove
BaggageDoor
Red
MasterWarning
GND Apply
StallWarn
Red
Advisory
PositiveRemove
GearWarn
Red
Advisory
PositiveApply
Arm-Autofeather
Green
Advisory
GND Apply
L. Ice Door
Green
Advisory
GND Remove
R. IceDoor
Green
Advisory
GND Remove
L. StartEngage
Amber
Advisory
PositiveApply
R.StartEngage
Amber
Advisory
PositiveApply
L. Gen.Off
Amber
Advisory
PositiveRemove
R.Gen.Off
Amber
Advisory
PositiveRemove
EFFECTIVITY:
040-999
Jan 10/90 31-50-00
0
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Annunciator
Panel (continued)
CHART 1 (Sheet2 of 2)
ANNUNCIATOR
IDENTIFICATION
Annunciation
Color
TypeAnnunciation
L. Ign On
Amber
Advisory
GND Apply
R. Ign On
Amber
Advisory
GND Apply
L. Bleed Air Off
Amber
Advisory
PositiveApply
R. BleedAir Off
Amber
Advisory
PositiveApply
L. Chip Detect
Amber
Advisory
GND Apply
R. Chip Detect
Amber
Advisory
GND Apply
L. Fuel Filter
Amber
Advisory
GND Apply
R. Fuel Filter
Amber
Advisory
GND Apply
L. Fire ExtInop
Amber
Advisory
GND Remove
R. Fire Ext Inop
Amber
Advisory
GND Remove
Auto Pilot Fail
Amber
Advisory
PositiveApply
Advisory
PositiveApply
Ext Pwr Attach
AppliedSignal
Annun Malf
Amber
Advisory
PositiveRemove
Wing Flap
Amber
Advisory
PositiveApply
Fail-Autofeather
Amber
Advisory
GND Apply
Stall Warn
Red
Advisory
PositiveRemove
Inv. Inop
Red
MasterWarning
PositiveRemove
Q-SensorOverride
Amber
Advisory
GND Apply
ECS Overtemp
Amber
MasterWarning
GND Apply
EMER Press
Amber
MasterWarning
PositiveApply
L. GroundBleed
Amber
Advisory
GND Apply
R. GroundBleed
Amber
Advisory
GND Apply
L. Fuel TempLow
Amber
Advisory
GND Apply
R. Fuel TempLow
Amber
Advisory
GND Apply
EFFECTIVITY:
040-999
31-50-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Annunciator
Panel (continued)
CHART2 (Sheet1 of 3)
ANNUNCIATORPANELFUNCTIONALTEST
ANNUNCIATION
PROCEDURE
Annunciator
Press-to-Test
Ensureelectricalpoweris appliedto annunciatorcontrolsystem. Activate
switchandobserveall annunciation.Placeday/nightdimming
press-to-test
switchto night(dim)positionandactivatepress-to-test
switch.Annunciator
lightsmustdim.
ExternalPowerSupply
AttachedAnnunciation
Apply 27.5 Vdc GPU. External power light must come on. Turn GPUoff.
Lightmust go out.
NOTE: When performingthe followingseriesof tests, use an auxiliarypowerunitto prevent
drainingthe battery.
AnnunciatorMalfunction
Pullannunciator
breaker(onessentialcircuitprotectionpanel).Annunciator
malfunction
lightmustcomeon. Pushbreakerin andlightmustgo out.
Starter Engage
Annunciation
Whenstartingengine,engageleft or right starterandobserverespective
starterengagelight.
EngineFire Annunciation
functionis checked.
Circuittest isachievedwhenpress-to-test
NOTE: Annunciation
ispartof fire extinguisher
switch.
Engine Fire Extinguisher
InoperativeAnnunciation
Disconnectwire E36M from left fire extinguisher(E36L for right fire extinguisher). Ensurerespectivefire extinguisherlight come on. Reconnectwire
and ensure light goes out.
NOTE: Annunciation
is partof fireextinguisher
switch.
Chip Detector
Annunciation
RemoveconnectorE116for leftchip detector(orconnectorE214for right
chipdetector.ShortpinsA and B togetherandrespectivechipdetectlight
mustcomeon. Removeshortandinstallconnector;
lightmustgo out.
OilTemperature
Annunciation
test (orconnectorE217for
RemoveconnectorE119for leftoil temperature
rightoil temperature
test). Usinga resistancedecadebox,select130ohms
and placeresistancein serieswith pinsA andB of connector.Respective
oil temperaturelight and masterwarning hornand light must come on.
light,master
126ohms. Oiltemperature
Lowerresistanceto approximately
warninghornandlightmustgo out. Installconnector.
FuelFilterAnnunciation
wiresQ11S-20
andQ11T-20for leftfuel filtercheck(orQ22S-20
Disconnect
and Q22T-20for rightfuel filter check)and jumptwo wirestogether. The
respectivelightmustcomeon. Removejumperand ensurelightgoesout.
Reconnect
wiresto fuelfilter.
EFFECTIVITY:
040-999
31-50-00
Jan10/90
0
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. Annunciator
Panel(continued)
CHART2 (Sheet2 of 3)
ANNUNCIATORPANELFUNCTIONALTEST
ANNUNCIATION
Bleed Air Hot Annunciation
PROCEDURE
Ground the following wires to their respective ground jumper wires or
airframeground. (Refer to 21-10-00,PA-42-720(AdvancedTrainer) Wiring
DiagramManual.for Bleed Air ControlWiringDiagram).
Wire to temperaturesensorswithinbleed air tubes are as follows:
Left Wing Root Forward: E24R-20
RightWing Root Forward: E24H20
Wiresto temperaturesensorsin bleedare shieldsare as follows:
Left Wing Root Forward: E24T-20
Right Wing Root Forward: E24F20
Wiresfrombleedair ducttemperature
sensorsbehindeachfirewallare as
follows:
LeftNacelle:E24S-20
RightNacelle:E24B-20
When each wire is grounded, the respective (left or right) Bleed Air Hot
warning light must come on, along with the master caution horn. After
disconnecting them from ground, the light must go out (also upon
reconnectionto the sensor/harness).
BatteryHot Annunciation
Disconnect wire P11C-20 in battery compartment. Battery hot light and
masterwarning horn light mustcomeon. Reconnectwire and light mustgo
out.
BaggageDoor
Annunciation
Openbaggagedoor. Baggage
doorajarlightandmasterwarninghornand
light mustcomeon. Openbaggagedoor (to lock nosecone)and close
noseconeandbaggagedoor. Baggage
doorlightmustgo out.
Cabin DoorAnnunciation
Opencabinandcargodoor. Cabindoorlight,masterwarninghornandlight
mustcomeon. Closebothdoors;all warningsmustgo out.
Fuel Heat Annunciation
Locateand activateFUELTEMPSENSEcircuitbreaker.On the aft, right
side of eachengine,locatefuel temperatureprobesand disconnecttheir
respectiveplugs(ConnE114,left side: ConnE212,right side). Placea
resistancevalue of 90.5 to 90.8 ohms betweenpins A and B of each
connector.
In nose baggagearea behindclose out panels,locatefuel temperature
monitorbox. On the box,adjustappropriatechannel(channel1, left side;
channel2, rightside)untilFUELTEMPLO annunciator
for thesideaffected
justcomeson.
IgnitionOnAnnunciation
Whenstartingengine,placeleft(orright)ignitionswitchto ONposition.Left
(or right)IgnitionOnlightmustcomeon. Moveignitionswitchin AUTOand
lightmustremainon. Startengineand bringtorqueabove400 ft-lbs. The
annunciator
lightmustgoout.
EFFECTIVITY:
040-999
31-50-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. Annunciator
Panel (continued)
CHART2 (Sheet3 of 3)
ANNUNCIATORPANELFUNCTIONALTEST
ANNUNCIATION
PROCEDURE
InverterInoperative
Activateinverterno. 1 and 2 circuitbreakers(on Left Mainand Essential
bus). Activateavionicsmasterswitch,selectinverterno. 1 switchposition,
andensurelightgoesout. Repeatprocessfor inverterno.2 switchposition.
Pull no. 1 and 2 circuitbreakersalternately,while in appropriateinverter
annunciation.
switchposition,andobserveinverterinoperative
ElectricTrim
CollinsAPS-65. Onthe pilot'scontrolwheel,pushthe left sideof the trim
switchdownandthe righthalf up. Trimmustfail in one second,coinciding
with activationof trim annunciatorand masterwarning horn and light.
Repeattest usingswitcheson copilot'swheel. Pull electrictrim circuit
lightand
breakeron left handbreakerpanelandtheelectrictrimannunciator
masterwarninghornandannunciator
mustactivate.
Wing Flap Annunciation
Locate flap systemtest switch on lower instrumentpanel. Move flap
selector handlefully DOWNand when flaps reachapproximately10° ,
activatetest switch. Flapextensionmuststopandflapcautionannunciator
light(amber)mustcomeon. Releaseswitch;ensurelightgoesoutandflaps
continuedown.
andArm
Fail Autofeather
Autofeather
Annunciation
Referto Autofeather
GroundOperational
Checkin 61-20-00.
StallWarningAnnunciation
Referto Functional
Testof systemsin 27-30-00.
CabinPress.Annunciation
Referto Pressurization
Checkwith TestUnit,21-30-00.
GearWarnAnnunciation
Referto PositionandWaming,32-60-00.
Fuel Pressure
Annunciation Referto Testof AutomaticFuelPumpSystem,28-40-00.
BleedAir OffAnnunciation
CheckwithTestUnit,21-30-00.
Referto Pressurization
EmergencyPressure
Annunciation
With right hand engineoperatingat 70%Ngor less,positionECSselector
switchto emergency
position. Theemergencypressurelighton the cabin
comfortcontrolpanelmustcomeon.
NOTE: Donotoperaterighthandengineon thegroundat powersettingsover70%Ng,with
position.Thiscouldproducebleedair
the ECSselectorswitchin theemergency
conditions.
overtemperature
q-SensorOverride
Annunciation
for q-sensorin 34-10-00.
Referto test procedure
ECSOvertemperature
Annunciation
specifiedin 21-40-00.
Referto procedure
EFFECTIVITY:
Jan 10190O
31-50-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. AnnunciatorPanel (continued)
CHART 3
GROUND OPERATIONAL CHECK OF ANNUNCIATOR PANEL
ANNUNCIATION
PROCEDURE
These checkare madewith both enginesat idle and duringengineshutdown.
GroundBleed
Annunciations
Whenstartingengines,ensureeachBLEEDAIR OFF annunciatorlightcomes
on. When engines are running, lights must go out, but come back on
wheneverthe bleedair switchesor the ECS switch are in the OFF position.
After enginestart, set brakesand positionleftand right bleed air switchesto
the LO position,and ECS select switch to GND. With engine power levers
at ground idle, ensure left and right GROUNDBLEED (amber) annunciator
lights are on. Advancepower levers slowly,and at 70 to 75% Ng, ensure
lightsgo out. Advanceenginepowerlevers to 80% Ng, slowly retardpower
levers,and ensurelightscomeon again at 65 to 70% Ng.
GeneratorOff
Annunciation
With both enginesat idle, place left (or right)startergeneratorswitchin generator position. Ensure respectiveGENERATOROFF light (amber) goes
out.
Ice DoorAnnunciation
Activateleft (or right)ice door switchand ensurerespectiveice door light
(green)comeon. Activateswitchto closedoorandensurelightgoesout.
Oil PressureAnnunciation
Duringshutdownof left (or right)engine,respectivepressurelight,master
warninghorn,andlightmustcomeon as oil pressurepasses60 psi on dual
oil pressure/temperature
gauge.
EFFECTIVITY:
040-999
31-50-00
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 32
LIST OF EFFECTIVE PAGES
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LISTOFEFFECTIVE
PAGES
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER 32
LIST OF EFFECTIVE PAGES (continued)
CHAPTER
SECTION
PAGE
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LIST OF EFFECTIVE PAGES
DATE
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER32 - LANDINGGEAR
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
32-10-00
Main Gear and Doors
Fault Isolation- MainGear and Doors
Removalof MainLanding Gear
Installationof MainLandingGear
Adjustmentof MainLandingGear
Alignmentof MainLandingGear
Inspectionof MainLandingGear
Cleaningof MainLanding Gear
Disassemblyof Main Gear Oleo
Assemblyof MainGear Oleo
Inspectionof MainGear Oleo
Cleaningof MainGear Oleo
Repairof MainGear Oleo
Removalof MainGear DoorAssembly
Installationof MainGear DoorAssembly
Adjustmentof MainGear Doors
Inspectionof MainGear DoorAssembly
Cleaningof MainGear DoorAssembly
Repairof MainGear DoorAssembly
1
1
2
6
6
11
13
14
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17
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19
32-20-00
NoseGear and Doors
Fault Isolation- Nose Gear and Doors
Removalof NoseGear
Installationof NoseGear
Adjustmentof NoseGear
Alignmentof NoseGear
Adjustmentof LandingGear Propeller
ReverseSwitch
Inspectionof NoseGear
Cleaningof NoseGear
Repairof NoseGear
Disassemblyof NoseGear Oleo
Assemblyof NoseGear Oleo
Inspectionof NoseGear Oleo
Cleaningof NoseGear Oleo
Repairof NoseGear Oleo
Removalof WiperStrip on Gear Strut
Installationof WiperStrip on Gear Strut
Removalof NoseGear DoorAssembly
Installationof Nose Gear DoorAssembly
Adjustmentof Nose Gear DoorAssembly
Inspectionof NoseGear DoorAssembly
Cleaningof NoseGear DoorAssembly
Repairof NoseGear DoorAssembly
1
1
3
7
8
11
12
13
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18
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18
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EFFECTIVITY:
040-999
CONTENTSJan
Jan 10/90
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER 32 - LANDING GEAR
TABLE OF CONTENTS (continued)
SUBJECT
CHAPTER
PAGE
32-30-00
Extensionand Retraction
Descriptionand Operation
Fault Isolation- Extensionand Retraction
ServicingAfter Activationof Emergency
Gear ExtensionSystem(EES)
FunctionalProof Pressureand Leak
Test For EES
Testingof EmergencyBlowdownSystem
Testingof ExplosiveValve
Removalof Main Gear ActuatingCylinders
Disassemblyof MainGear Actuating
Cylinders
Assemblyof Main Gear Actuating
Cylinders
Installationof MainGear Actuating
Cylinders
Inspectionof MainGear Actuating
Cylinders
Cleaning of Main Gear Actuating
Cylinders
Repairof Main Gear Actuating
Cylinders
Removalof NoseGear ActuatingCylinder
Disassemblyof NoseGear Actuating
Cylinder
Assemblyof Nose Gear Actuating
Cylinder
Installationof Nose Gear Actuating
Cylinder
Inspectionof Nose Gear Actuating
Cylinder
Cleaningof NoseGear ActuatingCylinder
Repair of NoseGear ActuatingCylinder
Removalof Gear DoorActuatingCylinders
Disassemblyof Gear DoorActuating
Cylinders
Assemblyof Gear DoorActuatingCylinders
Installationof Gear DoorActuating
Cylinders
Inspectionof Gear DoorActuating
Cylinders
Cleaningof Gear DoorActuatingCylinders
Repair of Gear DoorActuatingCylinders
1
1
4
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6
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9
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EFFECTIVITY:
040-999
Jan 10/9
0
CONTENTS
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER32 - LANDINGGEAR
TABLEOF CONTENTS(continued)
SUBJECT
CHAPTER
PAGE
32-40-00
Wheelsand Brakes
Wheels
Fault Isolation- WheelAssemblies
Removaland Disassemblyof B. F.
Goodrich3-1392MainWheel
Assemblyand Installationof B. F.
Goodrich3-1392 MainWheel
Inspectionof MainWheelAssembly
Cleaningof MainWheelAssemblies
Repairof MainWheel Assemblies
Replacementof Wheel BearingCup
Removaland Disassemblyof Nose
Wheel (B.F.Goodrich)
Assemblyand Installationof Nose
Wheel (B. F.Goodrich)
Inspectionof NoseWheelAssembly
(B. F. Goodrich)
Cleaningof NoseWheelAssembly
(B. F.Goodrich)
Repair and Replacementof Nose
WheelAssembly(B. F.Goodrich)
Removaland Disassemblyof Nose
Wheel (Cleveland)
Assemblyand Installationof Nose
Wheel (Cleveland)
Inspectionof Nose WheelAssembly
(Cleveland)
BrakeAssemblies
Descriptionand Operation- Brakes
Fault Isolation- Brakes
Removaland Disassemblyof Brake
and Disc-CarrierAssembly
Assemblyand Installationof Brake
and Disc-CarrierAssembly
Inspectionof BrakeAssembly
Cleaningof BrakeAssembly
BrakeWear Limits
Removalof BrakeMasterCylinder
Disassemblyof BrakeMaster Cylinder
Assemblyof BrakeMaster Cylinder
Installationof Brake MasterCylinder
Inspectionof BrakeMaster Cylinder
Cleaningof BrakeMaster Cylinder
Repairof BrakeMasterCylinder
Removalof ParkingBrakeValve
1
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EFFECTIVITY:
040-999
CONTENTSJan
10/90
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER32 - LANDINGGEAR
TABLEOF CONTENTS (continued)
SUBJECT
CHAPTER
PAGE
32-40-00
Wheelsand Brakes (continued)
Brakes (continued)
Removalof ParkingBrakeValve
Disassemblyof ParkingBrakeValve
Assemblyof ParkingBrakeValve
Installationof Parking BrakeValve
Inspectionof ParkingBrakeValve
Cleaningof ParkingBrakeValve
Repairof ParkingBrakeValve
BleedingProcedure
Tires
21
21
22
22
22
22
22
22
24
32-50-00
1
1
2
Steering
Fault Isolation- Steering
Removalof NoseGear SteeringAssembly
Installationof NoseGear Steering
Assembly
4
32-60-00
Positionand Warning
Descriptionand Operation- Positionand
Warning
Fault Isolation- Positionand Warning
Adjustmentof MainGear Up Light Switch
Adjustmentof MainGear Down LightSwitch
Adjustmentof NoseGear Up Light Switch
Adjustmentof NoseGear DownLight Switch
Adjustmentof Main InboardGear
DoorAjar Switches
Removalof Gear WarningSwitches
Installationof Gear WarningSwitches
Adjustmentof Gear WarningSwitches
1
1
1
3
3
4
4
5
5
6
7
EFFECTIVITY:
040-999
Jan 10/90
CONTENTS
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
LandingGear
The PA-42-720uses a tricyclelandinggear design, incorporatingair oleo shockstruts and is fully
retractablewith coveredgear doors.
A. MainGear and Doors
1. Fault Isolation- MainGear and Doors
NOTE: Place airplaneon jacks beforeattemptingfault isolationof landinggear system (refer to
7-10-00).
CHART 1
FAULT ISOLATION (MAIN GEAR AND DOORS)
Fault
Cause
Remedy
No green light on panel
when gear are down.
Gear not lockedin down
position.
Adjustthegear
Main gearfails to lock
up.
Uplockcable out of
adjustment.
Adjustcable.
Actuatorout of adjustment.
Adjustactuator.
Tire out of balance.
Checkbalanceandreplacetireif
necessary.(referto 32-40-00)
Worn or loosewheel
bearings.
Replaceand/oradjustwheel
bearings.(referto 32-40-00)
Worntorque link bolts
and/orbushings.
Replaceboltsand/ or bushings.
Insufficientair and / or fluid
Servicestrutwithair and/ orfluid.
Defectiveinternalparts
in strut.
Replacedefectiveparts.
Incorrectoperatingpressure.
Inflatetireto correctpressure.
(referto 32-40-00)
Wheeloutof alignment
(toe-inor toe-out).
Checkwheelalignment.
Doorsareriggedtootight.
Adjustriggingof doors.
Microswitchon power
packoutof adjustment.
Adjust microswitch. (referto
32-30-00)
Main landinggear
shimmiesduringfast taxi,
takeoffand landing.
Strut bottomson normal
landingor whentaxiing
over roughground.
Excessiveor uneven
wear on maintires.
Doorscomeopen in
flight.
Doorsfail to close.
EFFECTIVITY:
040-999
in strut.
Referto 32-30-00 Chart 1 and
32-60-00 Chart 1.
32-10-00 JanPAGE
1
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main Gear and Doors (continued)
2. Removalof Main LandingGear (refer to 32-10-00 Figure 401)
(a) Placeairplaneon jacks. (referto Jacking,7-10-00.)
(b) Removetwo access platesforwardand two accessplates aft of the outboardwheeldoor.
(c) With the hand pump, retractmain gear slightlyto relievegear from its down lockedpositionand
to lower inboardgear door out of the way.
(d) Disconnectbrake line.
(e) To removeside brace link assembly,usethe followingprocedure:
(1.) Disconnectactuatingcylinderand down lock cablefrom upperside brace link arm by
removingthe clevis bolt. Disconnectotherend of the down lock rod or cable at the down
lock hook.
(2.) Removedown lock hookand springby removingpivot bolt.
(3.) Removedown lock switchby removingthe four screwsattachingthe bracketbetweenthe
forwardand aft side brace links. Removeclampssecuringthe electricalwiringto the side
brace link.
(4.) Disconnectlower side brace link from gearoleo housing;let link assemblyswing down.
(5.) Removebolt connectingthe upperand lowerside brace links.
(6.) Disconnectaft link from its attachmentplate.
(7.) Toremoveforward link, removenut with washersholdingthe link on its pivot shaft. Slide
link from the pivot shaft.
(8.) The pivot shaft is removedby reachingthroughpivot shaftbracketaccesshole and
removingthe bolt securingthe shaftto the shaftfitting. Slide the tube throughthe
attachmentbracket. The shaft fitting it attachedwith cap bolts,washers,and anchor nuts.
NOTE: Before removingthe pivot shaft attachmentfitting fromthe spar, notewhere and
how many spacers/shimswere usedduring installation.Use samenumberof
shims at reinstallationand note bolt sizes at the locationsremoved.
(f) Disconnectoutboardgear door retractionrods at the gear housing. With the lowerside brace
link disconnectedfrom the housing,the gear is removedby removingattachmentbolt
assembliesat the attachmentplates on each side of the gear housing. Note the numberand
locationof spacerwashersbetweenthe gear housingand attachmentplates. Main landing
gear bolt retainersmust be removed.
(g) The up lock hook and springis removedby disconnectingup lock cable and blowdownactuator
rod from hook and the hookpivot bolt.
(h) The up lock cable is removedby disconnectingit at the lock crank.
(i) The landinggear and upperdrag link attachmentplatesare removedby reachingthroughthe
access holes in the nuts securingthe plates. While holdingthe nutswith a wrench, remove
attachmentbolts.
EFFECTIVITY:
040-999
32-10-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
-29
NOTE: Referto nextpage
for callouts.
Aft TrunnionBolt
RetainerPlate
ForwardTrunnionBolt
RetainerPlate
MainGearInstallation
Figure 401 (Sheet1 of 3)
EFFECTIVITY:
040-999
32-10-00 anPAGE
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main Gear and Doors (continued)
Inboard
Door
70
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
31.
32.
33.
34.
35.
36.
37.
Bracket,LockCylinder
LockCylinder
BearingHinge
Bracket,InboardDoor
Hinge,InboardDoor
Bearing,Hinge
Door, Inboard
Bracket,UplockHook
Spring, Uplock
Bolt Assemblyand Bushing
Hook, Uplock
BoltAssemblyand Bushing
Nut, Lock
UplockCable
Actuator
Switch,Uplock
Wire Assembly
Bracket,Switch
Bracket,Cylinder Mounting
Nut, Lock
CrankAssembly
Rod End
DownlockCable
Nut, Lock
Rod End
Arm, GearRetraction
PlateAttachment
Pivot Shaft
Fitting,Shaft
Fitting,Grease
Side Brace,Upper Forward
Switch,Downlock
Bracket,Switch
Hook,Downlock
Side Brace,Lower
Side Brace,UpperAft
Plate, Mounting
38.
39.
40.
41.
42.
43.
44.
45.
46.
47.
48.
49.
50.
51.
52.
53.
54.
55.
56.
57.
58.
59.
60.
61.
62.
63.
64.
65.
66.
67.
68.
69.
70.
71.
72.
73.
74.
BoltAssembly
ValveAssembly
Housing,Gear
Switch,Squat
Link,TorqueUpper
Link,TorqueLower
Line, Brake
StrutAssembly
ValveAssembly,Bleeder
BrakeAssembly
BoltAssembly
Wheeland Tire
Hinge,OutboardDoor
Bearing,Hinge
Door,Outboard
Bracket,Door
Rod,Retraction
Tube, Piston
Nut, Lock
Washer
CylinderAssembly
Valve
EmergencyUplockRelease
Dust Boot
Pin, Downlock
ClevisBolt
Bushing
Washer
Bolt,HookPivot
Bolt,AN178-33
Spring, Downlock
ShuttleValve
DoorAjar Switch
UplockActuator
TrunnionBolt Retainer
Fork AntirotationStop (Clip)
Fork
MainGearInstallation
Figure 401 (Sheet2 of3)
PAGE
4
Jan 10/90
32-10-00
EFFECTIVITY:
040-999
A. MainGear and Doors (continued)
A
r
Sketch A
Bushing
Bushing
(42129-9) (42129-10) Washer
2 Req.)
MainGear Installation
Figure 401 (Sheet 3 of 3)
EFFECTIVITY:
040-999
5
32-10-00
32-10-00 JanPAGE
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
of MainLandingGear (referto 32-10-00Figure401)
3. Installation
CAUTION: WHEN ASSEMBLINGANY UNITS,LUBRICATEBEARINGS,BUSHINGS,AND
FRICTIONSURFACEWITHPROPERLUBRICANT.
platesof landinggearhousingandupperdraglinksandboltin place.
(a) Positionattachment
(b) Theup lockhookis installedasfollows:
(1.) PlaceU endof theup lockspringoverthebackof thehookwith loopstowardtheback.
throughhook.
(2.) Spreadthe springandfit loopsoverbushingextending
(3.) Slidehookinboardthroughthebracketuntilthebracketholealignswiththe boltholein
hook.
(4.) Installpivotboltandtightenso hookrotatesfreelywithoutsideplay.
(c) Attachup lockcableandblowdownup lockrodwithslidingendsattachedto the hookandthe
otherendof theirfittings.
pointson the housingalign
positiongearso attachment
(d) Toinstallmaingearhousingassembly,
to allowa
plates. If needed,installspacerwashersbetweenattachments
with attachment
minimumamountof endplay.Tightennuton eachpivotboltto a snugfit, allowinggearto
swingfreeandsafetyandinstallmainlandinggearboltretainers(forwardandaft).
(e) Theupperand lowersidebracelinkassemblyis installedasfollows:
fittingasfollows:
(1.) Reinstallpivotshaft(forwarduppersidebracelink)sparattachment
mountingholein the
(a.) Slideawasherovereachbolt. Insertboltsthroughappropriate
fitting.
(b.) Withboltsin theirfittings,installthe requiredshimsto correctlyspacefittingaway
of thepivotshaft.
fromthe sparfor properpositioning
(c.) Withshimson theboltsof thefitting,carefullyinsertfittingthroughaccessholeand
boltthefittingto thespar.
(d.) Afterthefourboltsaretightened,removeoneboltat a timeandreinstallthemsoonly
onethreadis engagedin thesparrivnut.Pullon theboltandcheckdistancebetween
bearingsurfaceof boltheadandthepivotshaftfitting(orsurfaceof washer).The
allowabletoleranceof thegapis 0.370inchminimumto 0.385inchmaximum.One
additional0.03125(1/32)inchwashercanbe usedunderthe boltheadto preventthe
shankfrombottomingin therivnut. Ifthegapis notbig enough,usethe
unthreaded
nextsizeAN-4-##Abolt (referto 32-10-00Figure401). Reinstalleachbolt and
torqueto 70 inch-pounds.
platemountedto thewheelwellandintothe
(2.) Slidepivotshaftthroughattachment
fitting.
fittingon thespar. Securepivotshaftat attachment
attachment
on the link,installthe linkon thepivotshaft
(3.) Checkthattheforwardupperarmis installed
andsecureit withwashersandnut.
platepivotbolt.
(4.) Theaft upperdraglinkis installedbyslidingthelinkon aft attachment
Tightennutto allowlinkto swingfreewithno sideplay;safetythe nut.
(5.) Positionlowerlinkbetweenupperdraglinkends,installtheboltassemblyandtighten,
allowingthe linkto turnfreewith nosideplay.
(6.) Attachlowerdraglinkto landinggearhousing;secureandsafety.Movegearin andoutof
thedownlockpositionseveraltimesto ensureno bindingexists.
32-10-00
10/90
PAGE6
Jan
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
3. Installation
of MainLandingGear (referto 32-10-00Figure401)(continued)
(f) Positiondown lock switchbracketbetweenforwardand aft upperdrag links and bolt in place.
(g) The down lock hookis installedon the drag link assemblyas follows:
(1.) PlaceU endof downlockspringoverthebackof thehookwiththeloopstowardtheback.
(2.) Spreadthespringandfit loopsoverbushingextending
throughhook.
(3.) Insertendsof springintoholeslocatedin downlockswitchbracketon eachsideof drag
linkassembly.Pushhookdownbetweentwoupperdraglinksuntilbolt holesin thelinks
alignwith bushingholeof thehook.
(4.) Insertpivotboltandon eachsideofthe bushing,installspacerwashersto maintaina
minimumamountof sideplay. Secureboltandsafetyit.
(h) The down lock cable is installedby boltingthe slidingend of cableto the down lock hookand
the other end of the upperdrag link arm while attachingthe landinggear actuatingcylinder.
Check lubricationof slidingend of down lock cable.
(i) Lubricatelandinggear assembly. (referto 12-20-00 Chart 2 and Figure 301.)
(j) Check maingear adjustment,operation,and alignment.
4. Adjustmentof Main LandingGear
(a) Withthe airplaneon jacks and gear extended,disconnectinboardand outboardgear door
operatingrods, keepingdoors in the open position.
(b) Disconnectdown lock operatingrod or cable from down lock hook.
(c) The through-centeradjustmentof the side brace links is as follows:
(1.) Maintaingearin downlockedpositionwithstopsurfacesof thesidebracelinkstouching.
(2.) Checkthatthelinkageis 0.219to 0.281of an inchthroughcenter.
(3.) If onesideof thestopsurfacesdoesnottouch,file it to obtaindesiredthroughtravel.
CAUTION: DO NOT FILE PIN OR LET LINKAGEEXCEED0.281 INCHTHROUGH
CENTER.
NOTE: A fabricated
toolcan be constructed
to checkthrough-center
travelof theside
bracelinkassemblywhilethelinksareinstalled.(referto 32-10-00Figure501.))
(d) Usethefabricatedtool in thefollowingprocedure:
(1.) Thegearmustbe downandlockedwithno hydraulicpressureon system.
NOTE: Theairplanecaneitherbeon or off jacks.
(2.) Removecotterpinswhichsafetythenutssecuringbothuppersidebracelinksto
attachment
plates.
NOTE: On rightgearonly,removepinatthe nutthatsecuringthe lowerlinkto thegear
housing.Do notremovethenuts.
(3.) Placetooltubethroughelongatedholein toolplate. Placetubeoverandbetweenupper
linkattachment
nuts.
EFFECTIVITY:
040-999
32-10-00Jan
Jan 10/90
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main Gear and Doors (continued)
MATERIAL: Steel or hard aluminum
1.0 x .083 x 13.251 Tube
1.0 x 1.0 Rod
.125 x 18.062 x 3.125 Plate
holesfor installationof bushing,
sightslot and elongatedhole.
1.0x .083x 1.25Tube
1.0 x .083 x 1.25 Tube18.085
.125
Main Gear Side Brace Link Travel Tool
Figure 501
EFFECTIVITY:
040-999
Jan10/9032-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
4. Adjustment
of MainLandingGear(continued)
(continued):
(d) Usethefabricatedtool in thefollowingprocedure
theupperandlowerlinks. The
(4.) Swingplateup againsttheheadof theboltconnecting
thelowerlinkto gear
platesleeveslidesoverthenuton theheadof theboltconnecting
housing.
(5.) Lookthroughsightholein theplateandcheckthatcenterof bolt is 0.219to 0.281inch
belowcenterlineon place.
(6.) Removetool andreinstallcotterpins.
if it engagesfreely.Openandclosejoint
(e) Operatedownlockhookbyhandto determine
severaltimesto assurethe hookisworkingproperly.If thehookdoesnotclearthepin,
continueasfollows:
(1.) Ensureside brace stopsare both touching.
CAUTION: DO NOT FILE PIN OR LET THE LINKAGESEXCEED0.281 INCHES
THROUGHCENTER.
(2.) If onelink'sstopistoo high,file it downuntilbothsidesmate.
(f) Whenthe hookisoperatingproperly,proceedasfollows:
(1.) Engagehookoverpin.
(2.) Forcesidebracelinkageupwarduntilthehookstrikesthepinandstopsmovement.
(3.) Checkgapbetweensidebracestopsurfacesandensureit doesn'texceed0.020inches.
If clearancebetweenstopsexceeds0.020inch,thepinshowslittleor nowear,andthe
linkthroughtraveliswithinlimits,replacethehook.
cutpin,file off anyburrsleftbythecut, anddrivethepinout
(g) If thepin requiresreplacement,
fromeitherside. Installa newpin andflange.
CAUTION: DO NOTTRY TO DRILLTHE PIN OUT,WHICHCOULD DAMAGETHE LINK.
armlocatedat thetopof theforwardsidebrace,
(h) Withdownlockhookengaged,pullretraction
towardsthedownlockhookto thelimitof itstravel. Pulldownlockoperatingrodor cableout
to itsfull lengthandadjusttherodor cableenduntilthehookboltcanbe freelyinserted
throughhooklugs.
CAUTION: DO NOT INSERTANY TOOLTHROUGHHOLEIN ROD END BALLTO
FACILITATETURNINGROD END. DAMAGEWOULDRESULTTO THE
BRONZEBUSHING.
(i) Removebolt,extendrodendonefullturnor 1/2turnif cableis installed,tightenlocknutand
installattachingbolt.
EFFECTIVITY:
040-999
32-10-00 Jan 10/90
AGE
9
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. MainGear and Doors(continued)
4. Adjustmentof Main LandingGear (continued)
(j) Partiallyretractand extendgear severaltimes to seethat down lock is operatingproperly.
NOTE: Referto adjustmentof landinggear light switches(32-60-00).
(k) Pull retractionarm outboardin its slot. Crank assemblyinboardin its slot.
(I) With actuatorretractedunder pressure,adjust actuatorrod end until fork bolt slips in easily.
Turn actuatorrod end in one turn and installfork bolt.
NOTE: When installingfork bolt in the actuatorrod end, be sure that the forked end is properly
alignedwith the down lock operatingrod.
(m) Partiallyretractand extendthe gear. As the side bracesapproachthe lockedposition,exert a
sideforce inboardon the wheelso the hydraulicactuatorforces the linkageinto the locked
position. If gear fails to lock, adjust actuatorrod end inward in half turn incrementsuntil gear
locksdown againstthe side load.
(n) Adjust up lock hookusing the followingprocedure:
(1.) Disconnectuplockhookoperatingrod or cablefrom hook.
(2.) Retractgear,being carefulto keepthe rod clearof moving parts.
(3.) As up lock roller approachesthe hook,operate hookby hand until roller is engaged.
CAUTION BE SURE ALL ROD ENDSHAVESUFFICIENTGRIPPINGTHREADSO A WIRE
CANNOTGO THROUGHTHECHECKHOLE IN THE ROD.
(4.) To ensure uplockcrank remainsin its properposition,maintainhydraulicpressureon the
actuatorand pull both up lock rods out to full length.
(5.) Adjust rod ends until the bolt can be freely inserted;turn them out one to three full turns.
Installbolt and spacerand tighten locknutson rod ends.
(6.) Increasehydraulicpressureuntil cockpithandlemovesto neutral. Gear musthand on up
lock hook. Adjust gear up switchuntil red light in cockpitgoes out.
NOTE: It is necessaryto actuateoppositemaingear switch and nosegear switchalso to
extinguishred light. Referto 32-60-00for landing gear light switches.
(7.) Adjust outboarddoor rods to maximumlength. Boltthem to door attachmentfittings.
CAUTION: DAMAGEMAYRESULTTO THE DOORSIF THE RODSARE LEFTTOO
SHORT.
(8.) Shorten rods by several turns of the rod ends. Retractgear again.
(9.) Repeatstepsg and h till door closedproperly.
(10.) Adjust inboarddoors using sameprocedureas outboarddoors.
(11.) Adjust safety switcheson left and rightgear torque linksso they actuatein the last 0.25 +
0.12 inch travelof the oleo.
(12.) Operategearthrough severalcyclesto assureall parts are operatingproperly.
PAGE
10 32=1n00
Jan 10/90
EFFECTIVITY:
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main Gear and Doors(continued)
5. Alignmentof Main LandingGear (referto 32-10-00 Figure503)
The followingsteps must be completedpriorto checkingand adjustingmainwheelalignment:
(a) Ensurethe airplaneis parkedon a level surfaceand ensure that full weightof airplaneis on
landinggear.
(b) Roll airplanea minimumof two mainwheelrevolutionsusing a tow bar. Moveairplanein a
straightline, stabilizinglandinggear position.
The remainingstepscover alignmentprocedure:
(c) Placea straightedgeno less than 20 feet long acrossthe front of both main landinggear
wheels. Butt the straightedgeagainstthe tires at the hub level of landinggear. Ensurethe
straightedgeis equallydistantfrom the forwardside of the axle hubs. Devisea supportto hold
straightedgein position.
(d) Fabricatea spacerblock (usingdimensionsgiven in 32-10-00 Figure504) and placespacer
blockagainstthe wheel rim at the hub linewith the wide end of the spacertowardsthe front of
the wheel.
NOTE: The fabricatedspacerblockis laid out to give the propertoe-in of 0.5 degrees.
