AMP Tecnam P2002-JF Ed3 Rev0

Kazakhstan Association of Small
Approved on behalf of the Owner:

Aviation
Position: _____________________ Position: _________________________
Signature: _______________________ Signature: ________________________
Name and Surname: ___________________ Name and Surname: U. Kenesbaev_____
Date: __________________________ Date: ___________________________
AIRCRAFTMAINTENANCE
PROGRAMTECNAM P2002-JF
( ПРОГРАММА ТЕХНИЧЕСКОГО
ОБСЛУЖИВАНИЯ)
Typeofaircraft:TecnamP2002-JF
Registration marks:UP-LA 266s/n:171;UP-LA197 s/n:221;
Type of engine: Rotax 912S2
Type of propeller: Hoffmann HO 17GHM
Operator: «Falcon Avia» LLP;
«Falcon Avia» LLP;

050012, Almaty city, Maulenov street 96/77 apt. 16
Issue 3 / rev 0 / 18-03-2022

TECNAM P2002-JF AIRCRAFT MAINTENANCE PROGRAM
TABLE OF CONTENT
Table of content........................................................................................................................................................................... 0-2

List of effective pages................................................................................................................................................................. 0-3
List of revisions............................................................................................................................................................................ 0-4
Revision description page........................................................................................................................................................ 0-5
List of annual reviews................................................................................................................................................................ 0-6
List of abbreviations................................................................................................................................................................... 0-7
Obligations of operator............................................................................................................................................................. 0-8
Standards and responsibilities.............................................................................................................................................. 0-9
Section 1 - Inspection................................................................................................................................................................ 1-1
Section 2 -Servicing.................................................................................................................................................................... 2-1
Section 3 - Repetitive Airworthiness directives and Service bulletins..................................................................3-1
Section 4 -Component time limits........................................................................................................................................ 4-1
Section 5 -Battery servicing.................................................................................................................................................... 5-1
TABLE OF CONTENT Issue 3 /rev. 0 / 18-03-2022 0-2

LIST OF EFFECTIVE PAGES

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Approved on behalf of the Owner: Kazakhstan Association of Small Aviation

Position: _____________ Position: President
Signature: __________________ Signature: ___________________
Name and Surname: ___________ Name and Surname: U. Kenesbaev
Date: 18.03.2022 Date: _______________________
LIST OF EFFECTIVE PAGES Issue 3 /rev. 0 / 18-03-2022 0-3

LIST OF REVISIONS
Revision
Revision date Incorporated by Incorporation date Signature
No.
LIST OF REVISIONS Issue 3 /rev. 0 / 18-03-2022 0-4

REVISION DESCRIPTION PAGE

Issue No. Issue date Rev. No. Rev. date
3 18-03-2022
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Prepared by: Checked by:
Position: ______________________________________________ Position: ______________________________________________
Signature: ____________________________________________ Signature: ____________________________________________
Name and Surname: ________________________________ Name and Surname: ________________________________
Date: _________________ Date:_________________
REVISION DESCRIPTION PAGE Issue 3 /rev. 0 / 18-03-2022 0-5

LIST OF ANNUAL REVIEWS

The annual review cycle (one calendar year) will be start from the date of the first approval of the AMP.
Original approval date of this AMP: First due:
No. Date of review Name Signature Next due date
LIST OF ANNUAL REVIEWS Issue 3 /rev. 0 / 18-03-2022 0-6

LIST OF ABBREVIATIONS
Abbreviation Description
AD Airworthiness Directive
AFM Aircraft Flight Manual
(A)MP (Aircraft) Maintenance Program
CRS Certificate of Release to Service
EASA European Aviation Safety Agency
SB Service Bulletin
SL Service Letter
STC Supplemental Type Certificate
TC Type Certificate
P2002-JF-AMM Tecnam P2002-JF Aircraft maintenance manual
OMM No. E 0110.74 Operation and maintenance manual for Hoffmann HO-series fixed pitch propeller
MM(L) Rotax 912 S2 Line maintenance manual for Rotax 912 series engines
MM(H) Rotax 912 S2 Heavy maintenance manual for Rotax 912 series engines
LIST OF ABBREVIATIONS Issue 3 /rev. 0 / 18-03-2022 0-7

OBLIGATIONS OF OPERATOR
«Falcon Avia» LLP;
1. The AIRCRAFT MAINTENANCE PROGRAM (AMP) is applied for AIRCRAFT:

Aircraft type – Tecnam P2002-JF (EASA TCDS No. EASA.A.006);
Registration numbers (serial numbers): UP-LA 266 s/n: 171; UP-LA197 s/n: 221;UP-LA196 s/n: 220;
Engine – Rotax 912S2(EASA TCDS No. E.121);
Propeller – Hoffmann HO-17GHM (FAA TCDS No. P26NE).
2. Information about Operator:

Operator: «Falcon Avia» LLP;
3. Identification of the program:

3.1. The name of the program.
MP, Tecnam P2002-JF” Issue3 / rev.0 / 18.03.2022
3.2. The AMP is developed on the basis of following documents:

a) TecnamP2002-JF Maintenance manual; Doc. No. 2002/30; edition No. 2 / rev. No. 5 /02-11-2020;
b) Line maintenance manual for Rotax 912 series engines; Doc.No. MML-912;
edition No. 4 / rev. No. 1 / 07-09-2021;
c) Heavy maintenance manual for Rotax 912 series engines; Doc.No. MMH-912;
edition No. 1 / rev. No. 6 / 01-07-2018;
d)Operation and maintenance manual for Hoffmann HO-series fixed pitch propeller; Doc. No. E0110.74;
edition No. 8 / Feb-2002;
4. The Operator statement:

