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THE
cherol-lee ARCHER
PILOT'
S
OPERATING MANUAL
_,, ··~--
~ -·
· ·•
BV
" ~ · ~ l _
_ /
This manual is incomplete without an APPROPRIATE FAA APPROVED AIRPLANE
FLI
GH
T MANUAL and an APPROPRIATE WEIGHT AND BALANCE REPORT.
28-7505222 N1185X
,~~~PR75UTZff~~
1-20-75
TABLE OF CONTENTS
GENERAL SPECIFICATIONS
DESCRIPTION
&
AIRPLANE
MANUAL
EMERGENCY PROCEDURES
WEIGHT AND BALANCE
LOADING INSTRUCTIONS
OPERATING INSTRUCTIONS
OPERATING TIPS
PERFORMANCE CHARTS
HANDLING AND SERVICING
APPLICABILITY
This manual is applicable to Piper Model PA-28-180 aircraft having serial
28-7405001 through 28-7505259. Contact Piper Customer Services for specific information on the application of this manual.
REVISIONS
The information in the Pilot's Operating Manual will distributed to the airplane owners. material will consist of necessary to manual and/or to add information to cover added airplane
I. Revisions current revisions the text
L
II. Material of
Black lines will current revisions with changes and text and illustrations. Changes in capitalization, location of material on a page will not be identified by symbols.
Ill. Original Pages Issued
The original pages issued for this manual prior to revision are given below:
1-1 through 1-3, 2-1 through 2-18, 3-1 through 3-18, 4-1 through 4-6, 5-1 through 5-27,
7-1 through 7-10, 8-1 through 8-2, 9-1 through 9-10, 10-1through10-15.
iii
OPERA TING MANUAL LOG OF REVISIONS l iv
0
7-11
7-12
8-1 ii
Air Conditioner
Airplane Performance.
Added
Added page.
Revised item 6.
Added PAC Approval Form.
Added Applicability and Item III. ... nii;u••'"
Pages Issued.
Added l to
Rev. 2 to
AIRCRAFT DELIVERED WITH
MANUALS PRIOR TO THIS REVISION
DO NOT REQUIRE THIS REVISION.)
2-9a l
2
6
AF/M
W/B
7-4
8-1
Added footnote.
Added page (added material from page 2-8).
Relocated page (Alternator-Starter
Schematic).
Added page (Alternator-Starter Schematic).
Added Annunciator Panel information and footnote.
Revised Instrument Panel illustration.
Added Seat Removal instructions.
Added Rev. 2 to Report: VB-558.
Added Rev. 3 to Report· VB-547.
Added Annunciator Panel check to Warmup and Ground Check; added footnote.
Revised item 6; added footnote.
Relocated material from page 8-1.
PILOT'S OPERATING MANUAL LOG OF REVISIONS (1.:ont)
Revi'iion
Rev. 3 (cont)
Rev. 4 - 761 556
(PR750120)
Revised
Pages
Description Da tl'
9-i
9-2
9-3
9-4
9-5
9-6
9-7
9-8
9-9
9-10 l 0-11
Revised Performance Charts Index.
Revised Takeoff Chart.
Revised Climb Chart.
Revised Range Chart.
Revised Engine Chart.
Revised Airspeed Chart.
Revised Stall Speed vs Weight Chart.
Revised Stall Speed vs Angle of Bank Chart.
Revised Glide Chart.
Revised Landing Chart.
Revised Battery Service.
1-2
2-1
Added 0-360-A4M engine designation and Jan. 20, 1975 footnote.
Added 0-360-A4M engine designation and footnote.
AF/M Added Rev. 3 to Report: VB-558.
W/B Added Rev. 4 to Report: VB-547.
7-4 Added new item 9.; revised existing item nos. under TAKEOFF.
7-8
8-2
I 0-8
Revised EL T info.
Added item 11.
Added 0-360-A4M engine designation under Oil Requirements.
Rev. 5 - 761 556
(PR751121)
Re\.6-761556
(PR 790326) iii l - l
Added concluding ser. no. to Applicability. Nov. 21, 1975
Revised Cruise Speed and Range figures; revised Empty Weight and Useful Load;
1-2 deleted footnote.
Deleted footnote.
2-1 Revised Airframe info; deleted footnote.
A F/M Added Rev. 4 to Report: VB-558.
W/B Added Rev. 5 to Report: VB-54 7.
8-1
9-4
Revised item 8 (Fuel Warning Tip).
Revised Cruise Performance - Range chart.
9-6 Revised Cruise Performance - True
Airspeed chart.
2-8
2-8a
2-14
WiB
Added Warning.
Added info.
Added Caution.
Added Rev. 6 to Report: VB-547.
7-2 Revised items.
7-8, 7-9 Revised ELT info.
March 26, 1979 iv-a
OF REVISIONS
Date
March 16,
CHEROKEE ARCHER
GE'NERAL SPECIFICATIONS
PERFORMANCE
Published conditions at sea from published are for standard airplanes flown at gross weight under standard unless otherwise stated. Performance for a specific airplane may vary depending upon the equipment installed, the condition of engine, airplane equipment, atmospheric conditions and piloting technique. Each performance figure below is subject to the same conditions as on the corresponding performance chart from which it is taken in the Performance Charts Section.
Takeoff Ground Run, 25 ° flaps, sea level (ft)
Distance Over 50-ft Obstacle, 25° flaps, sea level (ft)
Best Rate of Climb Speed (mph)
Rate of Climb (ft per min)
Best Angle of Climb Speed, sea level (mph)
Max sea level (mph)
Optimum Altitude 9300 ft, 75'Yo power (TAS) (mph)
(
(ft) at best power mixture (mph) power. 2,800 ft power. 14,000 ft
Range at best power mixture (mi)** power, 9300 ft power, l 2,800 ft at best economy mixture (mph) power, 9300 ft power, 12,600 ft
Range at best economy mixture (mi)** pOWl.)L
9300 ft
12.600 rt down (CAS) (mph)
Landing up (CAS) (mph) sea level, flaps down (ft)
Distance Over 50-ft Obstacle, sea level (ft)
720
1625
85
725
76
148*
141*
14,150
16,500
132*
125*
705
131*
123*
715
774
61
11
68 are with optional wheel fairings installed. Subtract 3 mph if wheel
WEIGHTS
Gross
Standard I Wl'iglil (lbs)
Maximum Useful Load (lbs)
2450
1404
1046
GENERAL SPECIFICATIONS
REVISED: NOVEMBER 21, 1975 1-1
O-J60-A4A
I 00
6.00
(i.()()
32' 2.50"
. /
24' 00"
12' I0.511"
30"
63"
DESCRIPTION
AND
2-15
6
THE AIRPLANE
DESCRIPTION
AIRPLANE AND SYSTEMS
CHEROKEE ARCHER defrosting.
AIRPLANE AND
SYSTEMS
REVISED: NOVEMBER 2t, 1975 propeller is
2-1
2-2
Main Wheel Assembly
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
C HEROKEE ARCHER
2-4
Console
FLIGHT CONTROLS
Dual controls are provided as standard equipment , with a cable system used between the controls and the surfaces. The horizontal tail (stabilator) is of the all-movable slab type with a trim tab mounted on the trailing edge of the stabilator to reduce the control system forces. This tab is actuated by a control wheel on the floor between the front seats .
The stabilator provides extra stability and controllability with less size, drag and weight than conventional tail surfaces . The ailerons are provided with a differential action which tends to reduc e adverse yaw in turning maneuvers , and which also reduces the amount of coordination required in normal turns. A rudder trim adjustment is mounted on the right side of the pedestal b e low the throttle quadrant and permits directional trim as needed in flight.
The flaps are manually operated, balanced for light operating forces and spring-loaded to r e turn to th e up position . A past-center lo c k incorporated in the actuating linkage holds the flap when it is in the up position so that it may be used as a step on the right side. The flap will not support a step load except when in the full up position, so it must be completely retracted when us e d as a s tep. The flaps have three extended positions , l 0 , 25 and 40 degrees.
•
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
•
CHEROKEE ARCHER
\
··.
~ .
-~-.
AIRPLANE AND SYSTEMS
ISSUED : JULY 9, 1973
Throttle Quadrant and Console
2 5
CHEROKEE ARCHER
---------------· ----· -------------------
-; .
. .
. ~
-
_: .:;.
:--
::: .·
,_
----
Fuel Selector
FUEL SYSTEM
Fuel is stored in two twenty-five gallon (24 gallons usuable) tanks which are secured to the leading edge structure of each wing by screws and nut plates. This allows easy re moval for service or inspection.
TI1e fuel selector control is located on the left side-panel, forward of the pilot ' s seat. The button on the selector cover must be depressed and held while the handle is moved to the OFF position. The button releases automatically when the handle is moved back into the ON position.
An auxiliary electric fuel pump is provided in case of failure of th e engine driven pump.
The electric pump should be on for all takeoffs and landings, and when switching tanks. The pump swi tch is located in the switch panel abov e the throttle quadrant.
Each t a nk has an individual quick drain located at the bottom , inboard rear comer , and should be drained to check for water before each flight (a special c ontain e r i s furnished for this operation). The fuel strainer, which is also equipped with a quick dra in, is located on the front lower left corner of the fire wall. This s trainer should be drained regularly to check for water or sed im e nt ac c umulation. To drain th e lines from th e tanks , the tank selector valve must be switched to each tank in turn, with th e electri c pump on , and th e gascolator drain valve opened.
( R ef er to th e Handling and S e rvicing Section for the complete procedure.)
Fu e l quantity and press ur e are indicated on gauges located in a cluster on the left side of the instrum e nt panel.
An optional engine priming system is available to facilitate starting. The primer p u mp is located to the immediate left of the throttle quadrant.
2-{)
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
CHEROKEE ARCHER
FUEL QUANTITY GAUGES
MAIN TANK
FUEL TANK SELECTOR VALVE
FUEL PRESSURE GAUGE
MAIN TANK
ENGINE FUEL PUMP
ELECTRIC FUEL PUMP
CARBURETOR
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
Fuel System Schematic
2-7
WARNING
...,.,.,., .... '"""'""" light can when flying through overcast spacial msonem.anon. close proximity to ground, during
'
4 master switch.,. hereafter this manual both the
"'BAT" alternator side "ALT" are to be depressed simultaneously to OFF or
ON as directed. nos. 7505001 and up
AIRPLANE AND SYSTEMS
REVISED: MARCH 26, 1979
CHEROKEE ARCHER
Unlike previous generator systems, the ammeter does not indicate battery discharge; rather it displays in amperes the load placed on the alternator. With all electrical equipment off
(except master switch) the ammeter will be indicating the amount of charging current demanded by the battery. As each item of electrical equipment is turned on, the current will increase to a total appearing on the ammeter. This total includes the battery. The maximum continuous load for night flight, with radios on, is about 30 amperes. This 30 ampere value, plus approximately two amperes for a fully charged battery, will appear continuously under flight conditions. The amount of current shown on the ammeter will tell immediately if the alternator system is operating normally, as the amount of current shown should equal the total amperage drawn by the equipment which is operating.
If no output is indicated on turning off all unnecessary electrical ammeter during flight, reduce the electrical load by
Check both 5 ampere field and 60 ampere output breaker and reset if open. If neither circuit breaker is open, tum off the "ALT" switch for 1 second to reset the overvoltage relay. If ammeter continues to indicate no output, maintain minimum electrical
load
and terminate flight as soon as practical.
Maintenance on the alternator should prove to be a minor factor. Should service be required, contact the local Piper Dealer.
AIRPLANE AND SYSTEMS
REVISED: MAR CH 26, 1979 2-8a
AMMfTER
SOURCE-POWER
RELAY ENERGIZING CIRCUIT
MASTER
SWITCH
2-9 and Starter Schematic (Ser. nos. 7405001 through 7405290)
AIRPLANE AND SYSTEMS
REVISED: JUNE 17,
CHEROKEE ARCHER
•
\
~ ·
. \
· \·
2-10
\
.~ -.
\
Circuit Break e r Panel
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
•
5 6 41
11 l 0
13 14 15 16 17 18 19
20 21 22 23 24 25 26 27
I. STALL WARNING LIGHT
2. CLOCK
3. TURN INDICATOR
4. AIRSPEED INDICATOR
~. DIRECTIONAL GYRO
6. ATTITUDE GYRO
7 . VERTICAL SPEED INDICATOR
8 . ALTIMETER
9. TRANSPONDER
10. MARKER BEACON l l . MAGNETIC COMPASS
12. OMNI & GLIDE SLOPE INDICATORS
13 . AUDIO SELECTOR PANEL
14. UHFTRANSCEIVERS
28 29 30 3' J2 33 34 35
15 . ADF RECEIVER
16. DME RECEIVER
17. CIGAR LIGHTER
18. SUCTION GAUGE
19. HEAT& DEFROST CONTROL
20. MIKE JACK
2 I. PHONE JACK
2 2. AUTOPILOT
23. ENGINE INSTRUMENT CLUSTER
24. OMNI COUPLER
25. NAV SWITCH
26. MAGNETO& STARTER SWITCH
27 . PITCH CONTROL
28. CHECKLIST
36 37 38 39 40
2 9 .
30.
31.
32.
TACHOMETER
FUEL GAUGES
PRIMER
MICROPHONE
33.
34.
35.
36.
37.
38.
THROTTLE QUADRANT
FRICTION LOCK
CARBURETOR HEAT CONTROL
EGT INDICATOR
INSTRUMENT PANEL LIGHTS
CIRCUIT BREAKER PANEL
39.
40.
41.
CIRCUIT BREAKER COVER
CLIMATE CONTROL
ANNUNCIATOR PANEL (SER . NOS.
7505001 AND UP)
• •
CHEROKEE ARCHER
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
Pitot - Static System
2-13
CHEROKEE ARCHER
PITOT-STATIC SYSTEM and water parked, a cover should head will give erratic or zero
NOTE
During the preflight, check to make sure the pitot cover is removed.
HEATING AND VENTILATING SYSTEM
~ Heat the cabin interior and the defroster system is provided a heater muff attached to the exhaust system. The amount of heat desired can be regulated with the controls located on the far right side of the instrument panel.
The air flow can be regulated between the front and rear seats by levers """"'"' .... L"''""' on top of the heat ducts next to the console. air inlets are located in leading of the wing at the mtersiect:ton
A large adjustable outlet is located on the the cabin near the floor seat air outlets are outlet under the rear seat. A cabin air as optional equipment. Air is exhausted blower, incorporated in the system, vailable as optional equipment. An optional blower available on models without air conditioning. This blower is switch with 4 positions - "OFF," "LOW," "MED," or "HIGH." with a cabin air by a "FAN"
CAUTION
When cabin heat is operated, heat duct surface becomes hot. This could result in burns if arms or legs are placed too close to heat duct outlets or surface.
2-14
AIRPLANE AND SYSTEMS
REVISED: MARCH 26, 1979
\
\
\
CHEROKEE ARCHER
\
I
/
....
"
...........
"' ,. "
NM'<i'IJ)\Or-.OOO>O"""'N
AIRPLANE AND SYSTEMS
ISSUED: JULY 9, 1973
Heating and Ventilating System
5
I L F T
NOTE
FAA
H. W. BARNHOUSE
PIPER AIRCRAFT CORPORATION
D. 0. A. No. S0-1
VERO BEACH, FLORIDA
DATE OF APPROVAL: MAY 14, 1973
APPROVAL BASIS: CAR 3
REPORT:
VB-SSS
MODEL: PA-28-180
CHEROKEE ARCHER
TABLE CONTENTS
. 3-iii
I.
J.
. . . . . . . . . . . . . . . . . . . . 3-1
3-1
. . . . . . . . . . . . . . . . . . 3-1
3-2
3-2
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-3
"",..., ......... ,..,. ..... ",, Airplanes . . . . . . ~ . . . . ~ . . . . . . ~ . . . . . . . . 3-5
SECTION II
Procedures
SECTION III
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-7
. . . . . . . . . . . . . 3-9
IV
Optional ~4•-•.tP''u"'·'"
A. Trim Installation . . . . . . . . . . . . . . . . . . . . . . . . . lI Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . B.
c.
D.
Air Conditioner
Installation Of
3-1 l
3-13
3-16
I
I
AutoControl III and/or AutoControl IIIB . . . . . . 3-19
FAA APPROVED MAY 14.1
REVISED: JANUARY 20, 1975
REPORT: VB-558 PAGE 3-i
MODEL: PA-28-180
BLANK
REPORT: VB-558
MODEL: PA-28-180
APPROVED MAY 14, 1973
AIRPLANE
Revision Revised
Title
,(..
,
3
3-i
3-11
9,
3-21,
3-i
3-1
13
14
3-15
3-16
3-I 9
4
FAA
APPROVED
MAY 14, 1
REVISED: NOVEMBER 2L 1
REVISIONS
R
CHEROKEE ARCHER
SECTION I
LIMITATIONS following limitations must be observed in the operation of this airplane:
A. ENGINE
Lycoming 0-360-A4A or 0-360-A4M with carburetor setting I0-3878
ENGINE LIMITS
For all operations 2700 RPM, 180 HP
B. FUEL (AVGAS ONI Y) l 00/l 30 minimum octane aviation fuel
C. PROPELLER
Sensenich M76EMMS inches. or 76EM8S5. Maximum diameter 76 inches, minimum 76
Static RPM at maximum permissible throttle setting. Not over 2425, not under
No additional tolerance permitted.
D. POWERlNSTRUMENTS
OIL TEMPERATURE
Green Arc (Normal Operating Range)
Red Line (Maximum)
OIL PRESSURE
Green Arc (Normal Operating Range)
Yellow Arc (Caution Range)
Red Line (Minimum)
Red Line (Maximum)
PRESSURE
Green Arc (Normal Operating Range)
Red Line (Minimum)
Red Linc (Maximum)
TACHOMETER
Green Arc (Normal Operating Range)
Red Line (Maximum Continuous Power)
F to
60 PSI to 90 PSI
PSI to 60
25 PSI
90 PSI
.5 PSI to 8 PSI
.5 PSI
8 PSI
500 to 2700 RPM
2700 RPM
FAA APPROVED MAY 14, 1973
REVISED: MARCH 16. 1984
REPORT: VB-558 PAGE 3-1
MODEL: PA-28-180
to 140 MPH
KTS to 1 l
61MPHtoll MPH
( KTS to 100
LBS
1950 LBS
MAY 14, 1973
A.
Ill IIIB
APPROVED
REVISED: JANUARY
PAGE
3-11
MODEL: PA·28-180
INTENTIONALLY LEFT BLANK
2 FAA APPROVED MAY 14, 1973
L an trim.
3.