Carpenters
Square
Fabricated
SpacerBlock
Main Gear Alignment
Figure 503
EFFECTIVITY:
040-999
32-10-00Jan
Jan10/90
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGear and Doors(continued)
1.10
I
I
11.56
Material:
Hard Wood
1.10 x1 x 11.56
MainGearToe- In Adjustment
SpacerBlock
Figure504
5. Alignmentof MainLandingGear(continued)
legbears
andspacerblock. Ensurethattheoutstanding
(e) Seta squareagainstthestraightedge
againstthe spacerblock.
NOTE: A carpenter'ssquare,becauseof its longlegs,is recommended
for checkingthemain
landinggearwheelalignment.
(f) If a gapappearsatthe rearbetweentheblockandsquare,thewheelistoed-outandmustbe
realigned.If a gapappearsattheforwardendbetweentheblockandthesquare,thewheel
hastoo muchtoe-inandmustbe realignedfora 0.5degreetoe-in.
theupperandlowertorque
removetheboltconnecting
(g) Tocorrecttoe-inortoe-outconditions,
links,removeor addspacerwashersto movethewheelin thedesireddirection,andreinstall
the bolt.
is correct,safetythecastellatednutwitha new
(h) Recheckwheelalignment.If thealignment
stillexists,separatethetorquelinksandaddor removea spacer
cotterpin. If misalignment
of thecotterpin in the
washer.Limitthe numberof spacersinstalledto allowfor installation
bolt.
EFFECTIVITY:
040-999
Jan 10/90 32-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Main Gear and Doors (continued)
6. Inspection
of MainLandingGear
(a) Inspectbolts,bearings,bushings,andballjointsfor excesswear,corrosion,anddamage.
(b) Inspectthe gearhousing,sidebracelinks,idlerlinks,rods,andattachment
platesforcracks,
bends,or misalignment.
(c) Inspectlockhookfor wearandoversizedbearingsurfaces.
(d) Inspectthe lockhookspringsforthe following:
(1.) Excesswearorcorrosionespeciallyaroundthe hookportionof springs.A springmustbe
rejectedif wearor corrosionexceedsone-quarter
thediameterof spring.
(2.) Checklockhookspringsforloadtensionsbelowtheminimumallowabletolerances.The
minimumtensionfor up lockhookspringsis4 poundsandthedownlockhooksprings7
pounds.Performthesechecksbyfasteninga fishtypescaleto theparticularhookand
springandpullingagainstthehookandspringfor a readingon thescale.
(e) Inspectup lockrollerforfreemovement
andminimumwobble.
(f) Inspectionbothup lockanddownlockrodsslidingsurfacesfor corrosion,freemovement,
and
lubrication.
(g) Inspectgeneralconditionof limitswitchesandwiringforfraying,poorconnections,
or
conditionsleadingto failures.
(h) Attachupperandlowerdraglinks. Ensurethatwhenstopsurfacesof thetwolinkscontact,
linkageis 0.219to 0.281inchthroughcenter(referto 32-10-00Figure401). Ifthisdistance
exceedsthe requiredthroughcentertravel,andif all boltsandbushings
are tight,replaceone
or bothsidebracelinks.
(i) Inspectlandinggeartrunnionboltsto ensureproperlengthboltsare installed.(Aminimumof
onethreadmustbe showingbeyondthetopof thenuts.)
(j). Inspectmainlandinggearforwardsidebracesasfollows:
(1.) Removepaint(referto 32-10-00Figure601)on bothforwardsidebraces.
ApproximateArea of Cracks.
PaintTo Be RemovedFor Inspection.
MainGearForwardSideBrace
Figure601
NOTE: If alodineis undamaged,
repaintingis notnecessary
betweenrepetitive50 hour
inspection
intervals.
(2.) InspectareaforcracksusingdyepenetrantorZygloprocedures.Payparticularattention
to top surfaceof affectedparts.
(3.) If cracksarefound,replaceaffectedpart(s)immediately
priorto anyfurtherflights.
(4.) Completeappropriate
logbookentry.
EFFECTIVITY:
32-10-00 Jan
PAGE13
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
7. Cleaningof MainLandingGear
(a) Cleanall partswitha suitablecleaningsolvent.
(b) If lockhookspringsarecorroded[referto Inspection
of MainLandingGear,step(d)(1.)],clean
all corrosionandrepaintthe springs.
8. Repairof MainLandingGear
Repairof thelandinggearis limitedto replacingbearingsandbushings,smoothing
out minornicks
andscratches,repaintingareaswherepainthaschippedor peeled,andreplacement
of parts.
9. Disassembly
of MainGearOleo (referto32-10-00Figure402)
Themaingearoleoassemblyis removedand disassembled
fromthe gearoleohousingwiththe
gearremovedor installedon theairplaneasfollows:
(a) Placeairplaneon jacks. (Referto Jacking,7-10-00.)
(b) Placea drippanundermaingearto catchspillage.
(c) Removeair andfluidfromoleo. (Referto OleoStruts.)
(d) To removepistontubeassemblyfromoleohousing,removeupperandlowertorquelink
connectingboltassemblyandseparatelinks. Notenumberandthicknessof spacerwashers
betweentwolinks.
(e) Compresspistontube,reachup alongthetube,andreleasethe retainerringfromtheannular
slotat thebottomof oleohousing.
(f) Pullpistontubewithcomponentpartsfromhousingcylinder.
areremovedbyreachingin thetubeandpushingouttheupper
(g) Theforktubecomponents
bearingretainingpins. Slideoff theupperbearing,spacer,lowerbearingwith O-ringsor
dynamicsealandwiper,washer,andretainerring.
(h) To removeorificetubefromtheoleohousing,cutsafetywireandremovecap boltandwasher
fromtop of housing.
(i) Theorificeplateis removedfromtheorificetubebyreleasingthe retainerringholdingtheplate
in position.
10. Assemblyof MainGearOleo(referto 32-10-00Figure402)
(a) Ensureall partsarecleanedandinspected.
(b) Toassembleandinstalltheorificetube,insertorificeplateintothebottomof thetube,with
countersunk
sideofthe orificeholeexposed.Secureplatewithretainerring. Lubricateand
installO-ringon theupperendof thetubeandinserttubeupthroughthebottomoleohousing.
on
to theoleohousingby installingtubecomponents
(c) Thepistontubeassemblyisassembled
thetube. Slidethe retainerring,washer,lowerbearingwithinnerandouterO-rings,spacer,
andupperbearingontothetube. Alignlockpinholesof theupperbearingandtube;install
retainerpins.
NOTE: Referto partscatalogfor correctpartnumberwhenreplacingO-ringsandwiperstrip.
PAG
10/9032-10-00
Jan 10/90
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main Gear and Doors (continued)
1
1. Bolt, OrificeTube
2. Washer
3. O-Ring, Packing
4. Tube, Orifice
5. Plate,Orifice
6. Ring, Retainer
7. Pin, Retainer
8. Bearing,Upper
9. Spacer
10. O-Ring Gasket
11. Bearing,Lower
12. O-Ring, Packing
13. Wiper Strip
14. Washer
15. Ring, Retainer
16. O-Ring, Packing
17. Plug
18. GreaseFitting
19. Valve,Air
20. Plug,Filler
21. Housing,Oleo
22. Tube, Piston
23. Bolt Assembly
24. Fork
25. Pin, Cotter
2
19
37
36
39
33
35
34
Main Gear Oleo Strut Assembly
Figure 402 (Sheet 1 of 2)
EFFECTIVITY:
040-999
32-10-00
Jan
an 10/90
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
7
NOTE: Referto previouspageforcallouts.
VIEWA
MainGearOleoStrutAssembly
Figure402 (Sheet2 of 2)
EFFECTIVITY:
040-999
Jan 10/9032-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGear and Doors(continued)
10. Assemblyof MainGear Oleo (refer to 32-10-00 Figure 402) (continued)
(d) Carefullyinsertpiston tube assemblyintothe oleo housing,guidingthe orificetube intothe
pistontube, until retainerring can be installedin the annularslot at the lowerend of the
housing. Installwiper strip,slide washerinto positionand secureassemblywith retainerring.
At the top of the housing,tightencap bolt.
(e) Installupper and lowertorque links. (Use samethicknessspacerwashersbetweenthe two
links removed,to maintaincorrectwheelalignment.)
(f) Lubricategear assembly. (referto 12-20-00 Chart2.)
(g) Serviceoleo strut with fluid and air (referto 12-10-00,Oleo Struts) and safetywith
MS20995C40wire betweenfiller plug and cap bolt.
(h) Checkgear alignmentand gear operation.
11. Inspectionof Main Gear Oleo
(a) Inspectthe landinggear oleo assemblycomponentfor the following:
(1.) Bearingsand bushingsfor excesswear,corrosion,scratches,and overall damage.
(2.) Retainingpins for wear and damage.
(3.) Lock ringsfor cracks,burrs,etc.
(4.) Cylinder,cylindersteelinsert,and orificetube for corrosion,scratches,nicks,and excess
wear.
(5.) Orifice platefor hole restriction.
(6.) Forktube for corrosion,scratches,nicks,dents,and misalignment.
(7.) Air valvefor generalcondition.
12. Cleaningof MainGear Oleo
Clean all parts with a suitabledry type cleaningsolvent.
13. Repairof Main Gear Oleo
(a) Repairof the oleo is limitedto smoothingout minor scratches,nicksand dentsand
replacementof parts.
(b) Individualreplacementof wiper strips is possible.
14. Removalof MainGear DoorAssembly
(a) To removethe outboardgear door,disconnectthe retractionrods from the door and removethe
hingebolts.
(b) To removethe inboardgear door,place the airplaneon jacks, retractthe gear enoughto allow
the door to open, disconnectthe actuatingcylinderrod, and removehingebolts.
EFFECTIVITY:
040-999
32-10-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MainGearandDoors(continued)
15. Installation
of MainGearDoorAssembly
(a) Installtheinboardgeardoorbyaligningthe hingebracketholeswiththebearingsandinstalling
and securingboltassembly.Installtheactuatingcylinderrodto the door.
(b) Installtheoutboardgeardoorby aligningthe hingebracketholeswiththebearingsand
installingandsecuringboltassemblies.Attachtheactuatingrodsbetweenthedoorand
landinggearhousing.
16 Adjustmentof Main Gear Doors
(a) Checkthat the mainlandinggear is properlyadjusted.
CAUTION: DAMAGETO THE DOORCAN RESULTIF RODSARE TOOSHORT.
(b) Adjustoutboarddoorrodsto maximumlengthandboltthemto bossesonthegearhousing.
Retractgearandobservetheamountof gap. Shortenrodsbyseveralturnsof the rodends
andretractthegearagain. Repeatuntilthedoorclosedproperly.
(c) Adjusttheinboarddoorusingsameprocedure
usedfor theoutboarddoor.
NOTE: If it is necessaryto fit new doorsor refit the presentdoors, maintaina gap of
approximately0.062of an inch exceptat the hingeside, betweenthe door,and the
skin surfaceof the wing. A gap of approximately0.092 of an inch mustbe maintained
at the hingeside of the door.
17. Inspection
of MainGearDoorAssembly
Inspecttheoutboard or inboarddoorsfor cracksor bentskin,loosehingebrackets,andwornor
corrodedbearings.
18. Cleaningof MainGearDoorAssembly
Cleanall partswitha suitablecleaningsolvent.
19. Repairof MainGearDoorAssembly
Repairto door assembliesis limitedto replacinghingebearing,bracketor rivets,minor skin
repairs,and painting.
PAGE18
Jan 10/90 3
EFFECTIVITY:
040-999
0 0-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. NoseGear and Doors
1. Fault Isolation- NoseGear and Doors
NOTE: Place airplaneon jacks before attemptingfault isolationof landinggear system (referto
7-10-00).
CHART 1
FAULT ISOLATION (NOSE LANDING GEAR AND DOORS) (Sheet 1 of 2)
Fault
Cause
No green light on panel
whengear are down.
Gear not lockedin down
position.
Adjust the gear.
Nosegear shimmies
during fasttaxi, takeoff
and landing.
Internalwear in shimmy
dampener.
Replaceshimmydampener.
Shimmydampeneror
bracketloose at mounting.
Replacenecessaryparts and bolts.
Tire out of balance.
Check balanceand replacetire
if necessary.
Wornor loosewheel
bearings.
Replaceand/oradjust wheel
bearings. (referto 32-40-00)
Worntorque link bolts
and/or bushings.
Replacebolts and / or bushings.
(referto 32-40-00)
Insufficientair and / or fluid
in strut.
Servicestrut with air and / or fluid.
Defectiveinternalparts
Replacedefectiveparts.
Strut bottomson normal
landingor whentaxiing
over roughground.
Remedy
in strut.
Excessive
or uneven
wearontire.
Doorscomeopenin
flight.
Doorsfailto close.
EFFECTIVITY:
040-999
Incorrectoperatingpressure.
Inflatetireto correctpressure.
(referto 32-40-00)
Wheeloutof alignment
(toe-inortoe-out).
Checkwheelalignment.
Doorsare riggedtootight.
Adjustriggingof doors.
Microswitchon power
packoutof adjustment.
Adjustmicroswitch.(referto
32-30-00)
Referto 32-30-00 Chart 1 and
32-60-00 Chart 1.
32-20-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseLandingGearandDoors(continued)
1. FaultIsolation- NoseGearandDoors(continued)
CHART 1
FAULTISOLATION (NOSELANDINGGEAR AND DOORS) (Sheet 2 of 2)
Fault
Nosegearfailsto steer
properly.
Cause
Remedy
Oleocylinderbindingin
struthousing.
Lubricatestruthousing.
Onebrakedragging.
Determine
causeandcorrect.
(referto 32-40-00)
Steeringarmrollersheared
at topof strut.
Replacedefectiveroller.
EFFECTIVITY:
040-999
Jan 10/9032-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
2. Removalof NoseGear (referto 32-20-00Figure401)
(a) Removerightandleft nosesectionsideaccesspanels.
(b) Removelowerradiosandradioshelf.
(c) Removethewaterseparatorassembly.(referto 21-70-00.)
(d) Placethe airplaneonjacks. (Referto Jacking,7-10-00.)
(e) Withthe handpump,retractthe nosegearslightlyto relievethegearfromits downlocked
position.
(f) Toremovethedraglinkassembly,
thefollowingprocedure
is used:
(1.) Disconnect
thegearretractionrodfromtheupperrightdraglink.
(2.) Disconnect
the lowerdraglinkfromthegearoleohousing.
(3.) Theupperandlowerlinkassemblies
are removedasoneunitby removing
theupperdrag
linksattachment
boltsat theirattachment
plates.
(g) Withthe lowerdraglinkdisconnected
fromthegearhousing,removethegearby removing
the
attachment
boltassemblies
at theattachment
plateson eachsideof thegearhousing.Note
the numberandlocationof spacerwashersbetweenthegearhousingandattachment
plates.
(h) Theidlerlinkis removedafterdisconnecting
thegearoperatingrodasfollows:
(1.) Removethedownlockspringandtheeyeboltattachedto the idlerlink.
(2.) Disconnect
thegearactuatingcylinderrodfromthelink.
(3.) Removethelinkpivotboltby slidingtheboltoutof thelinkallowingthe headto enterthe
holein thesideof the limitbracket.Withtheheadthroughthe brackethole,thethreaded
endof theboltcancontinueoutof thelink.
(4.) Removetheidlerlink.
(i) Theup lockcableisremovedbyremoving
the nutfromtheactuatingcylindersupportbolt and
slidingthecableoff thebolt. Retaintheboltin placeto supportthe cylinder.
(j) Theup lockhookis removedafterremovalof theup lockcable,blowdown
actuatingrod,and
the hookpivotbolt. Removethehookwiththeup lockspring.
NOTE:Theidlerlink,up lockcableandup lockhookcanbe removedwiththesupporttubeas
oneunit.
(k) Toremovesupporttube,removetheup limitswitchandwiresupportclamps.Holdsupport
nutsin thenosesectionwitha wrenchwhileremovingboltsandremovesupporttube.
(I) Thegearhousingattachment
platesare removedbygrindingthe rivetheadsflushwiththe
plateandremovingtherivets.
(m)Theupperdraglinksandattachment
platesareremovedbyholdingtheattachment
nutsin the
nosesectionwith awrenchandremovingthesupportbolts.
EFFECTIVITY:
040-999
32-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGear and Doors (continued)
NOTE:Referto Page6 for callouts.
NoseGearInstallation
Figure401 (Sheet1 of 3)
PAGE4 322000
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
56
62
25
52
57 57
33
Sketch B
60
36
36
Sketch A
Sketch C
NOTE:Referto Page6forcallouts.
NoseGearInstallation
Figure401 (Sheet2 of 3)
EFFECTIVITY:
040-999
PAGE
5
32-20-00
Jan
10/90
PIPER AIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
Calloutsfor Figure 401
1.
2.
3.
4.
5.
6.
7.
8.
9.
10.
11.
12.
13.
14.
15.
16.
17.
18.
19.
20.
21.
22.
23.
24.
25.
26.
27.
28.
29.
30.
31.
32.
33.
Door
Hinge,Aft
Bushing,Steering
Arm, Steering
BushingAssembly
BellcrankAssembly
Rod End, Steering
Nut, Lock
Rod, Steering
Hook, Uplock
Spring, Uplock
Bolt, Uplock
Rod End, Uplock Cable
Nut, Lock
Switch, Up Limit
Bracket,Switch
Tube,Support
Uplock Cable
Bolt Assembly
Bolt Assembly
Bracket
Spring, Downlock
Fitting,Grease
Link, Idler
Cylinder,Actuating
Hinge, Forward
Plate, DoorActuator
Door Actuator
Bracket, DownSwitch
Tab,Down Switch
Switch, Gear Down
Spring, DoorActuator
Rod End, Cylinder
34.
35.
36.
37.
38.
39.
40.
41.
42.
43.
44.
45.
46.
47.
48.
49.
50.
51.
52.
53.
54.
55.
56.
57.
58.
59.
60.
61.
62.
63.
64.
65.
Rod End, RetractionRod
RetractionRod
Nut, Lock
Drag Link, UpperLeft
PlateAttachment
DragLink, UpperRight
Rod, Door Retraction
DragLink, Lower
Stud, DoorActuator
Bolt Assembly
Housing,Gear Oleo
ShimmyDampener
TorqueLink, Upper
TorqueLink, Lower
ForkAssembly
Tire
Wheel
Bolt, Eye
Stop,Stroke
Nut, Lock
Bearing,Uplock
Bolt Assembly
UplockActuator
Key,Lock
Switch,Squat(PropellerReverse
NoseGear CenteringSpringAssembly
NoseGear BlowdownBottle
Valve
Rod End, UplockCableand BlowdownBottle
Bracket,DownSwitch
Clip, DownSwitch
Clip, DownSwitch
NoseGearInstallation
Figure401 (Sheet3 of 3)
PAGE 6
32-20-00
Jan10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
3. Installation
of NoseGear (referto 32-20-00Figure401)
NOTE: When assemblingany units of landinggear, lubricatebearingsand friction surfaces
with properlubricant(referto 12-20-00 Chart 3 and Figure 302)..
(a) Positionrightandleftupperdraglinkplatesandboltin place.
(b) If previouslyremoved,
positionrightandleftgearhousingattachment
platesandrivetin place.
(c) Installsupporttubeandsecure.Connectup limitswitchandsecureelectricalwiringto tube.
NOTE: Theuplockhook,uplockcable,idlerlink,andretractionrodcanbe assembled
on
supporttubeas a unitandinstalledon airplane(oreachcomponent
can be installed
individually),
aftersupporttubehasbeeninstalled.
(d) Theuplockhookwithuplockspringare installedasfollows:
(1.) Place U end of up lock springover back of hookwith loops towardthe back.
(2.) Spread springand snap loopsover bushingextendingthroughthe hook.
(3.) Hook ears of springover aft sideof hookbracketand push hookforwarduntil bolt holes in
bracketalign with holes in the hook.
(4.) Bolt hookin positionand be sure it rotatesfreelywith no side play,then safety.
(e) Installuplockcableandblowdownactuatingrodby attachingandsecuringslidingendto up
lockhookandtheotherendon gearactuatingcylindersupportbolt. Lubricateslidingendof
rodper lubrication
chart(referto 12-20-00Chart3).
(f) Theidlerlinkis installedasfollows:
(1.) Align bolt holein the link with lug holes of supporttube and with down limit switchcontact
boss to the right.
(2.) Insert headof pivot bolt into holein the side of up limit switch bracketfar enoughto allow
threaded end of the bolt to be insertedinto tube lug and link. Tightennut on bolt,allowing
link to turn free with no side play.
(3.) Attach retractionand actuatingcylinderrod end to idlerlink. Do not connectretractionrod
to drag link until gear adjustmentis completed.
(4.) The downlockspring is attachedaftergear checkand adjustmentis completed.
(g) Toinstallgearhousingassembly,
positiongearso attachment
pointson housingalignwith
attachment
plates.If needed,installspacerwashersbetweenattachments
allowinga minimum
amountof sideplay. Tightenpivotboltnutsto a snugfit allowinggearto swingfree;safetywire
nuts.
(h) Thedraglinksareinstalledasfollows:
(1.) Alignupperandlowerdraglinkboltsholes,installbolt,uplockbearing,andsecure.
(2.) Checkthatlinkagethrough-center
travelis withintolerance.
(3.) Attachupperdraglinksto attachment
plates,tightennutsto a snugfit allowinglinksto
swingfree,andsafetywirethenuts.
(4.) Attachlowerdraglinkto landinggearhousingandtemporarily
installbolt. Secureand
safetythebolt aftergearisadjusted.
(5.) Manuallyretractandextendlandinggearseveraltimesto checkforsmoothoperation.
(6.) Attachretraction
rodto upperrightdraglink. Adjustrodto obtainapproximately
0.06of an
inchclearancebetweenlowerlocknutandlink.
EFFECTIVITY:
32-20-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
3. Installation
of NoseGear (referto 32-20-00Figure401)(continued)
NOTE: Besurelocknutsaretightenedagainstretraction
rod.
(i) Graspgearfork androtateto ensurenogapsexistbetweensteeringarmtravelbushingsand
steeringbellcrank,whichcouldcausethenosewheelto shimmy.Bushingsareavailablein
severaldifferentdiametersto establishproperclearance.Adjustment
mustbe madewith no
loadatthesepoints.
(j) Lubricatelandinggearassembly.(Referto 12-20-00Chart 3 andFigure302).)
(k) Checknosegearfor alignmentandoperation.
4. Adjustment
of NoseGear(referto 32-20-00Figures401and501)
NOTE: Useemergency
handpumpin thecockpitor hydraulic
test unitto supplyhydraulic
pressureforadjustmentoperations.
(a) With airplaneon jacks and gear extended,disconnectdoor retractionrods and securedoors in
the open position.
(b) To facilitateadjustmentof up lock, observethe following:
(1.) Disconnect
lowerdraglinkfromgearoleohousing.
(2.) Disconnect
actuatingcylinderrodendfromidlerlink.
(3.) Disconnect
endof downlockspringfromidlerlink.
(4.) Disconnect
andslipbootoverup lockrodandlocknutbackalongroduntiladjustment
is
complete.
(5.) Pullactuatingcylinderbarreldownandforwarduntilactuatorattachingbolt is atthe
bottomof theslotsin attachment
bracket.
(6.) Rotatedraglinkassemblyby handuntilup lockhookengagesup lockbearing.
(7.) Withbothup lockrodsfullyextendedandthehookrestingfullyonthe up lockroller,adjust
the rodends(up lockandblowdown
actuatingrod)untiltheattachingbolton thehookcan
befreelyinserted.Removethebolt,extendtherodendsonefullturnandlock. Reinstall
the boltandsecure.
NOTE: Theactuatingcylinder'sandup lockrod'sattachingboltmustremainin the
bottomof theattachment
fittingslotsduringthisadjustment.
(8.) Lubricateas necessary,
slipbootovertheup lockrodendlocknutandsecureafterthe
adjustmentof nosegearis complete.
(c) Returnthedraglinksto the DOWNposition,attachthe lowerdraglinkto the landinggear
housing;secureandsafetyunlesscheckingthelinkthroughitstravel.
(d) Thethroughtravelof the linkischeckedasfollows:
(1.) Withthegearin the DOWNpositionandthe stopsurfacesof thedraglinkstouching,
checkthe linkageis 0.063to 0.156inchesthroughcenter.
NOTE: The linkagemustnotexceed0.156inchesthroughcenter.A fabricatedtoolcan
be constructed
to checkthrough-center
travelofthe draglinkassemblywhilethe
linksare installedon theairplane.(Referto 32-20-00Figure501).)
EFFECTIVITY:
PAGE 8
32-20-00
32-20-00
Jan 10/90
A. NoseGear and Doors(continued)
1.25
MATERIAL: Steelor hardaluminum
.875 x .095 x 9.188 Tube
.125 x 3.50 x 24.71 Plate
NOTE: It is importantthatcenter line
accuracybe usedwhen locating
holes for installationof bushing,
sightslot and elongatedhole.
.50
See Note
as
.25
R
.875
NoseGear GaugeLinkTravelTool
Figure 501
4. Adjustmentof Nose Gear (referto 32-20-00 Figures 401 and 501) (continued)
(2.) To use the fabricatedtool, be surethe gear is in the down lockedpositionwith no
hydraulicpressureon the system.
(3.) Removecotter pins whichsafetythe nutssecuringboth upperdrag linksto their
attachmentplates and the lower link to the gear housing.
(4.) Placethe tool tube throughthe elongatedhole in the tool plate. Place the tube over and
betweenthe upper link attachingnuts.
(5.) Swingthe plateup againstthe head of the bolt connectingthe upper and lowerlinks. The
plate sleeveslidesover the nut of the boltconnectingthe lower link to the gear housing.
(6.) Lookthroughthe right hole in the plateto ensurethe center of the bolt is 0.063 to 0.156 of
an inch belowthe centerlineon the plate.
(7.) Removetool and reinstallcotter pins.
EFFECTIVITY:
040-999
32-20-00Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGear and Doors (continued)
4. Adjustmentof NoseGear (refer to 32-20-00 Figure 501) (continued)
(e) The idler or retractionrod must be adjustedto providea distinct snap-throughaction as the
idler linkagepassesthroughcenter.
(f) Adjust the idler link stop bolt on the right side of the wheelso the idler linkageis 0.22 to 0.28
inchesthroughcenter. Tightennutson idlerlinks.
(g) Connectdownlockspringto the idlerlink.
(h) Extendactuatorpistonwith hydraulicpressureand adjust rod end until the attachingboltcan
be freely inserted. Releasepressureand extendrod end one full turn. Reinstallbolt and
secure. Tightenthe rod end locknutand safetywire.
NOTE: Rod ends and strokecontrol are lockedwith an NAS559lockingkey and safetywire.
Use the propertechnique.
(i) Reinstallattachingbolt and secure. Place key locks betweenlocknutsand the keywayin the
rod. Screw locknuton the rod and keepthe key lock centeredin the keywaywhile tightening
the locknuts(32-20-00 Figure401 showsproperinstallationof the locks on the piston rod end).
NOTE: It could be necessaryto partiallyretractthe gear to tightenthe locknuts.
() Retractgearandadjuststrokecontrolstopontheactuatoruntiltheup lockbearingclearsthe
insideof the up lockhooksurfaceby 0.030to 0.060of an inch. Tightenthe locknuton the
strokecontrolstop(referto 32-20-00Figure401).
(k) Withthe gearup andlocked,closeonedoorat a timeandadjustdooroperatingrodsuntilbolts
canbe freelyinserted.Shortenrodsonefull turnof therodends. Donot installbolts.
(I) Extendgearandinstalldooroperatingrodbolts.Adjustdooropenstopboltsto allowthedoor
linkageto pass0.06to 0.12inchesthroughcenter.
(m)Retractgearslowly(usehandpump)andensureall partsareoperatingsatisfactorily.
(n) If gearfailsto remainretractedafterthecockpithandlereturnsto neutral,it isnecessaryto
readjusteitheror bothof thefollowing,untilthegearlocks up:
(1.) Increasethe actuatorstrokeby turningoutthe strokecontrolstop.
(2.) Relievedoorpinchbylengthening
thedooroperating
rods.
CAUTION: CHECKALL ROD ENDSFORADEQUATETHREADENGAGEMENT.
(o) Adjust the propellerreverseswitch, locatedon the nosegear torquelink, to activatewhen the
oleo strut is within 0.25 inches± 0.12 inchesof its fully extendedposition.
(1.) Extend and compressthe strut to ensureswitch actuatesproperly. Connecton ohmmeter
to the electricalswitchleads. Measurethe strut extensionat the point wherethe switch
closes. This distancemust be withinthe rangegiven.
(2.) Ensurepropellersmoveinto their reversepositionduring taxi test only.
EFFECTIVITY:
040-999
Jan 10/90 32
2000
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Nose Gear and Doors (continued)
5. Alignmentof NoseGear (referto 32-20-00 Figure 502)
(a) Placeairplaneon a smoothlevel floor whichwill showthe strikingof a chalk line.
(b) Placeairplaneon jacks. (Referto 7-10-00.)
(c) Level airplanelaterallyand longitudinally.(Referto 8-20-00 Figure1.)
(d) From the centerof the tail skid, extenda plumbbob and mark the contactpoint on the floor.
(e) Extendand attacha plumbbob from a pointapproximately24 inchesforwardalongthe bottomcenter rowof rivets measuredfrom tile wheelwell opening. Markthe point of contacton the
floor.
(f) Usingthe two plumb bob marksas a guide,snapa chalk line extendingseveralfeet beyond
eachmark.
(g) Placethe rubberpedals in neutral position(referto 32-20-00 Figure 503).
NOTE: The ruddercontrolsystemmustbe properlyrigged beforealigningnosegearsteering.
(h) Adjust steeringrod end bearingsto align nosewheelwith chalk line. Toalign nosewheel
straightforward,stand in front of the nosegear,align the center rib of the tire with the chalk
line, or lay a straightedgealongthe side of the tire paralleland straightedgewith the chalk line.
One end of the rod mustbe disconnectedand jam nuts loosenedto makethis adjustment.Do
not attemptto makeadjustmentwith one bearing;dividethe adjustmentbetweenthe bearings
at each end of the rod. Checkthat rod ends havesufficientthread engagement,reinstallthe
rod and securejam nuts.
PlumbBob
Chalk Line
Alignmentof NoseGear
Figure 502
EFFECTIVITY:
040-999
32-20-00 Jan
PAGE
11
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
Rudder
Pedal
Assembly
Fuselage
Station
57.00
Rudder Pedals Neutral Position
Figure 503
5. Alignmentof NoseGear(referto 32-20-00Figure502) (continued)
(i) Tochecknosegearsteeringfor 24degreemaximumrightand16degreelefttravel,marka line
on eachsideof thenosewheelfor properanglefromcenterline
andwheelpivotpoint. Turn
wheelto maximumtravelin bothdirections
to checkfor allowabletravel.Shouldtravelbe
exceededin onedirectionandnotenoughin theotherdirection,checkfor possibledamageto
the gearfork,torquelinks,or steeringtorquetube.
NOTE: To ensurefull travel of the nosewheel,ensure no gapsexist at pointswherethe
steering armtravel bushingscontactwith the steeringbellcrank.
6. Adjustment
of LandingGearPropellerReverseSwitch
Thepropellerreverseswitchis locatedonthenosegeartorquelink.
(a) Adjustswitchto activatewhenthe oleostrutis within0.25+ 0.12inchesof itsfully extended
position.
(b) Extendandcompressstrutto pressureswitchactuatesproperly.Connectanohmmeter
to the
electricalleadsof the switch.Measurethestrutextensionat thepointwherethe switchcloses.
Thedistancemustbe withinrangegivenin step(a).
(c) Checkto be surepropellersmoveintotheirreversepositionduringtaxitest.
CAUTION: DO NOT ATTEMPTTO MOVETHE POWERLEVERSINTO REVERSEWITH
THE ENGINESSTATIC,AS DAMAGEWILL RESULTTO THE LINKAGE.
EFFECTIVITY:
PAGE
12 32-20-00
10/90
Jan
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
7. Inspection
of NoseGear
(a) Inspectbolts,bearings,bushings,
andall balljointsfor excessive
wear,corrosion,anddamage.
(b) Inspectthegearhousing,draglinks,idlerlink,uplockcable,rods,andattachment
platesfor
cracks,bends,or misalignment.
(c) Inspectthedownlockspringasfollows:
(1.) Checkfor excesswearorcorrosion,especiallyaroundthelockportionof thespring.The
springmustreturnto completecompression.A springmustbe rejectedif wearor
corrosionexceedsone-quarter
thediameterofthe spring.Cleanawayallcorrosionand
repaintthe springs.
(2.) Checktherightandleftgeardooractuatorspringsfor loadtensionsbelowtheminimum
allowable
tolerances.Theminimum
tensionfortheactuatorspringsis 10poundsat 3 inch
extension.If onespringis rejected,replacebothsprings.
(3.) Checkthedownlockspringatthe idlerlinkfor loadtension.Theminimum
tensionis 20.5
poundsat 7.312inchesextension
and47 poundsat 11.312inchesextension.
(4.) Checktheuplockspringat theuplockhookfor loadtension.Theminimumtensionis 4
pounds.Thischeckis performed
byfasteninga fishtypescaletothe hookandspring.
Pullsteadilyagainstthehookandspringto geta reading.
(d) Inspecttheuplockhookfor wearandoversizedbearingsurfaces.
(e) Inspecttheuplockrollerforfreemovement
andminimumwobble.
(f) Inspectbothuplockcableslidingsurfacesforcorrosion,freemovement,
andlubrication.
(g) Checkthegeneralconditionof limitswitchesandwiringfor fraying,poorconnections,
or
conditions
whichcouldleadto failures.
(h) Attachtheupperandlowerdraglinksandcheck,whenstopsurfaces
touch,thatlinkageis
0.063to 0.156inchthroughcenter.Shouldthisdistanceexceedtherequiredthrough-center
travelandboltandbushingsaretight,replaceoneor alldraglinks.
(i) Inspectshimmydampener
for security,damage,corrosion,andleaks.
8. Cleaningof NoseGear
(a) Cleanall partswitha suitablecleaningsolvent.
9. Repairof NoseGear
NOTE: Theshimmydampener
requiresno repairotherthanroutineinspection.In caseof
damageor malfunction,
thedampenermustbe replaced,notrepaired.
Repairto the landinggearis limitedto reconditioning
of parts,suchasreplacingbearingsand
bushings,smoothing
outminornicksandscratches,repainting
of areaswherepainthaschipped
or peeled,andreplacingof parts.
EFFECTIVITY:
040-999
Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
10. Disassembly
of NoseGearOleo (referto 32-20-00Figure402)
Thenosegearoleoassemblyis removedanddisassembled
fromthegearoleohousingwiththe
gearremovedfromor installedon theairplane.
(a) Placethe airplaneon jacks. (Referto 7-10-00.)
(b) Placea drippanunderthenosegearto catchspillage.
(c) Removeair andfluidfromtheoleo. (Referto OleoStruts,12-10-00.)
(d) Toremovecompletecylinderandforkassembly
fromtheoleohousing,cut thesafetywireand
removecapboltsattachingthesteeringarmandalignerguidebracketto thetopof theoleo
cylinder.
(e) Disconnect
theshimmydampenerbyremovingtheboltassemblyconnecting
thedampener
to
thecylinder.
(f) Releaseandremovethe retainerringatthetopof thehousing.Pullthe completecylinder
assemblyfromthebottomof thehousing.Theupperandlowerhousingbushingsmustremain
pressedin thehousing.
(g) Toremovethepistontubeassemblyfromthecylinder,separateupperandlowertorquelinks
by removingtheconnecting
boltwithwasher,nut,andcotterpin. Notethespacerwasher
betweenthetwolinks.
(h) Compressthepistontube,reachup alongthetubeandreleasethesnapringfromtheannular
slotat thebottomof theoleohousing.
(i) Pullpistontubewithcomponent
partsfromcylinder.
(j) Thepistontubecomponents
are removedbyreachingin thetubeandpushingouttheupper
bearingretainingpins. Slideoff thetube,theupperbearing,spacer,lowerbearingwithouter
and innerO-rings,wiperstrip,washer,andretainerring.
(k) Toremovetheorificetube,removethelargeboltof theorificetubeandlockplatefromtopof
thecylinder.Pullthetubefromthecylinder.
(I) Theorificeplaceis removedfromthebottomof theorificetubeby releasingtheretainerring
holdingthe platein position.
NOTE: Do notremovethepistontubeplugor O-ringof thepistontubefromthefork.
11. Assembly
of NoseGearOleo (referto 32-20-00Figure402)
(a) Ensurepartsarecleanandinspected.
(b) Toassembleorificetube,insertorificeplateintothebottomof tubewithcountersunk
sideofthe
orificeholeexposed.Securetheplatewiththeretainerring. LubricateandinstalltheO-ringon
theupperendof tube.
(c) Inserttubeup throughbottomof cylinder.Withthetubeexposedthroughthetopof the
cylinder,installorificetubeboltfingertight.
(d) Thepistontubeassemblyis assembled
byinstallingthetubecomponents
on thetube. Slide
the retainerring,washer,lowerbearingwithouterandinnerseals,spacer,andupperbearing
ontotube. Alignbearingretainerpin holesoftheupperbearingandpistontube;installpins.
NOTE: Referto partscatalogforcorrectpartnumberwhenreplacingO-ringsandwiperstrip.
(e) Lubricateinnerwallof cylinderandcarefullyinsertthe pistontubeassemblyintothebottomof
thecylinder,allowingtheorificetubeto guideitselfintothepistontube,untiltheretainerring
can be installedin the annularslot,at theendof thecylinder.Installthewiperstripandslide
thewasherintopositionsecuringtheassemblywiththe retainerring.