The operator confirms and takes the responsibility for that the aircraft Tecnam P2002-JF will be
provided with service according to the approved “MP, Tecnam P2002-JF”.
The operator confirms that the airplane will be continuously managed and that it will provide
continuous monitoring of AD, SB, changes in TC and STC and upon necessity will issue changes to this
aircraft maintenance program.
The program is exposed to the analysis and obligatory periodic revision at least once in the year with
modification and additions.
The Operator recognizes, that competent authority has the right to cancel, suspend or limit AMP action,
if are received acknowledgements of that AMP does not provide observance of Airworthiness standards
of the Aircraft.
Signed on behalf of the aircraft owner (operator):
Name and Surname: _________________ Signature:__________________
Date:18.03.2022
OBLIGATIONS OF OPERATOR Issue 3 /rev. 0 / 18-03-2021 0-8

STANDARDS AND RESPONSIBILITIES

1. Owner responsibilities:
1.1. The owner is responsible for the aircraft continuing airworthiness.
2. Certificate of release to service (CRS):
2.1. On completion of any the AMP maintenance checks, a detailed, referenced entry must be made in
the relevant log book(s) with anappropriate CRS by the certifying person.
3. Airworthiness life limitations:
3.1. Airworthiness life limitations shall be those published by the state of design TC holder and STC
holders.
3.2. Airworthiness life limitations shall be recorded in document or system acceptable to the Competent
Authority.
4. Airworthiness directives (AD’s):
4.1. ADs shall be those issued by EASA or and NAA responsible for the TC holder and STC holder.
4.2. Forecasting and compliance with ADs shall be recorded in documents or systems acceptable to the
Competent Authority.
5. Overhaul, additional inspection and test periods:
5.1. Overhaul, additional inspections and test periods shall be those recommended by the TC holder or
STC holders.
5.2. EASA, NAA responsible of TC holder and the Competent Authority may vary or mandate overhaul
and test periods and additional inspections.
5.3. The forecasting and compliance with overhaul, additional inspections and test periods shall be
recorded in document or system acceptable to the Competent Authority.
6. Instructions for continued airworthiness:
6.1. Instructions for continued airworthiness consist of in-service data published by the TC or STC
holder in Maintenance manual, SBs, SLs, etc.
6.2. Continued airworthiness instructions shall be recorded in documents or systems acceptable to the
Competent Authority.
7. Changes (modifications or repairs):
7.1. EASA approved changes (modifications), which have been carried out, must be recorded in the
documents or systems acceptable to the Competent Authority.
7.2. Any additional instructions for continued airworthiness due to the change shall be recorded in
documents or systems acceptable to the Competent Authority.
STANDARDS AND RESPONSIBILIETIES Issue 3 /rev. 0 / 18-03-2022 0-9

8. Independent inspections:
8.1. The TC holder or STC holder’s instructions for continued airworthiness should be followed when
determining the need for an independent inspection.
8.2. In the absence of these inspection standards, an independent inspection must be carried out after
any flight safety sensitive maintenance task.
9. Defects:
Any defect that hazards seriously the flight safety shall be rectified before further flight.
Any aircraft defect that would not hazard seriously the flight safety shall be rectified as soon as
practicable, after the date of the aircraft defect was first identified and within any limits specified in the
maintenance data. Any defect not rectified before flight shall be recorded in the aircraft maintenance
record system.
10. Performance of maintenance:
All maintenance shall be performed following the methods, techniques, standards and instructions
specified in Part-M. The aircraft should only be maintained with this approved AMP.
The general maintenance and inspection standards applied to individual maintenance tasks should
meet the recommended standards and practices of the organization responsible for the type design
which are published in the Maintenance Manual and others maintenance instructions.
11. Corrosion control program:

It is important to keep the aircraft clean and to remove any collection of corrosive agents such as oil,
grease, dregs and other foreign matter. To avoid damage to finish, do not use polishing detergents.
Original or equivalent corrosion prevention must be re-applied after any alteration or repair. If any
trace of corrosion is detected it should be removed as soon as possible and part should be immediately
treated to prevent further corrosion.
(a) For steel parts, with the exception of highly stressed components or stainless steel, it is possible to
use abrasives, power brushes, steel brushes if operated manually and steel wool. Removing corrosion
by products from highly stressed steel components (main gear steel spring) requires particular care.
(b) For aluminum parts, treatment consists in mechanically removing as much as possible corrosion
by products, applying corrosion inhibitor and replacing original finish. Steel wool, emery or steel
brushes (unless stainless steel) along with other highly abrasive material should not be used since steel
or emery particles become embedded in the softer material causing corrosion. After cleaning surface
corrosion, parts must be treated with an anti-corrosion product. Tecnam suggests for steel and
aluminum parts as anticorrosion product, ACF-50 or products with similar technical features, which
stops the existing corrosion and remain
effective for 24 months. In low Salt or low Humidity Environments the ACF-50 have to be used every 24
months to prevent the presence of corrosion on aircraft. If the aircraft flies in high Salt environments
refer to the unscheduled maintenance and follow the application intervals.
12. Test flight:
Test flight could be done on decision of Technical director or Flight operations manager, or requirement
of CAA.Usually, check flights are performed after such maintenance as:
a) engine or flight control removal /installation;
b) Long storage more 12 month.
c)etc.
STANDARDS AND RESPONSIBILIETIES Issue 3 /rev. 0 / 18-03-2022 0-10

SECTION 1 – INSPECTION.
This Chapter lists the components that are recommended to be replaced or overhauled within specific
time limits, individual inspections that are to be performed at specified intervals and Special
Scheduled/Unscheduled Inspections.
The tasks contained in this section include requirements for performing special and periodic
inspections. Perform all inspection tasks in the following inspection checklists at the specified intervals.
Intervals are measured in hours of operation and, as applicable, calendar months.
Every porthole, fairing, panel, etc., shall be removed to allow for inspection.
1) Line Maintenance Inspection.