4. In ft in case trim trim trim may be results in JO 0
, a malfunction can result in a 5
°
pitch change and 50
FAA APPROVED MAY 14, 1973
REVISED: JANUARY 20, 1975
REPORT: VB-558 PAGE 3-13
MODEL: PA-28-180
THIS PAGE
BLANK
VB·558 PAGE 3-14
MODEL: PA-28-180
FAA APPROVED MAY 14, 1973
REVISED: JANUARY 20, 1975
be che:ckf~d
4. must to insure nonnal if an in failure is
APPROVED MAY 14, 1
REVISED: JANUARY 20. 1975
REPORT: VB-558 PAGE 3-17
MODEL: PA-28--180
THIS PAGE INTENTIONALLY LEFT BLANK
REPORT: VB-558 PAGE 3-18
MODEL: PA-28-180
FAA APPROVED MAY 14, 1973
CAS. disconnect switch on control wheel.
Rocker switch on instrument -OFF.
Unit may be
In an autopilot runway, with a 3 bank, and 190 ft altitude loss. approach configuration an autopilot runaway, with a 1 in I 5° bank and 40 ft altitude loss.
REPORT: VB-558 PAGE 3-16
MODEL: PA-28-180
FAA APPROVED MAY 14, 1973
REVISED: JANUARY 20~ 1975
lNTENTIONALL Y
FAA APPROVED MAY
REVISED: JANUARY 20, l
REPORT: VB-SSS PAGE
MODEL: PA-2&.180
D. INSTALLATION OF PIPER III nm in command knob control wheel center knob .
..... "",,,.,, .... ,. on D&G. to Engage rotate Heading Indice right and Aircraft control wheel should turn same as Indice. While D.G. indice is set for a left turn, grasp control wheel and override the servo to the Repeat in opposite direction for right
( c) turn.
If VOR Omni mode on Radio Coupler by swinging Omni needle left and right slowly. Observe that control wheel rotates in direction of needle movement.
( d) Disengage by placing the A/P ON/OFF switch to the "'OFF,, position. b. IN-FLIGHT
(1) Trim airplane {ball centered).
(2) Check air pressure or vacuum to ascertain that the Directional Gyro and Attitude Gyro are receiving sufficient air.
(3) Ron Section
(a) To engage, center Roll Command Knob, place the A/P
ON/OFF switch to the "ON" position. To turn rotate roll command knob in desired bank should not exceed 30° .}
(Maximum angle of
( b) For heading mode, set Directional with Magnetic
Compass. Push directional gyro HDG knob in, rotate to aircraft heading. Place the console HDG ON/OFF switch to the "ON" position. To select a new aircraft heading, push
D ,G. knob IN and rotate, in desired of turn, to the desired heading.
NOTE
In HDG mode the maximum bank angles are limited to approximately 20° and single command, heading changes should be limited to 150°. (HOG Indice not more than I 50° from actual aircraft heading.)
FAA APPROVED JUNE 17, 1974
REVISED: JANUARY 20, 1975
REPORT: VB-558 PAGE 3-19
MODEL: PA-28~180
VOR
( is more than
, .......... ,.,,,,.,. passage. As the turn in alternate the zone will an as the OMNI indicator needle
This alternate banking limited to the standard D.G. bank angle, is an indication of station passage.
(b) To select new course:
1. To select a new course or radial, rotate the HDG indice to the desired HDG (match course).
2. Rotate OBS to the new course. Aircraft will
To l. automatically turn to the intercept heading for the new course. stations: same course is desired, merely tune receiver to new
2. station frequency.
If different course is desired, position mode selector to HDG mode. Dial course selector D.G. to new course. Dial OBS to new course and position
(5) VOR Approach coupler mode selector to OMNI mode.
Track in bound to station as described in VOR navigation section.
After station passage.
(a) Dial outbound course on Course Selector D.G., then dial same course on OBS.
(b) After established on outbound radial, position coupler mode selector to HDG mode and select outbound procedure turn heading. After 40 seconds to 1 minute select a turn in the desired direction with the Course Selector D.G. to the inbound procedure tum heading.
(c) OBS to inbound course.
( d) When aircraft heading is 45
°
to the inbound course, dial
Selector to inbound course and position coupler mode selector to OMNI mode.
REPORT: VB-558 PAGE 3-20
MODEL: PA-28-180
FAA APPROVED JUNE 17, 1974
position coupler station passage. mode selector to outbound neatarntg dial inbound course
0 heading is to mode.
( 6)
(7)
LOC Approach Only
(a) To intercept dial ILS outbound course on Course
D .G. When stabilized, position
LOC REV mode.
(b) After mode selector to and when beyond outer position coupler mode selector to HDG mode and dial outbound procedure tum heading. After one minute, dial inbound procedure turn heading in direction of turn.
( c) When aircraft heading is 45 ° to ILS inbound course dial inbound course on Course and position coupler mode selector to LOC NORM mode.
At the missed approach point (M.A.P.), or when missed (d) approach is elected, position coupler mode selector to HDG mode and execute missed approach procedure.
LOC Approach - Back Course (Reverse)
(a) To intercept dial ILS Back Course outbound heading on
(b)
Course Selector D.G. When stabilized, position coupler mode selector to LOC NORM mode.
After interception and when beyond fix, position coupler mode selector to HDG and diaJ outbound procedure turn heading. After one minute, dial inbound procedure turn heading in direction of turn.
(c) When heading 45
°
to inbound course, dial inbound course on Course Selector D.G. and position coupler mode selector to LOC REV mode.
(d) Approximately l mile from runway, position coupler
(e) mode selector to HDG mode to prevent .. S" turn over ILS station near runway threshold.
Missed approach~ same as Front Course. {See (6) d)
FAAAPPROVEDJUNE
17.1974 REPORT: VB-SS8 PAGE 3-21
MODEL: PA-28-180
PERFORMANCE
No v.l.l,Q.,UJI'>'-'
REPORT: VB-558 PAGE 3-22
MODEL: PA-28~180
FAA APPROVED JUNE 17, 1974
REVISED: JANUARY 20, 1975
NOTE
WARRANTY
NOTE
Pilot's Operating Manual Revision Only
This Is Not A Complete Manual
Rev. 8 - 761 556 (PR900320) Dated March 20, 1990
This revision shall be inserted into the current PA-28-180
Cherokee Archer Pilot's Operating Manual,
PIN
761 556, issued
July 9, 1973.
PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)
Revision
Rev. 3 (cont)
Rev. 4 - 761 556
(PR750120)
Rev. 5 - 761 556
(PR751121)
Rev. 6 - 761 556
(PR790326)
Revised
Pages
Description
9-i
9-2
9-3
9-4
9-5
9-6
9-7
9-8
Revised Perfonnance Charts Index.
Revised Takeoff Chart.
Revised Climb Chart.
Revised Range Chart.
Revised Engine Chart.
Revised Airspeed Chart.
Revised Stall Speed vs Weight Chart.
Revised Stall Speed vs Angle of Bank Chart.
9-9
9-10
Revised Glide Chart.
Revised Landing Chart.
10-11 Revised Battery Service.
1-2 Added 0-360-A4M engine designation and footnote.
Added 0-360-A4M engine designation and 2-1 footnote.
AF/M Added Rev. 3 to Report: VB-558.
W/B
7-4
Added Rev. 4 to Report: VB-547.
Added new item 9.; revised existing item
7-8
8-2
10-8 nos. under TAKEOFF.
Revised ELT info.
Added item 11.
Added 0-360-A4M engine designation under Oil Requirements. iii
1-1
Added concluding ser. no. to Applicability.
Revised Cruise Speed and Range figures; revised Empty Weight and Useful Load; deleted footnote.
1-2 Deleted footnote.
2-1 Revised Airframe info; deleted footnote.
AF/M Added Rev. 4 to Report: VB-558.
W/B Added Rev. 5 to Report: VB-547.
8-1 Revised item 8 (Fuel Warning Tip).
9-4
9-6
Revised Cruise Perfonnance - Range chart.
Revised Cruise Perfonnance - True
Airspeed chart.
2-8
2-Sa
2-14
W/B
Added Warning.
Added info.
Added Caution.
Added Rev. 6 to Report: VB-547.
7-2 Revised items.
7-8, 7-9 Revised ELT info.
Date
Jan.20, 1975
Nov. 21, 1975
March 26, 1979 iv-a
Revision
PILOT'S OPERATING MANUAL LOG OF REVISIONS (cont)
Rev. 7 - 761 556
(PR840316)
Revised
Pages
Description
1-2
2-16
AFM
W/B
7-1
7-4
Revised fuel and oil.
Revised para.
Added Rev. 5 to Report VB-558.
Added Rev. 7 to Report VB-547.
Added to preflight.
Added to text info.
9-i
10-1
10-9
10-11
Added Warning.
Added to text info.
Added text info.
Revised para.
10-12, Revised preventive maintenance info.
10-13
Date
March 16, 1984
Rev. 8 - 761 556
(PR900320)
10-7
10-8 para.
10-11, Revised para.
10-12
Relocated info. from p. 10-8.
Moved info. top. 10-7. Revised
10-13 Revised para.
March 20, 1990 iv-b
CHEROKEE ARCHER
BRAKE SERVICE
The brake system is filled with MIL-H-5606 (petroleum base) hydraulic brake fluid. This should be checked at every 50 hour inspection and replenished when necessary by filling the brake reservoir on the firewall to the indicated level. If the entire system has to be refilled, it should be done by filling from the brake end of the system with fluid under pressure. This will eliminate air from the system.
No adjustment of brake clearances is necessary on the Cherokee. If after extended service the brake blocks become worn excessively, they are easily replaced with new segments.
LANDING GEAR SERVICE
The three landing gears use Cleveland 6.00 x 6 wheels, the main gear wheels being provided with brake drums and Cleveland single disc hydraulic brake assemblies. All three wheels use 6.00 x 6. four-ply rating, Type III tires with tubes.
Main wheels are removed by taking off the wheel fairings. hub cap, axle nut, and the two bolts holding the brake segment into place. The wheel will slip easily from the axle.
Tires are removed from the wheels by first deflating the tire, then removing the through bolts, and separating the wheel halves.
Landing gear oleo struts should be checked for proper strut exposures and fluid leaks. The required extensions for the strut when under normal static load (empty weight of airplane plus full fuel and oil) are 3-1/4 inches for the nose gear and 4-1!2 inches for the main gear. Should the strut exposure be below that required, it should be determined whether air or oil is required by first raising the airplane on jacks. Depress the valve core to allow air to escape from the strut housing chamber. Remove the filler plug and slowly raise the strut to full compression. If the strut has sufficient fluid, it will be visible up to the bottom of the filler plug hole and will then require only proper inflation.
Should fluid be below the bottom of the filler plug hole, oil should be added. Replace the plug with valve core removed; attach a clear plastic hose to the valve stem of the filler plug and submerge the other end in a container of hydraulic fluid (MIL-H-5606). Fully compress and extend the strut several times, thus drawing fluid from the container and expelling air from the strut chamber. To allow fluid to enter the bottom chamber of the main gear strut housing, the torque link assembly must be disconnected to let the strut be extended a minimum of 10 inches
(the nose gear torque links need not be disconnected). Do not allow the strut to extend more than 12 inches. When air bubbles cease to flow through the hose, compress the strut fully and again check fluid level. Reinstall the valve core and filler plug, and the main gear torque links, if disconnected.
With fluid in the strut housing at the correct level. attach a strut pump to the air valve and with the aiiplane on the ground, inflate the oleo strut to the correct height.
In jacking the Cherokee for landing gear service, a jack kit (available through the Piper
Dealers and Distributors) should be used. This kit consists of two hydraulic jacks and a tail stand. At least 250 pounds of ballast should be placed on the tail stand before jacking the aircraft. The jacks should be placed under the jack points on the wing and the airplane jacked up until the tail skid is at the right height to attach the tail stand. After attaching the tail stand and adding ballast, jacking may be continued until the aircraft is at the height desired.
I HANDLING AND SERVICING
REVISED: MARCH 20, 1990 10-7
CHEROKEE ARCHER
The steering arms from the rudder pedals to the nose wheel are adjusted at the rudder pedals or at the nose wheel by turning in or out the threaded rod end bearings. Adjustment is normally accomplished at the forward end of the rods and should be done in such a way that the nose wheel is in line with the fore and aft axis of the plane when the rudder pedals and rudder are centered. Alignment of the nose wheel can be checked by pushing the airplane back and forth with the rudder centered to determine that the plane follows a perfectly straight line.
The turning arc of the nose wheel is 30 degrees in either direction and is factory adjusted at stops on the bottom of the forging.
The steering arm stops should be carfully adjusted so that the nose wheel reaches its full travel just after the rudder hits its stops. This guarantees that the rudder will be allowed to move through its full travel.
PROPELLER SERVICE
The spinner and backing plate should be cleaned and inspected frequently for cracks. The propeller should be inspected before each flight for nicks, scratches, and corrosion. If found, they should be taken care of as soon as possible by a rated mechanic, because nicks and scratches cause areas of increased stress which can cause serious damage or loss of a propeller tip. The back face of the blades should be painted when necessary with flat black paint to retard glare to the pilot's eyes. To prevent corrosion, the surface should be cleaned and waxed periodically.
OIL REQUIREMENTS
The oil capacity of the Lycoming 0-320-A4A and 0-360-A4M series engines is 8 quarts, and the minimum safe quantity is 2 quarts. It is recommended that engine oil be drained and renewed every 50 hours. The oil filter element should be changed every 50 hours of operation. The interval between oil and oil filter changes should not exceed a total of four months. Under unfavorable dusty conditions, the oil and oil filter should be changed more frequently. Should fuel other than the specified octane rating for the power plant be used, refer to the latest issue of Lycoming Service
Letter No. L185 for additional information and recommended service procedures.
The following seasonal aviation oil grades and seasonal ambient temperature ranges are recommended:
Average Ambient
Temperature
MIL-L-6082B
Mineral
SAE Grade
MIL-L-22851
Ashless Dispersant
SAE Grades
All Temperatures
Above 80"F
Above60"F
30"Fto90"F
O"Fto 1o•p o·F to 9o·F
Below 10°F
60
50
40
30
20W-50
20
15W-50 or 20W-50
60
40 or 50
40
30, 40 or 20W-40
20W-50 or 15W-50
30 or20W-30
When operating temperatures overlap indicated ranges, use the lighter grade oil.
NOTE
Refer to the latest issue of Textron Lycoming Service Instruction 1014
(Lubricating Oil Recommendations) for further infonnation.
I
10-s
HANDLING AND SERVICING
REVISED: MARCH 20, 1990
CHEROKEE ARCHER
BATTERY SERVICE
Access to the 12-volt battery is through the removal of the panel at the right rear side of the baggage compartment. The battery box has a plastic drain tube which should be opened occasionally to drain off any accumulation of liquid. Check the battery for proper fluid level.
(Do not fill above the baffle plates.) Use only water - no acid. A hydrometer check should be performed to determine the percent of charge present in the battery.
If the battery is not up to charge, recharge starting at a 4 amp rate and finishing with a 2 amp rate. Quick charges are not recommended.
FACTS YOU SHOULD KNOW
The Federal Aviation Administration (FAA) occasionally publishes Airworthiness
Directives (ADs) that apply to specific groups of aircraft. They are mandatory changes and are to be complied with within a time limit set by the FAA. When an AD is issued, it is sent by the FAA to the latest registered owner of the affected aircraft and also to subscribers of their service.
Owners should periodically check with their Piper Service Center or Piper's Customer Services
Department to see whether they have the latest AD against their airplane. The owner is solely responsible for keeping up with ADs.
Piper Aircraft Corporation takes a continuing interest in having owners get the most efficient use from their airplane and keeping it in the best mechanical condition. Consequently, Piper Aircraft, from time to time, issues service releases including Service Bulletins. Service Letters. Service Spares
Letters, and others relating to the airplane.
Piper Service Bulletins are of special importance and Piper considers compliance mandatory.
These are sent directly to the latest FAA-registered owners in the United States (U.S.) and Piper
Service Centers worldwide. Depending on the nature of the release, material and labor allowances may apply. This information is provided to all authorized Piper Service Centers.
Service Letters deal with product improvements and servicing techniques pertaining to the airplane. They are sent to Piper Service Centers and, if necessary, to the latest FAA-registered owners in the U.S. Owners should give careful attention to Service Letter information.
Service Spares Letters offer improved parts, kits, and optional equipment which were not
I
available originally, and which may be of interest to the owner.
Piper Aircraft Corporation offers a subscription service for Service Bulletins, Service
Letters, and Service Spares Letters. This service is available to interested persons such as owners,
I pilots, and mechanics at a nominal fee, and may be obtained through an authorized Piper Service
Center or Piper's Customer Services Department.
Service manuals, parts catalogs, and revisions to both, are available from Piper Service
I
Centers or Piper's Customer Services Department. Any correspondence regarding the airplane should include the airplane model and serial number to ensure proper response.
HANDLING AND SERVICING
REVISED: MARCH 20, 1990 10-11
CHEROKEE CRUISER
Pilot's Operating Manual supplements are distributed by the manufacturer as necessary.
These revisions and additions should be studied and put into the operating manual to keep it up to date. This manual contains important information about the operation of the aircraft and should be kept with the aircraft at all times, even after resale. Every owner, to avail themselves of the latest information concerning their airplane, should stay in close contact with an authorized Piper Service Center or Piper's Customer Services Department.
If the owner desires to have his aircraft modified, he must obtain FAA approval for the alteration. Major alterations accomplished in accordance with Advisory Circular 43.13-2. when performed by an A & P mechanic, may be approved by the local FAA office. Major alterations to the basic airframe or systems not covered by AC43.13-2 require a Supplemental Type
Certificate.
The owner or pilot is required to ascertain that the following Aircraft Papers are in order and in the aircraft. a. To be displayed in the aircraft at all times:
1. Aircraft Airworthiness Certificate Form FAA-1362B.
2. Aircraft Registration Certificate Form FAA-500A.
3. Aircraft Radio Station License FCC-404A, if transmitters are installed. b. To be carried on the aircraft at all times:
(1) Aircraft Flight Manual.
(2) Weight and Balance Data plus a copy of the latest Repair and Alteration Form
FAA-33 7, if applicable.
(3) Aircraft equipment list.
Although the aircraft and engine logbooks are not required to be in the aircraft, they should be made available upon request. Logbooks should be complete and up to date. Good records will reduce maintenance cost by giving the mechanic information about what has or has not been accomplished.
PREVENTIVE MAINTENANCE
The holder of a Pilot Certificate issued under FAR Part 61 may perform certain preventive maintenance described in FAR Part 43. This maintenance may be performed only on an aircraft which the pilot owns or operates and which is not used to carry persons or property for hire, except as provided in applicable FAR's. Although such maintenance is allowed by law, each individual should make a self-analysis as to whether he has the ability to perform the work.
All other maintenance required on the airplane should be accomplished by appropriately licensed personnel.
If maintenance is accomplished, an entry must be made in the appropriate logbook. The entry should contain:
(a) The date the work was accomplished.
(b) Description of the work.
(c) Number of hours on the aircraft.
(d) The certificate number of pilot performing the work.
( e) Signature of the individual doing the work.