EFFECTIVITY:
040-999
Jan 10/90 32
2000
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
1. Pin, Retainer
2. Bearing,Upper
3. Spacer
4. O-Ring, Outer Packing
5. Bearing,Lower
6. O-Ring, Inner Packing
7. Wiper Strip
8. Washer
9. Ring,Retainer
10. Ring,Retainer
11. Bushing,HousingTop
12. Cylinder,Oleo
13. Bushing,HousingBottom
14. O-Ring, Packing
15. Tube,Orifice
16. Plate,Orifice
17. Ring, Retainer
18. GreaseFitting
19. Fork
20. Bolt Assembly
21. Fork Assembly
22. TorqueLink, Upper
23. Washer,Spacer
24. Bolt Assembly
25. TorqueLink, Lower
26. Tube, Piston
27. ShimmyDampener
28. Bolt Assembly
29. Bolt Assembly
30. Bolts and SafetyWire
31. Bracket
32. Bushing
33. Stud, DoorUplock
34. Placard,Service
35. Housing,Oleo
36. Bushing
37. Bolt,Cap
38. Bolt
39. Plug, Filler
40. Aligner GuideBracket
41. Valve,Air
42. Arm, Steering
43. Pin, Cotter
44. Safety Wire(.041)
45. Piston Ring
46. Bushing,Steering
47. O-Ring, Packing
48. Plug, PistonTube
28
49. Screw,FlushHead
50. Bushing
51. Seal
52. Pin, Metering
53. Nut, Washer,O-Ring
54. O-Ring
Nose Gear Oleo Strut Assembly
Figure 402 (Sheet 1 of 2)
EFFECTIVITY:
040-999
32-20-00PAGE
15
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
SEE VIEW B
VIEW B
NoseGearOleoStrutAssembly
Figure 402 (Sheet2 of 2)
PAGE
1 32-20-00
Jan 10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
11. Assemblyof NoseGearOleo (referto 32-20-00Figure402) (continued)
(f) At thetopof thecylinder,tightentheorificetubebolt.
(g) Installtheupperandlowertorquelinks.
(h) Checkthe upperandloweroleohousingbushingsare installedandlubricatethe bearing
surfaceslightlywithMolykoteNo.33. Installthecylinderintotheoleohousingandsecurewith
retainerring.
(i) At thetopof theoleohousing,installthealignerguidebracketandsteeringarmon thecylinder.
Tightencap boltsto 30 - 35 inch-pounds
andsafetywithMS20995C41
wire.
as
follows:
dampener
Rig
shimmy
shimmy
dampener.
(j) Installthe
(1.) Rotatethe nosegearto full righttowlimitandretain.
(2.) Extendshimmydampener
to itsfulltravel.
(3.) Adjusttherodendbearinguntiltheattachment
boltfits theholein thebracket.
(4.) Removetheboltandturntherodendbearingoutonefull turn.
(5.) Securetherodendto thebracketwithbolt,washer,andself-locking
nut.
(k) Lubricate
the gearassembly.(Referto 12-20-00Chart 3 andFigure302.)
(I) Servicetheoleostrutwithfluidandair. (Referto OleoStruts,12-10-00)
(m)Checkthenosegearfor alignment
andoperation.
12. Inspectionof Nose Gear Oleo
(a) Inspectthe landinggear oleo assemblycomponentfor the following:
(1.) Bearingsandbushings
for excesswear,corrosion,scratches,
andoveralldamage.
(2.) Retainingpinsforwearanddamage.
(3.) Lockringsforcracks,burrs,etc.
(4.) Cylinder,cylindersteelinsert,andorificetubefor corrosion,scratches,nicks,andexcess
wear.
(5.) Orificeplatefor holerestriction.
(6.) Forktubefor corrosion,scratches,
nicks,dents,andmisalignment.
(7.) Airvalvefor generalcondition.
13. Cleaningof NoseGearOleo
Cleanall partswitha suitabledrytubecleaningsolvent.
14. Repairof NoseGearOleo
(a) Repairof the oleois limitedto smoothing
outminorscratches,
nicksanddentsand
replacement
of parts.
(b)Wiperstripson gearstrutscanbe individually
replaced(referto 32-20-00).
EFFECTIVITY:
32-20-00
PAGE
17
32-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGearandDoors(continued)
15. Removalof WiperStripon GearStrut
(a) Placeairplaneon jacks. (Referto 7-10-00.)
(b) Jackairplanehighenoughto takeweightoff gear.
(c) Releaseair pressurefromstrutbydepressing
thevalvecorepinuntilpressurehasdiminished.
(d) Usingsnapringpliers,disengagesnapringfromannularslotin theoleohousing,allowingit to
layat the lowerendof thepistontubealongwiththewiperstripretainerwasher.
(e) Removeoldwiperstripfromhousingandcleanandinspectthehousingto ensurenopieces
remain.
(f) WipepistontubeandcheckIt for anyabrasions
whichcoulddamagethe newwiper. Polish
tubeto removeanyabrasions.
16. Installation
of WiperStripon GearStrut
(a) A newwiperstripmustbe cutwith a 30degreebevel,a littlelongerthanneeded,to circlethe
pistontube.
(b) Insertnewwiperstripup intotheoleohousingwiththetaperededgedown. Slidetheretainer
washerandsnapringup thepistontube. Insertthemintotheoleohousing.Usingsnapring
pliersto compressthe snapring,installit intotheannularslotin theoleohousing.
(c) Inflatetheoleostrutaccording
to instructions
givenin OleoStruts(referto 12-10-00).Remove
airplanefromjack.
17. Removalof NoseGearDoorAssembly
(a) Toremovegeardoor,disconnect
retractionrodat thedoorandremovehingeboltsat eachside
of thewheelwell.
(b) Toremovedoorretractionmechanism,
be sureretractionrodis disconnected.
Disconnect
the
downlockspringandremovethesnapringholdingthe retraction
mechanism
on its support
shaft. Pullthe retractionmechanism
fromshaft.
18.Installation
of NoseGearDoorAssembly
(a) To installthedoorretractionmechanism,
positionandboltunitin place. Connectthedownlock
spring.
(b) Thegeardooris installedbyaligningthe bracketbolt holewiththe hinge,installingbolt
assemblyandsecuringit. Attachandsecuretheretractionrod.
Jan 10/90
32-20-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. NoseGear and Doors (continued)
19. Adjustmentof NoseGear DoorAssembly
(a) Checkthat nose landinggear is properlyadjusted.
(b) With gear up and locked,closeone door at a time and adjustdoor operatingrods until bolts
can be freely inserted. Shorten rodsone full turn of rod end bearings. Do not installbolts.
(c) Extendgear and installdoor operatingrod bolts. Adjustdoor open stop bolts, allowingdoor
linkageto pass 0.060to 0.120 inchesthroughcenter.
(d) Retractthe gear slowly. Ensureall parts are operatingsatisfactorily.
(e) If gearfails to remain retractedafterthe cockpit handlereturnsto neutral,it is necessaryto
readjusteither or both the followingitems until gear locksup:
(1.) Increaseactuatorstrokeby turning out the strokecontrol stop.
(2.) Relievedoor pinch by lengtheningthe door operatingrods.
20. Inspectionof NoseGear DoorAssembly
(a) Inspectdoor for cracksor bent skin, loosehinge brackets,and worn or corrodedbearings.
(b) Check retractionmechanismfor a worn down lock springand worn or damagedsurfaces.
21. Cleaningof NoseGear Door Assembly
Cleanall partswith a suitablecleaningsolvent.
22. Repairof NoseGear DoorAssembly
Repairto the door assemblyis limitedto replacinghingebearings,rivets, mechanismparts, minor
skin repairs,and repainting.
EFFECTIVITY:
040-999
32-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extensionand Retraction
(1) Descriptionand Operation
The nosegear retractsaft intothe nosesection,pullingmechanicallyinterconnectedgeardoors
closed. The main landinggears retract inboardinto eachwing and are coveredby hydraulically
actuateddoors and those mechanicallyconnectedto eachgear.
The gearoperatingmechanismsusetwo systems. The primarysystemuses hydraulicpower
during normal operationsand is coveredin Chapter29. A secondaryor redundantsystem,
incorporatedinto each gear operatingmechanism,providesa way of extendingthe requiredgear if
any partof the hydraulicsystemfails. The secondarysystem,incorporatedas an emergency
backupfor the hydraulicsystem,only movesthe affectedgear to the down position.
The landinggearoperatingcontrolsare locatedon the pilot's side of the instrumentpanel. The
gear selector,with the indicatorlightsto its right, is situatedon the bottomof the paneldirectly
underthe columnof engineinstruments.The emergencyextensionbutton is also mountedon the
pilot's side of the instrumentpanel,just belowthe oxygen pressuregauge,to the rightof the
alternatestatic sourceselector.
Two meansof emergencyextensionare available. The emergencyextension(blowdown)system
(EES)(refer to 32-30-00 Figure 1) employsa logic circuitwhich sensesgears not extended.
Whenthe button is pushed,the remaininggears are extendedand lockedin place. The system
worksso if one or moregears fail to extendand the emergencyextensionbuttonis pushed,the
logic relayallows electricalpowerto ignite an explosivechargeon the affectedgear's system.
After the charge is blown,compresseddry nitrogenis releasedthrough its own systemof tubing
and intothe workingactuators. Each individualsystemuses a gas supplybottle,shuttlevalve,and
up lock-unlockingactuator,all of which aregas operated.
Besidesthe emergencyblowdownsystem,the gear can also be pumpeddown. A hand pump
found under a floor access panelbetweenthe pilot's and copilot'sseatcan be usedto extendthe
gear if the hydraulicpump systemfails. If a problemdoesdevelop, and time permits,use the hand
pump first becauseoncethe emergencyextensionsystemis activated,the affectedmechanism
and hydraulicsystemmustbe purgedand serviced.
An anti-retractionsystemis installedto guardagainst inadvertentretractionof the landinggear
when the airplaneis on the ground,a solenoidlatch is positionedjust abovethe controllever. A
squatswitch on the landinggear and a dynamicpressureq sensormust operatethis latch before
the landinggear selectorcontrolcan be movedupward. The landinggear controlknobis in the
shapeof a wheelto differentiateit from the flap control,which has a knob in the shaftof an airfoil.
EFFECTIVITY:
040-999
32-30-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ExtensionandRetraction(continued)
4
NOTE:See FollowingPageFor Callouts.
EmergencyExtensionSystemInstallation
Figure 1 (Sheet1 of 2)
EFFECTIVITY:
Jan 10/90 32-30-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ExtensionandRetraction(continued)
1. Pump- EngineDriven
J.K.M. Filter
N. Reservoir
P. LandingGearSelectorValve
Q. SelectorValveDetent
R. SelectorValveSpringReturn
S. ElectricalSwitch
T. ElectricalConnector
11. PressurePortValve
12. SuctionPortToggleValve
13. Hand PumpCheckValve
AA.Cylinder
BB.ExplosiveValve
CC.Fill Valve
DD.Burst Disc
EE.Gauge
15. UnlockActuator
16. ShuttleValve,Main Gear
17. ShuttleValve,NoseGear
2. Filter
3. CheckValves
4. HandPump
5. SelectorHandle
6. RestrictorValve
7. Actuator,NoseGear
8. Actuator,MainGear
9. Actuator,MainGearDoor
10. PowerPackAssembly
A. MainReliefValve
B. EnginePumpCheckValve
C. PriorityValve
D. DoorSolenoidValve
E. VentValve
F. TimeDelayCheckValve
G. TimeDelayValve
H. HandPumpReliefValve
BOTTLEFILL PRESSURES
FILL PORT- DRYNITROGENONLY
SEE SERVICEMANUAL
FOR INSTRUCTIONS
TEMP.- PRESSURERANGE
F
-40
-20
0
+20
+40
PSIG
1585
1560
1735
1815
1890
F
+60
+70
+80
+100
+120
PSIG
1960
2000
2035
2110
2185
EmergencyExtensionSystemInstallation
Figure 1 (Sheet 2 of 2)
EFFECTIVITY:
040-999
3
32-30-00JanPAGE
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. ExtensionandRetraction(continued)
2. Fault Isolation- Extensionand Retraction
NOTE: Placeairplaneon jacks before attemptingfault isolationof landinggear system (refer to
7-10-00).
CHART 1
FAULT ISOLATION (EXTENSION AND RETRACTION) (Sheet 1 of 2)
Cause
Remedy
Selectorlevercannotbe
movedto thegearup
positionwhilethe LEFT
maingearstrutiscompressedorwiththepower
off.
Ensurethat the LEFT maingear
strut is extendedand that the
power is on.
Faultysafetyswitch on
left maingear.
Adjust or replacesafety
switch.
Priorityvalve leaksin
power pack.
Check priorityvalve
crackingpressure.
Solenoidvalve stuckin
closedposition.
Turn off powerand hand
pump doors open.
Microswitch on power
pack out of adjustment.
Checkfor bent bracketor loose
mountingor wire and adjust.
Doors comeopen in
flight.
Micro switch on power
Adjust microswitch.
Doorsfailto close.
Circuitbreakerout.
Checkcircuitbreaker.
(refer to 32-60-00)
Lightswitchoutof
adjustment.
Adjust limit switch.
(referto 32-60-00)
Gearnotfullyretracted.
Checkadjustment.
Cannonplugon power
packloose.
Tightenplug.
Solenoidvalvestuckin
dooropenposition.
Checkwiringto solenoidvalve.
Notenoughactuatorstroke.
Increasetheactuatorstroke.
Fault
Landinggear selector
handlefails to operate
to gear up position.
Gear retractsor extends
before the doors open.
Nosegearfailsto lock
up whenhandlereturns
to neutral.
pack out of adjustment.
EFFECTIVITY:
040-999
Jan 10/9032-30-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extension
andRetraction(continued)
2. FaultIsolation- Extension
andRetraction
(continued)
CHART 1
FAULTISOLATION (EXTENSIONAND RETRACTION) (Sheet2 of 2)
Fault
Maingearfailsto lock
up.
Nogreenlighton panel
whengearsaredown.
EFFECTIVITY:
040-999
Cause
Remedy
Uplockrodoutof adjustment.
Adjustrod.
Actuatoroutof adjustment.
Adjustactuator.
Lockswitchdefective
or outof adjustment.
Replaceand/oradjust
lockswitch.
Gearnotlockedin down
position.
Adjustthe gear. (refer to
32-10-00and 32-20-00)
PAGE 5
10/90
Jan10/90
32-30-00Jan
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extension
andRetraction(continued)
3. ServicingAfter Activationof EmergencyGear ExtensionSystem(EES) (referto 32-30-00 Figure
301)
NOTE: Shelflife of the EESexplosivevalvesis5 years.Anyexplosive
valveover5 yearsold
mustbe replaced.
Afterusingthe EES,pneumatic
pressurefromthesystemmustbe releasedandthehydraulic
systempurged.
(a) Toreleasepressure,loosencapon teefittingserviceporttill thepressurerecedes.Leavethe
caplooseon thefitting.
(b) Oncethedamageis corrected
on thehydraulicsystem,connectthe hydraulic
test cartto
hydraulictest ports.
(c) Usingthetest cart,cyclethegearto theDOWNpositionandat least6 moretimesto ensure
the shuttlevalveandsystemis in thehydraulicmode. It maybe necessary,
depending
on the
damageto the hydraulicsystem,to actuatethegearmorethan6 timesto removeanyair in the
system.
(d) Retighten
the capon servicefitting.
(e) Disconnect
electricalwiringandpneumaticlinefromexplosive
valveon thestoragebottle.
NOTE: On the nose gear bottle,the tee fitting mustbe removedfromthe explosivevalve. Be
sure to note that the fitting is installedwith the test port inboard.
(f) Installreplacement
valveon thebottle.
(g) Reconnect
electricalwiringandpneumaticlineto theexplosive
bottle.
(h) Chargebottlewithdrynitrogento pressureindicatedonthe placardmountedon thewheelwell
nextto thefill valve(referto 32-30-00Figure1).
(i) Performfunctionaltestcoveredin 32-30-00.
4. FunctionalProofPressureandLeakTestForEES
(a) Supportaircraftonjacks.
(b) Disconnect
nosegearandmaingearstrutdoors.Securethemin full OPENposition.
(c) Connecta hydraulic
test cart(referto 29-10-00)
to thehydraulicsystemserviceports.
(d) Loosencapsfromtheteetest portsinstalledin theEESlinesleftandrightmaingearsandon
theexplosivevalveon thenosegearstoragebottle.
(e) Activatehydraulicsystemthroughthetestcartandcyclethegearsixtimesto ensureshuttle
valveis in the hydraulicmode. Onthelastcycle,leavegearin the UPandlockedpositionand
placegearselectorhandlein theneutral,DOWNposition.
(f) Removecap fromteetest portat theleftmaingear. Connecta nitrogensourceof 4000to
5000psi (referto 32-30-00Figure301).
(g) Carefullypressurizesystemto 2000± 50 psi.
(h) Ensureleftmaingeardooropensfully,thegearunlocksfromtheUPposition,andlowersto the
DOWNandlockedposition.
(i) Slowlyincreasepressureinthe systemto 3000± 50 psi andmaintainfor 3 minuteswhile
checkingtheshuttlevalves,theunlock,geardoor,andgearactuatorsfor leakageand
deformation.
() Depressurize
thesystem,disconnectalternatenitrogensource,andscrewcapon teefittingso
excesspressurecanescape.
EFFECTIVITY:
PAGE6
Jan10/90
32-30-00
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extension
andRetraction(continued)
12
11
11
GearIn DownandLockedPosition
WithDoorsClosedandLocked- Using
Hydraulic,
Emergency
SystemInactive.
1. DoorClosedLine
2. DoorOpenLine
3. LandingGearUpLine
4. LandingGearDownLine
5. NoseGearBottle
6. ShuttleValve- NoseGear
7. UnlockActuator- NoseGear
8. NoseGearUpLock
9. NoseGearActuator
10. NoseGear
11. MainGear Bottle- Left
12. MainGear Bottle- Right
13. ShuttleValve- Left MainGear
14. UnlockActuator- Left Main
DOWN
15. LeftMainGearUpLock
16. LeftMainGearActuator
17. Left Door- ShuttleValve
18. RightDoor- ShuttleValve
19. RightMainGearActuator
20. RightMainGearUp Lock
21. RightMain- UnlockActuator
22. ShuttleValve- RightMainGear
23. LeftMainGear
24. LeftMainGearDoor
25. LeftMainGearDoorActuator
26. RightMainGearDoorActuator
27. RightMainGearDoor
28. RightMainGear
EmergencyExtensionSystemOperational
Schematic
Figure301
EFFECTIVITY:
040-999
32-30-00 Jan
PAGE
10/90 7
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extension
and Retraction(continued)
4. FunctionalProofPressureandLeakTestForEES (continued)
(k) Usingthetest cart,cyclethegearsixtimeswiththefirstcyclein the DOWNpositioninitiating
the shuttlevalveintothe hydraulic
position.Thisensuresthesystemandshuttlevalveis in the
full hydraulicmode.
(I) Retightencapon theteetest port.
(m)Performsameteston othergear.
(n) Reconnect
andrig geardoors.
(o) Functionally
test hydraulic
system.
CAUTION: THOUGHTHE GEAR IS ALREADYDOWNAND LOCKEDAFTER PNEUMATIC
EXTENSION,THE GEAR HANDLEMUSTBE MOVEDTO THE DOWN
POSITIONAND THE SYSTEMHYDRAULICPRESSUREALLOWEDTO BUILD
UP. OTHERWISE,THE PNEUMATICLINE AND THE UP LOCKHOOK
RELEASEACTUATORWILLBE FILLEDWITH HYDRAULICFLUID.
5. Testingof Emergency
BlowdownSystem
The blowdownsystem,which consistsof three individualblowdownsystems,musthave eachunit
individuallytested.
(a) Withthe airplanefirmlyjackedup,disconnect
appropriate
actuatorfromthe gearsystem
linkageto be tested.
(b) Disconnect
wiresfromsquibunitto betested. Ensurethetwosquibwiresare interconnected
with eithera U-clipor aluminum
foil.
(c) Connecta multimeter
to leadscomingfromthe aircraftsystem.
(d) Turnon masterswitch.Ensureallothergearsare lockedin the DOWNposition.
(e) Whileobservingthemeter,activatetheblowdownswitchandcheckfor proper
voltage/amperage.
6. Testingof ExplosiveValve
CAUTION: THE MINIMUMCIRCUITRESISTANCEFORTHE SQUIBIS 0.6 TO 1.2 OHMS,
BUT MAXIMUMCONTINUITYTEST CURRENTALLOWEDIS 0.01 AMPS. DO
NOT EXCEED10 MILLIAMPS.
(a) Using an ohmmeterwith a 4 1/2 digit reader,whichdoesnt exceed 10 milliamps,test squib
circuit for 0.6 to 1.2 ohms.
EFFECTIVITY:
PAGE8
Jan 10/90 32-30-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Extensionand Retraction(continued)
7. Removalof Main Gear ActuatingCylinders
(a) Placeairplaneon jacks.
(b) Disconnecthydraulicline and shuttle valvefrom actuatingcylinder. Cover open line endsto
preventcontamination.
(c) Disconnectcylinderoperatingrod end from link assembly.
(d) Disconnectattachmentend of cylinderby removingbolt securingthe cylinderand maingear up
lockcrank assembly.
(e) Removecylinderfrom wheelwell.
8. Disassemblyof MainGear ActuatingCylinders (referto 32-30-00 Figure401)
(a) Beforedisassembly,establishrod end engagementdistanceto air in preliminaryassemblyof
actuatingcylinder.
(b) Withcylinderremovedfrom the airplane,removesafety wire attachedto end cap and cylinder
body.
(c) Loosennut and removekey and rod end.
(d) Unscrewend capfrom cylinderbody.
(e) Drawpiston from cylinderbody.
9. Assemblyof MainGear ActuatingCylinders (referto 32-30-00 Figure401)
Lubricateall parts with hydraulicfluid (MIL-H-5606)priorto assembly.
(a) InstallGT-ringon piston.
(b) InstallO-ring and back up on exteriorof end cap.
(c) InstallGT-ringand scraperon interiorof end cap.
(d) Slide end cap on piston and screwend cap into piston. Torqueend cap to 65 + 15 inchpounds.
(e) Installnut and key on rod end.
(f) Adjust rod end to lengthobtainedbeforedisassembly. Referto Adjustmentof Main Landing
Gear for final adjustments.Torquenut to 85 + 15 inch-pounds.
(g) Reconnectsafetywire.
10. Installationof MainGear ActuatingCylinders
(a) Positionattachmentend of cylinderand up lock crank assemblyon their mountingbrackets.
Installattachmentbolts and secure.
(b) Connectoperatingrod end of cylinderto the gear link assembly.
(c) Connecthydrauliclinesto cylinder.
(d) Checkoperationof installationand landinggear rigging.
(e) Removeairplanefromjacks.
11. Inspectionof MainGear ActuatingCylinders
(a) Inspectcylinderinteriorwalls and piston exteriorsurfacesfor scratches,burrs, corrosion,etc.
(b) Inspectthreadedareasfor damage.
(c) Inspectrod end fittingsfor wear and corrosion.
EFFECTIVITY:
32-30-00 JanPAGE
9
10/90
CylinderBody
GT-Ring
MainGearActuatingCylinder
Figure401
PAGE 10 32-30-00
Jan10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. ExtensionandRetraction(continued)
12. Cleaningof MainGearActuatingCylinders
(a) Cleancylinderpartswitha suitablesolventanddrythoroughly.
13. Repairof MainGearActuatingCylinders
Repairsto cylinderarelimitedto polishingoutsmallscratches,burrs,replacingparts,etc.
14. Removalof NoseGearActuatingCylinders
(a) Placeairplaneon jacks. (Referto 7-10-00.)
(b) Disconnecthydrauliclines from actuatingcylinder. Cover open line endsto prevent
contamination.
(c) Disconnectcylinderoperatingrod end from link assembly.
(d) Disconnectattachmentend of cylinderby removingthe bolt securingthe cylinderand nose
gear up lock rod.
(e) Removecylinderfrom wheelwell.
15. Disassembly
of NoseGearActuatingCylinders(referto 32-30-00Figure402)
(a) Beforedisassembly,establishrod end engagementdistanceto aid in preliminaryassemblyof
actuatingcylinder.
(b) Loosennut to disengagekey. Removerod end.
(c) Cut safetywire and remove. Removenut, key, and stopfrom piston.
(d) Removesafetywire and end cap from cylinderbody by unthreadingend cap and pullingout the
piston.
(e) Slide end capfrom piston.
16. Assemblyof NoseGear ActuatingCylinders (referto 32-30-00 Figure402)
Lubricateall parts with hydraulicfluid (MIL-H-5606)prior to assembly.
(a) InstallGT-ringon the pistonhead.
(b) Installbackup andO-ringintooutsidegrooveof endcap.
(c) InstallGT-ringandscraperintoinsidegroovesof endcap. Taperlip of scraperto faceforward.
andtheboreof cylinderbody.
endcapassembly,
(d) Lubricatethepistonassembly,
(e) Slideendcapassemblyontothepistonassembly.
(f) Slidepistonwithendcap intocylinder,torquingendcapto 65 inch-pounds.Secureto cylinder
bodyusingsafetywire.
(g) Installstopandnutwithkeyon piston.
(h) Installrodendwithnutandkeyintopiston.
(i) Adjuststopforproperpistonstroke,torquingnutto 65 inch-pounds.Securebywiringnutto
keywith safetywire.
of NoseLanding
Referto Adjustment
(j) Adjustrod endto lengthobtainedbeforedisassembly.
Gearfor finaladjustments.Engagekeyandtorquenutto 85 inch-pounds.
EFFECTIVITY:
32-30-00Jan
10/90
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. ExtensionandRetraction(continued)
CylinderBody
Piston
O-Ring
BackUp
End Cap
GT-Ring
Scrapper
stop
Nut
Key
Safety Wire
Key
RodEnd
NoseGearActuatingCylinder
Figure 402
EFFECTIVITY:
PAGE12
32-30-00
Jan 10/90
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extension
andRetraction(continued)
17. Installation
of NoseGearActuatingCylinder
(a) Positionattachment
endof cylinderandup lockrodendof nosegearon mountingbracket.
Installattachment
bolt andsecure.
(b) Connectoperatingrodendof cylinderto gearlinkassembly.
(c) Connecthydrauliclinesto cylinder.
(d) Checkoperation
of installationandlandinggearrigging.
(e) Removeairplanefromjacks.
18. Inspection
of NoseGearActuating
Cylinder
(a) Inspectcylinderinteriorwallsandpistonexteriorsurfacesfor scratches,
burrs,corrosion,etc.
(b) Inspectthreadedareasfor damage.
(c) Inspectrodendfittingforwearandcorrosion.
19. Cleaningof NoseGearActuatingCylinder
(a) Cleancylinderpartswitha suitablesolventanddrythoroughly.
20. Repairof NoseGearActuatingCylinder
Repairsto cylinderis limitedto polishingoutsmallscratches,
burrs,etc,andreplacingparts.
21. Removal
of GearDoorActuatingCylinders
(a) Withmasterswitchoff,actuatehandpumphandleto bringgeardooropen.
(b) Disconnect
hydrauliclinesfromactuatingcylinder.Coveropenlineendsto prevent
contamination.
(c) Disconnect
cylinderfromthedoorandits mountingbracket.
(d) Removecylinderfromwheelwell.
22. Disassembly
of GearDoorActuatingCylinders(referto 32-30-00Figure403)
(a) Unlockcylinderby applyinghydraulicpressureto theclevisendport. Extendpistonfully.
(b) Loosenlocknutand removerodend. Removelocknutfrompiston.
(c) Removesafetywireandloosenbothknurlednuts.
(d) Removeendcapfrombarrel.
(e) Removeclevisendfrombarrel. Pullpistonwithendcapfrombarrel,beingcarefulnotto lose
anyof thesixballsnestedin theheadendof thepiston.
(f) Removeendcapfrompiston.
(g) Pullrace,plunger,andspringoutof theclevisend.
(h) RemoveGT-ringfromendcap.
(i) RemoveO-ringsandbackup ringsfrombarrel.
(j) RemoveGT-ringfrompiston.
(k) RemoveO-ringandbackup ringfromplunger.
EFFECTIVITY:
32-30-00
Jan
10/90
32-30-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extensionand Retraction(continued)
RodEnd
GT-Ring
LocknutEndCap
SafetyWire
Piston
GT-Ring
Back Up
O-Ring
Nut
Barrel
Nut
Back Up
O-Ring
Race
Ball
PlungerBack Up
ClevisEnd
)-Ring
Spring
SafetyWire
Gear DoorActuatingCylinder
Figure 403
EFFECTIVITY:
Jan10/9032-30-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Extensionand Retraction(continued)
22. Assemblyof Gear DoorActuatingCylinders (referto 32-30-00 Figure403)
Lubricateall parts with oil (MIL-H-5606)priorto assembly.
(a) InstallO-ring and back up ring into plungergroove.
(b) Installnutson barrel.
(c) Installback up rings and O-ringsinto groovesof barrel.
(d) Installspring,plunger,and race into clevis end. Secureby screwingbarrel intoclevis end.
Torquebarrel down againstthe race to 120 - 140 inch-poundsand nut against clevis end to
120- 140 inch-pounds.
(e) InstallGT-ringintogroove of piston.
(f) InstallGT-ringintogroove insideend cap.
(g) Slide piston into end cap. Installsix balls into holesin pistonhead and insertassemblyinto
boreof barrel. Screw end cap onto barreland alignport in end capwith port in clevis end.
Tightennut againstend cap and torqueto 120 - 140 inch-pounds.
(h) Securenut to end cap using safetywire.
(i) Securenut to clevis end using safetywire.
(j) Installlocknutand rod end on piston.
(k) Adjust rod endfor properlengthof actuatorassemblyand lock with locknut.
23. Installationof Gear DoorActuatingCylinders
(a) Positioncylinderon its mountingbracket. Securewith attachmentbolts.
(b) Extendcylindercontrolrod enoughto attachrod end to door. Securewith attachmentbolt.
(c) Connecthydraulicline to cylinder.
(d) Tobring gear door backto the closedposition,set masterswitchON. Placegear leverin the
DOWNpositionand actuatethe handpump until the door closes.
24. Inspectionof Gear DoorActuatingCylinders
(a) Inspectall threadedsurfacesfor cleanliness,cracks,and excessivewear.
(b) Inspectplungerspringfor breaks and distortion. Compressspringto a lengthof 0.750 inches
and measureload. Load shouldbe 30 ± 2 pounds.
(c) Inspectend cap, piston,barrel, race, plunger,and clevis end for cracks,chips,scratches,
scoring,wear,and surfaceirregularitieswhichcould affectfunctionof door actuatorcylinder.
25. Cleaningof Gear DoorActuatingCylinders
(a) Cleancylinderparts with a suitablesolvent;dry thoroughly.
26. Repairof Gear DoorActuatingCylinders
(a) Replaceall defectivelandinggear actuatorassemblyparts with new parts.
(b) Minorscratchesand scorescan be removedby polishingwith fine abrasivecrocuscloth
(FederalSpecificationP-C-458)providingtheir removaldoes not affectoperationof actuator
assembly.
(c) Replaceall O-rings,backup rings,and GT-ringswith new onesduring reassemblyof actuator.
EFFECTIVITY:
32-30-00Jan
Jan 10/90
10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Wheel Assemblies
NOTE: Referto vendor publicationslist for B. F.Goodrichmanual.
1. Fault Isolation- WheelAssemblies
NOTE: Place airplaneon jacks beforeattemptingfault isolationof landinggear system (refer to
7-10-00).
CHART 1
FAULT ISOLATION (WHEEL ASSEMBLIES)
Fault
Cause
Nose gear shimmies
during fast taxi, takeoff
and landing.
Mainlandinggear
shimmiesduringfast
taxi, takeoff and landing.
Excessiveor uneven
wear on maintires.
Remedy
Tire out of balance.
Checkbalanceand replace
tire if necessary.
Worn or loose wheel
bearings.
Replaceand / or adjustwheel
bearings.
Tire out of balance.
Checkbalanceand replacetire
if necessary.
Worn or loose wheelbearings.
Replaceand / or adjustwheel
bearings.
Incorrectoperatingpressure.
Inflatetire to correctpressure.
Wheelout of alignment
(toe-inor toe-out).
Checkwheelalignment.
EFFECTIVITY:
040-999
32-40-00
32-40-00 Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Wheel Assemblies (continued)
2. Removaland Disassembly
of B.F.Goodrich3-1392MainWheel (referto 32-40-00Figure401)
(a) Placeairplaneon jacks (referto 7-10-00).
(b) Putparkingbrakeon to holdthebrakeassemblydisc-carrier
in position.
(c) Removewireretainingring,hubcap,cotterpin,andaxlenut.
(d) Removewheelfromaxle.
(e) Releaseall air outof tireby depressing
andremoving
valve.
(f) Thetirebeadmustbe brokenfromwheelflangeusinga mallet,beadbreaker,pneumatic
tire
dismounter,
or otherapplicable,
non-metallic
instrument.
CAUTION: DO NOT PRY BETWEENWHEELAND BEADWITH SHARPTOOLSWHICH
COULD DAMAGEWHEELAND TIRE. DO NOT USE POWEROR IMPACT
WRENCHESTO REMOVEWHEELBOLTSOR NUTS.
(g) Removeeighttie-boltsandwashersfromwheel;separatethehalves.
(h) If wheelhalvepackingO-ringis to be reused,markpositionto reinstallascloselyas possible.
(i) Toremovebearingcups,heatwheels(explained
in Repairof MainWheelAssembly)
andafter
coolingcupsevenly,drivethemoutof theirwheelhalveswitha non-ferrous,
soft metal,or
non-metallic
driftpin. If possible,use an arborpress.
3. Assemblyand Installation
of B.F.Goodrich3-1392MainWheel(referto 32-40-00Figure401)
NOTE: Wheninflatingtireson BFGwheels,allowassemblyto standat least12hoursfortire
andwheelto stabilize.
(a) Retreating
andRepainting.
(1.) Thoroughlyclean repairedsurfacesand areasof the wheelwhere paint hasbeen
removed.
(2.) Treat cleanedsurfaceswith DowNo. 1 solution(MIL-M-3171).Paintwith one coat of zinc
chromateprimer (specificationTT-P-1757)and one coat of aluminumpolyurethanepaint.
NOTE: Neverpaintworkingsurfacesof bearingcups. Thewheelregistersurfacesand
boltbossesmustreceiveonlyonemistcoatof zincchromateprimer.
(b) Placetheinnerwheelhalfon a cleanflatsurface.Withthe matingflangeup,placethepacking
O-ringontoits register,positioningit as closeaspossibleto its originalpositionif the O-ringis
reused.
(c) Installtireandouterwheelhalf respectively
on theinnerwheelhalf. Besureto properlyalign
themaleandfemaleregisters,whereapplicable.
(d) Installwashersandconnecting
bolts. Staggertorquethem190- 210inch-pounds.
(Lubetorque)
NOTE: Aftertorquingis completed,retorqueboltsa secondtime,ensuringpropertorqueis
achieved.Compression
of thepackingO-ringcausesthe initialreadingto befalse.
EFFECTIVITY:
2
PAGE
Jan 10/9032-40-00
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Wheel Assemblies (continued)
Packing Ring
Screw
NOTE: At eachtirechange,Visuallyinspectwheel
halvesfor corrosion,especiallynotingbeadseat
area(tirecontactsurface)andtiretie boltholes.
Removecorrosionwith400gritemeryclothand
touchup withDowNo. 19solutionor equivalent,
Primealltreatedareaswithonecoatof
uerethane
primer.Baremagnesium
is silverin
color.Theprotectivefinishputon wheelhalves
at thefactoryis goldin color.(DowNo.7 or
IriditeNo. 15).If corrosioncannotbe removed
by sandingdownto baremetalwithinlimits
specifiedin32-40-00Figure402,takewheel
halfoutof service
Lockwire(MS2099C32)
View A
InnerWheelHalf
Torque Key
View B
ApplyMIL-T-5544
Compound
To TheseSurfaces
B. F. Goodrich 3-3192 Main Wheel Installation
Figure 401
EFFECTIVITY:
040-999
32-40-00
32-40-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies(continued)
of B.F.Goodrich3-1392MainWheel(referto 32-40-00Figure401)
3. Assemblyand Installation
(continued)
(e) If theair valveis removed,installandtorqueto 35 - 65 inch-pounds.
(f) Withthevalvecoreremoved,inflatetireenoughto seatthetire beadsagainstthewheel
flanges.
(g) Installthevalvecoreandinflatetireto 110psi. If tireis new,proceedto step(h). If tireis used,
proceedto step(i).
(h) Letinflatedtirestandfor 12to 24 hoursandcheckfor normal10%pressureloss. Reinflate
tire,brushwateror soapsolutionoverexteriorof tire,andinspectfor leaks.
NOTE: Bubbleformationaroundsidewallventsontire is normalduringwateror soapsolution
test.
a readingof 105- 110psi.
Ensuretire pressureafter24 hoursindicates
(i) Brushwateror soapsolutionoverexterioroftireandcheckfor leaks.Checktirepressureafter
24 hoursfor a readingof 105to 110psi. If pressurelossexceeds5 psi,checktirefor damage
andrepairor replace,asnecessary.
NOTE: Applygreasesparingly.Do notfully lubricate.
(j) Pack the bearing cones. Coat the bearingcups and inboardseal lip with bearinggrease
(MIL-G-3545).
CAUTION:
USE CARE WHEN INSTALLING THE WHEEL ASSEMBLY TO PREVENT
DAMAGING THE BEARING CONES, RACES, AND SEALS.
(k) Installwheelsasfollows:
(1.) Installthegreasesealandinboardbearingconeontothe axle.
withthewheel,carefullyplacethewheelovertheaxleuntil
(2.) Whilealigningthe disc-carrier
the wheelraceengagestheinboardcone.
(3.) Installtheoutboardbearingandtorquetheaxlenutto 50 foot-pounds.
andwhilerotatingthewheel,retorqueto 25 foot-pounds.
(4.) Loosenthe nutto 0 foot-pounds,
NOTE: If, aftertorquingtheaxlenut,thecotterpincannotbe installed,advancethenut
an additional30 degreesto alignthesafetyholes.
(I) Installbearingcupandretainingplug.
EFFECTIVITY:
040-999
4000
Jan 10/9032-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. WheelAssemblies (continued)
4. Inspectionof MainWheel Assembly
(a) Visuallyinspectbearingcupsand conesfor damageand wear. Be carefulnot to handle
bearingswith bare hands.