1.1 Daily check.
№ Maintenance Task Description
Coolant level
Verify coolant level in the expansion tank, replenish as required up to top. The max. coolant level must be flush with the bottom
of the filler neck.
Verify coolant level in the overflow bottle, replenish as required. The coolant level must be between max.andmin. mark.
Mech./electronic components
Turn propeller slowly by hand in direction of engine rotation several times and observe engine for odd noises or excessive
3
resistance and normal compression.
Gear box
Turn the propeller by hand to and fro, feeling the free rotation of 30° before the crankshaft starts to rotate.
4
If propeller can be turned between the dogs frictionless (lower than 25 Nm (19 ft.lb)), further inspection is required.
SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-1

Carburetor
5 Verify free movement of throttle cable and starting carburetor over the complete range. Check from the cockpit.
Exhaust system
6 Inspect for damages, leakage and general condition.

Propeller
Clean the propeller. Inspection of wooden composite propellers is easy and gives reliable results. Critical conditions will show up
7
early as surface cracks in the paint. Therefore correct judgement of such cracks is very important.
Erosion on the leading edge of the blades is normal and not critical. Metal
propellers erode too. On a composite propeller the erosion sheet (Type A and B)
becomes visible under the paint.
The erosion tipping (Type A) of the propeller blades ends in

theinner third of the blade. Fine cracks in the paint along the
tipping are no reason for concern.
The erosion tipping (Type B and C) ends in the inner third of the
blade. Fine cracks in the paint along the tipping are no reason for
concern. Cracks in the tipping perpendicular to the blade axis are
not dangerous as long as the tipping does not lift off from the blade
10
body. Slide your fingernail along the leading edge from the hub to
the tip. If the tipping lifts off from a crack, remove propeller for
repair.
Fine cracks in the paint or the tipping across the blade axis,
especially in the outer third of the blade, are indications of bending
vibration. In an advanced stage the tipping may break or come off
piece by piece. Notches in the tipping support this procedure. If such
cracks occur, contact the factory or a service station which is
11
authorised by Hoffmann.
Cracks in the paint or in the blade, starting from the blade tip and
extending parallel or at any angle to the blade axis, are indications for
torsional vibrations. Such cracks occur very seldom. If such cracks
occur, contact the factory or a service station authorised by
Hoffmann.
12

Hair- cracks in the paint of the blade, starting from the blade tip
and / or in the blade root area and extending in any direction are
indications of vibrations or overload of the propeller blade. They
are uncritical as long as they are paint cracks only. If they start
growing quickly and penetrating into the fibre cover contact the
13
factory or a service station authorised by Hoffmann.
Radial crack, is less critical if it is limited to the outer

lamella, and the crack is not longer than the flange
diameter. This is an indication that the propeller was
loos. It may be repairable.
14
Tangential crack is critical and an indication of overload.

The propeller has to be removed from service
immediately.
15
A hair crack at the end of a short lamella (see para. 2.2.1) is

less critical. Paint has to be used to close the crack in order to
avoid the penetration of moisture.
16

1.2 Pre-Flight check.

№ Maintenance Task Description
Cabin inspection
1 Aircraft documents (ARC, Certificate of Airworthiness, Noise certificate, Radio COM certificate, AFM): check current and on board.
2 Safety belts: connected to hard points, check condition
3 Magnetos: OFF, keys extracted
4 Master switch: ON
5 Voltmeter: check (10-12 V); Ammeter check (red).
6 Lights: all ON, check operation
7 Acoustic stall warning: check operation
8 Master switch: OFF
9 Baggage: check first aid kit, canopy hammer, fire extinguisher, luggage stowage and fastened with restraint net.
Aircraft Walk-Around
Left fuel filler cap: check visually for desired fuel level. Drain the left fueltank by drainage valve using a cup to collect fuel
A
Check for wateror other contaminants. Closefillercap.
Remove protection plug (if provided) and check the Pitot tube and the staticports mounted on left wing are unobstructed; do not
B
blow inside vents.
C Left side leading edge and wing skin: visual inspection.
D Left aileron, trim tab and hinges: visual inspection, check free of play, friction;Left tank vent: check for obstructions.
E Left flap and hinges: visual inspection
F Left main landing gear: check inflation, tire condition, alignment, fuselageskin condition.
G Horizontal tail and tab: visual inspection, check free of play, friction.
H Vertical tail, rudder and trim tab: visual inspection, check free of play,friction.
I Right main landing gear; check inflation, tire condition, alignment, fuselageskin condition.
L Right flap and hinges: visual inspection.
M Right aileron, trim tab and hinges: visual inspection, check free of play,friction; Right side tank vent: check for obstructions.
N Right leading edge and wing skin: visual inspection
Right fuel filler cap: check visually for desired fuel level. Drain the rightfuel tank by the drainage valve using a cup to collect fuel.
O Drainage operationmust be carried out with the aircraft parked on a level surface. Checkfor water or other contaminants. Close
filler cap.
Set the fuel selector valve to ON. Drain circuit using a cup to collect fuelby opening the specific drainage valve (part of the
P
gascolator). Check forwater or other contaminants.
Q Nose wheel strut and tire: check inflation, tire and rubber shock absorberdiscs condition.
Propeller and spinner condition: check for nicks, cracks, dents and otherdefects, propeller should rotate freely. Check fixing and
P
lack of play betweenblades and hub.
Open engine cowling:
1. Check no foreign objects are present.
2. Verify coolant level in the overflow bottle: level must be between min.and max. mark. Replenish if required.
3. Only before the first flight of the day:
a. Verify coolant level in the expansion tank, replenish as requiredup to top (level must be at least 2/3 of the expansion tank).
b. Turn the propeller by hand to and fro, feeling the free rotation of15°or 30° before the crankshaft starts to rotate. If the propeller
can be turned between the dogs with practically no friction at allfurther investigation is necessary. Turn propeller by hand in
directionof engine rotation several times and observe engine forodd noises or excessive resistance and normal compression.
c. Carburettors: check the throttle cable condition and installation.
S d. Exhaust: inspect for damages, leakage and general condition
4. Check radiators. There should be no indication of leakage of fluidand they have to be free of obstructions.
5. Check oil level and replenish as required. Prior to oil check, havingmagnetos switched off turn the propeller by hand in
direction of enginerotation several times to pump oil from the engine into the oil tank, orlet the engine idle for 1 minute. This
process is finished when air is returningback to the oil tank and can be noticed by a murmur from theopen oil tank. Prior to long
flights oil should be added so that the oillevel reaches the “max” mark.
6. Inspect fuel circuit for leakages.
7. Check integrity of silent-block suspensions.
8. Check connection and integrity of air intake system, visually inspectthat ram air intake is unobstructed.
9. Check that all parts are secured or safetied.
T Close engine cowling, check for proper alignment of cam-locks.
U Visual inspection of the Landing and Strobe Light.
V Remove tow bar and chocks, stow on board pitot, static ports and stallwarning protective covers.


