SC-AMM-1-0-00 - Czech Sport Aircraft

SC-AMM-1-0-00 - Czech Sport Aircraft
SC-AMM-1-0-00
SportCruiser / PiperSport
AIRPLANE MAINTENANCE
MANUAL
Revision No.: 11
i
Date of issue: 2018-01-22
SC-AMM-1-0-00
INTENTIONALLY LEFT BLANK
Date of issue: : 2018-01-22
ii
Revision No.: 11
SC-AMM-1-0-00
SportCruiser / PiperSport
AIRPLANE MAINTENANCE
MANUAL
SportCruiser / PiperSport airplane is designed and manufactured by
Czech Sport Aircraft a.s.
Na Záhonech 212, 686 04 Kunovice
Czech Republic
www. czechsportaircraft.com; office@czechsportaircraft.com
Fax: +420 576 519 394, Phone: +420 576 514 034 (Sales Dept.)
Revision No.: 11
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Date of issue: 2018-01-22
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Date of issue: : 2018-01-22
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SportCruiser
PiperSport
RECORD OF REVISIONS
Rev.
No.
Issue date
Date and
signature
2013-09-05
2013-05-09
Konečný
2013-10-11
2013-10-11
Konečný
2014-02-17
2013-02-17
Konečný
2014-09-08
2014-09-08
Konečný
2015-05-24
2015-05-24
Konečný
i to iv,
0-1, 0-5, 0-7, 0-8, 0-9
1-14,
10-3, 10-4, 10-36, 10-46,
12-3, 12-4, 12-5, 12-6, 127, 12-8, 12-9,
12-13, 12-21, 12-46, 17-6
2016-01-18
2016-01-18
Konečný
I to iv
0-1, 0-5, 0-7,
2-3, 2-4, 2-8, 2-9, 2-15
10-1, 10-2, 10-37, 10-38,
10-39, 10-40, 10-41
2016-03-30
2016-04-05
Konečný
8
New cockpit with Dynon
HDX1100 system
– valid for SportCruiser S/N
C0596 and C0600.
I to iv,
RoR: 0-1,
LoEF: 0-5, 0-6, 0-7, 0-8,
2-1, 2-3, 2-17,
6-1, 6-6, 6-7,
9-1, 9-5, 9-6,
11-1, 11-6, 11-7, 11-8, 119, 11-10,
12-1, 12-2, 12-10, 12-11,
12-22, 12-45, 12-46
2017-06-30
2017-06-30
Konečný
9
New landing light Trail Tech
D112-SX as an approved
replacement of the Trail Tech
4213-SX.
Cleaning and maintenance of
the plexiglass cover
i to iv
RoR:0-1
LoEP: 0-1
11-1, 11-6, 11-7, 11-8, 119, 11-10
13-1, 13-3
2017-09-15
2017-09-15
Konečný
1
2
3
4
5
6
7
Revision name
Supplementation of LiFePo4
battery
Check of nose landing gear leg
for cracks
Supplementation of improved
nose landing gear and
modification of relevant
maintenance practices
Supplementation of balance
ballast description and
installation.
The inspection interval of NLG
leg Dwg. No. SG0270N has
been changed from the original
50 flight hours to 25 flight hours
or 50 cycles whatever occurs
first.
Coolant Temperature (CT) as an
alternative to the Cylinder Head
Temperature (CHT) added for
cases that the engine is
equipped with new cylinder
heads design acc.to the SB-912066 and SB-912-066UL Rotax
bulletin
New / updated propeller limits
(inspections, works) for:
Woodcomp Klassic 170/3/R
Sensenich 3B0R5R68C
Sensenich 2A0R5R70EN
Changed pages
i, ii, iii, iv, 0-1, 0-5, 0-7, 0-8,
0-9
i, ii, iii, iv, 0-1, 0-5 to
0-7, 2-8, 2-12, 8-1, 8-21 to
8-30
i, ii, iii, iv, 0-1, 0-5, 0-6, 0-7,
2-8, 2-12, 8-5,
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Date of issue: 2017-09-15
Revision No.: 9
0-1
SportCruiser
SC-AMM-1-0-00
PiperSport
Rev.
No.
RECORD OF REVISIONS
Revision name
10
Fuel Return Line – additional
information added
Nose Landing Gear – Discard of
old types from operation
11
Supplementation of conditions
for operation with old types of
nose landing gear leg and new
inspection interval for the older
nose landing gear checks.
Changed pages
i to iv
RoR: 0-2
LoEP: 0-5, 0-6, 0-7
2-1, 2-5, 2-9, 2-10,
2-14,
4-6,
8-1, 8-5, 8-15, 8-20,
8-22, 8-30,
9-1, 9-8
i to iv
RoR: 0-2,
LoEP: 0-5, 0-6, 0-7,
1-1, 1-11, 2-1, 2-5, 2-7,
2-10, 2-14,
8-1, 8-5, 8-15, 8-21,
8-30
Revision No.: 11
Issue date
Date and
signature
2017-10-18
2017-10-18
Konečný
2018-01-22
2018-01-22
Konečný
Date of issue: 2018-01-22
0-2
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PiperSport
RECORD OF REVISIONS
Rev.
No.
Revision name
Changed pages
Date of issue: 2013-06-30
Issue date
Date and
signature
Revision No.: 0-3
SportCruiser
SC-AMM-1-0-00
PiperSport
Rev.
No.
RECORD OF REVISIONS
Revision name
Changed pages
Revision No.: -
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Date and
signature
Date of issue: 2013-06-30
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SportCruiser
PiperSport
LIST OF EFFECTIVE PAGES
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PiperSport
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PiperSport
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Revision No.: 9
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PiperSport
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PiperSport
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SportCruiser
PiperSport
CHAPTER 1 – GENERAL
Chapter 1
- General ................................................................................... 1-1
Chapter 2
- Limitations / Maintenance checks ........................................ 2-1
Chapter 3
- Fuselage................................................................................. 3-1
Chapter 4
- Wing ....................................................................................... 4-1
Chapter 5
- Tail unit .................................................................................. 5-1
Chapter 6
- Control system ...................................................................... 6-1
Chapter 7
- Equipment .............................................................................. 7-1
Chapter 8
- Landing gear .......................................................................... 8-1
Chapter 9
- Fuel system............................................................................ 9-1
Chapter 10
- Power unit ............................................................................ 10-1
Chapter 11
- Electrical system ................................................................. 11-1
Chapter 12
- Instruments and Avionics ................................................... 12-1
Chapter 13
- Venting / Heating ................................................................. 13-1
Chapter 14
- Airplane handling ................................................................ 14-1
Chapter 15
- Airplane repairs ................................................................... 15-1
Chapter 16
- Wiring diagrams .................................................................. 16-1
Chapter 17
- Appendices .......................................................................... 17-1
Date of issue: 2018-01-22
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PiperSport
CHAPTER 1 – GENERAL
Contents
1.1
Introduction ............................................................................................................ 1-5
1.2
Airplane Classification ........................................................................................... 1-6
1.2.1
Power Unit ................................................................................................ 1-6
1.2.2
Main Technical Data ................................................................................. 1-7
1.3
Airplane Manufacturer and Type Certificate Holder ............................................ 1-11
1.4
Chapter Order ...................................................................................................... 1-11
1.4.1
Page Numbering..................................................................................... 1-11
1.5
Warnings, Cautions and Notes ............................................................................ 1-11
1.6
Equipment List ..................................................................................................... 1-12
1.7
Sources to Purchase Parts .................................................................................. 1-12
1.8
List of Disposable Replacement Parts................................................................. 1-12
1.9
Weight and Balance Information ......................................................................... 1-12
1.10 Tire Inflation Pressure.......................................................................................... 1-12
1.11 Approved Oils and Capacities ............................................................................. 1-12
1.12 Recommended Fastener Torque Values............................................................. 1-12
1.13 Instructions for Reporting Possible Safety of Flight concerns
during Inspection / Maintenance.......................................................................... 1-12
1.14 General Safety Information.................................................................................. 1-13
1.15 Definitions and Abbreviations .............................................................................. 1-14
Date of issue: 2013-06-30
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SportCruiser
PiperSport
CHAPTER 1 – GENERAL
1.1
Introduction
In accordance with requirements of the ASTM LSA regulations, the Czech Sport Aircraft a.s.,
as manufacturer of SportCruiser / PiperSport airplane, provides information on maintaining
airworthiness of the SportCruiser / PiperSport airplane. Information is also contained in the
following manuals issued by airplane manufacturer or by manufacturers of equipment used on
the airplane:
•
Pilot Operating Handbook
•
Airplane Maintenance Manual (Doc. No. SC-AMM-1-0-00)
•
Illustrated Parts Catalog (Doc. No. CR-IPC-1-0-00)
•
PS-28 Cruiser / SportCruiser Wiring Manual (Doc. No. CR-WMA-1-0-01, 1-0-02, 1-0-03,
1-0-04)
•
PiperSport -LTD- Wiring Manual (Doc. No. PS-WM-1-0-01)
•
PS-28 Cruiser / SportCruiser Instructions for Continued Airworthiness (Doc. No. CR- ICA1-0-00)
•
PiperSport Instructions for Continued Airworthiness (Doc. No. PS-ICA-1-0-00)
•
SportCruiser Instructions for Continued Airworthiness (Doc. No. SC-ICA-1-0-00)
•
PS-28 Cruiser / SportCruiser Aircraft Assembly Manual (Doc. No. CR-AMM-1-0-00)
•
PiperSport Aircraft Assembly Manual (Doc. No. PS-AMM-1-0-00)
•
SportCruiser Aircraft Assembly Manual (Doc. No. SC-AMM-1-0-00)
•
Installation Manual for ROTAX Engine Type 912 Series (IM-912, P/N 898643)
•
Operator's Manual for ROTAX Engine Type 912 Series (OM-912, P/N 899649)
•
Maintenance Manual (Line Maintenance) for ROTAX Engine Type 912 Series (MML-912,
P/N 899191)
•
Maintenance
Manual
(Heavy
Maintenance)
for
ROTAX
Engine
Type
912
Series (MMH-912, P/N 899603)
•
Owner's Manual for BRS-6 Emergency Parachute Recovery Systems (Doc. No. 02000003)
•
Parachute Installation Manual for the BRS-1350 onto the Czech Sport Aircraft PS-28
Cruiser & SportCruiser (Doc. No. 020016-PM)
•
Woodcomp Klassic operation and assembly instructions
•
Operator´s Manual Electrical Adjustable Aircraft Propeller SR 3000
•
EZ-Pitch Composite Aircraft Propeller Installation and Operation Instructions (Doc. No.
comp-ac-cf-rev-1a)
•
Sensenich Three Blade Composite Aircraft Propeller Installation and Operation
Instructions for Rotax Engines (Doc. No. 3b0r5)
•
Installation and operation instructions for the installed equipment
This Airplane Maintenance Manual contains information on airplane maintenance including
description of airplane structure and function.
Date of issue: 2013-06-30
Revision No.: 1-5
SportCruiser
SC-AMM-1-0-00
PiperSport
1.2
CHAPTER 1 – GENERAL
Airplane Classification
SportCruiser / PiperSport airplane is two-seat, single engine, low-wing, all-metal airplane with
fixed three-wheel landing gear.
The airplane is designed for basic and advanced training and for leisure time flying.
1.2.1 Power Unit
Power unit consists of:
•
Four-stroke, four-cylinder engine with opposite pistons Rotax 912 ULS2 with max.
continuous power of 69 kW (92.5 hp) at 5,500 RPM.
•
Woodcomp Klassic 170/3/R three-blade, ground adjustable propeller or
•
Woodcomp SR 3000/2W two-blade, in flight adjustable propeller or
•
Sensenich 2A0R5R70EN two-blade, ground adjustable propeller or
•
Sensenich 3B0R5R68C three-blade, ground adjustable propeller.
Revision No.: -
Date of issue: 2013-06-30
1-6
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 1 – GENERAL
1.2.2 Main Technical Data
PiperSport / SportCruiser (early model)
Wing
•
Span.......................................................................... 8.810 m
•
Area........................................................................... 12.30 m
•
MAC .......................................................................... 1,500 mm
•
Wing loading ............................................................. 49 kg/m
•
Aileron area............................................................... 0.46 m
2
(4.98 sq.ft)
•
Flap area ................................................................... 0.65 m
2
(7.0 sq.ft)
(28.90 ft)
2
2
(132.3 sq.ft)
(59.1 in)
(10.0 lb/sq.ft)
Fuselage
•
Length ....................................................................... 6.500 m
(21.33 ft)
•
Width ......................................................................... 1.280 m
(50.4 in)
•
Height........................................................................ 2.370 m
(7.78 ft)
•
Cockpit width............................................................. 1.170 m
(46 in)
Horizontal tail unit
•
•
•
Span.......................................................................... 2.930 m
(9.61 ft)
HTU area................................................................... 2.2 m
2
(23.7 sq.ft)
Elevator area............................................................. 0.8 m
2
(8.6 sq.ft)
Vertical tail unit
•
Height........................................................................ 1.070 m
•
VTU area................................................................... 1 m
•
2
Rudder area .............................................................. 0.4 m
(3.51 ft)
(10.7 sq.ft)
2
(4.3 sq.ft)
Landing gear
•
Wheel track ............................................................... 1.520 m
(4.98 ft)
•
Wheel base ............................................................... 2.070 m
(6.79 ft)
•
Nose landing gear wheel diameter ........................... 343 mm
(13.5 in)
•
Main landing gear wheel diameter ............................ 343 mm
(13.5 in)
Date of issue: 2013-06-30
Revision No.: 1-7
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 1 – GENERAL
Fig. 1-1: SportCruiser / PiperSport Three-view drawing
Revision No.: -
Date of issue: 2013-06-30
1-8
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 1 – GENERAL
SportCruiser (S/N P1102012, P1102014, P1102015, P1102016, P1102019,
P1102027, P1102031, P1102034, C0416 and up)
Wing
•
Span………………………………………………….. ... 8.600 m
•
Area........................................................................... 12.30 m
•
MAC .......................................................................... 1,500 mm
•
Wing loading ............................................................. 49 kg/m
•
Aileron area............................................................... 0.40 m
2
(4.31 sq.ft)
•
Flap area ................................................................... 0.65 m
2
(7.0 sq.ft)
(28.22 ft)
2
2
(132.3 sq.ft)
(59.1 in)
(10.0 lb/sq.ft)
Fuselage
•
Length…………………………………………………. . .6.620 m
(21.78 ft)
•
Width ......................................................................... 1.280 m
(50.4 in)
•
Height………………………………………………… ... 2.315 m
(7.60 ft)
•
Cockpit width............................................................. 1.170 m
(46 in)
Horizontal tail unit
•
•
•
Span.......................................................................... 2.930 m
(9.61 ft)
HTU area................................................................... 2.2 m
2
(23.7 sq.ft)
Elevator area............................................................. 0.8 m
2
(8.6 sq.ft)
Vertical tail unit
•
Height........................................................................ 1.070 m
•
VTU area................................................................... 1 m
•
2
Rudder area .............................................................. 0.4 m
(3.51 ft)
(10.7 sq.ft)
2
(4.3 sq.ft)
Landing gear
•
Wheel track ............................................................... 1.520 m
(4.98 ft)
•
Wheel base ............................................................... 2.070 m
(6.79 ft)
•
Nose landing gear wheel diameter ........................... 343 mm
(13.5 in)
•
Main landing gear wheel diameter ............................ 343 mm
(13.5 in)
Date of issue: 2013-06-30
Revision No.: 1-9
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 1 – GENERAL
Fig. 1-2: SportCruisert Three-view drawing
Revision No.: -
Date of issue: 2013-06-30
1 - 10
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 1 – GENERAL
1.3
Airplane Manufacturer
Czech Sport Aircraft a.s.
Na Záhonech 212, 686 04 Kunovice
Czech Republic
www.czechsportaircraft.com; office@czechsportaircraft.com
Fax: +420 576 519 394, Phone: +420 576 514 034 (Sales Dept.)
1.4
Chapter Order
Chapters in this manual are ordered in ascending sequence from No. 1. Every chapter
describes one system or assembly.
1.4.1 Page Numbering
Example:
1.5
Warnings, Cautions, and Notes
WARNING:
MEANS THAT NON-OBSERVATION OF THE CORRESPONDING
OPERATING
INSTRUCTION,
INSPECTION
OR
MAINTENANCE
PROCEDURE CAN LEAD TO INJURY OR DEATH OF PERSONS.
CAUTION:
MEANS THAT NON-OBSERVATION OF THE CORRESPONDING
OPERATING
INSTRUCTION,
INSPECTION
OR
MAINTENANCE
PROCEDURE CAN LEAD TO DAMAGE OR DESTRUCTION OF DEVICE.
NOTE:
Means that the corresponding operating instruction,
maintenance procedure is considered to be important.
Date of issue: 2013-06-30
inspection
or
Revision No.: 11
1 - 11
SC-AMM-1-0-00
SportCruiser
PiperSport
1.6
CHAPTER 1 – GENERAL
Equipment List
Refer to the SportCruiser / PiperSport Pilot′s Operating Handbook, Section 9 for actual
Equipment list.
1.7
Sources to Purchase Parts
Spare parts can be ordered from CSA through the PS-28 Cruiser / SportCruiser / PiperSport
Illustrated Parts Catalogue (Doc. No. CR-IPC-1-0-00).
1.8
List of Disposable Replacement Parts
ITEM
1.9
PART NUMBER
SOURCE
Czech Sport Aircraft
BRP-Powertrain
Czech Sport Aircraft
Aircraft Parts Store
Czech Sport Aircraft
BRP-Powertrain
Air filter
825710
Fuel filter
10543-1
Oil filter
825701
Tire and tube
Goodyear Flight Special II –
5.00-5
Czech Sport Aircraft
Aircraft Parts Store
Brake lining
WHLM66-106
Czech Sport Aircraft
Aircraft Parts Store
Weight and Balance Information
Refer to SportCruiser / PiperSport Pilot′s Operating Handbook, Section 4 or 6 for the Weight
and Balance Data.
1.10
Tire Inflation Pressure
Refer to Section 8.5.1 of this manual for the tire inflation data.
1.11
Approved Oils and Capacities
Refer to the SportCruiser / PiperSport Pilot′s Operating Handbook, Section 9 or Section 17.5
of this manual for the approved oil and capacity data.
1.12
Recommended Fastener Torque Values
Refer to Section 15.7 of this manual for the torque moments.
1.13
Instructions for Reporting Possible Safety of Flight concerns during
Inspection / Maintenance
If you discover any problems during maintenance of this airplane that in your opinion can
cause safety of flight issues, please report that concern to Czech Sport Aircraft a.s. For this
purpose use Airplane Failure Card (see 17.4).
Please note that if the concern is related to the engine internals, we may refer you to a
certified engine service station.
Revision No.: -
Date of issue: 2013-06-30
1 - 12
SC-AMM-1-0-00
PiperSport
CHAPTER 1 – GENERAL
1.14
SportCruiser
General Safety Information
Safety must be considered the first priority when performing maintenance or service on an
aircraft or part. To minimize the risk to both yourself and others, begin by thinking through
each task that is to be performed before starting any work. Using common sense, think of
ways to avoid these hazards. Be sure to also use the right tool for the task at hand and to use
the proper personal protective equipment. Such equipment may include, but is not limited to:
•
Eye protection – safety glasses, goggles, and face shield
•
Gloves
•
Hearing protection – ear plugs or muffs
•
Apron
•
Protective footwear with non-slip soles
Some other general rules to follow are:
•
Prior to performing maintenance or repair always disconnect the negative (-) battery cable
from the battery.
•
During all service and repair work beware of activating the BRS rocket (if installed).
•
Never leave the ignition switch or the master switch turned on when the engine is not
running. While running the engine on the ground, keep away from the propeller.
•
Remove any loose clothing, such as neckties and scarves. Tuck in your shirt and secure
any long hair to prevent them from becoming tangled in power tools.
•
Remove all jewelry. Not only can items such as rings, watches, and necklaces become
caught in rotating tools, they can also conduct electricity and may cause a short circuit.
This could result in burns or damage to electrical circuits.
•
Aviation gasoline is also highly flammable. When working with the fuel system, always
work in a well-ventilated environment. Any nearby source of ignition such as sparks or an
open flame can result in a fire or explosion. Keep all ignition sources away. Always ground
the airframe to a suitable earth ground during fueling/defueling operations to reduce the
risk of a static discharge ignition source.
•
When working with the landing gear, always support the aircraft properly with jacks. Do
not work underneath the aircraft unless it is properly supported.
Date of issue: 2013-06-30
Revision No.: 1 - 13
SC-AMM-1-0-00
SportCruiser
PiperSport
1.15
CHAPTER 1 – GENERAL
Definitions and abbreviations
ACCU
Accumulator
ADAHRS
Air Data Attitude and Heading Reference System
Annual condition inspection
detailed inspection accomplished once a year on a LSA in accordance with
instructions provided in the maintenance manual supplied with the aircraft. The
purpose of the inspection is to look for any wear, corrosion, or damage that
would cause an aircraft to not be in a condition for safe operation.
ALT
Altimeter
A&P
airframe and powerplant mechanic as defined by Part 66 or 14 CFR Part 65
ATC
Air Traffic Control
bar
Pressure unit (1 bar = 14.5037 psi)
BEACON
Anti-collision beacon
°C
Temperature in degree of Celsius (1°C = (°F - 32) / 1.8)
CAS
Calibrated Airspeed
CHT/CT
Cylinder Head Temperature / Coolant Temperature
COMM
Communication transmitter
EASA
European Aviation Safety Agency
EFIS
Electronic Flight Instrument System
ELT
Emergency Locator Transmitter
EMS
Engine Monitoring System
°F
Temperature in degree of Fahrenheit (1°F = (°C x 1.8) + 32)
FAA
United States Federal Aviation Administration
ft
foot / feet (1 ft = 12 in = 0.3048 m = 304.8 mm)
ft/min
Vertical speed in feet per minute
GPS
Global Positioning System
Heavy maintenance
any maintenance, inspection, repair, or alteration a manufacturer has
designated that requires specialized training, equipment, or facilities
hp
Power unit (1 hp = 0.7457 kW)
HTU
Horizontal Tail Unit
IAS
Indicated Airspeed
IC
Intercom
IFR
Instrument Flight Rules
in
inch (1 in = 25.4 mm)
ISA
International Standard Atmosphere
KCAS
Calibrated Airspeed in knots
kg
kilogram (1 kg = 2.2046 lb)
knot
Speed in NM per hour
KIAS
Indicated Airspeed in knots
km/h
Speed in kilometer per hour
knot
Speed in NM per hour
Revision No.: 6
Date of issue: 2016-01-18
1 - 14
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 1 – GENERAL
kW
Power unit (1 kW = 1.341 hp)
I
liter (1 l = 0.22 UK gal = 0.264 US gal)
lb
pounds (1 lb = 0.4536 kg)
lbf
force unit (1 lbf = 4.45 N)
Line maintenance
any repair, maintenance, scheduled checks, servicing, inspections, or
alterations not considered heavy maintenance that is approved by the
manufacturer and is specified in the manufacturer’s maintenance manual
LoEP
List of Effective Pages
LSA Airplane (Light Sport Aircraft Airplane)
a powered fixed wing aircraft designed per CS-LSA / Specification F2245
LSA Repairman Inspection
U.S. FAA certificated repairman (light sport aircraft) with an inspection rating,
defined by 14 CFR Part 65, authorized to perform the annual condition
inspection on experimental light sport aircraft, or an equivalent rating issued by
other civil aviation authorities.
LSA Repairman Maintenance
U.S. FAA certificated repairman (light sport aircraft) with a maintenance rating
as defined by 14 CPR Part 65, authorized to perform line maintenance on
aircraft certificated as special LSA aircraft. Authorized to perform the annual
condition/100-hour inspection on an LSA, or an equivalent rating issued by
other civil aviation authorities.
m
meter (1 m = 1,000 mm = 3.28 ft = 39.37 in)
mm
millimeter (1 mm = 0.03937 in)
MAC
Mean Aerodynamic Chord
Maintenance manual manual provided by an LSA manufacturer or supplier that specifies all
maintenance, repairs, and alterations authorized by the manufacturer
Major repair, alteration, or maintenance
any repair, alteration, or maintenance for which instructions to complete the task
excluded from the maintenance manual(s) supplied to the consumer are
considered major
Manufacturer
any entity engaged in the production of an LSA or component used on an LSA
max.
maximum
min.
minimum or minute
Minor repair, alteration, or maintenance
any repair, alteration, or maintenance for which instructions provided for in the
maintenance manual(s) supplied to the consumer of the product are considered
minor
mph
Speed in statute miles per hour
N
Newton - force unit (1 N = 0.225 lbf)
Date of issue: 2013-06-30
Revision No.: 1 - 15
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 1 – GENERAL
NM
Nautical Mile (1 NM = 1,852 m)
OAT
Outside Air Temperature
OFF
System is switched off or control element is in off-position
ON
System is switched on or control element is in on- position
Overhaul
maintenance, inspection, repair, or alterations that are only to be accomplished
by the original manufacturer or a facility approved by the original manufacturer
of the product
POH
Pilot Operating Handbook
psi
Pressure unit - pounds per square inch (1 psi = 0.0689bar)
RoR
Record of Revisions
rpm
revolutions per minute
sec.
second
SM
Statute Mile (1SM = 1.609 m)
US gal
US gallon (1 US gal = 0.83 UK gal = 3.785 l)
V
Volt
VFR
Visual Flight Rules
VMC
Visual Meteorological Conditions
VSI
Vertical Speed Indicator
VTU
Vertical Tail Unit
VA
Maneuvering airspeed
VFE
Maximum flap extended speed
VNE
Never exceed speed
VNO
Maximum structural cruising speed
VSO
Stall speed with wing flaps in extended position
VS1
Stall speed with wing flaps in retracted position
VX
Best angle of climb speed
VY
Best rate of climb speed
XPDR
Secondary radar transponder
TSN
Time since new
TSO
Time since overhaul
FH
Flight hour
Cycle
Flight
100-h inspection
same as an annual condition inspection, except the interval of inspection is
100h of operation instead of 12 calendar months. This inspection is utilized
when the LSA is being used for commercial operations such as flight instruction
or rental, or both
Revision No.: -
Date of issue: 2013-06-30
1 - 16
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
PiperSport
Contents
2.1
General .................................................................................................................. 2-3
2.2
Airframe life limitation ............................................................................................ 2-3
2.3
Aircraft parts life limitation ...................................................................................... 2-3
2.4
Ordering spare parts .............................................................................................. 2-4
2.5
Terms and list of aircraft regular maintenance works ............................................ 2-4
2.6
2.5.1
General ..................................................................................................... 2-4
2.5.2
Tables of inspection tasks ........................................................................ 2-5
Lubrication chart .................................................................................................. 2-17
Date of issue: 2018-01-22
Revision No.: 11
2-1
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
2-2
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
2.1
PiperSport
General
This chapter contains information about:
 airframe life limitations
 aircraft parts life limitations
 terms and list of aircraft regular maintenance works
 lubrication chart
2.2
Airframe life limitation
Initial airframe life is 5,000 FH.
2.3
Aircraft parts life limitation
2.3.1
Aircraft parts life time limitation
ITEM
INTERVAL
REPLACE
2,000 FH or
15 years
1
Engine
2
BRS rocket
12 years
X
3
BRS parachute
25 years
X
5 years
X
5 years
X
5 years
X
5 years or
at capacity
drop below
80%
X
5 years
X
4
5
6
7
8
9
10
11
12
Flexible fuel
system hoses
Flexible oil
system hoses
Flexible cooling
system hoses
Battery
OVERHAUL
X
ELT main unit
battery
ELT remote unit
battery
Dynon EFIS
D100 battery unit
5 years
X
At low
capacity 1)
X
Dynon SV-D1000
battery unit
Dynon SV-HDX
1100 battery unit
At low
capacity 2)
At low
capacity 3)
NOTES
Whichever comes first
See OM for Engine
Type 912 Series
Every 6 years repack
Whichever comes first
X
X
1) For battery test, see procedure in the EFIS-D100 Installation Guide, P/N 100478-000,
Rev.H, dated August, 2010, Page 7-1: Internal Battery Check.
2) For battery test, see procedure in the SkyView Pilot’s User Guide, Document 101321-016,
Rev.R dated August, 2014, Section 3-11 Backup Battery Charging and Testing.
3) For battery test, see procedure in the Dynon SkiView HDX System Installation Guide,
Document 101320-027, Rev.AB, dated March, 2017.
Date of issue: 2017-06-30
Revision No.: 8
2-3
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
2.3.2 Propeller parts life time limitation:
- Woodcomp Klassic 170/3/R
- Sensenich 3B0R5R68C
- Sensenich 2A0R5R70EN
ITEM
Klassic 170/3/R
propeller
Sensenich
3B0R5R68C
or
2A0R5R70EN
propeller
TIME TO
PERIODIC
INSPECTION
TIME TO
GENERAL
OVERHAUL
LIFE TIME
NOTES
500 oper. hrs or
24 months
1000 oper. hrs
or 60 months
2000 oper.
hrs or 120
months
Whichever comes first
None
No specified overhaul
time. The propeller
parts are removed
from service when
they can no longer
meet the Continued
Airworthiness
Requirements
2000 hrs
None
Note: see also last instructions issued by the propeller manufacturer
2.3.3 Propeller SR3000/2W – Periodical inspections
OPERATION HOURS
PLACE OF ACTION
AUTHORISATION TO PERFORM
25 hrs.
150 hrs.
300 hrs.
450 hrs.
600 hrs.
750 hrs.
900 hrs.
1050 hrs.
1200 hrs.
1350 hrs.
1500 hrs.
On the airplane
On the airplane
Service organization
On the airplane
Service organization
On the airplane
Service organization
On the airplane
Production plant
On the airplane
Production plant
Aircraft engineer *
Aircraft engineer *
Manufacturer or Service organization
Aircraft engineer *
Manufacturer or Service organization
Aircraft engineer *
Manufacturer or Service organization
Aircraft engineer *
Manufacturer
Aircraft engineer *
Manufacturer
Note: See also last instructions issued by the propeller manufacturer.
*) Aircraft engineer ( AML ICAO, AML part 66, etc.)
Revision No.: 7
Date of issue: 2016-03-30
2-4
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
2.4
PiperSport
Ordering spare parts
Order spare parts through the Airplane failures card - see Section 17.4.
2.5
Terms and list of aircraft regular maintenance works
2.5.1 General
Authorization to perform Time Limits/Maintenance Checks and Inspections:
Repairman (LS-M) or Mechanic (A&P)
Maintenance system serves to maintain flight airworthiness of the SportCruiser / PiperSport
airplane.
Maintenance system is composed of special and scheduled inspections, which must be
performed at least in the following intervals:
CAUTION:
THE INTERVALS OF ENGINE INSPECTIONS AND THE LIST OF WORKS
ARE SHOWN IN THE MAINTENANCE MANUAL (LINE MAINTENANCE)
FOR INSTALLED ENGINE. THE INTERVALS OF PROPELLER
INSPECTIONS AND THE LIST OF WORKS ARE SHOWN IN INSTALLATION
AND OPERATION INSTRUCTIONS FOR THE INSTALLED PROPELLER. IF
THE PERIODICAL INSPECTION IS PERFORMED BEFORE REACHING
THE SPECIFIED TIME INTERVAL, THEN THE FOLLOWING INSPECTION
MUST BE PERFORMED AT THE LATEST WITHIN THE SPECIFIED TIME
INTERVAL FROM THIS INSPECTION (E.G. IF THE FIRST 100-FH
INSPECTION IS PERFORMED AFTER 87 FH THEN THE FOLLOWING 100FH INSPECTION MUST BE PERFORMED AT THE LATEST AFTER 187 FH).
(a) Preflight inspection is performed within the scope given in the POH, Section 4.
(b) Scheduled special inspection of original, old NLG leg (i.e. other than SG0300N) after each
25 landings.
(c) Scheduled special propeller inspection after 25, 50, 150, 500 FH and 2,000 FH (see
Installation and Operating Instructions for installed propeller)
NOTE:
To be performed with a newly installed propeller or with the propeller that was
dismantled and reinstalled on the airplane.
(d) Special engine inspection after the first 25 FH.
CAUTION:
INSPECTION AFTER THE FIRST 25 FH TO BE PERFORMED WITH THE
new engine or with the engine after overhaul.
(e) Scheduled inspection after 50 FH - inspection of engine compartment and NLG leg
Dwg.No.SG0300N.
(f) Scheduled inspection after 100+5 FH - airframe and propeller inspections, engine
inspection according to maintenance system, which is described in Maintenance Manual
(Line Maintenance) for installed engine.
CAUTION:
100-FH LIMIT CAN BE EXCEEDED MAX. BY 5 FH PROVIDING THAT THIS
EXCEEDING WILL BE JUST TO FINISH FLIGHT WHICH STARTED
BEFORE REACTING 100-FH TERM OR FOR FLIGHT WITH THE PURPOSE
TO REACH A PLACE WHERE THE INSPECTION WILL BE CARRIED OUT.
OPERATION TIME, WHICH EXCEEDED 100-FH INTERVAL, MUST BE
INCLUDED AS A TIME FLOWN FOR DETERMINATION OF THE NEXT 100FH INSPECTION.
(g) Scheduled annual inspection contains works of 100-FH inspection and other specified
works (inspections of airframe, engine and propeller).
Date of issue: 2018-01-22
Revision No.: 11
2-5
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
2.5.2 Tables of inspection tasks
Tables of inspection tasks include the list of all works, which are performed during inspection.
Number of chapter is indicated in the first column of this Maintenance Manual where you can
also find more detailed information for performing individual works.
The description of works, which are performed during inspection, is indicated in the second
column.
CAUTION:
ALL DEFECTS FOUND OUT DURING AIRCRAFT INSPECTIONS MUST BE
ELIMINATED!
Revision No.: 5
Date of issue: 2015-05-24
2-6
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
PiperSport
SCHEDULED SPECIAL INSPECTION
Aircraft S/N:
…………………
TSN (FH):
…………
Registration mark:
…………………
TSN (cycles):
…………
Prescribed works
Chpt.
8
Made by
Page: 1 of 1
Checked by
Nose landing Gear
Inspection after each 25 landings
8.4.3
Check of nose landing gear for cracks
Check of the original, old (i.e. other than SG0300N) nose landing
gear leg for cracks, bendings or any non-standard changes of
the NLG shape or function.
Notes:
Date:
…………………
Signature: …………………
SPECIAL INSPECTION AFTER
FIRST 25 FH
Aircraft S/N:
…………………
TSN (FH):
…………
Registration mark:
…………………
TSN (cycles):
…………
Page: 1 of 1
Chpt.
10
Prescribed works
Made by
Checked by
Engine and propeller
List of performed operations for engine is shown in
Maintenance Manual (Line Maintenance) for ROTAX
Engine Type 912 Series (MML-912).
Remove and check engine cowlings for evident signs of
heat damage or cracks.
Inspect and check tightening and securing bolts on the
engine brackets and the engine mount.
Check the engine mount for occurrence of cracks.
Check the exhaust system (and its attachment) for
occurrence of cracks on the exhaust system and welds
(see 10.4.11).
Remove and clean the fuel filter screen inserted in
gascolator.
Fuel system – visual check of tightness.
Oil system – visual check of tightness.
Cooling system – visual check of tightness.
Notes:
Date:
…………………
Signature: …………………
Date of issue: 2018-01-22
Revision No.: 11
2-7
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
SCHEDULED SPECIAL INSPECTION
Aircraft S/N:
…………………
TSN (FH):
…………
Registration mark:
…………………
TSN (cycles):
…………
Prescribed works
Chpt.
10
Made by
Page: 1 of 1
Checked by
Klassic 170 /3/R propeller
Inspection after the first 25 hrs of operation (see 10.4.2.2).
Remove the propeller spinner.
Visually check the propeller.
Tighten the fixing bolts and bolts on spokes of the hub.
Install the propeller spinner.
Inspection after 100 hrs of operation or 12 months * (see
10.4.2.2).
Remove the propeller spinner.
Visually check the propeller and check the grip.
Visually check the propeller hub.
Tighten the fixing bolts and bolts on spokes of the hub.
Install the propeller spinner.
Inspection after 500 hrs of operation or 24 months *
Remove the propeller and send it to the manufacturer/authorized
service organization - checking of propeller after 500 hrs is done
at manufacturer or his authorized service organization.
Inspection after 1,000 hrs of operation or 60 months *
Remove the propeller and send it to the manufacturer/authorized
service organization - checking of propeller after 1,000 hrs is
done at manufacturer or his authorized service organization.
Inspection after 2,000 hrs of operation or 120 months *
Remove the propeller and send it to the manufacturer - checking
of propeller after 2,000 hrs is done at manufacturer.
SR3000 propeller
Inspection after 25 hrs of operation
See 10.4.3.2
Inspection after 150 hrs of operation and following each
next 150 hrs
See 10.4.4.3.2
Notes:
*) hrs of operation or months, whichever comes first
Date:
…………………
Signature: …………………
Revision No.: 7
Date of issue: 2016-03-30
2-8
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
PiperSport
SCHEDULED SPECIAL INSPECTION - continue
Aircraft S/N:
…………………
TSN (FH):
…………
Registration mark:
…………………
TSN (cycles):
…………
Prescribed works
Chpt.
10
3.2.2
Made by
Page: 1 of 1
Checked by
Sensenich 3B0R5R68C / 2A0R5R70EN propeller.
Inspection after the first 25 hrs of operation
See the propeller manufacturer documentation - Sensenich
Three/Two Blade Composite Aircraft Propeller Installation and
Operation Instructions for Rotax Engines
Inspection after 100 hrs of operation or 12 months *
See the propeller manufacturer documentation - Sensenich
Three/Two Blade Composite Aircraft Propeller Installation and
Operation Instructions for Rotax Engines
Major inspection after 2000 hrs of operation
Remove the propeller and send it to the manufacturer/authorized
service organization - checking of propeller after 2000 hrs is
done at manufacturer or his authorized service organization.
Notes:
*)
hrs of operation or months, whichever comes first
Date:
…………………
Signature: …………………
Date of issue: 2017-10-18
Revision No.: 10
2-9
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
SCHEDULED INSPECTION AFTER
50 FH
Aircraft S/N:
…………………
TSN (FH):
…………
Registration mark:
…………………
TSN (cycles):
…………
Page: 1 of 1
Chpt.
8
Prescribed works
Made by
Checked by
Landing Gear
Main Landing Gear
Check visually (using mirror) the condition and wearing
of brake pads (minimum admissible thickness of brake
pad is 2.5 mm) and brake disc.
Check visually the condition and wearing of brake disc minimum admissible thickness of brake disc is 4.25 mm
(0.167 in).
Nose Landing Gear
10
Check of the landing gear leg for cracks.
Engine
Remove and check engine cowlings for evident signs of
heat damage or cracks.
Check the engine mount for occurrence of cracks.
Check the exhaust system (and its attachment) for
occurrence of cracks on the exhaust system and on
welds (see 10.4.11).
Notes:
Date:
…………………
Signature: …………………
Revision No.: 11
Date of issue: 2018-01-22
2 - 10
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
PiperSport
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Aircraft S/N:
…………………
TSN (FH):
…………
Registration mark:
…………………
TSN (cycles):
…………
Type of inspection:
…………………
Page: 1 of 7
Chpt
.
Prescribed works
Made by
Checked by
General
Check the aircraft’s logbooks for condition and check if all
prescribed records are current (airplane log book, engine log
book, propeller log book, and etc.).
Check the remaining service life of life limited items.
Check that the replacement or overhaul of life limited parts
has been in accordance to their specified intervals.
Assure that replacements of these parts are performed in
appropriate intervals.
Check all issued Airworthiness Directives for their
accomplishment.
Check all aircraft, engine and propeller service bulletins for
their accomplishment.
Clean the cockpit carefully.
Clean the aircraft’s exterior, engine and propeller carefully.
Check all exterior and interior markings and placards for their
condition (legibility, placement and security).
Remove and/or open all required covers and hatches.
3
Jack and support the aircraft.
Fuselage
Visually check surface condition including fiberglass parts loosened rivets, deformation, cracks and some other
damage.
Check condition of fuselage-wing and fuselage-stabilizer
fairings.
Check condition of foot rests.
Check condition and attachment of the tailskid.
Check condition and attachment of the canopy frame.
Check condition of the canopy plexiglass and fixed windows
(scratches, cracks, silvering).
Check condition and function of canopy gas struts.
Check attachment and function of the sunshield.
Check condition of the canopy control including canopy lock.
Check condition and adjustment of terminal switches.
Check condition of rubber sealing of the canopy.
Date of issue: 2013-06-30
Revision No.: 2 - 11
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Page: 2 of 7
Chpt
.
4
Prescribed works
Made by
Checked by
Wing
Visually check surface condition - loosened rivets,
deformation, cracks and some other damage.
Check play in the wing attachments; check fuselage – wing
attachment hardware for tightening.
Check condition of antislip strips.
Check condition of the wing lockers.
Check condition and attachment of the wing tips.
Aileron
Visually check surface condition - loosened rivets,
deformation, cracks and some other damage.
Check for free travel.
Check hinges.
Check for securing control links.
Check condition and attachment of the trim tab (right aileron
only).
Flap
Visually check surface condition - loosened rivets,
deformation, cracks and some other damage.
Check for free travel.
Check hinges.
5
Check condition of the control rods and actuator.
Tail Unit
HTU
Visually check surface condition - loosened rivets,
deformation, cracks and some other damage.
Check horizontal stabilizer attachment and securing.
Check elevator attachment and securing.
Check condition and attachment of elevator tips.
Check free travel of the elevator.
Check condition of stop (elevator fully deflected down).
Check condition and attachment of the trim tab.
Check trim tab actuator connector for connection and
securing.
Check condition and attachment of the balance tab (if
installed).
Check condition and securing of the elevator control rod and
the trim tab control actuator.
VTU
Visually check surface condition - loosened rivets,
deformation, cracks and some other damage.
Check attachment and securing of the rudder lower hinge.
Revision No.: -
Date of issue: 2013-06-30
2 - 12
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
PiperSport
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Page: 3 of 7
Chpt
.
5
Prescribed works
Made by
Checked by
Tail Unit (continued)
Check for free travel of the rudder.
Check condition of the stops on the vertical fin.
Check attachment and securing of rudder cables.
6
Check run cables over pulleys, securing of the pulleys.
Control
Aileron and Elevator Control
Check for free travel of control (see 6.4.2).
Check plays (see 6.4.1).
Check securing of links.
Check condition of the stops.
Rudder Control
Check free play of control (see 6.4.2).
Check plays (see 6.4.1).
Check securing of turnbuckles.
Check condition and attachment of pedal springs.
Check condition and of cables (see 6.4.5).
Check adjustment of pedals and full deflections in all position.
Flap Control
Check for free travel of the control lever.
Check securing of links.
Check condition of control actuator and position indicator.
Control of the Pitch and Roll Trim Tab
Check condition of the control actuators and position
indicators.
Check plays (see 6.4.1).
Check securing of links.
7
Check trim tab neutral position adjustment.
Equipment
Check cleanness and condition of upholstery.
Check condition of seats.
Check condition, damage, function and attachment of safety
harnesses and straps in baggage compartment.
Check condition and attachment of ELT.
Check attachment and security of BRS parachute container
and rocket.
Check security and routing of airframe BRS bridles
Date of issue: 2013-06-30
Revision No.: 2 - 13
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Page: 4 of 7
Chpt.
7
Prescribed works
Made by
Checked by
Equipment (continued)
Check attachment, security and routing of BRS activating
handle.
Check attachment of egress cover.
8
Landing Gear
Main Landing Gear
Check condition of landing gear legs and attachment points.
Check attachment of the wheel axis.
Remove and disassemble wheel, clean and lubricate the
bearings; reassemble it and install back.
Check condition, wear and inflation of tires.
Check condition of the wheel disk for occurrence of cracks.
Check securing of bolts.
Check wheel for free rotation.
Check condition and attachment of wheel fairings.
Check function of brakes and parking brake.
Check condition and attachment of brake hoses.
Check visually (using mirror) the condition and wearing of brake
pads – min. admissible thickness of brake pad is 2.5 mm (0.1 in).
Check visually the condition and wearing of brake disc –min.
admissible thickness of brake disc is 4.25 mm (0.167 in).
Check brake fluid leakage - brake fluid hoses, brake pumps,
brake cylinders. Replenish brake fluid as needed (see 8.5.5).
Exchange brake fluid - applied for annual inspection only (see
8.5.5).
Nose Landing Gear
Check condition and attachment points of landing gear leg in
fuselage.
Check of the landing gear leg for cracks.
Remove and disassemble wheel, clean and lubricate the
bearings; reassemble it and install back.
Check condition, wear and inflation of tire.
Check condition of wheel disk and for occurrence of cracks.
Check securing of bolts.
Check for free travel of wheel rotation.
Check of friction shock absorber, check friction torque; as
necessary tighten the nut (see 8.4.2).
Check condition and attachment of wheel fairing.
Check depression of nose wheel absorber (see 8.4.1).
Revision No.: 11
Date of issue: 2018-01-22
2 - 14
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Page: 5 of 7
Chpt.
9
Prescribed works
Made by
Checked by
Fuel System
Drain fuel tanks and gascolator (see 9.5.2).
Remove and clean or replace the fuel filter screen inserted in
gascolator (see 9.5.3).
Check condition and integrity of fuel pumps and hose sleeves in
the engine compartment.
Check fuel selector valve for attachment, function and
arrestment.
Visually check for fuel system tightness.
Check of condition and function of filler caps.
Check tightness and condition of fuel pump for occurrence of
cracks on the pump body (see 9.4.2).
Visual check for impurities in the tank.
10
Check the fuel tank’s vent for its condition (assure that the vent
tube is not clogged).
Engine and Propeller
List of performed operations for engine is shown in Maintenance
Manual (Line Maintenance) for ROTAX Engine Type 912 Series
(MML-912).
List of performed operations for the propeller is shown in
Installation and Operating Instructions for installed propeller.
See also 10.4.2.2 or 10.4.4.1, as applicable.
Remove and check engine cowlings for evident signs of heat
damage or cracks.
Check attachment of the propeller and propeller spacer.
Check condition of the firewall and equipment on firewall.
Inspect and check for tightening and securing the bolts on the
engine brackets and the engine mount.
Check the engine mount for cracks.
Check the exhaust system (and its attachment) for cracks on
the exhaust system and on welds (see 10.4.11).
Check condition and attachment of the airbox.
Check condition and cleanness of the air filter.
Check for leak of fluids.
Check function and condition of throttle and choke controls.
Remove and clean oil tank; install tank back - applied for annual
inspection only.
Date of issue: 2016-03-30
Revision No.: 7
2 - 15
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Page: 6 of 7
Chpt.
11
Prescribed works
Made by
Checked by
Electrical System
Check attachment and condition of battery.
Check level of battery charge.
Perform battery capacity test- applied for annual inspection
only.
Check condition, attachment and integrity of wiring.
Check condition and securing of plug/socket outlets.
Check condition of switches, fuses and circuit breakers.
Check condition of the landing light.
12
Check condition of the position / strobe lights.
Instruments and Avionics
Check general condition and attachment of the instrument panel.
Check condition and attachment of instruments.
Check condition and attachment of the pitot tube.
Check cleanness of air inlet holes of pitot tube.
Check attachment and securing of hoses to the instruments.
Check for pitot-static system tightness (see 12.4.1) (with 2
years periodicity).
13
Visually check condition of navigation and communication
instruments.
Perform compensation of magnetic and EFIS compass applied for annual inspection only.
Check condition of COMM, ELT, XPDR, NAV antennas and OAT
probe.
Perform capacity test of EFIS D100 internal emergency battery
- applied for annual inspection only.
Heating and Ventilation System
Check cleanness and passage of air inlet holes.
Check line and integrity of the heating and ventilation system
hoses.
Check condition and attachment of the heat exchanger.
Check of functionality of rod and flap.
All
Check for corrosion.
Check for hard handling.
Revision No.: -
Date of issue: 2013-06-30
2 - 16
SC-AMM-1-0-00
SportCruiser
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
PiperSport
SCHEDULED ANNUAL PERIODICAL INSPECTION OR
INSPECTION AFTER 100 FH
Page: 7 of 7
Chpt.
Prescribed works
Made by
Checked by
Operational and Functional Tests
Check the function of the interior and exterior lighting.
Check the function of the canopy closed signalization.
Check the function of the flap control actuator including
signalization.
Check the function of the roll and pitch control actuators
including signalization.
Check function of navigation and communication instruments
- in accordance with all valid and applicable regulations applied for annual inspection only.
ELT - perform a functional test according to the applicable
regulations
Dynon EFIS D100 - perform backup battery test
Dynon EFIS D1000 - perform backup battery test
Dynon SV-HDX 1100 - perform backup battery test
Check function of the signalling / warning lights.
Check all instruments for their function.
Close up Tasks
Lubricate all items according to the lubrication chart.
Install and close all covers and hatches.
Lower the aircraft.
Carry out an engine performance check and verify the
engine’s power (see 10.4.1).
After engine run-up, test and visually check the fuel and oil
system for leakage and their security of all components.
Check the removal of all detected defects.
Fill out the required logbook entries.
Notes:
Date:
…………………
Signature:
Date of issue: 2017-06-30
…………………
Revision No.: 8
2 - 17
SC-AMM-1-0-00
SportCruiser
PiperSport
2.6
Unit
Engine
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
Lubrication chart
Area of lubrication
After first
25 FH
Every
100 FH
Every
500 FH
X
X
X
LPS1
X
X
X
LPS1
Throttle control cable on the inlet into
terminal (in the engine compartment).
Choke control cable on the inlet into
terminal (in the engine compartment).
Lubricant
Nose
landing
gear
Landing gear leg in the area of
mounting (lubricator) and the axis of
rotation (see 8.5.4).
X
X
X
AeroShell
Grease 22
Main
landing
gear
Brake pad pins.
X
X
X
LPS3
Revision No.: -
Date of issue: 2013-06-30
2 - 18
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
Unit
Ailerons
After first
25 FH
Every
100 FH
Every
500 FH
Hinges.
X
X
X
Rod end bearings of the control tubes.
-
-
X
Two-arm control levers in the
fuselage.
-
-
X
Bell cranks in the wings.
-
-
X
AeroShell
Grease 22
Hinges.
X
X
X
AeroShell
Grease 22
Rod end bearings on actuator.
-
-
X
AeroShell
Grease 22
Elevator hinges.
X
X
X
-
-
X
Area of lubrication
Flaps
HTU
Rod end bearing of the elevator
control tubes.
Pins (front stabilizer hinge)
Annual insp.
Date of issue: 2013-06-30
Lubricant
AeroShell
Grease 22
AeroShell
Grease 22
AeroShell
Grease 22
AeroShell
Grease 22
AeroShell
Grease 22
LPS3
Revision No.: 2 - 19
SC-AMM-1-0-00
SportCruiser
PiperSport
Unit
VTU
Trim
and
balance
tabs
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
After first
25 FH
Every
100 FH
Every
500 FH
Rudder hinges.
X
X
X
Cable shackles on the rudder control
cables.
X
X
X
Tabs hinges.
X
X
X
LPS1
Rod end on actuators.
X
X
X
AeroShell
Grease 22
Area of lubrication
Revision No.: -
Lubricant
AeroShell
Grease 22
AeroShell
Grease 22
Date of issue: 2013-06-30
2 - 20
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
Unit
Aileron,
elevator
control
Rudder
control
After first
25 FH
Every
100 FH
Every
500 FH
All movable links in the cockpit.
-
-
X
All movable links in the cockpit.
-
-
X
Cable shackles of rudder control.
X
-
X
Area of lubrication
Date of issue: 2013-06-30
Lubricant
AeroShell
Grease 22
AeroShell
Grease 22
AeroShell
Grease 22
Revision No.: 2 - 21
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 2 – TIME LIMITS / MAINTENANCE CHECKS
Revision No.: -
Date of issue: 2013-06-30
2 - 22
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 3 – FUSELAGE
Contents
3.1
General .................................................................................................................. 3-3
3.2
Description and operation...................................................................................... 3-3
3.2.1
Front part of the fuselage ...................................................................... 3-3
3.2.2
Rear part of the fuselage ....................................................................... 3-3
3.2.3
Cockpit................................................................................................... 3-4
3.2.4
Baggage compartment .......................................................................... 3-5
3.2.5
Crew canopy.......................................................................................... 3-5
3.2.6
3.3
3.4
3.2.5.1
Canopy .................................................................................. 3-6
3.2.5.2
Rear fixed canopy windows .................................................. 3-6
Balance ballast ...................................................................................... 3-6
Removal / Installation ............................................................................................ 3-7
3.3.1
Canopy removal .................................................................................... 3-7
3.3.2
Canopy installation ................................................................................ 3-7
3.3.3
Gas strut removal .................................................................................. 3-8
3.3.4
Gas strut installation .............................................................................. 3-9
3.3.5
Cabin lock removal ................................................................................ 3-9
3.3.6
Cabin lock installation.......................................................................... 3-10
3.3.7
Balance ballast installation...............................................................................3-10
Check / Adjustment.............................................................................................. 3-10
3.4.1
Canopy lock adjustment ...................................................................... 3-12
3.4.2
Towing gear control cable adjustment................................................. 3-12
Date of issue: 2014-09-08
Revision No.: 4
3-1
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 3 – FUSELAGE
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
3-2
SC-AMM-1-0-00
PiperSport
CHAPTER 3 – FUSELAGE
3.1
SportCruiser
General
SportCruiser / PiperSport fuselage is a semi-monocoque structure formed by stiffeners and
aluminum sheet. The fuselage consists of the front part with the cockpit and the rear part, the
integral part of which is the fin.
This chapter describes the following:
•
front part of the fuselage
•
rear part of the fuselage
•
cockpit (crew compartment)
•
baggage compartment
•
cockpit canopy.
Fig. 3-1: Fuselage layout
3.2
Description and operation
3.2.1
Front part of the fuselage
The front part of the fuselage consists of bulkheads No. 1 to 5 (see Fig. 3-1). The nose landing
gear attachments (1, Fig. 3-2) are located on the bulkhead No. 1, which also separate the
cockpit from the engine compartment. Cockpit with fixed seats is located between bulkheads
No. 1 and 5. The baggage compartment is located behind the seats. Center section of wing
consists of the main attachments (2) are located between bulkheads No. 2 and 3 and the rear
attachment (3), which is located on the bulkhead No. 5, main landing gear attachment points
(4) are located behind main center wing spar, the engine mount attachment points (5) are
located on the bulkhead No. 1, which is firewall.