(b) If the paintedsurfacemustbe removed,be sure not to removethe magnesiumsurface
treatment. Abrasiveblasting,using groundwalnut hulls. (MIL-G-5634,Type II or IIIis
suggestedbecauseit does not removesurfacetreatmentand requiresmaskingor removalof
bearingcup.) Referto manufacturer'sservicemanuallist in front of manualfor appropriate
surfacetreatment.
(c) Inspectwheel halves,tie bolts, and other necessaryhardwarefor cracks,adversedistortion,
and corrosion. The followingprocedureshouldbe accomplishedafter the fifth and third
subsequenttire change,for a total of twentytire changesand at eachtire changethereafter:
(1.) Inspecteachtie bolt for magneticparticleand torquekey (MIL-1-6870- longitudinal
magnetization)for fatigueand crack indications. Replaceas necessary,especiallytorque
keys worn to lessthan 0.060 inchthickness.
NOTE: Becausedye checkingcan stain the wheel,use it only in the tube well, especially
the bead set radius,wherethe tire bead heelscontactthe wheel.
(2.) With dye-checkor fluorescentpenetrant,inspectthe bead seats, tube well, and especially
the web junctionareas.
(d) Inspectall areas for nicks. For repairlimitsof the BF Goodrichwheel,refer to 32-40-00 Figure
801. Small nicks or gougesin castingmust be blendedout and polishedwith 400 grit abrasive
paperor emery cloth. Blendedareas mustsurrounddamageby 1 1/2 inch.
(e) InspectO-ring seatingareas for nick or distortion. BadlydistortedsectionshamperO-ring
sealingcharacteristicsand requireswheelhalf replacement.
(f) Inspectsnap rings and grease sealsfor distortion. Replacegrease sealfits if badly wornor
contaminated.
(g) Overheatedwheel halvesmust be inspectedfor BrinellHardness. Checkhardnesson wheel
halve flangeareas by contactingthe manufacturerfor appropriatehardnessvalue.
5. Cleaningof MainWheelAssemblies
(a) Clean and degreasebearingsand all metalparts; dry thoroughly.
CAUTION: DO NOT USE CLEANINGSOLVENTSTO CLEANRUBBERPARTSOR SPIN
DRY BEARINGS.
(b) Areaswherethe protectivecoatinghasbeen removedor showslight corrosionmustbe
thoroughlycleanedand repaintedwith one coat of urethaneprimerand one coat of aluminum
polyeurethane.
NOTE: Neverpaint bearingcupworkingsurfaces.
(c) Lightlysaturatenewor reusedgreaseseal felts with SAE 10 oil before installation.
NOTE: Do not soak grease sealfelts with oil.
EFFECTIVITY:
040-999
PAGE
5
32-40-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies (continued)
NOTE: Fordetailedrepairprocedures,
referto B.F.G.Manual.
- B
Theboltholesmaybe reamed
to 0.345max.dia.typicalof
bothwheelhalves. 0.040radius
or chamferbothsides
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies (continued)
6. Repairof Main WheelAssemblies (referto 32-40-00 Figure 801)
Repairsto the mainwheel assemblyare limitedto blendingout small nicks,scratches,gouges,
areas of slight corrosion,and replacingof parts which are crackedor badly corroded.
NOTE: At eachtire change,visuallyinspectwheel halvesfor corrosion,especiallyat the bead
seat area(tire contactsurface)and tie bolt holes. Corrosioncan be removedwith 400
grit emery cloth and touchedup with Dow No. 19 solutionor equivalent. Primeall
treated areas with one coat urethaneprimer. A protectivefinish is put on wheelhalves
at the factory. If corrosioncannotbe removedby sandingdown to bare metalwithin
limits (shownin 32-40-00 Figure 801 for BFG wheel),wheel half mustbe taken out of
service.
7. Replacementof Wheel BearingCup
(a) Removebearingcup as follows:
(1.) Heat wheel sub-assemblyin boilingwaterfor 30 minutesor in an oven not exceeding
80°C (150°F)for 20 minutes.
(2.) Removesub-assemblyfrom heat and removebearingcup.
NOTE: The bearingcup mustbe looseenoughto fall out of bearingboreafter heatingthe
wheel sub-assemblyand invertingit. If the cup does not drop out, use an arbor
pressor tap evenlyfrom the borewith a fiberdrift pin. Be careful not to damage
wheelhalf.
(b) Installbearingcup as follows:
(1.) Placewheel sub-assemblyin boilingwaterfor 30 minutesor in an oven not exceeding
149°C (300°F)for 30 minutes. Chill bearingcup on dry ice.
(2.) Removewheel halffrom heatsource. Dry chill bearingcupthoroughly. Coatcontacting
surfacesof cup with zinc chromateprimeror paste.
(3.) Installchilledbearingcup into heatedwheel sub-assembly.Tap intoplace evenlywith a
fiber drift pin.
NOTE: The bearingcup mustbe installedwhile the primeror paste is still wet.
EFFECTIVITY:
040-999
32-40-00Jan10/90
PIPEF AIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies(continued)
8. RemovalandDisassembly
of NoseWheel(B.F.Goodrich)(referto 32-40-00Figure402)
(a) Placeairplaneon jacks (referto 7-10-00).
(b) Todismountnosewheel,removeaxlenut,andboltandaxleplugs.Taptheaxleoutof the
wheelassemblyandforkusinga 1 7/16inchODtube.
(c) Flexforkenoughto allowthewheelandwheelspacersto cleartheforkassembly.
(d) Todisassemble
thewheel,deflatethetireandbreaktire beadsawayfromtheflangesby
pressingwith heelsof the handsor a tirepress.
(e) Removenuts,washers,andtie boltsfromthewheel.Separatewheelhalves,removethetire,
and removethevalvestemassembly,
if installed.
NOTE: Bearingcupsarepressfittedintothewheelhalvesandmustnot be removed,
unless
replacement
is necessary.If cupsareto be replaced,heatwheelhalfto 275° to 300°F
andpressoutthecupswitha plug. Supportwheelhubwhileremovingcups.
(f) Thewheelbearingandsealareremovedbytappingoutevenlyfromthe insidewitha brass
drift. Becarefulnotto damagethebearingcage.
Bearing
Grease
WheelHalf
Bearing
Seal
Retainer,
Grease
Seal
-Retainer,
Grease
Seal
WheelHalf
Grease
Nut
Seal
NoseWheel Assembly (B. F. Goodrich3-1076)
Figure 402
EFFECTIVITY:
PAGE
8
Jan 10/9032-40-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies (continued)
9. Assemblyand Installationof NoseWheel (B. F.Goodrich) (referto 32-40-00 Figure402)
(a) If cups are removed,reinstallas follows:
(1.) Heatwheelhalvesto 275° to 300°F.Coolcupsto 0°F.
(2.) Supportwheelhub,painttheinsidediameterof thehubwithzincchromateprimer,and
pressthecupsintothewheelhalf.
NOTE: The wet zinc chromateprimer lubricatesparts to be pressedtogetherand assists
in preventinggalvaniccorrosionbetweenparts.
(b) Reinstallvalvestemand balanceweightsif removed.
(c) Lubricatepackingwith grease (MIL-G-3545Cor equivalent). Installin the wheel halfpacking
groove.
(d) Installtire and join the two wheel halves. Apply a generous coat of thread component
(MIL-T-554)to threads of bolts, faces of washers, and bearing face of nuts. Using the
sameprocedure, retighten all nuts and torque to specificationgiven on the wheel.
NOTE: Do not use an impactwrenchto applyfinal torque. Use a preset handtorque wrench
only.
(e) Inflatetire (referto 6-00-00. Chart 1) and test for leakage.
(f) Repackwheelbearingswith grease (MIL-G-3545C)and lubricatecups. Placebearingsin
wheelassembly. Installgrease seals.
(g) Installwheel and spacersin fork and insertaxle. Referto parts catalogfor properspacers
requiredfor particulartire installed.
(h) Adjust axle bolt to allow wheelto turn freely with no side play.
10. Inspectionof Nose WheelAssembly (B. F.Goodrich)
(a) On the bolt head radiusor shank,magnafluxbolts for cracks,breaks,and surfaceblemishes.
(b) Inspectwheel halvesfor cracksand breaks(particularlythe bead seat,tube well, andweb
junctionareas)with dye checkor Zyglo.
(c) Visuallyinspectall metalpartsfor pitting,corrosion,cracks,breaks,unevenwear,and other
surfacedefects.
(d) Inspectpackingsealingsurfacesfor smoothness.
(e) Inspectpackingfor pits, cuts, and other defects. Replaceas necessary.
11. Cleaningof NoseWheel Assembly (B. F.Goodrich)
(a) Cleanmetalparts in solventand air dry thoroughly.
(b) Cleanrubberpartsby wipingwith a clean, lint-freecloth.
EFFECTIVITY:
040-999
32-40-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies(continued)
12. Repairand Replacement
of NoseWheelAssembly(B. F.Goodrich)
(a) Repairscratches,nicks,andotherminorsurfaceblemishes
on thewheelhalvesby sanding
withemerycloth;removeas littlemetalaspossible.Polishandsurfacetreatrepairedsurface
withDowNo.7.
NOTE: Do not removemorethan 0.020 inch beloworiginal surfacefor generalblending.
(b) Paint repairedsurfaceswith two coats zinc chromateprimerand one coat aluminumlacquer.
NOTE: Useonlyonecoatof zincchromate
primerandusenofinishcoaton matingsurfaces
andthepackinggroove.
(c) Replaceall partscontainingvisiblecracks.Replacepartsthataredamagedbeyondrepair.
(d) Replacepackingandgrommetat eachoverhaul.
13. RemovalandDisassembly
of NoseWheel(Cleveland)(referto 32-40-00Figure403)
(a) Placeairplaneon jacks (referto 7-10-00).
(b) Toremovethe nosewheel,removeaxletie rodandtie rodaxleplugs. Inserta 1-7/16inch
diametertube intothefork. Tapout axlefromwheelassembly.
(c) Flexforkenoughto removethewheelsspacers.Allowthewheelto cleartheforkassembly.
(d) Thewheelhalvesare separated
bydeflatingthetireandremovingthesixwheelbolts. Pullthe
wheelhalvesfromthetire byremovingthewheelhalfoppositethevalvestemfirstfollowedby
theotherhalf.
Grease
Seal
Bearing
Cup
Bearing
Cone
Bearing
Cup
WheelHalf
WheelHalf
Bearing
Cone
Bolt
Grease
Seal
NoseWheelAssembly(Cleveland40-140)
Figure403
EFFECTIVITY:
040-999
Jan
10/90
32-40-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. WheelAssemblies(continued)
of NoseWheel(Cleveland)(referto 32-40-00Figure403)(continued)
13. RemovalandDisassembly
the snaprings
areremovedfromeachwheelhalfbyremoving
(e) Thewheelbearingassemblies
the retainers,
greaseseals,andbearingcones.The
securingthegreasesealretainers,
andcanbe removedbytappingoutevenly
bearingcupsmustbe removedonlyfor replacement
fromthe inside.
of NoseWheel(Cleveland)(referto 32-40-00Figure403)
14. AssemblyandInstallation
(a) Ensurebearingcupin eachwheelisproperlyinstalled.
(b) Installtireandjointhetwowheelhalves.
listedon
(c) Insertthroughboltswithnutsto wheelstemsideandtorqueboltsto specifications
wheel.
(d) Inflatetireto 80 psi. If tireis new,proceedto step5. If tireis used,proceedto step6.
(e) Letinflatedtirestandfor 12to 24 hoursandcheckfor normal10%pressureloss. Reinflate
tire,brushwateror soapsolutionoverexteriorof tireandinspectfor leaks.
NOTE: Bubbleformationaroundsidewallventson tireis normalduringwateror soapsolution
test.
(f) Ensuretirepressureafter24 hoursindicatesa readingof 76 - 80 psi. Ifpressurelossexceeds
4 psi,checktirefor damageandrepairor replace,as necessary.
(g) Lubricatebearingconesandinstallcones,greaseseals,andsealretainerrings. Securewith
snaprings.
Trainer)
(Advanced
(h) Flexforkenoughto installwheelandspacertubes. Referto PA-42-720
IllustratedPartsCatalogforproperspacersrequiredfor 80 psitire.
(i) Insertaxletube,forkcapsandtie bolt. Adjusttie boltnotto allowwheelto turnfreely,buttight
of wheel.
enoughto preventlateralmovement
15. Inspection
of NoseWheelAssembly(Cleveland)
wear,andcorrosion.
defects,excessive
(a) Visuallycheckall partsfor cracks,distortion,
or failure.
(b) Checktie boltsfor looseness
(c) Checkinternaldiameterof feltgreaseseals. Replacethefelt greasesealif surfaceis hardor
gritty.
(d) Checktire forcuts,internalbruises,anddeterioration.
(e) Checkbearingconesandcupsforwearandpitting;relubricate.
(f) Replaceanywheelcastingwithvisiblecracks.
EFFECTIVITY:
32-40-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies
1. Descriptionand Operation- Brakes
Thebrakesare hydraulically
actuatedbyindividualmastercylindersmountedon theleftandright
setsof rudderpedals.Thebrakereservoirisaccessible
throughan accessdooron theupperright
portionof the nosesection.
Forfurtherinformation
onservicingof brakes,referto frontof manualfor vendorpublications
list.
2. Fault Isolation- Brakes
CHART 2
FAULTISOLATION(BRAKES)
Fault
Hydraulicfluidleaking
frompistonarea.
Fluidleakingfrom
bleedervalvesor
reducerfitting.
Insufficientclearance
(i.e. DISKCANNOTBE
MOVEDWITH HANDS).
Cause
Remedy
Wompacking(s).
Replacepacking.
Damaged
piston(s)or
pistonbore(s).
Replacepistonor repair
bore.
Loosebleedervalve(s).
Tightenbleeders.
Damaged
bleedervalve.
Replacevalve.
Damagedreducerfitting
or packing.
Replacereduceror packing.
Heatstackwarpedbeyond
tolerance.
Repairor replacepartsoutof
toleranceperREPAIR.
Airin system.
Properlybleedbrakesystem
andhydrauliclines.
EFFECTIVITY:
32-40-00
PAGE12
Jan10/9032-40-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
3. RemovalandDisassembly
of BrakeandDisc- CarrierAssembly(referto 32-40-00Figure404)
(a) Placeairplaneon jacks (referto 7-10-00).
(b) Removeappropriate
wheel.
(c) Ifonlyremovalor inspection
ofthe lininganddisc-carrier
assemblyis required,proceedwith
thefollowinginstruction;
proceedto step(d)for entirebrakeassemblyremoval.
(1.) Makesureall hydraulicpressureis off brakes.
(2.) Removetenanchorboltsretaining
pistonhousingassemblyin alignment
withthebrake
torqueplate. Becarefulnotto letthedisc-carrier
andspacerplatedropoutandbe
damaged.
Piston
Housing\
- Piston
Tapped
Hole
ApplyMIL-T-5544
Compound
ToTheseSurfaces
ViewA
LubetorqueRequirement
ViewB
CorrectPistonInstallation
NOTE: ForfurtherInformation
on servicingB.F.G.Brake,referto the manufacture's
servicemanual
for the2-1435-2brake.
B. F. Goodrich Brake Installation
Figure 404 (Sheet 1 of 2)
EFFECTIVITY:
32-40-00JanPAGE
13
10/90
PIPER AIRCRAFT
PA-42 720 (Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
Piston Housing
Max.
Carrier Lining and
Torque Button Assembly
B. F.Goodrich Brake Installation
Figure 404 (Sheet 2 of 2)
3. Removaland Disassemblyof Brakeand Disc - CarrierAssembly (referto 32-40-00 Figure 404)
(continued)
(3.) Makesurethepistonhousingandhydrauliclinesare notdamaged.Removesixtorque
boltsfasteningthe braketorqueplateto the axletorqueplate.
(4.) Withdrawbraketorqueplateanddisc-carrier
fromtheaxle.
(5.) Inspectliningsanddisc-carrier
forexcessivewear,scoring,corrosion,
warpage,and
gritcarbideor
hand
using
a
medium
be
removed
by
cracks. If possible,corrosionmust
wet/drysandpaper.
CAUTION: BE SURETO CLEANOFFTHE DISC-CARRIERAND ALL LININGAFTER
WORKINGON THESEPARTS,PREVENTINGANY CHANGEOF SCORING
AFTER REASSEMBLY.
thebrakedisc-carrier.If anypartof the
(6.) Inspectgroovedareasofthe wheelaccepting
corroded,replacethewheelhalf.
castingiscrackedor excessively
WARNING: BE SURE TO RELEASEALL AIR PRESSUREBEFOREDISMANTLING
ANY WHEEL.
(7.) Anysmallnicksor gougesmustbe blendedoutwith400gritcarbidepaper(wet/dry).
with onecoatof
cleanedandrepainted
Areasexhibitinglightcorrosionmustbe thoroughly
paint.
aluminum
polyurethane
one
coat
of
zinc chromateprimerand
housinganchorboltsfor cracks,corrosion,andthread
(8.) Inspectthetorqueplate/piston
damage.Replaceif necessary.
EFFECTIVITY:
040-999
Jan 10/9032-40-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
3. Removaland Disassemblyof Brakeand Disc - CarrierAssembly (refer to 32-40-00 Figure 404)
(continued)
(d) Toremoveentirebrakeassembly,
proceedasfollows:
(1.) Besurenopressureexistsin thebrakesystem.Removeandcapthe hydraulic
brake
lines.
(2.) Removesix highsheartorquebolts.Withdrawthebrakeassembly.
4. Assembly
and Installation
of BrakeandDisc- CarrierAssembly(referto 32-40-00Figure404)
(a) If pistonhousing,disc-carrier,
spacerplate,andtorqueplatehavebeenassembled,
proceedas
follows:
(1.) Lay piston housingassemblyon a clean, flat surfacewith the pistonhousing'sopen side
up.
(2.) Installcarrierswith liningson their pistons.
(3.) Lay disc-carrierassemblyover and liningsonto the piston housing.
(4.) Withcarriers and liningsinstalledon torqueplate, align spacerplateon piston housing
and installtorque plate onto piston housingwith anchor bolts.
(5.) Lubetorquethe anchor boltsto 350 - 370 inch-pounds.
(b) Withthebrakeassembled,
positionpistonhousingtowardthe inboardsideof thegearwiththe
openendup. Installbrakeassembly
torqueplateontotheaxletorqueplateusinghighshear
torquebolts.Torqueto 170± 10inch-pounds.
(c) Reconnect
hydrauliclinesandbleedbrakes.
(d) Reinstallwheelbyslowlyslidingit overthe axle. Alignthebrakedisc-carrier
teethwithslotsin
thewheel.
(e) Installaxlenutensuringthebearingsareseatingproperly.(Referto 32-40-00Assemblyand
Installation
of MainWheel.)
EFFECTIVITY:
32-40-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies (continued)
5. Inspectionof BrakeAssembly
(a) InspectO-ringsfor nicks,distortion,or excessivewear. Replaceas necessary.
6. Cleaningof BrakeAssembly
(a) Except for disc-carriersand liningassemblies,cleanall metalparts with a Stoddardsolventor
suitableequivalent.
(b) Removeand clean O-ringswith denaturedalcohol;dry thoroughly.
(c) If the finish on torque plateor housingassemblyneedsrefinishingor removal,use the following
instructionsto removeold paintfrom metalsurfaces.
NOTE: It is not necessaryto strippaint on assemblyto inspectusingdye-checkor fluorescent
penetrant.
7. BrakeWear Limits (referto32-40-00 Chart 3)
BREAKWEAR LIMITS
CHART 3
InspectionAreas
Disk Carrierand
Linign Assembly
Carler, Lining and
Torque Button Assys
Thickness
Max.
Min.
0.519
*0.370
0.265
*0.160
Dishing
(Flatness)
Max.
Min.
0.050
0.000
+0.025
0.000
I.D.
Max.
Min.
7.000
6.800
7.000
6.800
*Minimumthicknessis 85 percentof liningsurface. This is an overhaullimit only.
Parts maywear beyondthese dimensionsin service.
+Carrier,lining,and torque button assembliescan be coldflattenedwith a malletand
flat plate. Checkflatnesson liningside of segment.
In order to preventprematureremovaland subsequentoverhaulof brakesstill serviceable,B. F.
Goodrich hasestablisheda brake removalwear limit (BFGS/B 399) checkprocedure. Proceedas
follows:
(a) Pressurizebrake to 100 psi.
(b) Measuredistancebetweenthe carrier. Line and torquebutton assemblyand the piston
housing(referto 32-40-00 Figure 404). (A 0.350inch measurementindicatesbrake needsto
be overhauled.)
EFFECTIVITY:
040-999
10/9032-40-00
PAGE
Jan 16
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies (continued)
8. Removalof BrakeMasterCylinder (referto 32-40-00 Figure 405)
(a) Ensureall hydraulicpressureis off the brake systemand parkingbrake is off.
(b) Disconnectand cap brake lines from the affectedcylinderto preventcontaminationof system.
(c) Removebolt connectingboss end of braketo its fitting or channelassembly. Removethe bolt
connectingbrake rod end bearingto pedalattachingarm.
(d) Removecylinderfrom aircraft.
9. Disassemblyof BrakeMasterCylinder (referto 32-40-00 Figure 406)
(a) Internalparts of brake mastercylinderare removedby removingthe snap ring fromthe annular
slot at the lower endof the cylinder. Pullcompletepiston assemblyfrom cylinder.
(b) Slidethe packinggland,O-ring, washer,and springfrom piston rod.
(c) Thepiston valveassemblyis removedby taking off the self-lockingnut from the pistonrod,
allowingthe pistonwith componentpartsto be removed.
10. Assemblyof BrakeMasterCylinder (refer to 32-40-00 Figure 406)
(a) InstallO-ring on cylinderpiston and assemblethe piston,spring,washerseal, and valveonto
the piston rod. Allowthe valveto extendinto the baseof the piston. Slidethe O-ring and
washer in place. Securewith self-lockingnut.
(b) InstallO-ring sealon packinggland and slide spring,washer,O-ring,and packingglandonto
pistonrod.
(c) Dip piston assemblyin hydraulicfluid (MIL-H-5606)and install assemblyinto cylinder. Push
packinggland intocylinderuntil snapring can be installedintothe annularslot at the bottomof
cylinder.
11. Installationof BrakeMaster Cylinder (refer to 32-40-00 Figure 405)
(a) Compresspistonwithincylinder. Adjust rod end bearingso the total length(referto 32-40-00
Figure 406).
(b) Withcylinder portstowardsthe front of the aircraft,mount boss end of mastercylinderto the
fittingconnectingthe cylinderto its supportassembly.
(c) Connectrod end bearingto its rudderpedalcontrolarm.
(d) If brake pedalis out of alignmentwith otherpedals,adjust by disconnectingthe rod end in or
out, whicheveris required.
(e) Removecaps from hydrauliclines. Reassemblelines with supplyline attachedto the upper
port and pressureline attachedto the lowerpart.
(f) Bleedbrakesand ensure no sponginessexistsin the operationof the brakes.
(g) Put on the parkingbrake and checkall lines,ensuringno leaksor spongy lines exists.
EFFECTIVITY:
32-40-00 Jan10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
B. Brake Assemblies (continued)
ReferTo Following
PageFor Specific
CylinderAssembly
Installation
Pressure
Bulkhead
Master Cylinder Support Channel
Rudder Pedal Arm
Assembly (Pilots Left)
Push Rod from
Left RudderPedal
10-23 Master
Cylinder
Rudder Pedal
Rudder Pedal Bellcrank Assembly
Push Rod to RudderCable Control Sector
Master Cylinder Installation
Figure 405 (Sheet 1 of 2)
PAGE
18 32-40-00
Jan10/90 32-40-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
10.63"
Pilot's Right
Brake Cylinder
10.63"
Copilot'sLeft
Brake Cylinder
10.36"
Copilot's Right
Brake Cylinder
10.11"
Pilot'sLeft
BrakeCylinder
MasterCylinderInstallation
Figure 405 (Sheet2 of 2)
EFFECTIVITY:
040-999
32-40-00Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
6.38"
Master CylinderAssembly
Figure 406
12. Inspection
of BrakeMasterCylinder
burrs,corrosion,etc.
(a) Inspectinteriorwallsof cylinderfor scratches,
(b) Inspectgeneralconditionof cylinderfittingthreads.
burrs,corrosion,etc.
(c) Checkpistonandvalvefor scratches,
13. Cleaningof BrakeMasterCylinder
(a) Cleancylinderpartswith a suitablesolventanddrythoroughly.
14. Repairof BrakeMasterCylinder
burrs,etc.
(a) Repairsto cylinderarelimitedto polishingoutsmallscratches,
(b) ReplacevalvewashersealandO-rings.
4000
32-40-00
Jan
Jan10/9032
10/90
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies (continued)
15. Removalof ParkingBrakeValve
(a) Disconnectparkingbrake cable from valveactuatingarm.
(b) Disconnectfluid lines from valve.
(c) Removescrewsattachingvalveto its mountingbracket.
(d) Cap line openingsto preventcontaminationof system.
16. Disassemblyof ParkingBrakeValve (refer to 32-40-00 Figure 407)
(a) Removetwo fittingsfrom outsidethe valve body. A valve springis held in place by the fittings.
Do not loosenthesewhen removingthe fittings.
(b) Fromvalve body,removethe valvespring and valve.
(c) To removevalvecam, removethe nut, washer,bushingand spring. Pull camfrom valvebody.
Bushing
Parking BrakeValveAssembly
Figure 407
EFFECTIVITY:
040-999
32-40-00 Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
15. Assemblyof ParkingBrakeValve(referto 32-40-00Figure407)
(a) InstallO-ringson valvecam.
(b) LubricateO-ringswith hydraulicfluid(MIL-H-5606),
insertcamintovalvebodyandsecurewith
spring,bushing,washer,andself-locking
nut.
(c) InstallO-ringon valve,insertvalvein theoutporthole,installvalvespring,andsecurewith
outletfitting.
16. Installation
of ParkingBrakeValve
(a) Attachvalveto bulkheadmountingbracketwithscrews.
(b) Connectfluidlinesto valve.
(c) Connectcontrolcableto valvelever. Ensurewhenvalveleverfits in thecloseddetent,parking
brakehandleis 0.062to 0.125inchof beingfullyin againstthestop.
(d) Bleedbrakesystem(referto 32-40-00BleedingProcedure).
17. Inspectionof ParkingBrakeValve
(a) Inspectcamandseatvalvebodysurfacesfor excesswearandcorrosion.
(b) Inspectcamassemblyfor burrs,scratches,excesswear,looseoperatinglever,etc.
(c) Checkgeneralconditionof valvesandspring.
18. Cleaningof ParkingBrakeValve
(a) Cleanvalvepartswitha suitablesolvent.
(b) Drythemthoroughly.
19. Repairof ParkingBrakeValve
Repairto valveis limitedto smoothing
burredor scratched
surfacesandreplacingO-rings.
20. BleedingProcedure(referto32-40-00Figure601)
Ifbrakesystemhasbeendrained,hashadpartsreplaced,or hadhadanylineconnection
broken,
bleedit as follows:
(a) Placea suitablecontainerat thereservoirto collectfluidoverflow.
(b) Removerubberbleederfittingcaplocatedon landinggearbrakeunithousing.
(c) Slidepressurehosefrompressurepotoverbleedervalve.
(d) Pressurize
thepressurepotto 48 ± 2 psi. Openthebleedervalve.
NOTE: Bywatchingfluidflowingintothe reservoir,
determine
whetheranyair hasenteredthe
system.If air bubblesareevident,continuefillingthesystemuntilall air is outof the
systemanda steadyflowof fluidisobtained.
(e) Allowat least2 gallonsto flow.
(f) Simultaneously
depresspilot'sbrakepedalsapproximately
1 inchin successive
motions.
Returnto neutralforcinganybubblesin thesystemdownstream.Repeatwithcopilot'sbrake
pedalsuntilno air is expelledat reservoir.
(g) Closebleedportsanddepressurize
system.
Jan 10/9032-40-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
Catch
Tank
(5-Gallon)
Airplane
Reservoir
Copilot'sBrake
MasterCylinder
Right
Left
Pilot's Brake
MasterCylinder
BleedPort
Dual Parking
Brake Valve
(Open)
BleedPort
t
Brake
Bleeder
(FillWith
MIL-H-5606A)
Regulator
Shop
Air
BleedingBrakes
Figure 601
EFFECTIVITY:
040-999
32-40-00
PAGE
23
10/90
Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
B. BrakeAssemblies(continued)
20. BleedingProcedure(continued)
(h) Checkbrakesfor properpedalpressureandoperation.
NOTE: If properpedalpressureisnotattained,repeatprocedure.
(i) Repeatprocedure
on theothergear.
(j). Servicebrakereservoir(referto 12-10-00).
C. Tires
Referto Tires, 12-10-00 for air replenishingprocedures
For balancingtires, use tire balancer(referto 32-40-00 Figure 1).
9.:
3
2
5
Thefollowinglistof materialsareusedin makingthebalancer:
ItemNo.
Item
1
2
3
4
5
6
Base
Tee
Sides
Axle
Nuts
Spacer
Spacer
Bushing
Bushing
Pipe
Bearings
7
8
Dimensions
MaterialSpecifications
CQuantity
0.1902024 T3 clad aluminumalloy
1 ea.
0.190 2024 T4 extrudedaluminumalloy
2 ea.
0.125 2024 clad T3 aluminumalloy
2 ea.
4130 steel, normalized
1 ea.
AN365-624
2 ea.
0.50 x 2.25
5052-0aluminumtubing
2 ea.
0.50 x 1.25
5052-0aluminumtubing
2 ea.
1.480 x 1.625 x 1.00 Richlight,phenolicor aluminum
2 ea.
2.240 x 1.37 x 1.00
Richlight,phenolicor aluminum
2 ea.
0.125 x 903
blacksteel pipe
1 ea.
Savetwo of each sizeworn wheelbearingsfrom previousinspections. 2 ea.
12x 11
2.5 x 2 x 11
14 x 11
0.125 x 10.25
Tire Balancer
Figure 1
PAGE 24
Jan 10/90
32-40-00
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Steering
1. Fault Isolation- Steering
NOTE: Placeairplaneon jacksbefore attemptingfault isolationof landinggear system (referto
7-10-00).
CHART 1
FAULTISOLATION(STEERING)
Fault
Nosegear fails to steer
properly.
Nosegear shimmies
during fasttaxi, takeoff
and landing.
Cause
Remedy
Oleo cylinderbindingin
strut housing.
Lubricatestrut housing.
One brake dragging.
Determinecause and correct.
(referto 32-40-00)
Steeringarm rollersheared
at top of strut.
Replacedefectiveroller.
Internalwear in shimmy
dampener.
Replaceshimmydampener.
Shimmydampeneror
bracketloose at mounting.
Replacenecessaryparts and
bolts. (referto 32-20-00)
Tire out of balance.
Checkbalanceand replace
tire if necessary.
Worn or loosewheelbearings.
Replaceand / or adjustwheel
bearings. (referto 32-40-00)
Worntorque link bolts and /
or bushings.
Replacebolts and / or bushings.
(referto 32-20-00)
EFFECTIVITY:
32-50-00 Jan
Jan 10/90
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Steering(continued)
2. Removalof NoseGearSteeringAssembly(referto 32-50-00Figure401)
(a) Removepilot'sseatandfloorpanelsin frontof andbehindcontrolcolumn.
(b) Removeaccesspanelon leftsideof the aircraft'snose.
on thebulkheadsandlowershelf(floor)requiredto gainaccessto the
(c) Removeequipment
steeringrod comingthroughthebulkhead.
to thenosegearsteering.
NOTE: Do notrotaterodendbearingsunlessasan adjustment
(d) Removerequiredshelfandfloorpanels.
for removalof thetorquetubeattachedto the ruddercontrol
(e) Usethefollowinginstructions
sector:
(1.) Removeforwardwormscrewclampholdingpressuresealbellowto tube.
(2.) Unboltrodendbearingsfromthe sectorinsidethe aircraftandcontrolarminsideaccess
area.
(3.) Carefullydrawtubeforwardandup throughbellows.If rod endbearingdoesnotfit
throughbellows,removetherodend;do notforceit.
Nose
Gear
Tube
Rollers
NoseGearSteeringInstallation
Figure401 (Sheet1 of 2)
EFFECTIVITY:
040-999
Jan 10/90 32-50-00
PAGE
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Steering (continued)
Rudder
Pedal
Assembly
Right
Pedal
Pushrod
Nose
Gear
Steering
-ControlArm
Pushrod
Nose
Gear
Steering
Tube
RudderControlCables
Compensating
Bellows
Bulkhead
Sta.57.00
RudderControlSector
Nose Gear Steering Installation
Figure 401 (Sheet 2 of 2)
EFFECTIVITY:
040-999
32-50-00
JanPAGE
10/90
3
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Steering(continued)
2. Removalof NoseGearSteeringAssembly(referto 32-50-00Figure401) (continued)
(f) Theoutboardsteeringarm,locatedinthe accessarea,is removedby disconnecting
torque
tube,runningup fromtheruddercontrolsector.Removethethroughboltattachingthearmto
bearingsupportwashersto facilitate
thebearingshaft. Notethenumberof AN960D-1616
installation.
WARNING: THE BUNGEETUBE ASSEMBLYMUST BE HANDLEDCAUTIOUSLY.IF
FOUNDTO BE DEFECTIVEOR DAMAGEDIN ANY WAY,IT MUSTBE
REPLACEDWITH A NEW ASSEMBLY.UNDERNO CONDITIONSHOULDTHIS
PARTBE DISASSEMBLED.THEREARE SPRINGSUNDERCOMPRESSION
LOCATEDINSIDETHE TUBE. THE LOCKINGCLIPSMUST NOT BE
REMOVED.
thebungee
(g) Theinboardsteeringarm,locatedin thewheelwell,is removedbydisconnecting
tubefromthe arm. Removethethroughboltattachingthearmto thebearingshaft. To
facilitateinstallation,
notehowmanyAN960-1616L
washersareused.
(h) Thebungeetubeis attachedto boththeinboardsteeringarmandnosegearprimarydrivearm.
theaft endof the
Thebungeetubeis removedbyreachingintothewheelwell,disconnecting
thetubefrom
tubeto theinboardsteeringarm,pivotingthegearto theleft,anddisconnecting
theprimarydrivearm.
3. Installationof Nose Gear SteeringAssembly (referto 32-50-00 Figure 401)
WARNING: THE BUNGEETUBE ASSEMBLYMUSTBE HANDLEDCAUTIOUSLY.IF
FOUNDTO BE DEFECTIVEOR DAMAGEDIN ANY WAY,IT MUSTBE
REPLACEDWITH A NEW ASSEMBLY.UNDERNO CONDITIONSHOULDTHIS
PARTBE DISASSEMBLED.THEREARE SPRINGSUNDERCOMPRESSION
LOCATEDINSIDETHE TUBE. THE LOCKINGCLIPSMUST NOT BE
REMOVED.
(a) Installnosegearsteeringassemblyin reverseorderof removal.Toensurenosegearis
alignedproperly,proceedasfollows:
(1.) Witha plumbbob,dropa pointdirectlydownfromthetail skidandthecenterof thenose.
(2.) Laya chalklinebetweenthesetwopoints.Afterlayinga chalklinearoundthecenterof
thetire,alignthetirecenterlinewiththegroundchalkline.
(3.) Clamprudderpedalsin a neutralposition.
(4.) Withat leastthreethreadsengagedin therod ends,installsteeringassemblies.
EFFECTIVITY:
040-999
Jan
32
10/9032-50-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PositionandWarning
1. Descriptionand Operation- Positionand Warning
A squatswitchon the landinggear and a dynamicpressureq sensormustoperatethis latch
beforethe landinggear selectorcontrolcan be movedupward. The landinggear control knob is in
the shapeof a wheelto differentiateit from the flap control,which has a knob in the shaftof an
airfoil.
A differentialpressureq sensoris installedin the copilot'spitot/staticsystemwhich senses
dynamicpressure(q). The sensoris set to actuateat 100 ± 4 KIAS on increasingairspeedand
100 plus 4 KIAS minus 10 KIASon decreasingairspeed. Theq sensingsystemis providedas an
alternate(backup)meansof controllingmajorcircuitswhich are operatedthroughthe landinggear
squatswitches;groundcoolingfan solenoid,cabin pressuredump solenoid,ice protectionselector
switch,gear lock solenoidand high/lowselectionfor the stall recognitionsystemlift detectorheat.
2. Fault Isolation- Positionand Warning
CHART 1
FAULT ISOLATION (POSITION AND WARNING) (Sheet 1 of 2)
Fault
Cause
Remedy
Circuitbreakerout.
Checkcircuitbreaker.
Indicatorlight burnedout.
Replaceindicatorlight.
Circuitwire broken.
Checkwiring.
Circuit breakerout.
Checkcircuitbreaker.
Indicatorlight burnedout.
Replaceindicatorlight.
Lock switchdefective
or out of adjustment.
Replaceand / or adjustlock switch.
(referto 32-30-00)
Gear not lockedin down
position.
Adjustthe gear. (referto 32-30-00)
Gear refusesto retract
above 100_ 4 knots
increasing,100+ 4 -10
knots decreasing.
"q" pressureswitch
inoperative- stuck in
closedposition.
Replaceas required.
Gear selectorrefusesto
unlockabove 100± 4
knots.
Failureof K2 relay.
Replacecomponent.
No red light on panel
when gears are in
transit.
No green lighton panel
when gears are down.
EFFECTIVITY:
040-999
32-60-00
PAGE
1
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Positionand Warning(continued)
2. Fault Isolation- Positionand Warning(continued)
CHART 1
FAULTISOLATION(POSITIONAND WARNING)(Sheet 2 of 2)
Fault
Cause
Remedy
Flashingred indicator
lightor warning horn
soundingwhen power
from one or both engines
is above 150 foot-pounds
of torque.
Powerlever switchesare
faulty.
Replaceswitches.
Powerlever switchout of
adjustment.
Adjust throttle switches.
Red indicatorlight stays
on with gear up and
locked.