2) Base Maintenance Inspection.
2.1 First 25 hours of aircraft.
№ Section Reference Maintenance Task Description Mechanic Inspector
ATA 32: Landing gear

P2002-JF-AMM Check for correct torque of the MLG attachment bolts. Replace leather
1
32:10 Page 203 spacer if necessary
ATA 71: Powerplant
P2002-JF-AMM
2 Engine mounts isolators: check for integrity
71:20
Visually inspect engine mount structure for bent, cracked or buckled
P2002-JF-AMM
3 tubes and engine mount isolators attachments. Check engine mount
71:20
bolts and engine electrical bonding
P2002-JF-AMM
4 Check carburettors fuel drainage lines. Check air box drainage lines
5:20
P2002-JF-AMM
5 Visually inspect air induction system for integrity. Clean filter if required
5:20; 71:30
Engine compartment: check for fuel, oil and coolant liquid leakages;
inspect hoses, fittings, clamps and all other components of the systems
for cracks, holes, dents, bulges, and other signs of damage that might
restrict the fluid flow or cause a leakage. All lines must be inspected to
P2002-JF-AMM
6 ensure that they are properly supported and are not rubbing against a
5:20
structure. Fittings should be checked for signs of improper installation,
over-torqueing, excessive tension, or other conditions which may lead to
a failure. Inspect engine parameters sensors for general condition and
security of installation.
ATA 78: Exhaust
P2002-JF-AMM Visually inspect exhaust manifold, muffler and heat exchanger for
7
5:20 condition and security of installation
P2002-JF-AMM
8 Muffler mounting springs: check for integrity
5:20
ATA 79: Oil system
P2002-JF-AMM
9 Check oil circuit: there should be no indication of leakages
5:20
2.2First 25 hours of engine.

ATA 71: Powerplant
Differential pressure check
Check the compression by the differential pressure method.
Test pressure________hPa (psi).
MM(L) Rotax 912 S2

1 12–20–20Checking
the compression
Spark plug
MM(L) Rotax 912 S2 Remove all spark plugs and check for spark plug defects (deposits, ex-
2 12–20–20Remove cessive wear melting....)
the spark plugs Replace if defective. Check if GENUINE ROTAX® spark plugs are used.
Inspecting the magnetic plug
MM(L) Rotax 912 S2
3 12–20–20Inspecting Check the magnetic plug.
the magnetic plug
Inspecting the oil filter

MM(L) Rotax 912 Remove old oil filter from engine. Cut old filter without producing any
S212–20– metal chips and inspect following components for wear and/or
4
20Inspection of the missing material. Perform filter mat inspection:
oil filter components Findings.__________________________________________________
Visual inspection of the engine
General visual inspection of the engine for damage or abnormalities.
MM(L) Rotax 912
Check cooling air duct and cooling fins of the cylinders for obstruction,
5 S212–20–20Visual
cracks, wear and good condition. Take note of changes caused by
inspection
temperature influence.
MM(L) Rotax 912
Inspect temperature sensors and oil pressure sensor for secure fit and
6 S212–20–20Visual
signs of wear.
inspection
MM(L) Rotax 912 S2 Inspect all coolant hoses of the engine for damage, including leakage,
7 12–20–20 hardening from heat, porosity, loose connections and secure
Leakage check attachment. Verify routing is free of kinks and restrictions.
MM(L) Rotax 912 S2 Carry out visual inspection of leakage bore at the base of the water
8 12–20–20
Leakage check pump for signs of leakage.
MM(L) Rotax 912 S2 Inspect the expansion tank for damage and abnormalities. Check
9 12–20–20Expansion coolant level, replenish as necessary. Inspect radiator cap.
tank, radiator cap Inspect protection rubber on expansion tank base for correct fit.
Inspect the overflow bottle for damage and abnormalities.
MM(L) Rotax 912 S2 Verify coolant level, replenish as necessary.
10 12–20–20 Inspect line from expansion tank to overflow bottle for damage,
Overflow bottle leakage and clear passage.
Inspect venting bore in cap of overflow bottle for clear passage.
MM(L) Rotax 912 S2 Inspect all oil lines for damage, leakage, hardening from heat, porosity,
11 12–20–20 security of connections and attachments. Verify routing is free of kinks
Leakage check and restrictions.
Inspect all fuel lines for damage, leakage, hardening from heat,
MM(L) Rotax 912 S2
porosity, security connections and attachments. Verify routing is free
of kinks and restrictions. Check steel fuel lines for any cracks and/or
the fuel lines
scuffing marks.
MM(L) Rotax 912 S2
Inspect the wiring and its connections for secure fit, damage and signs
13 12–20–20Check of
of wear.
wiring
MM(L) Rotax 912 S2
12–20–20Checking Inspect engine suspension and fasteners (GENUINE ROTAX® ) for
14
the engine secure fit, including damage from heat, deformation, cracks.
suspension
P2002-JF-AMM
Check the airbox (GENUINE ROTAX ® ) incl. air flap actuation. Inspect
15 S-4Air-box control
sensors for tight fit, damage from heat, damage and signs of wear.
rigging
MM(L) Rotax 912 S2
16 12–20–20Cleaning Checkingtheairfilter.
the dry air filter
Inspect of the GENUINE ROTAX® exhaust system included in the
MM(L) Rotax 912 standard delivery.
17 S212–20–20Visual NOTE
inspection If there is no standard/genuine exhaust system in use, the
specifications of the manufacturer must be observed.
Oil change
MM(L) Rotax 912 S2
12–20–20
18 Drain oil from oil tank.
Oil change,Flushing
the oil circuit
MM(L) Rotax 912 S2
12–20–20Oil
19 Check the oil tank and clean the oil tank if contaminated.
change,Cleaning
the oil tank