3.2.2
Rear part of the fuselage
The rear part of the fuselage is located in the area from the bulkhead No. 6 up to the bulkhead
No. 13 (see Fig. 3-1). It is a semi-monocoque structure formed by stiffeners and aluminum
skin. The rear part of fuselage is of elliptic section covered by aluminum sheet. The fin with
rudder attachments (6, Fig. 3-2) and stabilizer attachments (7) is an integral part of the rear
part of the fuselage. The bulkheads No. 12 and 13 form the stabilizer attachment points.
Date of issue: 2013-06-30
Revision No.: 3-3
SC-AMM-1-0-00
SportCruiser
PiperSport
1
2
3
4
5
6
7
CHAPTER 3 – FUSELAGE
Nose landing gear attachments
Wing attachment, main
Wing attachment, rear
Main landing gear attachments
Engine mount attachments
Rudder attachments
Stabilizer attachments
Fig. 3-2: Fuselage monocoque
3.2.3
Cockpit
The cockpit (see Fig. 3-1) is located in the front part of the fuselage between the bulkheads
No. 1 and 5. The instrument panel is located between bulkhead No. 1 and frame No. 2. In the
middle of the cockpit there is a middle console with control elements. The cockpit is equipped
with two fixed seats.
NOTE:
Current instrument panel arrangement is stated in the Pilot′s Operation
Handbook, Supplement No. 2.
The cockpit floor and baggage compartment is covered with a removable carpet and the
middle console is covered with thin upholstery. The interior cockpit sides are covered with
padded panels containing pockets and armrests.
Revision No.: -
Date of issue: 2013-06-30
3-4
SC-AMM-1-0-00
PiperSport
CHAPTER 3 – FUSELAGE
3.2.4
SportCruiser
Baggage compartment
Baggage compartment (8, Fig. 3-3) is located between the seats and the bulkhead No. 7.
Max. baggage weight transported in the baggage compartment is 18 kg (40 lbs).
3.2.5
Crew canopy
The crew canopy is produced of organic glass and consists of opening canopy and rear fixed
canopy windows.
1
2
3
4
5
Canopy
Canopy hinge
Gas strut
Canopy lock
Inside opening lever
6
7
8
9
10
Locking lever
Rear canopy window
Baggage compartment
Sunshield
Sliding side ventilation window
Fig. 3-3: Canopy, rear canopy window
Date of issue: 2013-06-30
Revision No.: 3-5
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 3 – FUSELAGE
3.2.5.1 Canopy
The canopy (1, Fig. 3-3) has a semi drop shape and enables access to the cockpit. The
canopy consists of composite frame on which the windscreen is attached. The canopy is
suspended in two swivel hinges (2) on front sides of the composite fixed frame. The canopy
can be opened forward and is lightened by a gas strut (3) each side which keep it in the
opened position. The canopy lock (4) is placed on the left side of fuselage below the cockpit
frame. The locking levers (6) are installed inside the fixed frame. The opening lever (5) is
placed between the seats backs. The handle (7, Fig. 3-5) is attached on the upper part of the
composite frame. Along its whole perimeter, the canopy is sealed with a silicone profile. The
canopy is generally equipped with the sunshield (9, Fig. 3-3) and sliding ventilation windows
located on both sides of the canopy.
For newer models of the SportCruiser airplane closing and securing of the canopy is sensed
by one terminal switch, located at the inside opening lever between the seats (see Wiring
Manual). If the canopy is not properly closed and secured, the CABIN OPENED light will be
flashed in red on the upper part of the left instrument panel.
3.2.5.2 Rear fixed canopy windows
The rear fixed canopy windows consists of two symmetrical windows (7, Fig. 3-2) riveted and
glued on the fuselage side skins.
3.2.6
Balance ballast
The airplane can be equipped with balance ballast (see Fig. 3-8), installed in the airplane tail
part. Balance ballast ensures of not exceeding of the approved maximal front C.G. position of
the empty airplane if combination of the optional “nose heavy” airplane installation (e.g.
Sensenich propeller, improved nose landing gear leg, efficient heating, BRS) is installed.
Balance ballasts are graduated – 0.25 kg, 0.5 kg and 0.8 kg. The total weight is the sum of
weight of all items - plate, fasteners and balance ballast.
Revision No.: 4
Date of issue: 2014-09-08
3-6
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 3 – FUSELAGE
3.3
Removal / Installation
3.3.1
Canopy removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
socket wrench 7/16”
-
screwdriver
-
pliers
CAUTION:
DURING CANOPY REMOVAL BE CAREFULLY TO AVOID SCRATCHING
THE GLASS.
NOTE:
For canopy removal two persons are requested.
(a) Open the canopy (1, Fig. 3-4).
(b) Remove the dummy plugs (3).
(c) Disconnect upper end of the gas struts (2) on both sides of canopy (1) (see 3.3.3).
(d) Hold the canopy.
(e) Unscrew the nuts (5), remove the washers (6) and the bolts (4).
(f) Carefully remove the canopy (1) and store it in a safe place so that windscreen damage
cannot occur.
3.3.2
Canopy installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Socket wrench size 7/16
-
screwdriver
-
pliers
CAUTION:
DURING CANOPY INSTALLATION
SCRATCHING THE GLASS.
BE
CAREFULLY
NOTE:
For canopy installation two persons are requested.
TO
AVOID
(a) Set the canopy (1, Fig. 3-4) on the fixed frame.
(b) Insert the bolts (4) into the hinges, install the washers (6), screw and tighten the nuts (5).
(c) Open the canopy (1) and hold it.
(d) Connect upper end of the gas struts (2) on both sides of canopy (1) (see 3.3.4).
(e) Install new dummy plugs (3).
Date of issue: 2013-06-30
Revision No.: 3-7
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SportCruiser
PiperSport
CHAPTER 3 – FUSELAGE
NOTE
Access to the nuts (5) and
washers (6) is from the cockpit.
1
2
3
4
Canopy
Gas strut
Dummy plug
Bolt
5 Nut
6 Washer
7 Handle
Fig. 3-4: Canopy removal / installation
3.3.3
Gas strut removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
-
pliers
(a) Open the canopy (5, Fig. 3-5); hold it.
(b) Remove the safety clip (3) from the ball joint end fittings (2) on the canopy frame (5) and
on the fixed frame (6).
(c) Remove the gas strut (1).
Revision No.: -
Date of issue: 2013-06-30
3-8
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PiperSport
CHAPTER 3 – FUSELAGE
1
2
3
4
5
6
Gas strut
Ball joint end fitting
Safety clip
Ball stud
Canopy frame
Fixed frame
Fig. 3-5: Gas strut removal / installation
3.3.4
Gas strut installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
pliers
(a) Inspect the strut (1, Fig. 3-5) whether it is not damaged.
(b) Insert top ball joint end fitting (2) on the ball stud (4) on the canopy frame (5), and bottom
ball joint end fitting (2) on the ball stud (4) on the fixed frame (6)
(c) Secure the joints with safety clips (3).
3.3.5
Cabin lock removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher
Tools needed:
-
screwdriver
(a) Unscrew the screw (2, Fig. 3-6) attaching the lock (1) to the fuselage skin.
Date of issue: 2013-06-30
Revision No.: 3-9
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 3 – FUSELAGE
(b) Remove the lock (1).
1 Lock
2 Screw
Fig 3-6: Canopy lock removal / installation
3.3.6
Cabin lock installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
(a) Put the lock (1, Fig. 3-6) in to the hole in the fuselage skin.
(b) Screw the screw (3) attaching lock to the fuselage skin.
3.3.7
Balance ballast installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 3/8, 7/16 in
-
screwdriver
-
pliers
-
electric drill
-
drill bit 4.8 mm (7/16 in)
Revision No.: 4
Date of issue: 2014-09-08
3 - 10
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 3 – FUSELAGE
CAUTION:
USE ONLY ONE BALANCE BALLAST, NOT THEIR COMBINATION. MAX.
WEIGHT OF BALLAST IS 0.8 KG.
(a) By weighing or computation determine the mass of required ballast (mass of ballast: 0.25
kg or 0.5 kg or 0.8 kg; arm of ballast: 4,545 mm). Weighing process is given in the POH,
Section 6.
(b) Remove the horizontal stabilizer (see 5.3.1).
(c) Unscrew the bolts (12, Fig. 3-8) and remove the cover (11).
(d) According to Fig. 3-8 insert to the upper holes of the bulkhead No. 13 bolts (6) with
washers (8), on the bolts insert balance ballast (1), plate (2), washers (8); screw and
tighten nuts (7).
(e) According holes in the plate (2) drill both lower holes.
(f) Insert to the lower holes of the bulkhead No. 13 bolts (3) with washers (5), on the bolts
insert washers (5); screw and tighten nuts (4).
(g) Place the cover (11) and fasten it by bolts (12).
(h) Install the horizontal stabilizer (see 5.3.2).
(i) Weight the airplane and verify that C.G. of the empty airplane is in desire range.
1
2
3
4
5
Balance ballast
Plate
Bolt (2 pcs.)
Nut (2 pcs.)
Washer (4 pcs.)
6 Bolt (2 pcs.)
7 Nut (2 pcs.)
8 Washer (4 pcs.)
For information:
9 Rear cover
10 Bolt
11 Cover
12 Bolt
Fig 3-8: Balance ballast installation
Date of issue: 2014-09-08
Revision No.: 4
3 - 11
SportCruiser
SC-AMM-1-0-00
PiperSport
3.4
Check / Adjustment
3.4.1
Canopy lock adjustment
CHAPTER 3 – FUSELAGE
Adjust the locks so that the canopy could be locked freely.
Set the length of the rod.
3.4.2
Towing gear control cable adjustment
Adjust the length of towing gear control cable so that the control lever and hook lever in the
open position touched the stops.
Revision No.: -
Date of issue: 2013-06-30
3 - 12
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 4 - WING
Contents
4.1
General .................................................................................................................. 4-3
4.2
Description and operation...................................................................................... 4-3
4.3
4.2.1
Wing ...................................................................................................... 4-3
4.2.2
Wing flaps.............................................................................................. 4-4
4.2.3
Ailerons.................................................................................................. 4-5
4.2.4
Fuel tanks .............................................................................................. 4-6
4.2.5
Wing lockers .......................................................................................... 4-6
Removal / Installation ............................................................................................ 4-6
4.3.1
Wing removal......................................................................................... 4-6
4.3.2
Wing installation .................................................................................... 4-7
4.3.3
Wing flap removal.................................................................................. 4-9
4.3.4
Wing flap installation............................................................................ 4-10
4.3.5
Aileron removal.................................................................................... 4-10
4.3.6
Aileron installation ............................................................................... 4-11
4.4
Check / Adjustment.............................................................................................. 4-12
4.5
Exchanges / Service information ......................................................................... 4-12
Date of issue: 2013-06-30
Revision No.: 4-1
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 4 - WING
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
4-2
SC-AMM-1-0-00
PiperSport
CHAPTER 4 - WING
4.1
SportCruiser
General
SportCruiser / PiperSport wing is an aluminum structure and is equipped with flaps, ailerons
and fuel tanks.
This chapter describes the structure of:
•
wings
•
wing flaps
•
ailerons
•
fuel tanks
Fig. 4-1: Wing layout
4.2
Description and operation
4.2.1
Wing
The wing of the airplane is formed from center section of wing made as main and rear spar,
which is integrated part of fuselage (Fig. 3-1), and from outer wings placed between ribs No. 1
and 9, which have trapezoid shape (Fig. 4-1). The wing is of all-metal main spar structure with
a rear spar. In the outer wings are installed between ribs No. 4 and 6a leading edge fuel tanks,
on the aft spar there are hinged ailerons (1, Fig. 4-2) and flaps (2). The wing tips (3), made out
of fiberglass, are riveted on the wing ribs No. 9. On wing tips are installed the position lights
(6). The outer wing is attached to the center section by means of 6 bolts (4) and the rear
attachment (5) (positioned on the rear spar). The aileron control push rods are lead between
the spars. The aileron trim tab is installed on the right aileron.
Date of issue: 2013-06-30
Revision No.: 4-3
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PiperSport
1
2
3
4
5
CHAPTER 4 - WING
Aileron
Flap
Wing tip
Front attachment
Rear attachment
6
7
8
9
Position light
Wing locker
Fuel quantity sensor cover
Filler cap
Fig. 4-2: Wing, left
4.2.2
Wing flaps
Flaps are of all-metal structure consisting of the skin (1, Fig. 4-3) aluminum sheet metal, spar
and ribs (2) which are connected by means of riveting. Flaps are suspended on the wing aft
spar by means of two hinges (4). There is a guiding plate (3) on flap root rib, where is
connected the flap control pin. The flap control actuator is installed in the fuselage behind left
seat under floor of baggage space.
Revision No.: -
Date of issue: 2013-06-30
4-4
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PiperSport
CHAPTER 4 - WING
1
2
3
4
SportCruiser
Flap skin
Flap rib
Guiding plate
Flap hinge
Fig. 4-3: Wing flap, left
4.2.3
Ailerons
Ailerons (Fig. 4-4) are of aluminum structure consisting of the skin (1) aluminum sheet metal,
spar and ribs (2) which are connected by means of riveting. Ailerons are suspended on the
rear spar by means of two hinges (4). Moreover the trim tab (5) is installed on the right aileron
serving the lateral balance of airplane. The trim tab actuator is installed inside of aileron.
Control lever (3) is installed on the root aileron rib.
1
2
3
4
5
Aileron skin
Aileron rib
Aileron control lever
Aileron hinge
Aileron trim tab
Fig. 4-4: Aileron, right
Date of issue: 2013-06-30
Revision No.: 4-5
SC-AMM-1-0-00
SportCruiser
PiperSport
4.2.4
CHAPTER 4 - WING
Fuel tanks
Fuel tanks are of welded all-metal structure consisting of aluminum sheet metal skin (1, Fig. 45) and two ribs (2). There are on each tank filler neck (3), fuel quantity sensor (4), venting tube
(5), finger screen (6) and drain valve (7).
1
2
3
4
Metal skin
Rib
Filler neck
Fuel quantity sensor
Fuel tank, right
4.2.5
Fig. 4-5:
5 Venting tube
6 Finger screen
7 Drain valve
Fuel tank, left
Wing lockers
Wings are equipped with wing locker (7, Fig. 4-2) placed between ribs No.4 and 5 behind main
spar. Capacity of each wing locker is 10 kg (22 lbs). Access doors installed on piano hinge are
locked per quick fasteners.
4.3
Removal / Installation
4.3.1
Wing removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in, 1/2 in
-
Phillips PH2 screwdriver
-
cutting pliers
-
hammer
(a) Remove the seats and access cover plates on the seats floor.
(b) Disconnect whole 6 nuts from the attachment bolts on the main spar and remove 6 bolts.
(c) Disconnect aileron control push rod on the control lever in fuselage behind the seats.
Revision No.: 10
Date of issue: 2017-10-18
4-6
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CHAPTER 4 - WING
(d) Remove bushes (24, Fig. 4-6) (if installed) from the aileron control push rod (valid for
SportCruiser airplanes from S/N C0416).
(e) Remove cover (11, Fig. 4-7) on the bottom wing root.
(f) Disconnect rear attachment bolts on rear spar.
(g) Secure the flap in closed position by means of the cable ties (on flap hinges).
(h) The first person will hold the wing on the wing tip.
(i) One person hold the wing on the winglet side, the second person by the root on the
leading edge side remove first bottom attachment bolt from the main spar, the third person
by the root on the trailing edge.
(h) Release the wing by slight lifting the wing tip upwards.
(i) By pulling the wing in direction from the fuselage, disconnect the outer wing from the
fuselage.
(j) Move the wing about 300 mm (12 in) out from the fuselage and disconnect fuel lines,
cable plugs, aileron rod sealing, sockets of electrical systems and on left wing also pitotstatic tubes.
(k) Position the disconnected wing in such a way that its damaging cannot occur.
4.3.2
Wing installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in, 1/2 in
-
Phillips PH2 screwdriver
-
pliers
-
hammer
Install the wing according to the following procedure:
(a) Before installation clean the attachments and bolts of the outer and center wing from dirt.
Preserve bolts and attachments by means of lubricating grease.
(b) Set the wing about 300 mm (12 in) to the fuselage side. The first person will hold the wing
on the wing tip, the second person near the root on the leading edge and the third person
near the root on the trailing edge.
(c) Connect wiring (see Wiring Manual or Chapter 17).
(d) Connect fuel hoses and pitot-static hoses on the left wing; attach the aileron rod sealing.
(e) Set the outer wing carefully with the wing attachments on the center wing so that the
attachments on the wing and on the fuselage are concentric and flap control pin placed in
the flap guiding plate.
(f) The person keeping the wing on the leading edge will insert the first bolt into the upper
main attachment (the bolt head is in flight direction) and shift it by means of slight
hammering to the stop (shifting can be facilitated by slight moving the wing tip up and
Date of issue: 2013-06-30
Revision No.: 4-7
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 4 - WING
down). Then insert the bolts into the lower main attachment and shift them by slight
hammering to the stop.
(g) Attach the bolt and nut into the rear attachment of the wing and tight it with the tightening
moment 11 – 16 Nm (100 – 140 inch.lb).
(j) Put the washers on all of 6 attachment bolts of the wing and screw the nuts on them.
(k) Connect the aileron control push rod on control lever behind the seats and perform
tightening up to the tightening torque.
(l) Install bushes (24, Fig. 4-6) (if installed) to the aileron control push rod (valid for
SportCruiser airplanes from S/N C0416).
(m) Perform check the trim tab operation, flaps and ailerons deflections (see 6.4.3), possibly
adjusting of theirs deflections (see 6.4.4).
(n) Install access cover plates on the seats floor and access cover on the bottom wing root.
1
2
3
4
5
6
7
Wing, left
Bolt (6 pcs.)
Nut (6 pcs.)
Washer (10 pcs.)
Bolt
Nut
Washer
8
Bolt
9
Nut
10 Washer
11 Fuel hose
12 Hose connector
13 Hose clamp
14 Pitot static hose
15 Hose connector
16 Fuel quantity sensor
wiring
17 Aileron trim tab wiring
(only right side)
18 Position light wiring
19
20
21
22
23
24
25
Front attachment
Front attachment
Rear attachment
Control lever
Aileron rod sealing
Bush (2 pcs.)
Cable tie (2 pcs.)
Fig. 4-6: Wing removal / installation
Revision No.: -
Date of issue: 2013-06-30
4-8
SC-AMM-1-0-00
PiperSport
CHAPTER 4 - WING
4.3.3
SportCruiser
Wing flap removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
(a) Open the flap (1, Fig, 4-7) in full position.
(b) Unscrew the nuts (5), remove the washers (6), bolts (4) and disconnect both flap hinges;
remove the washers (7).
(c) Carefully remove the flap (1) from the wing.
(d) Store the removed flap on a safe place and prevent it from damage.
1
2
3
4
5
6
Wing flap
Inner flap hinge
Outer flap hinge
Bolt
Nut
Washer
7
8
9
10
11
Washer
Wing inner flap hinge
Wing outer flap hinge
Control pin
Rear attachment cover
Fig. 4-7: Wing flap removal / installation
Date of issue: 2013-06-30
Revision No.: 4-9
SportCruiser
SC-AMM-1-0-00
PiperSport
4.3.4
CHAPTER 4 - WING
Wing flap installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
(a) Clean all attachments and apply lubricant on it (see 2.6). Do the same for the hinges on
the wing.
(b) Set the flap hinges (2; 3, Fig. 4-7) in to the wing hinges (8; 9) and control pin (10) in to the
guiding plate.
(c) Insert the bolts (4) and the washers (7) in to the hinges.
(d) Install the washers (6) and the nuts (5); tight the nuts with prescribed tightening moment
5.5 – 8 Nm (50 – 70 inch lb).
(e) Close the flap in the zero (up) position.
(f) Perform check the wing flaps operation and their deflections (see 6.4.3).
4.3.5
Aileron removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
cutting pliers
(a) Disconnect the control rod with control lever.
(b) On the right aileron only:
•
remove the cover (10, Fig, 6-8) from the hole for access to trim tab actuator (1)
•
disconnect trim tab actuator wires (2).
(c) Unscrew the nuts (4, Fig. 4-8), remove the washers (5), bolts (3) and disconnect both
aileron hinges.
(d) Carefully remove the aileron (1) from the wing.
(e) Store the removed aileron on a safe place and prevent it from damage.
Revision No.: -
Date of issue: 2013-06-30
4 - 10
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 4 - WING
4.3.6
Aileron installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
-
Tools needed:
-
wrench size 7/16 in
-
pliers
(a) Clean all attachments and apply lubricant on it (see 2.6). Do the same for the hinges on
the wing.
(b) Set the aileron (1, Fig. 4-8) on the wing in to the both hinges.
(c) Insert trim tab actuator wires (2, Fig. 6-8) going out from wing to the aileron.
(d) Insert the bolts (3, Fig. 4-8) in to the hinges, install the washers (5) and screw the nuts (4).
(e) Connect the control rod (6) with aileron control lever (2) by means of bolt (7), nut (8) and
washer (9).
(f) Connect trim tab actuator wires (2, Fig. 6, 8); close the access hole with cover (10) - on
the right aileron only (see Wiring Manual or Chapter 17).
(g) Perform check the trim tab operation and aileron deflections (see 6.4.3), possibly adjusting
of aileron deflections (see 6.4.4).
1
2
3
4
5
Aileron
Control lever
Bolt
Nut
Washer
6
7
8
9
Control rod
Bolt
Nut
Washer
Fig. 4-8: Aileron removal / installation
Date of issue: 2013-06-30
Revision No.: 4 - 11
SportCruiser
SC-AMM-1-0-00
PiperSport
4.4
CHAPTER 4 - WING
Check / Adjustment
No procedures included.
4.5
Exchanges / Service information
No procedures included.
Revision No.: -
Date of issue: 2013-06-30
4 - 12
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 5 – TAIL UNIT
Contents
5.1
General .................................................................................................................. 5-3
5.2
Description and operation...................................................................................... 5-3
5.3
5.2.1
Horizontal stabilizer ............................................................................... 5-3
5.2.2
Elevator with tabs .................................................................................. 5-4
5.2.3
Fin.......................................................................................................... 5-5
5.2.4
Rudder ................................................................................................... 5-6
Removal / Installation ............................................................................................ 5-7
5.3.1
Horizontal stabilizer removal ................................................................. 5-7
5.3.2
Horizontal stabilizer installation ............................................................. 5-7
5.3.3
Elevator removal.................................................................................... 5-9
5.3.4
Elevator installation ............................................................................... 5-9
5.3.5
Trim tab removal.................................................................................. 5-10
5.3.6
Trim tab installation ............................................................................. 5-10
5.3.7
Balance tab removal............................................................................ 5-12
5.3.8
Balance tab installation ....................................................................... 5-12
5.3.9
Rudder removal ................................................................................... 5-12
5.3.10
Rudder installation............................................................................... 5-13
5.4
Check / Adjustment.............................................................................................. 5-14
5.5
Exchanges / Service information ......................................................................... 5-14
Date of issue: 2013-06-30
Revision No.: 5-1
PS-28 Cruiser
SC-AMM-1-0-00
SportCruiser
CHAPTER 5 – TAIL UNIT
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
5-2
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 5 – TAIL UNIT
5.1
General
Tail unit of SportCruiser / PiperSport airplane is of all-metal structure and is composed of:
•
stabilizer
•
elevator with tabs
•
fin
•
rudder.
5.2
Description and operation
5.2.1
Stabilizer
Stabilizer (1, Fig. 5-1) is of the all-metal structure consisting of the two spars, ribs and
aluminum skin. Individual parts are assembled by riveting. The elevator is attached to the rear
spar by means of three hinges (2; 3). The horizontal stabilizer is mounted on the fuselage by
means of front and rear attachments. The front attachments consist of two pins (5, Fig. 5-3),
which are riveted on bulkhead No. 12 and bushings (4, Fig. 5-1) riveted on front stabilizer
spar. The rear attachments consist of two hinges (6, Fig. 5-3) riveted on sides of bulkhead
No. 13.
1
2
3
4
5
Stabilizer
Elevator centre hinge
Elevator outer hinge
Bushing
Balance tab rod hinge
Fig. 5-1: Stabilizer
Date of issue: 2013-06-30
Revision No.: 5-3
PS-28 Cruiser
SC-AMM-1-0-00
SportCruiser
5.2.2
CHAPTER 5 – TAIL UNIT
Elevator with tabs
Elevator (1, Fig.5-2) is of all-metal structure and consists of aluminum skin, spar and ribs.
Individual parts are assembled by riveting. Control lever (5) is riveted on middle elevator rib.
Mass balances (6) are riveted at the both elevator ends and covered composite tips (7). The
elevator is equipped with the trim tab (2); newer SportCruiser airplanes also have balance tab
(3). Both tabs are hinged by means of the piano hinge on the rear spar close to the trailing
edge of the elevator. The balance tab (3) is interconnected by means of the rod with the hinge
(5, Fig. 5-1) on the stabilizer. The tabs are made of aluminum sheet.
1
2
3
4
5
6
7
8
Elevator
Trim tab
Balance tab
Outer hinge
Centre hinge
Control lever
Mass balance
Elevator tip
Fig. 5-2: Elevator
Revision No.: -
Date of issue: 2013-06-30
5-4
SC-AMM-1-0-00
PiperSport
CHAPTER 5 – TAIL UNIT
5.2.3
SportCruiser
Fin
The vertical fin (1, Fig. 5-3) is of an aluminum structure and is an integral part with the rear
part of the fuselage. The fin consists of stiffeners, spar, ribs and aluminum skin. Individual
parts are assembled by riveting. The fin tip (4) is made of fiberglass. On the spar are two
rudder hinges, lower one (3) and upper one (2).
1 Fin
2 Rudder upper hinge
3 Rudder lower hinge
4 Fin tip
5 Pin - front stabilizer hinge
6 Rear stabilizer hinge
Fig. 5-3: Fin
Date of issue: 2013-06-30
Revision No.: 5-5
PS-28 Cruiser
SC-AMM-1-0-00
SportCruiser
5.2.4
CHAPTER 5 – TAIL UNIT
Rudder
The rudder (1, Fig. 5-4) is of aluminum structure and consists of spar, ribs and aluminum skin.
Individual parts are assembled by riveting. On the spar are two attachments lower one (3) and
upper one (2) for the rudder suspension on the fin. Control lever (4) is riveted on root rib. On
the trailing edge is riveted fixed trim tab (6) – only newer SportCruiser airplanes.
1
2
3
4
5
6
Rudder
Upper hinge
Lower hinge
Control lever
Rudder tip
Fixed trim tab
Fig. 5-4: Rudder
Revision No.: -
Date of issue: 2013-06-30
5-6
SC-AMM-1-0-00
PiperSport
CHAPTER 5 – TAIL UNIT
5.3
Removal / Installation
5.3.1
Horizontal stabilizer removal
SportCruiser
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
-
cutting pliers
NOTE:
For stabilizer removal three persons are requested.
(a) Remove the bolts (6, Fig. 5-5) from top side of the stabilizer fairing (5).
(b) Unscrew the bolts (4) and remove fiberglass cover (3).
(c) Disconnect the trim tab actuator connector located between the stabilizer and fuselage.
(d) Unscrew the nut (19, Fig. 5-5), remove washer (20), bolt (18) and disconnect elevator
control rod (17).
(e) Unscrew the nuts (11), remove washers (12), and bolts (10).
(f) Hold the full deflection of the rudder.
(g) Carefully pull out the stabilizer (1) in horizontal direction of the attachments and store it in
such a way that a damage cannot occur.
5.3.2
Horizontal stabilizer installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
-
pliers
NOTE:
For stabilizer installation three persons are requested.
(a) Clean all attachments and apply lubricant grease on it.
(b) Hold the full deflection of the rudder.
(c) Put the horizontal stabilizer (1, Fig. 5-5) from behind to the fuselage so that it slides on two
pins (7); slip stabilizer up to stop.
(d) Insert bolts (10) into rear hinges (8; 9), slip washers (12), screw and tighten nuts (11).
(e) Connect the trim tab actuator connector, and secure it with cable tie.
(f) By means of the bolt (18), washers (20), and nut (19) connect elevator control rod (17)
and tighten nut.
(g) Install rear cover (3). The lower bolt (4) screw at first.
(h) Screw the bolts (6) on top side stabilizer fairings (5).
Date of issue: 2013-06-30
Revision No.: 5-7
PS-28 Cruiser
SC-AMM-1-0-00
SportCruiser
CHAPTER 5 – TAIL UNIT
(i) Perform check the trim tab operation and elevator deflections (see 6.4.3), possibly
adjusting of elevator deflections (see 6.4.4).
Fig. 5-5: Stabilizer, elevator removal / installation (page 1 of 2)
Revision No.: -
Date of issue: 2013-06-30
5-8
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 5 – TAIL UNIT
1 Stabilizer
2 Elevator
3 Rear cover
4 Bolt
5 Stabilizer fairing
6 Bolt
7 Pin - front stabilizer hinge
8 Rear stabilizer hinge
9 Rear hinge
10 Bolt
11 Nut
12 Washer
13 Bolt
14
15
16
17
18
19
20
21
22
23
24
25
26
Nut
Washer
Bolt
Elevator control rod
Bolt
Nut
Washer
Cover
Balance tab control rod
Balance tab rod hinge
Pin
Washer
Cotter pin
Fig. 5-5: Stabilizer, elevator removal / installation (page 2 of 2)
5.3.3
Elevator removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
cutting pliers
NOTE:
For elevator removal two persons are requested.
(a) Remove the cover (21, Fig. 5-5) from the bottom elevator surface (see 6.3.6).
(b) Disconnect the trim tab actuator connector (see Fig 6-8).
(c) Unscrew the bolts (4, Fig. 5-5) and remove fiberglass cover (3).
(d) Unscrew the nut (19), remove washer (20), bolt (18) and disconnect elevator control rod
(17).
(e) Only if balance tab installed, remove the cotter pin (26), washers (25), pin (24) and
disconnect the rod (22) from the hinge (23).
(f) Unscrew the nuts (14), remove washers (15), and bolts (13; 16) from all three hinges.
(g) Carefully remove the elevator (2) from the stabilizer (1) and store it in such a way that a
damage cannot occur.
5.3.4
Elevator installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P).
Tools needed:
-
wrench size 7/16 in
-
pliers
Date of issue: 2013-06-30
Revision No.: 5-9
SC-AMM-1-0-00
PS-28 Cruiser
SportCruiser
NOTE:
CHAPTER 5 – TAIL UNIT
For elevator installation two persons are requested.
(a) Inspect the hinges on the elevator, clean them and apply lubricant on them (see 2.6). Do
the same for the hinges on the stabilizer.
(b) Put the elevator (2, Fig. 5-5) in all three hinges on the stabilizer (1).
(c) Insert the trim tab actuator wires going from the stabilizer to the elevator.
(d) Insert bolts (13; 16) into all three hinges, slip washers (15), screw and tighten nuts (14).
(e) Only if balance tab installed, fit the rod (22) to the hinge (23), insert pin (24) with washer
(25) into the hole, insert the washer (25) and secure with the new cotter pin (26).
(f) By means of the bolt (18), washers (20), and nut (19) connect elevator control rod (17)
and tighten nut.
(g) Install rear cover (3). The lower bolt (4) screw at first.
(h) Connect the trim tab actuator wires (see Fig.6-8).
(i) Install the cover (21, Fig. 5-5) on the bottom elevator surface (see 6.3.7).
(j) Perform check the trim tab operation and elevator deflections (see 6.4.3), possibly
adjusting of elevator deflections (see 6.4.4).
5.3.5
Trim tab removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
pliers, cutting pliers
-
electric drill, drill diam. 3.2 mm (1/8 in)
(a) Remove cotter pin (5, Fig. 5-6), washers (4), pin (3) and disconnect control rod (6) from
the trim tab control lever (2).
(b) Drill out the rivets (8) connecting the piano hinge with elevator.
(c) Remove the trim tab (1) with piano hinge (7) from elevator.
5.3.6
Trim tab installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
pliers, cutting pliers
-
pliers for riveting
(a) Put the trim tab (1, Fig. 5-6) with piano hinge (7) in appropriate position to the elevator.
(b) Rivet the piano hinge into the elevator.
(c) Check for free rotation of the trim tab.
(d) By means of the pin (3), washers (4) connect control rod (6) to the control lever (2); secure
the pin with the new cotter pin (5). At installation follow instructions in 6.3.1.
(e) Perform check (see 6.4.3), possibly adjustment (see 6.4.4) of trim tab deflections.
Revision No.: -
Date of issue: 2013-06-30
5 - 10
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PiperSport
CHAPTER 5 – TAIL UNIT
1
2
3
4
5
6
SportCruiser
Trim tab
Control lever
Pin
Washer
Cotter pin
Control rod
7
8
9
10
11
Piano hinge
Rivet
Balance tab
Control lever
Control rod
Fig. 5-6: Elevator tabs removal / installation
Date of issue: 2013-06-30
Revision No.: 5 - 11
SC-AMM-1-0-00
PS-28 Cruiser
SportCruiser
5.3.7
CHAPTER 5 – TAIL UNIT
Balance tab removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
pliers, cutting pliers
-
electric drill, drill diam. 3.2 mm (1/8 in)
(a) Remove cotter pin (5, Fig. 5-6), washers (4), pin (3) and disconnect control rod (11) from
the tab control lever (10).
(b) Drill out the rivets (8) connecting the piano hinge with elevator.
(c) Remove the balance tab (9) with piano hinge from elevator.
5.3.8
Balance tab installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P).
Tools needed:
-
pliers, cutting pliers
-
pliers for riveting
(a) Put the balance tab (9, Fig. 5-6) with piano hinge in appropriate position to the elevator.
(b) Rivet the piano hinge into the elevator.
(c) Check for free rotation of the tab.
(d) By means of the pin (3), washers (4) connect control rod (11) to the control lever (10);
secure the pin with the new cotter pin (5).
(e) Perform check (see 6.4.3), possibly adjustment (see 6.4.4) of balance tab deflections.
5.3.9
Rudder removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 3/8 in, 7/16 in
NOTE:
For rudder removal on two persons are requested.
(a) Remove the two cotter pins (9, Fig. 5-7), unscrew nuts (7), remove washers (8) and bolts
(6) and disconnect control cables (5) from the control lever on the root rudder rib.
(b) Remove the nuts (3) and washers (4) from the bolts on both hinges of the rudder.
(c) Remove top bolt (2) from the hinge and lift the rudder (1) from lower hinge.
(d) Carefully remove the rudder and store it in such a way that a damage cannot occur.
Revision No.: -
Date of issue: 2013-06-30
5 - 12
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 5 – TAIL UNIT
5.3.10 Rudder installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 3/8 in, 7/16 in
NOTE:
For rudder installation two persons are requested.
(a) Inspect the hinges on the rudder, clean them and apply lubricant on them (see 2.6). Do
the same for the hinges on the fin.
(b) Set the rudder (1, Fig. 5-7) to the hinges on the fin.
(c) Put the bolt (2) on the top hinge, slip washers (4), screw and tighten nuts (3) with the
tightening torque.
(d) By means of the bolts (6), washers (8), and nuts (7) connect rudder cable (5) to the control
lever observing the tightening torques.
(e) Secure the nuts (7) with the new cotter pins (9).
(f) Perform check (see 6.4.3), possibly adjustment (see 6.4.4) of rudder deflections.
Date of issue: 2013-06-30
Revision No.: 5 - 13
SC-AMM-1-0-00
PS-28 Cruiser
SportCruiser
1
2
3
4
5
CHAPTER 5 – TAIL UNIT
Rudder
Bolt
Nut
Washer
Rudder control cable
6
7
8
9
Bolt
Nut
Washer
Cotter pin
Fig. 5-7: Rudder removal / installation
5.4
Check / Adjustment
No procedures included.
5.5
Exchanges / Service information
No procedures included.
Revision No.: -
Date of issue: 2013-06-30
5 - 14
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
SportCruiser
PiperSport
Contents
6.1
General .................................................................................................................. 6-3
6.2
Description and operation ...................................................................................... 6-3
6.3
6.2.1
Lateral control ........................................................................................ 6-3
6.2.2
Longitudinal control ............................................................................... 6-4
6.2.3
Directional control .................................................................................. 6-4
6.2.4
Elevator and aileron trim tab control...................................................... 6-5
6.2.5
Wing flap control .................................................................................... 6-6
6.2.6
Autopilot system .................................................................................... 6-7
Removal / Installation ............................................................................................ 6-8
6.3.1
General principles for work on control system ...................................... 6-8
6.3.2
Control stick removal ............................................................................. 6-8
6.3.3
Control stick installation ......................................................................... 6-9
6.3.4
Flap control actuator removal .............................................................. 6-11
6.3.5
Flap control actuator installation.......................................................... 6-12
6.3.6
Trim tab control actuator removal........................................................ 6-12
6.3.7
Trim tab control actuator installation ................................................... 6-13
6.3.8
Removal of aileron control lever behind the seats .............................. 6-14
6.3.9
Installation of aileron control lever behind the seats .................………6-15
6.3.10
Removal of aileron control bell crank in the wing… ..................………6-16
6.3.11
Installation of aileron control bell crank in the wing… .................. ……6-18
6.3.12
Removal of two-arm levers in the fuselage ......................................... 6-18
6.3.13
6.3.14
6.3.15
6.3.12.1
Removal of front two-arm lever ........................................ 6-18
6.3.12.2
Removal of middle two-arm lever .................................... 6-19
6.3.12.3
Removal of rear two-arm lever ........................................ 6-19
Installation of two-arm levers in the fuselage ...................................... 6-19
6.3.13.1
Installation of front two-arm lever ..................................... 6-19
6.3.13.2
Installation of middle two-arm lever ................................. 6-20
6.3.13.3
Installation of rear two-arm lever ..................................... 6-20
Autopilot servos removal ..................................................................... 6-22
6.3.14.1
Removal of roll servo ....................................................... 6-22
6.3.14.2
Removal of pitch servo .................................................... 6-22
Autopilot servos installation ................................................................. 6-23
6.3.15.1
Installation of roll servo .................................................... 6-24
6.3.15.2
Installation of pitch servo ................................................. 6-24
Date of issue: 2017-06-30
Revision No.: 8
6-1
SportCruiser
PiperSport
6.4
6.5
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
Check / Adjustment.............................................................................................. 6-27
6.4.1
Check of play in control ....................................................................... 6-27
6.4.2
Check for friction in control system ..................................................... 6-28
6.4.3
Checking control surface deflections................................................... 6-29
6.4.4
Adjustment of control surface deflections ........................................... 6-32
6.4.5
Checking condition and tension of foot control cables ........................ 6-33
Exchanges / Service information ......................................................................... 6-33
6.5.1
Rudder control cable exchange........................................................... 6-33
Revision No.: -
Date of issue: 2013-06-30
6-2
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
SportCruiser
PiperSport
6.1 General
SportCruiser / PiperSport airplane is equipped with dual controls which enables pilot training.
Airplane control includes:
•
lateral control (aileron control)
•
longitudinal control (elevator control)
•
directional control (rudder control)
•
aileron trim tab control
•
elevator trim tab control
•
wing flap control
•
autopilot system
6.2 Description and operation
6.2.1
Lateral control
Ailerons are controlled by control sticks. Movement of control sticks is transferred by two push
rods lead from the control stick to the transmission tube which transmits the movement to two
push rods installed behind bulkhead No. 5 behind the seats. This two push rods lead to the
control levers installed in the fuselage. Deflection from the control lever is transferred by
means of the push rods to the bell crank installed on rear rib No. 7 in outer wing. Bell crank is
connected per push rod with aileron control lever. Push rods have adjustable terminals with
spherical bearings on the ends enabling aileron deflection adjustment. Lateral control stops
are located on control sticks and the transmission tube.
Fig. 6-1: Lateral control scheme
Date of issue: 2013-06-30
Revision No.: 6-3
SC-AMM-1-0-00
SportCruiser
PiperSport
6.2.2
CHAPTER 6 – CONTROL SYSTEM
Longitudinal control
The elevator is controlled by control sticks. Movement of control sticks is transferred by
system of transmission levers and push rods to the elevator. Forward and backward
movement of the control stick is transferred by the push rod lead through the central channel
between seats to the two-arm lever which is located under the baggage floor. Lever deflection
is transferred to the movement of the push rods in the rear part of fuselage to the elevator.
Push rods have adjustable terminals with spherical bearings on the ends enabling elevator
deflection adjustment.
Fig. 6-2: Longitudinal control scheme
6.2.3
Directional control
The rudder control is controlled by means of foot control pedals. Pedal deflections of foot
control are transferred by means of steel cables to the rudder. Steel cables are lead through
middle channel of the fuselage. Cable ends are bent over the pulleys installed on bulkhead
No. 12 and attached to the rudder control lever installed on root rudder rib. Other cable end is
connected with foot control pedals.
Foot control pedals are setting to three positions (back, middle and front) by means of control
lever PEDAL SETTING located on the side wall of fuselage under instrument panel.
Revision No.: -
Date of issue: 2013-06-30
6-4
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CHAPTER 6 – CONTROL SYSTEM
SportCruiser
PiperSport
Fig. 6-3: Directional control scheme
6.2.4
Elevator and aileron trim tab control
The elevator and aileron trim tabs are controlled by the electrical actuators installed in
elevator/right aileron and connected per threaded rod with trim tab. Control switches are
integrated part of grips. Trim tabs position is displayed either on the two separate indicators or
on the EFIS.
Fig. 6-4: Trim tabs control scheme
Date of issue: 2013-06-30
Revision No.: 6-5
SportCruiser
PiperSport
6.2.5
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
Wing flap control
Wing flaps are controlled by electric flaps actuator connected with flaps per torque tube with
control pins on each end. The flaps actuator located in fuselage under floor of baggage space
and is controlled by a rocker switch located in cockpit. A LED position indicator is installed
together with the rocker switch (with positions FLAPS DOWN, FLAPS UP) on the middle
channel under instrument panel. It is possible to set the wing flaps to whatever position from
0° to 30°.
Fig. 6-5: Wing flap control scheme
Note: The picture of the instrument panel is for information only and could differ from the real
state.
Revision No.: 8
Date of issue: 2017-06-30
6-6
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
6.2.6
SportCruiser
PiperSport
Autopilot system
The EFIS D100 autopilot system is a digital flight control system that provides roll and pitch
control. The system has the following components:
- EFIS D100
- AP74 autopilot interface module
- HS34 HSI expansion module
- SV32 roll servo
- SV32 pitch servo.
The autopilot system is controlled via the AP74 autopilot interface module.
Fig. 6-6: Autopilot control scheme
Note: The picture of the instrument panel is for information only and could differ from the real
state.
The roll and pitch servo are located behind the left seat. They are mounted on mounting plates
which are made from sheet aluminum. Movement of each servo is transmitted to the
appropriate control lever through a rod. The AUTOPILOT DISCONNNECT button serves for
quickly turn off the autopilot and is installed on the left instrument panel.
NOTE:
For details about operation and the indications concerning autopilot functions
refer to EFIS D100 Pilot's User Guide, P/N 100447-000, latest revision.
Date of issue: 2017-06-30
Revision No.: 8
6-7
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
6.3 Removal / Installation
6.3.1
General principles for work on control system
Push rod assembly
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
Set the push rods to the prescribed length before assembling, tighten the nuts slightly, and do
not secure them for the time being. It is necessary to keep the following principles:
(a) Terminal thread must overlap the inspection hole in the push rod
(b) Terminals of all push rods must be uniformly screwed for setting the neutral position that
serve for adjustment of control.
Grease bearings with lubricant grease before installing the push rods into airplane unless
otherwise stated by the bearing manufacturer. Do not grease nor rinse the bearings with
permanent filing that are covered by metal or plastic covers. Do not rinse bearings and
articulated joints with technical gasoline. Mechanically remove contaminated lubricant grease
carefully and refill the clean one.
Orientation of bolts and cotter pins
Put the bolts to the joint on the basis of “top-down” rule or “From the front to the back" with
regard to the flight direction. This rule decreases possibility of spontaneous bolt falling out of
the clamp joint in case that nut unlocking and falling out occurs in the course of operation.
Follow the same rule also in case of securing nuts by securing pins or by cotter pins, with the
exception of those cases when it is not possible to install the bolt for design or operation
limitation reasons.
Lubrication
At assembling parts grease al joints and friction surfaces (bolts, pins, and threads) after
mechanical or chemical cleaning by lubricant grease.
6.3.2
Control stick removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in, 3/8 in
-
cutting pliers
(a) Unscrew the nut (6, Fig. 6-7), remove the washers (7), bolt (5) and disconnect the elevator
control rod (26) and fork on the transmission tube (1).
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 6 – CONTROL SYSTEM
SportCruiser
PiperSport
(b) Unscrew the nuts (17), remove the washers (18) and disconnect the aileron control rods
(4) from sticks (2); remove the cases (19).
(c) Remove the grips (3) and disconnect wires (24) for trim tab switches and PTT on the
grips.
(d) Remove the cotter pins (16), unscrew the nuts (13), remove the washers (14), bolts (12)
and washers (15).
(e) Carefully remove the control sticks assembly from the cockpit.
(f) Remove the cotter pin (23), unscrew the nut (21), remove the washers (22) and bolt (20);
turn the stick (2) 90 degree and remove it from the transmission tube (1).
6.3.3
Control stick installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in, 3/8 in
-
pliers
(a) Put the stick (2, Fig. 6-7) in the transmission tube (1).
(b) Turn the stick (2) 90 degree and insert the bolt (20) with the washer (22) into the
transmission tube (1) and stick (2), insert the washers (22), screw and carefully tighten the
nut (21).
(c) Secure the nut (21) with the new cotter pin (23).
(d) Put the control stick assembly with the washers (17) between the brackets (25).
(e) Insert the bolts (12) into the holes, insert the washers (14), screw and carefully tighten the
nuts (13).
(f) Secure the nuts (13) with the new cotter pin (16).
(g) Connect the wires (24) for trim tab switches and PTT on the grips (3); install grips (see
Wiring Manual or Chapter 16).
(h) On the control sticks screw insert the cases (19), aileron rods (4), and washers (18),
screw and tighten the nuts (17).
(i) Put the control rod (26) to the fork on the transmission tube (1), insert the bolt (5) with
washer (7) into the hole, insert the washer (7), screw and carefully tighten the nut (6).
(j) Check aileron and elevator deflections (see 6.4.3) and check plays in control (see 6.4.1).
Date of issue: 2013-06-30
Revision No.: 6-9
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
1 Transmission tube
2 Control stick
3 Grip
4 Aileron control rod
5 Bolt
6 Nut
7 Washer
8 Nut
9 Washer
10 Case
11 Lever
12 Bolt
13 Nut
14
15
16
17
18
19
20
21
22
23
24
25
26
Washer
Nylon washer
Cotter pin
Nut
Washer
Case
Bolt
Nut
Washer
Cotter pin
Electrical wires
Bracket
Elevator control rod
Fig. 6-7: Control stick removal / installation
Revision No.: -
Date of issue: 2013-06-30
6 - 10
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.4
Flap control actuator removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in, 1/2 in,
-
screwdriver
(a) Set the flap to the landing position; switch off electrical power of the airplane.
(b) Open the cover behind the left seat on the floor of baggage space.
(c) Disconnect flap actuator wire (2, Fig. 6-8).
(c) Remove the cotter pin (9), unscrew the nut (7), remove the washer (8), bolt (6) and
disconnect flap arm (11) from the flap actuator (1).
(d) Unscrew the nut (4), remove the washer (5), bolt (3), and disconnect actuator (1) from the
actuator hinge (10).
(e) Remove the flap actuator (1).
1 Flap actuator
2 Actuator wire
3 Bolt
4 Nut
5 Washer
6 Bolt
7 Nut
8 Washer
9 Cotter pin
For information:
10 Actuator hinge
11 Flap control arm
Fig. 6-8: Flap control actuator removal / installation
Date of issue: 2013-06-30
Revision No.: 6 - 11
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SportCruiser
PiperSport
6.3.5
CHAPTER 6 – CONTROL SYSTEM
Flap control actuator installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in, 1/2 in,
-
screwdriver
(a) Fit the flap actuator (1, Fig. 6-8) to the actuator hinge (10), insert the bolt (3) to the hole,
install the washer (5), screw and tighten the nut (4).
(b) Fit the actuator rod to the flap arm (11), insert the bolt (6) to the hole, install washer (8),
screw and slightly tighten the nut (7).
(c) Secure the nut (7) with the new cotter pin (9).
(d) Connect the actuator wire (2) (see Wiring Manual or Chapter 16).
(e) Check the flap operation and deflections (see 6.4.3).
(c) Install the cover on the floor of baggage space.
6.3.6
Trim tab control actuator removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P).
Tools needed:
-
wrench size No.5
-
screwdriver
-
cutting pliers, pliers
-
electric drill, drill diam. 3.2 mm (1/8 in)
NOTE:
The trim tab control actuator is located in the elevator and the right aileron.
(f) Drill out the rivets (11, Fig. 6-9) and remove the cover (10) from the access hole.
(g) Disconnect the trim tab actuator wires (2).
(h) Remove the cotter pin (9), washers (8), pin (7) and disconnect the actuator rod (5) from
the trim tab control lever (12).
(i) Unscrew the nuts (4), remove washers (5) and carefully remove the actuator (1) from the
elevator or aileron through access hole.
(j) As requirement, remove the cotter pin (9), wasters (8), pin (7) and disconnect the actuator
rod (5) from the actuator (1).
Revision No.: -
Date of issue: 2013-06-30
6 - 12
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CHAPTER 6 – CONTROL SYSTEM
6.3.7
SportCruiser
PiperSport
Trim tab control actuator installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.5
-
screwdriver
-
pliers
-
pliers for riveting
(a) Fit the rod (6, Fig. 6-9) to the actuator rod, insert pin (7) with washer (8) into the hole,
insert the washer (5) and secure with the new cotter pin (9).
(b) Insert the trim tab actuator (1) into the elevator or aileron through access hole and fit in
place.
(c) Insert the screws (3) into the holes, insert the washers (5), screw and carefully tighten the
nuts (4).
(d) Fit the rod (6) to the control lever (12), insert pin (7) with washer (8) into the hole, insert
the washer (5) and secure with the new cotter pin (9).
(e) Connect the actuator wires (3) (see Wiring Manual).
(f) Check correct trim tab operation and adjustment of trim tab deflections (see 6.4.4).
(g) Fit the cover (10) to the access hole and rivet it.
(h) Check trim tab deflections (see 6.4.3) and check plays in control (see 6.4.1).
Date of issue: 2013-06-30
Revision No.: 6 - 13
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
NOTE
Figure shows the elevator
trim tab control actuator.
1
2
3
4
5
6
Trim tab control actuator
Actuator wires
Screw
Nut
Washer
Actuator rod
7
8
9
10
11
12
Pin (2 pcs.)
Washer (2 pcs.)
Cotter pin (2 pcs.)
Cover
Rivet (9 pcs.)
Trim tab control lever
Fig. 6-9: Trim tab control actuator removal / installation
6.3.8
Removal of aileron control lever behind the seats
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
(a) Tilt the seat backs.
(b) Unscrew the nuts (3; 6, Fig. 6-10), remove washers (4; 7) and bolts (2; 5) and disconnect
rods (13; 14) from the control lever (1).
(c) Remove the cotter pin (12), unscrew the nut (9), remove washer (10), and bolt (8).
(d) Remove the control lever (1) and washers (11) from the bracket (15).
Revision No.: -
Date of issue: 2013-06-30
6 - 14
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.9
Installation of aileron control lever behind the seats
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
(a) Check condition of the control lever and lubrication of the friction surfaces. If the friction
surfaces are contaminated, then carefully remove contamination and grease them with
lubricant (see 2.6).
(b) Fit the control lever (1, Fig. 6-10) with the nylon washers (11) to the bracket (15), insert
the bolt (8) to the hole, install washer (10), screw and slightly tighten the nut (9).
(c) Secure the nut (9) with the new cotter pin (12).
NOTE:
The control lever must not show axial play after installing and its travel must
be continuous without dragging.
(d) Fit the rods (13; 14) to the control lever (1), insert the bolts (2; 5) with the first washers (4;
7) to the holes, install the second washers (4; 7), screw and tighten the nuts (3; 6).
(e) Tilt the seat backs to backwards.
(f) Check aileron deflections (see 6.4.3) and check plays in control (see 6.4.1).
Date of issue: 2013-06-30
Revision No.: 6 - 15
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SportCruiser
PiperSport
1
2
3
4
5
6
7
8
CHAPTER 6 – CONTROL SYSTEM
Two-arm lever
Bolt
Nut
Washer
Bolt
Nut
Washer
Bolt
9 Nut
10 Washer
11 Nylon washer
12 Cotter pin
13 Control rod I
14 Control rod II
For information:
15 Bracket
Fig. 6-10: Aileron control lever behind the seats removal / installation
6.3.10 Removal of aileron control bell crank in the wing
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
Revision No.: -
Date of issue: 2013-06-30
6 - 16
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
NOTE:
The bell cranks located on the bracket in the position of the rear rib No. 7
between the spars. Removal is identical for the left and the right aileron bell
crank.
(a) Unscrew the screws (13, Fig. 6-11) and remove the cover (12).
(b) Unscrew the nuts (8), remove the washers (4), bolts (7), and disconnect the rods (9; 10)
from the bell crank (1).
(c) Remove the cotter pin (6), unscrew the nut (3), remove the washers (4; 5), bolt (2), and
the bell crank (1).
NOTE
Figure shows the left aileron
bell crank.
1
2
3
4
5
6
7
Aileron bell crank
Bolt
Nut
Washer
Nylon washer
Cotter pin
Bolt
8
9
10
11
12
13
Nut
Control rod I
Control rod II
Bracket
Cover
Screw
Fig. 6-11: Aileron bell crank removal / installation
Date of issue: 2013-06-30
Revision No.: 6 - 17
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.11 Installation of aileron control bell crank in the wing
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
NOTE:
Installation is identical for the left and the right aileron bell crank.
(a) Check condition and lubrication of bell crank bearings. If the bearings are contaminated,
then carefully eliminate the contamination and grease them with lubricant (see 2.6).
(b) Fit the bell crank (1, Fig. 6-11) with the nylon washers (5) to the bracket (11), insert the
bolt (8) with the first washer (4) to the hole, install the second washer (4), screw and
slightly tighten the nut (3).