Doorscould be open.
Adjust doors. (referto 32-10-00
and 32-20-00)
Switchdefective.
Replacedefectiveswitch.
Powerleverswitchesout
of adjustment.
Adjust throttle switches.
Powerleverswitchesare
defective.
Replaceswitch.
Horn or light defective.
Replacedefectivepart.
Defectivewiring.
Checkwiring.
Flashingred light and
warninghorn fail to
operatewhen power
from both engines is
reducedbelow 150
foot poundsof torque.
EFFECTIVITY:
PAGE2
Jan 10/90 32-60-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Positionand Warning(continued)
3. Adjustmentof Main Gear Up Light Switch
(a) Checkthat the mainlandinggear up lock is properlyadjusted.
(b) Retractgear fully and ensurethe up lock roller is engagedand restingon the up lock hook.
(Nopressureon hydraulicsystem.)
(c) Adjustgear up lock switchtowardthe link until it actuates. The red indicatorlight in the cockpit
mustgo out.
NOTE: Oppositemaingear switch and nosegear switchmust be actuatedto extinguishthe
red light.
(d) Extendand retractgear to ensure properadjustment.
4. Adjustmentof MainGear Down LightSwitch (referto 32-60-00 Figure 501)
(a) Ensurethat the mainlandinggear down lock is properlyadjusted.
(b) Withgear down and locked,the green indicatorlight in the cockpit must comeon whenthe
downlock hook is loweredwithin 0.030 to 0.069 inch of bottomingin the hookslot of the lower
side brace link. Usethe followingcheckand adjustmentprocedure:
(1.) By hand, raisethe down lock hookuntil the down lock switch actuates (click).
(2.) With the hookraised,place a 0.070 inchwire feelergauge betweenthe hookand bottom
surfaceof the slot in the side brace link (referto 32-60-00 Figure501).
(3.) Lowerthe hook,allowingit to rest on the feeler gauge. (The end of the gauge mustbe
even with the lockpin.) The switch mustnot actuate(click).
(4.) Raisethe hookagain. Allow the switchto actuateand place a 0.030 gauge in the side
brace link slot.
(5.) Lowerthe hook. The switch mustactuate,allowingthe green indicatorlight in the cockpit
to illuminate.
(6.) Whenloweringthe hook, if the switchactuatestoo soonadjust the switchtowardthe
hook. If it actuatestoo late, adjustthe switchawayfrom the hook.
EFFECTIVITY:
040-999
32-60-00 Jan
Jan
1090
10/90
PIPERAIRCRAFT
PA-42-72C(AdvancedTrainer)
MAINTENANCEMANUAL
A. Positionand Warning(continued)
Main Gear Down Limit Switch
Figure 501
5. Adjustmentof Nose Gear Up Light Switch
(a) Checkthat the noselandinggear up lock is properlyadjusted.
(b) Retractgear fully and ensurethe up lock roller is engagedand restingagainstthe up lock hook.
(No pressureon hydraulicsystem.)
(c) Adjust gear up lock switch towardthe hook until it actuates. The red indicatorlight in cockpit
must go out.
NOTE: Maingear up switchesmust be actuatedto extinguishthe red light.
(d) Extendand retractgear to ensure properadjustment.
6. Adjustmentof Nose Gear DownLight Switch
(a) Be sure the gear is properlyadjustedfor down lock position.
(b) With the gear down and locked,adjust geardown switch toward link until it actuates. The
green indicatorin the cockpitmust comeon.
(c) Check switch operationby partiallyretractingand extendingthe gear severaltimes.
EFFECTIVITY:
32-60-00
PAGE
Jan 10/900
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PositionandWarning(continued)
7. Adjustment
of MainInboardGearDoorAjar Switches
(a) Ensure
the maininboardgeardoorsareadjustedproperly.
(b) Withthemasterswitchoff,actuatehandpumpto bringgeardoorsdown.
(c) Disconnect
actuatorcylinderrodfromdoorsto theyhangfreely.
CAUTION: AVOIDEXTREMEOUTWARDADJUSTMENTCAUSINGTHE SWITCH
MOUNTINGTABTO BEND BACKWHEN THE DOORIS CLOSED,RESULTING
IN DAMAGETO THE SWITCHUNIT.
(d) Positionswitch by adjustingretainernuts so when the door is closedby hand a click is heard
approximately1 inch beforethe door is completelyclosed.
NOTE: An ohmmeteror continuitytester can be used to indicateswitchactuation.
(e) Installactuatorcylinderrodto thedoor.
(f) TurnmasterswitchON andwiththegearselectorin DOWNposition,actuatehandpumpuntil
doorcloses.
8. Removalof GearWarningSwitches(referto 32-60-00Figure401)
Thegearwarningswitchesare locatedwithinthecontrolpedestaldirectlyunderthe powerlevers.
Eachswitchactuatesthewarninghorn.
(a) Theswitchesareremovedfromtheirmountingbracketsasfollows:
(1.) Removetop cover platesof pedestal. (One is forwardof the controllevers,the other
surroundsthe leversby removingattachmentscrews.)
(2.) Removeswitchfrom its mountingbracketby removingtwo screwssecuringeither switch
and spacerblock. First removenut from eachscrewand allowthe bracketof the other
switch and spacerblockto swingfull forwardby turning the adjustmentscrew
counterclockwise.Pull aft on switch bracketto be removed. Pushout attachmentscrews.
(3.) Disconnectnecessaryelectricalleads.
(b) The switch mountingbracketare removedby removingthe controlleverassemblyas follows:
(1.) Disconnect
the enginecontrolcablesfromcontrolleversby removingconnecting
clevis
pin.
(2.) Removeflushheadscrewat eachsideof pedestalhousing.
(3.) Removefrictionknobwithwasherfromrightsideof pedestal.
(4.) Removecapboltssecuringframe.
(5.) Pullassemblyfrompedestalhousing.
(6.) Removecontrolkeepertubeholdingswitchbracketsin the controlframeby removing
tube
attachment
screwsfromeachsideof frame.
EFFECTIVITY:
040-999
32-60-00Jan 10/90
PIPER AIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. PositionandWarning(continued)
LeftThrottleLever
RightThrottleLever
Plate,ThrottleLever
Adjustment
Side
ScrewAdjustment
MountingBracket
Coil Spring
Switch,
Horn
Spacer Block
Switch,Hom
SpacerBlock
Mounting
Bracket
SpringTension
ScrewAdjustment
Gear WarningSwitches
Figure 401
9. Installationof Gear WarningSwitches (referto 32-60-00 Figure 401)
The switch mountingbrackets,as part of the control leverassembly,are installedas follows:
andspacerblocksare installedwithmountingbracket),
(a) Assemblemountingbrackets(switches
tensionsprings,andspacerwashersin thecontrolframe.Securewiththekeepertube.
Securekeepertubein frame.
(b) Installcontrolleverassemblyin pedestalhousing.Securewithcapboltsandscrews.
(c) Installfrictionknobwithwasheronthe endof thelevershaftat therightsideof the pedestal.
leverswithclevispin. Placewasheron ends
(d) Connectenginecontrolcablesto theirrespective
of clevispinsandsecurewithcotterpins.
Theswitchesareinstalledon mountingbracketsasfollows:
(Advanced
[Referto PA-42-720
(a) Connectelectricalleadsto theirrespectiveswitchterminals.
Trainer)WiringDiagramManualfor wireinstallation.
screws.Swingthe
(b) Placeswitchandspacerblockin its mountingbracket.Installattachment
screws.Install
bracketofthe otherswitchandspacerblockforwardto installthe attachment
nutson thescrews;secure.
(c) Positionpedestalcoverplateson pedestal;installscrewsandsecure.
(d) Adjustswitches.
EFFECTIVITY:
040-999
Jan 132-60-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Positionand Warning(continued)
10. Adjustmentof Gear WarningSwitches
The gearwarning hornswitchesare installedin the controlpedestal,each controlledby a power
lever. Eachswitch activatesthe warning hornwhen either or both powerlevers are reducedbelow
300 foot-poundsof enginetorque. The followingprocedureis for the adjustmentof the gear
warningswitches:
(a) GroundAdjustment:
(1.) Start and run engineswith propellerset for full increaserpm.
(2.) To set powerleverswitchesto actuateat a desiredpower leversetting, retardpower
levers until enginetorque gaugesread300 foot-poundsof torque. Mark powerlever cover
in relationto the powerleversfor adjustmentof switches.
(3.) Shut down engines.
(4.) Set powerleverat locationsmarked. Withadjustmentscrewon switch bracket,adjust
each switch separatelytowardactuatorangleuntil switch actuates. The adjustmentscrew
is reachedby insertinga longscrewdriverthroughthe travel slot of the powerlever in the
pedestalcover.
(b) HornOperationalCheck:
(1.) To checkhorn operation,jack airplaneand retractlandinggear. With masterswitch on,
retardeitherpower leveruntil gear up indicatorhornsounds. Check locationof power
leverto adjustingmark. The warninghornoperateswhen either or both powerlevers are
retarded.
(2.) With warning hornoperating,lowergear to ensure hornceasesto operatewhenthe gear
is down and locked.
(3.) Removeairplanefrom jacks.
(c) FlightCheck:
(1.) Ensureoperationof warningsystemwhen gear is up and either or both powerlevers are
reducedbelow300 foot-poundsof enginetorque.
EFFECTIVITY:
040-999
Jan
32-60-00
1
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 33
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
33-EFFECTIVITY
33-CONTENTS
33-00-00
33-00-00
33-00-00
33-00-00
33-20-00
33-40-00
33-40-00
33-40-00
33-40-00
33-40-00
PAGE
1
1
1
2
3
4
1
1
2
3
4
5
DATE
CHAPTER
SECTION
PAGE
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
LIST OF EFFECTIVEPAGES
DATE
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER33- LIGHTS
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
33-00-00
GeneralCompartment
WarningLight System
AnnunciatorPanelLampTest
FluorescentGlareshieldLighting
Removalof Pilot/CopilotFlood Lights
Installationof Pilot/CopilotFlood Lights
1
1
1
1
1
1
Adjustment
of Glareshield
Fluorescent
LightingInverter
FaultIsolationGeneralGuidlines
DimmerControlAssembly
Removalof DimmerControlAssembly
Repairof DimmerControlAssembly
Installation
of DimmerControlAssembly
DomeLight
Removalof DomeLight
Installation
of DomeLight
1
2
3
3
3
3
3
3
33-20-00
Passenger
Compartment
OverheadReadingLights
Removalof OverheadReadingLights
Installation
of OverheadReadingLights
1
1
1
1
33-40-00
Exterior
LandingandTaxiLights
Removalof LandingandTaxiLights
Adjustment
of LandingandTaxiLights
Installation
of LandingandTaxiLights
WingTipStrobeLights
Removalof WingTipStrobeLights
Installation
of WingTipStrobeLights
Removalof WingTipStrobePowerSupply
Installation
of WingTipStrobePowerSupply
FaultIsolation(WingTipStrobeLights)
Characteristics
of an XenonFlashTube
WingInspectionLight
Description
andOperation
Servicingof WingInspection
Light
Removalof WingInspectionLight
Installation
of WingInspection
Light
1
1
1
1
2
2
2
2
2
2
3
4
5
5
5
5
5
EFFECTIVITY:
040-999
CONTENTSJan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
Lights
A. GeneralCompartment
(Advanced
Trainer)WiringDiagramManual,provides
Thischapter,usedin conjunction
with PA-42-720
assistance
in servicingtheaircraft'slightingsystem.
WARNING: HIGH VOLTAGESEXISTIN LIGHTINGSYSTEMCIRCUITS. FAILURETO FOLLOW
SAFETYPRECAUTIONSMAYRESULTIN SERIOUSINJURYOR DEATH.
The electroluminescentEL panelsare activatedwith 140 Vac,400 Hertzfrom the EL inverter. The
fluorescent,glareshieldflood lightingis suppliedwith a minimumof 375 Vacvia the coaxial harness
and dimmerinverter. The anti-collisionstrobesare suppliedwith 450 Vdc to the xenontubesfrom the
strobe powersupply.
the PA-42Referto WiringDiagramManualfor pointto point,wire to wire information,and 24-30-OOof
components
such as
and
systems
Manual
for
power
distribution
720 (AdvancedTrainer)Maintenance
circuitbreakersand switch panel information.
1. WarningLight System
(a) AnnunciatorPanelLampTest
The annunciatorpanel is locatedabovethe instrumentpanel.
Pushthe PUSHTO TESTswitch to checkoperationof lamps.
2. FluorescentGlareshieldLighting
(a) Removalof Pilot/CopilotFloodLights
(1.) Ensureelectricalpowerisoff.
(2.) Removecoverpanelsto exposefluorescent
tubes.
(3.) Removetube,ortubes,fromfixtures.
(b) Installationof Pilot/CopilotFlood Lights
(1.) Replacetube, or tubes,in fixtures.
(2.) Reinstallroyalitepanel.
(3.) Installcoverpanelsto fluorescenttubes.
LightingInverter
Fluorescent
of Glareshield
(c) Adjustment
(1.) Ensureelectricalpoweris off.
(2.) Removecoverpanels.
(3.) Disconnectcoaxialcables (marked1 LFV 107064AA and 1 LFV106064AA)from copilot's
panel.
(4.) Placefluorescentfixed dimmingswitchin overheadpanelto DIM position.
(5.) Rotateall instrumentlightingdimmer rheostatsfully counterclockwiseto the lowestsetting
(See 24-30-00,Figure2).
NOTE: An assistantis requiredto adjustthepowersupply,locatedforwardof thepilot's
instrument
panel,at station0.00.
EFFECTIVITY:
040-999
33-00-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720 Advanced Trainer)
MAINTENANCEMANUAL
A. GeneralCompartment(continued)
2. Fluorescent
GlareshieldLighting(continued)
(c) Adjustment
of GlareshieldFluorescent
LightingInverter(continued)
(6.) Apply24 Vdcbuspower,beingcarefulnotto causeshortcircuitsandreadvoltageat
exposedendsof thecoaxcables.
(7.) Haveassistantadjustpotentiometer
FV2 (Figure501),witha fully insulatedslothead
screwdriver,
to 375Vacat endsof bothcoaxleads.
(8.) Turnoff 24 Vdcbuspower.Reconnect
coaxialleads.
(9.) Disconnect
coaxlead(marked1 LBD105064BB)
at copilot'spositionandcoaxlead
(marked1 LBD103064BB)
at pilot'sposition.
(10.)Againapply24 VdcbuspowerandhaveassistantadjusttheBright/Dim
potentiometer
to
375Vacat endsof bothcoaxleads.
(11.)Turnoff 24 Vdcbuspower.Reconnect
coaxends.
(12.)Disconnect
coaxleadsmarked1 LFV201064AA
and1 LFV202064AAatthepilot's
position.
(13.)Apply24 Vdcbuspowerandhaveassistantadjustthe FV 1potentiometer
to 375Vacat
thecoaxdisconnected
ends.
(14.)Turnoff 24 Vdcbuspower.Reconnect
remainingtwocoaxleads.Thiscompletesinverter
adjustments.
DimAdjustment
Inverter
Max.
FV1
Max.
Max.
D/B
FV2
ADJ.
A
FluorescentLighting Inverter/ControlUnit
Figure501
(d) FaultIsolationGeneralGuidelines
Withdimmercontrolsat fullbrightnessandtheentireEL lightinginoperative,
check24 Vdc
supplyto ELinverter/dimmer
controlunit. If onlyoneELpanelis inoperative,
unplugthatpanel
andtestfor 140Vac,400Hertz,at panelconnection.Workbackthroughthe harnessto the
inverter,if no voltageis present.Ifvoltageis present,benchtest ELpanelwith110Vac,60
Hertzpower.In all cases,conventional
pointto pointfaultisolationmethodsapply.
EFFECTIVITY:
PAGE 2
Jan 10/9033-00-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. GeneralCompartment (continued)
3. DimmerControlAssembly
The dimmercontrol assemblyis locatedin the forwardbaggagecompartmentarea around FS
0.00. Thedimmer controlis locatedon the undersideof the floorboardaccess panelat the aft left
corner (whenfacing forward)of the forwardbaggagecompartment.
(a) Removalof DimmerControlAssembly
(1.) Removeelectricalpowerfrom aircraftby disconnectingbattery. Open baggage
compartmentdoor.
(2.) Raisefloor liner in the aft left comer (whenfacing forward)of baggagecompartment.
(3.) Removescrews securingaccesspanel.
(4.) Lift accesspanel. Disconnectelectricalconnectorfrom dimmer control.
(5.) Removemountingscrewssecuringdimmercontrolto accesspanel. Separatepanelfrom
dimmercontrol.
(b) Repairof DimmerControlAssembly
Replacementparts are orderedfromthe parts catalog. See Figure801 for dimmercontrol
circuitry.
(c) Installationof DimmerControlAssembly
(1.) Positiondimmercontrolassemblyon accesspanel. Securewith appropriatehardware.
(2.) Connectelectricalconnectorto dimmercontrolassembly.
(3.) Place accesspanel into positionand secure.
(4.) Replacefloor liner.
(5.) Securebaggagecompartmentdoor.
(6.) Connectbatteryand performan operationalcheckof lightingsystem.
4. Dome Light
(a) Removalof DomeLight
(1.) Removefour screwssecuringdome light assemblyin headliner.
(2.) Let light assemblyhang from headliner.
(3.) From behindlight assembly,removelight bulb.
(b) Installationof Dome Light
(1.) Insert new bulb into socket.
(2.) Positionlight assemblyin place on headliner.
(3.) Secure light assemblywith appropriatescrews.
EFFECTIVITY:
040-999
PAGE3
33-00-00Jan
10/90
PIPERAIRCRAFT
PA-42-720(Aavanced Trainer)
MAINTENANCEMANUAL
A. GeneralCompartment (continued)
Conn E494
1
3
FixedDim.
AvionicsDim.
Ctr. Pnl.
28 VDC
R. Pnl.
Control
R.H. Pnl.
28 VDC
Placard
Control
Plac
28 VDC
All TransistorsAre Motorola2N6282
DimmerControl AssemblyCircuitry
Figure801
Jan 10/90
33-00-00
EFFECTIVITY:
040-999
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. PassengerCompartment
1. OverheadReadingLights
(a) Removalof OverheadReadingLights
Eightoverheadreadinglightsare locatedabovethe passengerwindows.
(1.) Removegroundwire from light assembly. Removecover from lamp.
(2.) Removebulbfrom socket.
(b) Installationof OverheadReadingLights
(1.) Insert new bulb into socket.
(2.) Replacegroundwire and coverover lamp.
(3.) Light has a screwon lock ring. Insert lightfrom back of panel and screwon lock ring.
EFFECTIVITY:
040-999"
33-20-00
Jan 10/90
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Exterior
1. Landingand TaxiLights
(a) Removalof Landingand TaxiLights (Figure501)
(1.) Ensurecircuitbreakeris off beforedoing anywork on the landingor taxi lights.
CAUTION:
WHEN REMOVING ATTACHMENT PLATE, BE SURE NOT TO DROP THE
LAMPS.
(2.) To removelamps fromthe mountingfixture, removescrewsfrom front of lampattachment
plate. Removeattachmentplatefrom mountingfixture.
(3.) Disconnectelectricalleadsfrom lamp.
NOTE: Indicatepositionof each electricallead to facilitate reinstallation.
(4.) To removecompleteassemblyfrom gearstrut, disconnectelectricalleadsfrom both lamps
and releaseclampssecuringassemblyto strut housing.
lightassemblycan be tiled to thedesiredangle.
Adjustment
Landingand TaxiLights
Figure 501
(b) Adjustment of Landing and Taxi Lights
Two adjusting screws, found on the mounting pad sides at the top, are loosened so the entire
light assembly can be tilted to the desired angle.
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A. Exterior (continued)
1. Landingand TaxiLights (continued)
(c) Installationof Landingand TaxiLights
(1.) Reconnectelectricalleads in properplaceon lamps.
(2.) Place lamp and lamps againstmountingpad. Positionattachmentplate and securewith
appropriatescrews.
NOTE: Tightenscrews enoughto allow lampsto fit snugly in mountingfixture.
(3.) Installlandinglight assemblystrut housingwith bottomof mountingfixture5.6 inchesup
from the bottomof strut housing(Figure501).
(4.) Align bracketlongitudinally.Securein place with clamps.
2. WingTip Strobe Lights
(a) Removalof Wing Tip Strobe Lights
The lightsare locatedon both wing tip tanks nextto the positionlights.
(1.) Removescrewsecuringlens retainerand removelens.
(2.) Removethree screwsmountinglight assemblyfrom the wing tank tip.
(3.) Pull out light assemblywith strobelight and positionlight still attached.
(4.) Disconnectthree pin connectorto strobe light.
(5.) Cut plug off threewires and discard.
(6.) Pull strobe lampout of light assembly. Discardwith wires still attached.
(b) InstallationWing Tip Strobe Lights
(1.) Positionstrobelight into placeon light assembly. Insertthree wires connectedto it
throughthe holeprovidedin light assembly.
(2.) Insertthree wires into three pin plug and secure. Wire plug accordingto 33-45-01,PA-42720 (AdvancedTrainer)Wiring DiagramManual.
(3.) Reconnectthreepin connectorto harnessfrom strobepowersupply.
(4.) Positionlight assemblyon wing tip tank.
(5.) With appropriatescrews, securelight assemblywith strobeand positionlight attached.
(6.) Replacelens and lens retainer. Securewith appropriatescrew.
(c) Removalof Wing Tip Strobe PowerSupply
The wing tip strobe power supply(L or R) are locatedinsidethe outboardwing rib.
(1.) Removeaccesspanelon bottomof wing insidewing station 239.00.
(2.) The powersupply(L or R) is located insidethe outboardwing rib. Disconnecttwo
electricalplugs.
(3.) Removescrewsmountingpower supplyto the wing. Removepowersupply.
(d) Installationof Wing Tip Strobe PowerSupply
(1.) Positionpowersupplyin place. Securewithappropriate
screws.
(2.) Connecttwo electricalplugs.
(3.) Installaccesspanelon bottomof winginsidewingstation239.00.
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A. Exterior (continued)
2. Wing Tip Strobe Lights (continued)
(e) FaultIsolation(WingTip Strobe Lights)
dischargesystem.A condenserinthe
Thestrobelightassemblyfunctionsas a condenser
450voltsdc anddischargedacrossthexenonflash
powersupplyis chargedto approximately
50 flashesperminute.Thecondenseris parallelacrossthe
tubeat intervalsof approximately
xenonflashtube,whichis designedto holdoffthe450voltsdc applied,untiltheflashtubeis
by a solidstatetimingcircuitinthe
triggeredby an externalpulse.Thispulseis generated
powersupply.
Whenisolatingfaultsin thestrobelightsystem,first determineif thefaultsis in theflashtubeor
powersupply.Replacing
of theflashtubewillconfirmif thefaultsis in theflashtubeor the
of theflashtubewillconfirmif thetubeis defective.A normal
powersupply.Replacement
operatingpowersupplywillemitan audibletoneof 1 to 1.5kHz. If no soundis emitted,check
systemusingthefollowinginstructions:
NOTE: When isolatingfaults in the system,use schematic33-45-01in PA-42-720(Advanced
Trainer)Wiring DiagramManual.
(1.) Ensureinputvoltageat powersupplyis 28 volts.
POWERSUPPLYINPUT
CAUTION: WHEN CONNECTING/DISCONNECTING
CONNECTIONS,DO NOT REVERSECONNECTIONS.REVERSED
POLARITYOF INPUTVOLTAGEWILLPERMANENTLYDAMAGETHE
POWERSUPPLY,DESTROYINGA PROTECTIVEDIODE,WHICH
CAUSESOVERHEATINGOF THE SUPPLY.THIS DAMAGEIS NOT
APPARENT,BUT WILLCAUSESYSTEM
ALWAYSIMMEDIATELY
FAILURE.
WHEN DISCONNECTINGPOWERSUPPLY,ALLOW FIVE MINUTES
BLEEDDOWNTIME BEFOREHANDLINGTHE UNIT.
(2.) Checkfor malfunctionin interconnectingcables.
cablearenotreversed.
(a.) Ensurepins1and3 of interconnecting
cable.
checkcontinuitybetweenpins1 and2 of interconnecting
(b.) Usinganohmmeter,
If a readingisobtainedonthe meter,thecableis shortedandmustbe replaced.
damageto
NOTE: A shortdescribedin steps(1.)and(2.)willnotcausepermanent
thepowersupply,butthesystemwill be inoperative.Avoidanyconnection
the
cablewhichdischarges
betweenpins1 and3 of interconnecting
in thepowersupplyanddestroysthetriggercircuit.
condenser
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A. Exterior (continued)
2. WingTip Strobe Lights (continued)
(e) Fault Isolation(WingTip StrobeLights) (continued)
(3.) Check interconnectingcablesfor shortsas follows:
(a.) Disconnectoutput cablesfrom powersupplyoutlets.
(b.) Check for continuitybetweenconnectorsof each interconnectingcable by checking
from pin 1 to pin 1, pin 2 to pin 2, and pin 3 to pin 3. Whenmakingchecks,if no
continuityexiststhe cable is broken and mustbe replaced.
(c.) Checkfor shorts betweenpins 1 and 2, pins 1 and 3, pins 2 and 3 of the
interconnectingcable. If continuityexistsbetweenany of these connections,the
cable is shortedand mustbe replaced.
(d.) Checkfor shortsfrom pins 1, 2, and 3 to aircraft ground. (Pin 2 is aircraftgroundin
power supply.)
(f) Characteristicsof an XenonFlashTube
(1.) A xenonflash tube can be photo-sensitiveand somecould become moredifficultto fire
when subjectedto darkness.
(2.) Xenonflash tubesbecomeharderto fire with age or when exposedto hightemperatures.
(3.) A hardfiring tube sometimesfires with an enginerunning,but will not fire under low
battery conditions.
(4.) Under hot and cold cycling,during normaloperation,egg shellingof the glassenvelope
can occur,or leakscan developin the glassseal.
(5.) Xenonflash tube can self-ionize(continuouslyglowinga light blue), renderingthe system
inoperative.
NOTE: All the aboveconditionsrequirereplacement.
(6.) Installationof one new tube sometimescausesthe other tube to misfireor skip, indicating
the end of its servicelife and replacementis necessary.
(7.) A fully functionaltube shouldfire on a reducedvoltage of 10 volts in a 14V systemor 22
volts in a 28V system.
PAGE 4
Jan 10/90
33-40-00
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A. Exterior (continued)
3. Wing InspectionLight
(a) Descriptionand Operation
The light is mountedin the left outboardedgeof the left nacelle,abovethe leadingedge of the
wing. it is a sealedbeam, 24-voltunit,controlledfrom a rocker type switch mountedin the
overheadswitch panel. The light is positionedin the nacelleto illuminatethe leadingedge of
the wing when the switch is activatedin the cockpit.
(b) Servicingof Wing InspectionLight
Servicerequiredfor this unit consistsof replacinga burnedout lampwith a new lamp, P/N
4593.
(c) Removalof Wing InspectionLight
(1.) Be sure switch is in the OFF position.
(2.) Removenacelleside access panelwhere lampassemblyis mounted. Disconnectwire
connectionson the backof lamp.
(3.) Removefour clips holdinglampto panel. Removelamp.
(d) Installationof Wing InspectionLight
(1.) Positiongasket and lamp on panel.
(2.) Installfour clips. Securewith screwsand nuts.
(3.) Connectelectricalleadsto backof lampassembly.
(4.) Positionentirepanelon nacelleside. Securewith screws.
(5.) Activateswitchin cockpitto checklampoperation.
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PIPER AIRCRAFT
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MAINTENANCE MANUAL
CHAPTER 34
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
34-EFFECTIVITY
34-CONTENTS
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CHAPTER
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PAGE
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CHAPTER 34 - NAVIGATION
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
34-00-00
General
Descriptionand Operation
InstrumentPanel
Instruments
Removaland Installationof Panel MountedInstruments
Removalof BezelMountedInstruments
Installationof BezelMountedInstruments
Removalof ClampMountedInstruments
Installationof ClampMountedInstruments
1
2
2
2
3
3
3
3
3
34-10-00
Flight EnvironmentData
Fault Isolation(Pitot/Static)
Pitot/StaticSysemTest
Inspectionand Checksof Instrumentsand System
"q"- DifferentialPressureSystem
"q" SensorFunctionalCheck
GroundCheck Procedure
FlightCheckProcedure
1
1
7
8
9
9
9
10
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Navigation
A. General
ThePA-42-720
includespanelmountedinstruments
andgauges,providingtheflightcrewwith
continualmonitoring
of engineperformance,
flightcharacteristics,
andothermiscellaneous
functions.
In addition,an annunciator
panel,mountedat thecenterof theglareshield,providesthecrewwith
visualwarningandadvisoryindications
of aircraftsystemfunctions.Enginepowerlevers,propeller
pitch,enginestartcontrols,elevatortrim,ailerontrim,ruddertrimwheels,andthe maincircuit
protectionpanelaremountedon a pedestallocatedat bottomcenterof instrument
panel.Locatedon
theleftandrightsidesof crewcompartment
are plasticcircuitprotectionpanelswith
electroluminescent
lighting.Anoverheadpanelcontainsenginecontrolswitchesandmiscellaneous
systemswitchesandgauges.
Instrument
Panel
Glareshield
Overhead
Panel
Left
Breaker
Panel
Main
Circuit
Right
Circuit
Breaker
Panel
Fuel
Control
Panel
Left
Outboard
Subpanel
Right Outboard
Subpanel
Flight Deck
Figure1
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B. Description and Operation
1. Instrument Panel (Figure 2)
The instrument panel consists of three upper metal panels and four electroluminescent plastic
lower panels. The upper right and upper left panels contain a flight instrument grouping and a
clock. The center panel contains power plant instruments and other related gauges. The four
lower panels contain various switches, controls, warning lights, and gauges for monitoring and
controlling aircraft functions. Refer to 23-00-00 for avionics information.
EngineInstrument
Section
- AnnunciatorPanel
Avionics(Radio Panel)Section
Stall Warning
Pilot's Flight
Instrument-
Flight
nt
ction
Glare
Shield
Right Outboard
Electroluminescent
Panel
Left Outboard
Electroluminescent
Panel
Right Inboard
Electroluminescent
Panel
Left Inboard
Electroluminescent
Panel
InstrumentPanel
Figure2
2. Instruments
mustbe
Maintenance
areeitherelectricalor non-electrical.
of the PA-42-720
Theinstruments
where
Makeadjustments
manufacturer.
performedby a certifiedrepairstationor instrument
specified.
The majorityof instrumentationis attachedto the instrumentpanel with either a bezel or clamp.
The flight instrumentsare bezel mounted,the engineinstrumentsclamp mounted,and the lower
panels are either bezel or clamp mountedattachedwith screws.
panel,
or an entireinstrument
NOTE: Whenremovingan individualpanelmountedinstrument
facesandknobswiththecontrolcolumn.Contactwith
preventcontactoftheinstrument
the columncouldcausedamageto theinstruments.Handleall gyrodriveninstruments
withextremecareto preventballdentingof the rotorbearings.
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C Removaland Installationof PanelMountedInstruments
1. Removalof Bezel MountedInstruments
a. Removeall electricalpowerfrom system.
b. If the mountingpanelto whichthe instrumentis attachedmust be removed:
(1.) Removescrewssecuringindividualinstrumentpanel.
(2.) Carefullypull the paneloff.
NOTE: If the mountingpanelto which the instrumentis attachedmustbe removed,
ensure panelis well supportedbeforeunscrewingit from its mountingsupports.
c. Disconnectthe electricalconnectorsor plumbingfrom instrument.
d. Wheretwo or morelines connectan instrument,identifyeachline to facilitateinstallation.
e. Attacha dust plugor cap to eachfitting.
f. Where applicable,unscrewelectricalconnectionfrom post light. Removelight by unscrewing
retainingnut.
g. Removescrews securinginstrumentin panel.
h. Removeinstrumentfrom panel.
2. Installationof Bezel MountedInstruments
a. Placeinstrumentinto positionon backside of panel. Securewith screws.
b. Removethe dustplug or capfrom eachfitting.
c. Attachappropriateelectricalconnectorsor plumbingto instrument.
d. Where applicable,insertpost light and securewith retainingnut, secureelectricalconnectionto
light.
e. Placepanel into position.Securewith screws.
3. Removalof ClampMountedInstruments
a. Removeall electricalpowerfrom system.
b. Rotateclamp actuatingscrewcounterclockwiseto loosenclamp securinginstrumentin panel.
c. Withdrawinstrumentfrom panel.
d. Disconnectany attachinglines or electricalwires on rear of instrument.
e. Capopenings as necessary.
4. Installationof ClampMountedInstruments
a. Connectany attachinglines or electricalwires previouslyremoved.
b. Insertinstrumentinto appropriateopeningin instrumentpanel.
c. Rotateclamp actuatingscrewclockwise;tightenclamp aroundinstrumentcase.
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A. Flight EnvironmentalData (Figures1 and 2)
Thepitotsystemtransfersramair fromtheelectrically
heatedpitottubelocatedon theundersideof
the fuselagenosethroughtubingto theairspeedindicator.
Thepurposeof thestaticsystemis to ventflightinstruments,
pneumaticpressuregauge,cabin
differentialpressuregauge,andthefuelandoil pressuregaugeto ambientatmospheric
pressure.The
staticsystemconsistsof fourstaticventslocatedin the aftfuselagesection,an alternatestaticair
sourcelocatedintheforwardfuselageandcontrolled
by a selectorvalvein thecockpit;all
interconnected
bytubing.
NOTE: As shown in Figure 1, two staticports exist on each side of the aircraft. The left sidetop and
rightside bottomports are usedfor the copilot'sinstrumentsand the reversefor the pilot's
instruments.
CHART 1.
FAULT ISOLATION (PITOT/STATIC SYSTEM)
Fault
Tube does not heat or clear
itself of ice with switch ON.
Remedy
Cause
Circuitbreakerpopped.
Reset.
Opencircuit.
Repair.
Excessive
voltagedrop
betweenbatteryat pitot
head.
Check voltageat pitot head.
Heatingelementburned
out.
Replacepitothead.
Pointersof staticinstruments
do not indicateproperly.
Leakin instrument,case
or in pitot lines.
Checkfor leak and seal.
Airspeed indicatorreads
high.
Leak in staticline.
Checkfor leak and seal.
Low or sluggishairspeed
indication.
Obstructionor leak in
pitot lines.
Removestaticlines from
all instrumentsand blow
line clearfrom cockpitto
pitot head,checkfor leaks.
Airspeed changesas aircraft
is banked.
Waterin staticline.
Clearlines.
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A. FlightEnvironmental
Data (continued)
CHART 1.
FAULTISOLATION(PITOT/STATICSYSTEM) (continued)
Fault
"q" backupcircuit
inoperative.
Cause
Remedy
"q" overrideswitchfailure
in overrideposition.
Replaceswitch.
Defective
"q"pressure
Replaceswitch.
switch - stuckin open
position.
Havingexceeded100 ± 4 knots
("q" switch armed speed)the
followingconditionsexist:
(1) Landinggear selector
lockedin down position.
(2) Cabinfails to pressurize.
(3) Ice protectioninoperative.
34-10-00
Jan 10/90
1090 34-10-00
Jan
Nosegeardownlockswitch
failedin openor outof rig.
Repairor replace.
Defective"q" pressureswitch.
Replaceswitch.
EFFECTIVITY:
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A. FlightEnvironmentalData (continued)
16
15
18
12
Pitot/StaticInstallation
Figure1 (Sheet1 of 3)
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A. FlightEnvironmentalData (continued)
35. FlexibleHose (Static2)
36. FlexibleHose (Pitot2)
37. FlexibleHose (Static 1)
38. FlexibleHose (Pitot 1)
39. FlexibleHose (Pitot)
40. FlexibleHose (Static)
41. FlexibleHose (Pitot2 to ADS)
42. FlexibleHose (Static2 to ADS)
43. FlexibleHose (Pitot )
44. LineAssembly(Static)
45. q - Sensor Switch
46. LineAssembly(Static)
47. FlexibleHose (Pitot 1 to ADS)
48. FlexibleHose (Pitot 1)
49. FlexibleHose (Static 1 to ADS)
50. FlexibleHose (Static)
51. FlexibleHose (Pitot2)
52. FlexibleHose (Static2)
53. FlexibleHoseto Test Ports
54. Pitotand StaticTest Port Plac
55. Pitotand StaticTest Ports
Pitot/StaticInstallation
Figure1 (Sheet2 of 3)
PAGE
4
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34-10-00
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A. FlightEnvironmentalData (continued)
1. MainStatic Vent Line(Pilot)
2. MainStatic Vent Line(Co-Pilot)
56. Static LineAssembly(Co-Pilot)
57. Static LineAssembly(Pilot)
58. Static Line (Pilot)
59. Static Line (Co-Pilot)
60. Tee Fitting(Pilot)
61. Tee Fitting(Co-Pilot)
62. Static Line (Co-Pilot)
63. StaticLine (Pilot)
64. Static Vent Fitting (Co-Pilot)
65.StaticVentFitting(Pilot)
66. StaticVent Fitting(Co-Pilot)
67. StaticVent Fitting(Pilot)
58
1
67.
Pitot/StaticInstallation
Figure1 (Sheet3 of 3)
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
A. Flight EnvironmentalData (continued)
1. PitotTubesElectricHeated
2. AlternateStatic
Source
Differential
Pressure
Switch
("q"Switch)
7. Pressure
Bukhead
ToDeice/Gyro
Pressure
System
4. Condensate
Drain
Valve/Sump
3. StaticSource
SelectorValve -
A
A/S
PG
-
R/C
C/A
AP
ADC
S
q
-
Altimeter
Airspeed
Deice/Gyro SystemPressure
Rate of Climb
Cabin Altitude/Pressure
Diffential
Autopilot
Air Data Computer
Static SourceSelector
Diff. PressSwitch
II
5. StaticPorts
- StaticLines
- PitotLines
0
Pitot/StaticSchematic
Figure2
34-10-00
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Jan 10/90
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A. Flight EnvironmentalData (continued)
1. Pitot/StaticSystemTest
CAUTION: DO NOT USEANY PETROLEUMPRODUCTSOR LOOSESEALINGMATERIALS
ON OR ABOUTANY TEST EQUIPMENT,STATICSYSTEMLINES,OR
CONNECTORS.DURINGTHE FOLLOWINGPROCEDURES,TAKE
PRECAUTIONSTO PREVENTINGESTIONOF FOREIGNMATERIALSINTO THE
TEST EQUIPMENTAND AIRCRAFTSYSTEMS.