10-12
HANDLING AND SERVICING
REVISED: MARCH 20, 1990
CHEROKEE CRUISER
REQUIRED SERVICE AND INSPECTION PERIODS
The Owner Seivice Agreement which the owner receives upon delivery of the aircraft should be kept in the aircraft at all times. This identifies him to authorized Piper dealers and entitles the owner to receive seivice in accordance with the regular seivice agreement terms. This agreement also entitles the transient owner full warranty by any Piper dealer in the world.
Piper Aircraft Corporation has developed inspection items and required inspection inteivals for the PA-28 (see PA-28 Seivice and Inspection Manuals). The PA-28 Inspection Manual contains appropriate forms, and all inspection procedures should be complied with by a properly trained, knowledgeable, and qualified mechanic at an authorized Piper Seivice Center or a reputable repair shop. Piper Aircraft Corporation cannot accept responsibility for the continued airworthiness of any aircraft not maintained to these standards. and/or not brought into compliance with applicable Seivice
Bulletins issued by Piper Aircraft Corporation. instructions issued by the engine, propeller, or accessory manufacturers, or Airworthiness Directives issued by the FAA.
A Programmed Inspection. approved by the Federal Aviation Administration (FAA), is also available to the owner. This involves routine and detailed inspections to allow maximum utilization of the airplane. Maintenance inspection costs are reduced, and the maximum standard of continued airworthiness is maintained. Complete details are available from Piper Aircraft Corporation.
In addition. but in conjunction with the above. the FAA requires periodic inspections on all aircraft to keep the Airworthiness Certificate in effecL The owner is responsible for assuring compliance with these inspection requirements and for maintaining proper documentation in logbooks and/or maintenance records.
A spectrographic analysis of the engine oil is available from several sources. This inspection, if performed properly, provides a good check of the internal condition of the engine. To be accurate, induction air filters must be cleaned or changed regularly, and oil samples must be taken and sent in at regular inteivals.
HANDLING AND SERVICING
REVISED: MARCH 20, 1990
TYPE OF LUBRICANT
IDENTIFICATION
U.TTER LUBRICANT SPECIFICATION c
D
A lllltRICATING OIL, GENERAL MIL-L-1870
PURPOSE, LOW TEMP . •
LUBRICATING Oil. AIRCRAFT Mll·l·6082
RECIPROCATING ENGINE
U'lSTONI GRADE AS SPECIFIED
SAE !iO ABOVE &O"F AIR TEMP.
SAE 40 30° TO 90"F AIR TEMP.
SAE 30 0° TO 70"F AIR TEMP.
SAE 20 et!t.OW tO"F AIR TEMP.
HYDRAULIC FLUID,
PETROLEUM BASE
GREASE, AIRCRAFT ANO
INSTRUMENT, GEAR ANO
ACTUATOR SCREW
GREASE, AIRCRAFT,
HIGH TEMP.
Mll·H-5606
Mll·G-23827
F
0
H
PARKER "O" RING LUBRICANT
AERO LUSRIPLATE
FLUOROC::AIUION RELEASE
AGENT DRY LUBRICANT
OREA.SE· LUBRICATION
OEN. PURPOSE AIRCRAFT
•MS-122
MIL·0-7111
PREFERRED PRODUCT
ANO VENDOR
TEXACO MARFAK All
PURPOSE GREASE,
MOBIL GREASE 11
IOR M081lUX EP21,
SHEU. At.VANIA El'
GREASE 2
FISKE BROS.
REFINING CO.
SPECIAL INSTRUCTIONS
1. AIR Fil TER · TO CLEAN Fil TER. TAP OENTL Y TO REMOVE DIRT PARTICLES. 00 NOT SLOW
OUT WITH COMl'AESSEO AIR OR USE Ott.. REPLACE FILTER IF PUNCTURED OR DAMAGED.
2. SEARINGS ANO BUSHINGS
LUBRICATING.
CLEAN !XTEfUOR MTH A DRY TYPE SOLVENT IEFORE
3. WHEEL BEARINGS· DISASSEMBLE ANO CLEAN WITH A DRY TYPE SOLVENT. ASCERTAIN THAT
GREASE IS PACKED 8£TWEEN THE BEARING ROt.LER ANO CONE. DO NOT PACK GREASe IN
WHEEL HOUSING.
4. OlEO STRUTS. AND tlRAKE RESERVOIR. FILL PER INSTRUCTIONS ON UNIT OR CONTAINER,
OR REFER TO SERVICE MANUAL, SECTION II.
II. ..0 .. RING. CONTROL SHAFT BUSH!NG IWITH 1.125 INCH SHAFT ONL YI OISASSEMBLE "O"
RING RETAINER PLATES FROM INSTRUMENT PANEL, LUBRICATE "O" RING AND ftEASSEMtlLE.
&. LUBRICATION POINTS. WIPE ALL LUBRICATION POlNTS CLEAN OF OLO GftEASE, OIL, DIRT,
ETC. tlEFORE LUBRICATING.
1. INTERVALS 8ETWEEN Oil CHANGES CAN BE INCREASED AS MUCH AS 100% ON ENGINES
EOUIPl'EO WITH FULL FLOW !CARTRIDGE TYPE! Oil FILTERS • PROVIDED THE ELEMENT IS
REPLACED EACH SO HOURS OF OPl!RATION.
SPECIAL INSTRUCTIONS (cont)
I. STABILATOR TRIM PULU.YS ·LUBRICATION MAY BE EXTENDED TO 250 HOURS WHEN DUSTY
CONDITIONS ARE AT A MINIMUM.
9. AILERON HINGES WITH TEFLON SLEEVES SHOULD NOT tlE LUBRICATED. AILERON HINGES
WITHOUT TEFLON SLEEVES SHOULD FIRST BE CLEANED WITH A DRY TYPE SOLVeNT THEN lUBfllCATED WITH Mll-L-1870 LUBRICATING Oil.
10. THIS TRANSMISSION TO BE 112 FULL Of GREASE. APPLY GREASE DURING ASSEMBLY AND lUllftlCATE TRANSMISSION BAU. NUT AND SCREW WITH Mll-G·23827 GREASE.
NOTES
1. PILOT AND PASSENGER SEATS· LUBRICATE TRACK ROLLERS AND STOP PINS AS REQUIRED.
ITYPe OF LUBRICANT: "A"l
2. WHEEL BEARINGS REQUIRE CLEANING ANO REPACKING AFTER EXPOSURE TO AN
ABNORMAL QUANTITY OF WATER.
3. FUEL SELECTOR VALVE · LUBRICATE FUEL SELECTOR VALVE AS REQUIRED, REFER TO
PIPER SERVICE LETTER NO. 351.
4. SEE LYCOMING SERVICE INSTRUCTIONS NO. 1014 FOR USE OF DETERGENT Oil.
CAUTIONS
1 00 NOT USE HYDRAULIC FLUID WITH A CASTOR Oil OR ESTER BASE.
:!:. 00 NOT OVER·LUtlRICATE COCKPIT CONTROLS.
3. DO NOT APPLY LUBRICANT TO RUBBER PARTS.
EXAMPLE
METHOD OF
LUBRICATIOH
Lubrication Nomenclature
\tnlUd ~tOttJ Of 9tnrtir0
J:lrportmcnt of 'l:ronsport titfon -federal 2Jl1iation 9dmini&trtJtion
~upplcmcntal '([)!pc ltcrtifirntc
.SA779NE
ur/0',bk..
41.Ju,,,,//,. U.S. Propeller Service of Connecticut
P
.o.
Box ld5
East Haddam. Connecticut 06423
2Al3
Piper
PA-28-180, -181
1Al70/BMS Propeller in accordance with U.S. Propeller ort No 28181, dated August 27. 1990, or later FAA on whi is determi other previous the airworthin
: not over 76"J not under 74" ould not be extended to other aircraft of these models ously approved modifications are incorporated unless it the interrelationship between this change and any of thoRe pproved modifications will introduce no adverse effect upon of those aircraft.
YL .c.!'rl'.y1uu
And
,/k.
.A.-y_yi.1....4'nr~61 A.t.h.t~A.,,;, a~
/r
~;,...·1¥t/..tA'
.. rl/r<;tt ...
u'n·
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..
-//"
..
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9:..-6..,f#h.-&~.,.: July 9, 1990
!:/,,& ?'
September 10, 1990
:1}}' ,d;1vr/,;.,, .,.///.r .r:i/111/mJ/rnlt,.
~9~--
( S1v1111"'')
Ronald L. Vavruska
Manager, Boston Aircrnft Certification Ofrh
(I ttlr)
'/Ito .,,11fuolt
NmJ 111 trnmfinrJ w ntrotdmut' wHf1 I AU :l I f i
U.S. PROPELLER SERVlCE O~ CT.
P .. O. BOX 415
GOODSPEED AIRPORT
EAST HJ\DDJ\M, C'l'. 06423
Dated
08-27-90
Report f
USP
28181
Descriptive
Data and Installation Ingt:ructions
for
conversion of pj per
PA 28-180 and PA 28-181
airplanes
7660 Pixed Pitch
Propeller. to the Mccauley
1A170/BMS
1.
2.
3.
4.
Remove existinq Sensenich propeller per instructlons in Piper
PA28-180
Maintenance Manuals.
Install
Mccauley Propeller, model number lAl 70/BMS.
7660 as
per
instruction
Installation revisions. on
McCauley
drawing
IC6626
titled .
WPropeller
1Al70/BMS"
dated
May 22nd 1990 or later
FM app:rovml.
Pill out a 337 form for and make
this STC. the
aircraft alteration
as
appropriate ..
all
neceasary changes
to
aircraft records.. Referencing
.Revise weighs
the
aircraft
weight and
bal~nce.
The
Mccauley
propeller
36 lbs.
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N1185X
P.T.
AERO SERVICE, INC.
Hanger l, T.F. Green Airport arwic~ R.l. 02886
401-737-7788
DfP.uTMENT or TIANSl'QUATIOH
FEDERAL AVIATION ADMINISTI!ATION
MAJOR REPAIR AND ALTERATION
(Airframe, Powerplant, Propeller, or Appliance)
Form A'Jf,ro v ed
Budget ureau No. 0 4-R< HiO. I
FOR FAA USE O N / .
) '
--- -
OFFICE IDENTIFICATION
INSTRUCTIONS: Print or type all entrie5. for instructions and disposition of this form .
See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revisi o n thereof)
1. AIRCRAFT
2 . OWNER
MAKE MODEL
Piper
SERIAL NO.
~ ··
28-7505222
NAME (As shown on registration certificate)
Halzel, Lenny
PA28-180
NATIONALITY AND REGISTRATION
Nll85X
MARK
3. FOR FAA USE ONLY
ADDRESS (As shown on registration certificate)
144
President Avenue
Providence, RI
02906
-- - -
-
UNIT
----
I-
AIRFRAME
MAKE
--·
4. UNIT IDENTIFICATION
MODEL I
-
SER I AL NO .
5 .
--;EPA;; ·
r -· A lTE · R ~
~. l 1 ()I I - -· -
· -ilf E
,,,,,,,,,,,,,,,,,#####(As described in item I above)######################
-· -~
-· - -
~-· · --
POWERPLANT
PROPELLER
TYPE
McCauley
APPLIANCE
MANUFACTURER
lAl 70/BMS
M
F028
· -
- - ·
L . - - - - - x
I
---
·· - - - - -
6. CONFORMITY SlATEMENT
A. AGENCY'S NAME AND ADDRESS 8. KIND OF AGENCY
c.
CERTIFICATE NO.
- · --
James
A. Thistlewai
te
5
Kennedy Drive
Coventry,
RI
02816
x
U .
S. CfltTlflCATEO MECHANIC
FOllEIGN CERTIFICATED MECHANIC
CERTIFICATED llEPAIR STATION
2073585
MANUFACTURER
- -
BY
D. I certify that the repair and / or alteration made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U .
S. federal Aviarion Regul a rions
DATE and chat the information furnished herein is true and correct to the best of my knowledge.
7-29-93
SIGNATURE OF AUTH~DIVIDUAl a rd ~
7. APPROV«Y FOR RETURN TO SERVltE
~
7
'L//
_rp , -,,,;
----~--·---
-- -·
Pursuanc co the authoricy given persons specified belo(' the unit the Adminiscracor of the Federal Aviation Administration and is
~entified in item 4 was inriected
APPROVJ;D
D
REJEC l:D
in che manner prescribed by
- - - - ---·-· ------
· -
'
MANUfAl:TUm . x lt!ISPfCTIOt:l AUTHORIZATION
OTHER (Specify)
FAA FLT . STANDARDS
..
INSPECTOR
'..
.
.
...
.
,, -
.
.
..
.
.
~ CANADIAN DEPARTMENT ·
Of TRANSPORT INSPECTOR FAA OESIGNEE · REPAIR STATION
Of AIRCRAFT
· ------··
l
DATE OF APPROVAL OR
REJECTION
CfRTIFICATE
, OR
DESIGNATION NO.
2073585
.
.
Sic<:aRE 9F
7-29-93
FAA Fonu 337
(7-67)
: .
i <-" ,h ' ' ' ',' ,/.Y"c"-"' ' .. - -
_I
(i>.J
L O)
Weight and balance or operating limitation changes shall be entered in the appropriate oin::raft record.
An alteration must be compatible with all previous alterations to
assure
continued conformity with the
Identify with air~
Pr
iftpartmtnt
'llnittt .Stitt.I t( ~..,.... er
'l:rJftlportation jcdcral
atmition 21dminlltrotion
~upplcmcntal ~~pc ~crtifirntc
Knots 2U • I nc •
1941 Highland Avenue
w
met te , 1 L 60091
~A#.;.,.,
M, #1(4;,.,.,.,.M;,,,.J,J
""1mNN1i~1C ,;!~,,./
J t/ ~
:N,_.r~&;.,...
\See Type Certificate Data Sheet 2Al3 for complete certification basiS).
!J,;..-.J:?.'..-.~-. ~,;.,
I
~~~.-6., lumli-, 2A 13
. lt,;t,
·Piper Aircraft Corporation
£1'--~~.,,. ;,f-"ijy.,!/',.,~yH l~u'~Y'.
.,//,.,6/: PA-28-140, PA-28-150, PA-28-160, PA-28-180,
PA-2B-235, PA-28R-180, PA-28R-200, PA-28-151,
PA-28-161, PA· ?fl-181, PA-28-201T, PA-28-236,
PA-28R-201, PA-2BR-201T, PA-28RT-201, PA-2BRT-201T
\ri$ti11
fa1r1~gs over flap hinges in accordance with Knots 2U, Inc. FlapH1nge
iiring
Installation
Manual,
issued 4/15/87, or later rl\A approved revisions.
I I
The
installer must determine the compatibility of this modification with previously approved
1nadtf1cat1ons •
. ~ ..,,,,-/ ""'*' • 1'/'/'1•11
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26, 1987 ilf tlw 1rtl1/11ult' u /1u1mlmhlf hp a /tni' of ttnl
( I ttl1)
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If
,(lfJ(J, or 1mpmonm,ttl m1t u1Htlut.i: .i pmrJ, OI b.•lh ·
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Btpartmtnt of 1Cronsportation --.fl:dmJI 2t\1i'1tion
2tdmini&tmtion
~upplrmrntal 1=llpr ~crtificatr
JI{;~
SA1216Gl
.~~;--1<~,~.....1
6 • Knots 2U, Inc.
1941 Highland Avenue
Wilmette, IL 60091 l'k>
.a,U.u.-..,.d,~,,.,,.,,,,u:,O,nunti·
</'fl!w-t:
3
-¥
/'k/ Ci
V i1 Air
~bn.1.,(See
Type Certificate Data Sheet
2Al3
for complete certification
basis).
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2A11
.. 1/ak,: Piper Aircraft Corporation
!::t~Wn.,.,YJ~,!/';,ed.t,?-n (/A.a~:
Jt.-6/: PA-28-140, PA-28-150, PA-28-160, PA-28-180,
PA-28-235, PA-28R-180, PA-28R-200, PA-28-151,
PA-28-161, PA-28-181, PA-28-201T, PA-28-236,
PA-28R-201, PA-28R-201T, PA-28RT-201, PA-28RT-201T
Install Wing Root Fairings in accordance with Knots 2U, Inc. Wing Root Fairing
Installation Manual, issued 7/4/87, or later FAA approved revision.
The installer must determine the compatibi1ity of this modification with previously approved modifications.
/N~4
,Q/
6,.rn,:na/,;..,,,,.d'nt,, 4f. fiy, d, . r:fdmin4f/,.,,/,.~ ?'th,,.
·Y~.~.un,.~l"l""~/_,_h.;-n. orn
Mana r, Chicago Aircraft Certification Offic
ACE-115C, Central
Region. FAA
( I lllt)
A '!JI alt nation of this urtificalt is punuhnhll' b)' a finr of not exrudm!!, 11 ,()()(}, or 1mprisonmn1f not txutdin1: 3 ytars' or both·
'1 lus rirltfimtr may br tramfnud
111 artardancr milh !-AR 21. 47.
ilmttd .Smru of 2lmttica
Brpertrnrnt of
~ransportation -Jrdcml
£l\1iation £ldmini.Stration
~upplcmmtal ~~pc <r:crtificatc
~SA603GL
Knots 2U, Inc.
P. 0. Box 589
Harbor Springs, MI 49740
~ad.~·~r~A?,,./k,r,~Y1~·~#/c:;u~~~~.~~~~~
3
~~ Civil Air
~n.d/. (See Type Certificate Data Sheet No. 2A13 for complete fication basis).
~~-.~,-fu~~/.A~m/~e4'-.
2Al3
~:Piper
~,dd: PA-28-140, PA-28-150, PA-28-160
~x=~~R~~g 6 6
Installation of Aileron, Flap, and Stabilator Gap Seals in accordance with the Knots 2U, Inc. PA-28 Straight Wing Models Gap Seals
Installation Manual, issued May 5, 1984, revised May· 30, 1990, or later FAA approved revisions.
_£~~.ef,,-nd'~·.·
1. Any or all combinations of the above items are approved.
2. This approval should not be extended to other aircraft of this model o~ which other previously approved modifications are incorporated unless it is determined by the installer that the interrelationship between this change and any of those other previously approved modifications will introduce no adverse effect
. uE_.on the airworthiness of that aircraft.
Y.huk~a.ak.arnd~ A.t#u#~~,da£a.~. ~.~/-ab~/~~"Vat'.aAal/,wqruu;w~#l,anhZ~
.!Z .. u~~.u:.a
6 .,,,..,: February 2 4 , 19 8 2
9J 46 ,¥~.a>n..u·: Apr i 1 12 , 19 8 2
!./,,,,/,,-
NituiN'd:
,JU 1 y 2 1
I
19 8 2 r
Y 46
August 31, 1982;
26, 1984; October 11, 1990
Y
~
Donald P. Michal, Manager
Chicago Aircraft Certification Off ice
A '!Y alteration of this Cl!riificalt zs punuhable by a fine of not excud£ng S 1,000, or imprisonment not excuding 3 years, or both.