MM(L) Rotax 912 S2
12–20–20Flushing
Refill oil tank with approx. 3 litres of oil. For oil quality, see Operators
20 the oil circuit,
Manual latest edition.
Purging the
oil system
MM(L) Rotax 912 S2
21 12–20–20Oil filter Installnewoilfilter.
change
Auxiliary alternator
MM(L) Rotax 912 S2
On configurations with auxiliary alternator, check the attachment and
the V-belt tension.
the V-belt tension
Checking the carburetors
MM(L) Rotax 912 S2
23 12–20–20Check the Checking the idle speed.
idle speed
MM(L) Rotax 912 S2 Check for free movement of the carburetor actuation (throttle lever
12–20–20Checking and starting carburetor).
24
carburetor actuation Check that the Bowden cable allows the full travel of the throttle lever
from stop to stop.
MM(L) Rotax 912 S2
12–20–20Checking Check carburetor synchronization. Mechanical and pneumatic
25
carburetor synchronization.
synchronization
Engine cleaning
MM(L) Rotax 912 S2
26 12–20–20 Engine cleaning.
Engine cleaning
Checking the air intake system
MM(L) Rotax 912 S2
27 12–20–20Checking Checking the air filter.
airintake system
Liquid level check
MM(L) Rotax 912 S2
28 12–10–00 Verify liquid level, replenish as necessary.
Fluid capacities
Checking the idle speed
MM(L) Rotax 912 S2
29 12–20–00Checking Checking the idle speed.
the idle speed
Engine test run
Observe the safety instructions!
Start the engine and run to operating temperature.
Limits see in Operators manual 912 series.
Ignition check at _____________ rpm engine speed.
Speed drop without ignition circuit:
A (Off) ______________ rpm
MM(L) Rotax 912 S2 B (Off) ______________ rpm
12–20–00
30 A/B (difference) ______________ rpm
Test run of Inspect carb heat system.
engine Hit the preheating and make a note of speed drop.
Speed drop ____________ rpm.
Preheating “OFF”, engine idle running and make a note of idle speed
running __________ rpm.
After engine test run, re-tighten the oil filter by hand (only at cold
engine).
Check for leaks.
2.3 First 25 hours of propeller (and after the first flight).

Propeller inspection
OMM No. E 0110.74 Check torque of hub bolts by, applying the necessary torque only. Lock
1
Page 11 wire bolts again.

2.4 50 hours inspection.
ATA 32: Landing gear (SB 214 – CS – Ed. 1 Rev. 0)
P2002-JF-AMM Check for correct torque of the MLG attachment bolts. Replace leather
1
32:10 Page 203 spacer if necessary.
ATA 71: Powerplant
P2002-JF-AMM
2 Engine mounts isolators: check for integrity.
71:20
Visually inspect engine mount structure for bent, cracked or buckled
P2002-JF-AMM
3 tubes and engine mount isolators attachments. Check engine mount
71:20
bolts and engine electrical bonding.
P2002-JF-AMM
4 Check carburettors fuel drainage lines. Check air box drainage lines.
71:40
P2002-JF-AMM Visually inspect air induction system for integrity. Clean filter if
5
71:30 required.
Engine compartment: check for fuel, oil and coolant liquid leakages;
inspect hoses, fittings, clamps and all other components of the systems
for cracks, holes, dents, bulges, and other signs of damage that might
restrict the fluid flow or cause a leakage. All lines must be inspected to
P2002-JF-AMM
6 ensure that they are properly supported and are not rubbing against a
5:20
structure. Fittings should be checked for signs of improper installation,
over-torqueing, excessive tension, or other conditions which may lead to
a failure. Inspect engine parameters sensors for general condition and
ATA 78: Exhaust
P2002-JF-AMM Visually inspect exhaust manifold, muffler and heat exchanger for
7
5:20; 78:10 condition and security of installation.
P2002-JF-AMM
8 Muffler mounting springs: check for integrity.
5:20; 78:10
ATA 79: Oil system
P2002-JF-AMM
9 Check oil circuit: there should be no indication of leakages
5:20; 79:10
Oil change
MM(L) Rotax 912 S2
12–20–20
10 Drain oil from oil tank.
Oil change,Flushing
the oil circuit
MM(L) Rotax 912 S2
12–20–20Oil
11 Check the oil tank and clean the oil tank if contaminated.
change,Cleaning
the oil tank
MM(L) Rotax 912 S2
12–20–20Flushing
Refill oil tank with approx. 3 litres of oil. For oil quality, see Operators
12 the oil circuit,
Manual latest edition.
Purging the
oil system
MM(L) Rotax 912 S2
13 12–20–20Oil filter Installnewoilfilter.
change
Inspecting the oil filter
MM(L) Rotax 912 Remove old oil filter from engine. Cut old filter without producing any
S212–20– metal chips and inspect following components for wear and/or missing
14
20Inspection of the material. Perform filter mat inspection:
oil filter components Findings.__________________________________________________
OMM No. E 0110.74
15 Same as daily inspection from para 4.1.1 through 4.1.3.
4.1.1; 4.1.2; 4.1.3
OMM No. E 0110.74 Check torque of hub bolts by, applying the necessary torque only. Lock
16
4.2 wire bolts again.