NOTE: The PA-42-720is equippedwith quick-disconnecting
test ports forwardof bulkheadat F.S.
17.00 which use an alternatestaticsystemtest unit. The followingprocedureis provided
if the procedureusingthe quick-disconnectports is not used.
The followingproceduresare to be accomplishedonly by qualifiedpersonnelper FAR
91.171 and 91.172,and in conjunctionwith FAR23 and AC 43.13-1A.
Use a BarfieldStatic LeakTester(BarfieldP/N2397F)or equivalentto performthe followingtest.A
suitableline adaptermustalso be attainedfor connectionto the aircraft pitottubes and staticvent
ports.
(a) Inspectall vents, ports, plumbing,and instrumentsfor looseconnectionsand physicaldamage.
Replacethe appropriateparts as required.
(b) Ensurethe systemis free of entrappedmoistureor restrictions. If necessary,purgethe system
with dry, oil-freeair or nitrogen,includingthoselines from the instruments. Purgethe lines
back throughthe staticvent ports.
CAUTION: MAKESUREALL LINES(TESTERAND EQUIPMENT)ARE PROPERLYAND
SECURELYCONNECTED,AND OBSERVEDDURINGEVACUATION
OF THE
WILL RESULTIN A SUDDEN
SYSTEM. AN UNEXPECTEDDISCONNECTION
PRESSURECHANGEAND PROBABLYCAUSEDAMAGETO BOTHTHE
TESTERAND AIRCRAFTINSTRUMENTS.
(c) Connecttest equipmentlinesto the pitottubesand staticvent ports. Seal staticventports not
being usedwith tape.
NOTE: Thereare two staticvent portsfor eachpitot static system,one on eachside of the
aircraft. However,it is significantthatthe two top ports are not to the same system.
The leftside top and bottomports are utilizedfor the copilot's instrumentsand the
reversefor the pilot'sinstruments.
(d) Withthe dual pilot/copilotsystemsinstalled(twopitot tubes),connect or plugtester lines such
that each systemcan be tested individually.Duringtest,closely observeairspeedto detect
and avoid reversemovement.
(e) Vacuumfor the test is to be pulledthroughthe two aft staticvent ports. With a vacuumpump
properlyconnected,evacuatethe staticsystemto a pressuredifferentialof 6.3 psig (13 inches
Hg).
(f) Whenthe rateof climb startsto reach2,500 fpm, slowlycloseoff the vacuumvalve. Do not
exceed2,500 fpm.
(g) Witha vacuum of 13.0 inchesof mercuryheldin the system,the altimetermustnot exceeda
loss of 100 feet in 1 minute.
(h) Uponcompletionof any tests, ensureall tape and sealingagentsare removed,especiallyat
the static ports.
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A. Flight EnvironmentalData (continued)
2. Inspectionand Checksof Instrumentsand System
Duringregularinspectionof the airplaneor wheneveran instrumentis changedor serviced,
completethe followinginspectionand checksfor the entire system:
(a) Inspectthe pitot-staticsystemfor cleanliness,security,and operation,per AdvisoryCircularNo.
AC 43-203A,for aircraft operatedin controlledairspaceunder IFRconditions. Aircraft not
operatedin controlledairspacemustbe testedper AdvisoryCircularAC 43-13-1A, Section4 of
Chapter16.
(b) Inspect instrumentsfor poor condition,mounting,marking,broken,loose, or missingknobs,
bent or missingpointers,and improperoperation(where applicable).
(c) Check power-offindicationsof instrumentpointersand warningflags for properindication.
(d) Apply powerand checkfor excessivemechanicalnoise or intermittentoperation,failureto
indicate,sluggishness,or indicationof excessivefriction. Note if the erectionor warm-uptime
is excessive,cagingfunctionsare normal,warningflag and indicatinglightsand test circuitsare
operable.
(e) Whenany air drivenattitudeor directionalgyrosare installed,inspectand changethe control
air filter every50 hours. Do not adjustthe vacuumregulatorwithoutfirst installinga new
centralair filter element. (Referto 36-10-00and 37-20-00)
(f) Note operationof instrumentsduring enginerunup. Checkfor intermittentor improper
operationof any instrument.
(g) Inspectcompletesystemfor overall condition,obviousdefects,loose attachments,tubing
connections,pneumatictubingcorrosion,cracks,bends,pinching,and evidenceof chafing.
(h) Check electricalconnectionsand circuitbreakersfor propersize, security,and condition.
Check instrumentlightingsystemfor illuminationrange,burned out bulbs, and defective
controls. Checkwiringfor chafing,excessivetension, impropersupport,or broken lacingand
ties.
(i) Check instrumentsfor overheatingor contaminationof equipmentby foreign matteror water.
Dust,dirt, and lint contributeto overheatingof equipment,poor ventilation,and malfunctioning.
Ensureventilationopeningsin equipmenthousingsare open and free from obstructinglint and
dust.
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A. FlightEnvironmentalData (continued)
3. "q" - DifferentialPressureSystem
A "q" sensorcircuit is a componentof the pitot/staticand electricalsystem. This circuitacts as a
backupin controllingcertainmajor circuitsif the landinggear squat switchesbecomeimpaired.
Withthis systemin operation("q" pressureswitchclosed),the followingconditionsare provided:
1. A groundis appliedto the ECU groundcoolingfan solenoidand cabin pressuredump solenoid.
2. Groundis removedfrom the ice protectionselectorswitch.
3. A + removedfrom the gear lock solenoid.
4. A highto low heat selectionoccursfor the stall recognitionsystemlift transducer.
The "q" pressurecircuitinvolvesthree doublepole, doublethrow relays operatingsimultaneously.
These relaysare controlledby normal/override,"q" differentialpressure,and nosegear down lock
switchesin series requiringall three to be closedfor operationof relays. If any three switches
open,the relays will deenergize.
The normal/overrideswitch, locatedat the upperright of the landinggear handle,acts as a control
to overridethe systemas necessaryand lights up when in override.
The pressureswitch, mountedto the forward,left side of bulkhead57.0, sensesdynamicpressure
and opensat 100 ± 4 knotswith increasingairspeedand closesat 100 +4/-10 knotswith
decreasingairspeed. Accessto the "q" switch is made throughthe left noseaccessorypanel.
4. "q" SensorFunctionalCheck
(a) GroundCheck Procedure
This proceduremaybe accomplishedduring a pitot/staticsystemcheckor as a separate
procedure.As follows:
1. Connectthe pitot/statictester as explainedin this chapter
2. Slowly increaseair speedreadingon tester until voltmeterindicates28 VDC
3. Checkfor sensoractivation(Activationshall be by 100 + 4 knots maximum).
4. Slowlydecreaseair speed readingon tester until voltmeterindicates0 VDC
5. Check for sensordeactivation( deactivationshouldbe at 90 knots minimum).
6. Slowlydecreaseair speed readingto zero.
7. After all test are completedinsurethat all tape and/orother sealingagentsare removed
from the aircraftpressureor staticports.
EFFECTIVITY:
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10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. FlightEnvironmental
Data (continued)
4. "q"SensorFunctional
Check (continued)
(b) FlightCheckProcedure
The"q"sensorcheck,performed
as partoftheflighttest procedures,
is asfollows:
1. Theaircraftmustbe at 15,000feetpressurealtitude,120KIAS.
2. Thefollowingconditions
mustbe met:
a. Landinggear and flaps down.
b. ECU in LO.
c. TemperatureAUTO,"q" sensoroverrideswitch in NORMAL.
d. Left and right engineice protectionsystemsactivated.
e. Left and right pitot stall recognitionheat switchesactivated.
NOTE: Observethe ammeterduring activationto assurethe functionof system.
3. Slowaircraftto 100+4/- 10knotsat 1 knot/second.Observe"q" sensoroperationin this
rangeasfollows:
a.
b.
c.
d.
4.
5.
6.
7.
8.
Deicesystemsmustdeactivate.(Currentflowdecreaseon ammeter.)
Cabinmustdepressurize.
ECUgroundventfanmustactivate.
Thelandinggearhandlecannotbe raised.
Accelerateto above 104 knots. Observeairspeed100± 4 knotswhen functionsreturn.
Place "q" sensor overrideswitchto OVERRIDE.The flashingamberlight mustactivate.
Slow aircraft to 95 knots and cyclethe landinggear. It must operatenormally.
Return"q" sensor overrideswitchto NORMALand accelerateto 110 KIAS. Cycle landing
gear to operate normally.
After flight test and at every normallyscheduledmaintenanceevent, inspectwires PR2L,
PR2D, PR2B,and PR2K(goingto leftgear squatswitch)for latentground faults,
preventinginadvertentcabin pressureloss. (Referto 32-20-01Wiring DiagramManual.)
(These wires are shieldedfor mechanicalprotection.)
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 35
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Feb 1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
CHAPTER35 - OXYGEN
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
35-00-00
Descriptionand Operation
Fault Isolation(OxygenSystem)
1
1
35-10-00
MaintenencePractices
OxygenSystemServicing
OverboardDischargeIndicator
Purging
Testingfor Leaks
OxygenCylinderand RegulatorRemoval
OxygenCylinderand RegulatorInstallation
ChargingValve Removal
ChargingValve Installation
PressureGaugeRemoval
PressureGaugeInstallation
Surge Valve Removal
Surge Valve Installation
Outlet Removal
Outlet Installation
OxygenPlumbingReplacement
Cleaning
Face Mask Cleaning
1
1
1
2
3
3
4
4
4
4
4
4
5
5
5
6
7
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EFFECTIVITY:
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CONTENTSan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
Oxygen
A. Descriptionand Operation(referto Figure 1)
The oxygen systemon the PA-42-720providesdiluter/demandoxygen for flight crew and can
automaticallypresentconstantflow for the passengers.Totaloxygensystemcapacityis 60 cu ft,
composedof both a 49 and 11cu ft storagecylinder. An oxygenpressuregauge mountedon the
lower left instrumentpaneldisplaysto the pilotthe storagecylinderpressure(1850psig-full;200 psigempty). Also featuredare a regulatorvalve,externalchargevalve,outlets, masks,and an ON/OFF
control.
Flightcrew oxygen masksare diluter/demandtype with a quick-donningharness. The masksare
stowedin the crew seat headrestand can be donnedwith one hand. The flight crew needtake no
further actionother than placingthe maskson their facesto start the flow of oxygenas the mask
supply hoseis alwayschargedwith oxygen.
Passengeroxygenmasksare constantflow type builtto TSO-C64. The masksare stowedin four dual
mask dropoutboxes in the cabin overheadand automaticallydeployedwhen the cabin altitude
becomesexcessive. The passengerneed only to graspa maskwhen presented,pull it to releasea
lanyardpin, and placethe mask on his face to obtainoxygen.
The maskdeploymentboxes are pneumaticallyoperatedby oxygen supplypressure. Whenoxygen
pressureis appliedto the maskbox, a piston is actuatedwhichpushesthe box lid off its latch and
allows the masksto fall into positionfor passengeruse.
Pressurefrom the oxygenregulator,which is always open, is preventedfrom reachingthe passenger
mask deploymentboxesby a normallyclosedsolenoidshutoffvalve. This shutoffvalveis openedon
increasingcabin altitudeby an absolutepressureswitchinsidethe pressurecabin at an altitudeof
12,500feet. The shutoffvalvecan also be manuallyactuatedby the flight crew througha leverin the
pilot side windowmouldingto ensure passengermaskdeploymentin the eventof a pressureswitch
malfunction.
In line betweenthe passengermaskdeploymentboxesand the oxygen shutoffsolenoidvalveare an
altitudecompensatingregulatorand a pressuresurge valve. The altitudecompensatingregulator
reducesthe oxygen supplypressureto the maskdeploymentboxes at loweraltitudesto reducethe
oxygen maskflow. Thisfeature allows a smalleroxygencylinderto be usedand still obtainthe
required10 minuteduration.
A visualoxygenoverboarddischargeindicatoris locatedon the belly of the nose section,underthe
baggagecompartmentarea (35-00-00Figure1 and 35-10-00Figure 1). This visual indicatoris
connectedto the oxygen systemthrougha highpressurecapillaryline. Any systemleakagewill
pressurizethis line, and when a line pressureof 60 +20/-20psig is reached,the green snap-in
indicatordisc ruptures. The absenceof the greendisc indicatesa systemleakdespite a normal
pressurereadingon the oxygen cylindergauge.
WARNING: EXERCISE UTMOST CARE IN SERVICING, HANDLING, AND INSPECTING THE
OXYGEN SYSTEM. A FULLY CHARGED OXYGEN CYLINDER CONTAINS ENOUGH
PRESSURE TO CAUSE SERIOUS INJURY TO PERSONNEL AND DAMAGE TO
EQUIPMENT. KEEP HANDS, TOOLS, AND WORKING AREA CLEAN. POST NO
SMOKING SIGNS. KEEP ALL COMPONENTS OF THE SYSTEM FREE FROM
HYDROCARBON-BASED MATERIALS, (OIL, GREASE, FUEL) AND ALL
COMBUSTIBLE MATERIALS. KEEP ELECTRICAL EQUIPMENT FROM COMING IN
CONTACT WITH CARELESSLY HANDLED TOOLS. AFTER SERVICING OR
FUNCTIONALLY TESTING THE OXYGEN SYSTEM, DO NOT SMOKE FOR AT LEAST
10 TO 13 MINUTES. OXYGEN IS LIKELY TO PERMEATE THE CLOTHING AND IS A
POSSIBLE COMBUSTION THREAT FOR THIS PERIOD OF TIME. WHEN SERVICING
THE OXYGEN SYSTEM OR WHEN PERFORMING ANY FUNCTIONAL TESTS ON THE
GROUND, ENSURE THAT THE AIRCRAFT IS ELECTRICALLY GROUNDED USE
OXYGEN SPECIFICATION MIL-O- 27210 TYPE I ONLY.
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PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Descriptionand Operation(continued)
10.Oxygen StorageCylinders
9. GreenOverpressureDischargeD
8. ExternalCylinderChargingValve
OxygenSystemInstallation
Figure1
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Descriptionand Operation(continued)
CHART 1
FAULT ISOLATION (OXYGEN SYSTEM)
Fault
No indicationof pressureon pressuregauge.
Cause
Remedy
Cylinderemptyor leak in
systemhas exhaustedpressure.
If empty,refill. If discharge
indicatordisk is ruptured, do
not refill. Referto instructions
below.
Pressure
gaugedefective.
Replacepressuregauge.
Defective
regulator.
Replaceregulator.
Oxygencylinderregulator
assemblydefective.
Replaceregulatorassembly.
On/ Off controlout of adjustment.
Adjust control.
Offensiveodors in oxygen.
Cylinderpressurebelow
50 psig.
Foreignmatterhas entered
the systemduring previous
servicing.
Purgeoxygen system.
Ruptureof green visual
indicatingdisc.
Oxygensystemleaking
Removeoxygen cylinderand
regulatorand returnto qualified
overhaulfacility. Replacedisc
as required(Figure35-2).
Pressureindicationnormal
but no oxygenflowing.
EFFECTIVITY:
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PAGE 3
35-00-00
Jan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. MaintenancePractices
1. OxygenSystemServicing
(a) Checkthat all lines havesufficientclearancebetweenall adjacentstructuresand are secured
in place. Also checkthe mountingsecurityof the cylinder.
(b) Checkthe cylinderfor the ICC identificationnumberand date of the last FAA inspectionand test.
NOTE: If cylinderis completelyempty,it mustbe completelydisassembledand inspectedin
an FAAapprovedfacility beforerecharging.
(c) Replaceany lines that are defectivewith factoryreplacements.
(d) Cleanall lines and fittings.
(e) Use Permacel412 ribbondope threadon maleendsof fittingsonly.Wrap threadwith a 1/4inchor more overlapin directionof thread spiral,beginningwith the secondthread on the
fitting.Avoid gettingany sealant intothe lines.After joint hasbeen made, removeexcess
sealant.
CHART 1
OXYGEN SYSTEM COMPONENTS LIMITS
INSPECTION
PARTS
Regulator
Masks
Cylinders(DOT3HT), steel,
thin wall
ACTION
300 Flight Hours
EachUse
See Note
Replaceas necessary
3 Years
Hydrostatictest; Replaceevery
24 years or 4,380 filling cycles
Hydrostatictest
5 Years
Cylinders(DOT3AA), steel
Cylinders(DOTE-8162,E-8391),
3 Years
composite
Hydrostatictest; Replaceevery
15 years
NOTE: Regulatorsusedwith DOT3HT(steel,thinwall) cylindersand DOT E-8162,E-8391
(composite)cylinders:Performa functionalcheckevery3 yearsand overhaulevery
6 years.
Regulatorsusedwith DOT 3AA(steel)cylinders:Overhaulevery5 years.
2. OverboardDischargeIndicator
WARNING: REFER TO THE WARNING IN 35-00-00 PRIOR TO PERFORMING ANY
MAINTENANCE ON THE OXYGEN SYSTEM.
The greenvisual indicatingdisc is locatedon the belly of the nosesectionunderthe baggage
compartmentarea (referto 35-00-00Figure1 and 35-10-00Figure401).
NOTE: If the cylindersafetydisc has ruptured,removecylinderin accordancewith Oxygen
Cylinderand RegulatorRemovalparagraph.Returncylinderand valveassemblyto a
qualifiedoverhauldepot.
(a) Removal
(1.) Removesnap ring holdingvisualindicatingdisc in placeand removedisc or any
remainingpiecesif disc was blownout.
(2.) Checkframe and dumpoutletfor damageif disc was blownout and repairas required.
(3.) Flush/purgeif required.
EFFECTIVITY:
040-999
35-10-00
PAGE 1
Feb 1/98
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. MaintenancePractices(continued)
2. OverboardDischargeIndicator(continued)
(b) Installation
(1.) Ensuredump outlet is clean.
(2.) Insertvisual indicatingdisc into frame.
(3.) Installsnap ring.
(4.) Installcylinderper the sectiontitled OxygenCylinderand RegulatorInstallationif cylinder
was removed.
VisualIndicatingDisc
Figure401
3. Purging
Purgethe systemwheneverthe cylinderpressurefalls below50 psig, or if any linesare left open
for any lengthof time,or wheneverthere are any offensiveodors present.
(a) Park the airplanein a NO SMOKINGarea and exerciseextremecaution.
(b) Keepall doors and windowsopen.
(c) Be sure all electricalsystemsare shut off.
(d) Connectthe oxygenrechargingunit to the filler valve.
(e) Turn on the system.
(f) Set the rechargingunit pressureregulatorto deliver 50 psig and let the systempurgefor I hour.
If any odor is still present.repeatthe procedurefor 1 or morehours. If the odorpersistsafter
the secondpurging,replacethe cylinder.
EFFECTIVITY:
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Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. MaintenancePractices(continued)
4. Testingfor Leaks
Apply detectorfluid (MIL-L-25567C)solution. Shakesolutionto form sudsor foam. Apply suds or
foam sparinglyto the jointsof a closedsystem. Lookfor tracesof bubbles. No visible leakage
shouldbe found. Repairor replaceanydefectiveparts and retest system. With the system
pressurizedto servicepressure,furthertests can be made. The rate of any leak should not
exceed 1 percentof the totalsupply in any 24 hourperiod. Wipeoff all traces of the detectorfluid
at the conclusionof the examination.
An alternatemethodusing nitrogenmaybe used if so desired. This methodrequiresthe following
procedure:
(a) Disconnectthe pilot'sand copilot'soxygenmask lines fromtheir outlets.
(b) Inspectthe passengeroutletsto assureall lanyardpins are installed.
(c) Disconnectthe low pressureoxygenline fromthe regulatorattachedto the oxygen cylinder.
(d) Obtaina bottleof clean, dry nitrogenhavinga manualshutoffvalve and a sensitivepressure
gauge.
(e) Pressurizethe systemto 100 +10/-10psig, and ensurethe pressureholds. Pressuredecay is
not acceptable.
(f) If a pressuredecreaseis noted, applyleak detectorsolutionsparinglyat all joints and outlets.
Lookfor tracesof bubbles. Repairany leaks.
(g) Wipeoff any trace of the detectorsolutionfollowingthe test, and reconnectthe low pressure
oxygenline to the oxygencylinderregulator.
WARNING: DO NOT ACTUATEANY ELECTRICALSWITCHESNOR ALLOWANY SORT OF
COMBUSTIONTO OCCURSINCECABIN AREAWILLFILL WITH EXCESS
UNUSEDOXYGEN. CLEARCABIN AFTERPURGINGLINES,BEFORE
OPERATINGANY EQUIPMENT.
(h) Topurgeany nitrogenfrom the system,connectall the oxygenmasksto their outletsand pull
the lanyardpins. Withthe oxygenturnedon, wait for a minimumof 3 minutesbefore shuttingit
off.
(i) Returnall masksand lanyardpins to their normalpositionsand reinstallall panels and
hardware.
5. OxygenCylinderand RegulatorRemoval
The cylinderand regulatorare locatedin the forwardfuselagesection. Performthe followingsteps
to removethe cylinderand regulatorfromthe airplane:
WARNING: ENSURETHATTHE VALVEON THE CYLINDERIS CLOSEDBEFORE
DISCONNECTING
ANY LINESFROMTHE REGULATOR,
AND OBSERVEALL
SAFETYPRECAUTIONSRELATEDTO OXYGENSYSTEMHANDLINGAND
SERVICING.
(a) Disconnectthe controlcable and pressurelines from the cylinder. Disconnectthe restraining
cable attachedto the bulkhead.
(b) Supportthe cylinderand loosenand separatethe clampsthat holdthe cylinderin place.
(c) Removethe cylinderfrom the airplane. Use caution not to bumpthe neck of the cylinderand
regulator.
(d) If the cylinder is completelyempty,the regulatormay be removed.
(e) Inspectthe cylinderand regulatorin accordancewith AC 43.13-1A.
EFFECTIVITY:
040-999
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10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. MaintenancePractices(continued)
6. OxygenCylinderand RegulatorInstallation
(a) With the regulator attachedto the cylinder,place the cylinderintothe airplanethroughthe
forwardbaggagecompartmentwith the regulatorfacing towardsthe access opening. Do not
bump the regulatorand cylinderduring installation.
(b) Positionthe cylinder so the controlon the regulatoralignswith the controlcable.
(c) Securethe cylinder in placeby connectingand tighteningthe two clamps.
(d) Connectthe pressurelines and controlcableto the regulator.
(e) Rechargethe oxygencylinderif not alreadyaccomplished.Referto 12-10-00for instructions
on replenishingoxygen supply.
7. ChargingValve Removal
(a) Open accessdoor locatedat fuselagestation 22.64.
(b) Ensurethat the regulatorvalveis closed.
(c) Disconnectthe connectorfrom the chargingvalve.
(d) Removethe three nuts and bolts holdingthe chargingvalve in place and removethe valve
throughthe accessdoor on the outsideof the fuselage.
8. ChargingValve Installation
(a) Place the valve intopositionthroughthe accessdoor on the outsideof the airplaneand secure
with three bolts and nuts.
(b) Connectthe connectorto the valve usingthreadsealant and instructionsgiven in paragraph
titled OxygenSystemServicing.
(c) Securethe accesspanel.
9. PressureGauge Removal
(a) Close the control valveand depressurizethe oxygen systemas required.
(b) Disconnectthe line from the back of the pressuregauge.
(c) Loosen and removethe retainernut and clamp holdingthe gauge in place.
(d) Pull the gauge out from the front of the panel.
10. PressureGauge Installation
(a) Place the gauge into the panelfrom the front and replacethe clamp and retainernut on the
back of the gauge. Be sure the gauge is positionedproperlybeforetighteningthe clamp.
(b) Reconnectthe line at the rear of the gauge.
11. Surge ValveRemoval(refer to Figure402)
(a) Close the control valveand depressurizethe oxygen systemas required.
(b) Removethe surge valve.
(c) Check the operationof the system. If a malfunctionof surgevalveis found, disassemblethe
valve to the extentof removalof a defectivepart (diaphragm,O-ring,or spring).
(d) Inspectthe filter in the inlet port. If required,cleanthe assembledbody and sinteredfilter in an
ultrasoniccleaner. Ensurethat detail parts do not comeinto contactwith hydrocarbon-based
materials (solvents,oil, grease,etc).
(e) Reassembleusing new O-ringand serviceablereplacementparts as required.
EFFECTIVITY:
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. MaintenancePractices(continued)
12. Surge Valve Installation(referto Figure402)
(a) Installthe surge valve.
(b) Pressurizeand test the systemfor leaks.
1. Spring
DiaphragmPlate
6. Body
7. Filter
Surge Valve(CrossSection)
Figure402
13. Outlet Removal
(a) Usinga suitablespannerwrench, removethe outer halfof the outlet.
(b) Removethe screwsholdingthe trim paneland removethe panel.
(c) The outlet can now be removedfromthe low pressureline.
14. Outlet Installation
(a) ApplyPermacel#412 ribbondope thread sealantto the male end of the fitting.
(b) Connectthe outlet to the lower pressureline.
(c) Positionthe trim paneland securewith screws.
(d) Positionthe outer halfoutlet and securewith a suitablespannerwrench.
(e) Tightenthe fittings intothe outletsto a torqueof approximately30 inch-pounds. Do not
overtightenfittingsas this could damagethe outlet.
EFFECTIVITY:
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35-10-00 Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Maintenance
Practices(continued)
(referto Figure403)
15. OxygenPlumbingReplacement
of oxygenplumbinglinesif rigidtubingmustbe
on installation
Thefollowingprovidesinformation
in the rulesnoted
installed,especiallyif relocationis required.Safetylimitationsaredescribed
below.
(a) All installedoxygenplumbingmustbe aboveandat least6 inchesfromall hydraulicandfuel
plumbing.
betweenall oxygenplumbingand
(b) Theremustbe at leasttwoinchesminimumclearance
andanyaircraftmovingpartsinareaswherefuelor hydraulicplumbingand
components
mustbe at least12inchesfrom
electricalwiringexist.All oxygenplumbingandcomponents
primaryflightcontrolsandenginecontrols.
mustbe at least6 inchesfromelectrical
(c) Wherepossible,alloxygenplumbingandcomponents
Whereit is notpossibleto maintain6 inchesclearance,a 2 inch
wiringandcomponents.
providedthewirebundlesaresupportedin conduitorwithclosely
clearanceis acceptable
spacedclampsorclips.Where2 inchclearanceis notpossible,boththewiringandtheoxygen
insulationandsupportedin sucha mannerthat
with additional
mustbe protected
components
theycannotbe deflectedto within1 1/2inchof eachother.
of 1/8inchbetweenoxygentubingandthestructureadjoining
(d) Maintaina minimumclearance
clamp(SeesketchA).
the supporting
of 1/8inchto prevent
(e) All lowpressureoxygenlinesmustmaintaina minimumclearance
Thesame
supported.
contactwithanotherobject(nut,bolt,bracket,etc.)whensufficiently
holdstruefor highpressurelines,excepthighpressuremustmaintain1/2inchminimum
slearance(SeesketchB).
(f) Wherean oxygentubepassesthrougha grommet,thetubemustnotbearonthegrommetin
anywayto causethegrommetto cut in service(SeesketchC).
1/8"min.
1/8" min.
1/2"min
(HighPressure)
1/8" min.
1/8"min.
GROMMET
GROMMET
(Low
Pressure)
SKETCH B
(SEE ITEM5)
SKETCH A
(SEEITEM4)
CORRECT
INCORRECT
SKETCH C
(SEEITEM6)
OxygenTubing Installations
Figure403
EFFECTIVITY:
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Jan10/9035-10-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. MaintenancePractices(continued)
16. Cleaning
Removeoil and greasefrom tubingand fittings usingone of the followingcleaningmethods:
(a) FirstMethod:
(1.) Use vapor degreasingcontainingstabilizedtrichlorethyleneconformingto Specification
MIL-T-7003,(or freonTCM).
(2.) Blowtubing clean and dry with a streamof dry nitrogen.Exercisecare to ensurethat the
interior of the tubing and fittingsare thoroughlycleaned.
(b) SecondMethod:
(1.) Flushwith SpecificationTT-N-95naphtha.
(2.) Blow clean and dry off all solventwith water-pumpedair.
(3.) Flushwith SpecificationMIL-F-566anti-icingfluid or SpecificationTT-1-735alcohol.
(4.) Rinsethoroughlywith fresh water.
(5.) Dry thoroughlywith a streamof clean, dried,filteredair or by heatingto a temperatureof
250°F to 300°Fas required.
(6.) The solventsmaybe reusedprovidedthey do not becomeexcessivelycontaminatedwith
oil. This conditionshall be determinedas follows:
(a.) Completelyevaporate100 millilitersof the liquidin a weighedglassdish. Evaporation
maybe accomplishedby heatingat 200°F for approximately1/2 hour.
(b.) After evaporation,cool and weighthe residue. Do not use the solventif the residue
exceeds100 milligramsin weight.
(c) Third Method:
(1.) Flushwith hot inhibitedalkalinecleaneruntil free from oil and grease.
(2.) Rinsethoroughlywith fresh water.
(3.) Dry thoroughlywith a stream of clean,dry, filteredair or by heatingat a temperatureof
250°F to 300°F as required.
17. FaceMaskCleaning
The pilot,copilot,and passengermaskscan all be cleaned. Disregardthose instructionsnot
pertainingto the particularmask.
(a) Removethe microphonefrom the mask.
(b) Removethe spongerubberdiscsfrom the maskturrets. Do not usesoapto clean sponge
rubberdiscs; this could deterioratethe rubberand give off unpleasantodors. Cleanin clear
waterand squeezedry.
(c) Washthe rest of the maskwith a very mild solutionof soap and water.
(d) Rinsethe maskthoroughlyto removeall traces of soap.
(e) Makesure the sidesof the breathingbag do not stick togetherwhiledrying;this actionmay
decreasethe life of the rubberin the bag. The maskcan be sterilizedwith a solutionof 70
percentSpecificationTT-1-735alcohol.
EFFECTIVITY:
040-999
35-10-00
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10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER 36
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LISTOF EFFECTIVEPAGESJan10/90
PIPERAIRCRAFT
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CHAPTER 36 - PNEUMATIC
TABLE OF CONTENTS
SUBJECT
CHAPTER
PAGE
36-00-00
GeneralDescriptionand Operation
1
36-10-00
Distribution
ComponentDetailedDescriptions
Bleed Air ShutoffValve Removal
Bleed Air ShutoffValve Installation
IntercoolerRemoval
IntercoolerInstallation
BleedAir OvertemperatureSwitchesRemoval
BleedAir OvertemperatureSwitchesInstallation
PneumaticSystemCheckValvesRemoval
PneumaticSystemCheckValvesInstallation
PressureRegulatorand ReliefValveRemoval
PressureRegulatorand ReliefValveInstallation
Ejector Removal
Ejector Installation
DeicerValvesRemoval
DeicerValvesInstallation
PressureSwitchesRemoval
PressureSwitchesInstallation
CheckValve Removal
CheckValve Installation
VacuumRegulatorRemoval
VacuumRegulatorInstallation
Gyro CentralAir Inlet Filter Removal
Gyro CentralAir Inlet Filter Installation
Proof Pressureand LeakageTest of PneumaticLines
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EFFECTIVITY:
040-999
CONTENTSan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
PneumaticSystem
A GeneralDescriptionand Operation
Pneumaticsystempressureis obtainedfrom bleedair outletsof each enginecompressorstage.
Bleed air for the pneumaticsystemis takenfrom the main bleedline upstreamof the environmental
systembleedair shutoffvalve. Pneumaticsystembleed air is suppliedwhen the engines are operating
and cannotbe shut off. The bleedair movesonto the intercoolers,locatedin the engine nacelles,
wherethe hot bleed air temperatureis cooledto below200°Fby an air to air heat exchangeprocess.
Overtemperatureswitches,normallyopen, are installedat the outletsof the intercoolers.These
switches,set to closeat temperaturesof 425°For higher,warnthe pilot of an overtemperature
condition.
The pressurizedbleedair is routedintothe fuselage,underthe floor area, and throughpneumatic
systemlineswith checkvalvesto preventreverseflow to non-operatingengine. The pressurizedair
enters a pressureregulator,which regulatespressureto 18 ± 1 psig for deicer boot operation,door
and suppliesa sourceof air
seal operation,operationof the cabin pressurecontrolejector/regulator,
throughthe ejector. This createsa vacuumfor gyro instrumentsoperation. A reliefvalve in the
pressureregulatorrelievessystempressureat 20.5to 22 psig if the pressureregulatorfails. Air from
the pressureregulatoralso goesto the deicersystemvalves,which are normallyclosed,and provides
a vacuumthroughan integralejectorthe holdsthe deicer bootsdown. Whenthe deicertimer is
energized,the solenoidvalveon the deicervalveopens and allowspressurizedair to inflatethe boots.
Pressureswitcheswhich are normallyopen closewhen the bootsreach a pressureof 15 + 1 psig,
indicatingboot inflationto the pilot. Whenthe timer de-energizesthe solenoidvalves on the deicer
valves,boot pressureis dumpedand vacuumis reappliedto the boots.
A checkvalve is installedin the vacuumlinefrom the gyros,preventinga reverseflow in the vacuum
line to the gyros. A vacuumregulator,placedin the gyro instrumentline, regulatesvacuumat 4.5 to
5.4 in. Hg referencedto cabin pressure. An inlet filter is providedat the inlet of gyro vacuumsource.
Pneumaticpressureand suctiongaugesare mountedin the instrumentpanel.
The cabin door seal is controlledby a solenoidvalve,whichopensto pressurizethe seal whenthe
door is closed,and dumpspressurefrom the sealwhen the door is opened.
The bleedair systemprovides a regulatedsupplyof enginebleedair for aircraft pressurizationand
environmentaland pneumaticsystemsoperationsfrom sea levelto 35,000feet. The bleedair is
conditionedfor cooling,heating,and ventilatingby an environmentalcontrolunit.
The ECU bleedair supplysystemusestwo bleedair mixingand regulatingshutoffvalves.These
valvesprovidepositivebleed air shutofffor both the high and low enginebleed air flow, and regulate
bleedair to two presetpressurelevels(18 psig and 31 psig). One valveis located in each nacelle,
forwardof the firewall. The bleedair mixingvalves also providethe use of high and low enginebleed
air by mixingin an ejector. High pressurebleedair providesthe motiveflow throughthe ejector
nozzle,entrainingthe low pressurebleedair in the mixingthroatof the ejector. The valve regulator
sectionmaintainsthe outlet pressureselectedby the pilot at 18 psig or 31 psig. The regulatoradjusts
flow of highpressurebleed air to the minimumamountrequiredto bring bleed air mix up to selected
pressure.
EFFECTIVITY:
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution
The followingis a list of various componentsusedto distribute,control,and regulatethe pneumaticair
sourcein this airplane.
1. Component
DetailedDescriptions
(a) BleedAirShutoffValve:(Figure1)
Thebleedair shutoffvalveislocatedaft of theenginefireseal,on the leftside,at station89.71.
(-65°Fto +300°F)at altitudefrom
Thevalveoperatesovertherangeof ambienttemperature
sealevelto 33,000feet.Thevalveshu!sofftheairflowduringenginestartsandasdesiredby
thepilot.
(b) Intercooler:(Figure1)
is locatedaft of theenginefirewall,at theoutboardsideof station106.00.The
Theintercooler
below200°F,usingramairflow
intercooler
coolspneumaticsystembleedair to temperatures
forcooling.
(c) BleedAir Overtemperature
Switches:(Figure1)
switchesarelocatedaft ofthe enginefirewall,in thepneumatic
Thebleedair overtemperature
of 425°Forhigher,warningthe
closeattemperatures
linesat station106.00.Theseswitches
pilotof overtemperature
conditions.
SystemCheckValves:(Figure1)
(d) Pneumatic
checkvalvesarelocatedbelowthecabinfloorat fuselagestation151.30.The
Thepneumatic
air intoa non-operating
engine.
valvespreventreverseflowof pneumatic
andReliefValve:(Figure1)
(e) PressureRegulator
Thepressureregulatorandreliefvalveare locatedbelowthecabinfloorbetweenfuselage
bleedair pressureto 18± 1 psig
stations151.30and 162.60.Thepressureregulatorregulates
for deicerbootoperation,andsuppliesa sourceof airthroughtheejector,creatinga vacuum
operation.A reliefvalvein thepressureregulatorissetto relievesystem
for gyroinstrument
pressureat 20.5to 22 psig,if the pressureregulatorfails.
(f) Ejector:(Figure1)
Theejectorislocatedbelowthecabinfloorbetweenfuselagestations151.30and162.60.The
ejectorprovidesa vacuumsourceto operateallgyros.
(g) DeicerValves:(Figure1)
Thedeicervalvesarelocatedbelowthecabinfloorbetweenfuselagestations151.30and
162.60.Onevalveis usedforwingboots,theotherfortail boots.Thevalves,normallyclosed,
providea vacuumthroughan integralejector,holdingdeicerbootsdown.Whenthedeicer
air to
thesolenoidvalveon thedeicervalveopensandallowspressurized
timerisenergized,
pressurefromthedeicerbootsis
inflatethe boots.Whenthesolenoidisde-energized,
dumpedandvacuumisapplied.
(h) PressureSwitches:(Figure1)
Thepressureswitchesindicatebootinflationto thepilot,andwhenthebootpressurereaches
switchcloses.Onepressureswitchis locatedin theleftwing
15± 1 psig,theapplicable
leadingedgeat wingstation97.50andis usedfor wingboots.Thesecondswitchis locatedin
thetail sectionat fuselagestation321.00andis usedforthetail surfaceboots. Theswitches
turnon indicatorlightsat thetop ofthecopilot'scircuitbreakerpanelto indicateproper
of thedeicesystem.
operation
(i) CheckValve:(Figure1)
panelat
Thecheckvalveis locatedin thecockpit,behindtheleftsideof theinstrument
fuselagestation66.50. Thecheckvalvepreventsreverseflowfromthevacuumlineto gyros.