Thu crrt1ficate map bt transferred tn accordanet with FAR 21.47. f/V. ft>*M 8110-2 (10-68)
S1C No.. SA.603Gl
-
PIPER PA-28 STRAIGIT HlhG /ICXJE1..S
G4P S64LS MAMJAL REVISED 05/30/'!HJ
KNOTS 2U I N C
PART A. INSPECTIC>I
1. Daily ins;:ect:icn at preflight: to ensure there is no bending of the ccntrols~ t::Ent gap seals. abrading of rivets or ccntrol surfaces. or broken p;3rts.
2. When aircraft has been stored c:x.Jt:side during snow or freezing ccridit1cns, a careful inspecticn sh:x.Jld be made of area:s behind and under the accurrulat:icns. seals for ice
If 1ce is fOJnd, which cannot be rerroved by carefu1 brushing with seal held slightly away frcrn ccntro1 *surface, the aircraft sh::u1d be deiced or defrosted.
3. 100 I-a.Jr inspect:icns are suggested to check for abrading of the CO"'\tro1 surfaces and/or rivet hew:!ids. wear of the gap seals, ·and peeling of the Tef1cn coating. Check for loose rivets and/or other gap seal attacrrnent h..'9rdware.
PART B. MAINTENANCE
1. There are no spec:1a1 tools required to mciint:ain the seals. /lriy tools~ basic hand tools.
2. Maintenance of the gap seals is to keep the seal surface clean of 011. and dirt and the edge of the seal tcuching the CO"\trol surface sm:x:>thly. If the gap seal appears to be abrading the cc::ntrol surface 3M 5490 Tef1cn tape, or equivalent, may be applied to gap seal to act as a wear surface. Tre Teflcn tape sh::uld be applied before further flight: to prevent control wear.
3. If up:n inst:a11at:icn, or t:hro..sgh wear, there is a warp 1n the se.:!l,,
Of"'
1t 11es unevenly. you may drill a #40 size hole and cut the seal to the hole in a direct:ion 90 degrees t:o the trailing edge of the sea1. Dri11 the hole 1n the center of t:he warp~ 1/2 inch from the trailing e::ige of the surface to wh1ch the se.:tl is attached. The cut in the seol sh::AJld be trinmeld to give a slot 1/15th inch wide, with parallel edges. The slots shcu1d be no closer than S inches, to each other r or the end of the sea 1 . Refer to detai 1 c:n next page.
4. Wherl washing aircraft:, care sh:Juld be taken to brush a1cng the length of seal rather than perpendicular to, or across the seal. the
5. When aircraft 1s painted care sh::uld be taken to prevent p;3int, paint r'em:::M!r or solvents from contacting the Teflon. If Teflcn is dan\c:'lged, use the maintenance prcx:::edures with 3M 5490 tape, or equivalent.
PART C. BALANCING
1. If any changa is dcne to the rorizontal stabilator; if Teflon tape is added. slots are cut to r'elieve if warping, or if the seals are pc!inted, the stabilator m..Jst be re-balanced;
PART D. CRACKit4G, DEFECTS, l.CXlSE RIVETS
1. If cracks are fQ.Jnd in a gap seal, stop drill the crack. If there are rrore
3 cracks in a gap seal. the seal lll..JSt be replaced.
2. If the Teflon peals 3M 5490 Teflon tape, or equivalent. may be applied. than
3. If there are excessive bends or kinks in the seal, and the air flCM over the central surface is d1sturbed, the seal rrust be replaced.
4. If seal rivets beccme 1oose yo...i may drill the f"'ivets and r'e~ace with the next size rivet. f.
A -
'A. e.
P..
R o ~
PAGE -10-
..
)J~~~ cHl~~o
AlRCRAFl
.. "-
CERTlflCATJON OFFICE
. ~ENTRAJ.:. REGION
STC No. SA1194GL
PI PER PA--28
FLAP HINGE FAIRING MANUAL REVISED 10/15/88
SECTION 8. •MAINTENANCE MANUAL=
~RT A. INSPECTION
1. There are no special tools required to maintain the fairings.
Any tools needed are basic hand tools.
2. Daily inspection at preflight to check security of Flap Hinge
Fairing to aircraft attachment. Check for binding during flap operation. Also, check for cracks in the Flap Hinge Fairing.
3. Remove Flap Hinge Fairing, during annual or 100 hour inspections, to inspect flap hinge.
ART 8.
MAINTENANCE
1~ Keep slot of Hinge Fairing clear of obstructions. If the. aircraft is painted and paint stripper is used the fairings must not be permitted to contact the stripper. Removing the fairings during stripping may be the simplest way to protect them from damage.
'ART C. CRACKING OR DEFECTS
1. If any cracks are found on Flap Hinge Fairing, stop drill the crack.
2. If any crack exceeds 1/2 inch in length; or. if a crack runs from an attachment hole to the outer edge of the flange on the
Flap Hinge Fairing, the Fairing must be replaced.
K N 0 T S 2 u
E~A
'!'~
'P, P, R 0 V E D
I~OV 21988
4~~0 !fi~c;/(c
<:
:ut':r
1
~1CAllON O~tl-.:E
cr:;·~rnr,L. H£GiGN
PAGE -6x
N C
WING ROOT FAIRING
PIPER PA-28
STC No. SA1216GL REVISION ISSUE DATE 05/01/88
SECTION 12. =MAINTENANCE MANUAL=
K N 0 T S 2 U • I N C .
=========================
WING ROOT FAIRINGS
P I P E R P A 2 8
M A I N T E N A N C E M A N U A L
==================================
1. Before each flight, visually inspect the fairings for loose screws and proper fit.
2. Upon each annual or 100 hour inspection, inspect the fairings for proper f i t , loose screws, cracks or separated plies of the fiberglass.
3. If any of the above discrepancies are found; repair,
·using proper maintenance techniques and procedures, as outlined in FAR 43.13-1A
&
2
~
P.
E~X
E
R 0 V
'E:
D
A.U~
.~/pJ;~
0 11988
/f
C
6 -
/.)cA.:,"
/CHICAGO AIRCRAFT,
CERIIFJCAtlON OfffCE
C.ENIRAt: REGION
PAGE -5-
P. T.
AERO SERVICE, INC.
Hanger l, T.F. Green Airport
Warwick, R.I. 02886
401-737-7788
't
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
MAJOR REPAIR AND ALTERATION
(Airframe, Powerplant, Propeller, or Appliance)
Porm Approi1eJ
Budget Bureau No. 04-R060. l
FOR FAA USE ONL \''
OFFICE IDENTIFICATION
INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR H Appendix B, and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition •of this form.
MAKE
1. AIRCRAFT
SERIAL
NAME (As shown on registration certificate} ADDRESS (As shown on registration certificate)
2. OWNER
3. FOR FAA USE ONLY
UNIT
AIRFRAME
4. UNIT IDENTIFICATION
MODEL MAKE SERIAl NO.
######•##NH######### (As described in item 1 above)###HH##H#H###HH#
S. TYPE
REPAIR
AlTER·
ATION
POWERPLANT
PROPELLER
TYPE
APPLIANCE
MANUFACTURER
NAME AND ADDRESS
6. CONFORM! TY Sl A
8. KIND Of AGENCY
U.S. CERTIFICATED MECHANIC
FOREIGN CERTlflCATEO MECHANIC
CERTlffCATEO REPAIR STATION
MANUFACTURER
C. CERTIFICATE NO.
D. I certify that the repair and/or alteration made to. the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge.
DATE
Pursuant. t? the authority given persons specified below, the un the Administrator of the Federal Aviation Administration and is
FAA FLT. STANDARDS
INSPECTOR
MANUFACTURER ntified in item 4 was insi;ected in the manner prescribed by
APPROVED·
INSPECTION AUTHORIZATION
EC1ED
FAA DESIGNEE
DATE Of APPROVAL OR
REJECTION
REPAIR STAtlON
CERTIFICATE OR
DESIGNATION NO.
CANADIAN DEPARTMENT
OF TRANSPORT INSPECTOR
OF AIRCRAFT
SIG
FAA fon11
337·
(7-67) (8320)
NOTICE
'
Weight and balance or operating limitation changes shnll be entered in the appropriate aircraft record.
An alteration must be compatible with all previous alterations
to
assure continued conformity with the applicable airworthiness requirements.
8. DESCRIPTION OF WORK ACCOMPLISHED (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
0
ADDITIONAL SHEETS ARE ATTACHED
*U.S. GOVERNMENT PRINTING OFFICE: 1977-771-021/344
U.S. DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
MAJOR REPAIR AND ALTERATION
(Airfram•, Pow•rplant, Propeller, or Appliance)
Form Apprrwu/
BuJg,1 8uru1u No. 04-R060. l
FOR FAA USE O.\iLi'
OFFICE IOENilflCATION lNSTRlJCT10NS: Print or type 11! t'ntries. ~t' fAR 43.9, F\R H Appendix B. and AC 43.9-1 (or subsequent revision thereof} for instructions ind disposition of this form.
MAKE MODEL
1. AllCRAFT
SERIA1. NO.
2. OWNER
UNl.f
POWfR,lANT
HllAl NO.
S. TYPE
If PAii
Al TEI·
AflOM
xx
APPLIANCE
IMNVP 4ClUU ll
6. CONFORMITY STATEMENT
B. KIND Of AGENCY
. $. CUTIFICATEO MECHANIC
OltEIGN. CflTlftC.AfED MfCHAMIC
C. CERTIFICATE NO .
D. I certify that the repair and/ or alteration made to the unit( s) identified in item 4 above and described on the reverse or attach~enu h.ere1o hav~ ~t'n made in accordance w.ith the requiremenu of Part 43 of the U.S. Federal Aviation Regulation~ a.nd that the information furnished herein is true- and correct co the best of my knowledge.
DATE
Puriua.nt to the authority given penons specified below, the unit Jdentified in item 4 was inspected in the manner prescribed by
tu
Ad.minittracor of the federal Avution Administration and ia APPROVED REJECTED
OTHER (Specify]
•M PLT. JTANOAIOS
INUICTOI
M.ANUf ACTUUtt INSPECTION AUTHOfUZATION
IY
IM OISIONEE
FAA Fonn 337
t1-011 (8320)
NOTICE
Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements.
8 . DESCRIPTION OF WORK ACCOMPLISHED (If more space i s required , attach additional sheets .
Identify w i th aircra ft nat io nal i ty and registration mark and date work completed .
)
1> lnshlled of Apello 604TCA lo ua C systee according to 1illlufadurtrs instructions t 560-0023 Rev 03. Power to unit is suppl.itd throuth
1
N-gtutt TtlH l wire, protectN by
1
PH W58XC4C4Cl2A-5 up Circuit BrHktr 111d con11tde4 to the avi 011ic1 buss. Unit is p1111l 10W1ted in Ritt radio shck.
21 All interface virin9 is Ttfzel, and all 10Untin9 hardvare is staialess""t~eel.
31 Strudt11l MM1:nti119 of tll uih is sufficifflt to enturt the restraint of the equipaent lltlen subjtdN to the
HergflKy lln4int load appropri1t1 to the tircuft ut19ory. Refer to updated 'W.ighl and llhnce O.h and kppluental
Equipeent List' this d1t• for station loution of instilled equiplllflt,
4)
Full electric lotd don not cmnd 80% of tht 1l1ctriul 1y1tH up1city usin9 ukul1tH ttthod reftrettCe4 in AC
43.13-llt Chtp 11
1
StdiOG 2, Piri 428.
5) lnsh1l1H01 perfoned in accordntf vith AC 43. t3-IA
1
43.13-2A, C111pt1r1 2 • 3
1 pir1trtphs 21 thra ~.
Chapttr 15, Sectioas 1 thru 6
1
Pau:gnphs 747 thru 853 in• AC
6) 6r0Wld Md flight t11h p!rfor.O in 1ccort11Ka vith AC 20-121, StctiOft 6, Put A, Pangnph 1.
7> lo flight ii prediuttd upoa t~ uu of Util Loran C.
8) ltircuft is phuritd
•vn
USE 111.Y Of' LORMI c•.
9> ll.nuf1d1111r's op1r1tin9 inshuctioos providtd to 1ircrtft ovHr.
10) Aircraft 'We ight 1114 BllllKt Dah, and ~lHtnhl Equip_9fflt List• revised .
• c
C FAA AC 72-4901\
0 ADDITIONAL SHEETS ARE ATTACHED
-(/U.S. GOVERNMENT PRINTING OFFICE: 1986-659-121/40146
CARROLL AVXON:ICS• :INCa
HAN&AI SOOTH CMPLEX TIH HARVEY RD. IESTERlY, RI. 82891 (401) 349-HtSO fMI WSR25BM
REVISE.I> WEIGHT
AN,D
BALANCE DATA
AND SUPPLEMENTAL EQUIPMENT LIST
AIRCRAFT MAKE ltttD lliDEl: PIPER PA-28-180
Aircraft Serial luaber: 28-7505222
Aircraft Registration Nui1r1
Date of this Revision: ts-12 ... 90
Dat.e of PreviOIS R1v:i~ioot
HfffffffHHUHHHlfffffffflHHfffHHfffHHHHffiHHffH.ffffffHHffHHHHHIHHiHHHHHfffffffHJHHffiHHHH
A i r c r a f t :
WEISHT
1515.19
ARM
86.56
MOMENT
131156.97
Inst al 1 ed:
I) APOLLO 604TCA LORAN C
2)·APOU.O A..,16·MTEINA
New Empty ,weight:
New Center of Gravity,:
New Moment1
3.18
0.56
1518.93
58 .. 00
85.00
86 .. 50
194.44
47.60
131389.01
Gross Weight1 · <Noraal.) 2450 .. 00 lbs
Gross Waight:
New
<Utility>
Useful Load: <NormaD
1950.00 lbs.
931.07 tbs.
(Utility> 43.1 .. 07 tbs ..
NOTE:
It is the responsibility of the pilot-in-coanand to insur.e that the aircraft is properly loaded using the above Weight
!Oc!ldl.ng, charts. and Balance data and the owners manual
Inspector for CARROLL AVIONICS, INC.
2377051 F.A.A. Certified Repair Station 4t UQ5R25BN
US Department ot
Transportation feOlral AvkJtton
Admlntsffaflon
MAJOR REPAIR AND ALTERATION
(Airframe, Powerplant, Propeller, or Appliance)
Form Approved
OMB No. 2120-0020
For FAA Use Only
Office Identification
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9· 1 {or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421 ). Failure to report can result in a civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act of 1958).
1. Aircraft
Serial No.
Name (As shown on registration certificate)
2. Owner
3. For FAA Use Only
4. Unit Identification
Model
5. Type
Repair Alteration Unit
AIRFRAME
Make Serial No.
POWER PLANT
PROPELLER
APPLIANCE
Type
Manufacturer
A Agency's Name and Address
6. Conformity Statement
8. Kind of Agency icated Mechanic ificated Repair Station
C. Certificate No.
D. l certify that the repair and/or alteration. made to the unit(s) identified in item 4 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge.
Date Signature of Authorized Individual
7. Approval for Return To Service
Pursuant to the authority given persons specified below,
Administrator of the Federal Aviation Administration and is
FAA Flt. Standards
Inspector
Manufacturer identified in item 4 was inspected in the manner prescribed by the
0 REJECTED
Other (Specify)
Inspection Authorization
BY
FAA Designee Repair Station
Person Approved by Transport
Canada Airworthiness Group
Date of Approval or Rejection Signature of Authorized Individual
FAA Form 337
(4-87)
NOTICE
Weight and balance or operating (imitation changes shall be entered i n the appropr i ate aircraft record . An alteration must be compatl.ble w i th all previous alterat i ons to assure continued conformity with the applicable a i rworthiness requ i rements .
8. Description of Work Accomplished
(If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
D Installed 3M WX-B Weather Happing System in accordance with manufacturer's instructions (78-8041-7921-2).
2) Installation performed in accordance with AC 43.13-lA, Chapter 15,
Sections 1 thru 6, and AC 43.13-2A, Chapters 2 & 3.
3) Aircraft "Weight and Balance Data, and Supplemental Equipment List" revised.
=====================================END==============================
D Additional Sheets Are Attached
A r r a f l l e d :
New
New
New Ms::>ment:
SED WEIGHT AND BALANCE DATA
AND SUPPLEMENTAL IPMENT LI
156.97
S.
FAA AC 72-49flfi
ADDITIONAL. SHEETS f:r
AITACHEO
GOVERNMENT PRINTING
CHER
FOR
A
H
MODEL
PIPER AIRCRAFT CORPORATION
APPROVAL SIGNATURE AND
ISSUED: MAY 14, 1973
REVISED: NOVEMBER 21, 1975
REPORT: VB-547
MODEL: PA-28-180
CHEROKEE ARCHER
WEIGHT AND BALANCE LOG OF REVISIONS
Revised Pages
1
REPORT: VB-547
MODEL: PA-28-180
CHEROKEE ARCHER
WEIGllT AND BALAN('E U)(; OF Rl•:VISIONS (cont)
Revision Revised Pages
7 5-1
5-3
5-7
Description and Revision
Revised text info.
Revised text info.
Revised Weight and Balance Data.
Approved Date
WcaJe-11~
March 16. 1984
ISSUED: MARCH 16, 1984
REPORT: VB-547 PAGE 5-v
MODEL: PA-28-180
CHEROKEE ARCHER
WEIGHT AND BALANCE
In order to achieve the performance and flying characteristics which are designed into the airplane, it must be flown with the weight and center of gravity (C.G.) position within the approved envelope. The aircraft offers flexibility in loading. However, you cannot fill the airplane, with the maximum number of adult passengers, full fuel tanks and maximum baggage. With the flexibility comes responsibility. The pi lot must insure that the airplane is loaded within the loading envelope before he makes a takeoff.
M isloading carries consequences for any aircraft. An overloaded airplane will not take off, climb or cruise as well as a properly loaded one. The heavier the airplane is loaded, the less climb performance it will have.
Center of gravity is a determining factor in flight characteristics. If the C.G. is too farforward in any airplane, it may be difficult to rotate for takeoff or landing. If the C.G. is too far aft. the airplane may rotate prematurely on takeoff or try to pitch up during climb. Longitudinal stability will be reduced. This can lead to inadvertent stalls and even spins: and spin recovery becomes more difficult as the center of gravity moves aft of the approved limit.
A properly loaded aircraft, however, will perform as intended. Before the airplane is licensed, a basic weight and C.G. location is computed. (Basic weight consists of the empty weight of the aircraft plus the unusable fuel and full oil capacity.) Using the basic weight and C.G. location, the pilot can easily determine the weight and C.G. position for the loaded airplane by computing the total weight and moment and then determining whether they are within the approved envelope.
The basic weight and C.G. location for a particular airplane arc recorded in the Weight and
Balance section of the Airplane Flight Manual. The current values should always be used. Whenever new equipment is added or any modification work is done, the mechanic responsible for the work is required to compute a new basic weight and basic C.CL position and to write these in the aircraft log book. The owner should make sure that it is done.