2.5 100 hours / annual inspection.
ATA 05 – Time limits and maintenance schedule
1 P2002-JF-AMM Lubrication points:
5:30 Perform lubrication tasks: refer to Chapter 05-30 for lubrication charts
and related frequencies.
ATA 06 – Engine Cowlingand inspection caps
Before installing the caps removed for maintenance purposes, inspect

P2002-JF-AMM
2 for absence of loose tools, especially in correspondence of the flight
6:10
controls. Then make sure all inspection caps are installed and secured.
P2002-JF-AMM Remove cowlings and check them for condition. Check fasteners and
3
6:10;71:10 hinges for condition.
P2002-JF-AMM Check the integrity of ablative cowling coating (internal side of engine
4
6:10;71:10 cowlings). Repaint if necessary.
ATA 11 – Markings and placards
P2002-JF-AMM
5 Inspect internal placards, check for their readability and wear.
11:00
P2002-JF-AMM
6 Inspect external placards and ID board: check for readability and wear.
11:00
ATA 21 – Heating and ventilation
P2002-JF-AMM
7 Cabin heat valve: check for cracks and security of installation.
21:00
P2002-JF-AMM
8 Control the Cabin Heat valve return spring.
21:00
P2002-JF-AMM
9 Perform a cabin heat valve control cable rigging.
21:00
P2002-JF-AMM Control the hoses condition of Heating system. No damage is allowed.
10
21:00 Control fasteners.
P2002-JF-AMM Control cabin heat control knob and carburetor heat control knob for
11
21:00 condition.
P2002-JF-AMM
12 Check the air scoops for condition and free movement.
21:00
Inspect cabin heat and defrost controls for operation and condition.
P2002-JF-AMM
13 Check for operation, restricted movement, interference or unusual
21:00; 21:10
play. Check defrost valve for operation.
ATA 23 - Communications
Inspect Communication equipment for general condition, operation and
P2002-JF-AMM
14 security of installation. Inspect Audio panel for general condition,
23:00
operation and security of installation.
P2002-JF-AMM
15 Check antennas, for damage and security of installation.
23:00
P2002-JF-AMM
16 Check electrical bonding to the a/c.
23:00
ATA 24 – Electrical system
P2002-JF-AMM Check for proper battery installation. Inspect battery cables and
17
12:60; housing. Check vent and drain lines free of obstructions.
P2002-JF-AMM Remove the battery and perform capacity test. Re-install battery if
18
24:10 airworthy.
P2002-JF-AMM Inspect External Power Receptacle for absence of damage, corrosion and
19
24:10 arching.
P2002-JF-AMM Inspect circuit breakers panels for general condition and security of
20
24:00 installation. Inspect breakers markings for their readability and wear.

P2002-JF-AMM Check the hardware and related connection behind the instrument panel
21
24:00 for condition, corrosion, deformation and damage.
P2002-JF-AMM
22 Perform overvoltage relay test.
24:20
Remove all inspection caps and inspect all electrical wires, connectors
P2002-JF-AMM
23 and attaching parts for security, routing, chafing, deterioration, wear
24:00
and correct installation.
P2002-JF-AMM Check bus bars for general condition, cleanliness, and security of all
24
24:00 attachments and terminals.
ATA 25 – Equipment and furnishings
Inspect seat, check for condition, check the seat guide and seat guide
P2002-JF-AMM
25 attachments for unusual wear and friction. Check the locking lever free
25:00; 25:10
to move. Test locking system at both seat positions.
P2002-JF-AMM Check safety belts for condition and operation. Inspect safety belts
26
25:20 attachments.
P2002-JF-AMM Inspect the first aid kit, check for expiration date of the single parts (if
27
25:00 necessary replace the items).
P2002-JF-AMM
28 Inspect cargo net and the floor attachment points for condition.
25:20
ATA 26 – Fire protection
Inspect portable fire extinguisher, and related support: weigh and follow
P2002-JF-AMM
29 service instructions written on the bottle (if necessary replace). Check
26:00
security of installation and effortlessness of removal.
ATA 27 – Flight controls
Flight controls: check free and smooth, inspect control stick, Teflon
loops, rods, bellcranks, cables and turnbuckles removing floor
P2002-JF-AMM
30 inspection panels/cabin covers. Check for interferences, corrosion, rub
27TOC
marks, and wear out. Inspect cables for tension and condition. Check
turnbuckle locking for security of installation.
P2002-JF-AMM Inspect stabilator trim: check for full travel and correct operation. Check
31
27;40 related indicator for operation.
ATA 28 – Fuel system
P2002-JF-AMM Check fuel pump electrical connections. Check fuel line connections
32
28TOC forleakage. Control fireproof socks.
P2002-JF-AMM
33 Clean electrical fuel pump filter.
28:10
P2002-JF-AMM Clean Gascolator filter. Check quick drain valve for condition and
34
28:10 operation.
P2002-JF-AMM
35 Inspect fuel tanks and lines for leaks and condition.
28:10
P2002-JF-AMM
36 Inspect fuel tank vents free from obstruction.
28:10
Inspect fuel selector valve for leaks, general condition and security of
P2002-JF-AMM
37 installation. Check fuel tank sump drain valves for conditions and
28TOC
operation.
P2002-JF-AMM Inspect operation of fuel selector valve control knob. Check for
38
28TOC restrictedmovement, interference or unusual play.
ATA 31 – Indicating system
P2002-JF-AMM Inspect the individual instruments and switch panels for general
39
31TOC conditionand security of installation.
P2002-JF-AMM
40 Check stall detector for integrity and operation.
31TOC
P2002-JF-AMM
41 Inspect all instruments markings for their readability and wear.
31TOC

ATA 32 – Landing gear
Inspect nose and main gear attachments, bolts and bushings for
P2002-JF-AMM conditionand security. Check especially for cracks, corrosion and
42
32TOC: 32:10; 32:30 damagedsurface protection. Inspect for looseness, condition and
security ofmounting points.
Examine the structure to which MLG and NLG assembly is attached.