(c) Secure the nut (3) with the new cotter pin (6).
NOTE:
The bell crank must not show axial play after installing and its travel must be
continuous without dragging.
(d) Fit the rods (9; 10) to the bell crank, insert the bolts (7) to the holes, install the washers
(4), screw and tighten the nuts (8).
(e) Check aileron deflections (see 6.4.3) and check plays in control (see 6.4.1).
6.3.12 Removal of two-arm levers in the fuselage
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
-
pliers
6.3.12.1 Removal of front two-arm lever
(a) Remove the cover on the floor of baggage compartment.
(b) Unscrew the nuts (5, Fig. 6-12), remove washers (6) and bolts (4) and disconnect rods
(12; 13) from the control lever (1).
(c) Remove the cotter pin (11), unscrew the nut (8), remove washer (9), and bolt (7).
(d) Remove the control lever (1) and washers (10) from the bracket (16).
Revision No.: -
Date of issue: 2013-06-30
6 - 18
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.12.2 Removal of middle two-arm lever
(a) Remove the front cover (between bulkheads No. 8 and 9) at the bottom of the fuselage
rear part.
(b) Unscrew the nuts (5, Fig. 6-12), remove washers (6) and bolts (4) and disconnect rods
(13; 14) from the control lever (2).
(c) Remove the cotter pin (11), unscrew the nut (8), remove washer (9), and bolt (7).
(d) Remove the control lever (2) and washers (10) from the bracket (17).
6.3.12.3 Removal of rear two-arm lever
(a) Remove the rear cover (between bulkheads No. 10 and 11) at the bottom of the fuselage
rear part.
(b) Unscrew the nuts (5, Fig. 6-12), remove washers (6) and bolts (4) and disconnect rods
(14; 15) from the control lever (3).
(c) Remove the cotter pin (11), unscrew the nut (8), remove washer (9), and bolt (7).
(d) Remove the control lever (3) and washers (10) from the bracket (18).
6.3.13 Installation of two-arm levers in the fuselage
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
-
pliers
6.3.13.1 Installation of front two-arm lever
(a) Check condition of the control lever and lubrication of the friction surfaces. If the friction
surfaces are contaminated, then carefully remove contamination and grease them with
lubricant (see 2.6).
(b) Fit the control lever (1, Fig. 6-12) with the nylon washers (10) to the bracket (16), insert the
bolt (7) to the hole, install washer (9), screw and slightly tighten the nut (8).
(c) Secure the nut (8) with the new cotter pin (11).
NOTE:
The lever after installing must not show axial play and its travel must be
smooth without dragging.
(d) Fit the rods (12; 13) to the control lever (1), insert the bolts (4) with the first washers (6) to
the holes, install the second washers (6), screw and tighten the nuts (5).
(e) Check elevator deflections (see 6.4.3) and check plays in control (see 6.4.1).
Date of issue: 2013-06-30
Revision No.: 6 - 19
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.13.2 Installation of middle two-arm lever
(a) Check condition of the control lever and lubrication of the friction surfaces. If the friction
surfaces are contaminated, then carefully remove contamination and grease them with
lubricant (see 2.6).
(b) Fit the control lever (2, Fig. 6-12) with the nylon washers (10) to the bracket (17), insert the
bolt (7) to the hole, install washer (9), screw and slightly tighten the nut (8).
(c) Secure the nut (8) with the new cotter pin (11).
NOTE:
The lever after installing must not show axial play and its travel must be
smooth without dragging.
(d) Fit the rods (13; 14) to the control lever (2), insert the bolts (4) with the first washers (6) to
the holes, install the second washers (6), screw and tighten the nuts (5).
(e) Check elevator deflections (see 6.4.3) and check plays in control (see 6.4.1).
6.3.13.3 Installation of rear two-arm lever
(a) Check condition of the control lever and lubrication of the friction surfaces. If the friction
surfaces are contaminated, then carefully remove contamination and grease them with
lubricant (see 2.6).
(b) Fit the control lever (3, Fig. 6-12) with the nylon washers (10) to the bracket (18), insert the
bolt (7) to the hole, install washer (9), screw and slightly tighten the nut (8).
(c) Secure the nut (8) with the new cotter pin (11).
NOTE:
The lever after installing must not show axial play and its travel must be
smooth without dragging.
(d) Fit the rods (14; 15) to the control lever (3), insert the bolts (4) with the first washers (6) to
the holes, install the second washers (6), screw and tighten the nuts (5).
(e) Check elevator deflections (see 6.4.3) and check plays in control (see 6.4.1).
Revision No.: -
Date of issue: 2013-06-30
6 - 20
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PiperSport
CHAPTER 6 – CONTROL SYSTEM
1 Front two-arm lever
2 Middle two-arm lever
3 Rear two-arm lever
4 Bolt
5 Nut
6 Washer
7 Bolt
8 Nut
9 Washer
10 Nylon washer
SportCruiser
11 Cotter pin
12 Front control rod I
13 Front control rod II
14 Middle control rod
15 Rear control rod
For information:
16 Front bracket
17 Middle bracket
18 Rear bracket
Fig. 6-12: Two-arm levers removal / installation
Date of issue: 2013-06-30
Revision No.: 6 - 21
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.14 Autopilot servos removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
-
pliers
-
drill diam. 3.2 mm (1/8 in)
-
electric drill
NOTE:
From S/N P1102001 is aircraft equipped with a modified installation of the
roll servo. In case of exchange, replace the old installation of the roll servo
with the modified installation. Detail information are shown in the IPC, Doc.
No. CR-IPC-1-0-00, Chapter 22.
6.3.14.1 Removal of roll servo
(a) Set the MASTER BAT or MASTER, AUTOPIL switches, EFIS and ROLL SERVO or AP
and AP SERVO 1 circuit breakers to OFF.
(b) Remove the left seat (see Chapter 7).
(c) Disconnect the servo wires (2, Fig. 6-13).
(d) Unscrew the nut (15, Fig. 6-14), remove the washer (16) and the bolt (14) and disconnect
rod (13) from the servo control lever.
(e) Carefully drill out the bracket (3, Fig. 6-13); remove the bracket with the servo (1).
(f) Unscrew and remove the bolts (7) with the washers (8); remove the stop (9).
(g) Remove the lockwire, unscrew and remove the bolts (4) with the washers (5; 6); remove
the servo (1) from the bracket (3).
6.3.14.2 Removal of pitch servo
(a) Set the MASTER BAT or MASTER, AUTOPIL switches, EFIS and PITCH SERVO or AP
and AP SERVO 2 circuit breakers to OFF.
(b) Remove the left seat (see Chapter 7).
(c) Disconnect the servo wires (24, Fig. 6-15).
(d) Unscrew the nut (18), remove the washers (19) and the bolt (17) and disconnect rod (12)
from the servo control lever.
(e) Unscrew the nuts (22), remove the washers (5) ; remove the servo base (3) with the servo
(1) from the bracket (21).
(f) Unscrew the nuts (22), remove the washers (23 and the bolts (21) and remove the bracket
(20) with the servo (1) from the angles (26).
(g) Unscrew and remove the bolts (6) with the washers (7); remove the stop (2).
(h) Remove the lockwire, unscrew and remove the bolts (3) with the washers (4; 5); remove
the servo (1) from the bracket (20).
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 6 – CONTROL SYSTEM
1
2
3
4
5
6
7
8
9
SportCruiser
PiperSport
Roll servo
Servo wires
Bracket
Bolt (4 pcs)
Washer (3 pcs)
Washer
Bolt (2 pcs)
Washer (2 pcs)
Stop
(i) Fig. 6-13: Roll servo removal
6.3.15 Autopilot servos installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 7/16 in
-
screwdriver
-
pliers
Date of issue: 2013-06-30
Revision No.: 6 - 23
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.3.15.1 Installation of roll servo
(a) Rivet the new bracket (3, Fig. 6-14) on the rear seat stiffener angle and lower fuselage
skin.
(b) Insert the servo (1) to the servo base (9), insert the bolts (4) with the washers (5; 6) to the
holes and tighten the bolts; secure the bolts (4) with the lockwire.
NOTE:
Make sure correct location of the washers (5; 6) - see Fig. 6-14.
(c) Fit the stop (2) to the servo base (3) and fasten it by the bolts (9) with the washers (10).
(d) Fit the servo base (3) with the servo (1) to the bracket (21); insert the bolts (4) with the
washers (5) into the holes, screw and tighten the bolts (4).
(e) Fit the rod (11) to the servo control lever, insert the bolt (12) to the holes, install the
washer (14), screw and tighten the nut (13).
(f) Connect the servo wires (20) (see Wiring Manual).
(g) Install the left seat (see Chapter 7).
(h) Set the MASTER BAT or MASTER, AUTOPIL switches, EFIS and ROLL SERVO or AP
and AP SERVO 1 circuit breakers to ON.
(i) Do a test of the autopilot system - if no error message appears, then the system is
operative.
6.3.15.2 Installation of pitch servo
(a) Insert the servo (1, Fig. 6-15) to the bracket (20), insert the bolts (3) with the washers (4;
5) to the holes and tighten the bolts; secure the bolts (3) with the lockwire.
NOTE:
Make sure correct location of the washers (4; 5) - see Fig. 6-15.
(b) Fit the stop (2) to the servo base (3) and fasten it by the bolts (6) with the washers (7).
(c) Fit the bracket (20) with the servo (1) to the angles (26); insert the bolts (21) into the holes,
install the washers (23), screw and tighten the nuts (22).
(d) Fit the rod (12) to the servo control lever, insert the bolt (17) with the first washer (19) to
the holes, install the second washer (19), screw and tighten the nut (18).
(e) Connect the servo wires (24) (see Wiring Manual).
(f) Install the left seat (see Chapter 7).
(g) Set the MASTER BAT or MASTER, AUTOPIL switches, EFIS and PITCH SERVO or AP
and AP SERVO 2 circuit breakers to ON.
(h) Do a test of the autopilot system - if no error message appears, then the system is
operative.
Revision No.: -
Date of issue: 2013-06-30
6 - 24
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PiperSport
CHAPTER 6 – CONTROL SYSTEM
1 Roll servo
2 Servo wires
3 Bracket
4 Bolt (4 pcs)
5 Washer (3 pcs)
6 Washer
7 Bolt (2 pcs)
8 Washer (2 pcs)
9 Stop
10 Servo base
11 Bolt (4 pcs)
12 Washer (4 pcs)
SportCruiser
13 Rod
14 Bolt
15 Nut
16 Washer
17 Bolt
18 Nut
19 Washer
20 Bushing
21 Bushing
For information:
22 Control lever
Fig. 6-14: Roll servo installation
Date of issue: 2013-06-30
Revision No.: 6 - 25
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
NOTE
The nuts (22) and the washers (23)
are on the fuselage bottom side.
1 Pitch servo
2 Stop
3 Bolt (4 pcs)
4 Washer (3 pcs)
5 Washer
6 Bolt (2 pcs)
7 Washer (2 pcs)
8 Lever
9 Bolt (2 pcs)
10 Nut (2 pcs)
11 Washer (2 pcs)
12 Rod
13 Bolt
14 Bushing
15 Nut
16 Washer
17 Bolt
18 Nut
19 Washer
20 Bracket
21 Bolt (4 pcs)
22 Nut (4 pcs)
23 Washer (4 pcs)
24 Servo wires
For information:
25 Front two-arm lever
26 Angle
Fig. 6-15: Pitch servo removal / installation
Revision No.: -
Date of issue: 2013-06-30
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
6.4 Check / Adjustment
6.4.1
Check of play in control
Admissible plays in control are mentioned in the following table:
Control
Admissible play
Area to measure play
longitudinal
max 4 mm (5/32 in)
at the end of the control stick in longitudinal axis of the airplane
lateral
max 4 mm (5/32 in)
at the end of the control stick in lateral axis of the airplane
directional
max 4.8 mm (3/16 in) on pedals in longitudinal axis of the airplane
trim tabs
max 3.2 mm (1/8 in) at the end of the trim tab
wing flaps
max 3.2 mm (1/8 in) at the end of the wing flap
CAUTION:
IF THE MEASURED PLAYS EXCEED VALUES MENTIONED IN THE
TABLE THEN ELIMINATE THE CAUSE OF IT AND REPEAT MEASURING.
Measuring procedure
(a) Measure all plays three times and write down average values.
(b) Perform measuring with the blocked control surfaces. Before measuring it is necessary to
push down the control surface by hand several times (max force of 5 kg (11 lbs) in the
direction of the control surface deflection, so that the control system is unblocked and
plays can be more easily identified.
(c) Push on the control stick or the pedal by force of 3 kg (6.6 lbs). Deflect the controlling
element to one side and read the deflection. Then push the control stick to the other side
and read the deflection. Sum of deflections presents plays in control.
Longitudinal control
Measure play at the end of the control stick at the blocked elevator in the neutral position. The
total play must not exceed 4 mm (5/32 in) at the end of the control stick (see Fig. 6-16).
Fig. 6-16: Play in longitudinal control
Date of issue: 2013-06-30
Revision No.: 6 - 27
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 6 – CONTROL SYSTEM
Lateral control
Measure play at the end of the control stick by the measuring instrument from the fuselage
side at blocked ailerons in the neutral position. First block the right aileron and measure play
on the control stick, then measure play at the blocked left aileron. Total play of the control stick
must not exceed 4 mm (5/32 in) at the end of the control stick.
Play in foot control pedals
Measure play at the end of pedals by the measuring instrument from the inner wall of the
bulkhead No.1 at the blocked rudder at neutral position. Mutual total play between pedals
must not exceed 4.8 mm (3/16 in) on the pedal tube.
Play in trim tab control
Measure play in elevator neutral position. Set the balance tab to position “max on head" and
measure play at the end of the trim tab. Max play of the trim tab measured at the end of the
trailing edge must not exceed 3.2 mm (1/8 in).
Play in wing flap control
Measure play in individual position of wing flaps (0°, 10°, 20° and 30°). Set the flap actuator to
individual positions. Measure play in wing flap control on the wing flap trailing edge. Max play
of the wing flap measured on the trailing edge must not exceed 4.8 mm (3/16 in).
6.4.2
Check for friction in control system
Control system must function smoothly within the whole scope of deflections. There must not
be excessive friction or hitching in the control system. In case of failure detection, find out the
cause and eliminate the defect.
Friction in the longitudinal control system
(a) Balance elevator through the pulley to get it to neutral position.
(b) Measure force by the dynamometer attached on the end of the control stick. Move the
control stick from fully forward position to neutral and measure force. Then slowly move
stick forward and measure force. Substract forces from each other. Max. force can be
0.9 kg (2 lbs).
Friction in lateral control system
(a) Set ailerons to neutral position.
(b) Measure force at the moment od aileron deflection from neutral position by the
dynamometer attached on the end of the control stick. Max. force can be 0.6 kg (1.3 lbs).
Friction in directional control system
(a) Pushing move the rudder to max. L / R position.
(b) Slowly move the rudder back to neutral position. Maximal permissible residual deflection of
the rudder is on edge of central covering sheet (see Fig. 6-17).
Revision No.: -
Date of issue: 2013-06-30
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SportCruiser
PiperSport
CHAPTER 6 – CONTROL SYSTEM
Fig 6-17: Friction in directional control system
6.4.3
Checking control surface deflections
Control surface deflections of SportCruiser / PiperSport are shown in the following table:
Valid for S/N 06SC001
up to 08SC138 and all
QBK, except of
08SC134
Valid for S/N 08SC134
and from 08SC139
further, except of QBK
Valid for S/N P1102012,
P1102014, P1102015,
P1102016, P1102019,
P1102027, P1102031,
P1102034, C0416 and
up
28° ± 2° up
20° ± 2° up
15° ± 1° up
18° ± 2° down
15° ± 2° down
15° ± 1° down
30° ± 2° right
30° ± 2° right
30° ± 2° right
30° ± 2° left
30° ± 2° left
30° ± 2° left
28° ± 2° up
28° ± 2° up
24° ± 2° up
25° ± 2° down
25° ± 2° down
24° ± 2° down
Wing flap
0° to 30°
0° to 30°
0° to 30° ± 1°
Difference between L/R flap
deflections
± 0.5°
± 0.5°
± 0.5°
22° ± 2° up
22° ± 2° up
22° ± 2° up
22° ± 2° down
28° ± 2° down
28° ± 2° down
Aileron
Rudder
Elevator
Elevator trim tab
Elevator balance tab
Aileron trim tab
-
-
25° ± 2° up
-
19° ± 2° down
20° ± 2° up
20° ± 2° up
20° ± 2° up
20° ± 2° down
20° ± 2° down
20° ± 2° down
Tab. 6-1: Deflections of control surfaces
For measuring deflections use protractor with deflecting pointer that will be attached to an
appropriate control surface by means of the clamp.
Date of issue: 2013-06-30
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CHAPTER 6 – CONTROL SYSTEM
Measuring aileron deflections
(a) Attach the protractor with the deflecting pointer on the upper skin of the aileron by means
of the clamp.
(b) Set the aileron to neutral position.
(c) Set the protractor to 0° - starting value for measuring.
(d) Deflect aileron to the lower (possibly upper) extreme position and read the deflection value.
(e) Check deflection values according to the Tab. 6-1.
Measuring wing flap deflections
(a) Attach the protractor with the deflecting pointer on the upper flap skin by means of the
clamp.
(b) Set the wing flap to the 0°position.
(c) Set the protractor to 0° - starting value of measuring.
(d) Extend the flaps by means of the flap actuator to individual positions and read the
deflection.
(e) Check deflection values according to the Tab. 6-1.
Measuring elevator deflections
(a) Set the protractor with the deflecting pointer on the trailing edge of the elevator by means
of the clamps.
(b) Set the elevator to neutral position.
(c) Set the protractor to 0° - starting value of measuring.
(d) Deflect the elevator to extreme positions by means of the control stick and read the
deflection.
(e) Check values of deflections according to the Tab. 6-1.
Measuring rudder deflections
The airplane manufacturer uses a special jig for measuring rudder deflections that is slid on
the vertical tail unit and it is possible directly to read the rudder deflection. If you do not have
this special jig, use the alternative procedure:
(a) Set the rudder to neutral position.
(b) Put the rod to the trailing edge of the rudder and mark the lower margin of the rudder
trailing edge.
(c) Deflect the rudder to extreme positions and with the rule measure distance from the sign to
the lower margin of the rudder trailing edge.
(d) Calculate angle and compare it with the value mentioned in the Tab. 6-1.
Measuring trim tab deflections (PiperSport / early SportCruiser)
(a) Set the gauge to the trailing edge of the trim tab (see Fig. 6-18).
(b) Set the trim tab to neutral position - 0°.
(c) By means of the trim control actuator deflect the trim tab to extreme positions and read the
deflection.
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CHAPTER 6 – CONTROL SYSTEM
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PiperSport
(e) Check values of deflections according to the Tab. 6-1.
Fig 6-18: Measuring trim tab deflections
Measuring trim tab deflections (SportCruiser)
(a) Set the protractor with the deflecting pointer to the trailing edge of the trim tab by means of
the clamp.
(b) Set the trim tab to neutral position.
(c) Set the protractor to 0° - starting value of measuring.
(d) By means of the trim control actuator deflect the trim tab to extreme positions and read the
deflection.
(e) Check values of deflections according to the Tab. 6-1.
Date of issue: 2013-06-30
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PiperSport
6.4.4
CHAPTER 6 – CONTROL SYSTEM
Adjustment of control surface deflections
Adjustment of control surface deflections to be made to the values showed in the Tab. 6-1. At
adjusting the airplane control, neutral position of the control surfaces is taken as the starting
point.
CAUTION:
AFTER ADJUSTMENT OF CONTROL SURFACE DEFLECTIONS CHECK,
IF THE END PIECES ARE SEEN THROUGH THE INSPECTION HOLE OF
CONTROL RODS.
Adjusting aileron deflections
(a) Aileron deflections up and down (different) are adjusted at the manufacturer.
(b) For re-adjustment of the aileron neutral position:
- Set control sticks to neutral position;
- Through the adjustment of the end piece of the end control rod - set the left aileron
to the neutral position.
- Through the adjustment of the end piece of the end control rod - set the right aileron
to the neutral position.
(c) Adjust the range of deflections (if applicable) through the stops at control sticks.
Adjusting wing flap deflections
Wing flap deflections are given by the torque tube and actuator positioning in the fuselage. It is
not possible to adjust flap deflection outside manufacturing company.
Adjust flap deflections through eccentric parts of pins.
Adjusting elevator deflections
Range of elevator deflections is given by setting the push rod terminals in the fuselage. At
adjusting elevator deflections, proceed as follows:
(a) Remove the chosen push rod from the bell crank.
(b) Adjust the upper deflection as needed by means of the push rod terminal (or by means of
push rod terminal on the elevator lever).
(c) Put push rod end back and check if the deflections corresponds to the values mentioned in
the Tab. 6-1.
Adjusting rudder deflections
Rudder deflections are given by setting the stops on the rudder control lever installed on root
rudder rib.
(a) Set the foot control pedals to neutral position and check if the rudder is in the neutral
position.
(b) Carry out correction of rudder deflection setting by adjusting the turnbuckles on the foot
pedal side in cockpit.
Adjusting trim tab deflections
Trim tab deflections are given by control actuator and they are fixed.
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6.4.5
SportCruiser
PiperSport
Checking condition of rudder control cables.
(a) Carefully inspect the control cable especially on the following areas:
•
in the area of cable attachment on the rudder control pedals
•
in the area of cable attachment on rudder lever
•
in the area of cable inlet on rear fuselage
(b) Check for the following defects on the cable:
•
burst cable wires
•
evidence of sleeves deformation and damage on cable surface
•
evidence of cable corrosion
•
cable distortion
(c) Exchange the cable in cases as follows:
•
broken any wire
•
wear of cable surface resulted in permanent deformation of cable section.
•
it is not possible to set the rudder to neutral position (see 6.4.4)
(d) Check rudder deflections (see 6.4.3).
6.5 Exchanges / Service information
6.5.1
Rudder control cable exchange
(a) Remove the lockwire from the turnbuckle (4; 5; 6, Fig. 6-19).
(b) Cut the control cable (1) in the cockpit behind the rudder pedals.
(c) Remove the cotter pin (15), unscrew the nut (13), remove the washer (14), bolt (12) and
disconnect the cable shackle (11) from the rudder lever (3).
(d) Remove cable on the rudder side from the fuselage.
NOTE:
Grease the new cable with lubricant grease before installing it to the
fuselage.
(e) Insert the new cable (1) from the rudder side into the fuselage.
(f) Set Nicopress sleeve (3) on the cable end in cockpit.
(g) Bend the cable end in cockpit around the cable thimble (2), insert the turnbuckle eye (4)
to the cable thimble (2), set Nicopress sleeve (3) close to the cable thimble and press
Nicopress sleeve by Nicopress pliers (see 15.10).
(h) Connect new cable with turnbuckle (5; 6) installed on rudder pedal (16).
(i) Set the rudder and the pedal and secure them in neutral position.
(j) Set on rear end of cable thimble (2) and cable shackle (11) and connect cable shackle
with rudder lever (17) by means of the bolt (12).
(k) Remove the cable from the rudder lever (17), cut the cable end to fit to the marked length
and by means of Nicopress pliers (see 15.10) install the Nicopress sleeve (3).
(f) Fit the cable shackle (11) to the rudder lever (17), insert the bolt (12) to the hole, install
washer (14), screw and slightly tighten the nut (13).
(l) Secure the nut (13) with the new cotter pin (15).
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CHAPTER 6 – CONTROL SYSTEM
(m) Check (see 6.4.3) and adjust (see 6.4.4) rudder deflections.
(n) Secure the turnbuckle (4; 5; 6) with the lockwire.
1
2
3
4
5
6
7
8
9
Control cable
Cable thimble
Nicopress sleeve
Turnbuckle eye
Turnbuckle barrel
Turnbuckle fork
Bolt
Nut
Washer
10 Cotter pin
11 Cable shackle
12 Bolt
13 Nut
14 Washer
15 Cotter pin
For information:
16 Rudder pedals
17 Rudder lever
Fig 6-17: Rudder control cable exchange
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PiperSport
CHAPTER 7 – EQUIPMENT
Contents
7.1
General .................................................................................................................. 7-3
7.2
Description and operation...................................................................................... 7-3
7.3
7.4
7.2.1
Seats ..................................................................................................... 7-3
7.2.2
Safety harnesses................................................................................... 7-3
7.2.3
Ballistic Recovery System ..................................................................... 7-4
7.2.4
Emergency Locator Transmitter ............................................................ 7-4
Removal / Installation ............................................................................................ 7-5
7.3.1
Seats removal........................................................................................ 7-5
7.3.2
Safety harnesses removal..................................................................... 7-5
7.3.3
Safety harnesses installation................................................................. 7-5
7.3.4
BRS parachute removal ........................................................................ 7-6
7.3.5
BRS parachute installation .................................................................... 7-8
7.3.6
BRS rocket removal............................................................................... 7-8
7.3.7
BRS rocket installation ........................................................................ 7-10
7.3.8
ELT antenna removal .......................................................................... 7-11
7.3.9
ELT antenna installation ...................................................................... 7-11
Check / Adjustment.............................................................................................. 7-13
7.4.1
7.5
Checking of safety harnesses ............................................................. 7-13
Exchanges / Service information ......................................................................... 7-13
7.5.1
Cleaning seat covers and upholstery .................................................. 7-13
7.5.2
ELT main unit / remote unit battery replacement ................................ 7-13
Date of issue: 2013-06-30
Revision No.: 7-1
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 7 – EQUIPMENT
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
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PiperSport
CHAPTER 7 – EQUIPMENT
7.1
General
This is a two-seat cockpit with the side-by-side seat arrangement. The seats are fixed; the
rudder control pedals are adjustable. The seats are equipped with safety harnesses. The
baggage compartment is located behind the seats and is equipped with straps.
The equipment of SportCruiser / PiperSport airplane includes:
•
seats
•
safety harnesses
•
Ballistic Recovery System
•
Emergency Locator Transmitter.
7.2
Description and operation
7.2.1
Seats
Seats (1, Fig. 7-1) of the PS-28 Cruiser / SportCruiser airplane are fixed and are equipped
with upholstered cushions attached on Velcro. The seat backs (2) are attached to the
bulkhead No. 4 per piano hinge.
NOTE
For clearness is not displayed
the instrument panel and the
canopy.
1 Seat
2 Seat back
3 Safety harnesses
Fig. 7-1: SportCruiser / PiperSport cockpit
7.2.2
Safety harnesses
Seats are equipped with safety harnesses (3; 4, Fig. 7-1). Safety harnesses consist of two lap
belts, two shoulder belts and a safety harness lock. Length of the lap belts and the shoulder
belts is adjustable.
Date of issue: 2013-06-30
Revision No.: 7-3
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PiperSport
7.2.3
CHAPTER 7 – EQUIPMENT
Ballistic Recovery System
The aircraft can be equipped (optional) with BRS emergency parachute system.
BRS utilize a manually activated, solid propellant rocket motor to extract a round, nonsteerable parachute and recover the aircraft in life-threatening emergency situations.
The parachute with harnesses and the rocket are installed aft of the firewall. Activating handle
is located on the middle channel.
NOTE:
For detailed information refer to Owner's Manual for BRS-6 Emergency
Parachute Recovery Systems (Doc. No. 020000-03) and Parachute Installation
Manual for the BRS-1350 onto the Czech Sport Aircraft PS-28 Cruiser &
SportCruiser (Doc. No. 020016-PM), latest revision.
1 Parachute
2 Harnesses
3 Rocket
4 Rear attachment cable
5 Handle
Fig. 7-2: BRS scheme
7.2.4
Emergency Locator Transmitter
The aircraft is equipped with the AK-451 ELT Emergency Locator Transmitter.
The AK-451 ELT is micro controller based, batteries operated and self contained equipment.
The ELT is designed only for emergency use. The AK-451 consists of an ELT main unit with a
mounting tray, an aircraft-fixed antenna, remote switch unit, an audible buzzer monitor, and
interconnecting cables (see Fig. 7-6).
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CHAPTER 7 – EQUIPMENT
The ELT main unit is mounted in baggage compartment; some SportCruiser airplanes from
S/N C0416 have ELT main unit mounted below the right instrument panel (see Fig. 7-6). The
remote switch unit with the buzzer is mounted on the right instrument panel; the ELT antenna
is installed on the upper part of the fuselage.
NOTE:
For detailed information refer to Installation and Operation Manual for Model AK451-( ) Series, (Doc. No. IM 451), latest revision.
7.3
Removal / Installation
7.3.1
Seats removal
(a) Remove the seats from the Velcro
(b) Unscrew the seats together with the piano hinge.
(c) Seat back is not removable.
7.3.2
Safety harnesses removal
NOTE:
Removal of safety harnesses is the same for both safety harnesses models.
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in
(a) Unscrew the nut (4, Fig. 7-3), remove the washer (5), bolt (3), the bushing (2) and
disconnect the shoulder belts bracket (1) from the attachment bracket in baggage
compartment.
(b) Remove the bolt (3), the bushing (2), and disconnect the lap belt bracket (1) from the
attachment point on the fuselage / central console side.
7.3.3
Safety harnesses installation
NOTE:
Installation of safety harnesses is the same for both safety harnesses models.
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in
(a) Gradually put the bushing (2, Fig. 7-3), lap belt bracket (1) on the bolt (3); screw the bolt
into the attachment point on the fuselage / central console side.
(b) Put the bushing (2) and shoulder belts bracket (1) on the bolt (3), insert the bolt into the
attachment bracket in baggage compartment, insert the washer (5), screw and tighten the
nut (4).
Date of issue: 2013-06-30
Revision No.: 7-5
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PiperSport
CHAPTER 7 – EQUIPMENT
1 Attachment bracket
2 Bushing
3 Bolt
4 Nut
5 Washer
Fig. 7-3: Safety harnesses removal / installation
7.3.4
BRS parachute removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver, Philips screwdriver
-
wrench size No.7
-
cutting pliers, pliers
-
Allen wrench size 1/8 in, 1/4 in
Revision No.: -
Date of issue: 2013-06-30
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PiperSport
CHAPTER 7 – EQUIPMENT
WARNING: UNAUTHORIZED PERSONNEL SHOULD NOT ATTEMPT TO MODIFY,
REPAIR, OR DISASSEMBLE BRS SYSTEM AT ANY TIME. DURING ALL
SERVICE WORK BEWARE OF ACTIVATING THE BRS ROCKET!
NOTE:
BRS parachute must be removed from the aircraft for repacking. This
service date is printed on placards located on the side of centre panel and
on the parachute.
(a) Carefully unglue the cover over parachute on the canopy fixed frame.
(b) Remove both instrument panels and disconnect all cable and pitot-static connection.
(c) Remove COMM/NAV equipment from the centre panel and disassemble it.
(d) Pull open the front flap of the parachute (1, Fig. 7-4) and expose the small link;
unscrew the link nut and disconnect the rocket lanyards (5).
(e) Carefully remove the BRS rocket (see 7.3.6).
(f) Cut-off cable ties (4) securing link (3) to the tray.
(g) Unscrew the link (3) nut and disconnect the loop of the main brindle (6).
(h) Disengage all four Velcro retaining straps.
(i) Carefully remove parachute (1) from the tray (2).
(j) Repack the parachute by the authorized person.
1 Parachute
2 Tray
3 Link
4 Cable tie
5 Rocket lanyards
6 Main bridle loop
Fig. 7-4: BRS parachute removal / installation
Date of issue: 2013-06-30
Revision No.: 7-7
SC-AMM-1-0-00
SportCruiser
PiperSport
7.3.5
CHAPTER 7 – EQUIPMENT
BRS parachute installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver, Philips screwdriver
-
wrench size No.7
-
cutting pliers, pliers
-
Allen wrench size 1/8 in, 1/4 in
WARNING: UNAUTHORIZED PERSONNEL SHOULD NOT ATTEMPT TO MODIFY,
REPAIR, OR DISASSEMBLE BRS SYSTEMS AT ANY TIME. DURING
ALL SERVICE WORK BEWARE OF ACTIVATING THE BRS ROCKET!
(a) Install the parachute – see Parachute Installation Manual for the BRS-1350 onto the
Czech Sport Aircraft PS-28 Cruiser & SportCruiser (Doc. No. 020016-PM), points 2.8
to 2-17, and 3-5 to 3.11.
(b) Install the BRS rocket (see 7.3.7)
(c) Assemble centre panel and install COMM/NAV equipment.
(d) Connect all cable and pitot-static connection and install both instrument panels.
(e) Glue (by means of the Emfimastic PU 50 sealant) the cover over parachute on the
canopy fixed frame.
(f) Perform pitot-static leak test (see Chapter 12.4.1) and check correct function
appropriate instruments and systems.
7.3.6
BRS rocket removal
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver, Philips screwdriver
-
cutting pliers, pliers
-
Allen wrench size 1/8 in, 1/4 in
WARNING: UNAUTHORIZED PERSONNEL SHOULD NOT ATTEMPT TO MODIFY,
REPAIR, OR DISASSEMBLE BRS SYSTEM AT ANY TIME. DURING ALL
SERVICE WORK BEWARE OF ACTIVATING THE BRS ROCKET!
NOTE:
BRS rocket motor must be replaced by its date of expiry. This service date is
printed on placards located on the side of centre panel and on the rocket.
(a) Carefully unglue the cover over parachute on the canopy fixed frame.
(k) Pull open the front flap of the parachute (16, Fig. 7-5) and expose the small link;
unscrew the link nut and disconnect the rocket lanyards (2).
(b) Cut-off cable ties securing lanyards.
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 7 – EQUIPMENT
WARNING: NEVER POINT ROCKET AT ANYONE. ACCIDENTAL ACTIVATION MAY
CAUSE DEATH OR SERIOUS INJURY!
ASSEMBLY MUST BE DONE IN THIS SEQUENCE. IF DONE INCORRECTLY,
ACCIDENTAL DISCHARGE OF ROCKET MAY OCCUR AND MAY
CAUSE DEATH OR SERIOUS INJURY!
(c) Remove plastic cap (6).
CAUTION:
KEEP ALLEN WRENCH VERTICAL. BE CAREFUL NOT LO "LEVER"
WRENCH AGAINST SIDE, SO AS TO NOT ACCIDENTLY ACTIVATE
ROCKET!
(d) Remove screw (7) with 1/8 Allen wrench.
(e) Unscrew adapter (4) from rocket. Carefully remove housing (3) from rocket by turning
entire housing assembly.
(f) Loose set screws (10).
(g) Carefully remove the BRS rocket.
(h) As necessary, remove right side panel of the middle channel, unscrew the nut (14),
remove the washer (15), bolt (13) and activation housing (3).
9 Bracket
10 Set screw
11 Rocket pedestal
12 Bracket
13 Bolt
14 Nut
15 Washer
For information:
16 Parachute
1
2
3
4
5
6
7
8
BRS rocket
Rocket lanyards
Activation housing
Cone adapter
Steel cable
Plastic cap
Screw
Star washer
Fig. 7-5: BRS rocket removal / installation
Date of issue: 2013-06-30
Revision No.: 7-9
SportCruiser
SC-AMM-1-0-00
PiperSport
7.3.7
CHAPTER 7 – EQUIPMENT
BRS rocket installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver, Philips screwdriver
-
cutting pliers, pliers
-
Allen wrench size 1/8 in, 1/4 in
WARNING: UNAUTHORIZED PERSONNEL SHOULD NOT ATTEMPT TO MODIFY,
REPAIR, OR DISASSEMBLE BRS SYSTEM AT ANY TIME. DURING ALL
SERVICE WORK BEWARE OF ACTIVATING THE BRS ROCKET!
(a) Carefully unglue the cover over parachute on the canopy fixed frame.
(b) As necessary, install the activation housing (3) to the middle channel; fasten handle
by means of the bolt (13), washer (15) and nut (14); install right side panel of the
middle channel.
(c) Route the housing in a gentle arc to the base on the rocket. The housing cable should
have no abrupt bends.
(d) Install the rocket – see Parachute Installation Manual for the BRS-1350 onto the
Czech Sport Aircraft PS-28 Cruiser & SportCruiser (Doc. No. 020016-PM), points 3.1
to 3-11.
(e) Connect the activation housing to the rocket - see Parachute Installation Manual for
the BRS-1350 onto the Czech Sport Aircraft PS-28 Cruiser & SportCruiser (Doc. No.
020016-PM), points 5.1 to 5-7.
(f) Glue (by means of the Emfimastic PU 50 sealant) the cover over parachute on the
canopy fixed frame.
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PiperSport
CHAPTER 7 – EQUIPMENT
7.3.8
ELT antenna installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 3/4 in
(a) Remove the protective cover from the antenna connector.
(b) Insert the antenna (4, Fig. 7-6) to the hole in the fuselage upper part (7).
(c) Insert the washer (6), screw and tighten the nut (5) to between 25 to 30 inch lbs.
(d) Connect the connector (2) to the antenna (4).
(e) Install the circular cover on the aft wall of the baggage compartment.
(f) Do an operational test.
7.3.9
ELT antenna removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 3/4 in
(a) Remove the circular cover on the aft wall of the baggage compartment.
(b) Set the MASTER BAT switch to OFF.
(c) Disconnect the connector (2, Fig. 7-6) from the antenna.
(d) Unscrew the nut (5), remove the washer (6) and the antenna (4).
(e) Install the protective cover on the antenna connector.
Date of issue: 2013-06-30
Revision No.: 7 - 11
SportCruiser
SC-AMM-1-0-00
PiperSport
1
2
3
4
5
CHAPTER 7 – EQUIPMENT
ELT main unit
Cable connector
Mounting tray
ELT antenna
Nut
6 Lockwasher
For information:
7 Fuselage upper part
8 Bulkhead No. 1 beam
Fig. 7-6: ELT antenna removal / installation
Revision No.: -
Date of issue: 2013-06-30
7 - 12
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PiperSport
CHAPTER 7 – EQUIPMENT
7.4 Check / Adjustment
7.4.1
Checking of safety harnesses
Check harnesses surface for any damages. Check the lock system function. Check the
attachment points of shoulder and side harnesses for any damages or corrosion.
7.5 Exchanges / Service information
7.5.1
Cleaning seat covers and upholstery
(a) Take upholstery and covers out of the airplane.
(b) Brush impurities, possibly clean with warm water with addition of a suitable detergent.
(c) Before reinstalling upholstery and seats in the airplane, let it thoroughly dry.
7.5.2
ELT main unit / remote unit battery replacement
NOTE:
The battery pack has a 5 years useful life or batteries must be replaced when the
transmitter has been in use for more than one cumulative hour. This service date
is printed on placards located on ELT main unit.
For battery replacement refer to Installation and Operation Manual for Model AK-451-( )
Series, (Doc. No. IM 451), latest revision.
Date of issue: 2013-06-30
Revision No.: 7 - 13
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 7 – EQUIPMENT
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
7 - 14
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CHAPTER 8 – LANDING GEAR
SportCruiser
PiperSport
Contents
8.1
General .................................................................................................................. 8-3
8.2
Description and operation ...................................................................................... 8-3
8.3
8.4
8.5
8.2.1
Main landing gear .................................................................................. 8-3
8.2.1.1
Main landing gear wheel ....................................................................... 8-4
8.2.2
Nose landing gear ................................................................................. 8-5
8.2.2.1
Nose landing gear wheel ....................................................................... 8-6
8.2.3
Brake system ......................................................................................... 8-7
8.2.3.1
Parking brake ........................................................................................ 8-7
8.2.4
Wheel fairings ........................................................................................ 8-7
Removal / Installation ............................................................................................ 8-8
8.3.1
Removal of main wheel fairing .............................................................. 8-8
8.3.2
Installation of main wheel fairing ........................................................... 8-8
8.3.3
Removal of main landing gear wheel .................................................... 8-9
8.3.4
Installation of main landing gear wheel ............................................... 8-10
8.3.5
Removal of nose wheel fairing ............................................................ 8-10
8.3.6
Installation of nose wheel fairing ......................................................... 8-10
8.3.7
Removal of nose landing gear wheel .................................................. 8-12
8.3.8
Installation of nose landing gear wheel ............................................... 8-13
8.3.9
Removal of the main landing gear leg ................................................. 8-13
8.3.10
Installation of the main landing gear leg .............................................. 8-14
8.3.11
Removal of nose landing gear leg ....................................................... 8-15
8.3.12
Installation of nose landing gear leg .................................................... 8-15
8.3.13
Removal of brake pumps .................................................................... 8-16
8.3.14
Installation of brake pumps ................................................................. 8-17
Check / Adjustment .............................................................................................. 8-18
8.4.1
Check of nose landing gear shock absorber ...................................... 8-18
8.4.2
Check of nose landing gear after shimmy occurrence ........................ 8-18
8.4.3
Check of nose landing gear leg for cracks .......................................... 8-21
Changes / Service information............................................................................. 8-23
8.5.1
Tire change .......................................................................................... 8-23
8.5.2
Change of nose landing gear shock absorber dumping elements ...... 8-24
8.5.3
Change of brake lining ........................................................................ 8-26
8.5.4
Lubrication of axis of rotation of nose landing gear ............................. 8-27
8.5.5
Refilling / exchanging brake fluid ......................................................... 8-28
8.5.6
Bleeding the brake system .................................................................. 8-29
8.5.7
Conditioning procedures ..................................................................... 8-29
Date of issue: 2018-01-22
Revision No.: 11
8-1
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 8 – LANDING GEAR
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
8-2
SC-AMM-1-0-00
PiperSport
CHAPTER 8 – LANDING GEAR
8.1
SportCruiser
General
SportCruiser / PiperSport airplane landing gear is of three-wheel fixed design and consists of
the main landing gear and the nose landing gear. The nose landing gear is freely rotatable.
The main landing gear wheels are equipped with hydraulic disc brakes.
Type and dimension of wheels (manufacturer Matco mfg):
•
Main wheel - MHE51CZ (5 in)
•
Nose wheel - WHLNW51CC.75R (5 in)
•
Tire and tube - Goodyear FLIGHT SPECIAL II – 5.00-5 in (or equivalent aircraft grade).
This chapter provides information on:
•
main landing gear
•
nose landing gear
•
brake system
•
wheel fairings
NOTE:
For detailed information refer to MHE51B, MHE51B.75, .MHE51S,
MHE51CZ & MHE51J5“E – Series External Caliper Wheel and Brake
Technical Service Bulletin (latest edition).
8.2
Description and operation
8.2.1
Main landing gear
The main landing gear consists of the composite landing gear leg (1, Fig. 8-1), wheel axle and
wheel (2) equipped with the disc brake (3). The landing gear legs are inserted in the gear
channel under the seats, where they are attached by two bolts (5) and stirrup (6).
1 Main landing gear leg
2 Wheel
3 Disc brake
4 Wheel fairing
5 Bolt
6 Stirrup
Fig. 8-1: Main landing gear, right
Date of issue: 2013-06-30
Revision No.: 8-3
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 8 – LANDING GEAR
8.2.1.1 Main landing gear wheel
Main landing gear wheel rim (2; 3, Fig. 8-2) is pressed of aluminum. Wheel rim is split in order
to facilitate assembly and disassembly of tire. Both halves are joined by bolts (9). Main landing
gear wheels are equipped with the brake discs (7) which are attached to the inner half of the
wheel rims (3). Wheels are equipped with tires and tubes (6).
1
2
3
4
5
Main landing gear leg
Wheel rim, outer
Wheel rim, inner
Wheel axle
Nut and cotter pin
6 Tire with air tube
7 Brake disc
8 Wheel fairing
9 Bolt
10 Wheel fairing holder
Fig. 8-2: Main landing gear wheel
Revision No.: -
Date of issue: 2013-06-30
8-4
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PiperSport
CHAPTER 8 – LANDING GEAR
8.2.2
SportCruiser
Nose landing gear
The nose landing gear (NLG) of SportCruiser / PiperSport airplane is not steerable and
consists of steel welded landing gear leg (1, Fig. 8-3), aluminum fork (1, Fig. 8-4), shock
absorber (2, Fig. 8-3) and the wheel (9). The landing gear is attached to the brackets (7)
installed on the bulkhead No. 1.
There were several old versions of the NLG used in the past, see Figure 8-3 and the point
8.5.8, Figure 8-20. The new improved and reinforced NLG No. SG0300N has further improved
fatigue characteristics.
The new NLG has enlarged the inner cross section of the tube, modified fork (used stronger Al
alloy and added third reinforcement), modified pin (used stronger steel). All nose landing gear
legs have identical geometry.
NOTE:
1
2
3
4
5
Due to the similarity of the old and new nose landing gear legs and the same
maintenance procedures the original pictures are mostly retained.
Nose landing gear leg
Shock absorber
Guard
Bolt
Front part of the nose wheel fairing
6
7
8
9
Rear part of the nose wheel fairing
Bracket
Opening for tow bar
Wheel
Fig. 8-3: Nose landing gear
Date of issue: 2018-01-22
Revision No.: 11
8-5
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 8 – LANDING GEAR
8.2.2.1 Nose landing gear wheel
The nose landing gear wheel rim (2; 3, Fig. 8-4) is pressed of aluminum. Wheel rim is split in
order to facilitate assembly and disassembly of tire. Both halves are connected by bolts (9).
The wheel is equipped with tire and tube (6). Wheel rims are split in order to facilitate
assembly and disassembly of tires
1
2
3
4
5
6
Wheel fork
Wheel rim, left
Wheel rim, right
Wheel axle
Nut and cotter pin
Tire with air tube
7
8
9
10
11
Wheel fairing bracket
Wheel fairing
Bolt
Spacer
Tow bracket
Fig. 8-4: Nose landing gear wheel
Revision No.: 3
Date of issue: 2014-02-17
8-6
SC-AMM-1-0-00
PiperSport
CHAPTER 8 – LANDING GEAR
8.2.3
SportCruiser
Brake system
SportCruiser / PiperSport airplane is equipped with hydraulic disc brakes on the main landing
gear wheels. Brake system consists of the brake pedals (part of rudder control pedals, see
Fig. 8-9), brake pumps, parking brake valve, hoses for brake fluid supply, brake calipers and
brake pads. By depressing pedals, brake pumps are compressed and pressure generated in
the brake circuit and the calipers pushes the brake pads onto the brake discs. Braking
pressure can be controlled by force of brake pedal depressing.
1
2
3
4
Pilot brake pump, left
Pilot brake pump, right
Copilot brake pump, left
Copilot brake pump, right
5 Disc brake, left
6 Disc brake, right
7 Parking brake valve
Fig. 8-5: Brake system scheme
8.2.3.1 Parking brake
The airplane is equipped with the hydraulic manually controlled parking brake. The PARKING
BRAKE handle is located on the left instrument panel. The handle is mechanically connected
with the stop valve. By depressing the brake pedals and by turning the handle from PUSH
OFF to PULL ON position the brake hoses are locked and the pressure hold brake pads
pressed on brake discs.
8.2.4
Wheel fairings
Airplane is equipped with composite wheel fairings that decrease air drag and improve
aerodynamic properties of the airplane. The wheel fairings are installed on the brackets per
bolts.
Date of issue: 2013-06-30
Revision No.: 8-7
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 8 – LANDING GEAR
8.3
Removal / Installation
8.3.1
Removal of main wheel fairing
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Unscrew the bolts (4, Fig. 8-6) with the washers (5) (if used) attaching the wheel fairing (1)
on the brackets (2; 3).
(b) Remove the fairing (1).
8.3.2
Installation of main wheel fairing
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Set the wheel fairing (1, Fig. 8-6) to appropriate position.
(b) Attach the fairing (1) with bolts (4) and the washers (5) (if used) to the brackets (3).
(c) Attach the fairing (1) with bolts (4) and the washers (5) (if used) to the bracket (2).
1
2
3
4
5
Main wheel fairing
Outer bracket
Inner brackets
Bolt (7 pcs.)
Washer (7 pcs.)
Fig. 8-6: Main wheel fairing removal / installation
Revision No.: -
Date of issue: 2013-06-30
8-8
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CHAPTER 8 – LANDING GEAR
8.3.3
SportCruiser
Removal of main landing gear wheel
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
socket wrench size 1 1/2 in
-
Allen wrench size 3/16 in
-
pliers
The main landing gear wheel assembly consists of the wheel rim, the tube, the tire, the brake
disc and the brake.
(a) Jack and support the airplane (see 14.2).
(b) Disassemble wheel fairing (see 8.3.1).
(c) Remove the lockwire from the bolts (8, Fig. 8-7),
(d) Remove the bolts (8), washers (9) and wheel fairing outer bracket (7).
(e) Unscrew three bolts (4) attaching the wheel rim with brake disc (3).
(f) Remove the cotter pin (6), unscrew the nut (5) and remove washer (10).
(g) Remove the wheel (1) from the wheel axle (2).
1
2
3
4
5
Main landing gear wheel
Wheel axle
Brake disc
Bolt
Nut
6 Cotter pin
7 Outer bracket
8 Bolt
9 Washer
10 Washer
Fig. 8-7: Main landing gear wheel removal / installation
Date of issue: 2013-06-30
Revision No.: 8-9
SportCruiser
SC-AMM-1-0-00
PiperSport
8.3.4
CHAPTER 8 – LANDING GEAR
Installation of main landing gear wheel
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
socket wrench size 1 1/2 in
-
Allen wrench size 3/16 in
-
pliers
(a) Clear the wheel axle (2, Fig. 8-7) of impurities and apply slight layer of grease on it.
(b) Put the wheel (1) on the axle (2).
(c) Apply the securing liquid (blue Loctite 243) on the bolts threads (4) and attach with it the
wheel rim and brake disc (3).
(d) Install the washer (10), screw and tighten the nut (5) on the wheel axle (2) ; tighten the nut
until all play is out ot the assembly Rotate the wheel back and forth while tightening the
nut to help seat the bearings. When all play is out and the wheel rotates freely, tighten to
the next slot and insert the new cotter pin (6).
(e) Attach fairing outer bracket (7) with bolts (8) and washers (9) to the axle (2); secure bolts
with the lockwire.
(f) Install the wheel fairing (see 8.3.2).
8.3.5
Removal of nose wheel fairing
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Unscrew the bolts (3, Fig. 8-8) with the washers (7) (if used) attaching the front (1) and
rear part of the nose wheel fairing (2); remove front part (1).
(b) Unscrew the bolts (4) with the washers (7) (if used) and remove the rear part of the nose
wheel fairing (2).
8.3.6
Installation of nose wheel fairing
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Set the rear part of the nose wheel fairing (2, Fig. 8-8) to appropriate position and attach it
with bolts (4) and the washers (7) (if used) to the brackets (4; 5).
(b) Put the front part of the nose wheel fairing (1) to the rear part of the nose wheel fairing (2)
and attach it with bolts (3) and the washers (7) (if used).
Revision No.: -
Date of issue: 2013-06-30
8 - 10
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PiperSport
CHAPTER 8 – LANDING GEAR
1 Front part of the nose wheel fairing
2 Rear part of the nose wheel fairing
3 Bolt (8 pcs.)
SportCruiser
4 Bolt (10 pcs.)
5 Wheel bracket
6 Tow bracket
Fig. 8-8: Nose wheel fairing removal / installation
Date of issue: 2013-06-30
Revision No.: 8 - 11
SC-AMM-1-0-00
SportCruiser
PiperSport
8.3.7
CHAPTER 8 – LANDING GEAR
Removal of nose landing gear wheel
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1 1/8 in
-
pliers
(a) Jack and support the airplane (see 14.2).
(b) Disassemble wheel fairing (see 8.3.6).
(c) Remove the cotter pin (6, Fig. 8-9) securing nut (4) on wheel axle (2) – on one side only.
(d) Remove the nut (4), washer and tow bracket (8) from wheel axle (2).
(e) Release the wheel axle (2) from the wheel (1), bushings (3) and the wheel fork eyes (8).
1
2
3
4
5
6
7
8
Nose landing gear wheel
Wheel axle
Bushing
Nut
Washer
Cotter pin
Tow bracket
Wheel fork
Fig. 8-9: Nose landing gear wheel removal / installation
Revision No.: -
Date of issue: 2013-06-30
8 - 12
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PiperSport
CHAPTER 8 – LANDING GEAR
8.3.8
Installation of nose landing gear wheel
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1 1/8 in
-
pliers
(a) Clear the wheel axle (2, Fig. 8-9) of impurities and grease it slightly.
(b) From one side shift the axle (2) into the wheel fork eye (8).
(c) Gradually put first bushing (3), nose wheel (1) and second bushing (3) on the wheel axle
(2) and tow bracket (7) according to the figure.
(d) From one side install washer (5), screw nut (3) - set the tow brackets (7) so that the axes
of holes for bolts fastening fairings were horizontally; tighten nut (3).
(e) Check for free turning of the nose wheel (turning must be continual without catching).
(f) Secure the nut (3) with the new cotter pin (6).
(g) Install wheel fairing (see 8.3.6).
8.3.9
Removal of the main landing gear leg
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 9/16 in, 1/2 in
(a) Jack and support the airplane (see 14.2).
(b) Remove appropriate seat (see 7.3.1).
(c) Disconnect the brake line.
(d) Unscrew the nuts (8, Fig. 8-10), and remove the washers (9) and bolts (7).
(e) Unscrew the nuts (4), and remove the washers (5) and tube (3) ); remove the spacer (10)
(if used).
(f) Remove the landing gear leg (1) from the chamber (6) and put it on a suitable place.
Date of issue: 2013-06-30
Revision No.: 8 - 13
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 8 – LANDING GEAR
NOTE
For clearness is not displayed
the channel cover.
1
2
3
4
5
Main landing gear leg
Main gear attachment
Tube
Locknut
Washer
6 Chamber
7 Bolt
8 Locknut
9 Washer
10 Spacer
Fig. 8-10: Main landing gear leg removal / installation
8.3.10 Installation of the main landing gear leg
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 9/16 in, 1/2 in
(a) Check outer surface of the composite landing gear leg (1, Fig. 8-10) for occurrence of
cracks and whether the axle connection is not damaged before installing the landing gear
leg.
(b) Insert the landing gear leg (1) with the spacer (10) (if used) into the chamber (6) in
attachment channel on fuselage and fit the leg in main gear attachment (2).
(c) On the main gear attachment bolts (2) install the tube (3), washers (5), and slightly tighten
the nuts (4).
Revision No.: -
Date of issue: 2013-06-30
8 - 14
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CHAPTER 8 – LANDING GEAR
(d) Insert the bolts (7) through spacer (10) (if used), chamber (6) and leg (1), install the
washers (9) and tighten nuts (8; 4).