A weight and balance calculation is necessary in determining how much fuel or
"""J"'F,••F," be boarded so as to keep within allowable limits. Check calculations prior to adding fuel to against improper loading.
The following pages arc forms used in weighing an airplane in production and in computing basic weight. basic C.G. position, and useful load. Note that the useful load includes fueL oiL baggage, cargo and passengers. Following this is the method for computing takeoff weight and
C.G.
ISSUED: MAY 14, 1973
REVISED: MARCH 16, 1984
REPORT: VB-547 PAGE 5-1
MODEL: PA-28-180
LEFT BLANK
ISSUED: MAY 14, 1973
WEIGHT AND BALANCE DAT A
WEIGHING PROCEDURE
1. a. Be certain items checked in the ·~·"""*""" 11 in proper location in the '1 1 r~'\l'!l1'lP b. c. open tank until all undrainable
REVISED: a.
when airplane is ahead of at the intersection and tapered section.
MAY 14, 1973
b. measuring from a one leading at the intersection section, horizontally and parallel to the "''""""' 1
""'""
""""u~'"""1i1n.,, c. Obtain measurement "B" the distance from the main wheel and parallel to the airplane to each side of the nose wheel axle. average the measurements. d. The empty center of and undrainable oil) can be determined including the following formula:
Arm 78.4 +A - B(N)
-y-
C G. Arm
=
78.4
+ (
inches
5. LICENSED EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY
Arm Moment
Empty Weight (as weighed)
Unusable Fuel ( 13-1 /3 pints)
Licensed Empty Weight
+10.0 +1030
ISSUED: MAY 14, 1973
REVISED:
JANUARY
20, 1975
REPORT: VB-547 PAGE 5-5
MODEL: PA-28-180
THIS INTENTIONALLY LEFT BLANK
VB-547 PAGE 5-6
MODEL: PA-28-180
ISSUED: MAY 14. 1973
WEIGHT AND BALANCE DATA
MODEL PA-28-180 CHEROKEE
Item
AIRPLANE WEIGHT
Weight
(Lbs)
G.Ann x (Inches Aft of Datum)
Actual
Computed
10.0 103.0
Moment
1030 kn'l'°'tir nto
1 nnT lS n'3T~..-."'~ as dry empty weight (including paint and hYClfa\JIJC
1.8 lbs undrainable oiL
AIRPLANE USEFUL LOAD
=
Useful Load lbs) = (2450 lbs) ( lbs
(1950 lbs) ( lbs
IS LICENSED EMPTY WEIGHT, C.G. AND USEFUL LOAD FOR THE AIR
LICENSED AT THE FACTORY. REFER TO APPROPRIATE AIRCRAFT RECORD
\VHEN ALTERATIONS HAVE BEEN MADE .
........... .,,,,_,,.,,, MAY 14, 1973
REVISED: MARCH 16, 1984
REPORT: VB-S47 PAGE
MODEL: PA·28-1
Category) range and weight and balance
Moment
118.l 40154 inches aft of the
Since this point ua1cun;t; requirements.
OWNER TO INSURE
ISSUED: MAY 14, 1973
WAUKEGAN AVIONICS, INC.
WAUKEGAN MEMORIAL AIRPORT
3550 N
.
McAree
Waukegan. Illinois 60087
312-336-6075
MINOR ALTERATION AND EQUIPMENT LIST REVISION
Al RC RAFT MAKE
-----=-P...:I=.P-""E=R,_ _ _ _
Nll 85X
PA-28-180
SERIAL NO . 28-7505222
DATE 1 I 2 3 I 8
5
DESCRIPTION OF WORK ACCOMPLISHED:
INSTALLED NARCO AR-500 ENCODER. SEE FAA 337 THIS DATE FOR
APPROVAL INFORMATION.
, WEIGHT AND BALANCE EQUIPMENT LIST REVISION
AIRCRAFT EMPTY WEIGHT
INSTALL AR-500
1501. 4
1. 0
1502.4
86.4
52.0
129779
52
129831
NEW EMPTY WEIGHT 1502. 4 LBS.
NEW USEFUL LOAD
947.6 LBS .
NEW EMPTY WEIGHT C.G. 86. 4 INCHES
TH ORI ZED SIGNATURE
CRS C.O
. 3-46
2.
11, Wil is T.
UNIT
AIRFRAME
Cicero
Midlothian, IL 60445 x
LLED NA
OC74C CLASS L
AR-500 ENCODER, 8 MATED WITH CO AT50A,
FULLY CHECK ALTI
AC 43-6A A ND X 1.
R ING STEM N ACCORDANC
BOOK ENTRY DATED 1/23/85
IAN WITH FAR 91.36, 91.171, nd 91 172.
WITH
COM-
END-------- ----
ELGIN PHONE
741-6510
CHICAGO PHONE
626-6436
Area Code 312
P.
~~S ·EDGCUMBE INC.
e.
557 ILL! 60
MINOR ALTERATION AND ST REVISION
COMPLETE
AIR CHARTER SERVICE
AIRFRAME & POWERPLANT SERVICE
AIRPORT FACIUTJES
AIRCRAFT MAKE
Piper
--------
MODEL PA28-180 SERIAL NO.
N1185X
28-7505222
DATE 9 /4 /81
DESCRIPTION OF WORK ACCOMPLISHED: Installed Narco Com-810, Nav-825,
ADF-141, CP-136M & DME-890, cables & antennas. All work done in accordance with manufactures specifications, drawings and A.C.
43.13-lA & A.C. 43.13-2. Electrical load does not exceed electrical generating capabilities.
WEIGHT AND BALANCE -
AIRCRAFT EMPTY WEIGHT
INSTALLED
Com-810
Nav-825
ADF-141
DME-890
ID-825
CP-136M
ADF-141 Indicator
Loop Antenna
Loop Cable
Sense Antenna & Cable
#2 VHF Com Antenna
112 Cable
LIST REVISION
1480.5
3.5
3.3
2.5
3.9
1.0
2.0
1. 3
1.6
• 6
• 4
• 3
86.6
57.5
57.5
58.5
57.5
60.0
59.0
61. 0
162.0
105.5
147.5
-~---8
128262
201
190
146
224
60
118
79
259
63
59
58
60
129779
NEW EMPTY WEIGHT 1501.4
.NEW USEFUL LOAD 948.6
LBS.
NEW EMPTY WEIGHT C.G. 86.4
LBS.
INCHES.
WEIGHT AND BALANCE DATA
5/23/75
Nll85X
AIRPLANE EMPTY WEIGHT x
85.7
.6
(1480. 5
(1480. 5 469.5
1480.5 86.6 128262
2450 90.7 222277
2800
2600
C. G. RANGE AND WEIGHT
CHEROKEE ARCHER
EQUIPMENT LIST
The following is a list of equipment which may be installed in the PA-28-180. marked with an "X~' are items installed when the airplane was delivered by the
Item Item
Weight
Lbs.
Arm Aft
Datum Moment
Cert.
Basis
A. Propeller and Propeller Accessories ropell iper S
7 6EM8S5-0-60
850077-8
Spinner and Attachment Plates
Piper Dwg. 65803, 65804, 65805
39.2
4.5
3.8
3.4
149
15
TCP4EA
TC 2Al3
ISSUED: MAY 14, 1973
NOVEMBER 6, 1973
REPORT: VB-547 PAGE 5-11
MODEL: PA-28-180
CHEROKEE ARCHER
I
'
Item
B.
Item
Weight Arm Aft
Datum Moment
Cert.
Basis and
Engine - Lycoming Model
0-360-A4A Piper Dwg. 62941-14
&-15 288.9
Engine - Lycoming Model
0-360-A4M Dwg. 6 .0
Fuel Pump, Electric Auxiliary,
Bendix Model 478360
Fuel Pump, Engine Driven,
Lycoming Dwg. No. '74082,
148 or 75246
Oil Cooler, Piper Dwg. 18622
Harrison• C-8526250
Air Filter, Fram Model CA-161
PL or Purolator AFP-2
Starter - Lycoming 76211
(Prestolite MZ4206)
Oil Filter - Lycoming No.
75528 (AC #QF5578770)**
Oil Filter - Lycoming
#LW-13743 (Champion
#
CH-48110)**
L8
1.7
1.9
.9
*
18.0
3.3
2.8
.1
36.3
41.3
29.5
14.5
35.5
35.5
6096
66
62
78
27
261
117
TC P286
TC 2Al3
TC 2Al3
TC P286
TC 2A13
99
TC P286
3
TC 2AI3
*Included in Engine Weight.
**Serial nos. 7505001 and up
REPORT: VB-547 PAGE 5-12
MODEL:
PA-28-180
ISSUED: MAY 14,
1973
REVISED: NOVEMBER 21, 1975
Arm Aft
Moment c. and Brakes
109.6
Cleveland Aircraft Products
Wheel Assembly No. 40-86
Brake As..~embly No. 30-5 5
(b) Two Main 4-Ply Rating
6.00-6 with Regular Tubes
One Nose Wheel 6.00-6
(a) Cleveland Aircraft Products
Wheel Assembly No. 40-76B
(Less Brake Drum)
(b) One Nose Wheel 4-Ply Rating
Tire 6.00-6 with Regular
Tube
12.8 31.0
13
2Al3
Item
D.
Item
Stall Warning Device, Safe
Flight Instrument
No.
Voltage Regulator, Wico
No. X-1
Battery l 2V, A.H.,
Rebat Model
Overvoltage Relay, Wico
Electric No. X16799
Annundator Lights*
Weight Arm Aft
Lbs. Datum Moment
Cert.
Basis
.2
.9
21.9
.5
.9
80.2
51.9
168.0
.4
55.5
16
47
3679
TSO C54
TC 2Al3
TC 2Al3
50
TC 13
TC 2A13
CHEROKEE ARCHER
ISSUED: MAY 14, 1973
REVISED: JANUARY 20, 1975
REPORT: VB-547 PAGE 5-15
MODEL: PA-28-180
Item
PS50039-4-3
Seats
Dwg. 76170
Manual
Tow Bar,
99458
Dwg.
Toe Brakes (Dual)
Piper Dwg. 63473
Lbs.
Arm Aft
Datum Moment
Cert. l.5 81.9
1.5 119.6
123 TSO C22
TC 2Al3
I .4
22.8
123.0
124.2
1.3
11.0
161.8
49.6
172
2832
210
546
TSO
TC 2Al3
TC 2Al3
TC 2A13
TC 2Al3
REPORT: VB~547 PAGE 5-16
MODEL: PA-28-180
ISSUED: MAY 14, 1973
REVISED: JUNE 17, 197 4
CHEROKEE ARCHER
Item Item
G.
Engine and Engine Accessories
(Optional Equipment)
Weight
Lbs.
Arm Aft
Datum Moment
Cert.
Basis
Vacuum Pump, Airborne Mfg.
Co., Model No. 1 Q..113A l, l 13A5, or 200cc and Drive 5.0
Oil Filter - Lycoming No.
75528 (AC~OF5578770)*
Oil Filter - Lycoming
•LW-13743 (Champion
•ctt-48110)*
3.3
2.8
Vacuum Regulator, Airborne*
Mfg. Co.,~ l 33A4
Vacuum Filter, Airborne
Mfg. Co.,* 117-1 Piper
Dwg. 66673
.6
.3
Vacuum Pump, Airborne
Mfg. Co., Model 21 lcc and Drive, PAC 79399-0 3.2
Low Vacuum Annunciator Light
* *
Neglect
Vacuum Regulator, Airborne**
Mfg. Co.
#
2H3- l 9 .5
32.0
35.5
35.5
52.0
52.0
32.0
52.0
160
117
TC 2Al3
TC 2Al3
99
31
16
103
26
TC 2Al3
TC 2A13
TC 2A13
TC 2A13
TC 2A13
TC 2A13
*Serial nos. 7405001 through 7405290
**Serial nos. 7505001 and up
ISSUED: MAY 14, 1973
REVISED: JUNE 17, 197 4
REPORT: VB-547 PAGE S-17
MODEL: PA-28-180
CHEROKEE ARCHER
Item Item
H. Equipment (Optional
Equipment)
Weight Arm Aft
Lbs. Datum Moment
Cert.
Basis
Landing Light, G .E.
Model 4509
Navigation Lights (2)
Grimes Model Al 285
(Red and Green)
Navigation Light (Rear) (1)
- - -
Grimes Model 2064 (White)
Battery l 2V, 35 A.H.,
Rebat R-35 (Weight 27 .2 lbs.)
Cabin Light, Piper Dwgs.
66632-0 & 95229-0
Cabin Speaker SB-:15052 or
6EU 1937,, Quincy Speaker Co.,
Oakton, Indiana
Auxiliary Power Receptacle,
Piper Dwg. 65647
External Power Cable 62355-2
Piper Pitch Trim, Piper
Dwg. 67496-2 or 67496-3**
Heated Pitot Head
Piper Dwg. 69041-5
1.5
.5
263.4
13.1
.4
.2
106.6
281.0
5.3 *
168.0
.3 99.0
395
7
TC 2A13
TC 2Al3
43 TSO C30b
56 TSO C30b
890
30
TC 2Al3
TC 2Al3
.8
2.7
4.6
4.3
.4
99.0
178.5
142.8
155.3
100.0
79
482
657
668
40
TC 2AI3
TC 2A13
TC 2Al3
TC 2A13
TC 2Al3 and moment difference between standard and optional equipment. numbers 287505080 through 287505259.
REPORT: VB-547 PAGE 5-18
MODEL: PA-28-180
ISSUED: MAY 14, 1973
REVISED: NOVEMBER 21, 1975
.4
(Fin Tip)
Cable
Lights (Wing Tip) (2)
Cables
3.0
.3
2.0
.4
.4 ,230.7
106.6
115.6
105
92
32
231
3
TC 2Al3
TSO C30b
TC 2Al3
CHEROKEE
Item
J.
Item
Equipment)
Weight Ann Aft
Lbs. Datum Moment
Cert.
2.5
1.2
.7
2.3 Attitude
Omni Coupler,
#
1 C388 .9 iii
1C363-1-183R
Panel Unit.~ or-4
AutoControl III B **
Roll Servo '* i l-183R
- - -
Console, ~ l C338 {S/N 10000 & up)
Cables
Attitude Gyro. *52066
Directional Gyro. ft
52054
Omni Coupler, ~ l C388
2.5
.7
2.4
2.5
1.0
.s
2.7
2.9
LO
..,
1
60. l
95.S
59.4
59.0
59.3
1
93.4
59.4
122.2
60. l
95.5
59.4
59.0
59.3
72
67
137
189
STC SA l 406SW
STC SAl
SAl406SW
STC SA l 406SW
STC SA l 406SW
53 STC SA l 406SW
306 STC SA 1406SW
65 STC SA 1406SW
143 STC SA l 406SW
306 STC SA l 406SW
60 STC SA I 406SW
48 STC SA l 406SW
160 STC SA l 406SW l 71 STC SA1406SW
59 STC SA l 406SW
*Serial nos. 7405001 through 7405290
**Serial nos. 7505001 and up
ISSUED: MAY 14, 1973
.REVISED: JUNE 17, 1974
REPORT: VB-547 PAGE S-21
MODEL: PA-28-180
Item
Weight Arm Aft
Lbs. Datum Moment Basis
Comm/Nav)*
Narco
VOA-SOM Omni
Omni
Narco VOA-40 Omni Converter*
*
*
Narco Comm lOA VHF
Transceiver
Narco Comm 1 lA VHF
7.5
15.0
2.1
1.9
1.9
3.9
3.6
Narco Dual Comm 1 IA VHF
Transceiver
Narco Nav I 0 VHF
N arco Nav l I VHF Receiver
Nav 1 2 VHF Receiver
Narco Dual Nav 11 VHF
7.1
1.9
2.8
3.4
King KX-175 ( ) VHF Transceiver
King KN-73 Glide Slope
Receiver
King KN-77 VOR/LOC
Converter
King KNI-520 VOR/ILS
Indicator
King KX-175 ( ) VHF Transceiver
(2nd)
King KN-77 VOR/LOC
Converter
King KNI-520 VOR/ILS
Indicator
*Serial nos. 7405001 through 7405290
8.6
4.2
2.8
5.6
9.4
3.2
3.6
2.8
REPORT: VB-547 PAGE 5-22
MODEL: PA-28-180
57.4
57.4
58.6
58.6
58.6
58.6
56.6
184.3
183.6
60.5
56.9
56.9
59.9
59.9
59.9
57.4
56.6
183.6
60.5
328
532
590
661
169
408
111
164
199
427
854
126
114
114
224
207
487
771
169
TC 2Al3
TC 2Al3
TC 2A13
TC 2Al3
TC 2A13
TC 2A13
TC 2A13
TC 2Al3
TC 2A13
TC 2Al 3
TC 2Al 3
TC 2Al3
TC 2Al3
TC 2 13
TC 2A13
TC 2Al3
TC 2Al3
TC 2A13
TC 2A13
ISSUED: MAY 14, 1973
REVISED: JANUARY
20, 1975
Anti Static Kit
Basis
x x
Narco DME-890
Narco CP-136M
3.9
2.0
57.5
59.0
224
118
3
Cert.
Item l 3 VOR/LOC/GS
Indicator*
&
3.9
1.5
L3
60.4
59.4
161.5
108.0
51.0
50.0
LS l
1 I 2Al3
TC 2A13
2AI3
2A13
3
2Al3 o Com-810
Narco Nav-825
Narco ID-825
Narco ADF-141
Ind.
3.5
3.3
1.0
2.5
1.3
57.5
57.5
60.0
58.5
61.0
201
190
60
146
79
Item Item
K. Radio Equipment (Optional
Equipment) (cont)
Narco Dual Comm 111 B VHF
Transceiver
*
Narco Nav 14 VHF Receiver
*
Narco Nav 114 VHF Receiver*
Narco UGR-3 Glide Slope*
Receiver
Cable
Antenna
Cable, Antenna
Narco CP-125 Audio Selector
Panel*
Narco ADF-140
*
Receiver
Servo Indicator
Loop Antenna
Cable, Loop
Sense Antenna and Cable
Narco Dual ADF-140
*
Receivers
Dual Needle Indicator
Loop Antenna~ l
Cable, Loop
:it:
I
Sense Antenna and Cable'#: 1
Loop Antenna fl;
2
Cable, Loop
1:
2
Sense Antenna and Cable
:\I:
2
- Remote for Dual Ind.
Narco DME-190*
Receiver
Antenna
Cable, Antenna
Microphone (Dynamic)*
Piper Dwg. 68856-11
CHEROKEE ARCHER
Weight
Lbs.
Arm Aft
Datum Moment
Cert.