EFFECTIVITY:
040-999
36-10-00Jan
PAGE
1
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
Pilots Turn and Bank Indicator
Ports
EngineBleed Ports
DirectionalGyro
Gyro Horizon
1
13
2
DoorSeal
17
14
BleedAir Shutoff/Regulating
Valve
Intercooler
BleedAir Overtemperature
Switch
Pneumatic
SuctionGauge
GyroInletAir Filter
Valve
VacuumRegulator
Pneumatic
SystemCheckValves
CheckValve
9. Pressure
Regulator/Relief
Valve
1.
2.
3.
4.
5.
6.
7.
8.
10. Ejector
11. DoorSealSolenoidValve
12.TurnandBankTrimValve
13. GroundBleedAirBypassValve
14. DeiceBoots
15. WingDeiceValve
16. TailDeiceValve
17. PressureSwitch(N.O.)15± 1 psi
Pneumatic
SystemSchematic
Figure1
EFFECTIVITY:
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Jan
109036-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
(j) VacuumRegulator:(Figure1)
Thevacuumregulatoris locatedin thecockpit,behindtheleftsideof theinstrument
panelat
fuselagestation66.50. Thevacuumregulatorregulatesvacuumfor spinningthegyrosat 4.5
to 5.2inchesof mercury,reference
to cabinpressure.
(k) GyroInletFilter:(Figure1)
Thegyroinletfilteris locatedin thecockpit,behindthe leftsideof the instrument
panelat
fuselagestation66.50. Theinletfilterfilterscabinair inletto gyrosto 0.3micronparticlesat
99%efficiency.
(I) Pneumatic
Pressure
Gauge:(Figure1)
Thepneumatic
pressuregaugeis locatedin thecockpit,on theupperleftsideof theinstrument
panel.Thepneumatic
pressuregaugedisplayspneumatic
systempressureto thepilot.
(m)SuctionGauge:(Figure1)
Thesuctiongaugeislocatedin thecockpit,on theupperleftsideof theinstrument
panel.The
suctiongaugedisplaysgyrovacuumto thepilot.
(n) DoorSealSystem:(Referto 52-00-00
for detailedinformation.)
Bleedair,fedto thepneumatic
systempressureregulator/relief,
is regulatedandroutedto the
doorsealthrougha threewayvalve. Thisvalvedirectsregulatedairto thedoorsealat
pressurization
anddumpspressureoverboard
whenit is notdesired.
2. BleedAir ShutoffValve Removal
(a) Removetopcowlof affectedengineto gainaccessto shutoffvalveon theleftsideof engine.
(b) Removesafetywireandboltsto removecouplingssecuringvalveassemblyin bleedline.
(c) Disconnect
electricalconnectorfromvalve.
(d) Removevalvefromnacelle.
3. BleedAirShutoffValveInstallation
NOTE: If leakageoccurs at couplings,line the flanges with teflon tape threadsealant, (Referto
List of ConsumableMaterialsin 91-00-00.)makingsure tape is placed1/16 inch from the
edge of the flangeto preventingestionof tape in system.
(a) Installnewvalvein positionandsecurecouplings.
Torquecouplingboltsto 35-45inch-pounds
andsafetywire.
(b) Installelectricalconnectorto valve.
4. IntercoolerRemoval
(a) Removeturtlebackcowl to gain accessto intercooler,beingsure to removescrewssecuring
the inlet and outletducts. (Referto 54-00-00.)
(b) Disconnectand removeall ducts and plumbing.
(c) Removescrewsaroundflangeof the intercooler.Withdrawassemblyfromfirewall.
5. IntercoolerInstallation
(a) Mountintercoolerand coolingair inletduct to firewallwith screwspreviouslyremoved.
(b) Usinga new gasket at the intercooler/outletduct interface(refer to parts catalog),mount
coolingair outletduct with screwspreviouslyremoved.
(c) Connectplumbingto intercooler.
(d) If separated,reconnectinlet ductcouplingto ram air inlet scoop. Connectram air scoopto
bottomcowl.
(e) Replacecowl and install screwssecuringoutletduct to cowl.
EFFECTIVITY:
040-999
36-10-00
PAGE
Jan
10/903
36-10-00
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
6. BleedAir OvertemperatureSwitchesRemoval
(a) Removeturtlebackcowl to gain accessto switch.
(b) Disconnectelectricalleadsfrom switch.
NOTE: Note positionof eachwire removedto facilitate installation.
(c) Unscrewswitchfrom receptacle.
(d) Removeswitch and O-ring.
7. Bleed Air OvertemperatureSwitchesInstallation
NOTE: Apply siliconelubricantsparinglyto all O-rings.Avoid getting lubricantinsidetubes.
(a) Referto parts catalog and installnew O-ring in receptacle.
(b) Screw switch intoits receptacle.
(c) Connectwires to their properplace on switch.
8. PneumaticSystemCheck ValvesRemoval
(a) Gain accessto checkvalvesby removingthe floor panelson the right side of fuselage between
fuselagestations140.00 and 151.30.
(b) Disconnectpneumaticair supplylinesfrom valves.
(c) Unscrewvalves with O-ringsfrom fitting assembly.
9. PneumaticSystemCheckValvesInstallation
(a) Install newvalve with new gasketto fitting assembly.
(b) Connectpneumaticair supplylines to valves.
(c) Installfloor panels,carpet, and seats.
10. PressureRegulatorand ReliefValve Removal
(a) Gain accessto the pressureregulatorand reliefvalveby removingfloor panelson the right
side of fuselage,betweenfuselagestations151.30and 162.60.
(b) Disconnectunionand elbowfrom pressureregulatorand reliefvalveby unscrewingnuts.
(c) Removecup assemblyby looseninghoseclamp.
(d) Removefour bolts with washerssecuringregulatorto bracket.
(e) Removepressureregulatorand relief valve
11. PressureRegulatorand ReliefValve Installation
(a) Place pressureregulatorand relief valve in position.
(b) Securewith bolts and washerspreviouslyremoved. Ensurewashersare installedunderbolt
heads.
NOTE: Apply siliconelubricantsparinglyto all O-rings.Avoidgettinglubricantinsidetubes.
(c) ConnectunionandelbowwithnewO-ringsto pressureregulatorandreliefvalve.
(d) Installfloorpanels,carpet,andseats.
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
12. EjectorRemoval
(a) Removeright side floor panels betweenfuselagestations151.3,162.6, and the aft, lower,wing
to fuselagefairingfor accessto its outlet.
(b) Whileat the root, removenut from ejectoroutlet.
(c) Disconnectlines. Openclamp securingejectorto bracketassembly.
(d) Removeejectorby sliding assemblythroughthe holein fuselage.
13. EjectorInstallation
(a) Withejector in position,secureclamp. Reinstallall lines previouslyremoved.
(b) Installappropriatenut at ejectoroutletand wing to fuselagefairing.
(c) Installfloor panels, carpet and seats.
14. DeicerValvesRemoval
(a) Gainaccessto deicer valvesby removingcenter floor panel betweenF.S.151.30 and 162.60.
(b) Disconnectall lines at deicervalve beingremoved.
(c) Disconnectelectricalleads from valvebeingremoved.
(d) Removescrewssecuringassemblyin position.
(e) Removedeicervalve.
15. DeicerValvesInstallation
(a) Installnew valvein position.Securewith screwspreviouslyremoved.
(b) Connectelectricalleads to their properposition.
(c) Connectall lines disconnectedfrom valveduring removal.
(d) Installfloor paneland carpet.
16. PressureSwitchesRemoval
(a) The pressureswitchesare accessibleas follows:
(1.) Togain accessto the pressureswitchfor outboardwing boots,removeturtlebackcowl
and intercooleroutletduct.
(2.) The pressureswitchfor tail and inboardwing bootsis accessiblethroughthe forwardtail
accessopening,nearthe top of the aft pressurebulkhead.
(b) Disconnectelectricalwiring and pressurelines from switch.
(c) Removepressureswitch.
17. PressureSwitchesInstallation
(a) Installnew switch.Securelines with hoseclampspreviouslyremoved.
(b) Connectelectricalwiringto their properpositions.
(c) Installany panels,cowls, or other hardwareremoved.
EFFECTIVITY:
040-999
36-10-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
18. Check ValveRemoval
(a) Removecenter instrumentpanelfor accessto checkvalve.
(b) Removeclampssecuringvalvein position.Removelinesfrom valve.
(c) Removecheck valve.
19. Check ValveInstallation
(a) Install newvalve.
(b) Connectand securelines to valve.
(c) Replacecenter instrumentpanel.Reinstallother hardwareremoved.
20. VacuumRegulatorRemoval
(a) Removeor hand copilot'sinstrumentpanelto gain accessto regulator.
(b) Disconnectall lines from vacuum regulator.
(c) Removevacuumregulator.
21. Vacuum RegulatorInstallation
(a) Installvacuumregulator.
(b) Connectall lines to vacuum regulator.
(c) Replacecopilot's instrumentpanel and other hardwareremoved. Referto 37-20-00for
adjustmentprocedure.
22. Gyro CentralAir Inlet Filter Removal
(a) Removeor hang copilot's instrumentpanelto gainaccessto inletfilter.
(b) Disconnectlines from inlet filter.
(c) Removeinletfilter by removingcentralretainingboltretainingfilter to bracket.
23. Gyro CentralAir Inlet Filter Installation
(a) Installcentralair filter in position. Securewith washerand nut previouslyremoved.
(b) Connectall lines to inlet filter.
EFFECTIVITY:
040-999
36-10-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution(continued)
24. Proof Pressureand LeakageTest of PneumaticLines
CAUTION: PRIORTO PERFORMINGTHE PROOFPRESSUREAND LEAKAGETEST,
PERFORMTHE STATICSYSTEMTESTS IN 34-00-00,TO ENSURENO PITOTSTATICSYSTEMLEAKSEXISTS. CONDUCTINGCABIN PRESSURETESTSWITH
A LEAKINGPITOT-STATIC
SYSTEMCOULDDAMAGEDELICATEINSTRUMENTS.
(a) Removeupperand lower enginecowlingfrom left engine.(Describedin 71-00-00.)
(b) On left and right sides,disconnectengineprimarybleedair line at bleed air shutoffvalve
(Figure501, Item 2) and groundbypassvalveoutlets (Item3). Disconnectsecondarybleedair
linefrom groundbypasslines.
(c) Connectnitrogenbottle (Figure501, Item 7) with regulator(range0-500 psig) (Item 6), a
pressuregauge (range0-500psig) (Item4), and a manualshutoffvalve (range0-500 psig)
(Item5) to disconnectedlines.
(d) RemoveECU accesspanelfromforwardleft side of fuselage.
(e) Disconnectbleed air supplyline forwardof station57.00 pressurebulkheadand cap the line
(Figure501, Item 12).
(f) Disconnectthe secondarybleedair line from the emergencypressurizationshut-offvalvein the
right hand wing root and cap the line (Figure501, Item 12).
(g) Capbleed air line at bleedair valveand groundbypassvalve outlet. (Figure501, Item 12)
(h) Removefuselagefloorboardsat F.S.146.00.
(i) Disconnecttwo pneumaticsupplylines to checkvalves (Figure501, Item 11)and cap the
supplylines (Figure501, Item 12).
WARNING: BEFOREAPPLYINGHIGH PRESSURETO THE BLEEDAIR SYSTEM,ENSURE
ALL PERSONNELARE CLEAR,ALL CONNECTIONSARE TIGHT,AND HOSE
ENDSARE SECUREDTO ENGINEMOUNTWITH ROPEOR SAFETYWIRE.
(j) Slowlyopen regulatorvalveon nitrogenbottleuntil test pressuregauge (Figure501, Item7)
reads300 psig (roomtemperature).
(k) Applynitrogenpressureat 300 psig (roomtemperature)to disconnectedprimary and
secondarybleedair lines in left nacellefor 5 minutes.
(I) Conducta complete inspectionof bleedair and pneumaticsupplyducting (includingbleed
air/ramair intercooler- Figure501, Item6) for leakageand deformation.
(m) Componentsshowingpermanentdeformation(indicatedby loosenedmounts,clamps,or
distortedtubing) must be replaced.
(n) Usingmanualshutoffvalve,closevalveto isolatenitrogenbottle fromthe system.
(o) Withtest pressureof 300 psig trappedin ducts, monitorgaugefor pressuredrop.
NOTE: Pressuredrop cannotexceed50 psig overfive minutes.
(p) Repeatsteps (a) thru (o) for right hand supplyducts.
(q) Uponcompletionof test, relievepressurefrom system,removenitrogensupply,shutoffvalve
and gauge, reconnectenginebleedair lines,and installcowling.
(r) Removeall pressurecaps (installedfor test only)and test equipment. Reconnectall lines and
installall floorboardsand accesspanelspreviouslyremoved.
EFFECTIVITY:
04-999
36-10-00 Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Distribution (continued)
1. EngineBleedAir Ports
2. BleedAir ShutoffValve
3. GroundBypassValve
Bleed
View Showing
ShowingDisconneted
Disconnected
BleedLines
Lines
7. NitrogenBottle
ECU
6. NitrogenSupplyRegulator
5. ManualShutoff(TestOnly)
12. PressureCap
-
Sta.
57.00
4. PressureGauge(TestOnly)
I
View Showing N2 Connection
—9.BleedAir
Lines
8. Intercooler
SupplyLines
11. Check
Proof Pressureand LeakageTest Setup
Figure501 (Sheet 1 of 2)
EFFECTIVITY:
040-999
Jan 10/90 36-10-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
(continued)
ENGINELEFTSIDE
Pressure
FUSELAGE
LEFTSIDE- FORWARD
Proof Pressureand LeakageTestSetup
Figure501 (Sheet2 of 2)
EFFECTIVITY:
040-999
36-10-00JPAGE
36-10-00Jan 10/909
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
CHAPTER 37
LIST OF EFFECTIVE PAGES
CHAPTER
SECTION
37-EFFECTIVITY
37-CONTENTS
37-00-00
37-10-00
37-10-00
37-10-00
PAGE
1
1
1
1
2
3
DATE
CHAPTER
SECTION
PAGE
DATE
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
Jan 10/90
LISTOF EFFECTIVE
PAGESan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
CHAPTER 37- VACUUM
TABLE OF CONTENTS
SUBJECT
Description
andOperation
FaultIsolation
CHAPTER
PAGE
37-00-00
1
1
37-10-00
Distribution
VacuumSystemTest
VacuumRegulatorAdjustment
1
2
3
EFFECTIVITY:
040-999
CONTENTSan 10/90
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
VacuumSystem
A Descriptionand Operation
Thegyro-vacuum
systemfunctionsbybleedair beingforcedthrougha venturidevicecalledan ejector.
Astheprimarybleedairflow isforcedthroughtheejector,a decreasein pressuredevelopsproviding
flowactsasthesourceof airto the system.(Shownin Figure1)
the secondary
flow. Thesecondary
The inletfor secondaryflow is locatedbehindthe instrumentpanel. Attachedto the inlet, a filter cleans
air down to 0.3 micronparticleswith a 99% efficiency.
The vacuumis controlledon the vacuumside of the instrumentsby a vacuum regulatorand check
valve. The regulatormaintainsvacuum between4.5 and 5.2 inch mercury,relativeto cabinpressure.
On the vacuumside of the regulator,a checkvalve is built intothe line, preventingreverseflow to gyro
instruments.
Thevacuumsystemoperatesthepilotsturnandbankindicator.A suctiongauge,locatedon thelower
left of thepilot'sinstrument
panel,indicatesnegativepressurein the vacuumsystem.
CHART 1
FAULT ISOLATION (VACUUM SYSTEM)
Remedy
Fault
Cause
SuctionGauge- pressure
drop. (PressureGaugemay increase.) Pilot'sturn
and bank becomes
inaccurate.
Blockedbleedair
nozzleto Ejectorfails.
RemoveEjectorand blow
out nozzle.
CheckValvefailsclosed.
ReplaceCheckValve.
fails
VacuumRegulator
openor closed,or the
inletfilteris cloggedor
blocked.
ReplaceRegulatorand/
or clean Inlet Filter.
Tubingfrom Ejectorto
vacuumregulatorfailed
open or closed.
Repairor replaceTubing.
The tubingto the specific
instrumentsfailed open
or closed.
Replaceor repairtubing.
Specificvacuuminstruments
tumble.
EFFECTIVITY:
37-00-00Jan
Jan 10/90
1
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Distribution
Figure1 givesa schematicdescriptionof how the vacuum systemis arrangedin the aircraft.
Pilot'sTurn and Bank Indicator
Engine
Bleed
BleedAir
Checkand
Shutoff
Valve
Intercooler
Engine
Bleed
Inlet Filter
Suction
DirectionalGyro
PressureGauge
Gyro Horizon
VacuumRegulator
(4.2 to 5.2 in. Hg
BleedAir
Overtemperature
Switch
(N.O.)
PressureSwitch
(N.O.)
15+ 1 PSI
DoorSeal
Solenoid
Valve
(N.C.)
Valve(N.C.)
Deice
Boots
A. VacuumLineto Cabin Pressure
ControlSystem
B. To BleedAir and Cabin Pressure
System
VacuumSystemSchematic
Figure1
EFFECTIVITY:
040-999
PAGE
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10/90 1
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Distribution
1. VacuumSystemTest (Figure501)
(a) Removeseats, carpeting,and floor panelson the right side of fuselage,between F.S.117.88
and F.S.162.0.
(b) Disconnectthe hoseto the cabin pressurecontrol systemfrom the tee behindthe co-pilots
instrumentpanel. Plugthe porton the tee.
(c) Disconnectvacuum supplyline at the vacuumejectorunderthe cabinfloor just forwardof F.S.
151.30.
(d) Connecta vacuumpumpwhich producesat least 20 in. Hg suction,a test vacuum gauge,and
shutoffvalves in line with the vacuumsupplytubing fromthe gyros. (Figure501.)
NOTE: To eliminatethe effectsof instrumentcase and valve leakageduringthe systemleak
test, disconnectthe hoses at the inlet and outlet of eachgyro, the suctiongauge and
the turn and bank adjustmentvalve. Connectthe two hosesfrom eachinstrumentand
the valve using a piece of tubingbeadedon eachend and secure.
(e) Attain a vacuum of 20 in. Hgon the test gauge.
(f) Maintaina vacuumpressureof 20 in. Hg on the test gauge. Closeboth test shutoffvalves.
The suctiongauge can not decreasemorethan 1 in. Hg over 5 minutes. If the systemdoes not
holdthe vacuum,checkfor leaks.
(g) Reinstallall lines,floor panels,seats and hosesremovedor cappedfor this test.
SuctionGauge
T. & B. AdjustmentValve
Test VacuumGauge
0 - 30 in. Hg
Cap
DisconnectTubing
at VacuumEjector
DisconnectHoseto Cabin
PressureControlSystem
at this Portand PlugPort
Gyro Instruments
VacuumSystemTest Setup
Figure501
EFFECTIVITY:
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PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Distribution
2. VacuumRegulatorAdjustment (Figure502)
NOTE: Do not adjustvacuumregulatorwithoutchangingthe central air filter. Centralair filter
mustbe changedevery50 hours.
(a) Start enginesand turn ON leftand right bleedair switches.
(b) With one enginepowereddown, setthe other at 75%Ng. Checkvacuumgauge readingand
adjust vacuum regulator,if necessary,for not less than 4.5 in. Hg. The vacuumregulatorsare
locatedabovethe copilot's rudderpedals.
(c) Observingpropersafety precautions,advancepoweron both enginesto a minimum90% and
ensure vacuumgauge reads5.4 in. Hg minimum. Adjustvacuumregulatoraccordingly,reduce
powerand repeatstep (b).
(d) After establishingabove parameters,apply sufficientpowerestablishinga pressuregauge
readingof 16-20psig. Cycle deicerbootsand ensuregyro vacuumindicatesa steady4.5 in.
Hg, afterdeicer boot cycle is turnedOFF.
(e) If adjustmentsof the pneumaticsystemare required,refer to 36-10-00.
Poppet
DiaphragmAssembly
Seat
Vacuum
Source
Air From
Gyro
AdjustingScrew
VacuumRegulator
Figure502
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MAINTENANCE MANUAL
CHAPTER 51
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LISTOF EFFECTIVE
PAGESFeb 1/98
PIPERAIRCRAFT
PA-42-720
(Advanced
Trainer)
MANUAL
MAINTENANCE
CHAPTER51 - STANDARDPRACTICES
ANDSTRUCTURES- GENERAL
TABLEOFCONTENTS
SUBJECT
PAGE
CHAPTER
51-00-00
andStructures
- General
StandardPractices
General
StructuralRepairs
1
1
1
51-10-00
Smoothness
Investigation,
CleanupandAerodynamic
WindowSkin Inspection
Passenger
WingandAssociated
Structure
Empennage
andAssociatedStructure
Areas)
CracksIn BendRadiusof Flanges(Non-Pressurized
Cracksin Flange
HoleFlanges
Cracksin Lightening
CoolingScoop
Repairof CrackedorTom-OutDimpledHolesAroundGenerator
Section
FuselageRepairs- Pressurized
andAction
Reference
InspectionItem,Part,Description,
1
1
3
4
5
5
7
8
10
11
51-20-00
Processes
SealingProcedures
Sealingof NacelleFuelTank
SurfacePreparation
MaterialPreparation
Listof Materials
SealantApplication
FuselageSealing
SurfacePreparation
MaterialPreparation
Listof Equipment
Listof Materials
SealantApplication
SealingFayingSurfaces
SealingJoggles
SealingHolesandVoids
HolesandVoidsin (Cold)Air DuctWork
SealingSeamsandJoints
SealingFasteners
Fittings
Sealing"AN"StandardBulkhead
withSealingCompound
SealingElectricalHarnesses
Coverings
withHeatShrinkable
SealingElectricalHarnesses
of ReleaseAgent
Application
Gaskets
SealingFormed-In-Place
Removalof Sealant
CleanUp
Equipment
1
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CHAPTER51 - STANDARDPRACTICES
AND STRUCTURES - GENERAL
TABLE OF CONTENTS(continued)
SUBJECT
CHAPTER
51-20-00(continued)
Avionicsand ECUBayDoorSealing
Avionicsand ECUBay DoorSealsRemoval
Avionicsand ECUBay DoorSealsInstallation
Avionicsand ECUBayDoorCamlocFasteners
Sealing
PAGE
15
15
15
15
51-40-00
Fasteners
Rivet Replacement
OversizeRivet Replacement
Rivet Substitution
Blind Rivets
HollowRivets
High-ShearFasteners
1
1
2
3
3
3
3
51-70-00
Repairs
SheetMetal Repairs
FuselageRepairs- PressurizedSection
1
1
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
StandardPractices
andStructures
- General
A. General
structure.Thefuselagecontains
seriesaircraftcontainsa metal,semi-monocoque
ThePA-42-720
bulkheads,
stringers,andstiffenerswhichareattachedto theouterskin.Thecabinentranceand
exitis installedin thethird
cargodoorsarelocatedon theleftsideof theaircraft.Anemergency
arealsomadeof full
windowback,on the rightsideofthe aircraft.Thewingsandempennage
cantilever,
semi-monocoque
construction.
B. StructuralRepairs
inthischapterand
to recommended
repairprocedures
Structuralrepairsmustbe madeaccording
Figure
setforthin FAAAdvisoryCircular43.13-1A.Toassistin repairsandreplacements,
regulations
1 identifiesthetypeandthicknessof variousskinmaterialused. Neverreplaceskinor patchplatewith
materialotherthanof theoriginaltypeskin. Therepairmustbe as strongastheoriginalskin,and
flexibilitymustbe retainedsosurrounding
areaswillnotreceiveextrastress.
Whenmakingmajor structuralrepairsother than replacingfactorymanufacturedparts, the
manufacturermust be contacted.
WARNING: NO ACCESSHOLESARE PERMITTEDIN ANY CONTROLSURFACES.DO NOT USE
PATCHPLATESOR ANY FILLERMATERIALNORMALLYUSEDFOR REPAIROF
MINOR DENTS,ON ANY MOVABLETAIL SURFACES.
on theelevatorcontrolsystem,conducta frictioncheckto ensure
NOTE: Whenserviceis completed
systemfrictioniswithinlimits.
If access holesneed to be cut for skin repairson the aircraft,referto Figure2 for typical accesshole
specifications.In pressurizedareas, all skins,formers,stringers,etc, are consideredstructural
membersand must be treated as such. All repairmaterialmustbe free of defectssuch as nicks,
scratches,etc, which can cause stress risers. Do not dimple a structuralmemberby drivingthe rivet
head into the part.
windowsareremovedbybuffing,providingno morethan0.031inchof
Scratches
in acrylic-plastic
materialhasbeenremoved.Nocrazingor cracksareallowedin pressurewindows.
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B. StructuralRepairs (continued)
22
21
1
17
SKINTHICKNESS
NUMBER MATERIAL THICKNESS
1
2
3
4
5
6
7
8
Fiberglass
2024-T3
2024-T3
2024-0*
2024-T3
2024-0*
2024-T3
2024-0*
.020
.025
.025
.032
.032
.040
.040
NUMBER MATERIAL THICKNESS NUMBER MATERIAL THICKNESS
9
10
11
12
13
14
15
16
2024-T3
2024-T3
321 STSTL
2024-T3
2024-T3
2024-T3
2024-0*
2024-T3
.050
.064
.015
.080
.050
.090
.063
.016
17
18
19
20
21
22
23
24
2024**
Polyurethane
2024**
2024**
2024**
Kevlar
2024**
2024*
.040
.032
.050
.020
.025
.063
NOTE:
LeftWingShown,RightWingOppositeand NotedMaterialOutlinesin DotsUsedon RightWingOnly.
* HeatTreatto 2024-T4AfterForming.
** HeatTreatto 2024-T42AfterForming.
MaterialSkin Thickness
Figure 1 (Sheet 1 of 3)
PAGE
51-00-00
2
Jan 10/90
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B. StructuralRepairs (continued)
Left
Shown
Right
Opposite
MaterialSkinThickness
Figure1 (Sheet2 of 3)
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B. StructuralRepairs (continued)
2
19
5
2
12
SKINTHICKNESS
NUMBER
MATERIAL
1
Fiberglass
2024-T3
2024-T3
2024-0*
2024-T3
2024-0*
2024-T3
2024-0*
2024-T3
2024-T3
321 ST STL
2024-T3
2
3
4
5
6
7
8
9
10
11
12
THICKNESS
.020
.025
.025
.032
.032
.040
.040
.050
.064
.015
.080
NUMBER
MATERIAL
THICKNESS
13
14
15
16
17
18
19
20
21
22
23
24
2024-T3
2024-T3
2024-0*
2024-T3
2024**
Polyurethane
2024**
2024**
2024**
Kevlar
2024**
2024**
.050
.090
.063
.016
.040
.032
.050
.020
.025
.063
NOTE:
LeftWingShown,RightWingOppositeand NotedMaterialOutlinesin DotsUsedon RightWingOnly.
* HeatTreatto 2024-T4AfterForming.
** Heat Treat to 2024-T42 After Forming.
MaterialSkinThickness
Figure1 (Sheet3 of 3)
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B. StructuralRepairs(continued)
17318AccessHoleCoverPlate
20372AccessHole
Plate
Reinforcement
o
o
17317 Access Hole
Reinforcement Plate
o
o
o
17315AccessHole
Plate
Reinforcement
- 17316 Access
Hole Cover Plate
I
o
I
o
0
0
o
o
0
o
o
o
o
AN 507-8-32R10
o
5/16
6 15/16
7
TypicalAccessHolesandPanels
Figure2
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PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Investigation,Cleanupand AerodynamicSmoothness
1. PassengerWindowSkin Inspection
This inspectionis to be carriedout by the eddy-currentmethodof non-destructivetesting (NDT)
without strippingany paint fromthe inspectionarea. An experiencedtesting laboratorymust be
retainedto do the testing. The personnelconductingthe test mustbe certifiedto AmericanSociety
of NondestructiveTestingTC-1A,Level II minimum,and havetwo yearsof actualworking
experience.All passengerwindowsmustbe inspectedin the area indicatedin Figure601,
PassengerWindowSkin Inspection.
The eddy-currenttesting instrumentmust be in the 5 kHz to 500 kHz rangewith the lowest
possiblefrequencybeingpreferred. A small-tip(0.130inch)probe,with frequencymatchedto the
tester, mustbe used.
Inspectionequipmentcalibrationis unconventional,so a referencestandard(Piper P/N 73130-02)
is availableand mustbe usedfor calibration. Practicemay be necessarybeforethe operatoris
skilled in this procedure. Proceedas follows:
(a) Adjust gain controls.
(b) Set X and R controlsto obtainan on scalereading.
(c) Rotatelevel controlto bringpointer on scale.
(d) With the probe in air (awayfrom metal),tune the BalanceX controluntil a 60% meter is
obtained. If the pointerdrops off-scale,bring it backon-scalewith the level control.
(e) Repeatstep 4 for BalanceR control.
(f) Withthe probe on the calibrationstandardbetweenrivets and awayfrom cracks,a O meter
readingmust be obtained. If not, obtainthe lowestpossiblereadingby repeatingsteps4 and
5.
(g) The calibrationstandardsimulatesthe windowedge skin and inner doublerwith non-coincident
cracksin the skin and doubler. While cracksin the airframewill generallyrun to a rivet,the
simulatedcracksin the standardrunbetweenrivets. The inspectionarea is betweenthe rowof
universalhead rivets and the edgefarthestfrom them. With an O meterreadingbetweenrivets
and awayfrom cracks,a crack in the skin will registera 20-30%deflection,whileone in the
doublerwill register5-10%. The operatormustfamiliarizehimselfwith deflectionscausedby
the flush rivets.
(h) Onceinspectionpersonnelare certaintheir calibrationtechniqueis correct,readingsfrom the
airplanemust be comparedto thoseobtainedon the calibrationstandard. Equipmentmustbe
adjustedas closeas possibleto an O referencereadingon the airplane. Doublecheckusing
the referencestandardand simulatinganypaintthicknessvariation;use tape on the standard.
Wheninspectingthe airplane,ensurethe surfaceto be inspectedis clean and dry. The primary
area of concernis betweenthe windowcutoutedge and the row of flush rivets (5/16 inchfrom the
edge). However,the inspectionmust be carriedas far back as the first row of universalhead
rivets.
If a crackin the fuselageskin is found, the standardrepair (Figure51-23,StructuralRepairsFuselageSkin Repair)can be used. If the crack hasprogressedpastthe rivet hole or hasstarted
betweentwo rivets,the leadingedge of the crack mustbe stop-drilledusing a No. 40 (0.098dia.)
drill. The stop-drillhole mustgo throughthe skin and the inner doublerbehindit. Beforerivetting
on the repairdoubler,the airplaneexteriorpaint mustbe roughed-upin the area beneaththe repair
doublerand the faying surfacesealantappliedbetweenthe repairdoublerand the skin. Use
sealantwhich complieswith MIL-S-7502or 8802. Wipeoff excesssealantbefore it cures. Prime,
finish, and paint the repair areato matchthe aircraftexterior. If a crack is found in the inner
doubler,contact PiperAircraftCorporationfor a recommendedrepairprovidingspecificson the
problem.
CAUTION: FAILURETO COMPLYWITHTHESEINSPECTIONSAND REPAIRPROCEDURES
AT THETIMES SPECIFIEDCAN ULTIMATELY
LEADTO AN INABILITYTO MAINOR THE IN-FLIGHTLOSS OF THE WINDOWITSELF.
TAIN PRESSURIZATION
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PAGE
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Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
WindowSkinInspection(continued)
1. Passenger
Inspect
Blend
3 inches
WindowSkinInspection
Passenger
Figure601
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PIPERAIRCRAFT
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MAINTENANCEMANUAL
2. Wing and AssociatedStructure
Firewallto EngineMountExtensionBolts
NOTE:
Replacefirewallto engine mountextensionbolts (NAS626-8)at 7,500flight hours.
Wing Inspectionand RepairAreas
Figure602
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3. Empennageand AssociatedStructure
NOTES:
1. If rivets are intact at inspection,
reinspectevery 1,600hours.
2. Inspect right and left sides every 100
hour inspectionperiod.
D
C
B
InspectShadedAreas
F.S.
359.32
A. At 11,600flight hours,inspectrivetsat F.S.332.0,W.L. 32.0 for loose rivets(See Note 1).
B. Inspect rivets at F.S. 359.32,W.L. 29.45 TO W.L. 39.0. Replace"working"rivets (MS20470-AD5,13
EA.) with NAS 1738B5-4as required(See Note2).
C. Inspect rivets at F.S.359.32,W.L. 41.15 TO W.L. 52.50. Replace"working"rivets (MS20470-AD5,14
EA.) with NAS 1738B5-4as required(See Note2).
D. Inspect rivets at vertical fin rear spar, W.L. 57.628 TO W.L. 69.10. Replace "working" rivets
(MS20470-AD4,14 EA.) with NAS1738B5-4as required(SeeNote 2).
E. Inspect rivets at vertical fin rear spar, W.L. 26.65 TO W.L. 56.0. Replace "working" rivets
(MS20470-AD5,34 EA.) with NAS 1738B5-4as required(See Note 2).
Empennage Inspection and Rivet Replacement
Figure 603
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4. Cracksin BendRadiusof Flanges(Non-Pressurized
Areas)
(a) Whena flangehasa cracklessthan1/4inchlong,repairthecrackbygrindingit outsmoothly
whilemaintaining
a inchradiusat thebaseof thecrack.
(b) Whena flangehasa crackgreaterthan1/4inchlong,butnotexceedingoneinchin length,
andthecrackis locatedatthe endof theflange,proceedasfollows:
(1.) Stopdrillthecrack(specifiedin Chart801).
(2.) Installananglestiffenerof thesamematerial,thickness,heattreat,finish,andsufficient
lengthto pickup twoadditional
rivetsbeyondtheendof thecrack.
NOTE: Bothlegsof theanglemusthavethesamenumberof rivets.Wheninstalling
rivets,usethesametypeandsizeastheexistingrivets.
(c) A flangehavinga crackwhichdoesnotexceedoneinchin length,andwhichis notlocatedat
eitherendof theflange,canbe repairedasfollows:
(1.) Stopdrillthecrackat bothends(specified
in Chart801).
(2.) Installan anglestiffenerof thesamematerial,thickness,heattreat,andfinishasthe
originalflange.Thisstiffenermustbe of sufficient.length
to pickup twoadditional
rivets
beyondtheendof thecrackat bothends.
NOTE: Bothlegsof theanglemusthavethesamenumberof rivets.Therivetsused
mustbe ofthesametypeandsizeastheexistingrivets.
(d) Cracksin flangeshavingfourrivetsor less,mustbe repairedasfollows:
(1.) Cutoff flangeto removethecrack. Replacewithan angleof thesamematerial,
thickness,
heattreat,finish,andcontour.
(2.) Attachrepairanglewithtworivetsin thewebfor everyone rivetin theflange. Rivetsmust
be of the sametypeandsizeastheexistingrivets.
5. Cracksin Flange
(a) A shortcrackin a flangeoriginates
at theflangeedgedoesnotextendbeyondthelinemid-way
betweentheedgeandthebandtangentline,andis morethan2D (twicethenominaldiameter
of therivet)fromthe rivetholes. Donotusethisrepairwithintworivetsfroma splice.
(1.) Stopdrillas specifiedin Chart801.
(2.) Add a patchplateof the samematerialandthicknessastheflange.
NOTE: Radiusonecomerof theplateto providea snugfit intothebendradius.
(3.) Attachplatewiththenumberandsizerivetsshownin Chart802.
NOTE: Thenumbershownis thenumberof rivetson eachsideof thecrack. Shouldthe
crackbe betweenthesecondandthirdrivetfromthe endof theflange,thetwo
endrivetscanbe usedandthenumberwillonlyreferto the rivetsrequiredonthe
remainingside.
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5. Cracksin Flange (continued)
(b) Shortcracksto rivetholesincludethosewithin2Dfroma rivethole.
(1.) Stopdrill(specifiedin Chart801)thosecrackswhichdo notterminateat a rivethole.
(2.) Adda patchplateof thesamematerialandthicknessastheflange. Radiusonecornerof
theplateto providea snugfit intothebendradius.
(3.) Attachtheplatewiththenumberandsizerivetsspecifiedin Chart802.
sizeis
NOTE: Midspaceonerivetthatis onediameterlessthanoriginallyused(minimum
3/32inchdiameter)on eachsideof crackedhole. Maintainedgedistancesand
spacing.
(c) Longcracksoriginateattheflangeedgeandextendbeyondtheflangecenterline,not
extendingintothebendradius.
(1.) Stopdrillthecrackasspecifiedin Chart801.
(2.) Add an angleof thesamematerialandthicknessastheflange.Thelegsof theangle
mustbe of equallength.Thenumberandsizeof the rivetsto be usedarefoundin Chart
802.
NOTE: Bothlegsof theanglemusthavethesamenumberof rivets.If thestopdrilling
producesa doubleline,or if thestopdrillingiswithin2D of a rivethole,adda
rivetonediametersmaller(minimumdiameter3/32inch)on eachside
midspaced
of theaffectedhole.
CHART801
STOPDRILL SIZES
MATERIALTHICKNESS
DRILL SIZE
Up to .032
.040 to .064
.072to .081
#50 (.070)
#40 (.098)
#30 (.129)
CHART802
NUMBER AND SIZE OF AD RIVETSREQUIREDON EACH SIDEOF CRACKS
WIDTHOF FLANGE
UP TO .50 (Inch)
.50 TO .75 (Inch)
.75 TO 1.00 (Inch)
MATERIAL
THICKNESS
RIVET
SIZE
NUMBER
REQUIRED
RIVET
SIZE
NUMBER
REQUIRED
RIVET
SIZE
NUMBER
REQUIRED
UP TO .040 (inch)
3/32
1/8
5/32
3
3
2
3/32
1/8
5/32
4
3
3
3/32
1/8
5/32
5
4
3
1/8
5/32
4
3
1/8
5/32
4
4
1/8
5/32
5
4
.051 TO .064 (inch)
0
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PIPERAIRCRAFT
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6. Cracksin LighteningHoleFlanges
(a) If thecracklengthdoesnotexceedfiftypercentof thedistancebetweentheedgeandthe bend
radiustangentline,thecrackcanbe fairedoutgraduallywitha minimumradiusof inch.