P2002-JF-AMM
43 Checkespecially for cracks, nicks, cuts, corrosion damage, or any other
32TOC: 32:10; 32:30
conditionthat can cause stress concentrations and eventual failure.
P2002-JF-AMM Inspect gear fairings for cracks, deformation, proper rigging, and
44
32TOC: 32:10; 32:30 generalcondition.
P2002-JF-AMM
45 Inspect the NLG for movement, condition and relative steering system.
32TOC: 32:10; 32:30
P2002-JF-AMM
46 Check shock for general condition and state of rubber disks.
32TOC: 32:10; 32:30
P2002-JF-AMM Inspect tires for cuts, worn spots, bulges on the side walls, foreign
47
32TOC: 32:10; 32:30 bodiesin the treads, and tread condition. Check tire pressure.
Check for play in wheel bearings. Examine wheels: look especially for
P2002-JF-AMM cracks. Visually inspect the brakes and examine linings for excessive
48
32TOC: 32:10; 32:30 wear (if required replace linings) and disks for distortion and excessive
wear.
P2002-JF-AMM
49 Inspect the brakes lines and check retaining clamps.
32TOC: 32:10; 32:30
Check parking valve for damage, leakage and security of installation.
P2002-JF-AMM
50 Inspect parking brake handle, check for restricted movement,
32TOC: 32:10; 32:30
interferenceor unusual play.
P2002-JF-AMM
51 Inspect rudder pedals for operation and condition.
32TOC: 32:10; 32:30
P2002-JF-AMM
52 Check toe brakes for operation and master cylinders/hoses for leaks.
32TOC: 32:20
P2002-JF-AMM
53 Check oil level in brake reservoir. Replenish if needed.
32TOC: 32:20
ATA 33 – Lights
P2002-JF-AMM Inspect strobe, landing and navigation lights for operation, for condition
54
33TOC andsecurity of installation. Check electrical wiring.
P2002-JF-AMM Check instruments lights, cockpit cabin and switches lights and
55
33TOC relateddimmers devices operate correctly.
ATA 34 - Navigation
P2002-JF-AMM Inspect Navigation equipment for general condition, operation and
56
34TOC securityof installation.
P2002-JF-AMM Inspect electronic installations for condition and security: check
57
34TOC antennasand mounts for damage and security.
P2002-JF-AMM Pitot and static system: check static ports for condition and operation.
58
34TOC ExaminePitot-static system water trap, drain if required.
P2002-JF-AMM Inspect magnetic compass for condition, operation and security of
59
34TOC installation.
ATA 52 – Doors
P2002-JF-AMM Inspect the canopy for damage and operation. Check latches and
60
52TOC hingesfor condition and security of installation.
ATA 53 – Fuselage
P2002-JF-AMM Remove all cabin inspection caps. Inspect flight compartment for
61
53TOC absenceof loose equipment that might foul the controls.
P2002-JF-AMM Inspect externally skins, bulkheads, frames and rivets for damage and
62
53TOC sealing. Inspect drainage holes for free of obstructions.
P2002-JF-AMM
63 Check seat rails and stops and safety belt attachments
53TOC
ATA 55 – Stabilator and rudder
Inspect rudder for surface damage or irregularities (skin cracks,
P2002-JF-AMM distortion, dents, corrosion), structural defects (loose or missing rivets),
64
55TOC hinges and bearings damage and excessive wear, free to move. Check
control surface stops blocks for looseness/ effectiveness.