Basis
7.8
2.5
2.5
2.4
1.8
0.4
0.5
57.4
57.4
57.4
173.8
128.0
87.4
145.0
.0
58.3
61.0
162.0
105.5
147.5
58.3
61.0
162.0
105.5
143.8
150.0
93.5
143.8
185.5
61.8
113.9
85.6
69.9
2.5
1.3
1.6
0.6
0.4
5.0
3.5 l.6
0.6
0.4
L6
0.6
3.0
2.0
5.2
0.3
0.4
0.6
448
144
144
417
230
35
TC 2Al3
TC 2AI3
TC 2Al3
TC 2Al3
TC 2A13
TC 2Al3
TC 2A13
TC 2Al3
TC 2A13
TC 2A13
TC 2A13
TC 2Al3
TC 2Al3
TC 2Al3
TC 2Al3
TC 2A13
TC 2A13
TC 2A13
TC 2Al3
TC 2Al3
TC 2Al3
TC 2Al3
TC 2A13
TC 2A13
TC 2Al3
TC 2A13
121
146
79
259
63
59
292
214
259
63
58
240
56
431
371
321
34
34
42
*Serial nos. 7505001 and up
ISSUED: JUNE 17, 1974 REPORT: VB-547 PAGE 5-25b
MODEL: PA-28-180
CHEROKEE ARCHER
Item Item
(Optional
Fire Extinguisher,
Scott Aviation • 42211-00,
Piper Dwg. 76167-2
Assist Step
Piper Dwg. 65 384-0
Inertia Safety Belts
(Rear) (2) 0.8 lbs. each
Piper Spec. PS50039-4-14
Nose Wheel Fairing
Piper Dwg.. 65348-2
Main Wheel Fairings
Piper Dwg. 65237
Vert. Adj. Front
Dwg.
(Left) Piper Dwg. 79591-0
Vert. Adj. Front
(Right)
Piper Dwg. 76340-1
Dwg. 1-1
Super Cabin Sound Proofing
Piper Dwg. 79030-3
Lighter, l 2V Universal
#200462 and Coat Hook
62353-5
Strap, Piper Dwg. 79455
4.6
1.8
71.0
Moment
2Al3
3
1.6
3.6
7.6
140.3
36.3
113.6
*
6.6
*
6.6
*
*
18.1
.2
.2
80.7
80.3
80.0
86.8
62.9
109.5
109.5
131
863
2Al3
TC 2Al3
TC 2Al3
530
544
TC
2Al3
TC 2Al3
TC 2Al3
1571
13
22
TC 2A13
TC 2Al3
TC 2Al3
TC 2A13
CHEROKEE ARCHER
Item Item
Weight
Lbs.
L. Miscellaneous (Optional Equipment) (cont)
Arm Aft
Datum Moment
Cert.
Basis
Overhead Vent System with
Ground Ventilating Blower
Piper Dwg. 7 6304-2
Overhead Vent System
Piper Dwg. 76304-0
Overhead Vent System,
Piper Dwg. 76304-9
Overhead Vent System with
Ground Ventilating Blower,
Piper Dwg. 76304-10
13.2
5.6
6.4
14.0
Alternate Static Source
Calibrated Alternate Static Source
Placard Required: Yes No
Headrest (2) (Front) Piper
Dwg. 99255-3 or 79337-18
.4
Headrest (2) (Rear) Piper
Dwg. 99255-3 or 79337-18
Air Conditioning Installation
99575-0
Zinc Chromate Finish
Piper Dwg. 65665
2.2
67.4
5.0
3.0 Corrosive Resistant Kit
Stainless Steel Control Cables
170.4
157.3
159.6
170.7
61.0
94.5
132.1
102.8
158.0
106.0
2249
881
1022
2Al3
TC 2Al3
TC 2Al3
2390
24
TC 2A13
TC 2A13
208
291
6929
790
318
TC 2Al3
TC 2Al3
TC 2Al3
TC 2Al3
TC 2Al3
TC 2Al3
TOT AL OPTIONAL EQUIPMENT
ISSUED: MAY 14, 1973
REVISED: NOVEMBER 21, 1975
REPORT: VB-547 PAGE 5-27
MODEL: PA-28-180
EXTERIOR FINISH
Trim C o l o r - - - - - - - - - -
Accent Color - - - - - - - - -
Registration No. C o l o r - - - - - - -
Type Finish - - - - - - - - - -
REPORT: VB-547 PAGE 5-28
MODEL: PA-28-180
ISSUED: MAY 14, 1973
REVISED: NOVEMBER 21, 1975
CHEROKEE ARCHER
OPERATING INSTRUCTIONS
PREFLIGHT
I. a.
Release scat belt controls. b. Master switch ON. c. Check fuel indicators.
Master switch and ignition OFF.
Check for external and operational interference of control surfaces or
3. h. a. b. c. d. e. f. g.
Insure that wings and control surfaces are free of snow. ice or frost. check fuel supply and secure caps.
Drain fuel tank sumps (two), check for water. sediment and proper fuel.
Drain fuel sump (left side of aircraft), check for water, sediment and proper fuel.
Check that fuel vents are open.
Check main landing gear shock struts for proper inflation (approximately 4.50 inches showing).
Check tires for cuts, wear and proper inflation.
Check brake blocks and discs for wear and damage.
.------------··------2 ---·---··------··- _,
OPERATING INSTRUCTIONS
REVISED: MARCH 16, 1984
4
------··---·-·----··---·----- 3 --.. ·---·----"'
that all
INSTRUCTIONS
MAR CH lfi, 1979
CHEROKEE ARCHER l . the throttle fuJL
2. the master switch ON.
3. Turn the fuel pump OFF.
4. Put mixture control in IDLE CUT-OFF.
5. the starter switch and advance the mixture control and retard the throttle.
When the
P.nortnP indicated will take a in. When
~rn,,!lnt'P the throttle to 800 RPM. oil pressure is not and determine the trouble.
In
cold weather it an oil pressure indication. If the engine has
U U • ' - A o V ' - J V ' " ' ·
~"I'->·"''"' Troubles and Their Remedies." to start~
Starter manufacturers recommend that two minute rest between be limited to
Longer cranking will shorten the seconds with a of the starter.
STARTING POWER SOURCE*
6.
WARM-UP
2.
3.
4.
SWITCH to OFF.
RED lead of PEP kit jumper
"""1"
1
•
0 to POSITIVE (+)
" " ' and BLACK lead to NEGATIVE(-) terminal. into located on
ON and ....... ,..., nO£•r• of
MASTER SWITCH to and remove check alternator ammeter
IF IS NO for not more than two at low RPM as in warm
VVv<.LLl!LI v ...... ..., ...
J.,., ... may result in the
"H"''"'"'~''"' at 2000 RPM. The on either u1a,i::;.1u'"'"v within 50 RPM of the other. Prolonged on one
±
.1 n at
OPERATING
ISSUED:
JULY 7-3
STALLS
CHEROKEE ARCHER
AIRSPEED DATA
All airspeeds quoted in this manual are calibrated unless otherwise noted. Calibrated airspeed is indicated airspeed corrected for instrument and position errors. The following table gives the correlation between indicated airspeed and calibrated airspeed if zero instrument error is assumed. This calibration is valid only when flown at maximum gross weight in level flight.
AIRSPEED CORRECTION TABLE
Flaps 0°
IAS-MPH
CAS-MPH
60 70 80 90 100 110 120 130 140 150 160
68 76 84 92 101 110 119 128 137 147
Flaps 40°
IAS-MPH
CAS-MPH
60 70 80 90 100 110 120
66 74 82 90 99 109 118
ENGINE POWER WSS
The most common cause of engine power loss is mismanagement of the fuel. Therefore, the first step to take after engine power loss is to move the fuel selector valve to the tank not being used. This will often keep the engine running even if there is no apparent reason for the engine to stop on the tank being used.
If changing to another tank does not restore the engine:
1. Check fuel pressure and turn on electric fuel pump if off.
2. Push mixture control to full "RICH."
3. Check ignition switch. Turn to best operating magneto - left, right, or both.
MOORING
The Cherokee should be moved on the ground with the aid of the nose wheel tow bar provided with each plane and secured in the baggage compartment. Tie down ropes may be secured to rings provided under wing and to the tail skid. The aileron and stabilator controls should be secured by looping the seat belt through the control wheel and pulling it snug. The rudder is held in position by its connections to the nose wheel steering and normally does not have to be secured. The flaps are locked when in the full up position and should be left retracted.
WEIGHT AND BALANCE
It is the responsibility of the owner and pilot to determine that the airplane remains within the allowable weight vs. center of gravity envelope while in flight. For weight and balance data see the Airplane Flight Manual and Weight and Balance form supplied with each airplane.
OPERATING INSTRUCTIONS
REVISED: NOVEMBER 6, 1973
*Optional equipment
7-8
OPERATING INSTRUCTIONS
REVISED: MARCH 26, 1979
CHEROKEE ARCHER
Air Condition e r Controls
Th e locator should be check e d during the ground check to make certain th e unit ha s not been a c cidentally activated . Check b y tuning a radio receiver to 121.5 MHz. If th e re is an oscillating sound , the locator may have been activated and should be turned off immediately.
Reset to the "ARM" position and check again to insure against outside interferen c e.
NOTE
If for any reason a test transmission is necessary , the test transmi ss ion should be conducted only in the first five minutes of an y hour and limited to three audio sweeps. If tests must be made at an y other time , the tests should be coordinated with the nearest FAA tower or flight service station .
AIR CONDIDONING*
To operate the air conditioning system either on the ground or in flight :
I . Start the e ngine (ground operation) .
2. Turn the air conditioning Master Switch to "ON .
"
3 . Turn "TEMP" control to desired temperature. Oockwise rotation increas e s cooling.
4 . Select desired "FAN" position, "LOW , " "MED" or ''HIGH .
"
*Optional equipment
OPERATING INSTRUCTIONS
REVISED: MARCH 26, 1979
7-9
7-10
OPERATING INSTRUCTIONS
REVISED: NOVEMBER 6, 1973
OPERATING TIPS
CHEROKEE ARCHER
8-2
OPERATING TIPS
REVISED: JANUARY 20, 1975
PERFORMANCE CHARTS
Altitude Conversion Chart
Takeoff Performance
Climb Performance . . . . .
Cmise Performance - Range
Engine Performance . . . .
Cruise Performance - True Airspeed
Stalling Speed vs Weight . . . . .
Stalling Speed vs Angle of Bank
Glide Performance . . . . . . . .
Landing Distance vs Density Altitude
WARNING
Performance information derived by extrapolation beyond the limits shown on the charts should not be used for flight planning purposes.
9-1
9-2
9-3
9-4
9-5
9-6
9-7
9-8
9-9
9-10
9-i
5000
......
.....
....:.
Cl
=
!:::; c
......
c:;;
.....
Cl
4000
3800
2000
-18
CHEROKEE ARCHER
TAKEOFF GROSS WEIGHT 2450 LBS.
FLAP POSITION 0°
POWER FULL THROTTLE
PER LYCOMING
12000
~·········-+··--'i:lfl. ··~----+· -···+·········+····----··+······--+···-····+ ..............
··+· ········-····--+--··-·+·--·--+---··· .. .-.•
..... w...
...:,
=
_. c
10000
8000 f: c;)
.....
=
6000
0 200 400
RATE Of CUMB-FPM
600 800
NOTE: SEE SECTION 1 FOR EFFECTS OF AIR CONDITIONING
INSTALLATION ON PERFORMANCE.
PERFORMANCE CHARTS
REVISED: JUNE 17, 1974 9-3
PA-28-180
761 556
PERCENT APPROX.
~~~~
GPH
..,.__7_5 -+-8.8----t
OOlF©OO[rJ.lti\~~~ ~ OOti\~@~
GROSS WEIGHT, 2450 LBS. -
·-------+-,...,.__
WHEEL
FAIRINGS
INSTALLED
+---+------+--+--+-------i---+---4
48
GAL,
USABLE FUEL
70 8.1
BEST ECONOMY
60 7.t
MIXTURE LEAN PER LYCOMING INSTRUCTIONS
i.==:::i:===t===~-L------4--1-----1-.-
ZERO WIND
~--+------+-----+--+---+----+-+---1
8000
NO RESERVE +---+-----+--+------+--·-+·----+~-·+----+---4--+----+---+-------+--1----+-----1
- - -- 45 MIN. RESER
AT 55 % POWER--1---+----+--+--+-----1--+-----+--+----+--+--+-----t--+----+----1 l
1s%
I
8
6000 l---+----+---+---1---++----!---4------1-------1-~---+--··~
........
-~--!--+.--.......j.-~--Jil-----+---+-----4
'S
......
= i5!
~ c
4000
I
>-
:z
~ 2000 t----+---+-+---+-----+---++----+---+---1---+--
I
I
I
RANGE - STATUTE
MILES
p -
-1
12000
GROSS WEIGHT
1
BEST POWER
MIXTURE
*
LEAN PER LYCOMING INSTRUCTIONS
!
I
I
'"--~~~--l--~~-1--~~
I
I
.
I
I
CHEROKEE ARCHER
.....
..:..,,
8000
=
6000 !::; c v; z
LI.I
=
=
4000
2100 2200 2300 2400 2500
ENGINE RPM
NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING
INSTALLATION ON PERFORMANCE.
2600
PERFORMANCE CHARTS
REVISED: JUNE 17, 1974
2700
9-5
CHEROKEE ARCHER
1 t -
.......
"'-
.......
= t -
>-
1c::;:; z:
~ sooo~~~--~~~-+ ol~ ~~~~·~~~~··~~~~~~.-~~~~-~~~~~-~~~~
100 110 120 130 140 150
TRUE AIRSPEED-MPH
NOTE: SEE SECTION 7 FOR EFFECTS OF AIR CONDITIONING
INSTALLATION ON PERFORMANCE.
PERFORMANCE CHARTS
REVISED: NOVEMBER 21, 1975
PA-2 0
..... w..t
"""'
I=
.....
c
......
Vi
.....
Q
4000
3000
2000
HANDLING AND SERVICING
10-9
10-9
10-9
10-9
I 0-10
10-10
1 l l
CHEROKEE ARCHER
HANDLING AND SERVICING
This section contains information on preventive maintenance. Refer to the PA-28 Service
Manual for further maintenance procedures. Any complex repair or modification should be accomplished by a Piper Certified Service Center.
GROUND HANDLING
TOWING
The airplane may be moved by using the nose wheel steering bar provided, or power equipment that will not steering bar is stowed in the or cause excess strain to the nose gear assembly. The compartment.
CAUTION
When unving with power equipment, do not turn nose gear more than JO degrees in either direction, as this will result in damage to the nose gear and steering mechanism.
TAXIING
Before attempting to taxi the airplane, ground personnel should be instructed and approved by a qualified person authorized by the owner. Engine starting and shut-down procedures as \\
1 ell as ta xi techniques should be covered. When it is ascertained that the propeller back blast and taxi areas are clear, power should be applied to start the taxi roll, and the following checks should be performed, after releasing the parking brake. a. Taxi forward a few feet and apply brakes to determine their effectiveness. b. While taxiing, make slight turns to ascertain the effectiveness of the c. Observe wing clearances when taxiing near buildings or other stationary objects.
If possible, station a guide outside the airplane to observe. d. When on uneven ground, look for holes and ruts. e. Do not operate the engine at high RPM when running up or taxiing over ground containing loose stones. gravel or any loose material that may cause damage to the propeller blades.
HANDLING AND SERVICING
REVISED: MARCH 16, 1984
10-1
orc•tec;no~n and .,,...,.....,, .... .., u~t:AiUll'-'
.:u • ..., .... ,,'"" be used for proper seat belt through the at approximately material, leave contract.
Do not a
HANDLING AND SERVICING
ISSUED; JULY 9, 1973
0
'
I. BRAKE RESERVOIR
2. RIGHT BRAKE AND RUDDER PEDAL
3. LEFT BRAKE AND RUDDER PEDAL
4. RIGHT BRAKE CYLINDER
5. LEFT BRAKE CYLINDER
6. BRAKE HANDLE
7. HANDLE RELEASE BUTTON
8. LINE , INLET
9. CLEVIS PIN
10 . MASTER CYLINDER ASSEMBLY
11. BOLT ASSEMBLY
12. TORQUE TUBE
13 . COPILOT'S RIGHT BRAKE AND RUDDER PEDAL
14 . COPILOT'S LEFT BRAKE ANO RUDDER PEDAL
~0
) l
/
with the correct attach a strut pump to air valve oleo strut to correct •LV~lJl"..<•'b·
for gear a kit (available should be used. This kit consists two hydraulic
001um1s of ballast should be on the tail stand on the wing and the at the attach the tail stand. After
"°'""'"''""'i;:;.,
V••UU4""'·
!U'-'•'u•·~ may be continued until the aircraft is at height r1""• 1 n·P•n
""''""'"l
1
·r1 end or out threaded rod end of to the nose wheel are """''""~'"""',.,. the rods and should be is in such a way that the fore and axis of plane when the rudder pedals of nose wheel can be centered to
..,..,.,.,.,,,,,,... arc the nose wheel is 30 by the back that the plane follows a perfectly straight line . in either direction and is factory adjusted at on the bottom of the forging. arm should be adjusted so that the nose wheel reaches its full the rudder hits its stops. This guarantees that the rudder will be allowed to move through its full travel.
PROPELLER SERVICE
The and backing plate should be cleaned and inspected frequently for cracks. propeller should be inspected before each flight for nicks, scratches and corrosion. If found, should be taken care of as soon as possible by a rated mechanic, because nicks and
",.. .. ,,.,T',.. • ., 0
" cause areas of increased stress which can cause serious damage or loss of a propeller tip. The back face of the blades should be painted when necessary with flat black paint to retard glare to the pilot's eyes. To prevent corrosion the surface should be cleaned and waxed periodically.
OIL REQUIREMENTS
The oil of the Lycoming 0-360-A4A and 0-360-A4M series is 8 quarts and the minimum
.~n'""'""',, every 50 hours quantity is 2 or
It is recommended that the oil filter element be sooner under unfavorable conditions. Engine oil is normally changed with the filter. if the full How (cartridge type) oil filter is used and changed every SO hours of operation) the intervals between oil changes may be increased as much as 100 percent.
The following grades are recommended for the specified temperatures:
Temperatures above 60°F
Temperatures between 30° F and 90° F
Temperatures between 0° F and 70° F
Temperatures below 10° F
S.A.E. 50
S.A.E. 40
S.A.E. 30
S.A.E. 20
10-8
HANDLING AND SERVICING
REVISED: JANUARY~20,
1975
CHEROKEE ARCHER
Fl EL SYSTEM
I. u
F I R H) l llH M I· N I
s ( /\ v {
I/\ s
0 N I Yl
Aviation use of lower
100. l JO ()ctanc (minimum) fuel must be used in the Cherokee The can cause serious considered of such importance that the damage in a very short warranty is invalidated by of time, and is such use.
FILI IN(! H Fl. I ANKS
Observe all rct.Flircd precautions for hand! gaL usahk) tanks.
ro
obtain the standard totaL fill th1: tanks obtain the standard to the bottom ol the filler neck
Fuel is stored in two of lJ.S. or visual indicator. lo reserve quant fill the tanks to the top of the filler neck.