(e) Connect the brake lines.
(f) Install seat.
(g) Fill brake system with brake liquid and air-bleed it (see 8.5.4).
8.3.11 Removal of nose landing gear leg
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in, No.17
(a) Jack and support the airplane, (see 14.2).
(b) Remove the lockwire from the bolts (6, Fig. 8-11),
(c) Remove the bolts (6) and washers (7).
(d) Remove the tube (5) from the leg bracket (9).
(e) Remove the cotter pin (9), unscrew the nut (3), remove washers (4), bolt (2) and
disconnect the shock absorber (8) from the bracket on the nose gear leg (1).
(f) Remove the gear leg (1) from the fuselage and put it on a suitable place.(d)
8.3.12 Installation of nose landing gear leg
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in, No.17
(a) Check the welds of the gear leg for occurrence of cracks and corrosion and whether the
bearings are not damaged before installing the gear leg.
(b) Insert the gear leg (1, Fig, 8-11) into the bracket (9).
(c) Insert the tube (5) to the hole in the bracket (9).
(d) Screw the bolts (6) with the nuts (7) to the tube; tighten the bolts slightly; secure bolts with
the lockwire.
(e) Put the lower end of the shock absorber (8) to the bracket on the nose gear leg (1); install
the bolt (2) with the nut (3) and washers (4), secure the nut with the new cotter pin (9).
Date of issue: 2018-01-22
Revision No.: 11
8 - 15
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PiperSport
CHAPTER 8 – LANDING GEAR
1 Nose landing gear leg
2 Bolt
3 Nut
4 Washer
5 Tube
6 Bolt
7 Washer
8 Shock absorber
9 Cotter pin
For information:
10 Bracket
NOTE
Access to the bolts (6) is from the
cockpit.
Fig. 8-11: Nose landing gear leg removal / installation.
8.3.13 Removal of brake pumps
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in, 3/8 in
(a) Disconnect the brake system hose from the brake cylinder on the main landing gear wheel
and let brake fluid drain to a previously prepared can from that system line in which you
want to remove the brake pump.
(b) Disconnect the brake system hose (3, Fig. 8-12) from the brake pump (1; 2).
(c) Remove cotter pin (7), unscrew nut (11), remove washer (12), spacers (9; 10), bolt (8) and
disconnect brake pump rod eye from the rudder pedal (14).
(d) Remove cotter pin (7), unscrew nut (5), remove washer (6), bolt (4) and disconnect brake
pump from the bracket (13) on the floor.
Revision No.: -
Date of issue: 2013-06-30
8 - 16
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PiperSport
CHAPTER 8 – LANDING GEAR
8.3.14 Installation of brake pumps
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in, 3/8 in
(a) Insert the brake pump (1; 2, Fig. 8-12) according to the figure to the floor bracket (14) and
install the bolt (4) with the nut (5) and washer (6); secure the nut by the new cotter pin (7).
(b) Connect brake pump rod end eye with pedal (14) by means of the bolt (8) with the nut
(11), spacers (9; 10) and washer (12); secure the nut by the new cotter pin (7).
(c) Reinstall the brake system hose (3) on the brake pump (1; 2) and on the brake cylinder on
main landing gear.
(d) Fill the brake system with brake fluid and air-bleed it (see 8.5.4.).
1
2
3
4
5
Pilot brake pump
Copilot brake pump
Brake hose
Bolt
Nut
6 Washer
7 Cotter pin
8 Bolt
9 Spacer
10 Spacer
11 Nut
12 Washer
For information:
13 Bracket
14 Rudder pedal
Fig. 8-12: Brake pumps removal / installation
Date of issue: 2013-06-30
Revision No.: 8 - 17
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 8 – LANDING GEAR
8.4 Check / Adjustment
8.4.1
Check of nose landing gear shock absorber
(a) Several times hoist and lower the nose landing gear of the airplane.
(b) Measure value of absorber and nose landing gear compression according to Fig. 8-13.
Perform measuring in vertical direction between the bottom of the engine cowl and the
lower shock absorber attachment. The minimum value is 50 mm (2 in). If this value is
lower than change the dumping elements (see 8.5.2).
Fig. 8-13: Check of nose landing gear shock absorber
8.4.2
Check of nose landing gear after shimmy occurrence
Old version of the nose landing gear:
(a) Remove the nose wheel fairing (see 8.3.5).
(b) Remove the nose wheel (see 8.3.7).
(c) Unload the nose landing gear.
(d) Check condition of the fork, leg, and shock absorber for cracks (see Fig. 8-14). Use
magnifying glass.
(e) Check tire worn and specified inflation:
Air Trac 5.00-5
Sava 5.00-6
Goodyear FLIGHT SPECIAL II – 5.00-5
CAUTION:
(f)
0.8 + 0.2 bar (11.6 + 2.9 psi)
1.0 + 0.2 bar (14.5 + 2.9 psi)
1.2 + 0.1 bar (17.4 + 1.5 psi)
DO NOT EXCESS SPECIFIED TIRE PRESSURE. OVERPRESSURED
TIRE CAUSED SHIMMY.
Check condition of spring washers (2, Fig. 8-14). Keep washers free of lubricants.
Remove cotter pin (5), loose nut (3) and clean washers (2; 4) if necessary, use some
solvent for degreasing.
(g) Attach spring scale (6) to fork (see Fig. 8-14).
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 8 – LANDING GEAR
(h) Torque castellated nut (3) so a constant force of 4-6 kg is required to rotate nose wheel
fork. Take attention that nut does not spin against spindle (1) because there is a risk of
cotter pin shear. In this case you may drill a new hole ø2.5 mm (0.098 in) for the cotter
pin in spindle in a suitable position.
(i)
As necessary, install new spring washers (2) and repeat procedure (g).
(j)
Install new cotter pin (5).
(k) Install nose wheel (see 8.3.8) and nose wheel fairing (see 8.3.6).
1 Spindle
2 Spring washer
3 Nut
4
5
8
Washer
Cotter pin
Spring scale
Fig. 8-14: Check of old version nose landing gear after shimmy occurrence
New version of the nose landing gear:
(a) Remove the nose wheel fairing (see 8.3.5).
(b) Remove the nose wheel (see 8.3.7).
(c) Remove the cover (7, Fig. 8-15) and unload nose landing gear.
(d) Check condition of the fork, leg, and shock absorber for cracks (see Fig. 8-15). Use
magnifying glass.
Date of issue: 2013-06-30
Revision No.: 8 - 19
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PiperSport
CHAPTER 8 – LANDING GEAR
(e)
(f)
Check tire worn and specified inflation (1.2 + 0.1 bar (17.4 + 1.5 psi)).
CAUTION:
DO NOT EXCESS SPECIFIED TIRE PRESSURE OVERPRESSURED TIRE
CAUSED SHIMMY.
(g) Check condition of spring washers (3). Keep washers free of lubricants. Remove cotter
pin (6), loose nut (5) and clean washers (2; 3; 4; 11) if necessary, use some solvent
for degreasing.
(h) Attach spring scale (10) to fork.
(i)
Torque castellated nut (5) so a constant force of 8-10 kg is required to rotate nose wheel
fork.
(j)
Install new cotter pin (6).
(k) As necessary, grease the axle per grease nipple.
(l)
Apply Loctite 221 on the bolt (8) and install the cover (7); install nose wheel (see 8.3.8)
and nose wheel fairing (see 8.3.6).
1
2
3
4
5
Spindle
Friction washer
Spring washer
Thrust ring
Nut
6
7
8
9
10
11
Cotter pin
Cover
Bolt
Washer
Spring scale
Washer
Fig. 8-15: Check of new version nose landing gear leg after shimmy occurrence
Revision No.: 10
Date of issue: 2017-10-18
8 - 20
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CHAPTER 8 – LANDING GEAR
8.4.3
SportCruiser
PiperSport
Check of nose landing gear leg for cracks
Tools needed:
-
Flashlight
-
10x magnifier
(a) Remove key from ignition switch and disconnect battery.
(b) Remove the nose wheel fairing (see 8.3.5).
(c) Visually inspect the bottom side of the nose landing gear leg lower section, in the place of
the weld of the tube and the bracket (see Fig. 8-16) in accordance with FAA AC 43.131B, Chapter 5, Section 2, Visual Inspection.
(d) Using flashlight and 10x magnifier, inspect thoroughly nose landing gear leg and verify
there is no evidence of cracking in paint on or around place of the weld of the tube and
the bracket.
(e) If no cracking is evident, perform the following steps:
1. Install nose wheel fairing (see 8.3.6).
2. Connect battery and restore aircraft to the airworthy condition.
(f)
If an evidence of cracking is identified, perform the following steps for confirmation / not
confirmation of cracking:
1. Remove nose landing gear leg (see 8.3.11).
2. Using NDT Penetration Check Kit perform a NDT penetration check in accordance
with FAA AC 43.13-1B, Chapter 5, Section 5, Penetrant Inspection.
(g) In case of non confirmation of cracking, install nose landing gear leg back (see 8.3.12),
install nose wheel fairing (see 8.3.6), connect battery and restore aircraft to the airworthy
condition.
(h) In case of confirmation of cracking, perform the following steps:
1. Assure Aircraft on Ground (AOG).
2. Report this occurrence to the manufacturer (CSA) within 72 hours.
3. Ask the manufacturer (CSA) for the NLG No. SG0300N.
4. Install new nose landing leg (see 8.3.12).
5. Install nose wheel fairing (see 8.3.6), connect battery and restore aircraft to the
airworthy condition.
Date of issue: 2018-01-18
Revision No.: 11
8 - 21
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 8 – LANDING GEAR
Fig. 8-16: Inspected area of the nose landing gear leg
The pictures are for illustration only. The individual NLG types can differ in details
Revision No.: 10
Date of issue: 2017-10-18
8 - 22
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CHAPTER 8 – LANDING GEAR
SportCruiser
PiperSport
8.5 Changes / Service information
8.5.1
Tire change
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in
-
Allen wrench size 1/4 in
(a) Jack and support the airplane (see 14.2).
(b) Remove the wheel fairing (see 8.3.1).
(c) Remove the main landing gear wheel (see 8.3.3) or the nose landing gear wheel
(see 8.3.5).
(d) Deflate the tire.
(e) Unscrew the nuts (7, Fig. 8-17), remove the washers (8) and the bolts (5; 6).
(f) Set apart both halves of the rim (1; 2) and remove the tire (10) with the air tube (11).
(g) Exchange the air tube or the tire, if necessary.
(h) Put the air tube (11) into the tire (10) and inflate it slightly.
(i) Put the other half of the rim on this unit. Join both halves of the rim with the bolts (5; 6),
washers (8) and the nuts (7) – torque value 11.3 Nm (100 in lbs).
(j) Put the other half of the rim on this unit. Join both halves of the rim with bolts – torque
value 11.3 Nm (100 in lbs).
(k) Inflate tires to the prescribed pressure:
- nose wheel 1.2 + 0.1 bar (17.4 + 1.5 psi)
- main wheel 1.8 + 0.2 bar (26.1 + 2.9 psi)
(l) Mark position of the rim and the tire by redline overreaching about 10 mm (3/8 in) to the
rim and the tire (serves for checking the tire slewing against the wheel rim in operation).
Date of issue: 2013-10-11
Revision No.: 2
8 - 23
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SC-AMM-1-0-00
PiperSport
CHAPTER 8 – LANDING GEAR
NOTE
Figure shows the replacement tire of
the main landing gear wheel.
1
2
3
4
5
6
Wheel rim, outer
Wheel rim, inner
Hub
Brake disc
Bolt (3 pcs.)
Bolt (3 pcs.)
7 Lock nut (6 pcs.)
8 Washer (9 pcs.)
9 Screw (3 pcs.)
10 Tire
11 Air tube
12 Nordlock washer (6 pcs.)
Fig. 8-17: Tire change
8.5.2
Change of nose landing gear shock absorber dumping elements
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in
(a) Jack and support the airplane (see 14.2).
(b) Remove the cotter pin (10, Fig. 8-18), unscrew the nut (13), remove the washers (12), bolt
(11) and disconnect tube (1) from the bracket (2) on the nose gear leg.
(c) Remove the cotter pin (10), unscrew the nut (9) and remove washers (8; 6; 7; 5).
(d) Turn the tube (1) forward and remove tube (1), dumping elements (2) and washers (3).
(e) As needed, remove the cotter pins (15), push out the tube (14) and remove profile (18)
and case /19).
(f) Replace damaged dumping elements (3).
(g) Gradually put on the tube (1) shock absorbers (2), washers (3) and insert tube into the
hole on the tube (14) according to the figure.
Revision No.: 2
Date of issue: 2013-10-11
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PiperSport
CHAPTER 8 – LANDING GEAR
(h) Gradually install on the tube end (1) washers (5; 7; 6; 8), screw and tighten the nut (9);
secure it with new cotter pin (10).
(i) Put the lower end of the tube (1) to the bracket (16); install the bolt (11) with the nut (13)
and washers (12), secure nut with the new cotter pin (10).
(j) Lower the airplane on jacks.
1 Tube
2 Shock absorber
3 Washer
4 Washer
5 Washer
6 Washer
7 Rubber washer
8 Washer
9 Nut
10 Cotter pin
11
12
13
14
15
16
17
18
19
Bolt
Washer
Nut
Tube
Cotter pin
Nose leg bracket
Bracket
Profile
Case
Fig. 8-18: Change of the dumping elements in the nose landing gear
Date of issue: 2013-10-11
Revision No.: 2
8 - 25
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SportCruiser
PiperSport
8.5.3
CHAPTER 8 – LANDING GEAR
Change of brake lining
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher
Tools needed:
-
wrench size 7/16 in
-
drill # 25
-
electric drill
-
brake relining tool, pneumatic press
CAUTION:
EXCHANGE ALWAYS BOTH BRAKE PADS!
(a) Jack and support the airplane (see 14.2).
(b) Remove the main landing gear wheel (see 8.3.3).
(c) Remove the caliper from the wheel by removing the two bolts (1, Fig. 8-19) that hold in on.
(d) Remove old linings (4) by drilling the crimped side of the rivet (Do not use punch and
hammer). Using a # 25 drill (0.1495 in. diameter), drill through rivet taking care to avoid
damaging the rivet hole.
(e) After drilling crimped edge off rivets, lift old lining and remaining rivet pieces from the
brake shoe.
(f) Inspect the brake shoe (2; 3) for any bending or other damage that may have occurred
during service. A shoe with more than 0.010 in bend should be replaced. Inspect rivet
holes to ensure that no damage has occurred during removal.
(g) Using a brake relining tool or pneumatic press, replace the lining using brass rivet (5).
(h) Insert the brake disc and screw them with the caliper – torque value 11.3 Nm (100 in lbs).
(i) Reinstall the main landing gear wheel (see 8.3.4).
(j) Check the brake function and carry out the conditioning procedures (see 8.5.7).
1
2
3
4
5
6
Revision No.: 2
Bolt
Movable brake shoe
Stationary brake shoe
Lining
River
Brake bleeder valve
Date of issue: 2013-10-11
8 - 26
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CHAPTER 8 – LANDING GEAR
NOTE:
SportCruiser
PiperSport
The lining requires replacement when the wear indicator is no longer visible.
Fig. 8-19: Change of brake lining
8.5.4
Lubrication of axis of rotation of nose landing gear
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher
Tools needed:
-
wrench size 1/2 in
-
grease gun
(a) Uncscrew and remove the bolt (8, Fig. 8-15) with the washer (9) and remove cover (7).
(b) By means of the grease gun lubricate axis of rotation.
CAUTION:
AVOID TO GREASE CONTAMINATES THE FRICTION AREAS!
(c) Apply Loctite 221 on the bolt (8) with the washer (9) and install the cover (7).
Date of issue: 2013-10-11
Revision No.: 2
8 - 27
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SportCruiser
PiperSport
8.5.5
CHAPTER 8 – LANDING GEAR
Refilling / exchanging brake fluid
Draining brake fluid from brake system
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher
Tools needed:
-
wrench size 7/16”
(a) Disconnect the brake hose from the brake cylinder and let brake fluid drain into the
previously prepared can.
(b) You can accelerate brake fluid draining by compressing the relevant brake pedal.
Filing brake fluid into brake system
NOTE:
Brake fluid used by aircraft manufacturer is shown in Section 17.5.
(a) Fix the aircraft with help wedges.
(b) Release the parking brake.
(c) Bleed the hose of the filling equipment and connect it to the filling hole of the left wheel
brake.
(d) Unscrew the plug of the left brake cylinder with reservoir using the socket wrench.
(e) Slowly fill the brake system with hydraulic fluid.
(f) Repeatedly push the brake pedal.
(g) Check the brake hose from the point of view of occurrence of bubbles.
(h) Continuous occurrence of bubbles indicates a failure of the filling equipment.
(i) After the reservoir is filled up to the filler hole – stop the filling through closing of the filling
valve of the filling equipment.
(j) Disconnect the hose of the filling equipment.
(k) Suck off 20 ml of hydraulic fluid using the syrette.
(l) Screw down the closing plug using the socket wrench.
(m) Repeat the same procedure for the right brake cylinder.
(n) Check the proper resistance of pedals.
(o) Pull the parking brake.
By this way, both wheels must be braked equally.
(p) Remove the wedges.
Refilling brake fluid into brake system
For the refilling – use the procedure for filling (see above).
Revision No.: 2
Date of issue: 2013-10-11
8 - 28
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CHAPTER 8 – LANDING GEAR
8.5.6
SportCruiser
PiperSport
Bleeding the brake system
Type of maintenance: line
Authorization to perform:
-
Sport pilot or higher
Tools needed:
-
wrench size 7/16”
-
brake bleeder unit
(a) Open the brake bleeder valve (6, Fig. 8-19) slightly on the brake caliper to facilitate
bleeding of air from the system.
(b) Attach a tube from the nozzle of a squirt can or brake bleeder unit containing brake fluid to
the top of the brake bleeder valve. Pump the handle until oil flows bubble free from service
hose before attaching.
(c) Make sure that the master cylinder shaft is fully extended to open up the internal bypass
valve.
(d) Inject brake fluid into the puck housing and continue injecting until the fluid travels through
the system in to the master cylinder.
(e) Air in the system will be pushed up and out in to the master cylinder only if the master
cylinder is at the highest point in the system, and there are no loops in the brake lines.
(f) Fluid should be pushed through the system until it reaches approx. 6.4 mm (1/4 in) from
the top of the master cylinder.
(g) Close the brake bleeder valve, and remove the service hose.
(h) If the brake system is free of air, the brake pedal should feel firm and not spongy. If not,
repeat steps (a) through (g) until system is free of trapped air.
(i) Repeat for wheel of the opposite system.
(j) Fluid leakage from the top of the master cylinder during operation indicates too high a fluid
level.
8.5.7
Conditioning procedures
NOTE:
It is important to condition the new linings after installation to obtain
maximum service life and performance.
(a) After the linings have been installed, apply brake pressure during high throttle static runup. Note rpm at creep if any occurs.
(b) Perform two or three high speed taxi snubs. Apply firm braking at 25 – 35 kts down to 4
kts to generate the necessary 150 – 200 °C temperatures at the brake pads. Do not bring
the airplane to a complete stop during taxi runs, and continue to roll airplane until reaching
the tie down area. Release brake pressure at tie down area as soon as practical and park
with brake pressure released. Allow brakes to cool for 10 – 15 minutes
(c) Repeat step (a) and note rpm at creep if any occurs. There should be a noticeable
increase in holding torque.
Date of issue: 2013-10-11
Revision No.: 2
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PiperSport
CHAPTER 8 – LANDING GEAR
(d) If properly conditioned, the pads will have a uniform shiny appearance (glaze) on the
surface. Repeat steps (a) – (c) if necessary to produce glaze.
NOTE:
Forward movement of the airplane during runup could be caused by the
wheels skidding and not brake malfunction.
Conditioning removes high spots, and creates a layer of glazed material at the lining surface.
Normal braking will produce enough heat to maintain glazing during the life of the lining.
Glazing can be worn off during light use such as taxiing.
8.5.8
Design changes on the Nose Landing Gear
History of the Nose Landing gear design is illustrated in Figure 8-20 below.
Old NLG type SG0000N
Old NLG type SG0240N
New reinforced NLG type SG0300N
Fig. 8-20: Design changes of the Nose Landing Gear
Revision No.: 11
Date of issue: 2018-01-22
8 - 30
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CHAPTER 9 – FUEL SYSTEM
SportCruiser
PiperSport
Contents
9.1
General .................................................................................................................. 9-3
9.2
Description and operation ...................................................................................... 9-7
9.3
9.4
9.5
9.2.1
Fuel storage ........................................................................................... 9-7
9.2.2
Fuel distribution ..................................................................................... 9-7
9.2.3
Indication of fuel quantity and pressure................................................. 9-8
Removal / Installation ............................................................................................ 9-9
9.3.1
Fuel tank removal .................................................................................. 9-9
9.3.2
Fuel tank installation ............................................................................ 9-10
9.3.3
Removal of the finger screen .............................................................. 9-10
9.3.4
Installation of the finger screen ........................................................... 9-11
9.3.5
Fuel level sender removal ................................................................... 9-11
9.3.6
Fuel level sender installation ............................................................... 9-12
9.3.7
Fuel drain valve removal ..................................................................... 9-13
9.3.8
Fuel drain valve installation ................................................................. 9-14
Check / Adjustment.. ………………………………..…………………………………9-14
9.4.1
Checking fuel system tightness . ………………………………………....9-14
9.4.2
Fuel pump check . ………………………………………………………….9-14
Exchanges / Service information . ……………………………………………………9-15
9.5.1
Fuel tank filling. …………………………………………………………….9-15
9.5.2
Draining fuel system . ……………………………………………………...9-15
9.5.3
Fuel filter cleaning …………………………………….…………………...9-16
Date of issue: 2017-10-18
Revision No.: 10
9-1
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 9 – FUEL SYSTEM
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
9-2
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CHAPTER 9 – FUEL SYSTEM
9.1
SportCruiser
PiperSport
General
The fuel system (see Fig. 9.1) is used for storing fuel in the airplane and it’s delivering to the
engine. The fuel system of SportCruiser / PiperSport airplane consists of the following parts:
two fuel tanks, fuel tubing, selector valve, gascolator, mechanical fuel pump (located on the
engine), electrical fuel pump, fuel quantity sensor, fuel flow-meter, fuel pressure sensor and
Instrument panel with
EFIS / EMS
drain valves of the fuel tanks.
Fig. 9-1: Fuel system layout (page 1 of 4)
Date of issue: 2013-06-30
Revision No.: 9-3
SC-AMM-1-0-00
SportCruiser
PiperSport
Instrument panel with
EFIS / EMS
(new design)
CHAPTER 9 – FUEL SYSTEM
Fig. 9-1: Fuel system layout (page 2 of 4)
Revision No.: -
Date of issue: 2013-06-30
9-4
SC-AMM-1-0-00
PiperSport
Instrument panel with
analog instruments
CHAPTER 9 – FUEL SYSTEM
SportCruiser
Fig. 9-1: Fuel system layout (page 3 of 4)
Note: The picture of the instrument panel is for information only and could differ from the real state.
Date of issue: 2017-06-30
Revision No.: 8
9-5
1
2
3
4
5
Fuel tank, left
Fuel tank, right
Filler cap
Fuel quantity sensor
Finger screen
6 Fuel selector valve
7 Gascolator
8 El. fuel pump
9 Fuel pressure sensor
10 Fuel flow meter
11 Mech. fuel pump
12 Carburetor, left
13 Carburetor, right
14 Restrictor jet
15 EMS
PiperSport
16 Fuel quantity indic.
17 Fuel pressure indic.
18 Check valve
Instrument panel with
analog instruments
(new design)
SportCruiser
SC-AMM-1-0-00
CHAPTER 9 – FUEL SYSTEM
Fig. 9-1: Fuel system layout (page 4 of 4)
Note: The picture of the instrument panel is for information only and could differ from the real state.
Revision No.: 8
9-6
Date of issue: 2017-06-30
SC-AMM-1-0-00
PiperSport
CHAPTER 9 – FUEL SYSTEM
9.2
SportCruiser
Description and operation
9.2.1 Fuel storage
Fuel is stored in airplane in the fuel tanks. The fuel tanks are welded from Al-alloy sheet and
their volume is 57 liters (15 US gallons) each. The tanks are located in the outer wings
between ribs No.4 and 6a in front of the main spar. Their shape fits with 3.2 mm (1/8 in) offset
with outer wing shape. The gap is filled with cork strips glued on the fuel tank. Cork strips
protect the tank from touching the skin and the wing spar. Each fuel tank has a filler neck (1,
Fig. 9-2) with flush head filler cap (2), venting tube (3), finger screen (4) and drain valve (5).
Fuel is filled into the each tank through the filler neck (1), which is located on the top skin
close to rib No.6a. Fuel drain from the tank is possible through the drain valve (5) located in
the rear corner of bottom skin close to the root fuel tank rib.
1 Filler neck
2 Filler cap
3 Venting tube
4 Finger screen
5 Drain valve
6 Fuel quantity sensor
Fig. 9-2: Fuel tank, right
9.2.2 Fuel distribution
Fuel flows from the tank (1, Fig. 9-3.) and (2) through finger screens (3) to the fuel selector
valve (4) and from there to the gascolator (5), electrical fuel pump (6) to the mechanical fuel
pump (7) located on the engine. From there it is supplied through the fuel distributor to
carburetors.
The fuel selector valve (4) is used also for interruption of fuel supply in case of engine fire or
after long-time parking airplane. The fuel selector valve is located on the middle console
between the seats in the cockpit. The gascolator (5) is located on the firewall in lowest point of
Date of issue: 2013-06-30
Revision No.: 9-7
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 9 – FUEL SYSTEM
the firewall above the gascolator. The fuel return line (8) bleeds off any possible vapours into
the left tank.
1
2
3
4
Fuel tank, left
Fuel tank, right
Finger screen
Fuel selector valve
5
6
7
8
Gascolator
Electrical fuel pump
Mechanical fuel pump
Fuel return line
Fig. 9-3: Fuel system installation diagram
9.2.3 Indication of fuel quantity and pressure
Fuel quantity is measured by the fuel float sensor (see Fig. 9-4). The float position is
converted to an electrical signal and fuel quantity in the tank is indicated either on the EMS or
on the classical analog instruments (see Fig. 9-1).
Fuel pressure is measured by the electrical fuel pressure sensor. Electrical signal from the
sensor is indicated either on the EMS or on the classical analog instruments (see Fig. 9-1).
Revision No.: 10
Date of issue: 2017-10-18
9-8
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CHAPTER 9 – FUEL SYSTEM
SportCruiser
PiperSport
Fig. 9-4: Float mechanism
9.3
Removal / Installation
9.3.1 Fuel tank removal
Type of maintenance: heavy
Authorization to perform:
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No. 8, 1/2 in,
-
screwdriver
-
drill diam. 3.2 mm (1/8 in), 4.1 mm (5/32 in)
-
electric drill
-
cutting pliers, pliers
(a) Disconnect the battery.
(b) Drain fuel from the fuel system by the tank drain valve.
(c) Unscrew the filler cap.
(d) Remove the wing (see 4.3.1) and put it on the table.
(e) Drill out the top half of the leading edge skin.
(f) Disconnect wiring from fuel quantity sensor.
(g) Disconnect fuel line.
(h) Carefully remove the tank and store it. Seal the tank holes as needed.
Date of issue: 2013-06-30
Revision No.: 9-9
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 9 – FUEL SYSTEM
9.3.2 Fuel tank installation
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No. 8, 1/2 in,
-
screwdriver
-
riveting pliers
-
cutting pliers, pliers
(a) Remove any hole seals from the tank.
(b) Set the tank to the position between the ribs No.4 and 6a. Before installing the tank, check
the cork bands for completeness and damage. Change them, if needed.
(c) Connect fuel quantity sensor wire, insert the finger screen – use LOCTITE 565 or
equivalent sealant.
(d) Close the leading edge skin on the wing and fit it to the spars and ribs per clecos each
second hole through of securing harnesses.
(e) Rivet the skin on the ribs and spar.
(f) Screw back filler cap - use silicon to make connection of filler cap flange and wing skin
watertight.
(g) Install the wing (see 4.3.2).
(h) Check the fuel system (see 9.4.1).
(i) Connect the battery ground.
9.3.3 Removal of the finger screen
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
-
socket wrench 11/16 inch
NOTE:
The finger screen is located in the root tank rib.
(a) Drain fuel from the fuel system.
(b) Remove the wing (see 4.3.1).
(c) Remove the hose clamp (3, Fig. 9-5) and disconnect the fuel hose (4).
(d) Remove the finger screen (2).
Revision No.: -
Date of issue: 2013-06-30
9 - 10
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SportCruiser
PiperSport
CHAPTER 9 – FUEL SYSTEM
9.3.4 Installation of the finger screen
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Screwdriver
-
Socket wrench 11/16 inch
(a) Screw the finger screen (2, Fig. 9-5) into the root tank rib – use LOCTITE 565 or
equivalent sealant on finger screen thread.
(b) Connect fuel hose (4) on the finger screen; tighten the hose clamp (3).
(c) Install the wing (see 4.3.2).
(d) Check fuel system tightness (see 9.4.1).
1
2
3
4
Fuel tank
Fingers screen
Clamp
Fuel hose
Fig. 9-5: Finger screen removal / installation
9.3.5 Fuel quantity sensor removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
electric drill
-
drill diam. 3.2 mm (1/8 in)
-
screwdriver
-
cutting pliers, pliers
(a) Remove (drill off) the fuel quantity cover plate (6, Fig. 9-6).
(b) Disconnect fuel level sender wire (5).
(c) Unscrew bolts (3), remove washers (4) and fuel quantity sensor (1) and gasket (2).
Date of issue: 2013-06-30
Revision No.: 9 - 11
SC-AMM-1-0-00
SportCruiser
PiperSport
1
2
3
4
CHAPTER 9 – FUEL SYSTEM
Fuel quantity sensor
Gasket
Bolt
Washer
5 Wire
6 Cover plate
7 Rivet
Fig. 9-6: Fuel quantity sensor removal / installation
9.3.6 Fuel quantity sensor installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
-
riveting pliers (riveter)
-
cutting pliers, pliers
Revision No.: -
Date of issue: 2013-06-30
9 - 12
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PiperSport
CHAPTER 9 – FUEL SYSTEM
(a) Set the gasket (2, Fig. 9-6) on the fuel tank flange.
(b) Set position and length of the fuel quantity sensor lever according to the Fig. 9-4.
(c) Carefully put the fuel quantity sensor (1) into the tank and attach it using bolts (3) with
washers (4) – use LOCTITE 565 or equivalent sealant on bolts thread.
(d) Connect electrical wires (5) to the fuel quantity sensor (see Wiring Manual).
(e) Check fuel system tightness (see 9.4.1).
(f) Connect the battery and check fuel gauge function.
(g) Install (rivet) the cover plate (6).
9.3.7 Fuel drain valve removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in
NOTE:
The fuel drain valves are located on bottom side of the wings and on the
gascolator.
(a) Drain the fuel from the tank or gascolator.
(b) Unscrew drain valve (1, Fig. 9-7) from the tank (2) or gascolator.
(c) Check “O” ring and the valve spring.
NOTE
Figure shows the fuel drain
valve on the left wing.
1 Fuel drain valve
2 Fuel tank flange
Fig. 9-7: Fuel drain valve removal / installation
Date of issue: 2013-06-30
Revision No.: 9 - 13
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 9 – FUEL SYSTEM
9.3.8 Fuel drain valve installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size 1/2 in
(a) Screw the drain valve (1, Fig. 9-7) in the tank (2) or gascolator – use LOCTITE 565 or
equivalent sealant on the drain valve thread.
(b) Fill the tank with fuel and check drain valve tightness.
9.4
Check / Adjustment
9.4.1 Checking fuel system tightness
NOTE:
Tightness is checked by pressurized air. When performing a specific
tightness check, outside temperature fluctuations must not be bigger than
± 5 °C (± 9 °F). Reseal the found out leakage by a suitable method - by
tightening, by using a suitable sealing.
Checking airplane fuel system tightness by air
(a) Remove upper engine cowling.
(b) Close the fuel tank filler caps.
(c) Fuel selector valve - OFF position.
(d) Connect the pressurization equipment hose to the venting tube outlet on the L/R wing
bottom side.
(e) Disconnect the hoses from the carburetors and return line; blind them by plugs.
(f) Set the fuel selector valve to LEFT / RIGHT position (choose the tank).
(g) Supply air pressure of 2 kPa (0.02 bar; 0.29 psi) to the appropriate fuel tank by means of
the pressurization equipment.
(h) Shut the air pressure supply. During 15 minutes there must not be any loss in pressure.
Find out leakage by listening to and by soap water.
(i) As necessary, repeat procedure for the second fuel tank.
(j) Remove plugs from the hoses and reconnect them to the carburetors and return line.
(k) Install upper engine cowling.
9.4.2
Fuel pump check
Check for cracks
Check the fuel pump body for cracks, including the inlet and the outlet hose. If cracks are
detected, immediately exchange the fuel pump for the new pump.
Checking fuel leakage
Perform engine inspection and check the fuel pump body, including inlet and outlet hose, for
fuel leakage. In case of fuel leakage, find out the reason and if necessary exchange the fuel
pump for the new pump.
Revision No.: -
Date of issue: 2013-06-30
9 - 14
SC-AMM-1-0-00
CHAPTER 9 – FUEL SYSTEM
9.5
SportCruiser
PiperSport
Exchanges / Service information
9.5.1 Fuel tank filling
CAUTION:
WHEN FILLING FUEL IN THE AIRPLANE, USE ONLY APPROVED KINDS
OF FUEL MENTIONED IN THIS MANUAL IN 10.2.1, IN THE POH
SECTION 2.4, IN THE ROTAX OPERATOR’S MANUAL SECTION 10.2.2
FUEL, IN THE ROTAX SERVICE INSTRUCTIONS SI-912-016. SAFETY
INSTRUCTIONS FOR FILLING FUEL INTO THE AIRPLANE TANKS
(a) The fuel tanks can be filed with fuel only by persons who are fully instructed and
familiarized with safety instructions.
(b) It is prohibited to fill the fuel tank:
•
during rain and storm
•
in a closed space
•
when the engine is operating or with electric system switched on.
(c) A person filling the fuel tank must not be wearing polyester clothing or any clothing from a
material which creates static electricity.
(d)
It is prohibited to smoke or handle with open fire.
Procedure of fuel tank filing
(a) Ground the airplane. The airplane ground point is located on the nose landing gear leg.
(b) Open the fuel tank filler cap.
(c) Fill necessary quantity of fuel.
CAUTION:
WHEN FILLING FUEL INTO THE AIRPLANE, AVOID THE CONTACT OF
FUEL WITH THE AIRPLANE SURFACE – IT WOULD CAUSE DAMAGE TO
SURFACE TREATMENT OF THE AIRPLANE.
(d) When the airplane is filled with fuel, wipe the filler neck of the rest of fuel and close the
fuel neck filler cap.
(e) Remove conductive interconnection between the filling device and the airplane.
(f) Sludge the fuel tank.
9.5.2 Draining fuel system
Perform draining the fuel tanks and gascolator after every filling the tank with fuel before the
first flight of the day. The fuel tank draining points are on bottom side of the wings and on the
firewall.
Draining procedure
(a) Open the drain valve by pressing up.
(b) Drain required quantity of fuel.
NOTE:
Draining serves for elimination of impurities and sediments from fuel. Drain
so long unless clean fuel flows from the drain valve.
(c) Close the drain valve by releasing pressure.
(d) Check the purity of drained fuel (sediment, water).
Date of issue: 2013-06-30
Revision No.: 9 - 15
SportCruiser
SC-AMM-1-0-00
PiperSport
CHAPTER 9 – FUEL SYSTEM
9.5.3 Fuel filter cleaning
Perform fuel filter cleaning at each scheduled maintenance or signs of irregular engine
running.
Cleaning procedure
(a) Move the fuel selector valve to the OFF position.
(b) Use the drain valve to drain the existing fuel from the gascolator bowl.
(c) Remove the lockwire from nut (3. Fig. 9-8).
(d) Loose the nut (3) and remove the gascolator bowl (4) and the gasket (5).
(e) Use a small pointed tool to lift the edge of the filter screen (6) and carefully remove it for
cleaning.
(f) Clean the filter screen (6) by washing in fuel, or it can be blown off using an air line;
inspect bowl (4) and clean if required.
(g) Carefully install the filter screen (6) to the gascolator body, insert the gasket (5) and the
gascolator bowl (4); make sure to correct installation.
(h) Tighten the nut (3) and secure it by lockwire.
(i) Move the fuel selector valve to LEFT / RIGHT position; check the gascolator for fuel leak.
1
2
3
4
5
6
Gascolator body
Stirrup
Nut
Gascolator bowl
Gasket
Filter screen
Fig. 9-8: Fuel filter cleaning
Revision No.: -
Date of issue: 2013-06-30
9 - 16
SC-AMM-1-0-00
CHAPTER 10 – POWERPLANT
SportCruiser
PiperSport
Contents
10.1 General ................................................................................................................ 10-3
10.2 Description and operation .................................................................................... 10-3
10.2.1
10.2.2
Engine ................................................................................................. 10-3
10.2.1.1
Engine mount ................................................................... 10-4
10.2.1.2
Engine cowling ................................................................. 10-5
10.2.1.3
Engine control .................................................................. 10-5
10.2.1.4
Engine instruments .......................................................... 10-5
10.2.1.5
Engine cooling system ..................................................... 10-6
10.2.1.6
Engine lubrication system ................................................ 10-7
10.2.1.7
Engine air inlet system ..................................................... 10-7
10.2.1.8
Exhaust system ................................................................ 10-8
10.2.1.9
Ignition system ................................................................. 10-9
Propeller ............................................................................................ 10-10
10.3 Removal / Installation ........................................................................................ 10-12
10.3.1
Removal of the engine from the airplane .......................................... 10-12
10.3.2
Installation of the engine on the airplane........................................... 10-13
10.3.3
Klassic 107/3/R propeller removal ..................................................... 10-15
10.3.4
Klassic 107/3/R propeller installation ................................................ 10-16
10.3.5
SR 3000 propeller removal ................................................................ 10-17
10.3.6
SR 3000 propeller installation ........................................................... 10-18
10.3.7
2A0R5R70EN propeller removal ....................................................... 10-19
10.3.8
2A0R5R70EN propeller installation ................................................... 10-21
10.3.9
3B0R5R68C propeller removal ......................................................... 10-22
10.3.10
3B0R5R68C propeller installation ..................................................... 10-23
10.3.11
Air intake system removal ................................................................. 10-25
10.3.12
Air intake system installation ............................................................. 10-25
10.3.13
Exhaust system removal ................................................................... 10-26
10.3.14
Exhaust system installation ............................................................... 10-28
10.3.15
Oil cooler removal.............................................................................. 10-28
10.3.16
Oil cooler installation ......................................................................... 10-29
10.3.17
Water cooler removal ........................................................................ 10-30
10.3.18
Water cooler installation .................................................................... 10-30
10.3.19
Throttle and choke levers removal .................................................... 10-31
10.3.20
Throttle and choke levers installation ................................................ 10-33
10.3.21
Carburetors heating knob removal .................................................... 10-33
10.3.22
Carburetors heating knob installation ................................................ 10-34
Date of issue: 2016-03-30
Revision No.: 7
10 - 1
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 10 – POWERPLANT
10.4 Check / Adjustment ............................................................................................ 10-35
10.4.1
Engine test ......................................................................................... 10-35
10.4.2
Klassic 170/3/R propeller inspection ................................................. 10-37
10.4.3
10.4.4
10.4.2.1
Summary of propeller periodical inspection ................... 10-37
10.4.2.2
Prescribed inspection works .......................................... 10-37
10.4.2.3
Klassic 170/3/R propeller blades pitch setting ............... 10-39
SR3000 propeller inspections, works ................................................ 10-40
10.4.3.1
Summary of propeller periodical inspection ................... 10-40
10.4.3.2
Prescribed inspection works .......................................... 10-40
3B0R5R68C / 2A0R70EN propeller inspections ............................... 10-41
10.4.4.1
Summary of propeller periodical inspection ................... 10-41
10.4.5
Adjusting throttle control .................................................................... 10-41
10.4.6
Adjusting choke control ..................................................................... 10-41
10.4.7
Adjusting carburetors heating control ................................................ 10-42
10.4.8
Checking exhaust system ................................................................. 10-42
10.5 Exchanges / Service information ....................................................................... 10-43
10.5.1
Exchange / Refilling oil ...................................................................... 10-43
10.5.2
Exchange / Refilling cooling liquid ..................................................... 10-44
10.5.3
Exchange / Check of oil filter ............................................................. 10-44
10.5.4
Purging the oil system ....................................................................... 10-45
10.5.5
Exchange / Check of air filter ............................................................ 10-46
Revision No.: 7
Date of issue: 2016-03-30
10 - 2
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 10 – POWERPLANT
10.1
General
Power unit of SportCruiser / PiperSport airplane is the ROTAX 912ULS2 engine and:
- Woodcomp Klassic 170/3/R ground adjustable 3-blade propeller or
- Woodcomp SR 3000/2W electrical adjustable 2-blade propeller or
- Sensenich 2A0R5R70EN ground adjustable 2-blade propeller or
- Sensenich 3B0R5R68C ground adjustable 3-blade propeller.
10.2
Description and operation
10.2.1
Engine
The engine ROTAX 912 ULS2 is a four-stroke, four-cylinder, opposed - cylinder engine,
central cam shaft and OHV - mechanism with maximal power of 73.5 kW (98.6 HP) at
5,800 rpm.
Technical data of the engine:
Engine manufacturer:
Engine type:
Power:
BRP-Powertrain GmbH&Co.KG
ROTAX 912 ULS2
max. take-off
73.5 kW
(98.6 hp)
max. continuous
69.0 kW
(92.5 hp)
RPM:
max. take-off
5,800 rpm max. 5 minutes
max. continuous
5,500 rpm
idle
1,400 rpm
Cylinder head temperature CHT: max.
135°C
(275°F)
Coolant temperature CT: *
max.
120°C
(248°F)
Oil temperature:
max.
130°C
(266°F)
optimum operation
90 - 110°C
(194 - 230°F)
Oil pressure:
max.
7 bar
(102 psi)
min.
0.8 bar
(12 psi)
optimum operation
2 - 5 bar
(29 - 73 psi)
Fuel pressure:
max.
0.4 bar
(5.8 psi)
min.
0.15 bar
(2.2 psi)
* With the change to a new cylinder heads design (for the ROTAX 912 ULS2 engines
from S/N 6 781 410 inclusive and for 912 S2 engines from S/N 4 924 544 inclusive, or on
all engines with type designation followed by suffix-01, or on all engines which have been
later equipped with the new cylinder heads design of P/N 413185 at cylinder head position
2/3), no longer the cylinder head temperature (CHT) is measured, but the coolant
temperature (CT).
Coolant type:
Refer to the Rotax Operator’s Manual, Section 2.2 Operating limits, and Section 2.3
Operating media - Coolant; the Rotax Installation Manual - Cooling System; Rotax
Service Instruction SI-912-016.
Old cylinder head design (CHT measurement method, engine type marking without
suffix -01)
In principle, 2 different types of coolant are permitted:
•
•
Conventional coolant based on ethylene glycol (with 50% of water)
Waterless coolant based on propylene glycol
WARNING: THE COOLANT CONCENTRATE (PROPYLENE GLYCOL) MAY NOT BE
MIXED WITH CONVENTIONAL (GLYCOL/WATER) COOLANT OR WITH
ADDITIVES!
NON OBSERVANCE CAN LEAD TO DAMAGES TO THE COOLING
SYSTEM AND ENGINE!
Date of issue: 2016-01-18
Revision No.: 6
10 - 3
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SportCruiser
PiperSport
CHAPTER 10 – POWERPLANT
CAUTION:
THE CONVENTIONAL GLYCOL/WATER COOLANT REDUCE TO APPLY
MAXIMUM PERMISSIBLE COOLANT EXIT TEMPERATURE.
New cylinder head design
(CT measurement method, engine type marking with suffix -01, P/N 413185 for 2/3
cylinder head)
Only one type of coolant is permitted:
•
Conventional coolant based on ethylene glycol (with 50% of water)
CAUTION: Waterless coolant are not allowed to be used for Rotax engines with
new cylinder head design.
Type of coolant used by the aircraft manufacturer is shown in the Section 17.5.
Fuel type:
MOGAS (EN228 Super or EN228 Super plus with max. 5 % ethanol blend, min RON 95;
ASTM D4814, min. AKI 91); AVGAS (100LL; ASTM D910; ASTM D7547).
Refer to the Rotax Operator’s Manual, Section Section 2.4 Operating media - Fuel, Rotax
Service Instructions SI-912-016, latest revision.
Oil type:
Refer to the Rotax Operator’s Manual, Section 2.5 Operating media – Lubricants, Rotax
Service Instructions SI-912-016 , latest revision.
NOTE:
10.2.1.1
For detailed information refer to:
- Operator's Manual for ROTAX Engine Type 912 Series
(OM-912, P/N 899649);
- Maintenance Manual (Line Maintenance) for ROTAX Engine Type 912
Series (MML-912, P/N 899191)
Engine mount
The engine mount serves for mounting the power unit to the airplane. It is welded from
4130 steel tubes and is attached to the firewall and to the engine by means of bolts. The
engine mount is installed on the firewall by four attachments. The scheme of engine
mount attachment to the firewall and to the engine is shown in the Fig. 10-1.
1
2
3
4
Firewall
Engine mount
Attachment bolt
Nut
Fig. 10-1: Engine mount
Revision No.: 6
Date of issue: 2016-01-18
10 - 4
SC-AMM-1-0-00
CHAPTER 10 – POWERPLANT
10.2.1.2
SportCruiser
PiperSport
Engine cowling
The engine cowling (Fig. 10-2) consists of two parts: upper cowling and lower cowling.
The upper cowling (1) is attached by means of quick fasteners (4) to the firewall and to the
lower cowling (2). Unlock the quick fasteners by turning the bolt by 90° counter-clockwise.
The access cover (5), which is located on the upper cowling on the left in front of the
firewall enables to check oil quantity in the oil tank without removing the upper cowling.
The lower cowling (2) is attached by means of quick fasteners (4) to the firewall and to the
upper cowling (1). In the front part of the lower cowling (2), there is an oval hole (3) for air
inlet to the radiator. In the bottom part of the lower cowling (2), there is a hole for air inlet
to the oil cooler. On the left side in the lower cowling (2) there is a hole (6) for air inlet to
the air filter to the engine inlet system.
1
2
3
4
5
6
Upper engine cowling
Lower engine cowling
Air inlet hole for radiator
Quick fasteners
Access cover
Air inlet hole for engine
inlet system
7 Landing light
8 Air inlet hole for cylinder
cooling
Fig. 10-2: Engine cowling
10.2.1.3
Engine control
Engine power is controlled by means of the throttle control lever which is positioned on the
middle channel between the seats and which controls engine power from idle up to max.
take-off power. Engine power control lever is mechanically connected (by cable) to the
carburetors.
If the control lever is fully pushed, this position corresponds to max. take-off power of the
engine. If the control lever is fully pulled, this position corresponds to idle. Changes in the
engine power setting can be made by moving of the control lever forward and backward.
10.2.1.4
Engine instruments
Engine parameters (RPM, CHT, EGT, oil pressure and temperature, fuel pressure,
manifold pressure) are displayed either on the EMS or on the classical analog
instruments. A typical example of the EMS display is shown in the Figure 10-3.
Date of issue: 2016-01-18
Revision No.: 6
10 - 5
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PiperSport
SC-AMM-1-0-00
CHAPTER 10 – POWERPLANT
Fig. 10-3: EMS D-120
10.2.1.5
Engine cooling system
Engine cooling is combined, cylinder heads are liquid cooled, and cylinders are air cooled.
Cooling circuit of cylinder heads is made as a closed system containing the pump (5, Fig.
10-4), expansion tank (4) with the pressure cap (3) ), thermostatic valve (6) (if used) and
the overflow bottle (1).
1 Overflow bottle
2 Cooler
3 Pressure cap
4 Expansion tank
5 Pump
6 Thermostatic valve (from S/N C0416)
Fig. 10-4: Cooling system
Revision No.: -
Date of issue: 2013-06-30
10 - 6
SC-AMM-1-0-00
PiperSport
CHAPTER 10 – POWERPLANT
10.2.1.6
SportCruiser
Engine lubrication system
Engine lubrication system is made with the dry sump. Engine lubrication system is
equipped with the mechanically driven oil pump (3, Fig. 10-5) with oil filter (6) which
ensures oil supply from the oil tank (4) located on the firewall through the thermostatic
valve (9) (if used) and the oil cooler (5) to the lubricated points on the engine. The oil
pump is equipped with the pressure relief valve (1) and with the oil pressure sensor (2).
The oil tank is ventilated by venting (7), which is connected to hose and is led under the
airplane. Oil pressure and temperature are indicated either on the EMS or on the classical
analog instruments.
1
2
3
4
5
Pressure relief valve
Oil pressure sensor
Oil pump
Oil tank
Oil cooler
6
7
8
9
Oil filter
Oil tank venting
Oil temperature sensor
Thermostatic valve (from S/N C0416)
Fig. 10-5: Oil cooling system
10.2.1.7
Engine air inlet system
Engine air inlet system ensures supply of sufficient air volume to the engine. Air is
supplied to the engine by the NACA type inlet (left on the engine cowling) through the air
filter (4, Fig. 10-6) to the airbox (1). Heated air from the heat exchanger (2), which is
attached to the exhaust (3), is controlled by flaps in the airbox. The heating control flaps is
controlled by CARB HEAT knob (8) on the instrument panel.
Date of issue: 2013-06-30
Revision No.: 10 - 7
SC-AMM-1-0-00
SportCruiser
PiperSport
1
2
3
4
CHAPTER 10 – POWERPLANT
Airbox
Heat exchanger
Exhaust
Air filter
5
6
7
8
Oil cooler
Water cooler
CABIN HEATING knob
CARB HEAT knob
Fig. 10-6: Air inlet system
10.2.1.8
Exhaust system
Exhaust system of SportCruiser / PiperSport airplane consist of four exhaust tubes (1, Fig.
10-7) which lead exhaust gases from individual cylinders to the muffler (2). The muffler
serves at the same time as a silencer. Exhaust gases are led from there by the exhaust
tube (3) down the airplane.
On the muffler there is a heat exchanger (5) from which is taken the warm air for the
carburetor preheating and for the cockpit.
The whole exhaust system is manufactured by welding from the stainless steel sheet.
Revision No.: -
Date of issue: 2013-06-30
10 - 8
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PiperSport
CHAPTER 10 – POWERPLANT
1 Exhaust tube
2 Muffler
3 Outlet exhaust tube
4 Spring
5 Heat exchanger
6 Spring
Fig. 10-7: Exhaust system
10.2.1.9
Ignition system
The engine is equipped with the double contactless ignition system. Every ignition circuit
has its source of energy, control unit, 2-ignition coils and 4-spark plugs. It is fully
independent on the other circuit and battery. High voltage current is distributed to the
spark plugs by means of high voltage cables. The sequence of individual cylinder ignition
of the engine is as follows: 1-4-2-3.
Ignition circuits are controlled by the ignition switch on the instrument panel.
Positions of ignition switch:
OFF
R
L
BOTH
START
Engine ignition of
Only ignition circuit A on (spar plugs 1, 2 top; 3, 4 bottom)
Only ignition circuit B on (spar plugs 3, 4 top; 1, 2 bottom)
Both circuits on
Both circuits on and the starter is running up the engine
Fig. 10-8: Ignition selection switch
Date of issue: 2013-06-30
Revision No.: 10 - 9
SportCruiser
SC-AMM-1-0-00
PiperSport
10.2.2
CHAPTER 10 – POWERPLANT
Propeller
The Woodcomp Klassic is a three-blade ground adjustable composite propeller designed
for the airplanes with piston engines with power up to 75 kW (100 hp) and max. propeller
speed up to 2,600 rpm.
The Woodcomp SR 3000 is a two-blade electrically operated in flight adjustable propeller
of mixed structure designed for the airplanes with piston engines with power up to
85.8 kW (115 hp) and max. propeller speed up to 2,650 rpm.
The angle of blade setting is adjusted by a servomotor controlled from the cockpit and it
can be adjusted smoothly in the range from the minimum (fine) angle intended for take-off
up to the maximum (coarse) angle. The propeller can operate with either of manual control
or with automatic control as a constant speed propeller (see Fig. 10-9).
The Sensenich 2A0R5R70EN propeller is a two-blade ground adjustable composite
propeller designed for the airplanes with piston engines with power up to 85.8 kW (115 hp)
and max. propeller speed up to 2,600 rpm.
The Sensenich 3B0R5R68C propeller is a three-blade ground adjustable composite
propeller designed for the airplanes equipped with engines Rotax 912 / 914 series.
The leading edge of the propeller blades is protected from damaging side by polyurethane
tape (Woodcomp) and co-cured bonded stainless steel (Sensenich). The propeller surface
is provided with a sprayed-on coat of resistant polyurethane varnish. The composite
propeller spinner is a part of the propeller.
The propeller is attached to the engine by means of bolts.
Technical data of the propellers:
Woodcomp propellers
Propeller manufacturer:
Woodcomp s.r.o.
Propeller type:
Klassic 170/3/R
Max. speed:
2,600 rpm
Diameter:
1.712 m
Pitch setting:
17.5° ± 0.5°
Propeller type:
SR 3000/2W
Max. speed:
2,650 rpm
Diameter:
1.75 m
Range of setting:
12°
(67.4 in)
(68.9 in)
Sensenich propellers
Propeller manufacturer:
Sensenich Propeller Manufacturing Co., Inc.
Propeller type:
2A0R5R70EN
Max. speed:
2,600 rpm
Diameter:
1.78 m
Revision No.: -
(70 in)
Date of issue: 2013-06-30
10 - 10
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 10 – POWERPLANT
Propeller type:
3B0R5R68C
Max. speed:
5,800 rpm engine
Diameter:
1.73 m
Pitch setting:
No. 4
(68 in)
Fig. 10-9: SR 3000 propeller control scheme
NOTE:
For detailed information refer to:
- Operator´s Manual Electrical Adjustable Aircraft Propeller SR 3000;
- EZ-Pitch Composite Aircraft Propeller Installation and Operation
Instructions (Doc. No. comp-ac-cf-rev-1a)
- Sensenich Three Blade Composite Aircraft Propeller Installation and
Operation Instructions for Rotax Engines (Doc. No. 3b0r5).