(b) If thecracklengthexceedsfiftypercentof thedistancebetweentheedgeandthebendradius
tangentline,butdoesnotextendintothebendradius,proceedasfollows:
(1.) Stopdrillthecrackasspecifiedin Chart801.
(2.) Add a formeddoublerof thesamematerial,
thickness,andcontourastheweb.
NOTE: Doublerdetailsmustbe asshownin Figure801.
NOTES:
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7. Repairof Crackedor Tom-outDimpledHolesAround GeneratorCoolingScoop
Cracks in dimpledarea of
cowl skin stopdrill per
51-40-00,Chart 801
.098hole ; Countersink
100 X .179 dia. on outside
surfaceof outer cowlskin
(11 places).Matewith
doubler.
Installdoubleron inside surfaceof outercowl skin.
Cowl Repair
Figure802 (Sheet 1 of 2)
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Jan 109051-10-00
Jan 10/90 51-10-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
7.
Repair of Cracked or Torn-out Dimpled Holes Around Generator Cooling Scoop (continued)
7.60
.257 hole (6 places); Dimple
100° X .437 dia. far side.
Mate with existing holes in
cowl skin.
Doubler.025 2024-T3
aluminumsheet
.098 hole(8 places);
Countersink 100° X
.179 dia. nearside.
1.OOR(Typ)
Equallyspacedbetweendimpledholes( 4 places)
NAS1097AD3( 8 places)
double flush on installation
Crackedor torn -out dimpled
holes aroundgenerator
eductor(uppercowl ) and
fresh air inlet(lowercowl).
surfaceof cowl skin
Cowl Repair
Figure802 (Sheet2 of 2)
EFFECTIVITY:
040-999
Jan
51-10-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
8. FuselageRepairs- Pressurized
Section
Wheneverpossible,an insetis providedin the upperpartof thepagewiththe shadedportion
indicatingatypicalareawhererepaircouldbe required.Thematerialto be usedin therepairis
specifiedeitheron theillustration
or in thelowerrighthandsectionof thepage.
51-10-00,Figure604showstypicalbulkheadandchannelcracks.
51-10-00,Chart601 lists item numbers,part numbers,descriptions,referencepages,and actions
requiredif a crack is found during inspection. The requiredinspectionis visual only.
51-10-00,Figure605showstypicalinspection
areaslistedin 51-10-00,Chart601,andwhere
applicable,appliesto bothleftandrightsides.
51-70-00,Figure801showsapprovedrepairmethod.
All items in 51-10-00,Chart601 mustbe inspectedat 30,417 airframeflight hoursfor effectivity
codeA and 12,382airframeflight hoursfor effectivitycode B and repairedif cracksare found.
In addition, items33, 68, and 99 mustbe inspectedat 34,337airframeflight hours for effectivity
code A and 13,978airframeflight hoursfor effectivitycode B.
BulkheadEnd Repair
BulkheadStringer Cut-OutArea Repair
\
ChannelRepair
Forbulkheadandchannelcrackrepair,see FAAAcceptableMethods,Techniques,
and Practices
- Aircraft
InspectionandRepairManual.
Arrowsindicateareasproneto cracking.
CrackTypeIdentification
Figure604
Apr15/91
51-10-00
EFFECTIVITY:
A: 040-044,053, 055, 057, 059
B: 045-052,054, 056, 058, 060-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
9. InspectionItem, Part, Description,Referenceand Action
CHART 601
INSPECTION AREAS
ITEM NO.
PART NO.
DESCRIPTION
REF. PAGE
REPAIR
ACTION
1
2
3
4
5
6
7
8
56642-3
45162-20
45234-14
56284-25
45648-3
45224-2
Bulkhead
Bulkhead
INTENTIONALLY LEFT BLANK INTENTIONALLY LEFT BLANK Bulkhead
Bulkhead
Frame
Bulkhead
19
16
X
X
9
10
11
56243-10
45151-20
45234-2
18
15
20
18/
*17
15
16
18/
*17
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
X
X
X
R-19
R-19
X
X
R-20
R-20
- INTENTIONALLY LEFT BLANK 56076-4
Bulkhead
56796-28
Bulkhead
56068-3
Bulkhead
- INTENTIONALLY LEFT BLANK 56068-3
Bulkhead
56688-14/-10
Bulkhead
56796-24
Bulkhead
- INTENTIONALLY LEFT BLANK 54111-20
Bulkhead
- INTENTIONALLY LEFT BLANK 56507
Bulkhead
56775-48
Stringer
56053-14
Clip
56775-49
Stringer
56053-15
Clip
45086-2
Channel
- INTENTIONALLY LEFT BLANK 56287-18
Bulkhead
19
15
19
X
X
X
19
15
15
X
X
X
15
X
14
*2
14
*2
14
14
X
R-1
R
R-2
R
X
31
32
33
34
35
36
37
38
56036-8
80033-4
56254-2
45150-7
57628-6
15/
*3
*4
14
14
14
*5
R-3
R-3
R-4
R
X
X
R-5
56740-7
56286-20
39
40
56790-3
45191-9
*5
15/
*6
17
17
R-5
R-6
R-6
R
X
-
Bulkhead
Bulkhead
Bulkhead
Bulkhead
Clip
Channel
Bulkhead
Strap
INTENTIONALLY LEFT BLANK Strap
Bulkhead
Clip
Bulkhead
* See 51-70-00
EFFECTIVITY:
040-999
51-10-00Jan
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
9. InspectionItem, Part, Description,Referenceand Action (continued)
CHART601
INSPECTIONAREAS
ITEMNO.
PARTNO.
DESCRIPTION
41
42
43
44
45
46
47
48
49
45203-20
45113-0
45113-0
56507-9
56261-4
INTENTIONALLYLEFTBLANKBulkhead
Channel
Channel
LEFT BLANKINTENTIONALLY
Bulkhead
INTENTIONALLYLEFTBLANKINTENTIONALLYLEFTBLANKBulkhead
50
56770-3
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
Shelf
56297-12
- INTENTIONALLYLEFT BLANKLEFT BLANK- INTENTIONALLY
Bulkhead
46550-4
Bulkhead
46582-2
Bulkhead
56287-19/-22
Strap
56629-2
Skin
56695-3
- INTENTIONALLYLEFTBLANK- INTENTIONALLYLEFTBLANK
- INTENTIONALLYLEFT BLANKSupport
45083-0
Doubler
56511-2
Bulkhead
56261-6
LEFT BLANK- INTENTIONALLY
Bulkhead
56048-14
Bulkhead
56507-2
- INTENTIONALLYLEFTBLANKClip
56053-2
- INTENTIONALLYLEFT BLANKBulkhead
45085-4
- INTENTIONALLYLEFT BLANKBulkhead
45233-0
Bulkhead
45150-3
Bulkhead
45161-2
Bulkhead
56796-28
Bulkhead
56284-13
Channel
45055-5
Skin
56995-2
Skin
56995-2
Doubler
56511-2
LEFT BLANK
- INTENTIONALLY
Clip
REF.PAGE
REPAIR
ACTION
17
14
14
X
R
R
14
X
19/
*7
15/
*8
*10
R-7
R-7
R-8
R-8
R-11
20
20
15
*5
*9
X
X
X
R-5
R-9
14
*9
19
R
R-10
X
14
14
X
X
14
X
14
R
18
14
19
15
15
*11
*12
*12
*12
X
X
X
X
X
R-12
R-13
X
R-14
See 51-70-00
EFFECTIVITY:
040-999
51-10-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
9. InspectionItem, Part, Description,Referenceand Action (continued)
CHART601
INSPECTIONAREAS
ITEM NO.
PARTNO.
83
45112-1
Channel
84
-
85
86
56642-3
45151-20
87
88
89
-
90
91
92
93
94
DESCRIPTION
Bulkhead
Bulkhead
Beam
Channel
Bulkhead
Frame
Skin
INTENTIONALLY LEFT BLANK INTENTIONALLY LEFT BLANK -
98
-
INTENTIONALLY LEFT BLANK -
99
100
101
56507-10
45085-4
70456-2
Bulkhead
Frame
Skin
102
103
104
45112-1
45113-0
70456-3
Channel
Channel
Skin
105
106
45150-3
70226-3
Bulkhead
Bulkhead
56507-6
X
19
16/
'13
R
R-15
R-15
*14
*15
*16
18
*18
R-16
R-17
R-18
R
R-21
Bulkhead
18
X
18
18
18/
*9
18
18
18/
*9
18
18
X
R
R-9
R-9
X
R
R-13
R-13
X
X
18
X
- INTENTIONALLY LEFT BLANK -
107
108
14
INTENTIONALLY LEFT BLANK INTENTIONALLY LEFT BLANK INTENTIONALLY LEFT BLANK -
-
97
REPAIR
ACTION
INTENTIONALLY LEFT BLANK -
56269-20/-21
45160-0
56296-3
46678-3
56695-2
95
96
REF.PAGE
45203-13
Bulkhead
R-X
R
X
RepairNumber
ReplacePart
Stop Drill EndOf Crack(Ref. Chart801 For Hole Diameter)
*See 51-70-00
EFFECTIVITY:
51-10-00Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
9. InspectionItem,Part,Description,
Reference
andAction (continued)
(a) FuselageUpperCabinSection
LEGEND
A = BULKHEADSTRINGER
CUTOUT
= BULKHEADEND
= CHANNEL
TypicalInspection
Areas
Figure605 (Sheet1 of 7)
14 51-10-00
PAGE
10/90
Jan
EFFECTIVITY:
040-999
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
andAction (continued)
Reference
Item,Part,Description,
9. Inspection
LowerForwardFrame
(b) Fuselage
LEGEND
A = BULKHEADSTRINGERCUTOUT
O = BULKHEADEND
= CHANNEL
TypicalInspectionAreas
Figure605 (Sheet2 of 7)
EFFECTIVITY:
040-999
15
PAGE
51-10-00
10/90
51-10-00Jan
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
9. InspectionItem,Part,Description,
Reference
andAction (continued)
(c) FuselageLowerCenterFrame(F.S.135.00to 174.00)
I
3
LEGEND
A = BULKHEAD STRINGERCUTOUT
O = BULKHEADEND
51-10-00
Jan10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
9. Inspection
Item,Part,Description,
Reference
andAction (continued)
(d) FuselageLowerRearFrame(F.S.174.00to 215.00)
LEGEND
A = BULKHEAD STRINGERCUTOUT
O = BULKHEADEND
= CHANNEL
TypicalInspection
Areas
Figure605 (Sheet4 of 7)
EFFECTIVITY:
040-999
51-10-00 Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Tralner)
MAINTENANCEMANUAL
andAction(continued)
Reference
9. InspectionItem,Part,Description,
(e) FuselageAft Section(F.S.215.00to 280.00)
Item101
LEGEND
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
9. InspectionItem, Part,Description,Referenceand Action (continued)
(f) FuselageAft Section(F.S.280.00to 334.00)
4
Item
A1 BItem85
LEGEND
A = BULKHEADSTRINGERCUTOUT
O = BULKHEADEND
= CHANNEL
TypicalInspectionAreas
Figure605 (Sheet6 of 7)
EFFECTIVITY:
040-999
51-10-00 Jan
Jan 10/90
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
9. InspectionItem, Part, Description,Referenceand Action (continued)
(g) FuselageFloorboard
Installation
andCabinDoorEntrance
CabinDoorEntrance
Item 55
LEGEND
= BULKHEAD STRINGERCUTOUT
O = BULKHEAD END
= CHANNEL
TypicalInspection
Areas
Figure605 (Sheet7 of 7)
EFFECTIVITY:
040-999
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Processes
1. SealingProcedures
(a) Sealingof NacelleFuelTank
The followingproceduresmust be usedfor repairingleaksin the nacellefuel tank. Usingthe
specifiedmaterialsallowsthe leastamountof aircraft down time during repair.
(1.) SurfacePreparation
(a.) In areaswhere the originalsealanthas been scratched,gouged,or otherwise
damaged,removedamagedsectionof fillet with a sharp plexiglasscraper. Taperall
cuts in the old sealantat a 45° angle.
(b.) The originalsealantin the fuel tankwill be fuel soaked and mustbe dried in the repair
area. Use a vapor-proofheat lampor hot air blower.
(c.) Thoroughlyclean all areasto be repairedwith solventsuch as methylethylketone
(MEK). A progressivecleaningproceduremustbe used. Washa small area at a
time and dry with a cleancloth beforethe solventevaporatesto preventredeposition
of the oil, fuel, etc, on the surface. Alwayspour solventon washingcloth to maintain
a clean solventsupply. Do not use reclaimedsolvents.
WARNING: DO NOT ALLOWALODINESOLUTIONTO COME IN CONTACTWITH
HANDS,EYESOR CLOTHING.
(d.) Checkdamagedareafor other repairswhich haveto be made beforeapplyingnew
sealant. Re-alodinealuminumsurfaceswherethe original alodinecoatinghas been
removed. Apply alodine1200solution(undiluted)to affectedarea with a small nylon
brush. Allow solutionto dry until a light goldencolor appears. Whena coating has
been formed, removeexcesssolutionby wiping with a cleanwater moistenedcloth;
wipe dry.
(e.) Just prior to applicationof PR-1435-Gsealant,the affectedarea must be recleaned
with MEK (per instructiongiven in step (c.)).
(2.) MaterialPreparation
WARNING: PR-1435-GSEALANTCONTAINSFLAMMABLEAND VOLATILE
SOLVENTS.KEEPSEALANTAWAYFROM HEAT,SPARKSAND FLAME.
USE PROPERPRECAUTIONSWHENAPPLYINGTHIS SEALANT.
WARNING: AVOIDALL CONTACTOF SEALANTWITHYOURBODY,ESPECIALLY
CONTACTWITHOPENBREAKSIN THE SKIN. POLYETHYLENEMITTS
MUSTBE USEDAND HANDSWASHED,BEFOREEATINGOR SMOKING.
(a.) PR-1435-Gis a two-partpolysulfidesealantwhich,when mixed,has a short
applicationlife (15 minutesat 75°F and 50% relativehumidity). For every10°F rise in
temperature,the time is reducedin half. For every10°Fdrop in temperature,the time
is doubled. High humidityat time of mixingalso shortensthe applicationlife.
Usingpremeasuredkits, mixthe acceleratorwith the PR-1435-Gbase compound.
The mixingratio is 7.5 partsbase compoundto 1 part acceleratorby weight. Slowly
mix acceleratorinto basecompoundby hand until a uniformgray-greencolor is
obtained.
EFFECTIVITY:
040-999
51-20-00
51-20-00
1
Jan 109PAGE
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Processes (continued)
1. SealingProcedures (continued)
(3.) List of Materials
(a.) SealantMaterial- PR-1435-G(See 91-00-00)
(b.) Solvent- Methylethylketone(MEK)
(c.) AlodineSolution1200
(d.) Small nylon brush
(e.) Cleanwhitegauze pads (4 inch square)
(f.) Filletfairingtools (Referto 91-00-00)
(4.) SealantApplication
(a.) Apply the sealant 0.125to 0.187 inch thick to repairarea with spatulaor a paddle
shapedtool. Firmlypress sealantin placeand form intodesired shape.Lap new
sealantover old existingsealant0.125to 0.25 inch.
(b.) Allow sealantto cure until stiff.
This sealantcuresto an acceptablehardnessin approximately16 hoursat 75°F and
50% relativehumidity. Cure is hastenedwhen applyingheat up to 130°F.
NOTE: Nacellefuel tanks can be filled with fuel one hour after applicationof sealant.
The cure does not dependon exposureto air or elevatedtemperatures,and
will seal even whencombinedwith fuel, withoutaffectingsealingefficiency.
(c.) After all sealant hasdried, proceedas follows:
1 Plugall tank openingswith temporarycaps and gaskets.
Installa modifiedfiller cap, (shownin 91-00-00),whichacceptsan air hose
2
fitting.
Apply 2 psi (55 inchesof water) closedcircuit air pressureintotank.
3
Allow pressureto stabilize(normallythe air pressurewill drop slightly). When
4
pressurestabilizes,returntank pressureto 2 psi (55 inchesof water) and hold
this pressurefor 5 minutes. Therewill be no decreaseof pressureduringthis
time, as indicatedby the manometer.
Nothingless than a perfectseal is acceptable.
5
Checkall externalseams and rivets for leaks. Use a non-corrosiveleak
6
detectingsolution.
(b) FuselageSealing
Special sealingcompoundsare usedto seal sectionsof the aircraft against leakageof
pressurizedair. This sealingis done during construction.Any air leakagethroughoutthe
pressurizedfuselagecan normallybe detectedwhile carryingout the fuselagepressurecheck
in 21-30-00.
EFFECTIVITY:
Jan
10/90
Jan 10/90
51-20-00
51-20-00
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Processes (continued)
1,3,A
.
1,2,3
.1,2,3
1,2,3
View A
ForwardPressure
Bulkhead
TubeAssembly
Bulkhead
TubeAssembly
SealingMethods:
1. FayingSeal (NoteA)
3
3. Brushcoat
with "A" TypeSealant
: SPECIALINSTRUCTIONS
View A
F,Fayingsealwill be appliedto tube
flange and mating surface on
bulkheadpriorto assembly.
A. Use RTV 88 with RTV9811catalyst.
B. Use faying seal method for window
doublerall aroundwindowopeniing. Do
not use class "A" sealant.
C. Seal area beforeinstallinginner skin.
D.All skin laps in pressure area must
havefaying seals.
E. Use brushcoat as well as faying seal
methodon areaswhere skinsslide into
final position.
F. Brushcoat bulkhead TV skin flanges,
particularly at pressure bulkheads.
Make sure all "Seal Plates" stringers,
bolts, and rivetsare sealedproperly.
G.Apply glass cloth (Type 101) coated
with sealant.
FuselageSealing(Forward)
Figure201
EFFECTIVITY:
040-999
51-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Processes(continued)
1,2,
1,3 1,E,F
B.Use faying seal method for
windowdoublerall aroundwindow
opening. Do not use class "A"
sealant.
C.Seal area before installinginner
skin.
D.All skinlapsin pressureareamust
havefayingseals.
E. Use brushcoatas well as faying
sealmethodon areaswhereskins
slideintofinalposition.
F.Brushcoat bulkhead TV skin
flanges,particularlyat pressure
bulkheads.Make sure all "Seal
Plates"stringers,bolts,andrivets
aresealedproperly.
G.Apply glass cloth (Type 101)
coatedwithsealant.
FuselageSealing(Aft)
Figure202
EFFECTIVITY:
040-999
51-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Processes (continued)
1. SealingProcedures (continued)
(b) FuselageSealing (continued)
(1.) Surface Preparation(Figures201 and 202)
WARNING: WHEN USINGTHESECLEANINGSOLVENTSIN A CLOSEDAREA,
FORCEDVENTILATIONMUSTBE USEDTO PROTECTPERSONNEL
FROMTOXIC FUMES.
All parts to be sealedmustbe thoroughlycleaned.Methylethylketone(MEK)or aliphatic
naphthaare recommendedcleaningagents.
NOTE: Aliphaticnaphthais preferablesince it does not damagepaintedsurfacesor
acrylicplastic(plexiglas)windows.
(a.) All parts,sub-assemblies,and assembliesto be sealedmust be alodinedand primed
with zinc chromate,exceptpressurizedair ductwork, airboxes,etc,which are
alodinedonly.
(b.) Removeall filings, chips,loosedirt, and otherforeign objectson surfacesto be
sealedby forced air,or vacuumcleaningand brush.
(c.) Cleanall surfacesor voidsto be sealed,to removeall fingerprints,oil, or grease. To
clean,wipe affectedareaswith naphtha;use a clean, cottoncloth. Toprevent
redispositionof contaminantson surface,the cleanedsurfacesshould be wipeddry
immediatelyand not allowedto air dry.
(d.) It is essentialthat only clean clothsbe used for cleaning. When a cloth becomes
soiled,it must be cleanedor discarded.To avoidcontaminationof cleaningsolvent,it
mustbe pouredon the cloth. Repeatcleaningproceduresaboveuntil no
contaminatesare left on surfacesto be sealed.
NOTE: The importanceof propercleaningprior or applyingsealantcannotbe over
emphasized. Sealantwill not adhereproperlyto dirty,oily surfaces.
(2.) Material Preparation(Figures201 and 202)
Sealant manufacturerinstructionsmustbe followedexactlyfor both mixingand storageof
sealants.
Mix only enoughsealantneededfor the job. The applicationlife of A-2 and B-2 class
sealantsis two hours at 75° Fahrenheitand 50 percentrelativehumidity. For every 10°
temperaturerise, applicationlife is reducedin half;for every 10° drop in temperature,
applicationlife is doubled. Increasedhumiditydecreasesapplicationlife, and decreased
humidityincreasesapplicationlife.
°
The applicationlife of A-1/2class sealantis 1/2 hourunderthe same75 Fahrenheitand
50 percentrelativehumidity.
NOTE: Use care when mixingsealantto avoidgettingair intothe sealant.
EFFECTIVITY:
51-20-00
51-20-00Jan10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Processes(continued)
1. SealingProcedures(continued)
(b) Fuselage
Sealing(continued)
(3.) Listof Equipment(Figures201and202)
or SemcoNo.385Automaticor equivalent.
(a.) Mixers- SemcoNo.285 Portable,
withMIL-S(b.) Cartridges
- SemKitNo.6502 1/2ouncesand6 ouncesproportioned
ClassB sealantsonly.
7502or MIL-S-8802
ClassA sealantsonly(5fluidounces).
or MIL-S-8802
(c.) Halfpintkitsof MIL-S-7502
(d.) Airpoweredsealantgun(SemcoNo.250-6withextraretainersfor 2 1/2ounce
cartridgesor equivalents).
(e.) Assortednozzlesfor sealantgun.
(f.) Extensionfor sealantgun.
(g.) Solventdispensers
(polyethylene
squirtbottles).
(h.) Clean,white,cottoncloths.
(i.) Stiffbristlebrush(notnylon).
withcoversfor cleaningnozzles,tools,etc.
(j.) Solventcontainers
(k.) Filletfairingtools.(Referto 91-00-00.)
NOTE: Equipmentlistedis commerciallyavailablefrom vendorsshownin the List of
ConsumableMaterials,91-00-00.
(4.) Listof Materials(Figures201and202)
Only the followingmaterialsare to be used:
(a.) Sealants- MIL-S-7502or MIL-S-8802- ClassesA-1/2,A-2, B-2, B-4, B-6, and B-8.
(b.) Sealantmaterial- 3M - E.C. 1239.
(c.) Sealantmaterial- G.E.-SS-4404Primer.
(d.) Sealantmaterial- G.E. RTV88 with RTV9811 catalysts.
(e.) Sealantmaterial- PRC - PR 1422 (MIL-S-8802)and PR 1221(MIL-S-7502).
(f.) AluminumWool - Fine.
(g.) ReleaseAgent- PolyvinylAlcohol.(PVA.)
(h.) CleaningSolvents- Methylethylketone(MEK)or AliphaticNaphtha.
availablefromvendorsshownin theListof
NOTE: Materialslistedare commercially
91-00-00.
Materials,
Consumable
(5.) SealantApplication(Figures201and202)
of sealingmustbe observed:
Thefollowingsequence
whichare
priorto installation,
andsub-assemblies
(a.) Sealfayingsurfacesof assemblies
notaccessible
later.
(b.) Sealjoggles,holes,cutout,andanyothergaps.
(c.) Sealremainingseamsandjoints.
(d.) Sealbolts,screws,nuts,andotherfasteners.
(e.) Sealelectricalharness.
(f.) Sealformedin placegaskets.
NOTE: All sealingis doneon thepressuresideof the sealplane.Thisassuresthe
pressurewill helpholdsealin place.
EFFECTIVITY:
040-999
Jan 10/9051-20-00
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Processes(continued)
1. SealingProcedures (continued)
(b) FuselageSealing (Figures201 and 202) (continued)
(6.) SealingFayingSurfaces (Figure203)
Typicalparts requiringsealingprior to assemblyare bulkheadstationsextendingbeyond
the seal plane,betweenbulkheadstations57.0 and 332.0 inclusive,angles and skin joints
behindbox bulkheads,stringers,windshields,and windows.
NOTE: The PA-42-720floor panelsare not sealed,but are within the pressurevessel.
Type B-2 class sealantmustbe used. Applya liberal amountof sealantto eachmating
surfaceof the applicableparts. Assembleand securecomponentstogetherbefore
sealantdries. If specificcomponentsrequireriveting,the componentsmust be riveted
togetherwhile sealantis still wet. If permanentfasteningis not possibleat the time,
temporaryfastenersmust be used in at least 50% of the holesto be riveted.
NOTE: Sufficientsealantmustbe appliedto ensure a continuousextrusionon both sides
of the joint after assemblyof the faying surface. (Figure203) Permanent
fastening is requiredbeforework life of sealant has expired. A sandblasted
buckingbar mustbe usedto performthe rivetingoperation.
Allow class B-2 sealantto fully cure for 48 hours at 75°F and 50% relativehumidity.
(7.) SealingJoggles (Figure204)
Sealjoggles by completelyfilling them with class B-2 sealant. Apply sealantwith a
pressureapplicator,forcingthe sealantunderthe joggle from either side until it begins
extrudingon the oppositeside of the joggle.
(8.) SealingHolesand Voids (Figure205)
Voidsare defined as gaps betweenairframememberswhichpresenta direct opening
through the pressurevesselstructure. Suchgapsoccur at stringercutouts in the pressure
bulkheads,formingreliefsand flanges. Holesand voidswhich are less than 0.125 inch
wide mustbe filled with sealant,buildingup a bead with a minimumthicknessof 0.062
inch. If the gap is largerthan 0.125 inch wide,use a mechanicalclosuresuch as a soft
rivet, a screwand washer. If rivets are used,be sure to brush coat both sideswith class
A-1/2 sealant.
(9.) Holes and Voids in (Cold)Air DuctWork (Figure205)
Sealingin this area preventsair noisesand eliminatesundesirable,uncontrollabledrafts.
Apply sealantto any holes andvoids less than 0.125 inch wide. Apply3M 471 plastic
tape on insideor outsidesurfaceof any holes and voids largerthan 0.125 inch.
EFFECTIVITY:
040-999
51-20-00Jan
PAGE
7
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Processes(continued)
FayingSeal BetweenSkins at Skin Lap
Skin
an 10/90
Skin
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A. Processes (continued)
1. Bulkhead
2. Fayingseal
3. Stringer
4. Skin
5. Stringerseal plate
6. Brush coat with
Class A-1/2sealant
7. Fillet seal
8. Bulkheadcutout
9. Fuselageskin
10. Faying seal at
forward bulkheads
between skin and
stringer
11. Bulkheadflange
12.Screw
13.Seal plane (skin,
bulkhead,etc.)
14.Large hole (greater
than .125")
15.Nut
16.Washer
SEALING
STRINGERS
Pressure Side
14
SEALINGHOLES
Stringers,Holes and Voids Seals
Figure205
Apply Sealantwith FlowGun
D
ViewA
Application
of FilletSeal
View C
Dimensions
PressSealantinto Place
with FairingTool
D = 0.10" Min.
W = 0.20" Min.
A + B = W, Except A = 0 when
B = 0.20"or More
ViewB
Formingof Fillet Seal
FilletSeal
Figure206
EFFECTIVITY:
040-999
51-20-00an10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A. Processes(continued)
1. SealingProcedures(continued)
(b) FuselageSealing(continued)
(10.)SealingSeamsandJoints (Figure206)
Filletsealsmustbe usedalongedgesof all structuresrivettedto theskinin the
pressurized
area,suchasframes,stringers,doublers,laps,seams,andjoints. Apply
sealantwitha pressuregunandbe sureto avoidgettinggapsorbridgesalongthe seam
joint. Finaldimensions
of a crosssectionof beadmustconformto thoseshownin Figure
206.
CAUTION: ENSUREPRESSUREGUN CONTAINSENOUGHSEALANTTO
COMPLETEA SEALAT ONE INJECTIONWITHOUTANY BREAK.
STOPPINGAND STARTINGCAUSESAIR BUBBLESIN SEALSAND WILL
PRODUCEA POORSEAL.
(11.)SealingFasteners(Figure207)
Sealall fastenersinstalledin a sealplanebyfilletingaroundfasteners,afterinstallation,
witha coatof B-2classsealant.
NOTE: Ifa boltor nutisbeingsealed,it mustbe torquedbeforesealantsset. Tightening
aftersealantsetsis notrecommended.
(12.)Sealing
"AN"StandardBulkhead
Fittings
SealANfittingspassingthroughpressureplainof thebulkheadby cleaningaroundseal
area. Applysealantto insidesurfacearoundthe holeandinstallthefittingbeforethe
sealantsets.
0.06"
Bolthead
.005 to .015'
BoltsandRivetsSeals
Figure207
EFFECTIVITY:
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A Processes(continued)
1. SealingProcedures(continued)
(b) FuselageSealing(continued)
withsealingcompound(Figure208)
ElectricalHarnesses
(13.)Sealing
are
Thesestepspertainto themainfuselageandwingharnessonly. Thewireharnesses
sealedat thepointwheretheypassthroughthepressurebulkhead.
(a.) Cleanareaof bulkheadwheresealfittingswill seal.
(b.) Passwirebundlethroughholeprovidedin bulkhead.
(c.) Placesealfittinghalvesaroundwireharness,on pressuresideof bulkhead.
flangeof thefittinghalveswith sealant.(Referto viewA of
(d.) Fillgroovein mounting
Figure208.)
NOTE: Use enoughsealantto assureit extrudesaroundthe mountingflange after
securingthem to the bulkhead.
(e.) Securefitting to bulkheadwith fasteners.
(f.) Filletseal extrudedsealantaroundsidesof mountingflange (shownin view B of
Figure208).
(g.) Put nozzleof sealantgun in centerof wire harnessand work sealantthroughoutwires
insidesealfitting (shown in view C of Figure208).
(h.) Placea strongpiece of stringagainstthe seal assembly,parellelwith the wires.
(Referto view D of Figure208.)
(i.) Wrap fitting halveswith threeturns of 1.50 inchwide maskingtape. (Referto view D
of Figure208.)
(j.) Crimpwide maskingtape aroundseal assemblyto centerwire harness.
(k.) Wrapcrimpedend with three turnsof 0.750 inch maskingtape. (Referto view D of
Figure208.)
(I.) Puncturemaskingtape over mostconvenientinjectionhole in sealfitting. Inject
sealantwith pressuregun.
(m.) Apply sealantover seal fittingfasteners(explainedin FuselageSealing).
(n.) Removetape after sealanthascured (16 to 24 hours)by pulling rip string and
unwindingtape.
(o.) All other electricalharnessesandwires use O-ringtype pressureseal bulkhead
connectorsper MIL-C-5015or Dura-Gromtype seals.
withheatshrinkablecoverings(Figure208)
ElectricalHarnesses
(14.)Sealing
sealsusedto sealthewiringharnessat thepressurebulkheadareheat
Thefeed-through
coveringsmadeof variousplasticandelastomercompounds.Theyare
shrinkable
sizeandshape.
form,whenheated,shrinkto a predetermined
suppliedin expanded
asfollows:
ofthesesealsisaccomplished
Installation
required:
(a.) Equipment
Thermogun
heatingtool ModelCV-5000,Model500A.
1
P/N991023).
HeatreflectorTG-24(Raychem
2
seals.
feed-through
3
Pressure
uponinstallation.TypeA
NOTE:Twotypesof nutsmaybe useddepending
nutis pressedintoopeningin thebulkheadfromthesamesidethatthe
sealwillbe installed.TypeB nutis installedfromthe
feedthrough
seal.
bulkheadsideoppositethefeedthrough
EFFECTIVITY:
040-999
0 00 Jan
PAGE
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51-20-00
10/90
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A Processes(continued)
1. SealingProcedures(continued)
Fitting Halves
FilletExcessSealant
After Installation
of FittingHalves
View B
View C
MaskingTape
1-1/2"Width
String
MaskingTape
3/4" Width
WireHarnessSeals
Figure208(Sheet1 of 2)
EFFECTIVITY:
040-999
Jan 10/9051-20-00
PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A
Processes (continued)
1. Sealing Procedures (continued)
NOTE:
RecoverableEnd.Apply Heat in ThisArea
Type "A'Nut
O-Ring
Coating
End View
Side View
PressureBulkhead
Type Nut
Type"B" Nut
PressureBulkhead
HeatReflector
Type "A" Nut Installation
3
3
PressureBulkhead
Type "B"Nut Installation
Wire HarnessSeals
Figure208 (Sheet2 of 2)
EFFECTIVITY:
040-999
51-20-00 PAGE13
51-20-00
Jan 10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
A Processes (continued)
1. SealingProcedures (continued)
(b) FuselageSealing (continued)
(14.)SealingElectricalHarnesseswith heat shrinkablecoverings (Figure208) (continued)
(b.) Installation.
1
Installnut (type A or B) in the pressurebulkhead.
2
Insertwire or cablethroughfeedthrough,
3
EnsureO-ring is positionedin groove of feedthrough. Screwfeedthroughinto
nut. Tightento approximately(10) foot poundstorque.
4
Using recommendedheatingdeviceand heat reflector,apply heat to
recoverableend of feedthroughseal. (Shownin Figure208.1
5
After shrinking,inspectto ensureneck of feedthroughis generallyroundedand
has uniformwall thickness.
(15.)Applicationof ReleaseAgent
Edges and faying surfacesof removableor hingedpanelsmust receiveat leasttwo.coats
of releaseagent (PolyvinylAlcoholPVA)appliedapproximately0.50 inch wider thanthe
matingflange properto sealantapplication. The panelmust be allowedto air dry between
coats. Only removablecovers requiringa formed-in-placegasket receivean applicationof
release agent. Sealantmust be appliedto preparedsurfacewithin 2 hours after
completionof surfacepreparation. Surfacesnot sealedwithinthis time mustbe prepared
again.
CAUTION: DO NOT USE POLYVINYLALCOHOLAS A RELEASEAGENTNEAR
ACRYLIC(PLEXIGLAS)WINDOWS.IT WILL CRAZEACRYLICPLASTICS.
(16.)SealingFormed-in-PlaceGaskets
NOTE: This type of seal is usedon the radomelock handlecover of the airplane.
Unlessotherwisespecified,apply heavybead of classB-2 sealantto matingsurfacesnot
coated with a releaseagent. Spreadevenlyuntil coatingis approximately0.062 inch
thick. While sealant is still fluid, secureaccesscoverand smoothexcesssealantflush
with top of cover. Allow to fully cure for 48 hours at 70°F and 50% relativehumidity.After
curing, trim excesssealantfrom aroundcover;pry one comer of panel open, usingcare
not to damagethe gasket. Slowlyfree the rest of panel. Removeall releaseagentand
excess sealantfrom paneland matingsurface.
NOTE: Releaseagentscan be removedwith water.
NOTE: Do not pressuretest the fuselageuntil sealingcompoundhas thoroughlycured.
(17.)Removalof Sealant
When it is necessaryto removefilletsor beadsof sealantdue to reworkor repair,scrape
sealant off with scrapersmade of hardwoodor plexiglas. Removeonly major portionof
fillets or beads. After rework,clean, resealand test the areafor leaks.
(18.)EquipmentCleanup
Clean equipmentwithin 3 hours after exposureto roomtemperatureusingnaphtha,
Methylethylketone,or Toluolas a cleaningagent.
EFFECTIVITY:
PAGE14 51-20-00
Jan
51-20-00
10/90
040-999
PIPERAIRCRAFT
PA-42-720(AdvancedTrainer)
MAINTENANCEMANUAL
A Processes(continued)
2. Avionicsand ECU Bay DoorSealing
(a) Avionicsand ECUBay DoorSeals Removal
1. Apply mineralspiritsto seal to loosenadhesive. Usinga plastic scraperor other
appropriateinstrument,scrapeoff seal while applyingmineralspirits,as necessary,to
dissolveadhesive.
2. With seal removed,use a cleancloth and mineralspiritsto removeall excessadhesive.
(b) Avionicsand ECU Bay DoorSeals Installation
1. Cleandoor frame using a clean cloth and Prep-Sol,or a similarcleanerwhich will not
leave an oily residue.
2. Orientsealson the frame as follows. Mark the seal matingsurface:
(a) Aft - 56598-06
(b) Top- 56598-07
(c) Forward- 56598-08
(d) Bottom- 56598-09
3. Coat seal matingsurfacesand the bay frameface with 3M 1300Lcontact cement. Allow
to dry 15 minutes.
4. Installseals in their appropriatelocations.
(c) Avionicsand ECU Bay DoorCamloc FastenersSealing
Sealcamlocfastenerreceptacleson backsideof the bay frame as follows (refer to Figure209):
1. Apply PRC 1221 Type B-2 sealantaroundreceptacleperimeter,over rivet buckedtails,
and around baseof the receptacle'scenterpart.
2. Slip a sleevecap over center part of receptacle.Seat it firmly in sealantaroundbase.
Allow to cure properly.
3. Seal receptacleholes in the face of the baydoor frame. (Shownin Figure209)
Seal all seams
betweenskinsand
betweenskin and
Sealant
Sleeve
Cap
Receptacle
Door Frame
Avionicsand ECU Bay DoorSealing
Figure209
EFFECTIVITY:
040-999
51-20-00
Jan
10/90
PIPERAIRCRAFT
PA-42-720(Advanced Trainer)
MAINTENANCEMANUAL
Fasteners
A. Rivet Replacement
WARNING: UNDER NO CIRCUMSTANCES CAN A RIVET BE REPLACED WITH ONE OF LOWER
STRENGTH.
Wheneverpossible,rivetsmust be replacedwith the samesize and strengthoriginallyspeci">