DR/\INING FllFI VALVES AND l INFS lhc fuel should he drained daily prior to first flight and rcfuding to avoid the an~umulation of \vater or sediment. Each fuel tank is cquipped with an individual quick drain llH:atcd at tht: lower inboard rear corner of the tank. The fuel strainer is equipped v1ith an easy dram valve It is located on the front lower left corner of the fire wal It is important that the fuel be drained in the following manner: a. Open the easy drain \a!vc with the fuel selector valve on one tank, and allow fuel to llow ftHa fnv seconds. h. Place a container under I.he drain and examine the contents for sediment. water and propL'r fuel. c. When enough fuel has flowed to ensure that the
\Vat er and sediment. close the drain and and strainers are free of of the contents of the ncr. tL the procedure vvith the fuel selector valve changed to the other tank.
CAliTION
After and is not
When draining any amount nf fuel, care should he taken to en'>ure that no fire h<uard exists before in, it ;-.,hould be checked to make sure it has closed
HANDLING AND SERVICING
REVISED: MARCii 16. 1984 I0-9
CHEROKEE ARCHER
Fuel Drain
DRAINING FUEL SYSTEM
The bulk of the fuel may be drained from the system by opening ~he valve at the inboard end of each fuel tank. Push up on the arms of the drain valve and tum counterclockwise to hold the drain open. The r e maining fuel in the system may be drained through the filter bowl. Any individual tank may be drained by closing the selector valve and then draining the desired tank.
TIRE INFLATION
For maximum se rvic e from the tires , k ee p all three tires inflated to a pressure of 24 pound s . If necessary , interchang e the tires on th e main wheels to produce even w e ar. All wheels and tires arc balanc e d befor e original installation, and the relationship of the tir e, tube and wheel should be maint a ined if possible. Out of balance wheels can cause extreme vibration on takeoff. In the in s tall a tion of new c omponent s, it may be necessary to rebalance the wheel w i th the tire mounted .
10-10
HANDLING AND SERVICING
ISSUED: JULY 9, 1973
ARCHER at the rear side of drain tube which should be """'"'"'"''"
Check the for proper fluid level. check should be
4 amp rate and with 2
"''V''"~'·""'"' with , These on the nature of the not
'"rP•cr''''1 persons such as owners, dealers and
arc installed. and Alteration Form
AND SERVICING
REVISED: MARCH 16, 1984
CHEROKEE ARCHER
REQUIRED SERVICE AND INSPECTION PERIODS
The Owner Service Agreement which the owner upon ddivcry of the aircraft should at all times. This identifies him to authorized Piper dealers and entitles the mvner to in accordance with the regular service agreement terms. This agreement also entitles the transient owner full warranty by any Piper dealer in the world.
One hundred
Otherwise this hour inspections are required by law if the aircraft is used commercially. is left to the discretion of the owner. This inspection is a complete check of the and its and should be accomplished by a Piper Authorized Service aircraft and power plant mechanic who owns or works for a reputable is listed, in detail, in the inspection report of the appropriate Service
Manual.
An annual inspection is once a year to keep the Airworthiness Certificate in the same as a IOO-hour inspection except that is must be by an Inspection
..,,.,,..,-,"'" (IA) mechanic or a General Aviation District Office (GADO) representative. This is required whether the aircraft is operated commercially or for µ'"""''"'"'
A Progressive Maintenance program is approved by the FAA and is available to the owner.
It involves routine and detailed inspections at 50-hour intervals. The purpose of the program is to allow maximum of the aircraft, to reduce maintenance inspection cost and to maintain a maximum standard of continuous airworthiness. Complete details are available from
Piper dealers.
A spectographic analysis the oil is available from several sources. This if used provides a check of the internal condition the For this system to be accurate, oil samples must be sent in at regular intervals, and induction air must be cleaned or changed
HANDLING AND SERVICING
REVISED: MARCH 16, 1984
10-13
BANDUNG AND SBRVIONG
IDU!D: JULY 9, 1973
0
I
.
.
~ -.
I
.
'
6 mTCH H
0 0 0 0 6 ..t.~::;
•
1 e
-=.: :::..:..::.;_:;_ _
-'-
DAU
--------
~
-
~
------
•'c e
----· -
~~ ~
AS
·~u~1~11~n~-'--' ft
'.'.'.ca::_
CA•
_ _ _ _
c•
_ _
SPllAT
CAI
HISM IYHAU:
_ _ _ _ _ _ _
Fll•
_ _ _
Lubrication Ch ar t
SKETCH 1
_ _ _ _ _ _
0
0
0
0
PRECISE FLIGHT, INC.
AIRPLANE FLICHT MANUAL SUPPLE.i'!ENT
FOR
REC.
SER. attached to the FAA Approved Flight Manual when the the installatio
STC Number
F i Inc. or supersedes the basic manual only and performance information basic Airplane Flight Manual*
STANDBY VACUUM {SVS)
OPERATING INSTRUCTIONS is for emergency use only
PROCEDURES
Page 1 of 2
PRECISE FLIC~ INC:SA.-?
STC
.:zRJl.l•?'Al/r
fl
II • NORMAL PROCEDURES
1. Before starting engine push standby vacuum knob IN/OFF.
2. During run-up idle engine at low sp.:t.>d and woJJCntarily pull st&ndby vacuum knob out (ON) a1:d check vacuum gauge. Normally, the vacuum reading will be slightly higher. system control knob in (OFF).
Alter checking system pu:;h vacut1m
3. Regularly check vacuum gauge for proper vacuum system operation.
4. After landing turn Standby Vacuum System OFF.
'
Approx. Standby Vacuwa Available - Altitude - Power Chart for Aircraft with C.S. Prop. Hax. Cont. RPM
Approx. Standby ·Vacuum Available - Altitude - Power Chart for Aircraft with Fixed Pitch Prop
Prc:as.
Alt.
2000·
4000
6000 llfllVl
10000
RPH
SYS Vacuum
In.H2. Min.
V. PERFORMANCE
No Change.
AA ate
APPROVED
December 7. 1984
Page 2 of 2
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
MAJOR REPAIR AND ALTERATION
(Airframe, Powerplant, Propeller, or Appliance}
Form Approved
Budget Bureau No. 04-RC
FOR FAA USE 01'
OFFICE IDENTtftCATION
INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 43 Appendix B, and AC 43.9-1 (or subsequent revision for instructions and disposition of this form.
MAKE
1. AIRCRAFT
SERIAL
NAME (As shown on registration certificate)
2. OWNER
3. FOR FAA USE ONl Y
UNIT
AIRFRAME
POWERPLANT
MAKE
4. UNIT IDENTIFICATION
MODEL SERIAL NO.
5.
REPAIR
PROPELLER
TYPE
APPLIANCE
MANUFACTURER
DATE
...
~
A. AGENCY'S NAME AND ADDRESS
6. CONFORMITY STATEMENT
8. KIND OF AGENCY
ERTIFICATED MECHANIC
CERTIFICATED REPAIR STATION
C. CERTtFICATI that the repair and/ or alteration made to the unit ( s) identified in item 4 above and described on the re' hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Reg the information furnished herein is true and correct to the best of my knowledge.
SIGNATURE Of AUTHORIZED INDIVIDUAL
MANUFACTURER
REPAIR STATION
CERTIFICATE OR
DESIGNATION NO.
.llletttified in item 4 was in¥fil)ted in the manner prescr:
APPROVED OREJEC
OTHER (Specify)
INSPECTION AUTHORIZATION
CANADJAN DEPARTMENT
OF TRANSPORT INSPECTOR
OF AIRCRAFT
StGNATURE OF AUTHORIZED INDIVIDUAL
Weight ax1d
NOTICE
balance or operating limitation changes shall be entered in the appropriate aircraft record.
An alteration must be compatible with all previous alterations to assure continued conformity with the applicabt~ airworthiness requirements.
DESCRlrilON OF WORK ACCOMPLISHED (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.)
0
ADDlTIONAl SHEETS ARE ATTACHED
U.S. GOVERHMEHT P!!IHTING Ol'l'!CE 19Cl7 OF-tn-oes
DEPARTMENT OF TRANSPORTATION
FEDERAL AV!ATION ADMINISTRATION thereof)
3. FOR
UNIT
A~RFRAME
MAKE
POWERPLANT
PROPELLER
TYPE
MANUFACTURER
AGENCY'S NAME AND ADDRESS
6. CONFORMITY STATEMENT
8. KIND OF AGENCY
SERIAL NO.
5. TYPE
REPAIR
ALTER·
ATION
C. CERTIFICATE NO.
PUU. OPERATED
CABLE VALVE
FAA APPROVED AIRPLANE
FLIGHT MANUAL
SUPPLEMENT
OR
SUPPLEllENTAL FLIGHT
MANUAL
AIRCRAFT llODE1..:
SERU\L NUMBER:
FOR
-------
~~
REG&STRATION HUMBER:
111ma be dadiie:d to the FAA ~.Airplatie
Mli1*1i1111. Whal dilc Pre:ci5;c fligllf S1ald>y Vaiallllllll Im . . in wd.b STC(s).
SA116DW. SA2UJNM • Ain:raft
&.
SEl'119NML)'CUDmg~
«
•SEi13UNMC~
The ....
!!be ..X ~ mr. dlime
-
IR3S
noa
~ supcnedls lisltd. For cao1aa:d m
Proa:mn:s,.
dais~ k~A.Ep~
FAA
APPROVED:.~:::::::::~::::::;.:-----::::::=-~~
Man
Special
Ceftilication
Branch
Seattle Aircraft Certification
Office
DATE Of APPROVAL:
/J.
?-
2.~
1 of&
6 ofl
B.. EMERGENCY PROOBMIRHSbruary
4, 2000
1. PRIMARY VACUUM FAILURE WARNING
LIGHT ILLUMINATES
a. Pull tk S'lalldby v ..... Symm bob our -OHaad lld'jllllst sdbll!g as rieqWmJ to DPmM ~
~Kmllm foir de primacy~ SDd:ian Oaugc dacGK:al/uc lf~cdcs:md a
Iowa albmde to obtUn
11 IBger ddiimaill bd:ween
~Md~~VKUU!Dpown:rmm.t
Dlllllnilared dw::tiag tk wamm page h_ The
svs
is; lll!GC
~ ft. should be lakm lon:b'B lo VFR
ID 1-d.. If dliis is lllOI
~» shOllM 11.ic ~
&oremm
to VFk auililliicos or t.d dee Uplmc:.
WARNING: FAILURE OF THE VACUUM SYSTEll STl.L
CONSlllUTESAN BERGENCY SITUATION
REGAROLESS OF THE INSTAUATION OF TIE SVS. IT
MAY NOT BE POSSIBLE TO ~AINA
ALTITUDE AND llAKE USE OF THE SYS. IN SUCH A
SITUA llON THE AIRPLANE MUST BE FLOWN USING
NON-VACUUM POWERED INSTRUllENTS.
7of8
PtlU.. OPERATED
CABLE VALVE
ll OPERATING PROCEDURES
A. NORMAL PROCEDURES
1~
GROUND CHECK
.. YKtilllitm
c.-m
Knob OUT - ON -
, Kd Rl!l!m COl'd!ol .KDnb IN - OFF positioo..
2.. BEFORE TAKEOFF
&. llDt ~.a pill dae stmdby
W10MD mob OUT ON ad c.lledt va:mu ~
Normall,,. bv~ l'lighu.
After died:irig S)~ V11CU11J1D ~
• OFF-. Cbc::d: dal Y11i'D:Wm g;wge b5 rdm'l.l.elii ~
prams
readilllg.
3. ENROUTE
a ~!8:dy dMCk 1'lltllll8
warn.mg
UIUD!i.cl!Uf
~ $)'~ cpt:f~
PULL OPERATED
CABLE VALVE
Standbf Vacuum
Srstem
A.FM SUPPLEIENT
t
OPERA TING LIMITATIONS {CONT.)
8. PLACARDS
OllC of die ~·illlg plaal:ds plaited. r.u view oflle aevthe mdicallm llift=r ~adries ba'lt been JIDde.
Vaa111m -AUDdePoWG"Clmt r..-~we~Sptcd~-Muimum~
RPM. llAN..
PRESSURE
SVS VA.CUUll
K.HGlllN..
PRESS
ALT.(FT.,) RPM
2000
4000
6000
Miax.,
O::lnl ldax. com.
8000
10,000
I
Max.Cont.
Max .. Calll
Max. Coot
Sllabd!bJ Vaaamlll A~ wiillh
11
Find Piikh Pr~
PRESS
ALT. fFT.)
20!lQ
4000
6000
8l)(lM)
10.000
RPll
Powa-Clmt
SYS VACUUM
IN.HGMIN.
Sof8
PUU. OPERATED
CABLE VALVE
l OPERA TING UlllTA
8..
PLACARDS
Plilarrd lO tie loclded m tk peWpuJi COl:lkoi cable
Pfraiald to bl! r~ 6c UID for fhc: pump ioclp •miiing tight.
STANDBY VACUUM SYSTEM EQUIPPED: FOR
OPERATING INSTRUCTIONS ANO LIMITATIONS SEE
SUPPLEMENT IN OWtERS MANUAL OR PILOTS
OPERATING HANDBOOK
4ofl
PUU. OPERATED
CABLE VALVE
I. OPERA TING UMITA TIONS
A. INSTRUCTIONS
I. 'The ~ is fot ~or~ lmldlri'lltfur ~
2.. VlialUm fXNia:cd llllldfu VKllllUm gJm dim::u:d llldopiiot b ~
'ftiu:B YllllCUUl!D SJ*m is of
YIWiRllllll.
Vlill:mlm p.owua:i ac VKUmlll g)IO dill~ IWllOpikll should be Off wiaea opcra£ilig Wida I failed
S)'&aaa. l. llic $}stem i1s; lll<lt dcAped ID c:ipcn1e l1Ml!C:mllliilll:K: del-ic= Syskm.$. 00 NOT ~. do-ice wilall •81..Wled primlE)'
naun
~
'4. Al!low: I0,000 11ltirude, cagjac p.!Mller seaitp Dly bi: l1cdm:ed m provide 'Ni:quatc
Wlil:Dum.
'.i·. lf!GWCI km flH1>pU g)fll ~
n.c
m:: rcqwircd
ao
tie
a
w ricw of
Plot:
3ofl
SYSTEM DESCRIPTION
A P!C:cite
AidK
~ ~may lo prorid'e a lhcewaa of a pria:aary namm failure. The
S!m1by Vs;umn S)'Sll:m opmtcs m die~ lhe imate
_ _ . .
~ad dnooP ashdk Yoih"C
SJ*a
eu
miYI: JOOS ffiPt ~
CA.UTIOlt The use of the Slard>y VlillCUUll\ System reqviles a degree of Pilat st11
aoo
p1Cliciiency M. is best maintaille:i
Vwwgn
pnd::e. ltbir~ ~lFR il11 VFR condlililall'S.. in the preseu:e of a CA. 11e1 lie aicraft be i1bwn at the
RPM and or Manicfd Presswe ~ Ille required plat:ald
· ood et*red il Bis A.FMS. This procedure will famiarize tile piklt wlltl engine man8::*i vatUUm b ~ lievef ligtt .
2ofl
GAR\11N Ltd. or its subsidiaries c'o Garmin International l 200 E. l 5 l ' 1 Street, Olathe. KS 66062 LSA
AIRPLANE FLIGHT "vlA\iLAL SLPPLE"vlE\iT or SUPPLE"vlENTAL. AIRPLA'."\E FLIGHT :\!ANLJAL for a Garmin 400\V Series 1\avigation System
SECTION PAGE
Section I.
1.1 Garmin 400\V Series GPS.'\\ !\i\ S Nav Com
1.2 Operation
I .3 Class 11 Oceanic. Remote. and other Operations:
Section 2. l.l"vllTATIONS
2. I Pilot's Guide
2.2 System Software:
2.3
2.4
Navigation Database
Terrain Database
2.5 Navigation
2.6 Approaches
2.7 Autopilot Coupling
2.8 Terrain Dispi<t)
2.9 VNAV
4
9
2. I 0 \Veather Display
2. I l Trame Display
9
10
Section 3. EMERGENCY PROCEDLRES
3. l
3.2 Abnormal Procedures
11
11
11
Section 4. NOR!\IAL PROCEDLRES
4.1
4.2
Approaches vvith Vertical Guidance
\~ithout Vertical Guidance
1 J
13
14
For additional information on LP approaches refer to the 400\V Series unit
Pilot's Guide.
4.3 Autopilot Operation
4.4 Coupling the Autopilot during approaches
4.5 W F DE Prediction Program
Section 5. PERFORMAl\iCE
Section 6. \Iv EIGHT AND BALANCE
Section 7. SYSTE"v1 DESCRlPTIONS
14
14
I4
16
16
16
I6
7
7
8
8
9
9
4
5
5
6
6
6
190-00356-03 Rev. B
Page 3 of 16
•
GARVllN Ltd. or its subsidiaries c10
Garmin International
1200 E. 151 ' 1 Street Olathe. KS 66062 USA
AIRPLANE FLIGHT lv1ANUAL SUPPLEi'vlENT or SUPPU:::rv1ENTAL AIRPLA~E FLIGI-IT fVL!\NUAL for a Garmin 400W Series Navigation System
Section I. GENERAL
1.1 Garmin 400W Series GPS/WAAS Nav Com
The Garmin 400\V Series GPS/WAAS Navigator is a panel-mounted product that contains a GPS/WAAS receiver for GPS approved primary navigation. under TSO C 146a (plus optional VHF Com and V~ radios) in an integrated unit with a moving map and color display. The 400\V
Series unit features a graphical display which may also be used to depict traffic. weather. or terrain data.
The navigation functions are operated by dedicated keys and graphical menus which are controlled by the buttons and the dual concentric rotary knob along the bottom and right side of the display .
Optional VI IF Com and VHF Nav radio functions are controlled via dedicated buttons and knobs on the Jett side of the display and adjacent to frequencies they are controlling.
Clew r: req (ri .
/HZJ
Figure t 400\V Series Control and Display Layout
190-00356-03 Rev. B
Page 4of16 to activate)
Key
its subsidiaries
1200 S;\
\lRl'LA"iE r LIGHT \1A:\l AL SlPPLE\lE\:T or SlPPLE\lE\:Ti\L IRPLA\;E FLIGHT \!;\\:UAL for a Clarmin 400\V Series Navigation System
1.2 Operation
GPSWAAS TSO-CJ46a Class 3 Operation: The Garmin 400\V Series unit when installed in accordance with STC S:\019.BLA-D. uses GPS and WAAS (within the coverage of System compl}ing \vith !CAO Annex 10) prec~ision approach (
··L\:A V'". and ··LP'" guidance (including "L\:A, V with vertical
\:avigation is accomplished using the W(!S-84 (\:;\D-83) coordinate reference datum. GPS
Positioning S) stem ( GPS) data based upon use of only the Global by the Lnited States of America. l.3 Class II (keanic, Remote, and other Operations:
The Garmin 400\V Series. as installed. has been found to comply with the requirements for GPS remote airspace. when used in means l l navigation in oceanic and with WAAS Garmin Prediction
Program part number 006-i\O 154-03. Oceanic operations are supported vvhen the 400\V Series unit annunciates OC\:. This provides an alarm limit of four N\11 and a mask angle of five degrees. The 400\V series unit also has the ability to predict RAl\1 availability at any waypoint in the database or if
\\'A;\S corrections arc expected tn be absent or disabled. This AF\1S docs not constitute an for Oceanic Remote area operations. Additional equipment installations or operational approvals ma) be required. a) Oceanic additional range oceanic amt' or remote area stem independent display. sensors, antenna. and pmver source. (It may be a second 400W.