Date of issue: 2013-06-30
Revision No.: 10 - 11
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 10 – POWERPLANT
10.3
Removal / Installation
10.3.1
Removal of the engine from the airplane
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.8, No.9, 3/8”, 7/16”, 9/16”
-
Allen wrench size No.4
-
screwdriver
-
cutting pliers, pliers
-
Cobra pliers (for clamps)
(a) Remove engine cowling.
(b) Disconnect and remove the battery (see 11.3.1).
(c) Remove the propeller (see 10.3.3 or 10.3.5 or 10.3.7 or 10.3.9).
(d) Disconnect all electrical system wires and bonding between the engine mount and the
firewall.
(e) Shut the fuel selector valve (possibly drain fuel from the fuel installation).
(f) Drain oil from the engine (see 10.5.1) and cooling liquid (see 10.5.2).
(g) Disconnect hoses of the oil and the cooling system.
(h) Remove the oil cooler (see 10.3.15) and the water cooler (see 10.3.17).
(i) Disconnect control of carburetors and carburetors heating.
(j) Remove air intake (see 10.3.11).
(k) Remove the exhaust system (see 10.3.13).
(l) Blind all the holes on the engine so that no debris can get into the engine.
(m) Cut of the wire securing the bolt heads (2, Fig. 10-10).
(n) Remove bolts (2) and washers (3) attaching the engine to the engine mount (4).
(o) Take the engine (1) away from the engine mount by the crane or with help 2 assistants.
(p) Store the removed engine on a safe place on a suitable support and prevent it from
damage.
NOTE:
For detailed information refer to:
- Installation Manual for ROTAX Engine Type 912 Series
(IM-912, P/N 898643);
- Maintenance Manual (Line Maintenance) for ROTAX Engine Type 912
Series (MML-912, P/N 899191)
- Maintenance Manual (Heavy Maintenance) for ROTAX Engine Type 912
Series (MMH-912, P/N 899603)
Revision No.: -
Date of issue: 2013-06-30
10 - 12
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CHAPTER 10 – POWERPLANT
1 Engine
2 Bolt
SportCruiser
3 Washer
4 Engine mount
Fig. 10-10: Engine removal / installation
10.3.2 Installation of the engine on the airplane
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.8, No.9, 3/8”, 7/16”, 9/16”
-
Allen wrench size No.4
-
screwdriver
-
cutting pliers, pliers
-
Cobra pliers (for clamps)
(a) Put the engine (1, Fig. 10-10) on the engine mount (4) by the crane or with 2
assistants and attach it by the bolts (2) with washers (3). Tighten up to a torque of –
40 Nm (354 inch lb).
(b) Secure the bolt heads (2) by lockwire (see 15.8.2).
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(c) Install the exhaust system (see 10.3.14).
(d) Connect wiring according the wiring diagrams (see Chapter 16).
(e) Install the oil cooler (see 10.3.16).
(f) Install the water cooler (see 10.3.18).
(g) Connect and secure oil system hoses.
(h) Connect and secure fuel system hoses.
(i) Install air intake on the engine (see 10.3.12).
(j) Connect control cable of the carburetors preheating flap.
(k) According to the Fig. 10-11 connect control cables of the throttle and the choke on the
carburetors control levers. Adjust throttle control (see 10.4.8) and the choke (see
10.4.9).
(l) Connect the air hose from the heat exchanger for heating the airplane cockpit.
(m) Fill the prescribed amount oil and cooling liquid quantity.
(n) Check fuel system tightness (see 9.4.1).
(o) Install the propeller (see 10.3.4 or 10.3.6 or 10.3.8 or 10.3.10).
(p) Install and connect the battery (see 11.3.2).
(q) Install engine cowlings.
(r) Perform engine test (see 10.4.1).
1 Carburetor, left
2 Airbox
3 Throttle control cable
4 Choke control cable
5 Throttle control lever
6 Choke control lever
Fig. 10-11: Throttle and choke control connection
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CHAPTER 10 – POWERPLANT
10.3.3
SportCruiser
Klassic 170/3/R propeller removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13, No. 16 (5/8”)
-
Allen wrench size No.6
-
screwdriver
-
cutting pliers, pliers
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) Unscrew the screws (11, Fig. 10-12) with the washers (12) and remove the propeller
spinner (1).
(c) Cut of the wire securing the bolt heads (7).
(d) Unscrew and remove the bolts (7) with the washers (10) and take out the propeller
along with spinner flange (9) from the spacer (3).
(e) Put the protective covers on the propeller blades and store the propeller on a safe
place so that no damage can occur.
1
2
3
4
5
6
Propeller
Propeller spinner
Spacer
Drive bushing (6 pcs.)
Bolt (6 pcs.)
Propeller flange
7 Bolt (6 pcs.)
8 Nut (6 pcs.)
9 Spinner flange
10 Washer (12 pcs.)
11 Screw (6 pcs.)
12 Washer (6 pcs.)
Fig. 10-12: Klassic 170/3/R rpropeller removal / installation
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10.3.4
CHAPTER 10 – POWERPLANT
Klassic 170/3/R propeller installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13, No. 16 (5/8”)
-
Allen wrench size No.6
-
screwdriver
-
cutting pliers, pliers
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) Check the contacting areas of the spacer propeller shaft flange (3, Fig. 10-12) and the
propeller. Clear of all impurities.
(c) Remove protective covers from the propeller blades and carry out visual check of the
propeller integrity and condition.
(d) Check out possibly adjust the blades pitch of propeller according to the propeller
manual.
NOTE:
Propeller pitch is factory set to 17.5° ± 0. 5°.
(e) Attach the propeller (1) and the spinner flange (9) to the spacer (3) on the engine
flange (6) by means of the bolts (7) with washers (10).
(f) Secure the airplane against its movement (see 14.5).
(g) Tighten the bolts (7) using a star pattern (Fig.10-13) with torque 22 Nm (16.2 ft.lb.),
and measure the difference in distance of individual blade tips from marking (see Fig.
10-14).
Fig. 10-13: Bolt tightening sequence
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PiperSport
(h) The difference can be max. 1.5 mm (0.06 in). Possible bigger differences can be
corrected by repetition the procedure from point (d) or (f).
Fig. 10-14: Check of axial propeller running-out
(i) Secure bolt heads (7, Fig. 10-12) by lockwire (see 15.8.2).
(j) Put the propeller spinner (1) on the propeller and attach it with bolts (11) with washers
(12).
(k) Install spark plugs to the engine. Tighten up with torque 20 Nm (15 ft.lb.); connect the
battery.
10.3.5
SR3000 propeller removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13
-
screwdriver
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) As necessary, unscrew the screws (4, Fig. 10-15) with the washers (5) and remove
the propeller spinner (3).
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(c) Unscrew and remove the nuts (8) and take out the propeller from the propeller flange
(9).
(d) Put the protective covers on the propeller blades and store the propeller on a safe
place so that no damage can occur.
6
7
8
9
1
2
3
4
5
Carbon brush housing
Drive bushing (6 pcs.)
Nut (6 pcs.)
Propeller flange
Propeller
Propeller spinner
Slip ring
Screw (8 pcs.)
Washer (8 pcs.)
Fig. 10-15: SR 3000 propeller removal / installation
10.3.6
SR3000 propeller installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13
-
screwdriver
NOTE:
For detailed information refer to Operator´s Manual Electrical Adjustable
Aircraft Propeller SR 3000.
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) Check the contacting areas of the propeller flange (9, Fig. 10-15) and the propeller.
Clear of all impurities.
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(c) Remove protective covers from the propeller blades and carry out visual check of the
propeller integrity and condition.
(d) Loose the screws of the carbon brush housing flange and shift the carbon brush
housing (6) to its rear position.
(e) Gently push the propeller (1) to the propeller flange (9) by hand and screw the nuts (8).
(f) Secure the airplane against its movement (see 14.5).
(g) Tighten the nuts (7) using a star pattern (see Fig.10-13) with torque 22 Nm (16.2 ft.lb.).
(h) Adjust the carbon brush housing according to Fig. 10-16. Turn the propeller by hand
and check that the carbon brushes seat properly in the centers of the slip ring, and
makes contact with its entire surfaces.
Fig. 10-16: Carbon brush housing adjustment
(i) As necessary, put the propeller spinner (3, Fig. 10-15) on the propeller and attach it
with bolts (4) with washers (5).
(j) Install spark plugs to the engine. Tighten up with torque 20 Nm (15 ft.lb); connect the
battery.
10.3.7
2A0R5R70EN propeller removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13, No. 16 (5/8”)
-
Allen wrench size No. 6
-
screwdriver
-
cutting pliers, pliers
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WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
NOTE:
For propeller removal two persons are requested.
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) Unscrew the screws (13, Fig. 10-17) and remove the propeller spinner (6).
(c) Hold the blade (5); unscrew and remove the bolts (7), washers (8), hub clamp half (2),
blades (5) and pitch cylinder (3).
(d) Put the protective covers on the propeller blades and store the blades on a safe place
so that no damage can occur.
(e) Unscrew the nuts (16), remove the washers (8) bolts (10), bushings (9; 15), hub
mount half (1), spinner flange (1) and spacer (14).
1
2
3
4
5
6
7
8
Hub mount half
Hub clamp half
Pitch cylinder
Pitch stop
Propeller blade
Propeller spinner
Bolt (6 pcs.)
Lock washer (36 pcs.)
9
10
11
12
13
14
15
Locknut (6 pcs.)
Bolt (6 pcs.)
Propeller flange
Spinner flange
Screw (6 pcs.)
Spacer
Drive bushing (6 pcs.)
Fig. 10-17: 2A0R5R70EN propeller removal / installation
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10.3.8
SportCruiser
PiperSport
2A0R5R70EN propeller installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13, No. 16 (5/8”)
-
Allen wrench size No. 6
-
screwdriver
-
cutting pliers, pliers
NOTE:
For detailed information refer to EZ-Pitch Composite Aircraft Propeller
Installation and Operation Instructions (Doc. No. comp-ac-cf-rev-1a).
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
NOTE:
For propeller removal two persons are requested.
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) Check the contacting areas of the spacer (14, Fig. 10-17), propeller flange (11) and
hub halves (1; 2). Clear of all impurities.
(c) Remove protective covers from the propeller blades and carry out visual check of the
propeller part condition.
(d) Place the spinner flange (12), the hub mount half (1) and spacer (14) on the engine
propeller flange (11) (vertical orientation of the hub is recommended).
(e) Insert drive bushings (15) through the back face of the propeller flange and into the
hub mount half (1). Check for proper bushing and pilot stub fit into the hub mount half.
The hub must sit flush on the mounting flange.
(f) Place washers (8) on bolts (10) and insert into the mounting holes inside the hub
mount half (1). Place lock washers (8) and nuts (9) on the bolt and tighten the bolts
using a star pattern with torque 22 Nm (16.2 ft.lb) (see Fig. 10-18).
Fig. 10-18: Bolt tightening sequence
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CAUTION:
THE HUB MUST SIT FLUSH AGAINST THE MOUNTING FLANGE. BOLT
BREAKAGE WILL OCCUR IF NOT FLUSH.
(g) Insert the pitch cylinder (3, Fig. 10-17) into the hub mount half (1), aligning the blade
pin slots with the hub barrels. Each blade has a round side and a flat side, with the
round side facing forward into the wind. Insert one blade (5) at a time into the hub
mounting half (1), taking care to insert the blade pitch pin into the blade pin slot, then
rotating the blade shank fully into the hub.
(h) Place the hub cover half (2) over the blades. Place washers (8) on bolts (7) and insert
into the hub cover half (2). Hands tighten the bolts (7) into the threaded clamp
bushings, taking care to maintain an even gap between hub halves on all sides. Grasp
each blade shank and firmly pull outwards to seat each blade in the hub.
(i) Set blade pitch by grasping each blade shank and twisting the blades in opposite
directions. Align the index mark on the pitch cylinder with the appropriate pitch setting
(1, 2, 5) on the hub, as indicated the propeller manual.
(j) Using a torque wrench and rotating from bolt to bolt, tighten the bolts the bolts using a
star pattern with torque 22 Nm (16.2 ft.lb.) (see Fig. 10-18), Check the blade pitch
setting for rotation away from your desired pitch setting. Once properly torqued, a
small gap may remain between hub halves. Check the propeller blades for track (see
Fig. 10-14). The blades should track within 1/8” (3.175 mm) of each other at the tip.
Setting the pitch accurately is more important than track from blade to blade.
(k) Install spark plugs to the engine. Tighten up with torque 20 Nm (15 ft.lb.); connect the
battery.
(l) Run the propeller for approximately 5 minutes at 50% of the desired rpm. Check the
clamping bolts to see if they have lost torque. If they have, it is because the blades
have firmly seated themselves. Tighten again to the proper torque.
Note:
This torque value should be checked after the first 5 hours of operation and
every 25 hours thereafter.
(m) Put the propeller spinner (6, Fig. 10-17) on the propeller and attach it with bolts (13).
10.3.9
3B0R5R68C propeller removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13
-
Allen wrench size No. 6
-
screwdriver
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
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(b) Unscrew the screws (10, Fig. 10-19) with the washers (11) and remove the propeller
spinner (2).
(c) Unscrew and remove the nuts (6), the washers (7) and take out the propeller (1) along
with the spinner flange (9) and spacer (3) from the propeller flange (12).
(d) Put the protective covers on the propeller blades and store the propeller on a safe
place so that no damage can occur.
1
2
3
4
5
6
Propeller
Propeller spinner
Spacer
Drive bushing (6 pcs.)
Bolt (6 pcs.)
Nut (6 pcs.)
7
8
9
10
11
12
Lock washer (36 pcs.)
Spacer bushing (6 pcs.)
Spinner flange
Screw (6 pcs.)
Washers (6 pieces)
Propeller flange
Fig. 10-19: 3B0R5R68C propeller removal / installation
10.3.10
3B0R5R68C propeller installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13
-
Allen wrench size No. 6
-
screwdriver
NOTE:
For detailed information refer to Sensenich Three Blade Composite Aircraft
Propeller Installation and Operation Instructions for Rotax Engines (Doc. No.
3b0r5).
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WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Disconnect the battery and remove upper line of spark plugs from the engine.
(b) Check the contacting areas of the propeller flange (12, Fig. 10-19), propeller (1) and
spacer (3). Clear of all impurities.
(c) Remove protective covers from the propeller blades and carry out visual check of the
propeller integrity and condition.
(d) Check out possibly adjust the blades pitch of propeller according to the propeller
manual.
NOTE:
Propeller pitch is factory set to No. 4.
(e) Insert bushings (8) into the propeller hub from the back side.
(f) Place washers (7) on the bolts (5) and insert the bolts through the assembled
propeller hub.
NOTE:
Each washer (7) works in pairs with the “ramped” sides facing each other.
No other washers may be used in combination with those washers.
(g) Insert bushings (4) into the engine flange (12) from the back side, protruding into the
spacer.
(h) Place spinner flange (9), spacer (3) and the assembled propeller (1) on the propeller
mounting flange (12). The hub must sit flush on the mounting flange.
CAUTION:
THE HUB MUST SIT FLUSH AGAINST THE MOUNTING FLANGE. BOLT
BREAKAGE WILL OCCUR IF NOT FLUSH.
(i) Place washers (7) on the bolt threads (5) and hand thread the nuts (6) up to the
plastic stops.
(j) Using a calibrated torque wrench, torque the bolts (5) evenly using a star pattern.
Tighten the bolts in several increments up to full torque, such as 50 %, 75 %, and full
torque 24 – 27 Nm (18 – 20 ft.lb).
(k) Check the propeller blades for track. The blades should track within 3/16” (4.8 mm) of
each other at the tip (see Fig. 10-14). Setting the pitch accurately is more important
than track from blade to blade.
(l) Install spark plugs to the engine. Tighten up with torque 20 Nm (15 ft.lb.); connect the
battery.
(m) Run the propeller for approximately 5 minutes at 50% of the desired rpm. Check the
clamping bolts to see if they have lost torque. If they have, it is because the blades
have firmly seated themselves. Tighten again to the proper torque.
Note:
This torque value should be checked after the first 5 hours of operation and
every 25 hours thereafter.
(n) Put the propeller spinner (2, Fig. 10-19) on the propeller and attach it with screws (10)
and washers (11).
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10.3.11
SportCruiser
PiperSport
Air intake system removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.8, No.10
-
screwdriver
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Remove the upper engine cowling.
(b) Disconnect the control cable (13, Fig. 10-20) from the air intake changeover lever (14)
and from the holder.
(c) Remove the hose fasteners (4; 5; 16) and disconnect hoses (2; 3), drain hoses (6; 7),
and air hoses (8; 15).
(d) Unscrew nut (12), remove washer (11), silentblock (9), and disconnect the bracket
(10).
(e) Remove the airbox from the engine and store it.
10.3.12
Air intake system installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.8, No.10
-
screwdriver
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Attach the outlet pipe of the airbox (1, Fig. 10-20) to the hoses (2) on the carburetor
inlet necks; secure it by means of the hose clamps (4).
(b) Fix the airbox by means of the bracket (10), silentblock (9), nut (12) and washer (11)
to the firewall.
(c) Connect the air intake hoses to the airbox (1), one (8) from the air filter on the lower
engine cowling and the other (15) from the heat exchanger; secure them by hose
clamps (4).
CAUTION:
DO NOT CONFUSE THESE HOSES!
(d) Connect drain hoses (6) to the airbox (1) and the drain hoses (7) to the drip trays
under carburetors - lead them on the engine mount in direction down the airplane and
secure them by hose fasteners (5; 16). (fix them by cable ties on the engine mount).
(e) Connect the carburetors control cable of (13) to the lever (14); adjust function of
carburetors heating knob.
(f) Install the upper engine cowling.
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1
2
3
4
5
6
7
8
CHAPTER 10 – POWERPLANT
Airbox
Hose connecting airbox / carburetor
Hose
Hose clamp
Cable tie
Drain hose
Drain hose
Air hose – cold air
9
10
11
12
13
14
15
16
Silentblock
Bracket
Washer
Nut
Control cable
Air intake changeover lever
Air hose – preheated air
Hose clamp
Fig. 10-20: Air intake system removal / installation
10.3.13
Exhaust system removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13
-
pliers
-
small wire hook (spring removal/assembly jig)
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Remove engine cowlings.
(b) Disconnect air hoses from the heat exchanger (8, Fig. 10-20) (see 10.3.11).
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(c) Remove lockwire securing the springs (9, Fig. 10-21).
(d) Remove the springs (9) and dismantle the heat exchanger (8) from the muffler (1).
(e) Remove the springs (6) from the individual exhaust tubes (2; 3; 4; 5) and carefully
remove muffler (1).
(f) Unscrew nut (7) and remove exhaust tubes (2; 3; 4; 5) from the necks on the engine.
1
2
3
4
5
Muffler
Exhaust tube 1
Exhaust tube 2
Exhaust tube 3
Exhaust tube 4
6
7
8
9
Spring
Locknut
Heat exchanger
Spring
Fig. 10-21: Exhaust system removal / installation
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PiperSport
10.3.14
CHAPTER 10 – POWERPLANT
Exhaust system installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.13
-
pliers
-
small wire hook (spring removal/assembly jig)
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Install the exhaust tubes (2; 3; 4; 5, Fig. 10-21) to the engine necks.
Mind a proper arrangement, each tube is designed for specific necks.
Screw the nuts (7) on the bolts of the engine exhaust necks, do not tighten the nuts.
(b) To all muffler ball joints apply heat resistant lubricant (e.g. Loctite Antiseize).
(c) Install the muffler (1) to the exhaust tubes (2; 3; 4; 5) and secure the tubes by means
of the springs (6); secure springs with the lockwire (see 15.8.2).
(d) Gradually tighten all nuts (7) of the flanges on the engine necks – tightening torque 12
– 20 Nm (9 – 14 ft.lb)..
NOTE:
Ensure the sufficient space between the exhaust pipes and the other
installed parts.
(e) Put on muffler (1) heat exchanger (8) and secure it by means of springs (9).
(f) Install air hoses on the heat exchanger (see 10.3.12).
(g) Install engine cowlings.
10.3.15
Oil cooler removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.19, No.30
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Remove the upper and lower engine cowling.
(b) Drain oil from the oil system (see 10.5.1).
NOTE:
It is also possible to pump oil from the cooler to the oil tank. You can do it by
manual running the engine by means of the propeller, whereas from the oil
tank you will remove the hose leading to the oil cooler.
(c) Remove lockwire securing banjo bolts (6, Fig. 10-22).
(d) Loose hose clamps (9), and disconnect hoses (8) from the banjo fittings (5).
(e) Remove banjo bolts (6), banjo fittings (5), and sealing rings (7) from the oil cooler
necks.
(f) Unscrew nuts (4), remove the upper pairs of washers (2; 3), and cooler (1).
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1
2
3
4
5
Oil cooler
Washer
Rubber washer
Nut
Banjo fitting
SportCruiser
6
7
8
9
Banjo bolt
Sealing ring
Hose
Hose clamp
Fig. 10-22: Oil cooler removal / installation
10.3.16
Oil cooler installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.19, No.30
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Set the oil cooler (1, Fig. 10-22) to the bracket (10) and on the cooler necks install the
upper pairs of washers (2; 3), and gradually tight the nuts (4).
(b) Install the banjo fittings (5), screw the banjo bolts (6) with sealing rings (7) and secure
these bolts with the lockwire (see 15.8.2).
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(c) Install hoses (8) on the banjo fittings (5) and secure them with hose clamps (9).
(d) Fill the oil system with oil (see 10.5.1) and check oil system tightness.
(e) Install the lower and upper engine cowling.
10.3.17
Water cooler removal
Type of maintenance: line
Authorization to perform:
-
Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.10, No.17
-
screwdriver
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Remove the upper and lower engine cowling.
(b) Drain the cooling liquid from the cooling system (see 10.5.2).
(c) Remove the hose clamps (9, Fig. 10-23) and disconnect hoses (10; 12) from the
cooler outlets.
(d) Loose the bolts (7).
(e) Remove four nuts (5), washers (6) and cooler (1).
(f) As necessary, remove the silentblocks (4) from the cooler.
10.3.18
Water cooler installation
Type of maintenance: line
Authorization to perform:
-
Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.10, No.17
-
screwdriver
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) As necessary, screw the silentblocks (4, Fig. 10-23) to the cooler.
(b) Put the cooler on the lower (2) and the upper brackets (3).
(c) Install the washers (6), screw and tighten the nuts (5); tighten the bolts (7).
(d) Install hoses (10) on the cooler outlets and secure them with hose clamps (9).
(e) Fill the cooling system with cooling liquid (see 10.5.2) and check system tightness.
(f) Install the lower and upper engine cowling.
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1
2
3
4
5
6
7
Cooler
Lower bracket
Upper bracket
Silentblock
Cap nut
Lock washer
Bolt
SportCruiser
8
9
10
11
12
13
Washer
Hose clamp
Hose
Tube
Hose
Tube
Fig. 10-23: Water cooler removal / installation
10.3.19
Throttle and choke control levers removal
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.14
-
Allen wrench size No. 2
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-
screwdriver
-
cutting pliers
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Remove the cover (11, Fig. 10-24) from the middle channel.
(b) Remove the upper engine cowling.
(c) Disconnect the throttle (7) and choke (9) cables from carburetor levers (12; 3) and
from the throttle and choke control levers (1).
(d) Unscrew the nuts (5), remove washers (6), bolts (2), bushings (3; 4) and the throttle
control lever witch choke (1) from the middle channel.
1
2
3
4
5
6
7
Throttle control lever with choke
Bolt
Bushing
Bushing
Nut
Washer
Throttle cable
8 Throttle bowden
9 Choke cable
10 Choke bowden
For information:
11 Cover
12 Choke lever
13 Throttle lever
Fig. 10-24: Throttle control lever
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10.3.20
SportCruiser
PiperSport
Throttle and choke control levers installation
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.14
-
Allen wrench size No. 2
-
screwdriver
-
cutting pliers
WARNING: ENGINE IGNITION MUST BE SWITCHED OFF!
(a) Set the throttle control lever with choke (1, Fig, 10-24) into the middle channel.
(b) From one side shift the bolts (2) into the holes on the middle channel side.
(c) Gradually put first bushings (3), throttle control lever with choke (1) and second
bushings (4) on the wheel bolts (2) according to the figure.
(d) Install washers (6), screw and tighten nuts (5).
(e) Connect the throttle (7) and choke (9) cables to the throttle control lever with choke
(1), and to the carburetor levers (12; 13).
(f) Install the cover (11) on the middle channel.
(g) Install the upper engine cowling.
(h) Check for continuous travel of the throttle and choke control lever.
(i) Adjust the throttle / choke control (see 10.4.8, 10.4.9).
10.3.21
Carburetors heating knob removal
Type of maintenance: line
Authorization to perform:
-
Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.8, No.14
-
screwdriver
-
cutting pliers
(a) Remove the upper engine cowling.
(b) Disconnect the control cable (13 Fig. 10-20) on the changeover lever (14) of the air
intake.
(c) Remove the inner nut (1, Fig. 10-25) and pull out the knob (2) with the flexible housing
(3) from the firewall and instrument panel.
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1 Nut
2 Heating control knob
3 Flexible housing
Fig. 10-25: Carburetors heating knob
10.3.22
Carburetors heating knob installation
Type of maintenance: line
Authorization to perform:
-
Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No.8, No.14
-
screwdriver
-
cutting pliers
(a) Put the flexible housing (3, Fig. 10-25) with knob (2) into the hole in the instrument
panel and firewall from behind and fasten it from both sides of the instrument panel by
the nuts (6).
(b) Fasten the knob from both sides of the instrument panel by the nuts (1).
(c) Connect the control cable (13 Fig. 10-20) on the changeover lever (14) of the air
intake.
(d) Adjust carburetors heating control (see 10.4.10).
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10.4 Check / Adjustment
10.4.1
Engine test
CAUTION:
THE PERSON PERFORMING THE ENGINE TEST MUST BE MECHANIC
WITH A VALID CERTIFICATE AND WITH REGISTERED ENGINE TYPE
ROTAX 912 ULS. IN THE COURSE OF THE WHOLE TEST AN AIRCRAFT
MECHANIC WHO IS FAMILIARIZED WITH THE AIRCRAFT TYPE
SPORTCRUISER / PIPERSPORT MUST BE PRESENT.
(a) Perform the test out of the buildings at the place assigned for performing engine tests
in broad daylight.
(b) Test place must be equipped with extinguisher which is suitable for extinguishing
burning liquids and electrical installation.
(c) Brake the airplane and put the chocks under the landing gear wheels.
(d) Before performing engine test, carry out engine and propeller preflight check in the
range shown in the POH, Section 4.1, and the Rotax Operator’s Manual, Section 3.
(e) Start the engine according to the POH, Section 4.2 and the Rotax Operator’s Manual,
Section 3.
- activate starter for max.10 sec. only, followed by a cooling period of 2 min.
- as soon as engine runs, adjust throttle to achieved smooth running at
approximate 2,500 rpm
- check if oil pressure has risen within 10 sec. and monitor oil pressure
NOTE:
If oil pressure do not rise within 10 sec. above min. pressure 0.8 bar (12 psi),
switch off the engine. Is admissible max. oil pressure 7 bar (102 psi) for a
short period at cold start. Fuel pressure has been in range from 0.15 to 0.4
bar (2.2 to 5.8 psi).
(f) Engine warm up according to the POH, Section 4.2.3 and the Rotax Operator’s
Manual, Section 3.
As soon as oil pressure will be in range from 2 to 5 bar (29 to 73 psi) start warming up
period at 2,000 rpm for approx. 2 minutes, continue at 2,500 rpm, duration depending
on ambient temperature, until oil temperature reaches 50°C ( 122°F ).
(g) Choke – during engine warm up - OFF.
NOTE:Watch engine instruments and record the values of oil pressure, oil temperature
and head cylinder temperature into the Engine test report, see the Tab. 10-1.
(h) Ignition check:
Engine speed....................... 4,000 rpm
Ignition switch ...................... switch from position BOTH to L, record rpm drop
Ignition switch ...................... switch from position BOTH to R, record rpm drop
NOTE:
rpm drop between position BOTH and L or R must not exceed 300 rpm.
Mutual difference between ignition circuits L and R must not exceed 115
rpm. Write down results into the engine test report, see Tab. 10-1.
(i) Test of max. RPM on the ground:
Throttle ................................ MAX
NOTE:
Record max. rpm into the engine test report, see Tab. 10-1.
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ENGINE TEST REPORT
Aircraft
Registration
Engine
ROTAX
Type
Propeller
Serial No.
912 ULS2
Serial No.
Type
Serial No.
Activity
Set down values
Measured values
Starting up the engine
0.8 bar (12 psi)
1.
Min. oil pressure up to 10 sec.
2.
Max. oil pressure*
7 bar (102 psi)
3.
Min. fuel pressure
0.15 bar (2.2 psi)
4.
5.
6.
7.
Increase rpm as soon as oil pressure
reaches
Warming up the engine at
2,000 – 2,500 rpm
Voltage
Engine test
2 bar (29 psi)
smooth running
12.4 – 14.4 V
50°C (122°F)
Min. oil temperature
2-5 bar (29-73 psi)
8.
Oil pressure
9.
Max. cylinder head temperature CHT
135°C (275°F)
10.
Max. coolant temperature CT ****
120°C (248°F)
11.
Rpm drop between ignition position
BOTH and L/R at 4,000 rpm
12.
Acceleration
13.
Max. ground engine speed
max. 300
(115 rpm**)
2 – 3 sec.
***
14.
Idle
Defects:
***
*
**
During cold start for a short term only
***
Max. ground engine speed and idle varies according to the type of propeller:
Klassic 170/3/R max. 5,000 ± 100 rpm; idle 1,650 ± 5 rpm
SR3000/2W
max. 5,700 ± 100 rpm; idle 1,700 ± 5 rpm
3B0RTR68C
max. 4,950 ± 100 rpm; idle 1,650 ± 5 rpm
RPM drop between ignition position BOTH and position L or R must not exceed 300 rpm. Mutual difference
between left (L) and right (R) ignition circuit must not exceed 115 rpm.
**** With the change to a new cylinder heads design (applicable for ROTAX 912 ULS2 engines from S/N 6 781
410 inclusive and for 912 S2 engines from S/N 4 924 544 inclusive, or on all engines with type designation
followed by suffix-01, or on all engines which have been later equipped with the new cylinder heads design
of P/N 413185 at cylinder head position 2/3), no longer the cylinder head temperature is measured, but the
coolant temperature.
Coolant temperature is displayed as “CHT” on Dynon EMS–120 display.
Conclusion
Complying – Non-complying
Complying if the measured values are not out of the range of the prescribed values.
Elaborated by:
Signature:
Date:
Checked by:
Signature:
Date:
Tab. 10-1: Engine test report
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CHAPTER 10 – POWERPLANT
10.4.2
Klassic 170/3/R propeller - inspections, repairs, works
10.4.2.1
Summary of propeller periodical inspection: (see also 2.3.2. for details)
•
•
•
•
•
Inspection of propeller after the first 25 hours of operation.
Inspection of propeller after 100 hours of operation or 12 months *,
Inspection of propeller after 500 hours of operation or 24 months *,
Inspection of propeller after 1000 hours of operation or 60 months *,
Inspection of propeller after 2,000 hours of operation or 120 months (lifetime limit for
propeller blades) *,
*) hours of operation or months, whichever comes first.
Note: Inspection/overhaul of propeller must also be performed in the following cases:
- The propeller has contacted the ground and/or foreign object,
- The propeller has been overspeed (see max operating RPM in User’s Manual),
- The propeller has been damaged
- The propeller has no record of operating hours and/or calendar months.
10.4.2.2
Prescribed inspection works:
Note: Inspection of propeller after the first 25 and after 100 hours of operation may be
performed by aircraft engineer (AML ICAO, AML part 66, etc.).
Inspection/overhaul after 500, 1000 and 2000 hours of operation may be performed
by manufacturer or his authorized service organization only.
All works/operations must be performed in accordance with the respective maintenance
manuals, contact the manufacturer or authorized service organization for details.
Inspection of propeller after the first 25 hours of operation (see also the Operator’s
manual UM-07 or relevant instructions on the Woodcomp websites for details)
(a) Remove the propeller spinner.
(b) Visually check of propeller surface – propeller must not have apparent damages,
breakings and deformations.
(c) Check the propeller blades pitch setting and correct if needed, see 10.4.2.3.
(d) Cut off the lock wire securing the fixing bolt heads.
(e) Tighten the fixing bolts (Fig. 10-26) M8 by moment 22 Nm (16.2 ft.lb.).Tighten also the
fixing bolts of spacer In case it is used..
(f) Tighten the bolts M6 on spokes of the hub by moment 10 Nm (7.4 ft.lb.).
Fig. 10-26: Torque moments
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(g) Secure fixing bolt heads by lock wire (see 15.8.2).
(h) Install the propeller spinner.
Inspection of propeller after 100 hours of operation hours of operation or 12
months, whichever comes first
(a) Remove the propeller spinner.
(b) Cut off the lock wire securing the fixing bolt heads.
(c) Check the propeller blades pitch setting and correct if needed, see 10.4.2.3.
(d) Tighten the fixing bolts (Fig. 10-26) M8 by moment 22 Nm (16.2 ft.lb.)
(e) Tighten the bolts M6 on spokes of the hub by moment 10 Nm (7.4 ft.lb.).
(f) Inspect firm seating of all blades, - blades must not show any signs of movement or
play in the hub.
(g) Visually inspect the blades for damage due to a direct strike (rock, bolt, etc.) or traces
of damage or deformation. As a damage, it is not mentioned the usual operational
wear (by friction, operation, washing, etc). Relevant findings of failures must not be of
a higher extent than stated in the Operator’s manual UM-07, see the latest issue on
the WoodComp websites. The small failures stated in the Operators manual can be
repaired by the aircraft engineer (AML ICAO, AML Part 66, etc.).
(h) If the inspection doesn’t bring satisfactory results, stop using the propeller immediately
and have the propeller inspected/repaired by authorized service organization or by the
manufacturer.
(i) If the inspection is without findings, secure fixing bolt heads by lock wire (see 15.8.2).
(j) Install the propeller spinner.
Inspection of propeller after 500 hours of operation
Remove the propeller and send to the manufacturer or his authorized organization
Inspection of propeller on 1,000 hours of operation
Remove the propeller and send to the manufacturer or his authorized organization
Inspection of propeller after 2,000 hours of operation (lifetime limit for propeller
blades)
Remove the propeller and send to the manufacturer or his authorized organization
Note: checking of propeller after 500, 1000 and 2000 hours of operation is performed at
manufacturer or his authorized organization.
Small repairs of blades which can be performed by an aircraft engineer
(AML ICAO, AML Part 66, etc.). See the Woodcomp Operator’s manual UM-07 before
repair.
Repair of blades.
It is allowed to repair the failures like small scratches and notches appearing on the
propeller blade in area ranging from radius R=250 mm towards the blade tip, not more
than 5 pieces in one blade. Failures in the root blade area are allowed to be repaired by
the manufacturer or authorized service organization only.
Maximum acceptable depth of damaged leading or trailing propeller edge is 2 mm, while
the distance between the repaired spots may be not less than 80 mm. The spots length
shall be not more than 30 mm.
Maximum acceptable depth of damaged sucking or pressure blade side is 0,7 mm, while
the distance between the repaired spots may be not less than 100 mm and the spots may
be not larger than 1 cm2.
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Instructions for repair of blades:
1.
2.
3.
4.
5.
Clean and dry the damaged area carefully.
Grind the damaged place with help of a soft rasp or sand paper.
Seal the repaired area with cement on the epoxy basis.
Grind the surface after the cement is cured.
Re-paint the affected surface with polyurethan email.
Repair of hub and metal propeller parts.
Repairs of hub and metal propeller parts are strictly prohibited !!!
Repair of spinner and spinner plate.
Only repairs relating to small surface grooves on the outside spinner part or spinner plate
with max. depth of 0,5 mm are allowed.
Repairs of damaged or corrosion affected rivet nuts on the spinner plate are not allowed.
Instructions for repair of spinner or spinner plate:
1. Clean and dry the damaged area carefully.
2. Grind the damaged place with help of a soft rasp or sand paper.
3. Re-paint locally the groove with polyurethan email
Replacement of self-adhesive polyurethan tape.
Instructions for replacement:
1. Tear down the original tape carefully ( a moderate pre-heating of the tape with help
of hair dryer is recommended)
2. Use technical petrol and clean and degrease the blade leading edge. It is very
important to remove all the rests of adhesive from the old tape.
3. Strip off the protective foil from the new tape carefully, so that you do not touch or
contaminate the gluing side of the tape.
4. Touch the tape to the prepared blade surface.
5. Squeeze out air bubbles with help of a plastic spattle or perforate the tape with a
pin and apply a roller or fingers to push the air away. Do not use a blade or knife to
perforate the tape !!
6. In terms of operation the propeller is ready for use not sooner than after 24 hours
since the tape was touched to the surface and the adhesive has became
hardened.
10.4.2.3
Klassic 170/3/R propeller blades pitch setting
(a) Pull out each blade to it´s outer limit-away from the hub as there is an 1.5 mm (1/16″)
movement range in its lock for expansion.
(b) Use protractor to blades pitch adjustment (digital with an alternative zero or ordinary
bubble type). Place protractor 50 mm (2 in) from the tip of each blade. You can also
use wedges and set the pitch on a flat level table before mounting the propeller on
engine.
(c) Set blades pitch to 17.5° ± 0.5°.
(d) Tighten the bolts in this sequence: first tighten the bolts M6 on spokes of the hub by
moment 10 Nm (7.4 ft.lb.) then tighten the fixing bolts M8 by moment 22 Nm
(16.2 ft.lb.) (see Fig. 10-26).
(e) Secure fixing bolt heads by lock wire (see 15.8.2).
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10.4.3
SR3000 propeller inspections, works.
10.4.3.1
Summary of propeller periodical inspection:
•
Inspection of propeller after 25 hours of operation, performed by authorized mechanic.
•
Inspection of propeller on 150 hours of operation and following after each next 150
hours of operation. Inspection is performed by authorized mechanic.
NOTE:
10.4.3.2
Inspections after 300, 600 and 900 hours of operation are performed by the
authorized service or propeller manufacturer; inspections after 1,200 and
1,500 hours of operation are performed by the propeller manufacturer – see
Operator′s Manual - Electrical Adjustable Aircraft Propeller SR3000.
Prescribed inspection works:
Inspection of propeller after 25 and on 150 hours of operation and following after
each next 150 hours of operation
NOTE:
In order to inspect perfectly all items, it is necessary at first to carry out the
complete cleaning or washing of the all parts surfaces of the propeller.
(a) Check propeller blades for:
•
Surface damage of varnish, including evaluation of the further operational capability.
•
Damage of protective strips on leading edges.
•
Mechanical damage of blades influencing the propeller safety operation.
•
Occurrence of cracks at propeller root.
(b) Remove propeller spinner and check surface with attention to cracks at bottom holes
for attaching screws.
(c) Check slip ring for:
•
Attachment.
•
Damage and el. conductivity of the slipways.
•
Strength of joint of MK with a hub checked by moment 25 Nm (18.4 ft.lb.).
(d) Check propeller hub for:
•
Common state of surface.
•
Strength of connection of the upper part of hub to its lower part joint by bolts M6
checked by moment 10 Nm (7.4 ft.lb.).
•
Fixation of body to hub by bolts M5
•
Occurring permeability of grease in joint and around the blades roots.
•
Determine the axial clearance of blades by means of expanding cone.
(e) Check electrical equipment for:
•
Attachment and isolation of cables.
•
Check by hearing the operation of complete power unit.
•
Attachment of working and nonworking cams.
•
Wear of electrical switches.
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(f) Check by means of laser or electronic (digital) protractor the mechanical radial
clearance on the individual blades. This clearance must not exceed 2 degrees.
(g) According to the data of protocol for given propeller check the function of:
•
End switches and their operation at specified angles; the difference must not
exceed ± 20 angle minutes.
(h) Set the mean values of the angle range as a mean value for static balancing.
(i) Unconditionally eliminate the shortcomings, which could be a potential danger for the
safe operation of the propeller.
(j) Evaluate the capability of propeller for further operation.
(k) Install propeller spinner.
10.4.4
3B0R5R68C / 2A0R5R70EN propeller inspections
10.4.4.1
Summary of propeller periodical inspection:
•
Annual inspection of the propeller.
•
Major periodic inspection on 2,000 hours of operation.
NOTE:
10.4.5
Inspections are described in the propeller manufacturer documentation Sensenich Three/Two Blade Composite Aircraft Propeller - Installation and
Operation Instructions for Rotax Engines, Instructions for Continued
Airworthiness.
Adjusting throttle control
(a) Pull the throttle control to the stop. The throttle lever on the carburetor (5, Fig. 10-11)
must be on the stop. The bowden must be supported in the terminals.
(b) Release the nut on the control lever (5) and take up any slack on the cable and
tighten up the nut.
CAUTION:
CONTROL CABLE SHOULD NOT BE TOO TIGHT FOR THE REASON OF
A POSSIBLE DEFORMATION OF THE CONTROL LEVER ON THE
CARBURETOR.
(c) Check again whether the controller and the lever on the carburetor are on the stops. If
not, perform adjusting by means of adjustable terminals on bowdens.
(d) In order to prevent the bowdens at the carburetor from shifting out from the terminals,
secure the bowdens with lockwire. Mark all bolted joints with red paint.
10.4.6
Adjusting choke control
(a) Set the choke lever to the stops position and put it back about 3 mm (1/8 in). The
lever of choke control on the carburetor (6, Fig. 10-11) must be on the stop. The
bowden must rest on the terminals.
(b) Release the bolt on the lever of choke control (6), slightly loosen the cable and tighten
up the bolt.
(c) Check again if the choke lever and the lever on the carburetor are on the stops. If not,
carry out adjustment by adjustable bowden terminals.
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(d) To prevent the bowdens at the carburetor from shifting out of the terminal, secure the
bowdens with lockwire. Mark all bolted joints with red paint.
10.4.7
Adjusting carburetors heating control
(a) Push in the carburetor heating knob to the stop and pull it out by about 3 mm (1/8 in).
The changeover lever (14, Fig. 10-20) on the air intake must be on the stop. The
bowden must rest on the terminal.
(b) Release the bolt on the changeover lever (14), slightly stretch the cable and tighten up
the bolt.
(c) Check again whether the knob and the lever on the air intake are on the stops. If not,
carry out adjustment by adjustable bowden terminals.
(d) To prevent the bowdens from shifting out of the terminal, secure the bowdens with
lockwire. Mark all bolted joints with red paint.
10.4.8
Checking exhaust system
WARNING: CHECK OF EXHAUST SYSTEM VERY CAREFULLY. THE BURST OR
LEAKY EXHAUST CAN EXPOSE THE CREW TO DANGER PRESENTED
BY CARBON MONOXIDE OR CAN RESULT IN ENGINE POWER LOSS,
POSSIBLY FIRE.
Check the exhaust system for cracks. Pay special attention to the following areas:
•
muffler in the area of the input and the output pipe and the collector head
•
all welds and their immediate surrounding
•
carefully check all areas showing local overheating caused by exhaust gases
•
remove the heat exchanger and check muffler area located under it
•
check the whole exhaust pipe between the engine and the muffler including its
attachment to the engine
•
check outlet pipe from the muffler
•
check retaining springs for cracks.
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10.5 Exchanges / Service information
10.5.1
Exchange / Refilling oil
Refer to the Rotax Maintenance Manual, Chapter 12-20-00, Section 11 Lubrication.
NOTE:
Recommended kinds of oil are mentioned in the Rotax Operator's Manual,
Section 2.5 Operating media – Lubricants and Rotax Service Instructions SI912-016, latest revision.
Type of oil used by aircrafts manufacturer is shown in section 17.5 Operating Liquids.
Oil volume
Total oil volume in the lubrication system of Rotax 912 ULS2 engine is approximately
3.8 litres (1 US gallon).
Check oil volume preferably after running the propeller by hand in the sense of engine
rotation so that oil can fill in the engine space or operate the engine for 1 minute in idle
mode.
WARNING: SWITCH OFF IGNITION BEFORE MANUALLY TURNING THE ENGINE!
The oil tank is located in the engine compartment and oil dipstick is accessible after
opening the lid on the upper engine cowling (see 10.2.1.2). Oil level must lie between min
and max marks (flattening) on the dipstick and must not drop below min mark.
1 Oil tank
2 Cap
3 Dipstick
Fig. 10-30: Oil volume check
Oil draining
Drain oil from the oil tank by unscrewing the plug (wrench size No.17) on the lower side of
the oil tank. It is possible to drain oil from the engine after unscrewing the plug in the lower
part of the engine at the hose of the return branch of oil flow. It is recommended to drain
oil immediately after engine test or after finishing the operation when oil is sufficiently hot
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and better flows both from the engine and from the tank. Clean the tank before filing it with
new oil - see the Rotax Maintenance Manual.
Refilling oil
Refill oil in the oil tank that is located on the firewall.
Venting of the lubrication system
After short idling, stop engine and replenish oil to max. mark on dipstick. Never overfill
otherwise oil would escape through the vent tube during operation. At oil level inspect, do
not exceed the max. mark.
10.5.2
Exchange / Refilling cooling liquid
Refer to the Rotax Maintenance Manual - Cooling System.
NOTE:
Recommended types of coolant are shown in the Rotax Operator's Manual,
Section 2.3 Coolant, Rotax Installation Manual – Cooling System, Rotax
Service Instructions SI-912-016.
Type of coolant used by aircrafts manufacturer is shown in Section 17.5 Operating liquids.
Cooling liquid volume
Total volume of coolant in the engine is approximately 2.5 litres (0.7 US gallons).
Drainage of cooling liquid
Disconnect the hose supplying liquid from the radiator to the pump (at the lowest point of
the system) and drain cooling liquid into the prepared vessel.
Refilling cooling liquid
Refill cooling liquid into the expansion tank in the engine compartment. In addition to this
there is a overflow bottle which collects cooling liquid in case of engine overheating and is
attached to the fire wall.
10.5.3
Exchange / Check of oil filter
Refer to the Rotax Maintenance Manual, 12-20-00, Section 11 Lubrication.
NOTE:
Carry out at every oil exchange.
Tools needed:
-
wrench size No.10, No.17
-
screwdriver
-
oil filter wrench
(a) Remove engine cowling.
(b) Cut off the cable ties fastening the oil cooler tubes to the engine.
(c) Remove the nuts (2, Fig. 10-31) and the washers (3).
(d) Loosen the bolts (6) and and lift up the brackets (5).
NOTE:
For oil filter removal two persons are requested.
Revision No.: 6
Date of issue: 2016-01-18
10 - 44
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SportCruiser
PiperSport
CHAPTER 10 – POWERPLANT
(e) Pull the cooler (1) so that you obtain access to the oil filter (see Fig. 10-31); hold the
cooler.
(f) Remove used oil filter (7) with oil filter wrench.
(g) Clean the contact surface of the oil pump housing with a clean cloth.
(h) Apply a thin film of engine oil on the gasket of the new oil filter (1).
(i) Install the new oil filter on the engine:
– screw on filter until oil filter gasket is seated solidly
– tighten oil filter with 3/4 turn (270°).
(j) Put the cooler on the lower bracket (4), fit the upper brackets on the cooler; install the
washers (3), screw and tighten the nuts (2) and the bolts (6).
(k) Attach the oil cooler tubes to the engine by means of the cable ties.
(l) Remove the filter insert, cut of the upper and the lower lid of the insert. Remove the
middle part of the insert, disassemble and check for metal chips, foreign corpuscles
and contamination.
CAUTION:
1
2
3
4
IF YOU DETECT AN INCREASED QUANTITY OF METAL PARTICLES
(BRASS OR BRONZE CHIPS OR BEARING ABRASIVE), FIND OUT THE
REASON AND ELIMINATE IT.
Cooler
Cap nut
Lock washer
Lower bracket
5
6
7
Upper bracket
Bolt
Oil filter
Fig. 10-31: Exchange of oil filter
10.5.4
Purging the oil system
Refer to the Rotax Maintenance Manual, Chapter 12-20-00, Section 11 Lubrication and
Rotax Service Instructions SI-912-018 Purging the lubrication system, latest issue.
Date of issue: 2013-06-30
Revision No.:
10 - 45
SportCruiser
SC-AMM-1-0-00
PiperSport
10.5.5
CHAPTER 10 – POWERPLANT
Exchange / Check of air filter
(a) Remove the hose fastener and the bracket attaching the air filter to the left side lower
engine cowling and remove the air filter.
(b) Inspect the air filter and if contaminated, clean it according to instructions in the Rotax
Maintenance Manual, Chapter Chapter 12-20-00, Section 2.
(c) Attach the cleaned or the new filter to the hole on the left side of lower engine cowling
by means of the bracket and hose fastener.
Revision No.:-
Date of issue: 2013-06-30
10 - 46
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CHAPTER 11 – ELECTRICAL SYSTEM
SportCruiser
PiperSport
Contents
11.1 General ................................................................................................................ 11-3
11.2 Description and operation .................................................................................... 11-3
11.2.1
Switches .............................................................................................. 11-5
11.2.2
Switches - circuit breakers .................................................................. 11-6
11.2.3
Circuit breakers ................................................................................... 11-7
11.2.4
Fuses ................................................................................................. 11-10
11.2.5
Generator .......................................................................................... 11-11
11.2.6
Battery ............................................................................................... 11-11
11.2.7
Lighting .............................................................................................. 11-12
11.3 Removal / Installation ........................................................................................ 11-13
11.3.1
Electrical safety ................................................................................. 11-13
11.3.2
Battery removal ................................................................................. 11-13
11.3.3
Battery installation ............................................................................. 11-13
11.3.4
Position / strobe light removal ........................................................... 11-15
11.3.5
11.3.4.1
SportCruiser / PiperSport airplanes up to S/N C0416 ... 11-15
11.3.4.2
SportCruiser airplanes from S/N C0416 ........................ 11-15
Position / strobe light installation ....................................................... 11-15
11.3.5.1
SportCruiser / PiperSport airplanes up to S/N C0416 ... 11-15
11.3.5.2
SportCruiser airplanes from S/N C0416 ........................ 11-16
11.4 Exchanges / Service information ....................................................................... 11-16
11.4.1
Charging the battery .......................................................................... 11-16
11.4.2
Adjusting the optional wing landing light ........................................... 11-19
11.4.3
Exchange of the strobe light discharge tube ..................................... 11-19
Date of issue: 2017-09-15
Revision No.: 9
11 - 1
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 11 – ELECTRICAL SYSTEM
INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
11 - 2
SC-AMM-1-0-00
CHAPTER 11 – ELECTRICAL SYSTEM
11.1
SportCruiser
PiperSport
General
Electrical system of the SportCruiser / PiperSport airplane serves for supplying electrical
current to the instruments.
11.2
Description and operation
The airplane is equipped with 14 VDC electrical installations with grounded negative pole
(see Fig. 11-1). Primary source of electrical energy is formed by the generator. The
secondary source of electrical energy is the battery 12 V, which is located on the firewall. It
is used for starting the engine and in the case of generator failure as a back-up source of
electric energy.
DC voltage is distributed to the individual systems by means of the main busbar. Systems
are protected by circuit breakers which are permanently ON and switches-circuit breakers
which are turning ON as needed. If some of the circuit is overloaded, then the circuit breaker
disconnects the circuit. Some circuits are protected by the fuses.
After switching the MASTER BAT / MASTER switch ON and by turning the ignition key to
the position START the starter is activated. The starter is supplied from the battery before
starting the engine. After starting up the engine and reaching the idle rpm and switching the
MASTER GEN switch ON, the generator starts supplying current to the electrical network
(SportCruiser airplanes from S/N C0416 only).
Information about voltage in the main busbar is indicated by EMS or by the analog voltmeter
on the instrument panel.
NOTE:
Valid wiring diagrams are mentioned in SportCruiser or PiperSport Wiring
Manual. For the early SportCruiser airplanes wiring diagrams refer to
Chapter 16.
Date of issue: 2013-06-30
Revision No.: 11 - 3
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 11 – ELECTRICAL SYSTEM
Fig. 11-1: Electrical system scheme (from S/N C0416)
Revision No.: -
Date of issue: 2013-06-30
11 - 4
SC-AMM-1-0-00
CHAPTER 11 – ELECTRICAL SYSTEM
11.2.1
SportCruiser
PiperSport
Switches
The switches serve for switching (ON/OFF) individual electrical circuits. Every switch is
marked with a placard with designation of the circuit. The switches are located on the left
instrument panel and on the middle channel. The buttons for ailerons and elevator trim are
on the grip of the control stick.
NOTE:
Position of the switch:
I (ON)
The upper half of the switch pushed.
O (OFF)
The bottom half of the switch pushed.
Switches – instrument panel with the EFIS/EMS
Designation
Description
MASTER BAT
Main switch - switch of battery, VHF transceiver, intercom
MASTER GEN
Main switch - switch of generator
EMS
Switch of engine monitoring instrument
AVIONICS
Switch of EFIS, NAV/COM, GPS, XPDR
FUEL P
Switch of electric fuel pump
NAV L
Switch of position lights
STROBE
Switch of strobe lights
LDG L.
Switch of landing light
COCKPIT L
Rotary switch of cockpit lamp (with dimmer)
INSTR L
Rotary switch of instrument lighting (with dimmer)
FLAPS UP/DOWN
Switch of flaps control
AUTOPILOT
DISCONNECT
Quick disconnects of autopilot (momentary switch, optional)
Switches – instrument panel with the analog instruments
MASTER BAT
Main switch - switch of battery, VHF transceiver, intercom
MASTER GEN
Main switch - switch of generator
ENG INST
Switch of engine instruments
FLT INST
Switch of flight instruments
AVIONICS
Switch of VHF transponder, GPS and other optional avionics
FUEL P
Switch of electric fuel pump
NAV L
Switch of position lights
STROBE
Switch of strobe lights
LDG L
Switch of landing light
COCKPIT L
Switch of cockpit lamp
INSTR L
Switch of instrument lighting
DIM
Instrument lighting dimmer
NIGHT POS IND DAY
Switch of instrument lighting intensity
FLAPS UP/DOWN
Switch of flaps control
Tab.11-1: Switches (page 1 of 2)
Date of issue: 2013-06-30
Revision No.: 11 - 5
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
Switches – instrument panel with the Skyview
Designation
Description
MASTER BAT
Main switch - switch of battery, VHF transceiver, intercom
MASTER GEN
Main switch - switch of generator
EFIS1
Switch of EFIS 1 display
EFIS2
Switch of EFIS 2 (EMS) display
AVIONICS
Switch of EFIS, NAV/COM, GPS, XPDR
FUEL P
Switch of electric fuel pump
NAV L
Switch of position lights
STROBE
Switch of strobe lights
LDG L.
Switch of landing light
COCKPIT L
Rotary switch of cockpit lamp (with dimmer)
INSTR L
Rotary switch of instrument lighting (with dimmer)
FLAPS UP/DOWN
Switch of flaps control
AUTOPILOT
DISCONNECT
Quick disconnects of autopilot (momentary switch, optional)
Switches – PiperSport / SportCruiser up to S/N C0416
Designation
Description
INSTR
Switch of engine monitoring instruments (toggle switch)
AVIONICS
AUTOPIL
Switch of radio, intercom, transponder, GPS and other optional
avionics (toggle switch)
Switch of optional autopilot (toggle switch)
AUTOPILOT
DISCONNECT
Quick disconnects of autopilot (momentary switch)
FLAPS
Switch of flaps control (rocker switch)
TRIM
Switch of trim control (button switch)
Tab.11-1: Switches (page 2 of 2)
11.2.2
Switches – circuit breakers
The switches – circuit breakers serve for switching (ON/OFF) and protecting individual
electrical circuits from overloading together. The switches - circuit breakers are located on
the left instrument panel.
Switches – circuit breakers
Designation
Value
Description
EFIS1
5A
Switch - circuit breaker of EFIS 1 display
EFIS2
5A
Switch - circuit breaker of EFIS 2 (EMS) display
FUEL P
3A
Switch - circuit breaker of electric fuel pump
NAV L
5A
Switch - circuit breaker of position lights
STROBE
3A
Switch - circuit breaker of strobe lights
LDG L
5A
Switch - circuit breaker of landing light
LDG L
3A
Switch - circuit breaker of landing light (Trail Tech D112-SX)
Tab.11-2: Switches – circuit breakers (page 1 of 3)
Revision No.: 9
Date of issue: 2017-09-15
11 - 6
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SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
Switches – circuit breakers – PiperSport / SportCruiser up to S/N C0416
Designation
Value
Description
MASTER
25A
Main switch
STROBE
10A
Switch - circuit breaker of strobe lights
NAV L.
5A
Switch - circuit breaker of position lights
5A
LDG L
5A
Switch - circuit breaker of optional lighting of instruments on
the instrument panel
Switch - circuit breaker of landing light
LDG L
3A
Switch - circuit breaker of landing light (Trail Tech D112-SX)
FUEL P.
5A
Switch - circuit breaker of electric fuel pump
INSTR L
Tab.11-2: Switches – circuit breakers (page 2 of 3)
Switches – circuit breakers – SV-HDX1100
Designation
Value
Description
HDX 1
7,5A
Switch - circuit breaker of EFIS 1 display
HDX 2
7,5A
Switch - circuit breaker of EFIS 2 (EMS) display
FUEL P
3A
Switch - circuit breaker of electric fuel pump
NAV L
5A
Switch - circuit breaker of position lights
STROBE
5A
Switch - circuit breaker of strobe lights
LDG L
3A
Switch - circuit breaker of landing light
Tab.11-2: Switches – circuit breakers (page 3 of 3)
11.2.3
Circuit breakers
Circuit breakers serve for protecting individual electrical circuits from overloading. Every
circuit breaker is marked by the placard with a circuit designation. Circuit breakers are
located on the right instrument panel.
Circuit breakers – instrument panel with the EFIS/EMS
Designation
Value
Description
COMM
5A
Circuit breaker of VHF transceiver
IC
1A
Circuit breaker of intercom
EMS
2A
Circuit breaker of engine monitoring system display
NAV
2A
Circuit breaker of optional navigation device
EFIS
3A
Circuit breaker of flight instrument system display
HS34
1A
Circuit breaker of HSI navigation interface
GPS
4A
Circuit breaker of GPS
XPDR
5A
Circuit breaker of transponder
FUEL P
3A
Circuit breaker of electric fuel pump
FLAPS
3A
Circuit breaker of flaps
TRIM
1A
Circuit breaker of trims
NAV L
5A
Circuit breaker of position lights
STROBE
5A
Circuit breaker of strobe lights
LDG L
4A
Circuit breaker of landing light
Date of issue: 2017-09-15
Revision No.:9
11 - 7
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SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
LDG L
3A
Switch - circuit breaker of landing light (Trail Tech D112-SX)
INT L
2A
Circuit breaker of instrument lighting and cockpit lamp
12V
5A
Circuit breaker of 12V socket
AP
2A
Circuit breaker of optional autopilot control unit
ROLL SERVO
2A
Circuit breakers of optional autopilot servo
PITCH SERVO
2A
Circuit breakers of optional autopilot servo
PROP
5A
Circuit breaker of electrical adjustable propeller
Tab.11-2: Circuit breakers (page 1 of 4)
Circuit breakers – instrument panel with the analog instruments
COMM
5A
Circuit breaker of VHF transceiver
IC
1A
Circuit breaker of intercom
ENG INSTR
1A
Circuit breaker of engine instruments
NAV
2A
Circuit breaker of optional navigation device
GPS
3A
Circuit breaker of GPS
XPDR
5A
Circuit breaker of transponder
ATT
1A
Circuit breaker of attitude indicator
DG
2A
Circuit breaker of directional gyro
TURN IND
1A
FUEL P
3A
Circuit breaker of turn & bank indicator
Circuit breaker of electric fuel pump
FLAPS
3A
Circuit breaker of flaps
TRIM
2A
Circuit breaker of trims
STROBE
5A
Circuit breaker of strobe lights
NAV L
5A
Circuit breaker of position lights
LDG L
4A
Circuit breaker of landing light
LDG L
3A
Switch - circuit breaker of landing light (Trail Tech D112-SX)
INT L
2A
Circuit breaker of instrument lighting and cockpit lamp
12V
5A
Circuit breaker of 12V socket
PROP
5A
Circuit breaker of electrical adjustable propeller
Circuit breakers – instrument panel with the Skyview
Designation
Value
Description
COMM
5A
Circuit breaker of VHF transceiver
IC
1A
Circuit breaker of intercom
NAV
2A
Circuit breaker of optional navigation device
EFIS1
5A
Circuit breaker of EFIS 1 display
EFIS2
5A
Circuit breaker of EFIS 2 (EMS) display
FUEL P
3A
Circuit breaker of electric fuel pump
FLAPS
3A
Circuit breaker of flaps
TRIM
1A
Circuit breaker of trims
STROBE
5A
Circuit breaker of strobe lights
GPS
4A
XPDR
PITCH SERVO
5A
2A
Circuit breaker of GPS
Circuit breaker of transponder
ROLL SERVO
2A
Circuit breakers of autopilot servo
NAV L
5A
Circuit breaker of position lights
Circuit breakers of autopilot servo
Revision No.: 9
Date of issue: 2017-09-15
11 - 8
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PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
LDG L
4A
Circuit breaker of landing light
LDG L
3A
Switch - circuit breaker of landing light (Trail Tech D112-SX)
INT L
2A
Circuit breaker of instrument lighting and cockpit lamp
PROP
5A
Circuit breaker of electrical adjustable propeller
Tab.11-2: Circuit breakers (page 2 of 4)
Circuit breakers – PiperSport / SportCruiser up to S/N C0416
Designation
Value
Description
PWR
20A
Circuit breaker of DC rectifier
EMS
2A
Engine monitoring system display
EFIS
3A
Flight instrument system display
COMM
5A
Circuit breaker of radio
IC
1A
Circuit breaker of intercom
NAV
2A
Circuit breaker of optional navigation device
XPDR
5A
Circuit breaker of transponder
GPS
2A
Circuit breaker of GPS
FLAPS
5A
Circuit breaker of flaps
12V
7A
Circuit breaker of 12V socket
TRIM
1A
Circuit breaker of trims
AP
2A
Circuit breaker of optional autopilot control unit
AP SERVO 1/2
2A
Circuit breakers of optional autopilot servos
PROP
3A
Circuit breaker of electrical adjustable propeller
Tab.11-2: Circuit breakers (page 3 of 4)
Circuit breakers – instrument panel with the SV-HDX1100
Designation
Value
Description
COMM
10A
Circuit breaker of VHF transceiver
IC
1A
Circuit breaker of intercom
NAV
4A
Circuit breaker of optional navigation device
HDX 1
7,5A
Circuit breaker of EFIS 1 display
HDX 2
7,5A
Circuit breaker of EFIS 2 (EMS) display
FUEL P
3A
Circuit breaker of electric fuel pump
FLAPS
3A
Circuit breaker of flaps
TRIM
1A
Circuit breaker of trims
STROBE
5A
Circuit breaker of strobe lights
GPS
4A
Circuit breaker of GPS
XPDR
5A
Circuit breaker of transponder
PITCH SERVO
2A
Circuit breakers of autopilot servo
ROLL SERVO
2A
Circuit breakers of autopilot servo
NAV L
5A
Circuit breaker of position lights
LDG L
INT L
3A
2A
Circuit breaker of landing light
Circuit breaker of instrument lighting and cockpit lamp
PROP
5A
Circuit breaker of electrical adjustable propeller
Date of issue: 2017-09-15
Revision No.:9
11 - 9
SC-AMM-1-0-00
SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
12V
5A
Circuit breaker of 12V socket
AP
2A
Circuit breaker of optional autopilot control unit
Tab.11-2: Circuit breakers (page 4 of 4)
11.2.4
Fuses
Fuses serve for protecting individual electrical circuits from overloading. The box with the fuses is
located on the firewall in the engine compartment (valid for SportCruiser airplanes from S/N C0416).
Fuses – instrument panel with the EFIS/EMS
Designation
Description
1A SIGN. DOOR
Fuse of unlocked canopy signaling system
25A DC GEN
Fuse of generator
25 A BATTERY
Fuse of battery
Fuses – instrument panel with the analog instruments
Designation
Description
1A SIGN. DOOR
Fuse of unlocked canopy signaling system
1A VOLTMETER
Fuse of voltmeter
1A ENGIN. INSTR.
Fuse of engine instruments
25A DC GEN
Fuse of generator
25 A BATTERY
Fuse of battery
Fuses – instrument panel with the Skyview
Designation
Description
1A SIGN. DOOR
Fuse of unlocked canopy signaling system
25A DC GEN
Fuse of generator
25 A BATTERY
Fuse of battery
Tab.11-3: Fuses
Revision No.: 9
Date of issue: 2017-09-15
11 - 10
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CHAPTER 11 – ELECTRICAL SYSTEM
11.2.5
SportCruiser
PiperSport
Generator
The generator is a part of the engine which supplies electric current through the rectifier.
Regulator supplies electric current of 14 V voltage to onboard network.
Technical parameters of generator:
Maximum output power:
12 V / 20 A at 5,000 rpm
Technical parameters of rectifier - regulator:
Type:
electronic
Output voltage:
14 ± 0.3 V (from 1,000 ± 250 rpm)
Range of operation temperatures:
min. – 25 °C (- 13 °F)
max. + 90 °C (+ 194 °F)
Weight:
11.2.6
0.3 kg (0.66 lbs)
Battery
Lead-acid battery
Lead-acid maintenance-free battery is installed on firewall. Battery can be charged directly
in the airplane after its disconnecting from the onboard electrical system.
Technical parameters:
Voltage
12 V
Nominal capacity
20 Ah
Max. discharge current
300 A (5 s)
Short circuit current
1,000 A
Range of operation temperatures
- 20 to + 60 °C (-4 to + 140 °F)
Service life is about
3 - 5 years or at capacity drop below 80 %
Weight:
6 kg (13 lbs)
If the airplane is not operated for more than one month, then remove the battery from the
airplane and store it.
Always store the battery fully charged at temperature of 20 °C (68 °F). Daily discharging is
less than 0.1 % of battery nominal capacity.
Regularly recharge it up to the full capacity of charging once a month.
LiFePo4 battery
LiFePo4 maintenance-free battery is installed on firewall. Battery can be charged directly in
the airplane after its disconnecting from the onboard electrical system.
Technical parameters:
Nominal voltage
13.2 V
Capacity
9.2 Ah
Pulse discharge current
480 A (10 s)
Date of issue: 2013-09-05
Revision No.: 1
11 - 11
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 11 – ELECTRICAL SYSTEM
CCA Current
400 A
Continuous discharge current
280A¨
Nominal charging current
12 A @ 25 ° C
Max charging current
20 A @ 25 ° C
Duration
1000 cycles @ 100% Dod / 10C
2000 cycles @ 80% Dod / 10C
Life expectancy
Up to 5 – 7 years
Charging voltage
14.4 V
Maximum charging voltage
14.6 V
Weight
c. 1.62 kg
Dimensions [mm]
L 148 x P 67 x H 140
Ambient temperature
-30 ° C / +60 ° C [Operating and storage]
Maximum operating altitude
5,000 m
Capacity equivalent Pb
up to 18 Ah
If the airplane is not operated for more than one month, then remove the battery from the
airplane and store it.
Always store the battery fully charged at temperature of 20 °C (68 °F).
Regularly recharge it up to the full capacity of charging once a month.
11.2.7
Lighting
External lighting consists of the position / strobe lights which are located in the wing tips and
of the landing light which is located in the lower engine cowling. Position lights are switched
by the switch NAV L and strobe lights are switched by the switch STROBE. The landing
light is switched by the switch LDG L.
Internal lighting consists of the instrument lighting and of the cockpit lamp, which is located
on the instrument panel or on the canopy frame between pilots. The instrument lighting
(illumination of the altimeter and the airspeed indicator) is switched / controlled by the switch
INSTR L. The cockpit lamp is switched / controlled by the switch COCKPIT L.
Revision No.: 1
Date of issue: 2013-09-05
11 - 12
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SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
11.3
Removal / Installation
11.3.1
Electrical Safety
The aircraft has a low-voltage DC electrical system. When correctly maintained it is safe to
work on. But the battery can supply heavy current through low-resistance circuits (for
example, if you ground the positive output with a wrench by accident).
Always follow the usual safety practices for working on electrical equipment. Allow only
qualified persons to maintain the electrical system.
11.3.2
CAUTION:
DISCONNECT THE BATTERY BEFORE DOING MAINTENANCE ON
THE ELECTRICAL SYSTEM. MAKE SURE TO DISCONNECT THE
NEGATIVE LEAD FIRST.
CAUTION:
USE ONLY AIRCRAFT
MANUFACTURER.
SPARE
PARTS
APPROVED
BY
THE
Battery removal
Type of maintenance: line
Authorization to perform:
- Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
- wrench size No.8
(a) Set the MASTER BAT / MASTER, MASTER GEN switches to OFF.
(b) Remove engine cowlings.
(c) Unscrew the bolts (5, Fig. 11-2) with washers (6) and disconnect the wires (2; 3; 4) from
the battery contacts; make sure to disconnect the negative lead first. In the case of
installation LiFePo4 battery remove the nuts (12) from the battery contacts.
(d) Unscrew the bolts (8) with washers (9), disconnect the battery strap (7) and remove the
battery (1 / 11) from the airplane.
11.3.3
Battery installation
Type of maintenance: line
Authorization to perform:
- Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
- wrench size No.8
(a) Install the battery (1 / 11 Fig. 11-2) into the bracket on the firewall (10).
(b) Fasten it with battery strap (7), bolts (8), and washers (9); tighten bolts so that the
battery cannot move in the bracket.
(c) In the case of installation LiFePo4 battery insert the nuts (12) into the battery contacts.
(d) Install the wires (2; 3; 4) by means of bolts (5) with washers (6); make sure you connect
the positive lead first.
Date of issue: 2013-09-05
Revision No.: 1
11 - 13
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PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
(e) Grease the battery contacts with lubricating grease.
(f) Install the engine cowlings.
1
2
3
4
5
6
Lead-acid battery
Wire
Wire
Wire
Bolt
Washer
7
8
9
10
11
12
Battery strap
Bolt
Washer
Firewall
LiFePo4 battery
Nut
Fig. 11-2: Battery removal / installation
Revision No.: 1
Date of issue: 2013-09-05
11 - 14
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CHAPTER 11 – ELECTRICAL SYSTEM
11.3.4
11.3.4.1
SportCruiser
PiperSport
Position / strobe light removal
SportCruiser / PiperSport airplanes up to S/N C0416
Type of maintenance: line
Authorization to perform:
- Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
(a) Set the MASTER, NAV L, and STROBE switches to OFF.
(b) Unscrew the screws (6, Fig. 11-6) and remove the cover glass (4).
(c) Remove screws (5) attaching the light housing (1) to the wing tip (7), thus releasing the
light housing.
(d) Remove strobe/position light housing (1) and disconnect the wires (3).
11.3.4.2
SportCruiser airplanes from S/N C0416
Type of maintenance: line
Authorization to perform:
- Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
(a) Set the MASTER BAT, NAV L, and STROBE switches to OFF.
(b) Unscrew the screw (4, Fig. 11-3) and carefully release the light (1).
(c) Disconnect the wires (3) and remove position / strobe light (1) with the gasket (2).
11.3.5
11.3.5.1
Position / strobe light installation
SportCruiser / PiperSport airplanes up to S/N C0416
Type of maintenance: line
Authorization to perform:
- Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
(a) Thoroughly clean the contacting surfaces on the light and on the wing tip of the putty
residues.
(b) Connect the strobe/position lights wires (3, Fig. 11-3).
(c) Set the strobe/position light housing (1) to the wing tip (7) and fasten it with screws (5).
(d) Set the cover glass (4) to the light housing (1) and fasten it with screws (6).
(e) Seal the strobe/position light edges by polyurethane sealer to prevent water from in
leaking under the strobe/position light.
(f) Set the MASTER, NAV L, and STROBE switches to ON and check the correct function
of position / strobe lights.
(g) Set the MASTER, NAV L, and STROBE switches to OFF.
Date of issue: 2013-09-05
Revision No.: 1
11 - 15
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SportCruiser
PiperSport
11.3.5.2
CHAPTER 11 – ELECTRICAL SYSTEM
SportCruiser airplanes from S/N C0416
Type of maintenance: line
Authorization to perform:
- Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
(a) Pass the wires (3, Fig. 11-3) through the appropriate hole in the gasket (2).
(b) Connect the position / strobe light wires (3) (see Wiring Manual).
(c) Set the position light (1) with the gasket (2) to the wing tip (5) and fasten it with screw
(4).
(d) Set the MASTER BAT, NAV L, and STROBE switches to ON and check the correct
function of position / strobe lights.
(e) Set the MASTER BAT, NAV L, and STROBE switches to OFF.
1 Position light
2 Gasket
3 Wires
4 Screw
For information:
5 Wing tip
Fig. 11-3: Position light removal / installation
11.4 Exchanges / Service information
11.4.1
Charging the battery
Lead-acid battery
(a) Disconnect the battery from the onboard electrical network.
(b) Clean the battery contacts and connect the charging device on them. Mind the polarity!
(c) Charging voltage at temperature of 25 °C (77 °F) is:
- Cycle use 14.5-14.9 V
- Standby use 13.6 to 13.8 V. Maximum charging current is 8 A.
Revision No.: 1
Date of issue: 2013-09-05
11 - 16
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CHAPTER 11 – ELECTRICAL SYSTEM
SportCruiser
PiperSport
(d) After charging grease the battery contacts with lubricating grease and reconnect the
battery to the onboard electrical network.
LiFePo4 battery
CAUTION:
FOR BATTERY CHARGING USE ONLY ALIANT CB1210 OR CB1213
CHARGER.
(a) Disconnect the battery from the onboard electrical network.
(e) Clean the battery contacts and connect the charging device on them. Mind the polarity!
(f) After charging grease the battery contacts with lubricating grease and reconnect the
battery to the onboard electrical network.
Date of issue: 2013-09-05
Revision No.: 1
11 - 17
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 11 – ELECTRICAL SYSTEM
Fig. 11-4: Lead-acid battery characteristics
Revision No.: 1
Date of issue: 2013-09-05
11 - 18
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SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
11.4.2
Adjusting the optional wing landing light
NOTE:
Valid for some SportCruiser airplanes up to S/N C0416.
(a) Remove the plexiglass cover from the wing leading edge between ribs No.8 and 9.
(b) Do adjustment per securing bolts in the vertical direction in such a way that the light axis
is directed 5° below the reference plane of the wing.
(c) Do adjustment in the horizontal direction according to the Fig.11-5 in such a way that
the light axis is directed towards the airplane axis about 45m (150 ft) before the fuselage
nose.
(d) Install the plexiglass cover on the leading edge of the wing
Fig. 11-5: Setting the optional wing landing light
11.4.3
Exchange of the strobe light discharge tube
NOTE:
Valid for SportCruiser / PiperSport airplanes up to S/N C0416.
Type of maintenance: line
Authorization to perform:
- Sports pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- screwdriver
CAUTION:
DO NOT TOUCH THE NEW DISCHARGING TUBE WITH BARE HANDS.
USE THE CLOTH GLOVES OR A CLOTH.
(a) Switch off electrical power of the airplane.
(b) Unscrew the screws (6, Fig. 11-6) and remove the cover glass (4).
Date of issue: 2013-09-05
Revision No.: 1
11 - 19
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SportCruiser
PiperSport
CHAPTER 11 – ELECTRICAL SYSTEM
(c) Carefully remove the discharge tube (2), disconnect wires (3).
(d) Exchange the discharge tube for the same type; connect wires.
(e) Set the cover glass (4) to the light housing (1) and fasten it with screws (6).
1
2
3
4
Position / strobe light housing
Discharge tube
Wires
Cover glass
5 Screw
6 Screw
For information:
7 Wing tip
Fig. 11-6: Exchange of the strobe light discharge tube
Revision No.: 1
Date of issue: 2013-09-05
11 - 20
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
SportCruiser
PiperSport
Contents
12.1 General ................................................................................................................ 12-3
12.2 Description and operation .................................................................................. 12-11
12.2.1
Pitot-static system ............................................................................. 12-11
12.2.2
Stall warning system.......................................................................... 12-11
12.2.3
Flight instruments .............................................................................. 12-13
12.2.4
Engine instruments ............................................................................ 12-14
12.2.5
Avionics ............................................................................................. 12-14
12.2.6
Dynon SkyView system ..................................................................... 12-21
12.3 Removal / Installation ........................................................................................ 12-23
12.3.1
Removal of the pitot-static tube ......................................................... 12-23
12.3.2
Installation of the pitot-static tube ...................................................... 12-23
12.3.3
Removal of the stall warning system lift detector .............................. 12-24
12.3.4
Installation of the stall warning system lift detector ........................... 12-24
12.3.5
Removal of the flight instruments ...................................................... 12-25
12.3.6
Installation of the flight instruments ................................................... 12-26
12.3.7
Removal of the EFIS D100 ................................................................ 12-27
12.3.8
Installation of the EFIS D100............................................................. 12-29
12.3.9
Removal of the EDC-10A remote compass module ......................... 12-29
12.3.10
Installation of the EDC-10A remote compass module ...................... 12-30
12.3.11
Removal of the EMS D120 ................................................................ 12-30
12.3.12
Installation of the EMS D120 ............................................................. 12-32
12.3.13
Removal of transponder .................................................................... 12-32
12.3.14
Installation of transponder ................................................................. 12-32
12.3.15
Removal of COMM, COMM/NAV ...................................................... 12-33
12.3.16
Installation of COMM, COMM/NAV ................................................... 12-34
12.3.17
Removal of intercom.......................................................................... 12-35
12.3.18
Installation of intercom ...................................................................... 12-35
12.3.19
Removal of GPS / NAV / COM .......................................................... 12-36
12.3.20
Installation of GPS / NAV / COM ....................................................... 12-37
12.3.21
Removal of COMM antenna .............................................................. 12-38
12.3.22
Installation of COMM antenna ........................................................... 12-39
12.3.23
Removal of NAV antenna .................................................................. 12-38
12.3.24
Installation of NAV antenna ............................................................... 12-39
12.3.25
Removal of transponder antenna ...................................................... 12-41
12.3.26
Installation of transponder antenna ................................................... 12-41
12.3.27
Removal of GPS antenna .................................................................. 12-42
12.3.28
Installation of GPS antenna ............................................................... 12-43
Date of issue: 2017-06-30
Revision No.: 8
12 - 1
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.3.29
Removal of the SV-D1000 display .................................................... 12-43
12.3.30
Installation of the SV-D1000 display ................................................. 12-44
12.3.31
Removal of HDX1100 ........................................................................ 12-44
12.3.32
Installation of HDX1100 ..................................................................... 12-45
12.3.33
Removal of SV-BAT-320 backup battery / batteries ......................... 12-46
12.3.34
Installation of SV-BAT-320 battery / batteries ................................... 12-46
12.3.35
Removal of SV-EMS-220 module ..................................................... 12-47
12.3.36
Installation of SV-EMS-220 module .................................................. 12-48
12.3.37
Removal of SV-ADAHRS-200 / 201 module ..................................... 12-48
12.3.38
Installation of SV-ADAHRS-200 / 201 module .................................. 12-49
12.3.39
Removal of SV-OAT-340 probe ........................................................ 12-50
12.3.40
Installation of SV-OAT-340 probe ..................................................... 12-51
12.3.41
Removal of SV-XPDR-261 transponder ............................................ 12-51
12.3.42
Installation of SV-XPDR-261 transponder ......................................... 12-53
12.3.43
Removal of drain sump ..................................................................... 12-53
12.3.44
Installation of drain sump .................................................................. 12-53
12.3.45
Draining of drain sumps .................................................................... 12-54
12.3.45.1
SportCruiser airplanes manufactured up to April 2013 .. 12-54
12.3.45.2
SportCruiser airplanes manufactured from April 2013 .. 12-54
12.3.46
Removal of SV-ADSB-470 module ................................................... 12-55
12.3.37
Installation of SV-ADSB-470 module ................................................ 12-55
12.4 Check / Adjustment............................................................................................ 12-56
12.4.1
Check of pitot-static system tightness ............................................... 12-56
12.4.2
Dynon avionics pitot / static test ........................................................ 12-56
12.4.3
Magnetic compass compensation ..................................................... 12-57
12.4.4
EFIS compass heading calibration .................................................... 12-57
12.4.5
ADHRS magnetic heading calibration ............................................... 12-57
12.4.6
EFIS D100 internal emergency battery check ................................... 12-60
12.4.7
EFIS D100, EMS D120 firmware upgrade ........................................ 12-60
12.4.8
Flight test for verification of the stall warning system ........................ 12-61
Revision No.: 8
Date of issue: 2017-06-30
12 - 2
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.1
SportCruiser
PiperSport
General
This chapter provides information about pitot-static system, instruments and avionics.
The airplane is equipped with the instrument panel that contains all flight, navigation, and
engine instruments that are required for VFR operations. Figures 12-1 to 12-8 show the
typical instrument panels used for SportCruiser / PiperSport airplane.
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
EFIS D100
GTX 328 transponder
Airspeed indicator
Altimeter
GPSMAP® 695
AP74 Autopilot interface module
EMS D120
COCKPIT L dimmer
INSTR L dimmer
PARKING BRAKE knob
Air vent
MASTER BAT switch
MASTER GEN switch
EMS switch
AVIONICS switch
FUEL P switch
NAV L switch
STROBE switch
LDG L switch
Keyed ignition switch
AUTOPILOT DISCONNECT button
SL30 NAV/COMM
FLAPS UP/DOWN switch
WING FLAP UP/DOWN position indicator
FUEL selector valve
Socket 12 V
CARBURETOR HOT AIR knob
CABIN HEATER knob
BRS activation handle
PM3000 intercom
VOLUME Dynon alerts control
Circuit breakers
ELT remote switch
ELT remote audio buzzer
Cockpit light connector
Magnetic compass
HS34 HSI expansion module
EMS ALARM yellow warning light
CABIN OPENED red warning light
NOTE: In case the engine is equipped with new cylinder heads (P/N 413185 2/3 cylinder head) the coolant
temperature is measured and is displayed as “CHT” on the Dynon EMS-D120 screen.
Fig. 12-1: SportCruiser typical instrument panel with EFIS / EMS
Date of issue: 2016-01-18
Revision No.: 6
12 - 3
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SportCruiser
PiperSport
CHAPTER 12 – INSTRUMENTS AND AVIONICS
25 NAV L switch
26 STROBE switch
27 LDG L switch
28 Keyed ignition switch
29 PM3000 intercom
30 FLAPS UP/DOWN switch
31 WING FLAP UP/DOWN position indicator
32 FUEL selector valve
33 Socket 12 V
34 CARBURETOR HOT AIR knob
35 CABIN HEATER knob
36 Elevator TRIM UP/DOWN
37 AILERON TRIM L/R
38 Circuit breakers
39 Instrument lighting
40 Hourmeter
41 ELT remote switch
42 Cockpit light connector
43 Magnetic compass
44 COCKPIT L switch
45 INSTR L dimmer
46 GEN red warning light
47 FUEL PUMP green signaling light
48 CABIN OPENED red warning light
1 Airspeed indicator
2 Turn and bank indicator
3 Artificial horizon
4 Directional gyro
5 Altimeter
6 Vertical speed indicator
7 Aera 510 GPS
8 GTX 327 transponder
9 Engine speed indicator
10 Fuel pressure indicator
11 Oil pressure indicator
12 Fuel quantity indicator
13 Oil temperature indicator
14 CHT/CT* indicator
15 Voltmeter
16 SL40 VHF transceiver
17 PARKING BRAKE knob
18 Air vent
19 MASTER BAT switch
20 MASTER GEN switch
21 ENG INSTR switch
22 FLT INSTR switch
23 AVIONICS switch
24 FUEL P switch
* CT indicator in case the engine is equipped with new cylinder heads, (P/N 413185 for 2/3 cylinder head)
Fig. 12-2: SportCruiser typical instrument panel with analog instruments
Revision No.: 6
Date of issue: 2016-01-18
12 - 4
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
PFD SV-D1000
GPSMAP® 695
EMS SV-D1000
Lighting cover
Air vent
MASTER BAT switch
MASTER GEN switch
EFIS 1 switch
EFIS 2 switch
AVIONICS switch
FUEL P switch
NAV L switch
STROBE switch
LDG L switch
Keyed ignition switch
SL30 NAV/COMM
SportCruiser
PiperSport
FLAPS UP/DOWN switch
WING FLAP UP/DOWN position indicator
FUEL selector valve
PARKING BRAKE knob
CARBURETOR HOT AIR knob
CABIN HEATER knob
BRS activation handle (option)
PM3000 intercom
Circuit breakers
Cockpit light
ELT remote switch
Magnetic compass
INSTR L dimmer
COCKPIT L dimmer
EMS ALARM yellow warning light
NOTE: In case the engine is equipped with new cylinder heads (P/N 413185 2/3 cylinder head) the
coolant temperature (CT) instead of Cylinder Head temperature (CHT) is measured.
Fig. 12-3: SportCruiser typical instrument panel with Skyview system
Date of issue: 2016-01-18
Revision No.: 6
12 - 5
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SportCruiser
PiperSport
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
CHAPTER 12 – INSTRUMENTS AND AVIONICS
17
18
19
20
21
22
23
24
25
26
27
28
29
PFD SV-D1000
GPSMAP® 695
EMS SV-D1000
ELT remote switch
GNC 255A NAV/COMM
PM3000 intercom
Air vent
Keyed ignition switch
Lighting cover
12V socket
MASTER BAT switch
MASTER GEN switch
EFIS 1 circuit breaker
EFIS 2 circuit breaker
AVIONICS switch
FUEL P circuit breaker
NAV L circuit breaker
STROBE circuit breaker
LDG L circuit breaker
FLAPS UP/DOWN switch
AUTOPILOT DISCONNECT button
FUEL selector valve
PARKING BRAKE knob
CARBURETOR HOT AIR knob
CABIN HEATER knob
Circuit breakers
INSTR L dimmer
COCKPIT L dimmer
EMS ALARM yellow warning light
NOTE: In case the engine is equipped with new cylinder heads (P/N 413185 2/3 cylinder head) the
coolant temperature (CT) instead of Cylinder Head temperature (CHT) is measured.
Fig. 12-4: SportCruiser typical instrument panel with Skyview system (from S/N C0416)
Revision No.: 6
Date of issue: 2016-01-18
12 - 6
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
PFD SV-D1000
GPS Aera 795
Intentionally left blank
ELT remote switch
GNC 255A NAV/COMM
PM3000 intercom
Air vent
Keyed ignition switch
Lighting cover
12V socket
MASTER BAT switch
MASTER GEN switch
EFIS 1 circuit breaker
AVIONICS switch
FUEL P circuit breaker
NAV L circuit breaker
SportCruiser
PiperSport
STROBE circuit breaker
LDG L circuit breaker
Intentionally left blank
FLAPS UP/DOWN switch
AUTOPILOT DISCONNECT button
FUEL selector valve
PARKING BRAKE knob
CARBURETOR HOT AIR knob
CABIN HEATER knob
Circuit breakers
INSTR L dimmer
COCKPIT L dimmer
EMS ALARM yellow warning light
BRS activation handle cover
BRS activation handle
NOTE: In case the engine is equipped with new cylinder heads (P/N 413185 2/3 cylinder head) the
coolant temperature (CT) instead of Cylinder Head temperature (CHT) is measured.
Fig. 12-5: SportCruiser typical instrument panel with Skyview system (from S/N C0416)
Date of issue: 2016-01-18
Revision No.: 6
12 - 7
SC-AMM-1-0-00
SportCruiser
PiperSport
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
CHAPTER 12 – INSTRUMENTS AND AVIONICS
17
18
19
20
21
22
23
24
25
26
27
28
29
PFD SV-D1000
Intentionally left blank
Intentionally left blank
ELT remote switch
SL30 NAV/COMM
PM3000 intercom
Air vent
Keyed ignition switch
Lighting cover
12V socket
MASTER BAT switch
MASTER GEN switch
EFIS 1 circuit breaker
AVIONICS switch
FUEL P circuit breaker
NAV L circuit breaker
STROBE circuit breaker
LDG L circuit breaker
Intentionally left blank
FLAPS UP/DOWN switch
AUTOPILOT DISCONNECT button
FUEL selector valve
PARKING BRAKE knob
CARBURETOR HOT AIR knob
CABIN HEATER knob
Circuit breakers
INSTR L dimmer
COCKPIT L dimmer
EMS ALARM yellow warning light
NOTE: In case the engine is equipped with new cylinder heads (P/N 413185 2/3 cylinder head) the
coolant temperature (CT) instead of Cylinder Head temperature (CHT) is measured.
Fig. 12-6: SportCruiser typical instrument panel with Skyview system (from S/N C0416)
Revision No.: 6
Date of issue: 2016-01-18
12 - 8
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
EFIS D100
GTX 328 transponder
Airspeed indicator
Altimeter
GPSMAP® 695
AP74 Autopilot interface module
EMS D120
PARKING BRAKE knob
MASTER switch
INSTR switch
AVIONICS switch
AUTOPILOT switch
STROBE switch
NAV L switch
LDG L switch
FUEL P switch
Keyed ignition switch
SportCruiser
PiperSport
AUTOPILOT DISCONNECT button
SL30 NAV/COMM
FLAPS UP/DOWN switch
WING FLAP UP/DOWN position indicator
FUEL selector valve
Socket 12 V
CARBURETOR HOT AIR knob
CABIN HEATER knob
BRS activation handle
PM3000 intercom
VOLUME Dynon alerts control
Circuit breakers
ELT remote switch
ELT remote audio buzzer
Magnetic compass
HS34 HSI expansion module
EMS ALARM yellow warning light
NOTE: In case the engine is equipped with new cylinder heads (P/N 413185 2/3 cylinder head) the
coolant temperature is measured and is displayed as “CHT” on the Dynon EMS-D120 screen.
Fig. 12-7a: PiperSport instrument panel with EFIS / EMS
NOTE:
Current instrument panel arrangement is stated in the Pilot′s Operation
Handbook, Supplement No. 2.
Date of issue: 2016-01-18
Revision No.: 6
12 - 9
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SportCruiser
PiperSport
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
CHAPTER 12 – INSTRUMENTS AND AVIONICS
Dynon SV-HDX1100
Dynon SV-HDX1100
Instrument light
STALL WARNING TEST button
STALL WARNING light
EMS ALARM warning light
AUTOPILOT DISCONNECT button
USB port EFIS 1
Vent-Air Outlet
Ignition switch
Dynon SV-AP-PANEL
Dynon SV-KNOB-PANEL
Instrument light
PM 3000 intercom
COCKPIT L and INSTRUMENT L dimmers
Garmin GNC 255 NAV/COM
BRS activation handle
USB port EFIS 2
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
Socket 12V
ELT remote switch
Vent–Air outlet
CABIN HEATER knob
PARKING BRAKE knob
FUEL selector valve
CARBURETOR HOT AIR knob
FLAPS UP/DOWN switch
Circuit breakers
MASTER BATT switch
MASTER GEN switch
EFIS 1 switch/circuit breaker
EFIS 2 switch / circuit breaker
AVIONICS switch
FUEL P switch/circuit breaker
NAV L switch/circuit breaker
STROBE switch/circuit breaker
LDG L switch /circuit breaker
Fig. 12-7b: SportCruiser instrument panel with SV-HDX1100
- valid for SportCruiser S/N C0596 and C0600
NOTE: Current instrument panel arrangement is stated in the Pilot′s Operation Handbook,
Supplement No. 2
Revision No.: 8
Date of issue: 2017-06-30
12 - 10
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.2
Description and operation
12.2.1
Pitot-static system
SportCruiser
PiperSport
The pitot-static tube for sensing static and total pressure is located under the left half of the
wing close to the rib No. 4. Total pressure is sensed through the hole in the pitot-tube face
and static pressure is sensed through the holes on the tube circumference. Pressure
distribution to individual instruments is performed by means of flexible plastic hoses (see
Fig. 12-9).
Airplanes equipped with analog instruments:
Static pressure is lead to the ALT, ASI, VSI and altitude encoder. Total pressure is
connected to the ASI only.
Airplanes equipped with EFIS:
Static pressure is lead to the ALT, ASI and EFIS. Total pressure is connected to the ASI and
EFIS.
Airplanes equipped with Skyview:
Static and total pressure is lead to the double ADAHRS. The drain sumps are installed on
the both flexible hoses.
12.2.2
Stall warning system
The airplane can be optionally equipped with a vane–type lift detector. The lift detector is
located on the bottom of the left wing’s leading edge. Should the critical angle of attack be
approached (close to stall speed), the vane is actuated by the differences in pressures
acting on its front and the rear surfaces. Actuation of the vane triggers the stall warning
system’s electrical circuit. When the stall warning system is triggered, an audio alert is
activated (through the horn located behind the cabin) and the red STALL WARNING light
(1, Fig. 12-8) will illuminate on the left instrument panel. The audio and visual alerts will
remain on throughout the event.
The proper function of the system can be checked by pressing STALL WARNING TEST
button (2) located on the left instrument panel.
Fig. 12-8: Location of the stall warning light and test button
Date of issue: 2017-06-30
Revision No.: 8
12 - 11
SportCruiser
PiperSport
SC-AMM-1-0-00
CHAPTER 12 – INSTRUMENTS AND AVIONICS
Fig. 12-9: Pitot-static system scheme
Revision No.: -
Date of issue: 2013-06-30
12 - 12
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SportCruiser
PiperSport
CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.2.3
Flight instruments
Airspeed indicator - ASI
The airspeed indicator located on the left side of instrument panel is classical analogue
round pressure gauge.
The airspeed indicator color range marking is shown in Tab.12-1.
Marking
knot
IAS value or range
km/h
mph
Significance
Early SportCruiser, PiperSport
White
arc
32-75
59-139
37-86
Flap Operating Range.
Green
arc
39-108
72-200
45-124
Normal Operating Range.
Yellow
arc
108-138
200-255
124-158
Red line
138
255
158
Maneuvers must be conducted with
caution and only in smooth air.
Maximum speed for all operations.
SportCruiser from S/N C0416
White
arc
31-75
57-139
36-86
Flap Operating Range.
Green
arc
37-108
69-200
43-124
Normal Operating Range.
Yellow
arc
108-138
200-256
124-158
Red line
138
256
159
Maneuvers must be conducted with
caution and only in smooth air.
Maximum speed for all operations.
Tab.12-1: ASI color range marking
Altimeter - ALT
The altimeter located on the left side of instrument panel is classical analogue round
pressure gauge. Range of measure is up to 20,000 ft.
Magnetic compass
The magnetic compass is designed to determine magnetic course of the airplane. The
magnetic compass (if installed) is positioned on the upper edge of the instrument panel and
consists of the vessel filed with nonfreezing liquid with the little window in the front wall. The
compass rose is positioned on the rotary and swinging pivot inside the compass.
EFIS D100
The Dynon D100 is a panel-mounted Electronic Flight Instrument System (EFIS). The
instrument integrates multiple flight instruments, including airspeed, altitude, magnetic
compass, turn rate, slip/skid ball, bank angle, and vertical speed. Other useful functions
include a clock/timer, GPS data, outside air temperature and elevator trim indicator.
NOTE:
For detailed information refer to EFIS D100 Installation Guide (P/N
100487-000, latest edition).
Date of issue: 2013-06-30
Revision No.: 12 - 13
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PiperSport
12.2.4
CHAPTER 12 – INSTRUMENTS AND AVIONICS
Engine instruments
Engine parameters (RPM, CHT, EGT, oil pressure and temperature, fuel pressure, manifold
pressure) are displayed either on the EMS D120 or on the classical analog instruments. A
typical example of the EMS display is shown in the Figure 10-3. The EMS D120 is located
on the right side of instrument panel. The engine parameters color marking is shown in
Tab.12-2.
NOTE:
For detailed information refer to EMS D120 Installation Guide (P/N
100591-000, latest edition).
Value
Minimum
Limit
(red line)
Caution
Range
(yellow arc)
Normal
Operating
Range
(green arc)
Caution
Range
(yellow arc)
Maximum
Range
(red line)
Engine speed
[RPM]
-
0 – 1,400
1,400 – 5,500
5,500 – 5,800
5,800
Oil
Pressure
0.8 bar
(12 psi)
0.8 – 2 bar
(1 2 – 29 psi)
2 – 5 bar
(29 – 73 psi)
5 – 7 bar
(73 – 102 psi)
7 bar
(102 psi)
Oil
Temperature
50 °C
(122°F)
50 – 90 °C
(122 – 194 °F)
90 – 110 °C
(194 – 230 °F)
110 – 130 °C
(230 – 266 °F)
130 °C
(266 °F)
Cylinder Head
Temperature (CHT)
-
to 50 °C
(to 122 °F)
50 – 135 °C
(122 – 275°F)
-
135 °C
(275 °F)
-
-
-
to 300 °C
(to 572 °F)
0.15 bar
(2.2 psi)
-
0.14 bar**
(2.0 psi)
0.14 - 0.15 bar**
(2.0 – 2.2 psi)
0.15 - 0.50 bar**
(2.2 – 7.25 psi)
-
-
10 – 35 in Hg
Coolant Temperature
(CT)***
Exhaust Gas Temp.
(EGT)
Fuel Pressure
Manifold pressure
50 – 120 °C
(122 – 248°F)
300 – 850 °C
(572 – 1,562 °F)
0.15 – 0.4 bar
(2.2 – 5.8 psi)
0.15 – 0.5 bar*
(2.2 – 7.25 psi)
850 – 880 °C
(1,562 – 1,616 °F)
-
0.50 - 0.51 bar**
(7.25 – 7.4 psi)
120 °C
(248 °F)
880 °C
(1,616 °F)
0.4 bar
(5.8 psi)
0.5 bar*
(7.25 psi)
0.51 bar**
(7.4 psi)
* Applicable only for fuel pump from S/N 11.0036.
** Applicable for Dynon SkyView system.
*** Applicable for ROTAX 912 ULS2 engines from S/N 6 781 410 inclusive and for 912 S2
engines from S/N 4 924 544 inclusive, equipped with new cylinder heads, P/N 413185
for 2/3 cylinder head. The coolant temperature instead of cylinder head temperature is
measured. On Dynon EMS D120 screen the coolant temperature is displayed as “CHT”.
Tab.12-2: The engine instruments colour marking
12.2.5
Avionics
COMM, COMM/NAV system
The Apollo SL-30 includes a 760-channel VHF Comm transceiver and 200-channel
VOR/LOC/GS navigation receiver with DME display.
NOTE:
For detailed information refer to SL-30 Installation Manual (P/N 560-040403a, latest edition) and Pilot′s Guide (P/N 560-0403-01, latest edition).
Fig. 12-10: SL-30 COMM/NAV
Revision No.: 6
Date of issue: 2016-01-18
12 - 14
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PiperSport
The Apollo SL-40 is a 760-channel VHF Comm transceiver.
NOTE:
For detailed information refer to SL-40 Installation Manual (P/N 560-095602a, latest edition) and Pilot′s Guide (P/N 560-0954-02, latest edition).
Fig. 12-11: SL-40 VHF transceiver
GNC 255A includes a 760-channel (w/ 25 kHz spacing) and 2280-channel (w/ 8.33 kHz
spacing) VHF Comm transceiver and 200-channel VOR/LOC/GS navigation receiver.
NOTE:
For detailed information refer to GTR 225 / GNC 255 TSO Installation
Manual (P/N 190-01182-02, latest edition) and GNC 255A/255B Pilot′s
Guide (P/N 190-01182-01, latest edition).
Fig. 12-12: GNC 255A COMM/NAV
GTR 225A includes a 760-channel (w/ 25 kHz spacing) and 2280-channel (w/ 8.33 kHz
spacing) VHF Comm transceiver..
NOTE:
For detailed information refer to GTR 225 / GNC 255 TSO Installation
Manual (P/N 190-01182-02, latest edition) and GTR 225/225A/225B Pilot′s
Guide (P/N 190-01182-00, latest edition).
Fig. 12-13: GNC 255A COMM/NAV
Date of issue: 2013-06-30
Revision No.: 12 - 15
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
The PM3000 is a panel mounted, 4-place high-fidelity stereo intercom system that allows
the pilot and copilot/passenger to communicate and listen to music.
NOTE:
For detailed information refer to PM3000 Installation Manual (P/N 200-1930005, latest edition) and Pilot′s Guide (P/N 202-193-0001, latest edition).
Fig. 12-14: PM3000 intercom
Navigation system
The panel-mounted GTX 327 is a TSO-certified Mode A/C digital transponder with the
addition of altitude reporting and timing functions such as flight time and count-up and
count-down timers, as well as current pressure altitude.
NOTE:
For detailed information refer to GTX 327 Installation Manual (P/N 19000187-02, latest edition) and Pilot′s Guide (P/N 190-00187-00, latest
edition).
Fig. 12-15: GTX 327 transponder
The panel-mounted GTX 328 is a TSO-certified Mode S digital transponder. In addition to
displaying the code, reply symbol and mode of operation, the GTX 328 screen displays
pressure altitude, density altitude, temperature, and timer functions, depending on
equipment connections and configuration selection. The unit also features an altitude
monitor and flight timers. A voice or tone audio output announces altitude deviation and
count down timer expiration.
NOTE:
For detailed information refer to GTX 328 Maintenance Manual (P/N 19000420-05, latest edition) and Pilot′s Guide (P/N 190-00420-03, latest
edition).
Fig. 12-16: GTX 328 transponder
Revision No.: -
Date of issue: 2013-06-30
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PiperSport
The panel-mounted GTX 330 is a TSO-certified Mode S digital transponder. In addition to
displaying the code, reply symbol and mode of operation, the GTX 330 screen displays
pressure altitude, density altitude, temperature, and timer functions, depending on
equipment connections and configuration selection. The unit also features an altitude
monitor, TIS traffic advisories and flight timers. A voice or tone audio output announces
altitude deviation, TIS traffic advisory and count down timer expiration.
NOTE:
For detailed information refer to GTX 330 Installation Manual (P/N 19000207-02, latest edition) and Pilot′s Guide (P/N 190-00207-00, latest
edition).
Fig. 12-17: GTX 330 transponder
The GPSMAP 695/696 is the ultimate portable MFD. This portable GPS navigator presents
GPS-derived analog flight instrumentation, position, navigation, and hazard avoidance
information to the pilot using a bright 7-inch diagonal high-definition sunlight readable color
display.
NOTE:
For detailed information refer to GPS 695/696 Owner′s Manual (P/N 19000919-00, latest edition).
Fig. 12-18: GPSMAP 695/696
Date of issue: 2013-06-30
Revision No.: 12 - 17
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
The Aera 510 presents GPS-derived analog flight instrumentation, position, navigation, and
hazard avoidance information to the pilot using a bright 4.3-inch diagonal high-definition
sunlight readable color display with touch screen.
NOTE:
For detailed information refer to Aera Models 500, 510, 550, 560 Owner′s
Manual (P/N 190-01117-00, latest edition).
Fig. 12-19: GPS Aera 510
The GTN 650 unit is a panel mounted GPS / NAV / COM navigator. The GTN 650 unit is
6.25 in wide and 2.65 in tall. It features a 600 by 266 pixel color LCD touchscreen. The GTN
750 is a GPS / SBAS unit that meets requirements TSO-C146c and may be approved for
IFR en route, terminal, oceanic, non precision and precision approach operations. The GTN
650 unit includes an airborne VHF communications transceiver and airborne VOR / LOC
and G / S receivers.
NOTE:
For detailed information refer to GTN 6XX/ 7XX AML STC Installation
Manual (P/N 190-01007-A3, latest edition) and Pilot′s Guide (P/N 19001004-03, latest edition).
Fig. 12-20: GPS / NAV / COM GTN 650
Revision No.: -
Date of issue: 2013-06-30
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PiperSport
The GTN 750 unit is a panel mounted GPS / NAV / COM navigator. The GTN 750 unit is
6.25 in wide and 6.00 in tall. It features a 600 by 708 pixel color LCD touchscreen which
provides a rich and intuitive user interface. The GTN 750 is a GPS / SBAS unit that meets
requirements TSO-C146c and may be approved for IFR en route, terminal, oceanic, non
precision and precision approach operations. The GTN 750 unit includes an airborne VHF
communications transceiver and airborne VOR / LOC and G / S receivers.
NOTE:
For detailed information refer to GTN 6XX/ 7XX AML STC Installation
Manual (P/N 190-01007-A3, latest edition) and Pilot′s Guide (P/N 19001007-03, latest edition).
Fig. 12-21: GPS / NAV / COM GTN 750
Date of issue: 2013-06-30
Revision No.: 12 - 19
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
The Aera 795/796 GPS is the ultimate MFD and incorporates the features of the Garmin
GPSMAP 695/696, while adding new capabilities such as a touchscreen interface,
selectable screen orientation (landscape or portrait), and 3-D Vision. The Aera 795/796 also
takes the pilot one step closer to a paperless cockpit with a digital document viewer, scratch
pad and pre-loaded geo-referenced AeroNav IFR and VFR enroute charts. The aera 796 is
XM-weather capable.
NOTE:
For detailed information refer to Aera models: 795 and 796 Owner′s
Manual (P/N 190-01194-00, latest edition).
Fig. 12-22: GPS Aera 795/796
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
SportCruiser
PiperSport
Antennas
Fig. 12-23 shows the antenna locations. The COMM antenna (1) is installed on the upper
part of the fuselage behind the canopy. The ELT antenna (3) is installed directly in the rear
of the COMM antenna. The NAV antenna (2) is installed on the top of the fin. The
transponder antenna (4) is installed on the bottom part of the fuselage. The GPS antenna
(for GPSMAP 695/696 and GPS Aera 510) is attached to the upper side of the instrument
panel cover; GPS antenna (5) for GTN 750 GPS / NAV / COM is installed on the upper part
of the fuselage in front of canopy.
1
2
3
4
5
COMM antenna
NAV antenna
ELT antenna
XPDR antenna
GPS antenna
Fig. 12-23: Antenna locations
12.2.6
Dynon SkyView system
Dynon SkyView system is the next generation of glass panel avionics for light sport aircraft.
The system architecture is shown on Fig. 12-24.
The SV-D1000 / D1000T / HDX 1) displays are very bright, high-resolution screens and
contain the main control CPU, graphics processor, and terrain data-base. Displays can act
as a Primary Flight Display (PFD) with Synthetic Vision, an Engine Monitoring System
(EMS), and a Moving Map in a variety of customizable screen layouts.
The most used functions are accessed via two rotary/multi-direction joysticks. Almost all
other in flight commands are all available via eight buttons.
Every SkyView system display and module is connected by two independent power and
data buses. The failure of any bus connection or module results in automatic fail-over to a
working bus or module.
1) D100T and HDX 1100 are touch technology displays
Date of issue: 2013-06-30
Revision No.: 12 - 21
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
Two SV-BAT-320 Backup Batteries provides over an hour of backup power to displays and
modules.
SV-EMS-220 engine module measures engine parameters - engine speed, manifold
pressure, oil temperature and pressure, exhaust gas temperature, cylinder head/coolant*
temperature, fuel quantity, voltage, current, fuel pressure, fuel flow, flap and trim position.
The SV-ADAHRS-200 and SV-ADAHRS-201 is a complete MEMS-based attitude reference
and air data computer, integrated with a digital compass. This allows easier mounting and
higher accuracy calibration between the system components.
* Coolant temperature in case the engine is equipped with new cylinder heads;
P/N 413185 for 2/3 cylinder head.
SV32 servos enable SkyView to operate as an autopilot.
The SV-XPNDR-261 is a Class 1 Mode S transponder is controlled using the SkyView’s onscreen menu system. This allows the transponder to be mounted separately from the
instrument panel, and reduces the amount of panel space taken by the transponder.
SkyView also provides pressure altitude directly to the transponder, eliminating the need for
a separate altitude encoder.
NMEA compatible GPS receiver is connected to the SkyView system.
Convenient program and data updates via USB memory stick.
NOTE:
For detailed information refer to SkyView System Installation Guide
(Document 101320-013, latest revision) and SkyView Pilot′s User Guide
(Document 101321-012, latest revision).
Fig. 12-24: SkyView system architecture
Revision No.:8
Date of issue: 2017-06-30
12 - 22
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.3
Removal / Installation
12.3.1
Removal of the pitot-static tube
SportCruiser
PiperSport
Type of maintenance: line
Authorization to perform:
Repairman (LS-M) or Mechanic (A&P)
-
Tools needed:
-
Phillips PH1 screwdriver
-
pliers, cutting pliers
(a) Loose securing bolt (4, Fig. 12-25) in the pitot-static tube bracket (2) and pull out a bit
the pitot-static tube (1) with hoses from the bracket.