1
500\V Series unit.) b) Redundant VHF Com and VI F Nav systems may be than l .S. 14 CTR Part 91 Check for other regulation
(It may be a second 400W'500W Series unit.) for the use of the 400W Series unit
Prediction Program for operators civil aviation
I 90-00356-03 Rev. B
Page 5of16
GA RI\ 111\ Ltd. or its subsidiaries c 1
0
Garmin International
1200 E. 151'' Street. Olathe. KS 66062 LS
1
\
AIRPLANE FLIGHT l\1A>iUAL SLPPLEMENT or SlPPLEl\IE:\TAL AIRPLA'\E FLICill"l l\!Al\UAL for a Garmin 400\\ Series '.\avigation System
Section 2. LIMITATIO~S
2. l Pilot's G 11ide
The GARl\111\ 400\\ Series ()uide. part number and revision listed below (or later applicable revisions). must be immediately available for the crew whenever is predicated on the use of the 400Vv Series unit.
• 400\V Series Pilot's (iuide & Reference Pi?\ 190-00356-00 Rev E
• 400\V 500\V Series Optional Displays P 1 l\ 190-00356-30 Rev F
• 400\V 500\V Series Display Interfaces P 1 l\ 190-00356-31 Rev B
This AFl\l supplement does not grant limited to VFR for IFR operations to aircraft
Additional aircraft systems may be required for
IFR operational approval. S) stems limited to VFR shall be placarded in close proximity to the 400\V Series unit
"GPS LIMITED TO VFR lSE ONLY'.
2.2 System Software:
The s;stem must utilize the \lain and GPS soil ware versions listed below (or later FA:\ approved versions). The soflware versions are displayed on the self-test atkr turn-on for approximately 5 seconds or they
X page~.
Subsequent software versions may support different functions. Check the
400\\' Series Pilot's Guide for further information.
T II l \ is f tware
Solhvare Item
· ers1011s
Approved Software Version for later F LI approred rersions for this SI( ·1
SW version As displaved on unit
!\lain SW Version
GPS S\V Version
3.30
~ ')
. ) . _
3.30
., I
. ) . _
190-00356-03 Rev. B
Page 6 of 16
CiAR\llN Ltd. or its subsidiaries c.o Garmin International
1200 E. 151" Street. Olathe. KS 66062 LSA
AIRPLANE FLICi! IT \JA:\l AL SL i>PLE\lENT or SlPPLF\11::'\TAL AIRPL/\'\iE FLIGHT fvl/\Nl/\L for a Garmin 400\V Series "iavigation System
2.3 Navigation Database
The 400\V Series unit database card must be installed. (I/\ W the TSO deviations to Garmin for the 400\\ unit. navigation database cards may nut be marked with the part number. The software automatically precludes invalid databases for use the 400\\') a) IFR enroute and terminal is prohibited unless the pilot verities the currency of the database or verifies each selected way point !l.ir accuracy b; reference to current approved data. b) GPS instrument approaches the 400\V Series units are prohibited. unless the 400\V Series unit's approach data is verified by the pilot or crevv to be current. Instrument approaches must be accomplished in ac..:ordance with an approved instrument approach procedure that is loaded from the 400\\ Series unit database. c) Installations with dual 400\\ 500\\ Series units will only crossfill between units when contain the same database cycle. Lpdating of each database must be on the ground to 11ight.
2.4 Terrain Database
The 400W Series unit supports Terrain and requires a Terrain database card to be installed in order for the feature to operate. The table below lists compatible database cards fix the 400\V series. Each of the data base cards contains the data: a) The Terrain Database has an area
or
coverage from North 75 · Latitude to South 60') Latitude in all b) rhe Airpo1i Terrain Database has an area of coverage that includes the l nited States. Canada. l\lexico, Latin /\merica. and South America. c) The Obstacle Database has an area of coverage that includes the United
States. and is updated as frequently as every 56 days.
:\CHE: The area of coverage may be modified as additional terrain data sources become avai !able.
190-00356-03 Rev. B
Page 7 of
!(1
GAR\ll'.\ Ud. or its subsidiaries c"o Garmin International
1200 I~. 51 '
1 Street. Olathe. KS 66062 l SA
.\IRPLA'.\E FL!Cilll \L\'.\l'1\L SLPPLE\1E\.T or SLPPLE\1El\TAL AlRPLA'.\E FLIGllT \:lA'.\Ut\L for a Garmin 400\V Series '.\avigation System
2.5 '.\avigation
\io navigation is authorized north of 8 1)·
89° (degrees) south latitude. north latitude or south
or
2.(1 a)
Approaches
GPS the must the 400\V Series unit is mode. (L'.\.\ V. L'.\AV V. L/V'.\A V. LP. or
LPV) bl When conducting referenced to true '.\nrth. the heading selection on the A LX pages must be adjusted to TR t E. c) Accomplishment of an ILS. LOC. LOC-BC. LDA. SDF. MLS. YOR approach. or any other type of approach not approved for GPS overlay. is not authori1ed with GPS navigation guidance. d) tsc of the G\iS 430\V VOR"LOC:GS receiver to fly approaches not approved for Ci PS requires VOR"LOC GS navigation data to be present on the external indicator (i.e. proper CD! source selection). e) For aircraft with remote source st~lection annunciation or remote GPS navigation annunciations installed. !FR approaches is prohibited if the remote annunciation is found to be inoperative during pre-flight. (This limitation does not prohibit the conduct of an IFR approach if the required remote annunciation fails during flight. The f) indications provided on the 400'v\' Series unit display may be used as a backup).
Except in cmergenc; conditions. IFR approaches arc prohibited whenever any physical or visual obstruction (such as a throw-over yoke) restricts view or access to the 400\V Series unit or the affected CDI.
190-00356-03 Rev B
Page 8 of 16
GA R\ll:\ Ltd. or its subsidiaries co Garmin International
1200 E. l 51 '
1
Street. Olathe. KS 66062 l.'.SA
1
\IRPLX\E !LI Ci I IT \1\1\l AL SLPPLE'vlE:\T or SLPPLE\IE:\TAL AWPL:\1\E FLIGHT "vl/\:\LAL for a Garmin 400\\ Series System
2. 7 Autopilot Coupling
I FR installations of a Garmin 400\V Series unit allow the operator to fly all phases of flight based on the hovvever. not all modes may be information presented to the pilot: to the autopilot. All autopilots ma) be coupled in Oceanic ( OC1\ ), Enroute ( 1::1\R ), and Terminal (TER\l) modes: hovvever. the FAA requires that vertical coupling of an autopilot for be demonstrated to meet their intended function and provide safe and proper operation to published minimums. This installation is limited to:
:\o limitations frJr autopilot coupling.
D Lateral CPS coupling (L:..:A \ ). For 430\\ units: The GS of an
ILS (VLOC) may be coupled lo the autopilot without any limitations.
This limitation may be removed afl:er an Fr'u\ Flight Test demonstration.
Contact Garmin International. Tech Support for additional information.
2.8 Terrain Display
Terrain refers to the clispla: of terrain information. Pilots are NOT authorized to deviate from their current ATC clearance to comply with terrain/obstacle alerts. Terrain unit alerts are advisory only and are not equivalent to warnings provided b;. TA WS. 1\avigation must not be predicated upon the use of the terrain display.
The terrain is intended to as a situational awareness tool only.
By it may not either the accurac; or the fidelity on which to base decisions and plan maneuvers to avoid terrain or obstacles.
2.9 \':\AV
V'.\A V information may be utilized for information only. Lse of
V1\A V information for Instrument l)roeedures does not guarantee
Step-Down Fix altitude protection. or arrival at approach minimums in a normal position to land.
2.10 \Veather Display
190-00356-03 Rev. B
Page 9of16
CiAR\!l'\ Ltd. or its subsidiaries e'o Uarmin International
1200 E. l 51' Street. Ol<1the. KS 66062 LSA
AIRPLA'\E FLICJHT \IA'\lAL SlPPLE\IENT or SLPPLE\IL:'\TAL AIRPLA'\E FLIGHT \!:\'\LAL for a (]armin --IOOW Series Navigation System
If an weather information not be used in lieu or an official interfaced to the 400\V Series unit. the limited to supplemental use only and may data source.
2.11 Traffic Dispfa)
Traffic ma; be ed
011 the 400\\ Series unit when connected to an approved optional TCAS. TAS. or TIS traffic device. These systems are capable of providing traffic monitoring and alerting to the pilot. Tranic shown on the display may or may not have traffic alerting available. The display of traffic is an aid to visual acquisition and may not be utilized for aircratl maneuvering. Display of this traffic data and related operations arc described in the 400\V Series unit Pilot's Guide.
190-00356-03 Rev. B
Page l 0 l(J
();\R\ll'.\ LtJ. or its subsidiaries co (iarmin International
1200 E. l 'i I"' Street. Olathe. KS 66062 l SA
IRPL\'.\E FLICHT MA:\L AL SlPPLl:.\lLl\T or SLPPLE\11:::\TAL AIRPL\:\E l LIGHT \lA'.\L;\L for a Garmin 400\V Series :\avigation System
Section 3. E!\1ERGENCY PROCEDl RES
3.1 Emergcnc.Y Prot·edu res
:\o change.
3.2 Abuormal Procedures a) l f the Garmin 400 \\ Series unit G PS information is not available. or is invalid. utilize other remaining operational navigation installed in the as appropriate. I fthe 400W Series unit loses GPS and reverts to Dead Reckoning mode (indicated by the annunciation of··DR" in the lower left of the display). the moving map \\ill continue to he Airerafi position will be based upon the last valid GPS in and estimated Dead Reckoning methods. or\\ inds a loll can affect the estimated position substantial I). Dead is available in Enroute mode: rerminal and Approach modes do not support DR. b) l fa "'Loss oflntegrity" ( l\JTEG) message is displayed during:
Enroute!Tenninal: continue to navigate using GPS equipment and periodically cross-check the GPS guidance to other approved means of
GPS :\pproach: GPS appwaches are not authorized under l\TEG
- Execute missed c) During a (iPS LPV or revert to alternate navigation. or GPS L:\A V V'.\;\ V approach. the 400\\ Series unit will the approach if the Vertical alarm limits are exceeded. This will cause the vertical guidance to flag as unavailable. The ma) be continued using the L\A V onl) minimums. d) During a GPS LP approach. the -WO\\ Series may downgrade the approach prior to the Final Approach Fix if alarm limits are exceeded. If this occurs. a message will be advising the pilot to use L:\;\ V minimums. If alarm limits are exceeded atler the Final :\pproach Fix. the
400\V Series "ill the lateral guidance and generate a system message ··.\BOR'f ;\!'PRO:\( 'I I loss of navigation". Immediately upon the message the unit \viii reven to Terminal alarm limits. I fthe is vvithin these limits lateral \viii be restored
190-003'i6-03 l\1ge 11
or
16
Rev. B
GAR\111\ Ltd. or its subsidiaries cu Garmin International
1200 E. 15 I ·
1
Street Olathe. KS 66062 LS:\
1\IRPL:\'\L FLIGHT \1!\:\l /\L Sl PPLE:VIE:\T or SLPPLE\IE'.\T!\L 1\IRPLA:\E FIJGI IT i'vlA'\t !\L for a Garmin 400\\ Series 1\avigation System e) and the GPS may be used to execute the missed approach. otherwise alternate means of navigation should be utilin:d. in whieh precision and non-precision alarm limits arc the 400\\ Series unit will flag the lateral guidance and generate system message ··.\BORT APPROACH loss of upon vie\\ the message the unit will revert to Terminal alarm limits. If the position integrity is within these limits lateral will be restored and the GPS may be used to execute the missed utilized. othcnvisc alternate means of navigation should be
190-00356-03 Rev. B
Page I 2 of I 6
Gi\ R\l!:\ Ltd. or its suhsidiaries
1200 co Garmin International
r::.
l 51 '
1 Street Olathe. l\.S 66062 l S,\
AIRPL;\NE FLl(iHT \L\:\LAL SLPPLE\:lENT or SLPPLE'vlE:\TAL AIRPLA:\E ILIGllT tvlANL'Al. for a (]arm in 400W Series :\avigation System
Section 4. '\IORMAL PROCEDl RES
Refor to the 400W Series unit l'ilors Guide defined in paragraph 2.1 on page
6 of this document for normal This includes all GPS
Vl { 'O\l and . and \Julti-Function Display information.
For information on TIS traffic. or data linked weather see the Pilot's Guide addendum for !·or int\1rrnation on active tranie sensor or
Storrnscope operation and displays see the Pilot's Guide addendum for display interfaces.
Although intuitive and user the 400'vV Series unit requires a reasonahle of familiarity to prevent operations without becoming too engrossed at !he expense of basic instrument flying in l\1C and basic seeand-avoid in VV1C. Pilot workload will be for with limited familiarity in using the unit in an IFR environment. particularly without the autopilot (l<umin excellent !raining tools with the Pilors
Guide and PC based simulator. Pilots should take full advantage of these training tools to enhance system familiarization. Lse of an autopilot is strongly when the 400W Series unit in I \!IC conditions
4.1 with\ Htical Guidance
The 400\\' Series unit supports three types ofGPS approaches with vertical guidance: LPV '\:\AV (annunciated as L. V:\A V) approaches. and L:\A V with vertical guidance
(annunciated as LNA V · V ). For L:\A V approaches with advisory vertical guidance. the 400\V Series will annunciate L:\A V · V indicating vertical guidance is available. LN•\ V minimums will be controlling in this case.
!VOTE:
If flying an LPV or LI\.A V VNA V approach. be prepared to the L:\A V only approach prior to reaching the final approach fix
( l·Al· ). lfthe GPS integrity is not within vertical approach limits. the system will flag the vertical guidance. This may be annunciated b) a to L:\:\ V message.
For additional information on
400W Series unit Pilot's Guide. with vertical guidance reler to the
190-0035(,-03 Rev. B
Page 3 of 16
Gi\RV!li\ Ltd. or its subsidiaries c 1 o Garmin International
1200 E. 151" Olathe. KS 66062 USl\ i\IRPL;\1\E FLIGHT \!Ai\U\L SLPPLE\1ENT or SLl'PLEMENTAL AIRPLANE FLIGHT \JA'Jl. ;;\L for a Garmin 400\V Series Navigation System
4.2 Approaches" ithout Vertical Guidance
The 400W Series unit supports Localizer Performance approaches
(annuneiated as LP). Published LP minimums will be eontrolling in this ease.
If an LP
/VOTE: approaeh. be prepared to the LN
1
\
V only approach prior to reaching the final approach !ix ( AF). If the
GPS is not within LP limits. the system \viii
For additional infrJrmation on LI' approaches refor to the 400\V Series unit
Pilot's Guide.
4.3 Autopilot Operation
!he Garmin 400\V Series may be in the aircran when to an optional autopilot if installed in the Ll\llTATIONS section of this manual. For lateral
GPS Roll Steering in lieu of the analog deviation information. I fan HSI is used with GPSS the pilot should rotate the course pointer as prompted on the 400 \V Series unit to prevent loss of situational awareness and to prevent the aircratl from inappropriately if the autopilot is switched from digital (GPSS) tu mode. For autopilot operational instructions. refer to the FAA
Supplement for the autopilot.
Flight Vlanual or Flight \fonual
4.4 Coupling the Autopilot during approaches
The Garmin 400\V Series supports analog and digital (GPSS) control interfaces to an optionally installed autopilot. Some autopilots revert to
ROLL mode (wings level) amVor flag a NA V failure if the digital data becomes unavailable or is inhibited. The CDI selection of VLOC should inhibit the digital control interface. \lv'hen switching between GPS and
VLOC the pilot should be a\vare that the autopilot ma) need to be reintu 1\PR or NA V mode aHer changing the CDI source. in an to GPS vertical that the autopilot be to an !LS. Some autopilots may revert to ROLL mode when the navigation outputs of the
400\V Series unit sequence to the final approach fix. In these installations
190-00356-03 Rev. B
Page 14 of 16
CiAR\ Ltd. or its subsidiaries c o (]armin International
1200 E. 151" Street. Olathe. KS 66062 LS;\ f\IRPLA'.\E FLIGHT \IA\Jl.AL SLPPl.E\1E'.\T or Sl PPLE\IE'.'\Ti\L i\IRPL:\\:E FLIGI !T \!A'\LAL for a Garmin 400\V Series '\avigation System the unit \viii be configured to PRO\!PT the pilot to ··Enable the autopilot approach in order to prevent the from entering ROLL mode vvithout the pilot being aware of the transition.
D This installation prompts the
P outputs to and requires the pilot to enable the the autopilot in APR mode.
D This installation supports a seamless transition from digital (GPSS) to analog for the autupilot. To capture the vertical guidance. the pilnt nm) engage the autopilot in APR mode al any time \vhen the GPS
Glide (VD!) becomes valid ( displa;ed without a FL\G ).
D This installation interfaces to the in analog mode only. To capture the vertical the mode at any time when the CJPS (ilide may engage the autopilot in APR
(VD!) becomes valid.
The autopilot does not support airy vertical capture or tracking in this installation.
190-00356-03 Rev. B
Page 15of16
CJA.R\llN Ltd. or subsidiaries co Garmin International
1200 E. I 51" Street Olathe. KS 06062 l: SA
AIRPL\'\iE FLIGHT \1:\M AL SUPPLEMENT
Sl.'PPLE\1ENTAL A.mPL\:\E FLIGllT \IANLA.L for a Garmin 400W Series Navigation System
(GPSSl may autopilots should use A.PR mode for coupling to LNA. V
\Vhich support roll steering commands utilize:\;\ V mode and take
v
of the digital tracking
4.5 WFDE Prediction Program fhe Garmin \VA.AS Fault Detection and Exclusion ( WFDE) Prediction
Program is required for Remote.'Oceanic operations.
The Prediction Program should be used in conjunction with the Garmin
400W '500\V Simulator. After entering the intended route of flight in the
Simulator flight plan the pilot selects the FDE Prediction Program under the
Options menu of the Simulator program. for detailed information refor to the WFDL prediction program instructions
( 190-00M.\-O I). The availability of FDE is only required for Oceanic or
Remote operations.
Section 5. PERFOR:\IANCE
'\o
Section 6. WEIGHT AND BAL.\."ICE
See current and balance data.
Section 7. S\STE:\J DESCRIPTIO\'S
See Garmin 400\.\ Series unit Pilot's Guide for a complete description of the
400\\ Series unit. l lJ0-00.156-03
16 I
B

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