(b) Remove the cable ties from hoses (3). The hose and tube for static pressure line mark
by S letter and for total pressure mark by T letter.
(c) Disconnect the transparent hoses (3) of static and total pressure from the ports on the
pitot-static tube (1).
1
2
3
4
Pitot-static tube
Bracket
Hose
Bolt
Fig. 12-25: Removal / installation of the pitot-static tube
12.3.2
Installation of the pitot-static tube
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Date of issue: 2013-06-30
Revision No.: 12 - 23
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
Tools needed:
-
Phillips PH1 screwdriver
-
pliers, cutting pliers
(a) Connect the hoses (3, Fig. 12-25) to the ports on the pitot-static tube (1) and secure
them with cable ties.
WARNING:
WHEN CONNECTING THE PITOT-STATIC SYSTEM HOSES PAY
INCREASED ATTENTION. THERE MUST NOT BE ANY INCORRECT
CONNECTION! CONNECT THE HOSE MARKED S LETTER TO THE
PORT MARKED BY S LETTER AND THE HOSE MARKED T LETTER
TO THE PORT MARKED BY T LETTER.
(b) Insert the pitot-static tube (1) in the bracket (2).
(c) Secure pitot-static tube by means of securing bolt (4).
(d) Carry out check of pitot-static system tightness / Dynon avionics pitot / static test (see
12.4.1, 12.4.2).
(e) Check, that pitot-tube is parallel to bottom wing skin.
12.3.3
Removal of the stall warning system lift detector
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver, screwdriver
(a) Set the MASTER BAT, AVIONICS switches to OFF.
(b) Remove the cover on the underside of the wing near the lift detector.
(c) Remove the screws (4, Fig. 12-26) and carefully pull the lift detector (1).
(d) Remove the screws (3) and disconnect the wires (2).
12.3.4
Installation of the stall warning system lift detector
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver, screwdriver
(a) Connect the wires (2, Fig. 12-26) to the appropriate points on the lift detector (see
Wiring Manual); screw and tighten the screws (3).
(b) Insert the lift detector (1) into the hole in the wing leading edge (5).
(c) Align the detector (1) so that the tab was located 8 mm from the leading edge (see Fig.
12-22); screw and tighten the screws (4).
(d) Set the MASTER BAT, AVIONICS switches to ON, press STALL WARNING TEST
button and check test of the system.
(e) Carry out flight test, verify stall warning speed (see 12.4.8.).
Revision No.: -
Date of issue: 2013-06-30
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PiperSport
1 Lift detector
2 Wire
3 Screw
4 Screw (4 pcs.)
5. Leading edge
Fig. 12-26: Lift detector removal / installation
12.3.5
Removal of the flight instruments
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH1 screwdriver
-
pliers, cutting pliers
(a) Remove bolts securing the left instrument panel and carefully pull out and hold the
instrument panel.
(b) Remove the cable ties (9, Fig. 12-27) from the hoses (7; 8).
(c) Disconnect the hoses (7; 8) of static and total pressure from the rear ports on the
appropriate indicator (1; 2).
(d) Disconnect the wires (10) from the illuminator (3).
(e) Unscrew the nuts (5), remove the washers (6) and bolts (4).
(f) Remove the instrument (1; 2) and illuminator (3) from the panel.
(g) Install the protective cover on the rear ports of the instrument.
Date of issue: 2013-06-30
Revision No.: 12 - 25
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PiperSport
1
2
3
4
5
6
CHAPTER 12 – INSTRUMENTS AND AVIONICS
Altimeter
Airspeed indicator
Illuminator
Screw
Nut
Washer
7 Hose
8 Hose
9 Cable tie
10 Wires
For information:
11 Instrument panel
Fig. 12-27: Flight instruments removal / installation
12.3.6
Installation of the flight instruments
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH1 screwdriver
(a) Remove the protective covers from the rear ports of the instrument.
(b) Connect the hoses (7; 8, Fig. 12-27) to the rear ports on the instrument (1; 2) and
secure them with the cable ties (9).
WARNING:
WHEN CONNECTING THE PITOT-STATIC SYSTEM HOSES PAY
INCREASED ATTENTION. THERE MUST NOT BE ANY INCORRECT
CONNECTION! CONNECT THE HOSE MARKED S LETTER TO THE
PORTS MARKED BY S LETTER AND THE HOSE MARKED T LETTER
TO THE PORT MARKED BY T LETTER.
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
NOTE:
SportCruiser
PiperSport
The hose for static pressure line mark by S letter and for total pressure
mark by T letter.
(c) Connect the wires (10) to the illuminator (3).
(d) Put the instrument (1; 2) and illuminator (3) in position in the panel (11).
(e) Attach the instrument (1; 2) with the illuminator (3) by means of the bolts (4), nuts (5)
and washers (6).
(f) Install the left instrument panel (10).
(g) Carry out check of pitot-static system tightness / Dynon avionics pitot / static test (see
12.4.1, 12.4.2)
12.3.7
Removal of the EFIS D100
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
7/64 Allen wrench
-
cutting pliers
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Put a 7/64 Allen wrench into the access hole (2, Fig. 12-28) for the locking screw;
engage the screw.
(c) Turn the screw counter-clockwise until the unit disengages from the mounting rack.
CAUTION:
DO NOT PRY THE FACE-PLATE. YOU CAN DAMAGE THE UNIT.
(d) Pull gently on the sides of the unit (1) to remove it from the mounting rack (9).
(e) Remove the cable ties (7) from hoses (5; 6).
(f) Disconnect the hoses (5; 6) of static and total pressure from the rear ports (3; 4) on the
unit.
(g) Disconnect the connector (4) from the unit.
(h) Install the protective cover on the rear ports (3; 4) of the unit.
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Revision No.: 12 - 27
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1
2
3
4
5
CHAPTER 12 – INSTRUMENTS AND AVIONICS
EFIS D100
Access hole of the locking screw
Static port
Pitot port
Hose
6 Hose
7 Cable tie
8 Connector
For information:
9 Mounting rack
Fig. 12-28: EFIS D100 removal / installation
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.3.8
SportCruiser
PiperSport
Installation of the EFIS D100
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
7/64 Allen wrench
(a) Remove the protective covers from the rear ports on the unit.
(b) Connect the hoses (5; 6, Fig. 12-28) to the rear ports (3; 4) on the unit (1) and secure
them with cable ties (7).
WARNING:
WHEN CONNECTING THE PITOT-STATIC SYSTEM HOSES PAY
INCREASED ATTENTION. THERE MUST NOT BE ANY INCORRECT
CONNECTION! CONNECT THE HOSE MARKED S LETTER TO THE
PORTS MARKED BY STATIC AND THE HOSE MARKED T LETTER TO
THE PORT MARKED BY PITOT.
NOTE:
The hose for static pressure line mark by S letter and for total pressure
mark by T letter.
(c) Connect the connector (4) to the unit.
(d) Slide the unit (1) into the rack (9). Engage the locking screw so that the latch front lobe
touches the rack.
(e) Turn the locking screw clockwise so that the rear lobe engages the mounting rack.
CAUTION:
DO NOT OVER-TIGHTEN THE LOCKING SCREW. YOU CAN DAMAGE
THE LOCKING MECHANISM.
(f) Continue to turn the screw until the unit is fully installed in the mounting rack.
(g) Carry out check of pitot-static system tightness / Dynon avionics pitot / static test (see
12.4.1, 12.4.2).
(h) Set the MASTER BAT / MASTER switches to ON and do an operational test of the
system.
12.3.9
Removal of EDC-10A remote compass module
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
CAUTION:
DO NOT USE STANDARD MOUNTING HARDWARE. ALL MOUNTING
HARDWARE IS MADE FROM BRASS – NON FERROUS MATERIAL.
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Remove the cover on the bottom of the fuselage rear part.
(c) Disconnect the connector (2, Fig. 12-29) from the compass module.
(d) Unscrew the screws (3) with the washers (4) and remove the compass module (1).
Date of issue: 2013-06-30
Revision No.: 12 - 29
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PiperSport
CHAPTER 12 – INSTRUMENTS AND AVIONICS
1 Remote compass module
2 Connector
3 Screw (4 pcs.)
4 Washer (2 pcs.)
For information:
5 Bracket
Fig. 12-29: NAV antenna removal / installation
12.3.10 Installation of EDC-10A remote compass module
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
CAUTION:
DO NOT USE STANDARD MOUNTING HARDWARE. ALL MOUNTING
HARDWARE IS MADE FROM BRASS – NON FERROUS MATERIAL.
(a) Place the compass module (1, Fig. 12-29) on the bracket (5) and fasten it by means of
the screws (3) with the washers (4).
(b) Connect the connector (2) to the compass module.
(c) Install the cover on the bottom of the fuselage rear part.
(d) Perform EFIS compass heading calibration (see Chapter 12.4.4).
12.3.11 Removal of the EMS D120
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
7/64 Allen wrench
-
cutting pliers
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(a) Set the MASTER BAT / MASTER, EMS / INSTR switches to OFF.
(b) Put a 7/64 Allen wrench into the access hole (2, Fig. 12-30 for the locking screw;
engage the screw.
(c) Turn the screw counter-clockwise until the unit disengages from the mounting rack.
CAUTION:
DO NOT PRY THE FACE-PLATE. YOU CAN DAMAGE THE UNIT.
(d) Pull gently on the sides of the unit (1) to remove it from the mounting rack (5).
(e) Disconnect the connectors (3; 4) from the unit.
1 EMS D120
2 Access hole of the locking screw
3 Connector
4 Connector
For information:
5 Mounting rack
Fig. 12-30: EMS D120 removal / installation
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12.3.12 Installation of the EMS D120
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
7/64 Allen wrench
(a) Connect the connectors (3; 4, Fig. 12-30) to the unit (1).
(b) Slide the unit (1) into the rack (5). Engage the locking screw so that the latch front lobe
touches the rack.
(c) Turn the locking screw clockwise so that the rear lobe engages the mounting rack.
CAUTION:
DO NOT OVER-TIGHTEN THE LOCKING SCREW. YOU CAN DAMAGE
THE LOCKING MECHANISM.
(d) Continue to turn the screw until the unit is fully installed in the mounting rack.
(e) Set the MASTER BAT / MASTER, EMS / INSTR switches to ON and do an operational
test of the system.
12.3.13 Removal of transponder
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
3/32 Allen wrench
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Put a 3/32 Allen wrench into the access hole (2, Fig. 12-31) for the locking screw;
engage the screw.
(c) Turn the screw counter-clockwise until the transponder (1) disengages from the
mounting rack.
CAUTION:
DO NOT TOUCH THE CONNECTOR CARD AT THE REAR OF THE
UNIT. THE ELECTROSTATIC CHARGE ON YOUR BODY CAN DAMAGE
THE UNIT.
(d) Pull gently on the sides of the transponder (1) to remove it from the mounting rack (3).
(e) Install the protective covers on the rear connectors of the transponder.
12.3.14 Installation of transponder
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
3/32 Allen wrench
(a) Remove the protective covers from the connectors on the transponder.
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(b) Looking at the bottom of the unit, make sure the front lobe of the locking mechanism is
in a vertical positron.
(c) Slide the transponder (1, Fig. 12-31) into the rack (3). Engage the locking screw so that
the latch front lobe touches the rack.
(d) Turn the locking screw clockwise so that the rear lobe engages the mounting rack.
CAUTION:
DO NOT OVER-TIGHTEN THE LOCKING SCREW. YOU CAN DAMAGE
THE LOCKING MECHANISM.
(e) Continue to turn the screw until the transponder is fully installed in the mounting rack.
(f) Set the MASTER BAT / MASTER, AVIONICS switches to ON and do an operational
test.
NOTE
The location of the transponder
may be different.
1 Transponder
2 Access hole of the locking screw
For information:
3 Mounting rack
Fig. 12-31: Transponder removal / installation
12.3.15 Removal of COMM, COMM / NAV
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
3/32 Allen wrench
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
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(b) Put a 3/32 Allen wrench into the access hole (2, Fig. 12-32) for the locking screw;
engage the screw.
(c) Turn the screw counter-clockwise until the unit (1) disengages from the mounting rack.
CAUTION:
DO NOT PULL ON THE KNOBS. DO NOT PRY THE FACE-PLATE. YOU
CAN DAMAGE THE UNIT.
DO NOT TOUCH THE CONNECTOR CARD AT THE REAR OF THE
UNIT. THE ELECTROSTATIC CHARGE ON YOUR BODY CAN DAMAGE
THE UNIT.
(d) Pull gently on the sides of the unit (1) to remove it from the mounting rack (3).
(e) Install the protective covers on the rear connectors of the unit.
1 COMM/NAV unit
2 Access hole of the locking screw
For information:
3 Mounting rack
Fig. 12-32: COMM / NAV unit removal / installation
12.3.16 Installation of COMM, COMM / NAV
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
3/32 Allen wrench
(a) Remove the protective covers from the connectors on the unit.
(b) Looking at the bottom of the unit, make sure the front lobe of the locking mechanism is
in a vertical positron.
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(c) Slide the unit (1, Fig. 12-32) into the rack (3). Engage the locking screw so that the latch
front lobe touches the rack.
(d) Turn the locking screw clockwise so that the rear lobe engages the mounting rack.
(e) Continue to turn the screw until the unit is fully installed in the mounting rack.
CAUTION:
DO NOT OVER-TIGHTEN THE LOCKING SCREW. YOU CAN DAMAGE
THE LOCKING MECHANISM.
(f) Set the MASTER BAT / MASTER, AVIONICS switches to ON and do an operational
test.
12.3.17 Removal of intercom
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH1 screwdriver
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Disconnect the connector (5, Fig. 12-33) from the unit.
(c) Remove the knobs (2) from the volume and squelch control shafts.
(d) Unscrew the screws (4) and remove the faceplate (3).
(e) Carefully remove the unit (1).
CAUTION:
DO NOT TOUCH THE CONNECTOR CARD AT THE REAR OF THE
UNIT. THE ELECTROSTATIC CHARGE ON YOUR BODY CAN DAMAGE
THE UNIT.
(f) Install the protective cover on the rear connector of the unit.
12.3.18 Installation of intercom
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH1 screwdriver
(a) Remove the protective cover from the connector on the unit.
(b) Insert the unit (1, Fig. 12-33) from behind the instrument panel, aligning the holes for the
knobs, LED, and switch.
(c) Place the faceplate (3) over the knob shafts and secure it by means of the two screws
(4).
(d) Install the knobs (2) over the volume and squelch control shafts.
(e) Connect the connector (5) to the unit (1).
(f) Set the MASTER BAT / MASTER, AVIONICS switches to ON and do an operational
test.
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2
3
4
CHAPTER 12 – INSTRUMENTS AND AVIONICS
Intercom
Knob
Faceplate
Screw
5 Connector
For information:
6 Instrument panel
Fig. 12-33: Intercom removal / installation
12.3.19 Removal of GPS / NAV COM
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
3/32 Allen wrench
NOTE:
The procedure of removal / installation is the same for both units (GTN 650
and GTN 750).
(a) Set the MASTER BAT / MASTER, GPS switches to OFF.
(b) Put a 3/32 Allen wrench into the access hole (2, Fig. 12-34) for the locking screw;
engage the screw.
(c) Turn the screw counter-clockwise until the unit (1) is forced out about 9.5 mm (3/8 in)
and can be freely pulled from the mounting rack.
CAUTION:
DO NOT PULL ON THE KNOBS. DO NOT PRY THE FACE-PLATE.
YOUCAN DAMAGE THE UNIT.
DO NOT TOUCH THE CONNECTOR CARD AT THE REAR OF THE
UNIT. THE ELECTROSTATIC CHARGE ON YOUR BODY CAN DAMAGE
THE UNIT.
(d) Pull gently on the sides of the unit (1) to remove it from the mounting rack (3).
(e) Install the protective covers on the rear connectors of the unit.
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PiperSport
1 GPS / NAV / COM unit
2 Access hole of the locking screw
For information:
3 Mounting rack
Fig. 12-34: GPS / NAV / COM unit removal / installation
12.3.20 Installation of GPS / NAV COM
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
3/32 Allen wrench
NOTE:
The procedure of removal / installation is the same for both units (GTN 650
and GTN 750).
(a) Remove the protective covers from the connectors on the unit.
(b) Looking at the bottom of the unit, make sure the front lobe of the locking mechanism is
in a vertical positron.
(c) Slide the unit (1, Fig. 12-34) straight in the rack until it stops about 25 mm (1 in) short of
the final position.
(d) Insert Allen wrench into access hole (2).
(e) Turn the locking screw clockwise while press on the left side of the bezel unit until the
unit is firmly seated in the rack the mounting rack.
CAUTION:
DO NOT OVER-TIGHTEN THE LOCKING SCREW. THE APPLICATION
OF THE ALLEN WRENCH TORQUE EXCEEDING 0.01 Nm (15 lb in)
CAN DAMAGE THE LOCKING MECHANISM.
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(f) Set the MASTER BAT / MASTER, GPS switches to ON and do a post installation (see
17.6) and operational test.
12.3.21 Removal of COMM antenna
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
-
wrench No. 7
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Disconnect the connector (4, Fig. 12-35) from the antenna.
(c) Remove the nuts (4) with the washers (5)
(d) Remove the antenna (1) with the gasket (2), screws (3) and washers (6).
(e) Install the protective cover on the antenna connector.
1 COMM antenna
2 Gasket
3 Screw (4 pcs.)
4 Nut (4 pcs.)
5 Washer (4 pcs.)
6 Tooth washer (4 pcs.)
7 Cable connector
For information:
8 Fuselage upper part
Fig. 12-35 COMM antenna removal / installation
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
12.3.22 Installation of COMM antenna
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
-
wrench No. 7
(a) Remove the protective cover from the antenna connector.
(b) Place the antenna (1, Fig. 12-35) with the gasket (2) on the fuselage (8).
(c) Insert the screws (3) with washers (6) to the holes in the antenna body (1); install the
washers (5), screw and tighten the nuts (4).
(d) Connect the connector (7) to the antenna (1).
(e) Set the MASTER BAT / MASTER, AVIONICS switches to ON and do an operational
test.
12.3.23 Removal of NAV antenna
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
-
wrench No. 8
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Unscrew the screws (7, Fig. 12-36) and remove the fin tip (6).
(c) Remove the nuts (4) and disconnect the cables (5) from antenna studs.
(d) Unscrew the screws (2) with the washers (3) and remove the antenna (1).
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
1 NAV antenna
2 Screw (2 pcs.)
3 Washer (2 pcs.)
4 Nut (2 pcs.)
5 Cable (2 pcs.)
6 Fin tip
7 Screw (8 pcs.)
For information:
8 Fin
Fig. 12-36: NAV antenna removal / installation
12.3.24 Installation of NAV antenna
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
-
wrench No. 8
(a) Place the antenna (1, Fig. 12-36) on the bracket and fasten it by means of the screws
(2) with the washers (3).
(b) Connect the cables (5) to the antenna studs; screw and fasten the nuts (4).
(c) Place the fin tip (6) on the fin (8) and fasten it by means of the screws (7).
(d) Set the MASTER BAT / MASTER, AVIONICS switches to ON and do an operational
test.
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12.3.25 Removal of transponder antenna
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 3/4 in
(a) Tilt forward the right seat back.
(b) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(c) Disconnect the connector (4, Fig. 12-37) from the antenna.
(d) Unscrew the nut (2), remove the washer (3) and the antenna (1).
(e) Install the protective cover on the antenna connector.
1 XPDR antenna
2 Nut
3 Lockwasher
4 Cable connector
For information:
5 Fuselage bottom part
Fig. 12-37: Transponder antenna removal / installation
12.3.26 Installation of transponder antenna
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 3/4 in
(a) Remove the protective cover from the antenna connector.
(b) Insert the antenna (1, Fig. 12-37) to the hole in the fuselage bottom part (5).
(c) Insert the washer (3), screw and tighten the nut (2).
(d) Connect the connector (4) to the antenna (1).
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(e) Place the fin tip (6) on the fin (8) and fasten it by means of the screws (7).
(f) Tilt backward the right seat back.
(g) Set the MASTER BAT / MASTER, AVIONICS switches to ON and do an operational
test.
12.3.27 Removal of GPS antenna
NOTE:
This type of antenna is used when GPS / NAV / COM unit is installed.
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Set the MASTER BAT / MASTER, GPS switches to OFF.
(b) Disconnect the connector (4, Fig. 12-38) from the antenna.
(c) Remove the sealant around the antenna.
(d) Remove the screws (2) with and the antenna (1).
(e) Clean sealant residues.
(f) Install the protective cover on the antenna connector.
1 GPS antenna
2 Screw
3 Cable connector
For information:
4 Fuselage upper part
Fig. 12-38: GPS antenna removal / installation
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12.3.28 Installation of GPS antenna
NOTE:
This type of antenna is used when GPS / NAV / COM unit is installed.
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Remove the protective cover from the antenna connector.
(b) Place the antenna (1, Fig. 12-38) on the fuselage (4).
(c) Insert the screws (3) to the holes in the antenna body (1); screw and tighten the screws.
(d) Apply sealant (Emfimastic PU-50, white) around the antenna.
(e) Connect the connector (3) to the antenna (1).
(f) Set the MASTER BAT / MASTER, GPS switches to ON and do an operational test.
12.3.29 Removal of the SV-D1000 display
NOTE:
Removal is the same for both displays.
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
5/64” hex drive tool
-
screwdriver
(a) Set the MASTER BAT, EFIS1 / EFIS 2 switches to OFF.
(b) Unscrew the screws (6, Fig. 12-39) and release the display (1).
(c) Pull gently on the sides of the display (1) and carefully remove it.
(d) Disconnect the connectors (2; 3; 4; 5) from the display.
(e) Install the protective covers on the rear connectors of the display
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2
3
4
CHAPTER 12 – INSTRUMENTS AND AVIONICS
SV-D1000 display
DB37 display connector
SkyView network connector
USB connector
5 Ethernet connector
6 Screw (6 pcs.)
For information:
7 Instrument panel
Fig. 12-39: SV-D1000 display removal / installation
12.3.30 Installation of SV-D1000 display
NOTE:
Installation is the same for both displays.
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
5/64” hex drive tool
-
screwdriver
(a) Connect the connectors (2; 3; 4; 5, Fig. 12-39) to the display (1).
(b) Slide the display (1) to the panel (7) and fasten it by means of the screws (7).
(c) Set the MASTER BAT, EFIS1 / EFIS 2 switches to ON and do an operational test of the
system.
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12.3.31 Removal of EFIS D1100
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
7/64 Allen wrench
-
cutting pliers
(a) Set the MASTER BAT / MASTER, AVIONICS switches to OFF.
(b) Unscrew the mounting screws (6) attaching the HDX1100 (1) to the instrument panel
(c) Slide the HDX1100 (1) out of the instrument panel
(d) Disconnect the connectors (2,3,4,5) from the HDX1100 (1)
12.3.32 Installation of EFIS D1100
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
7/64 Allen wrench
(e) Connect the connectors (2,3,4,5) to the unit HDX1100 (1).
(f) Insert the HDX1100 (1) into the instrument panel hole
(g) Attach the HDX1100 (1) to the instrument panel with the screws (6).
(h) Set the MASTER BAT / MASTER switches to ON and do an operational test of the
system.
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
1 SV-HDX1100 display
2 DB37 display connector
3 SkyView network connector
4 USB connector
5 Ethernet connector
6 Screw (4 pcs.)
Fig. 12-40: EFIS D1100 removal / installation
12.3.33 Removal of SV-BAT-320 backup battery / batteries
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Set the MASTER BAT, EFIS1 / EFIS 2 switches to OFF.
(b) Remove the instrument panel cover (valid for airplanes manufactured before June
2013).
(c) Disconnect the connector (7, Fig. 12-41) from the backup battery (6).
(d) Unscrew the screws (8) and remove the backup battery (6).
12.3.34 Installation of of SV-BAT-320 backup battery / batteries
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
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Tools needed:
-
Phillips PH2 screwdriver
(a) Place the backup battery (6, Fig. 12-41) on the bracket (10 or 12) and fasten it by
means of the screws (8).
(b) Connect the connector (7) to the backup battery.
(c) Install the instrument panel cover (valid for airplanes manufactured before June 2013).
(d) Set the MASTER BAT, EFIS1 / EFIS 2 switches to ON and check backup battery
function.
12.3.35 Removal of SV-EMS-220 module
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Set the MASTER BAT, EFIS1 / EFIS 2 switches to OFF.
(b) Remove the instrument panel cover (valid for airplanes manufactured before June
2013).
(c) Disconnect the connectors (2; 3; 4, Fig. 12-41) from the EMS module (1).
(d) Unscrew the screws (5) and remove the EMS module (1).
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Date of issue: 2013-06-30
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1
2
3
4
5
6
7
SV-EMS-220 module
DB37 main sensor connector
DB25 CHT/CT*/EGT sensor connector
SkyView network connector
Screw (4 pcs.)
SV-BAT-320 backup battery
Connector
SportCruiser
PiperSport
8 Screw (2 pcs.)
For information:
9 Bracket
10 Bracket
11 Bracket
12 Bracket
* Applicable in case the engine is equipped with new cylinder heads;
P/N 413185 for 2/3 cylinder head.
Fig. 12-41: SV-EMS-220 engine module and SV-BAT-320 backup battery removal / installation)
12.3.36 Installation of SV-EMS-220 module
Type of maintenance: line
Authorization to perform:
- Repairman (LS-M) or Mechanic (A&P)
Tools needed:
- Phillips PH2 screwdriver
(a) Place the EMS module (1, Fig. 12-41) on the bracket (9 or 11) and fasten it by means of
the screws (5).
(b) Connect the connectors (2; 3; 4) to the EMS module.
(c) Install the instrument panel cover (valid for airplanes manufactured before June 2013).
(d) Set the MASTER BAT, EFIS1 / EFIS 2 switches to ON and do operational test of the
system.
12.3.37 Removal of SV-ADAHRS-200 / 201 module
NOTE:
Removal the same for both ADAHRS modules.
Type of maintenance: heavy
Authorization to perform:
- Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 7
Cobra hose clip pliers
CAUTION:
DO NOT USE STANDARD MOUNTING HARDWARE. ALL MOUNTING
HARDWARE IS MADE FROM BRASS – NON FERROUS MATERIAL.
(a) Set the MASTER BAT, EFIS1 / EFIS 2 switches to OFF.
(b) Remove the covers on the bottom of the fuselage rear part.
(c) Disconnect the connectors (2; 3, Fig. 12-42) from the ADAHRS module (1).
(d) Remove the hose clips (7) from hoses (5; 6).
(e) Disconnect hoses (6) of static and total pressure from the ports (4; 5) on the ADAHRS
module.
(f) Loose nuts (9), unscrew and remove the screws (8), nuts (9), washers (10) and the
ADAHRS module (1).
(g) Install the protective cover on the ports (4; 5) of the module.
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12.3.38 Installation of SV-ADAHRS-200 / 201 module
NOTE: Removal the same for both ADAHRS modules.
Type of maintenance: heavy
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 7
- Cobra hose clip pliers
CAUTION:
DO NOT USE STANDARD MOUNTING HARDWARE. ALL MOUNTING
HARDWARE IS MADE FROM BRASS – NON FERROUS MATERIAL.
(a) Remove the protective covers from the ports on the module.
(b) Insert the screws (8, Fig. 12-42) into ADAHRS module (1) mounting holes, place
washers (10) and screw the nuts (9); do not tighten it.
(c) Place the ADAHRS module (1) on the bracket (14) and fasten it by means of the screws
(8).
(d) Set the module (1) using the screws (8) so that the module is parallel to the fuselage
basic level, tighten the nuts (9). An ADAHRS module should be mounted within one
degree of parallel to all three aircraft axes.
(e) Connect the hoses (6) to the ports (3; 4) on the ADAHRS module (1) and secure them
with hose clips (7).
WARNING:
WHEN CONNECTING THE PITOT-STATIC SYSTEM HOSES PAY
INCREASED ATTENTION. THERE MUST NOT BE ANY INCORRECT
CONNECTION! CONNECT THE HOSE MARKED S LETTER TO THE
PORTS MARKED BY STATIC AND THE HOSE MARKED T LETTER TO
THE PORT MARKED BY PITOT.
NOTE:
The hose for static pressure line mark by S letter and for total pressure
mark by T letter.
(f) Connect the connectors (2; 3) to the ADAHRS module.
(g) Install the covers on the bottom of the fuselage rear part.
(h) Carry out check of pitot-static system tightness / Dynon avionics pitot / static test (see
12.4.1, 12.4.2).
(i)Set the MASTER BAT, EFIS1 / EFIS 2 switches to ON and do operational test of the
system.
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1
2
3
4
5
6
7
8
SV-ADAHRS-200 module
SkyView network connector
OAT probe connector
Pitot port
Static port
Hose
Hose clip
Screw (4 pcs.)
SportCruiser
PiperSport
9 Nut (4 pcs.)
10 Washer (4 pcs.)
11 SV-OAT-340 probe
12 Nut
13 Washer
For information:
14 Bracket
15 Fuselage skin
Fig. 12-42: SV-ADAHRS-200 module and SV-OAT-340 probe removal / installation
12.3.39 Removal of SV-OAT-340 probe
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 9/16 in
(a) Set the MASTER BAT, EFIS1 / EFIS 2 switches to OFF.
(b) Remove the covers on the bottom of the fuselage rear part.
(c) Disconnect connector (3, Fig. 12-42) from the ADAHRS module (1).
(d) Remove fastening members of the probe wires.
(e) Remove the connector (3) and pins from the probe wires
(f) Unscrew the nut (12), remove the washer (13) and pull out the probe (11).
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12.3.40 Installation of SV-OAT-340 probe
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench No. 9/16 in
NOTE:
Do not insert the pins on the ends of the OAT probe wires into the
connector until you are done running probe wires through the aircraft.
(a) On the outside of the fuselage, insert the wires and the probe (1, Fig. 12-42) through the
hole on the fuselage bottom skin (15).
(b) On the inside of the fuselage, insert the washer (13) and the nut (12) over the wires.
(c) Hand-thread the nut (12) onto the probe (11). At this point, the washer (13) should be
sandwiched between the nut (12) and the fuselage bottom skin (15); then carefully
tighten the nut using the wrench.
(d) Route and secure the probe wires to the location of the ADAHRS module.
(e) Carefully insert the pins on the wires into the connector. Pins are not polarized and lock
into place when inserted correctly.
(f) Connect the connector (3) to the ADAHRS module (1).
(g) Install the covers on the bottom of the fuselage rear part.
(h) Set the MASTER BAT, AVIONICS switches to ON and do an operational test.
12.3.41 Removal of SV-XPDR-261 transponder
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
(a) Set the MASTER BAT, AVIONICS switches to OFF.
(b) Tilt forward the right seat back (valid for airplanes manufactured before June 2013).
(c) Disconnect the connectors (2; 3, Fig. 12-43) from the transponder (1).
(d) Unlock the retaining wire (5) and remove the transponder (1) from the mounting tray (4).
(airplanes manufactured in June 2013 and later have mounting tray installed from
bellow the bracket (16)).
(e) Install the protective cover on the antenna connector.
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1
2
3
4
5
6
7
8
9
SV-XPDR-261 transponder
SkyView network connector
Antenna connector
Mounting tray
Retaining wire
Static pressure drain sump
Total pressure drain sump
Hose clip
Hose
SportCruiser
PiperSport
10 Drain sump body
11 Nut
12 O-ring
13 Drain sump bowl
14 Nut
For information:
15 Bracket
16 Bracket
Fig. 12-43: SV-XPDR-261 transponder and drain sumps removal / installation
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12.3.42 Installation of SV-XPDR-261 transponder
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
screwdriver
(a) Remove the protective cover from the antenna connector
(b) Put the transponder (1, Fig. 12-43) into the mounting tray (4) by hooking the connector
end under the lip on the tray.
(c) Lock the transponder (1) into the mounting tray (4) by clipping the retaining wire (5) over
the lugs on the opposite end (airplanes manufactured in June 2013 and later have
mounting tray installed from bellow the bracket (16)).
(d) Connect the connectors (2; 3) to the transponder.
(e) Tilt backward the right seat back (valid for airplanes manufactured before June 2013).
(f) Set the MASTER BAT, AVIONICS switches to ON and do an operational test.
12.3.43 Removal of drain sump
NOTE:
Following procedure valid for the airplanes manufactured after April 2013.
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Cobra hose clip pliers
-
wrench No. 27
(a) Tilt forward the left seat back.
(b) Remove the hose clips (8, Fig. 12-43) from hoses (9).
(c) Disconnect hoses (9) of from the drain sump body (10); install protective covers on the
hoses and hose ports of the drain sump body.
(d) Unscrew and remove the nut (14) with the drain sump bowl (13); unscrew and remove
the nut (11) and remove the drain sump body (10) from the bracket (15).
12.3.44 Installation of drain sump
NOTE:
Following procedure valid for the airplanes manufactured after April 2013.
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Cobra hose clip pliers
-
wrench No. 27
(a) Tilt forward the left seat back.
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(b) Insert the drain sump body (10, Fig. 12-43) into the hole in the bracket (15) and fasten it
with the nut (11).
(c) Check the condition of the o-ring (12) a transparent drain sump bowl (13) - replace
damaged parts.
(d) Insert the O-ring (12) to the drain sump body (10), set the drain sump bowl (13) to the
drain sump body, screw and carefully tighten the nut (14).
CAUTION:
DURING INSTALLATION OF THE DRAIN SUMP AVOID INCORRECT
SEATING OF THE O-RING BETWEEN THE DRAIN SUMP BODY AND
THE DRAIN SUMP BOWL.
(e) Remove the protective covers from the hoses and hose sockets of the drain sump body.
(f) Connect the hoses (9) to the ports on the drain sump body (10) and secure them with
hose clips (8).
(g) Carry out check of pitot-static system tightness test (see 12.4.1).
12.3.45 Draining of drain sumps
NOTE:
12.3.43.1
If you find impurities or water in pitot-static system drain sumps, these
sumps must be drain.
SportCruiser airplanes manufactured before April 2013
Tools needed:
-
Cobra hose clip pliers
(a) Tilt forward the left seat back.
(b) Remove the hose clips (8, Fig. 12-43) from hoses (9).
(c) Disconnect hoses (9) of static and total pressure from the drain sumps (6; 7).
(d) Clean and dry the sumps.
(e) Connect the hoses (9) to the drain sumps (6; 7) and secure them with cable clips (8).
(f) Tilt backward the left seat back and carry out check of pitot-static system tightness test
(see 12.4.1).
12.3.43.2
SportCruiser airplanes manufactured after April 2013
Tools needed:
-
wrench No. 27
(a) Tilt forward the left seat back.
(b) Unscrew and remove the nut (14, Fig. 12-43) with the drain sump bowl (13).
(c) Clean and dry the drain sump bowl (13).
(d) Check the condition of the o-ring (12) a transparent drain sump bowl (13) - replace
damaged parts.
(e) Insert the O-ring (12) to the drain sump body (10), set the drain sump bowl (13) to the
drain sump body, screw and carefully tighten the nut (14).
CAUTION:
DURING INSTALLATION OF THE DRAIN SUMP AVOID INCORRECT
SEATING OF THE O-RING BETWEEN THE DRAIN SUMP BODY AND
THE DRAIN SUMP BOWL.
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
(f) Tilt backward the left seat back and carry out check of pitot-static system tightness test
(see 12.4.1).
12.3.46 Removal of SV-ADSB-470 module
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Set the MASTER BAT, EFIS1 switches to OFF.
(b) Disconnect the connectors (2; 3, Fig. 12-44) from the ADSB module (1).
(c) Unscrew the screws (4) and remove the ADSB module (1).
1 SV-ADSB-470 module
2 Serial connector
3 Antenna connector
4 Screw (4 pcs.)
For information:
5 Bracket
Fig. 12-44: SV-ADSB transponder removal / installation
12.3.47 Installation of SV-ADSB-470 module
Type of maintenance: line
Authorization to perform:
-
Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Phillips PH2 screwdriver
(a) Place the ADSB module (1, Fig. 12-44) on the bracket (5) and fasten it by means of the
screws (4).
(b) Connect the connectors (2; 3) to the ADSB module.
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(c) Set the MASTER BAT, EFIS1 switches to ON and do operational test of the system.
12.4
Check / Adjustment
12.4.1
Check of pitot-static system tightness
(a) In the static pressure system create the under pressure by means of an appropriate
instrument corresponding to altitude of 1,000 ft. Drop in the indicated altitude per one
minute must not exceed 100 ft.
(b) In the system of total pressure create the overpressure corresponding to speed of
140 knots (260 km/h, 161 mph) by means of a suitable instrument. Drop in speed during
3 minutes must not exceed 2.3 knots (4.4 km/h, 2.7 mph).
12.4.2
Dynon avionics pitot / static test
Dynon ADAHRS / EFIS units use airspeed (or GPS ground speed when airspeed is
unavailable) in the calculation of attitude. The internal rate sensors that are used to
determine attitude are monitored and calibrated in-flight by using feedback from the
accelerometers and from airspeed to achieve a highly accurate attitude solution.
When a pitot or static test is performed, the ADAHRS / EFIS is being exposed to dynamics
that are impossible to achieve in a real airplane flight environment – namely, there are large
airspeed changes without the accompanying accelerations and rotations. This false
condition will cause a well-calibrated unit to incorrectly adjust its calibration. Furthermore,
when a unit is in a test situation a change in applied pitot or static pressure will cause the
attitude to pitch up or down. This is expected.
Performing the Dynon prescribed pitot and static test procedure to a Dynon ADAHRS or
EFIS will prevent problems with the unit’s performance in flight.
Dynon pitot / static test Instructions
Basic principles:
•
Ensure unit is warmed up during each test reading.
•
Unit should be powered off when changing pressures.
•
Keep aircraft still (do not move) when pressure is applied.
Steps:
(a) The airplane itself should be temperature stable. For example, if the aircraft is moved
from outside in the sun to a hangar for testing, tests should not be started until the
airplane has stabilized at the hangar temperature.
(b) Turn EFIS on and let it warm up until the altitude reading is stabilized. This period
should be at least 5 minutes, but may take longer depending on environmental
conditions.
(c) Turn EFIS off.
(d) While the EFIS is off, apply the pressure required by your test to pitot and / or static port
via your test equipment.
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(e) Turn on EFIS (external or internal battery power is acceptable). Keep airplane still while
EFIS is powered on. Do not adjust the pitot or static pressures being applied to the EFIS
/ ADAHRS while it is powered on.
(f) Verify airspeed and/or altitude reading.
(g) Turn EFIS off (using button 1 is a good option for this operation).
(h) Repeat steps 4-7 for each required pressure point in the test.
12.4.3
Magnetic compass compensation
Rules for doing compensation of the compasses:
(a) Compass compensation must be performed on the approved compass bases, which are
at least 100 m (300 ft) from steel structures, electric leading or other over ground or
underground steel equipment or objects.
(b) If the compass north is westward from magnetic north, the deviation is westward, i.e.
negative. If the compass north is eastward from magnetic north, the deviation is
eastward, i.e. positive.
Compensation procedure:
(a) Turn the airplane to "N" heading; eliminate the deviation by "C" screw.
(b) Turn the airplane to "S" heading; reduce the found out deviation to the half-value by "C"
screw and write down the rest of the deviation.
(c) Turn the airplane to "E" heading; eliminate the deviation by "B" screw.
(d) Turn the airplane to "W" heading; reduce the found out deviation to the half-value by "B"
screw and write down the rest of the deviation.
(e) Turn the airplane by grades indicated in the compensation report (see Tab. 12-3; 12-4)
and write down individual deviations in the table.
(f) After finishing compensation of the magnetic compass fill out the deviation card (see
Fig. 12-45) and position it in the airplane near the magnetic compass.
12.4.4
EFIS compass heading calibration
Procedures are mentioned in EFIS D100 Installation Guide (P/N 100487-000, latest edition).
12.4.5
ADHRS magnetic heading calibration
Procedures are mentioned in SkyView System Installation Guide (P/N 101320-008, latest
edition).
Fig. 12-45: Example of the deviation card
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
REPORT OF MAGNETIC COMPASS SWING
Aircraft
Aircraft S/N
Compass type
Check 1.
Compass S/N
All electrical equipment ON and operating
The engine running, idle
Fuselage placed in flying attitude
XPDR ON, XCVR receiving
Check 2.
Switched ON just those instruments, which are necessary for VFR flight. COM, NAV,
XPDR, lights - switched OFF
The engine running, idle
Fuselage placed in flying attitude
Heading
N
Measured
1.
Deviation
2.
1.
2.
000
030
060
E
090
120
150
S
180
210
240
W
270
300
330
Maximal allowed deviation ± 10°
If the compass deviations are not identical for both checks, two separate compass correction cards
should be done.
Note:
General evaluation
Performed by:
Complied
Elaborated by:
Failed
Date:
Tab. 12-3: Report of magnetic compass compensation
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CHAPTER 12 – INSTRUMENTS AND AVIONICS
REPORT OF EFIS COMPASS SWING
Aircraft
Aircraft S/N
Compass type
EFIS type
Check 1.
EDC-D10A
Compass S/N
DYNON D100
EFIS S/N
All electrical equipment ON and operating
The engine running, idle
Fuselage placed in flying attitude
XPDR ON, XCVR receiving
Check 2.
Switched ON just those instruments, which are necessary for VFR flight. COM, NAV,
XPDR, lights - switched OFF
The engine running, idle
Fuselage placed in flying attitude
Heading
N
Measured
1.
Deviation
2.
1.
2.
000
030
060
E
090
120
150
S
180
210
240
W
270
300
330
Maximal allowed deviation ± 10°
If the compass deviations are not identical for both checks, two separate compass correction cards
should be done.
Note:
General evaluation
Performed by:
Complied
Elaborated by:
Failed
Date:
Tab. 12-4: Report of magnetic compass compensation
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12.4.6
SportCruiser
PiperSport
EFIS D100 internal emergency battery check
EFIS-D100 has a rechargeable internal emergency battery, it is necessary to ensure that
the battery capacity is such that it will last at least 2 hours on a full charge. Once per year,
perform the battery capacity test. Procedure and replacing the battery pack is mentioned in
EFIS D100 Installation Guide (P/N 100487-000, latest edition).
12.4.7
EFIS D100, EMS D120 firmware upgrade
Dynon Avionics provides free firmware updates for all its products, and continues to add
new features periodically.
Each Dynon EMS or EFIS must be individually upgraded by connecting a PC to that
instrument’s serial port (see Fig. 12-46). The HS34 also must be individually upgraded via
its Serial 1 port. Firmware upgrades to EDC-D10A is performed automatically during
firmware upgrades of the attached EFIS product.
Fig. 12-46: Points for computer connection
(a) Check Dynon Avionics web pages for latest Dynon firmware.
(b) Download the appropriate firmware version from downloads.dynonavionics.com
(c) Install software according EFIS-D100 Installation Guide.
(d) Check correct function of instruments and avionics.
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12.4.8
CHAPTER 12 – INSTRUMENTS AND AVIONICS
Flight test for the verification of the stall warning system
Fly the airplane at a safe altitude in a heavy / forward CG configuration, since this
configuration has the narrowest stall margin. The airplane should have flaps retracted.
Note the airspeed at which the stall warning is activated vs the known stall speed of the
aircraft. The stall margin should be approximately 5 kts. If it is not, proceed as follows.
•
If the stall warning is too late:
If stall warning comes on too late, the position of the lift detector should be moved
forward if possible. Moving the detector forward will allow the detector to be activated at
a faster speed. A 6.3 mm (1/4 in) movement of the lift detector will change the stall
warning activation point approximately 5 knots.
•
If the stall warning is too early:
If stall warning comes on too early, the position of the lift detector should be moved
backward, if possible. Moving the detector backward will allow the detector to be
activated at a slower speed. A 6.3 mm (1/4 in) movement of the lift detector will change
the stall warning activation point approximately 5 knots.
When the adjustments are complete, fly the aircraft in heavy / aft, light / forward and light aft
to ensure that the stall warning margin is at least that which was obtained in the heavy /
forward configuration. Finally, ensure that no false warnings occur during a normal,
stabilized approach.
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CHAPTER 13 – VENTING / HEATING
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PiperSport
Contents
13.1 General ................................................................................................................ 13-3
13.2 Description and operation .................................................................................... 13-3
13.2.1
Venting system .................................................................................... 13-3
13.2.2
Heating system .................................................................................... 13-3
13.2.3
13.2.2.1
Standard heating system ................................................. 13-3
13.2.2.2
Efficient heating system ................................................... 13-4
Carbon monoxide detector .................................................................. 13-5
13.3 Removal / Installation .......................................................................................... 13-6
13.3.1
Heating control knob removal .............................................................. 13-6
13.3.2
Heating control knob installation ......................................................... 13-7
13.3.3
Air vents ............................................................................................... 13-7
13.3.3.1
Early SportCruiser / PiperSport airplane
air vents removal.............................................................. 13-7
13.3.3.2
Early SportCruiser / PiperSport airplane
air vents installation ......................................................... 13-7
13.3.3.3
SportCruiser airplane air vents removal
(from S/N C0416) ............................................................. 13-7
13.3.3.4
SportCruiser airplane air vents installation
(from S/N C0416) ............................................................. 13-8
13.3.4
Heat exchanger removal ..................................................................... 13-8
13.3.5
Heat exchanger installation ................................................................. 13-9
13.3.6
Defogging blowers removal ............................................................... 13-10
13.3.6
Defogging blowers installation........................................................... 13-10
13.4 Check / Adjustment............................................................................................ 13-12
13.4.1
Adjusting the heating control ............................................................. 13-12
13.5 Exchanges / Service information ....................................................................... 13-12
13.5.1
Carbon monoxide detector replacement ........................................... 13-12
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CHAPTER 13 – VENTING / HEATING
13.1
General
This chapter contains information on crew compartment heating and ventilation system.
13.2
Description and operation
13.2.1
Venting system
Cockpit ventilation is ensured by two regulated air vents located on the cockpit sides under
the instrument panel (see Fig.13-5) or on the instrument panel (see Fig.13-6). NACA type air
inlets are located on the fuselage sides in front of the canopy frame. Quantity of inlet air is
controlled by flaps which are movable in all directions which allow adjusting the air volume
and air flow direction together. It is also possible to ventilate the cabin through sliding side
windows located on the canopy (if installed).
For cleaning the canopy and sliding windows use warm water and soft cloth.
!!! NEVER use solution based on spirit or acid !!! Using those liquids may lead to failure and
cracking of the glass and sliding windows.
Be careful when opening the cabin windows. If the movement is too hard, spread the sliding
surfaces with a small amount of soap or paraffin.
13.2.2
Heating system
13.2.2.1 Standard heating system
Cockpit heating is ensured by hot air from the heat exchanger. The heat exchanger (1, Fig. 131) is located on the muffler (2). Ambient inlet air taken by the muffler (2) is heated in the heat
exchanger (1) and supplied through control flap (3) into the cockpit by air hoses (4). Quantity
of hot air is regulated by CABIN HEATING knob (5) on the instrument panel.
1 Heat exchanger
2 Muffler
3 Control flap
4 Air hose
5 CABIN HEATING knob
Fig. 13-1: Standard heating system
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CHAPTER 13 – VENTING / HEATING
13.2.2.2 Efficient heating system
Cockpit heating is ensured by hot air from the heat exchanger (1, Fig. 13-2). This heat
exchanger has a larger area compared with standard heat exchanger. The heat exchanger
is located on the muffler (2). Ambient air is supplied to the heat exchanger via air hose (4)
from the NACA inlet located on the right side of the lower engine cowling. Air is heated in
the heat exchanger (1) and supplied through control box (3) into the cockpit by air hose (5).
Quantity of hot air is regulated by CABIN HEATING knob (5) located on the central panel. If
the control flap in the control box is closed, the warm air flows through the hole in the box
body under the airplane.
Furthermore is installed defogging of the windshield by means of two electric blowers that
supply the air from the cockpit compartment via two air channels (6) on the windshield. The
blowers are not connected to the supply air from the heat exchanger and switch on by
means of the BLOWERS circuit breaker located on the right part of the instrument panel
(see Fig. 13-3).
1
2
3
4
Heat exchanger
Muffler
Control box
Cold air hose
5
6
7
8
Hot air hose
Air channel
CABIN HEATING knob
Blower
Fig. 13-2: Efficient heating system
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CHAPTER 13 – VENTING / HEATING
13.2.3
Carbon monoxide detector
The airplane is equipped with Quantum Eye carbon monoxide (CO) detector, if the efficient
heating system is installed.
The Quantum Eye is a multi-level carbon monoxide detector. It provides a visual indication
of carbon monoxide contamination. Each detector is packaged in a protective bag then
when opened activates it. Once activated the minimum product lifetime is 18 months. The
detector in installed on the instrument panel.
Condition color:
Normal
- Yellow
Caution
- Green
Danger
- Dark blue.
Sensor regeneration:
from caution - 2 hours
from danger
- 6 hours
CAUTION:
WATCH THE DATE ON THE DETECTOR AND WHEN NECESSARY
REPLACE IT. MARK THE DATE WHEN INSTALL THE NEW ONE.
NOTE:
For details information refer to the detector manufacturer website
www.qginc.com.
Fig. 13-3: Quantum Eye CO detector / blowers switch typically location
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CHAPTER 13 – VENTING / HEATING
13.3
Removal / Installation
13.3.1
Heating control knob removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No. 14, 9/16”
-
pliers, cutting pliers
(a) Disconnect the control cable on the control flap lever (3, Fig. 13-1, 13-2).
(b) Remove the nuts (1, Fig 13-4) thus releasing the flexible housing (3) with the heating
control knob (2).
(c) Remove the heating control knob with cable from the flexible housing (3).
1 Nut
2 Heating control knob
3 Flexible housing
Fig. 13-4: Heating control knob
13.3.2
Heating control knob installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
wrench size No. 14, 9/16”
-
pliers, cutting pliers
(a) Insert the heating control knob (2, Fig. 13-4) into the flexible housing and fasten it from
both sides of the instrument panel by means of nuts (1).
(b) Connect the control cable with control flap lever (3, Fig. 13-1, 13-2).
(c) Adjust heating control (see 13.4.1).
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CHAPTER 13 – VENTING / HEATING
13.3.3
SportCruiser
PiperSport
Air vents
13.3.3.1 Early SportCruiser / PiperSport airplane air vents removal
(a) Open the control flap (1, Fig. 13-5) 90 degree and pull the vent (2) out from the
housing (3).
1 Control flap
2 Vent
3 Housing
Fig. 13-5: Air vents removal / installation
13.3.3.2 Early SportCruiser / PiperSport airplane air vents installation
(a) Plug the vent (2, Fig. 13-5) into the housing (3) under the instrument panel.
(b) Check the control flap (1) movement.
13.3.3.3 SportCruiser airplane air vents removal (from S/N C0416)
(a) Unscrew the vent (1, Fig. 13-6) and remove it.
(b) Push back the tube (2), remove the cable tie (4) and pull the hose (3) out from the tube
(2).
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CHAPTER 13 – VENTING / HEATING
1 Vent
2 Tube
3 Hose
4 Cable tie
For information:
5 Instrument panel
Fig. 13-6: Air vents removal / installation
13.3.3.4 SportCruiser airplane air vents installation (from S/N C0416)
(a) Put the hose (3, Fig. 13-6) to the tube (2) and secure with the cable tie (4).
(b) Insert the tube (2) to the hole in the instrument panel (5), screw and tighten the vent (1).
(c) Check the vent (1) movement.
13.3.4
Heat exchanger removal
NOTE:
Removal of the standard heat exchanger is shown in Section 10.3.13.
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Screwdriver, pliers, cutting pliers
(a) Remove engine cowlings; during removal of the lower engine cowling disconnect the
hose (5, Fig. 13-7) from the NACA inlet.
(b) Remove the hose clamps (8; 9, 10) and disconnect hoses (5; 6; 7).
(c) Cut off lockwires (4) securing wires (3) and remove wires from the both piano hinges.
(d) Carefully remove both halves (1; 2) of the heat exchanger from the muffler.
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13.3.5
SportCruiser
PiperSport
Heat exchanger installation
NOTE:
Installation of the standard heat exchanger is shown in Section 10.3.14.
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Screwdriver, pliers, cutting pliers
(a) Carefully install both halves (1; 2, Fig. 13-7) of the heat exchanger on the muffler (13).
(b) Insert the wire (3) into each piano hinge; secure the wires with the lockwires (4).
(c) Connect the air hoses (5; 6; 7) to the heat exchanger; secure them by hose clamps (8;
9, 10).
(d) Install engine cowlings; during installation of the lower engine cowling connect the hose
(5) to the NACA inlet.
1
2
3
4
5
6
7
Heat exchanger front part
Heat exchanger aft part
Piano hinge wire
Lockwire
Inlet air hose
Air hose from airbox
Air hose
8 Hose clamp
9 Hose clamp
10 Hose clamp
11 Hose clamp
12 Control box
For information:
13 Muffler
Fig. 13-7: Heat exchanger removal / installation
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PiperSport
13.3.6
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CHAPTER 13 – VENTING / HEATING
Defogging blowers removal
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Screwdriver, pliers, cutting pliers
(a) Set the MASTER BAT, BLOWERS switches to OFF.
(b) As required, remove the instrument panel cover (9) and hoses (5; 6).
(c) Disconnect the blower wires from the wiring harness.
(d) Unscrew and remove the screws (4, Fig. 13-8), blower guard (2), spacers (3); and
remove the blower (1).
13.3.7
Defogging blowers installation
Type of maintenance: line
Authorization to perform:
-
Sport pilot, Repairman (LS-M) or Mechanic (A&P)
Tools needed:
-
Screwdriver, pliers, cutting pliers
(a) Align the guard (2, Fig. 13-8) on the blower (1), insert the screws (4) into the holes and
install the spacers (3).
(b) Parts align to the appropriate place and tighten the screws (4).
(c) Connect the blower wires to the wiring harness (see Wiring Manual).
(e) As required, install hoses (5; 6) and the instrument panel cover (9).
(f) Set the MASTER BAT, BLOWERS switches to ON and carry out operational test.
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1
2
3
4
5
Blower
Blower guard
Spacer (4 + 4 pcs.)
Screw (4 + 4 pcs.)
Hose
SportCruiser
PiperSport
6 Hose
7 Blower diffuser, left
8 Blower diffuser, right
For information:
9 Instrument panel cover
Fig. 13-8: Defogging blowers removal / installation
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PiperSport
13.4
Check / Adjustment
13.4.1
Adjusting the heating control
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CHAPTER 13 – VENTING / HEATING
(a) Adjust the control by screwing or unscrewing the control cable terminal from the control
flap.
(b) After adjustment of the control, mark the mutual position of the control cable terminal
and the flap controller with red color.
13.5
Exchanges / Service information
13.5.1
Carbon monoxide detector replacement
The Quantum Eye has an 18-month product life once it has been activated. Excessive dosages, multiple exposures, or use after the expiration date may cause the sensor to turn
permanently dark. If the sensor turns any color other than those shown, it has been
contaminated and must be replaced.
Keep the sensor away from water, grease, solvents, dirt, hot surfaces, cleaning solutions,
and other contaminants, which may destroy or shorten the life of the sensor. Carbon
monoxide (CO) is an insidious and cumulative poison. It is a colorless, odorless and
tasteless gas produced by the incomplete combustion of fuel.
Instructions:
(a) Activate detector by removing it from the plastic bag.
(b) Attach the detector on the instrument panel.
(c) If carbon monoxide is present the sensor changes color (see Chapter 13.2.3).
(d) When the air freshens, the sensor will regenerate to its original color and will be ready to
use again (unless it has been overexposed).
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CHAPTER 14 – AIRPLANE HANDLING
SportCruiser
PiperSport
Contents
14.1 General ................................................................................................................ 14-3
14.2 Jacking and supporting the airplane.................................................................... 14-3
14.3 Airplane towing .................................................................................................... 14-4
14.4 Airplane parking................................................................................................... 14-4
14.5 Airplane anchoring............................................................................................... 14-4
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CHAPTER 14 – AIRPLANE HANDLING
INTENTIONALLY LEFT BLANK
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CHAPTER 14 – AIRPLANE HANDLING
14.1
SportCruiser
PiperSport
General
This chapter contains information on airplane handling - jacking, parking and anchoring.
14.2
Jacking and supporting the airplane
Due to the relatively low empty weight, the airplane jacking can be carried out by two
persons.
There are two supporting points (see Fig.14-1). Front point (1) is positioned on main spar of
the wing center section. Aft point (2) is positioned on the tail skid.
For the front supports make two bedplates (e.g. from hardwood) according Fig. 14-1.
1 Front jack/support point
2 Aft jack/support point
Fig. 14-1: The airplane jack/support points
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PiperSport
14.3
CHAPTER 14 – AIRPLANE HANDLING
Airplane towing
The airplane can be moved by tow bar inserted into the bracket mounted on nose wheel
fork, by main gear legs, or pushing on the wing root.
14.4
WARNING:
SWITCH OFF THE IGNITION BEFORE HANDLING THE AIRPLANE ON
THE GROUND!
CAUTION:
AVOID EXERTING EXCESSIVE PRESSURE ON THE AIRFRAME
STRUCTURE, ESPECIALLY ON THE WING ENDS, FLAPS, AILERONS,
HTU, VTU, ETC.
CAUTION:
DO NOT USE THE PROPELLER AS TOW BAR TO MOVE AIRPLANE.
Airplane parking
The airplane should be preferably placed in the hangar, possibly in another covered space
with stable temperature, good ventilation, low humidity and dust free environment. In case of
parking outside the hangar it is necessary to anchor the airplane and to cover the canopy or
the whole airplane with suitable tarpaulins for long-term parking.
CAUTION:
14.5
USE THE PARKING BRAKE ONLY FOR SHORT-TERM PARKING
BETWEEN FLIGHTS DURING THE DAY. WHEN THE FLIGHT DAY IS
OVER OR UNDER LOW AIR TEMPERATURES, DO NOT USE THE
PARKING BRAKE AND APPLY THE WHEEL CHOCKS INSTEAD.
Airplane anchoring
When parking, the airplane outside the hangar after flight day, the airplane should be
anchored to the ground. It is necessary to anchor the airplane in order to protect it from a
possible damaging caused by wind and gusts. For this reason the airplane is equipped with
anchoring eyes on the lower side of wings and on rear part of fuselage.
Procedure:
•
check the fuel selector valve is OFF, switch OFF all switches, remove key from the
ignition switch
•
block the control stick, e.g. by using safety harnesses
•
release the parking brake if it was braked
•
close the vents
•
close and lock the canopy
•
park the aircraft into wind
•
insert the wheel chocks
•
anchor the airplane to the ground by means of cables pulled through the anchoring eyes
on the lower side of the wings and on the rear part of fuselage; as necessary anchor the
airplane at the nose landing gear leg (see Fig. 14-2).
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PiperSport
Fig. 14-2: Airplane anchoring
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PiperSport
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CHAPTER 14 – AIRPLANE HANDLING
INTENTIONALLY LEFT BLANK
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CHAPTER 15 – AIRPLANE REPAIRS
SportCruiser
PiperSport
CHAPTER 15 – AIRPLANE REPAIRS
15.1 General ................................................................................................................ 15-3
15.2 Removing rivets ................................................................................................... 15-3
15.3 Riveting ................................................................................................................ 15-4
15.3.1
General ................................................................................................ 15-4
15.3.2
Riveting procedure .............................................................................. 15-4
15.4 Skin repairs .......................................................................................................... 15-5
15.4.1
Removing damaged skins ................................................................... 15-5
15.4.2
Division of damaging into groups ........................................................ 15-5
15.4.3
Principles for repair method determination ......................................... 15-5
15.4.4
Angle repair ......................................................................................... 15-6
15.4.5
Skin repair ........................................................................................... 15-7
15.4.5.1
Stopping cracks and blinding small holes........................ 15-7
15.4.5.2
Repairing the skins with patches ..................................... 15-7
15.5 Repair of fiberglass parts................................................................................... 15-10
15.5.1
Damage classification ....................................................................... 15-10
15.5.2
General .............................................................................................. 15-10
15.5.3
Parts of external appearance ............................................................ 15-10
15.5.4
15.5.3.1
Small damage ................................................................ 15-10
15.5.3.2
Medium damage ............................................................ 15-11
15.5.3.3
Major damage ................................................................ 15-13
Structural parts .................................................................................. 15-13
15.6 Paint repairs....................................................................................................... 15-13
15.6.1
Safety rules........................................................................................ 15-13
15.6.2
Recommendation for additional surface treatment
of the airplane surface ....................................................................... 15-13
15.6.2.1
Washing and degreasing ............................................... 15-13
15.6.2.2
Bonding rivet heads, big irregularities
and material transitions.................................................. 15-14
15.6.3
15.6.2.3
Application of primer (paint) ........................................... 15-15
15.6.2.4
Bonding .......................................................................... 15-15
15.6.2.5
Application of top coat.................................................... 15-16
Small damage.................................................................................... 15-17
15.6.3.1
General .......................................................................... 15-17
15.6.3.2
Sanding .......................................................................... 15-17
15.6.3.3
Degreasing..................................................................... 15-17
15.6.3.4
Application of primer ...................................................... 15-17
15.6.3.5
Application of top coat.................................................... 15-18
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CHAPTER 15 – AIRPLANE REPAIRS
15.7 Torque moments................................................................................................ 15-19
15.8 Securing the bolt joints ...................................................................................... 15-19
15.8.1
General .............................................................................................. 15-19
15.8.2
Bolt joint securing by locking wire ..................................................... 15-19
15.8.3
Bolt joint securing by cotter pin ......................................................... 15-21
15.9 Bonding repairs.................................................................................................. 15-21
15.9.1 General ................................................................................................... 15-21
15.9.2 Removal and installation ........................................................................ 15-21
15.10
Installing clamps by Nicopress pliers ............................................................. 15-22
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CHAPTER 15 – AIRPLANE REPAIRS
15.1
SportCruiser
PiperSport
General
This chapter contains information about standard procedures for performing common
repairs of the airplane. These repairs can be made by an authorized organization. Other
procedures for repairing individual airplane systems you can find in the appropriate
chapter describing the system. Unless specified otherwise in this Chapter all airplane
repairs shall be done in accordance to the most current edition of FAA AC 43.13-1B and
AC 43.13-2A, Acceptable Methods, Techniques, and Practices - Aircraft Inspection and
Repair.
CAUTION:
BEFORE CARRYING OUT ANY STRUCTURAL REPAIRS TO
CONTACT THE RELEVANT AIRWORTHINESS AUTHORITY FOR
APPROVAL.
This chapter describes the following procedures:
15.2
•
Removing rivets
•
Riveting
•
Repair of skins
•
Repair of fiberglass parts
•
Recommendation for repairing surface protection of the airplane
•
Torque moments
•
Securing bolt joints and screwed fittings
•
Repairs of bonding
•
Installing clamps by Nicopress pliers
Removing rivets
Remove rivets from the side of the rivet, which is more accessible. Drill out the rivet head
and drive out the shank.
NOTE:
Center-dot heads of solid rivets, which shall be drilled off.
Use a drill bit by 0.6 mm (0.025 in) diameter smaller than the rivet shank and drill up to the
depth of 2/3 of the total depth riveted parts. Remove the drilled heads with a sharp cuter.
Drive out the shank with the soft material mandrel diameter by 0.1 mm (0.004 in) smaller
than rivet shank diameter. The rivets, which cannot be driven out should be drilled out full
depth. When removing rivets be careful that chips and rivets do not fall down to areas
were sensitive mechanisms are located, e.g. guides, control bearings etc.
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CHAPTER 15 – AIRPLANE REPAIRS
Fig. 15-1: Drilling of rivets (solid rivet displayed)
15.3
Riveting
15.3.1
General
Riveted parts are used in design of SportCruiser / PiperSport airplane for whole fuselage,
wings, flaps, ailerons and tail unit.
In the following table there is a survey of rivets that are used on SportCruiser / PiperSport
airplane structure.
Type of rivets
AVEX
Designation
Use
Aluminium rivet on steel stem
MS20426AD
MS20470AD
Aluminium rivet with countersunk Fuselage, wing, stabilizer, elevator
head
, rudder, flaps, ailerons
Aluminium rivets with universal
head
Tab. 15-1: Survey of rivets used in airplane structure
In case that different replacement rivets are used than shown in the Tab. 15-1 then rivet
dimensions must be identical with originally used rivets and material of rivets must fulfill
the same material characteristics.
15.3.2
Riveting procedure
(a) Fit the parts being connected and drill them together. Hole diameter must be by
0.1 mm (0.004 in) bigger than rivet shank diameter.
NOTE:
When drilling, fix by clamps or clecos mutual position of assembled parts.
Holes of higher diameters pre-drill with a drill bit of smaller diameter and
then redrill them to the final size.
(b) Disassemble the parts and deburr the holes.
NOTE:
For sunken rivets perform conical countersinking of the rivet head by 5°
smaller apex angle (e.g. the head with angle of 100° will have
countersinking of 95°±1°). After countersinking, th e cylindrical part of hole
with min. length of 0.3 mm (0.012 in) must remain in material.
Countersinking must be performed in such a way that the rivets head
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overruns the area before riveting max. by 0.2 mm (0.008 in), the rivet
head must not be under the surface level (sunk).
(c) Before applying the bonding sealant carefully clean the connected parts of impurities
and degrease contact surfaces by appropriate agent, e.g. industrial spirit.
NOTE:
For cleaning and degreasing use a clean paper towel or cloth. After
wiping, the towel or cloth must not show any contamination. For perfect
degreasing the whole surface, clean always smaller part of surface, after
its perfect cleaning continue on. Cleaning liquid always apply on the cloth
only and wipe it off from the surface before its evaporating.
(d) Apply bonding sealant on one of the surfaces, which should be sealed together. Apply
the adhesive directly from the packing by means of the extrusion gun, plastic spatula
or paintbrush in such a way that the layer of sealant is equally thick and integral,
without bubbles or uncovered areas. The optimum thickness of the applied coat is
0.25 mm (0.01 in).
NOTE:
The surfaces that are to be connected must be dry and clean before
application of bonding sealant.
(e) After applying bonding sealant connect both parts together, fix them by clecos and
rivet them.
NOTE:
After proper riveting the continual bur of adhesive is created on the edge
of connected surfaces. If this bur is big, it is possible to wipe it off with the
plastic spatula and finally with cloth dipped in degreasing agent.
(f) After riveting, seal rivet heads, there, where are used pop rivets - see 15.6.2.2
15.4
Skin repairs
15.4.1
Removing damaged skins
In case that it is necessary to remove bigger part of the skin, ensure reliable support of the
structure. Appropriately support the damaged part of the fuselage monocoque or the wing
by supports located in the area of fuselage frames or wing ribs. The shape of supports
must correspond with the shape of supported place and must be supplemented by
cushion (or with other suitable material), so that airplane skin surface cannot be damaged.
Remove rivets according to Section 15.2.
15.4.2
Division of damaging into groups
To determine way of repair, find out by inspection the scope of structural damage, also in
case of possible unriveting the skin.
Damage can be divided into the following groups:
(a) Little damage, which do not have to be repaired, such as local small impacts,
scratches in the skin not exceeding thickness of the zinc chromated layer, appearance
defects of paint coat etc.
(b) Damage, which can be eliminated by airplane operator. Methods of elimination are
describer further in the text.
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CHAPTER 15 – AIRPLANE REPAIRS
(c) Damage with disturbance of basic structural elements of the aircraft. (Deformation of
wing and stabilizer spar, deformation of wing ribs, fuselage bulkheads etc.). These
repairs can be made only by Czech Sport Aircraft a.s. as producer or by authorized
repair shop - for more detailed information contact Czech Sport Aircraft a.s.
15.4.3
Principles for repair method determination
When repairing the damaged skin or airplane structure keep the following principles:
(a) Drill of the loose or damaged rivets and replace them with new rivets
(see 15.2).
(b) Strength in any section of the repaired place must be as a minimum equal to the
strength of the original part.
(c) Use the same material for repairs as the material of a defective area (for survey of
used materials see Section 17.3).
(d) Carry out repair of skin damaging by means of patches having the same thickness as
the original skin or higher.
(e) Repair the angle defects with inserted angles with the section by 10 to 20% higher
than the section of the damaged angle (see 15.4.4).
(f) Loading from one side of the repaired area must carried through the repair element
directly to the other side.
(g) Length of overlapping in the area of repair must be satisfactorily big so that loading
can be equally distributed to nondefective part of the structure.
(h) Exist holes are, if possible, used for riveted joints. If these rivets are not able to
transfer loading, drill other holes. Rivets around of the repaired area are a criterion for
rivet size selection.
(i) Minimum distances of rivets from the edge of sheet metals or inserted bands are
shown in the Table 15-3:
Rivet diameter
2.4 mm
3.2 mm
4.0 mm
(3/32 in)
(1/8 in)
(5/32 in)
Distance of rivet axis from the edge of the sheet metal (angle)
minimum
5 mm
6 mm
7 mm
recommended
(0.2 in)
(0.24 in)
(0.27 in)
7 mm (0.27 in)
7 mm (0.27 in)
8 mm (0.31 in)
Tab. 15-2: Minimum distance of rivets from the edge
15.4.4
Angle repair
Repair method consists in stiffening the damaged angle by means of the new one. When
repairing observes the following instructions:
(a) Determine the section area of the damaged angle S1.
(b) Choose S2 = 1.1 S1 as section area of the stiffening angle.
(c) Thickness t2 = (1 to 1. 3) t1.
(d) Drill of rivets in the area of repair.
(e) Choose the same rivet diameter as in the damaged place.
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(f) Use at least two rivets on each side from the crack.
(g) At riveting follow Section 15.3.
Fig. 15-2: Scheme of angle repair
15.4.5
Skin repair
15.4.5.1
Stopping cracks and blinding small holes
Enlarging of small cracks can be stopped by drilling a hole with the drill bit of dia 3.2 mm
(1/8 in) at the utmost end of the crack. If enlarging continues, repeat the drilling. Support
the place of drilling with a wooden block at drilling thin skin and use the sharp drill bit so
that it will not drift and will not cause another damage to the skin. Check in the operation
whether the crack was successfully stopped.
At drilling the crack of the skin in the area of the flange, supporting stiffener etc., protect
these parts before drilling by supporting the drilled place by means of the thin steel band.
If the crack still enlarges after repeated drilling, cut out the affected area and repair the
skin by means of the patch - see next paragraph.
15.4.5.2
Repairing the skins with patches
CAUTION:
THE FOLLOWING PROCEDURE IS INTENDED FOR SKIN REPAIRS
2
ONLY WITH MAX. AREA OF THE PATCH UP TO 200 cm (31 sq in)
(AREA OF THE CUT OUT SKIN). BEFORE RIVETING THE PATCH
CHECK THE ADJACENT PART OF THE INNER STRUCTURE IN THE
DAMAGED AREA AND FIND OUT WHETHER ITS REPAIR IS NEEDED.
PLACE PATCHES ON THE FUSELAGE SO, THAT THE LONGER
PATCH SIDE LIES IN THE LONGITUDINAL PLANE OF THE AIRPLANE
(IN FLIGHT DIRECTION), SEE FIG.15-3. PLACE PATCHES ON THE
WING SO, THAT THE LONGER PATCH SIDE LIES IN DIRECTION OF
TRANSVERSAL AXIS OF THE AIRPLANE (PARALLEL WITH THE
WING LEADING EDGE), SEE FIG. 15-3.
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CHAPTER 15 – AIRPLANE REPAIRS
1 Correctly located patch
2
Incorrectly located patch
Fig. 15-3: Location of patches on the airplane skin
Mark the damaged surface area (preferably by spirit felt tip) and cut out the most suitable
geometrical shape (circle, square, rectangle).
Be careful that all cracks as well as adjacent corroded areas are cutted out. Corners of cut
out holes in the skin must have minimum radius of 12.7 mm (0.5 in) and their edges must
be smoothly filed off.
Size of patch overlapping depends on the cut out of skin area:
2
2
(a) Patch up to the area of 51.6 cm (8 in ) - rivet by one row of rivets, the patch edge
must overlap the edge of the cut out hole by minimum 19 mm (0.75 in).
2
2
(b) Patch with the area over 51.6 cm (8 in ) - rivet by two rows of rivets, the patch edge
must overlap the cut out hole by minimum 32 mm (1.25 in).
Both ways of patching are shown on Fig. 15-5.
If the damaged area is located near the spars and frames, choose such patch dimension
so that it covers all these elements of structure and it is possible to rivet it (Fig.15-4).
Types of patches, according to their position on the airframe structure.
(a) Surface patches - These can be used in the areas where surface smoothness is not
important
(b) Sunk patches - Use for patches on the wing, tail unit and control surfaces.
(c) Surface patches across obstacles and stiffeners in the skin - pay special
attention to drilling the patch together with the surrounding structure. Attach the patch
in several points and then drill holes for rivets from inner side (if possible). Use original
holes in frames and stiffeners.
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CHAPTER 15 – AIRPLANE REPAIRS
1 Skin
2 Patch
3
SportCruiser
Stiffening frame
Fig. 15-4: Repair of the punctured skin in the frame area
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SportCruiser
PiperSport
A
B
C
D
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CHAPTER 15 – AIRPLANE REPAIRS
Punctured skin
Cutting out and cleaning the damaged skin
Repair with the unsunk patch
Repair with the sunk patch
1
2
3
Patch
Frame
Skin
Fig. 15-5: Repair of the punctured skin
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CHAPTER 15 – AIRPLANE REPAIRS
15.5
Repair of fiberglass parts
15.5.1
Damage classification
SportCruiser
PiperSport
Any damage of parts from reinforced plastics with epoxy matrix leads to increased
saturation of the matrix with humidity and subsequently to loss of properties. Therefore we
recommend carry out their repair as soon as possible after the damage has occurred.
Two kinds of parts are made from these materials in the airplane:
•
structural, load-bearing parts (canopy frame)
•
design appearance, non load-bearing parts (fairings)
According to the damage size we can divide repairs into:
•
small damage (surface defects, not affecting the stiffeners)
•
medium damage (not more than 2/3 of stiffener thickness damaged)
•
big damage
We recommend carry out repairs by means of epoxy resin and glass or carbon stiffeners.
15.5.2
General
Epoxy resin mixtures are prepared in a given mass ratio by means of weighing (accuracy
of scales 1 gram (0.002 lbs)).
15.5.3
Parts of external appearance
15.5.3.1
Small damage
Repair of damage just by application of mastic and by varnish repair.
Preparatory grinding
For a good adhesion of repair layers it is necessary to carry out surface sanding at the
utmost up to the depth of contact with the stiffener (do not damage). It is necessary to do
surface sanding with overrun of 51 mm (2 in) from the damage location smoothly to the
top layer. It is suitable to do sanding with grain size of 160. Dry sanding equipment with
suction from the sanding area is used. Al2O3 or equivalent (fused corundum) can be used
as sanding material.
Dust removing
It is made by wiping with clean and dry brush or by a vacuum cleaner.
Application of smoothing layer
After preparation of mixture (for material recommendation see the Tab. 15-4) and its
eventual thickening, to enhance the noncurtaining capability (for vertical or lower areas) is
performed its application onto the repair area by means of a plastic spatula. For better
distribution of deposited material on irregular surface it is possible to form it through the
laid PE or PP transparent polyethylene. After proper application the layer is without
bubbles. Deposit thickness is given by necessary thickness of surrounding layers
(leveling) and ranges from 0.2 to 12.7 mm (0.008 to 0.5 in) in one deposit.
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PiperSport
CHAPTER 15 – AIRPLANE REPAIRS
Manufacturer,
name
MGS,
A: L285
B: Hardener
285
Type
epoxy
Mixing
ratio
Delay
A:B
100:40
to be
processed
within 50
min (for
0.2 kg
(0.44lbs)
mixture)
Rate of
setting
Time of
setting
40%
16 FH
(32 FH)
20-35°C
(17-20°C)
68-95°F
(62-68°F)
26 FH
(72 FH)
(2 FH)
20-35°C
(17-20°C)
(80°C)
68-95°F
(62-68°F)
(176°F)
100%
Temperature
Fillers
thickening:
Aerosil,
microballs
Tab. 15-3: Recommended materials for mixture preparation for application of leveling layer
Sanding
Sanding or eventually sealing the surface is made after setting the mixture and possible
tearing of the used polyethylene. It is suitable to start sanding with grain size up to 160
and finish with grain size of at least 400. It is carried out by dry sanding equipment with
suction from the sanding area. Al2O3 or equivalent (fused corundum) can be used as
sanding material. Basic material of the part must not be diminished at sanding.
NOTE:
Especially in case of C/K (carbon/Kevlar) stiffener in the basic part,
sanding through up to the stiffener must not occur (complication - see
note about preparatory sanding at medium damage).
Finishing
See section 15.6 - Paint repairs
15.5.3.2
Medium damage
Repair of damage by replacing the stiffener part, by mastic and varnish repair. At such
repair it is necessary to distinguish type of used stiffener (especially for sanding):
•
C/K (carbon/Kevlar), roving of fabric of black color (C) take turns with yellowish (K)
•
G (glass), rovings from milky white to transparent
Preparatory sanding
For good adhesion of repair layers it is necessary to do sanding up to the depth of
damage. It is necessary to do surface sanding from the damage area with overrun at the
least 25 mm (1 in) for every damaged stiffener layer smoothly up to the top layer and then
about 51 mm (2 in) for finishing and mastic application. It is convenient to do sanding with
sanding material having grain size of 160. It is carried out by dry sanding equipment with
suction from sanding area. Al2O3 or equivalent (fused corundum) can be used as sanding
material.
NOTE:
In case of C/K stiffener K roving tend to rise up from the surface at
sanding - it is difficult to sand them, we recommend using diamond
sanding tool and one-way sanding.
Dust removing
Dust is removed by wiping with a clean and dry brush or by a vacuum cleaner.
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CHAPTER 15 – AIRPLANE REPAIRS
SportCruiser
PiperSport
Stiffener preparation
For this kind of repairs we recommend the stiffener G (glass) with plain weave 150 g/m
2
2
(0.037 lb/ft ), with surface protection for epoxy resins. Number of needed stiffener layers
depends on depth of damage. It is possible to say that each layer of the mentioned fabric
represents at proper saturation by matrix resin thickness of 0.5 mm (0.020 in).
Stiffener layers must be prepared (cut out) gradually from the smallest (the lowest) up to
the bigger (upper), each with overrun of 19 mm (0.75 in).
Putting layers
After preparing lamination mixture (for recommendation of material see the Tab. 15-4), it
is applied to the place of repair by means of rigid brush. The first stiffener is laid into the
deposit and it is again saturated by brush. Another layer of stiffener is laid and saturated.
When putting the last layer it is necessary to pay attention to a proper saturation and
compression of stiffeners so that they cannot „come up" to the surface and subsequent
useless damage at final grinding. For better saturation of the surface by resin and
securing against curtaining it is possible to put PE or PP transparent foil across the
surface. When applied properly, the layer is without bubbles. Repair thickness should
exceed surrounding surface in this phase by about 0.5 to 1 mm (0.02 in to 0.04 in) for
finishing.
Sanding
Carry out sanding and eventually apply mastic on the surface after setting, eventually
tearing of the foil (see small damage). It is suitable to begin sanding by abrasive with grain
size of 160 and finish by grain size of at least 400. Dry sanding equipment is used with
suction from the sanding area. Al2O3 or equivalent can be used as sanding material. It is
important not to diminish basic material of the part at sanding.
NOTE:
Especially in case of c/k stiffener in the basic part there must not be any
sanding through up to the stiffener (complication - see the note about
preparatory sanding).
Finishing
See Section 15.6 - Paint repairs
15.5.3.3
Major damage
At such damage we recommend to change the part or to do this repair in a professional
facility. Use instructions in chapter about medium damage as recommendation for used
materials.
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PiperSport
15.5.4
CHAPTER 15 – AIRPLANE REPAIRS
Structural parts
On these parts we do not recommend to do other as small damages repair. In case of the
other damage we recommend to contact Czech Sport Aircraft a.s. as manufacturer.
CAUTION:
WHEN REPAIRING, IT IS NECESSARY TO PAY ATTENTION TO
TIMELY REPAIR (SEE THE TEXT ABOUT LOW OF PROPERTIES AT
HUMIDITY EFFECT AT THE BEGINNING OF 15.5.1)!
Small damage
Repairs are made according to instructions with appearance parts.
CAUTION:
15.6
Paint repairs
15.6.1
Safety rules
WHEN REPAIRING, IT IS NECESSARY TO CAREFULLY PAY
ATTENTION NOT TO DAMAGE THE STIFFENERS!
When working with paints, thinners and solvents follow the following safety rules:
•
it is necessary to follow safety rules for working with flammable and volatile
substances
15.6.2
•
working area must be properly aerated
•
it is prohibited to smoke and anyway handle with free fire in a working area
•
use protective working means such as goggles, gloves, respirator, etc.
Recommendation for additional surface treatment of the airplane surface
CAUTION:
15.6.2.1
BY APPLYING PERMANENT PROTECTIVE COATS WEIGHT OF
AIRPLANE IS INCREASED AND GRAVITY CENTER POSITION IS
CHANGED. INCREASE IN WEIGHT DEPENDS ON TYPE OF COAT
AND ITS THICKNESS.
Washing and degreasing
It is possible to use both organic solvents and solvents based on water.
(a) Organic solvents acetone, metyetylketone (MEK), benzine, toluene,
BASF Glasurit 360-4
•
Applied by spraying on washed surfaces (e.g. mechanical sprayer, jet ejector) or
by wiping with wet (by pouring, not by dipping because it would contaminate the
whole volume of solvent) textile wad. After applying it, the agent is wiped of by
clean absorbing material before solvent evaporation.
•
Advantages: fast and reliable evaporation even from the corners and borders
without additional warming
•
Disadvantages: it must be used without other dilution (expensive); not ecological
(danger of water contamination); detrimental to health (must be carried out in an
aerated area with personal protective means); waste (including dripping from the
area) must be eliminated in the incinerating plants.
•
Use: for Al-alloys surfaces, epoxy fiberglass
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CHAPTER 15 – AIRPLANE REPAIRS
CAUTION:
THESE AGENTS MUST NOT BE USED FOR DEGREASING PARTS
FROM PLASTICS (PC -LEXAN, PMMA PLEXIGLASS).
(b) Water-based agents - emulgation substances, wetting agents
•
Applied also by spraying onto washed surfaces or by wiping with wet (by pouring
and dipping) textile wad. After applying it, let it act for some time (see
manufacturers recommendation) and then it is rinsed with clear water (by means
of sponge dipped in ample amount of water or water jet).
•
Advantages: (different according to the type of product: it is possible to highly
dilute with water (cheap); ecological - waste (including dripping from the surface
due to ample amount of water it is necessary to contain it) can be generally
eliminated after its additional dilution with water in public sewerage; the least
detrimental to health.
•
Disadvantages: slow and unreliable evaporating from corners and borders,
additional warming (drying) mostly required imperfect elimination of water results
in wrong adhesion of paint coats; imperfect degreasing of fiberglass parts (not
possible to use)
•
15.6.2.2
Use: for Al-alloys surfaces and plastics
Bonding rivet heads, big irregularities and material transitions
CAUTION:
IN CASE THAT AIRPLANE SURFACE REMAINS WITHOUT TOP
COAT, CARRY OUT JUST RIVET HEAD BONDING.
After perfect degreasing, carry out bonding of rivet heads, big irregularities and transitions
of fiberglass parts with Al-sheet.
Epoxy and polyester bonding agents for car bodies are suitable; moreover for transitions
between two types of material with increased elasticity. Recommended bonding agents
are shown in the Tab. 15-5.
Polyester bonding agents are applied with plastic spatula after being mixed with initiator.
Sanding with sanding paper with grain size of 240 is made to smooth surface after drying.
Remove dust after sanding and clean with degreasing agent.
Epoxy bonding agent is applied from the special jet with static mixer by means of
extruding pistol. Excessive material is wiped off with spatula to final appearance before
setting (slight recess is not a defect) - do not sand!
Manufacturer,
name
BASF Glasurit
801-703 (base)
Other
components
BASF Glasurit
polyester
965-53 (initiator)
Transitions
epoxide – fiberglass
+ Al-alloys
BASF Glasurit
801-703 (base)
polyester
Rivet heads
BASF Glasurit
polyester
+ styren
Surface
Al-alloys
Type
BASF Glasurit
965-53 (initiator)
Drying (grindable)
[min] / 18°C ( 65°F )
20
20
20
Tab. 15-4: Recommended bonding agents
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PiperSport
15.6.2.3
CHAPTER 15 – AIRPLANE REPAIRS
Application of primer (paint)
In order to reach a uniform resistance to corrosion and smooth surface, we recommend
carry out application by means of spraying (air standard gun with the upper vessel, air
HVLP gun, airless electric gun). The adjusting of the used gun (given by manufacturer)
differs according to the type - air pressure, jet diameter. Primer should be applied in
several sprayings (total thickness is not reached at a blow) with defined maximum dwell
and total drying time till further treatment or handling. Primer serves especially for
anchoring (adhesion to the substrate) the topcoats and can serve also for eliminating
irregularities of the surface (function of filer, for sanding). For surfaces from Al-alloys we
recommend to use the etch-primers for light metals based on alkyd or materials based on
epoxy or polyurethane (2-component paints); specific recommendations according to the
table 15-6.
Surface
Manufacturer,
name
Type
Further
components
BASF
Glasurit
965-35/2
(hardener)
Al-alloys
epoxy –
fiberglass
PC (Lexan),
PMMA
(Plexiglass)
BASF
Glasurit
801-1880
(base)
epoxy
Glasurit
965-50
(thinner)
Surface
mass
1.6
2
[kg/mm/m ]
8.49
[lb/in/sq.ft]
Recom. thickness
Drying (between
spraying / total)
18°C ( 65°F )
0.025 mm (0.00098”)
(at 0.05 mm (0.00197”)
it can be also used as
filler)
15 min / 12 FH
Tab. 15-5: Recommended primers
15.6.2.4
Bonding
After total drying of basic coat we recommend to carry out total bonding of irregularities
including repairs of bonding. Recommended binders are shown in the table 15-5. After
drying perform sanding with emery paper with grain size of 240 until the surface is
smooth. After sanding clean dust and wipe of with grease remover and perform repairing
paint coat by primer (1/3 of coat thickness).
15.6.2.5
Application of top coat
In order to reach smooth surface we recommend again carry out the paint coat by
spraying (see 15.6.2.3).
Topcoat serves especially for creating the coat resistant to weather and external effects
for aesthetic rendering of the unit. Considering the higher loading by external effects we
recommend to use top materials, exclusively two-component ones, on the acrylicpolyurethane or polyurethane basis, always with guaranteed adhesiveness to the used
base coat (according to manufacturer). It is possible to use to advantage some of the coat
system for car repairing. In our recommendation (see Tab. 15-7)
there are two types of colors: single coat (color shade and protection in one) double coat
(one-component color shade is formed by the substrate and protection is ensured by twocomponent transparent top coat). By single coat paint it is possible to reach the wide
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CHAPTER 15 – AIRPLANE REPAIRS
spectrum of colors, but it is difficult to do metallic paint coats (we do not recommend
them).
Color
type
Single
coat
Manufacturer,
name
BASF Glasurit
R-68 / shade
(base)
base color
coat: BASF
Glasurit
R-55 / shade
(base)
Type
acrylic –
polyurethane
Other
items
Surface
mass
BASF
Glasurit
922-36
(standard
hardener)
1-1.6
2
[kg/mm/m ]
Glasurit
352-91
(standard
thinner)
acrylic –
polyurethane
BASF
Glasurit
352-216
(thinner,
long)
Recom. thickness
Drying (between
spraying / total)
18°C ( 65°F )
0.02-0.04 mm
5.24-8.38
2
[lb/inch/ft ]
15 min / 16 hrs
(0.00078-0.00157”)
(by shade)
1.2-1.4
2
[kg/mm/m ]
0.015-0.02 mm
6.29-7.33
2
[lb/inch/ft ]
10 min / 20 min
(0.00059-0.00078”)
(by shade)
Double
coat
Top coat,
acrylic –
bright:
BASF Glasurit polyurethane
923-155 (base)
BASF
Glasurit
929-93
(standard
hardener)
Glasurit
352-91
(standard
thinner)
0.9
2
[kg/mm/m ]
4.82
2
[lb/inch/ft ]
0.03-0.04 mm
5 min / 5 hrs
(0.00118-0.00157”)
Tab. 15-6: Recommended paints
15.6.3
Small damage
15.6.3.1
General
Small damage is a deterioration of corrosion resistance. At repair the situation is made
more difficult by the fact that the substrate for repair coats is not a compact surface of
basic material but mostly al coats of surface protection (after sanding), of which not al are
suitable for (in ageing stage) for good adhesion of paint coats. Therefore we recommend
to carry out such repairs by a verified system.
Before repairing it is necessary to differentiate the type of the existing topcoat, single coat
and two-coat (with the top coat). For repair it is necessary to follow the used type of color.
It is suitable to choose the delimited area (e.g. connection of sheets, wing edge) for the
scope of the place, which is being repaired transition, is then better blended. In the case
that it is not possible to choose the area in this way, it is necessary to take into
consideration the higher difficulty of the procedure as for the uniformity of shade and
elaboration of coat transition.
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PiperSport
15.6.3.2
CHAPTER 15 – AIRPLANE REPAIRS
Sanding
For good adhesion of the repair coats it is necessary to carry out sanding of the old paint
coat at least up to such depth as the depth of damage. Ground area must be larger from
51 to 102 mm (2 to 4 in) than damaged area. With two-coat type of the topcoat it is
necessary to add at least 51 mm (2 in) for the run-out of the top coat. Sanding can be
started with abrasive having grain size of max. 160 and finish with grain size of 400. It is
made by the sander equipped with the suction from the area of sanding or by manual
sanding under water.
CAUTION:
15.6.3.3
ANODIZED COAT CAN NOT BE DESTROYED BY SANDING ON THE
AL-ALLOY SHEET.
Degreasing
It is carried out in the same way as in the case of the total spray coat - see 15.6.2.1
15.6.3.4
Application of primer
For reaching the satisfactory equal adhesion we recommend to carry out a spray coat of
the place to be repaired by adhesive interlayer (see Tab. 15-8).
Surface
Manufacturer,
name
Al-alloys
Epoxy
fiberglass
BASF
Glasurit 934-0
Surface
weight
Recomm.
thickness
0.8
2
[kg/mm/m ]
0.005-0.01 mm
Type
singlecomponent
Old paint
coats
Drying (total)
18°C ( 65°F )
max 15 min
4.19
2
[lb/inch/ft ]
(0.00019-0.00039”)
Tab. 15-7: Adhesive interlayer
Subsequently the primer is applied according to the Table 15-6. Paint coat thickness is
given by necessary thickness of surrounding coats (leveling).
CAUTION:
IN CASE THAT THE PRIMER WAS NOT REMOVED BY THE
PREVIOUS STEP, IT IS NOT NECESSARY TO APPLY THE PRIMER
AGAIN. THE ORIGINAL GROUND PRIMER WITH ADHESIVE
INTERCOAT IS ENOUGH.
Actual application of primer will be carried out in the same way as for the total spray-coat
(see 15.6.2.3).
15.6.3.5
Application of top coat
CAUTION:
FOR REPAIRING IT IS NECESSARY TO CHOOSE THE IDENTICAL
TYPE (SINGLE COAT, DOUBLE COAT) OF THE REPAIR COLOR AS
ON THE ORIGINAL SURFACE.
Application of the top coat will be carried out by spraying as for the total spray coat (see
15.6.2.3) with the exception of used thinners and hardeners. Due to the need of smooth
transition to the basic surface it is necessary to use so called „spraying into the surface"
using longer time of drying initiations for a good result of work. The recommended
material is shown in the Table 15-9.
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CHAPTER 15 – AIRPLANE REPAIRS
Color
type
single
coat
Manufacturer,
name
BASF Glasurit
R-68 / shade
(base)
Type
Other
components
Surface
mass
1-1.6
2
[kg/mm/m ]
acrylic –
polyurethane
BASF
Glasurit
922-36
(standard
hardener)
Glasurit
352-319
(extra long
thinner)
5.24-8.38
2
[lb/inch/ft ]
Recomm.
thickness
Drying
(between spray
coats / total)
18°C ( 65°F )
0.02-0.04 mm
15 min / 19 hrs
(0.00078-0.00157”)
(according
to shade)
1.2-1.4
2
[kg/mm/m ]
basic color
code: BASF
Glasurit
R- 55 / hade
(base)
acrylic –
polyurethane
BASF
Glasurit
352-216
(long thinner)
6.29-7.33
2
[lb/inch/ft ]
0.015-0.02 mm
10 min / 20 min
(0.00059-0.00078”)
(according
to shade)
double
coat
Glossy top
coat:
acrylic –
BASF Glasurit polyurethane
923-155 (base)
BASF
Glasurit
929-93
(standard
hardener)
Glasurit
352-400
(extra long
thinner)
0.9
2
[kg/mm/m ]
4.82
2
[lb/inch/ft ]
0.03-0.04 mm
5 min / 6 hrs
(0.00118-0.00157”)
Tab. 15-8: Recommended colors
15.7
Torque moments
Unless otherwise prescribed, the torque moments shown in the following table can be
used. When tightening follows several rules:
(a) Unless specifically stated do not grease neither nut nor bolt.
(b) If possible always tighten the nut. If for some space reasons it is necessary to tighten
the bolt head and the scope of tightening moment is defined. Use higher moment for
tightening.
(c) Maximum moments are used only for the materials and surfaces, which have a
sufficient thickness, area and strength resistant to bursting, warping or other damage.
Maximum tightening moments must not be exceeded.
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CHAPTER 15 – AIRPLANE REPAIRS
Bolt size
Torque limits recomended
Nm
Max. allowable torque limits
Nm
AN3
2.3 - 2.8
in lb
20 - 25
4.5
in lb
40
AN4
5.7 - 7.9
50 - 70
11.3
100
AN5
11.3 - 15.8
100 - 140
25.4
225
AN6
18.1 - 21.5
160 - 190
44.1
390
AN7
50.9 - 56.5
450 - 500
94.9
840
AN8
54.2 - 78
480 - 690
124.3
1100
AN9
90.4 - 113
800 - 1000
180.8
1600
Tab. 15-9: Recommended torque values for oil-free, cadmium-plated threads
15.8
Securing the bolt joints
15.8.1
General
Bolt joint securing is used in order to prevent from their loosening due to vibration or force
action on the connected parts, which could result in the damage of the connected parts.
Three ways of bolt joint securing are used on the airplane: locking wire, cotter pin and
locking washer.
15.8.2
Bolt joint securing by locking wire
Procedure of bolt joint securing is shown on the Fig.15-6 and Fig.15-7. The zinc-coated or
stainless steel wire having diameter of 0.8 mm (0.032in) is used for securing.
Fig. 15-6: Ways of bolt joint securing
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1. Adjust the correct position of
holes for locking wire.
6. Pull the upper wire through the
hole in the other bolt. Hold the
wire end by pliers and tighten it
firm.
2. Pull the locking wire through
the hole in one bolt to be secured.
7. Hold the free end of wire by
hand, bend it around the bolt head
and along with the other end twist
it counterclockwise.
3. Hold the upper end of the wire
and wind it around the bolt head
and then by the other end of the
wire. Make sure that the wire is
properly tightened around the
head.
8. Hold the twisted end by pliers
and twist it tight.
4. Twist the wire to the hole in the
next bolt so tight as possible.
9. Bend the end of the wire under
the bolt head.
5. Tighten the wire and at the
same time continue its twisting
unless perfectly tightened. The
twisted wire can have
approximately from 3 to 4 threads
on the length of 10 mm (0,4 in).
10. Cut off the surplus wire.
Fig. 15-7: Procedure for securing the bolt joint with locking wire
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15.8.3
CHAPTER 15 – AIRPLANE REPAIRS
Bolt joint securing by cotter pin
Securing by cotter pin is used for independent bolt joints where securing by locking wire
could not be used. It is used for securing castle nuts. Cotter pin removal is very easy: by
means of a flat screwdriver straighten up the bent ends of the cotter pin and take out the
cotter pin of the hole by means of pliers.
CAUTION:
WHEN SECURING JOINTS ALWAYS USE NEW COTTER PINS.
Shift the new cotter into the hole in the bolt and bent the cotter pin ends according the
Fig.15-8.
Fig. 15-8: Securing by using the cotter pin.
15.9
Bonding repairs
15.9.1
General
In order to keep the set down values of the transition resistances between some stuctural
parts of the SportCruiser / PiperSport airplane structure, the bonding (conductive
interconnection) is installed between all important parts of the fuselage structure.
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15.9.2
SportCruiser
PiperSport
Removal and installation
Before installing the bonding remove the paint coat which protects the joint. Principles for
repeated installation of the bonding:
(a) Carefully clean the whole bonding including the washers, bolts and nuts from all
impurities, if necessary degrease the contacting surfaces on the connecting material.
(b) Carefully check whether wires of bonding band are not torn off. Change the damaged
band.
(c) Carefully clean and degrease contacting surfaces on the airplane structure. Clean
corroded surfaces with emery paper to the metallic luster.
CAUTION:
IF A NEW PART WAS INSTALLED INTO THE AIRPLANE, ITS
SURFACE IS PROVIDED BY NON-CONDUCTIVE SURFACE
PROTECTION (FOR EXAMPLE ANODIZING), THIS SURFACE
PROTECTION MUST BE REMOVED FROM THE AREA OF BONDING
INSTALLATION.
(d) The threaded joints, which fulfill a function of bonding, cannot be lubricated.
(e) On the same areas of the airplane structure install the same type of bonding which
you removed.
(f) After repeated bonding installation coat the remaining metallically clean surface of the
contact area, as well as protruding heads of bolts and nuts with protective paint.
15.10
Installing clamps by Nicopress pliers
Procedure of clamp installation by Nicopress pliers is shown on the Fig. 15-10.
First pull the cable through the clamp, make a loop around the thumb and pull the cable
end back through the clamp. The cable end should overlap by about 32 mm (1.25 in) from
the clamp after its puling through. The overlapping will ensure that the cable end will not
be pulled back into the clamp during the clamp squeezing. Before actual squeezing the
clamp it is also necessary to verify which cable terminal will be used, whether thimble or
suspension eye, because some terminals must be put into the cable before actual clamp
squeezing.
Date of issue: 2013-06-30
Revision No.: 15 - 23
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CHAPTER 15 – AIRPLANE REPAIRS
1 Clamp
2 Eye
3 Squeezing sequence
4
5
Inspection gauge
Gauge No.
Fig. 15-9: Installation of clamps by Nicopress pliers
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
SportCruiser
PiperSport
Contents
16.1 General ................................................................................................................ 16-3
16.2 Wiring diagram of the DC power system ............................................................ 16-4
16.3 Wiring diagram of the Rotax 912 engine ............................................................. 16-5
16.4 Wiring diagram of the EFIS D100, HS34............................................................. 16-6
16.5 Wiring diagram of the EMS D120 ........................................................................ 16-7
16.6 Wiring diagram of the intercom PM3000 ............................................................. 16-8
16.7 Wiring diagram of the NAV/COMM SL-30 ........................................................... 16-9
16.8 Wiring diagram of the aileron and elevator trim................................................. 16-10
16.9 Wiring diagram of the flaps ................................................................................ 16-11
16.10 Wiring diagram of the GPSMAP 296/396/495/496/695/696.............................. 16-12
16.11 Wiring diagram of the external lights Kuntzleman ............................................. 16-13
16.12 Wiring diagram of the XPDR GTX-328/330....................................................... 16-14
16.13 Wiring diagram of the autopilot AP-74............................................................... 16-15
Date of issue: 2013-06-30
Revision No.: 16 - 1
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Revision No.: -
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CHAPTER 16 – WIRING DIAGRAMS
16.1
SportCruiser
PiperSport
General
This chapter contains typical wiring diagrams of SportCruiser airplane systems, navigation
and communication means. Further wiring diagrams, relating to additional equipment of
the airplane, are the part of additional equipment description which is mentioned in
Chapter 17 - Appendices.
NOTE:
PiperSport airplanes and SportCruiser airplanes (S/N P1102012, P1102014,
P1102015, P1102016, P1102019, P1102027, P1102031, P1102034, C0416
and up) wiring diagrams are included in the Wiring Manual (see 1.1).
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
16.2 Wiring diagram of the DC power system
Fig. 16-1: Wiring diagram of the DC power system
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
16.3
SportCruiser
PiperSport
Wiring diagram of the Rotax 912 engine
Fig. 16-2: Wiring diagram of the Rotax 912 engine
Date of issue: 2013-06-30
Revision No.: 16 - 5
SportCruiser
PiperSport
16.4
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CHAPTER 16 – WIRING DIAGRAMS
Wiring diagram of the EFIS D100, HS34
Fig. 16-3: Wiring diagram of the EFIS D100, HS34
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
16.5
SportCruiser
PiperSport
Wiring diagrams of the EMS D120
Fig. 16-4: Wiring diagram of the EMS D120
Date of issue: 2013-06-30
Revision No.: 16 - 7
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PiperSport
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CHAPTER 16 – WIRING DIAGRAMS
Wiring diagram of the intercom PM3000
Fig. 16-5: Wiring diagram of the intercom PM3000
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
16.7
SportCruiser
PiperSport
Wiring diagram of the NAV/COMM SL-30
Fig. 16-6: Wiring diagram of the NAV/COMM SL-30
Date of issue: 2013-06-30
Revision No.: 16 - 9
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PiperSport
16.8
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CHAPTER 16 – WIRING DIAGRAMS
Wiring diagram of the aileron and elevator trim
Fig. 16-7: Wiring diagram of the aileron and elevator trim
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
16.9
SportCruiser
PiperSport
Wiring diagram of the flaps
Fig. 16-8: Wiring diagram of the flaps
Date of issue: 2013-06-30
Revision No.: 16 - 11
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PiperSport
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CHAPTER 16 – WIRING DIAGRAMS
16.10 Wiring diagram of the GPSMAP 296/396/495/496/695/696
Fig. 16-9: Wiring diagram of the GPSMAP 296/396/495/496/695/696
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
SportCruiser
PiperSport
16.11 Wiring diagram of the external lights Kuntzleman
Fig. 16-10: Wiring diagram of the external lights Kuntzleman
Date of issue: 2013-06-30
Revision No.: 16 - 13
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PiperSport
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CHAPTER 16 – WIRING DIAGRAMS
16.12 Wiring diagram of the XPDR GTX-328/330
Fig. 16-11: Wiring diagram of the XPDR GTX-328/330
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 16 – WIRING DIAGRAMS
SportCruiser
PiperSport
16.13 Wiring diagram of the autopilot AP-74
Fig. 16-12: Wiring diagram of the autopilot AP-74
Date of issue: 2013-06-30
Revision No.: 16 - 15
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PiperSport
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INTENTIONALLY LEFT BLANK
Revision No.: -
Date of issue: 2013-06-30
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CHAPTER 17 – APPENDICES
SportCruiser
PiperSport
Contents
17.1
General ............................................................................................................. 17-3
17.2
List of appendices............................................................................................. 17-3
17.3
List of used material for airframe production .................................................... 17-4
17.4
Airplane failure card.......................................................................................... 17-5
17.5
Operating liquids............................................................................................... 17-6
17.6
GTN 650 / 750 Post-Installation Checkout Log ................................................ 17-7
Date of issue: 2013-06-30
Revision No.: 17 - 1
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PiperSport
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Date of issue: 2013-06-30
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CHAPTER 17 – APPENDICES
17.1
SportCruiser
PiperSport
General
This chapter contains other information necessary to maintain the SportCruiser /
PiperSport airplane in the form of appendices.
17.2
List of appendices
No.
Title
17.3
List of used materials
17.4
Airplane failure card
17.5
Operating liquids
17.6
GTN 650 / 750 Post-Installation Checkout Log
Date of issue: 2013-06-30
Revision No.: 17 - 3
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PiperSport
17.3
CHAPTER 17 – APPENDICES
List of used materials for airframe production
Prescribed material
2024 T351
Duraluminium
6061 T6
Duraluminium
4130 N
Steel
15 130
Steel
11 353
Steel
17 240.4
Stainless steel
D 671
Stainless steel
Revision No.: -
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PiperSport
CHAPTER 17 – APPENDICES
17.4
Airplane failure card
CZECH SPORT AIRCRAFT a.s.
Na Záhonech 1177/212, 686 04 Kunovice, Czech Republic
Airplane Failures Card
Dear customer,
We would like to ask you for your assistance at obtaining information for continuous increasing
reliability of airplanes produced by our company. Please fill out the card in case of any failure on your
airplane. After filling out, send it to the address mentioned above. By sending us the card, you provide
us with valuable data, which enable us to improve reliability of your airplane as well.
Mandatory data
Airplane type:
Registration mark:
Airplane S/N:
1.
Flight units: FH – number of landing
| | | | |:| | |-| | | |
2.
Failure detection date: day – month – year (format: “dd mm yy”)
3.
Failure has been detected at:
(encircle appropriate number)
4.
Consequences for operation:
(encircle appropriate number)
5.
Failure description:
6.
Identification of the damaged part
| | | | | |
1. Flight
6. Landing run
2. Taxiing
7. Daily inspection
3. Take-off run
8. Periodical inspection
4. Take-off
9. Other
5. Touch down
1. No consequences
5. Emergency landing
2. Airplane put out of operation 6. Occurrence on the ground
3. Airplane returned from
7. Other
take-off
4. Flight with damaged aggregates
Catalogue number
of failed part
Failed part name
Worked out
operation units
Note: State maximum detectable data
7.
Serial No.*
* fill out if required
Notes, additional data (kind of failure, defect, incorrect activity):
Additional data
8.
Claimed (encircle what applicable):
YES - NO
9.
No. of claim:
Order of spare parts (encircle what applicable):
Item
Name of part
YES - NO
Catalogue part No.
Owner:
Home airport:
Operator:
Date:
Date of issue: 2013-06-30
No. of pieces
Elaborated by:
Revision No.: 17 - 5
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17.5
CHAPTER 17 – APPENDICES
Operating liquids
Airplane manufacturer used these operating liquids:
Engine oil
AeroShell Oil Sport Plus 4 (SAE 10W-40, API SL)
Coolant
Coolant type depends on cylinder head design as follows:
Old cylinder head design
(CHT measurement method, engine type marking without suffix -01)
In principle, 2 different types of coolant are permitted:
•
Conventional coolant based on ethylene glycol (with 50% of water)
•
Waterless coolant based on propylene glycol
WARNING:THE COOLANT CONCENTRATE (PROPYLENE GLYCOL) MAY NOT BE
MIXED WITH CONVENTIONAL (GLYCOL/WATER) COOLANT OR WITH
ADDITIVES! NON OBSERVANCE CAN LEAD TO DAMAGES TO THE
COOLING SYSTEM AND ENGINE!
CAUTION:
THE CONVENTIONAL GLYCOL/WATER COOLANT REDUCE TO APPLY
MAXIMUM PERMISSIBLE COOLANT EXIT TEMPERATURE.
New cylinder head design
(CT measurement method, engine type marking with suffix -01, P/N 413185 for 2/3
cylinder head)
Only one type of coolant is permitted:
•
Conventional coolant based on ethylene glycol (with 50% of water)
CAUTION: Waterless coolant are not allowed to be used for Rotax engines with
new cylinder head design.
Refer to the Rotax Operator’s Manual, Section 2.2 Operating limits, and Section 2.3
Operating media - Coolant; the Rotax Installation Manual - Cooling System; Rotax Service
Instruction SI-912-016.
Coolant used by manufacturer:
Specification ASTM D 3306,VW TL 744C-G11,
Mixture ratio coolant/water 50/50 [%]
Max. coolant temperature:
120°C
Hydraulic (brake) fluid
AeroShell Fluid 41 (MIL-H-5606, DOT5)
Revision No.: 6
Date of issue: 2016-01-18
17 - 6
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CHAPTER 17 – APPENDICES
17.6
SportCruiser
PiperSport
GTN 650 / 750 Post-Installation Checkout Log
Date of issue: 2013-06-30
Revision No.: 17 - 7
SportCruiser
PiperSport
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CHAPTER 17 – APPENDICES
Revision No.: -
Date of issue: 2013-06-30
17 - 8
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CHAPTER 17 – APPENDICES
Date of issue: 2013-06-30
SportCruiser
PiperSport
Revision No.: 17 - 9
SportCruiser
PiperSport
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CHAPTER 17 – APPENDICES
Revision No.: -
Date of issue: 2013-06-30
17 - 10
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