P2002-JF-AMM
65 Inspect rudder for condition, security and operation. Check travel.
55TOC
66 P2002-JF-AMM Inspect stabilator and tab for surface damage or irregularities (skin
55TOC cracks, distortion, dents and corrosion), structural defects (loose or
missing rivets), hinges and bearings damage and excessive wear, free to
move.
Inspect stabilator attachments and attach bracket for corrosion, rust and
P2002-JF-AMM
67 security. Check control surface stops for looseness/effectiveness and
55TOC
balance mass attachments.
P2002-JF-AMM
68 Check the stabilator trim tab attachments for unusual play.
55TOC
P2002-JF-AMM Inspect stabilator trim tab mechanism for condition, security and
69
55TOC operation. Check travel.
P2002-JF-AMM Inspect control surfaces electrical bonding connection for general
70
55TOC condition.
P2002-JF-AMM Remove aft fairings and check stabilator mounting plates for absence
71
55TOC ofcracks, corrosion and dust.
ATA 56 – Windows
P2002-JF-AMM
72 Inspect windows for condition and security.
56TOC
ATA 57 – Wings
Inspect wing surfaces and tips for damage and loose rivets. Check wing
P2002-JF-AMM
73 lower skin drain holes free of obstructions. Visually inspect the internal
57TOC
structure of the wing through wings inspections caps.
P2002-JF-AMM Inspect wing forward and aft attachment bolts for condition and security
74
57TOC (removing the closest part of the wing leading edge with the fuselage).
P2002-JF-AMM
75 Inspect ailerons bellcranks for condition and security of installation
57TOC
P2002-JF-AMM Inspect ailerons control rods, electrical wires and attaching parts for
76
57TOC security, routing, chafing, deterioration, wear and correct installation.
Inspect ailerons for surface damage or irregularities (skin cracks,
P2002-JF-AMM distortion, dents, corrosion), structural defects (loose or missing rivets),
77
57TOC hinge damage, excessive wear. Check balance mass mounting for
P2002-JF-AMM Inspect ailerons hinge pins and control rod for condition and security.
78
57TOC Check stops for looseness and effectiveness.
Inspect flaps for surface damage or irregularities (skin cracks, distortion,
P2002-JF-AMM
79 dents, corrosion), structural defects (loose or missing rivets), hinge
57TOC
damage, excessive wear. Check Flap travel limits.
P2002-JF-AMM
80 Inspect flaps hinge and control rod for condition and security.
57TOC
Inspect flap actuation mechanism and electrical connections. Check for
P2002-JF-AMM
81 condition, full travel and correct operation. Check related indicator for
57TOC
operation.
P2002-JF-AMM Inspect control surfaces electrical bonding connection for general
82
57TOC condition.
AA 61 - Propeller
P2002-JF-AMM Propeller: remove spinner and inspect attaching bolts for proper
83
61TOC lockwire.
OMM No. E 0110.74 Same as 50 hour inspection. Check track of propeller according to para
84
4.3; 3.1.10 3.1.10.
ATA 71 – Powerplant
P2002-JF-AMM Check integrity of engine firewall. Check for cracks, distortion or
85
71TOC wrinkles.
P2002-JF-AMM Engine electrical harness and equipment: check for condition and
86
71TOC security of installation.
P2002-JF-AMM Check on the air box the carburettor heating control leverage for
87
71TOC condition and operation.
Check for free movement of throttle, choke and carburetor heat levers.
P2002-JF-AMM Check bowden cables full travel and correct operation. Check for
88
71TOC restricted movement, interference or unusual play. Check friction for
operation.
ATA 75 – Coolant system

P2002-JF-AMM
89 Check coolant circuit: there should be no indication of leakages.
75TOC
P2002-JF-AMM
90 Check thermostatic valve for correct operation and no leakage.
75TOC
P2002-JF-AMM
91 Check coolant level in the expansion tank and overflow bottle.
75TOC
P2002-JF-AMM Visually inspect coolant overflow bottle and coolant radiator for
92
75TOC condition and security of installation.
ATA 78 - Exhaust
P2002-JF-AMM Disassembly the Exhaust system and check all the system for damage or
93
78TOC cracks.
ATA 79 – Oil system
P2002-JF-AMM
94 Disassembly, check and rinse the oil tank
79TOC
P2002-JF-AMM Visually inspect oil radiator and thermostatic valve for condition and
95
79TOC security of installation.
P2002-JF-AMM Visually inspect oil tank and tank vent line for condition and security of
96
79TOC installation.
P2002-JF-AMM
97 Check thermostatic valve for correct operation and leakage.
79TOC
P2002-JF-AMM
98 Check oil radiator for damage, cracks and leakage.
79TOC
Spark plug
MM(L) Rotax 912 S2 Remove all spark plugs and check for spark plug defects (deposits, ex-
99 12–20–20Remove cessive wear melting....)
the spark plugs Replace if defective.
Inspecting the magnetic plug
MM(L) Rotax 912 S2
100 12–20–20Inspecting Check the magnetic plug.
the magnetic plug
Visual inspection of the engine
General visual inspection of the engine for damage or abnormalities.
MM(L) Rotax 912
Check cooling air duct and cooling fins of the cylinders for obstruction,
101 S212–20–20Visual
cracks, wear and good condition. Take note of changes caused by
inspection
temperature influence.
MM(L) Rotax 912
Inspect temperature sensors and oil pressure sensor for secure fit and
102 S212–20–20Visual
signs of wear.
inspection
MM(L) Rotax 912 S2 Inspect all coolant hoses of the engine for damage, including leakage,
103 12–20–20 hardening from heat, porosity, loose connections and secure
Leakage check attachment. Verify routing is free of kinks and restrictions.
MM(L) Rotax 912 S2 Carry out visual inspection of leakage bore at the base of the water
104 12–20–20
Leakage check pump for signs of leakage.
MM(L) Rotax 912 S2 Inspect the expansion tank for damage and abnormalities. Check
105 12–20–20Expansion coolant level, replenish as necessary. Inspect radiator cap.
tank, radiator cap Inspect protection rubber on expansion tank base for correct fit.
MM(L) Rotax 912 S2 Inspect the overflow bottle for damage and abnormalities. Verify
106 12–20–20 coolant level, replenish as necessary. Inspect line from expansion tank
Overflow bottle to overflow bottle for damage, leakage and clear passage. Inspect
venting bore in cap of overflow bottle for clear passage.
MM(L) Rotax 912 S2 Inspect all oil lines for damage, leakage, hardening from heat, porosity,
107 12–20–20 security of connections and attachments. Verify routing is free of kinks
Leakage check and restrictions.
Inspect all fuel lines for damage, leakage, hardening from heat,
MM(L) Rotax 912 S2
porosity, security connections and attachments. Verify routing is free
of kinks and restrictions. Check steel fuel lines for any cracks and/or
the fuel lines
scuffing marks.
MM(L) Rotax 912 S2
Inspect the wiring and its connections for secure fit, damage and signs
109 12–20–20Check of
of wear.
wiring
110 MM(L) Rotax 912 S2 Inspect engine suspension and fasteners (GENUINE ROTAX® ) for
12–20–20Checking secure fit, including damage from heat, deformation, cracks.
the engine
suspension
P2002-JF-AMM
Check the airbox (GENUINE ROTAX ® ) incl. air flap actuation. Inspect
111 S-4Air-box control
sensors for tight fit, damage from heat, damage and signs of wear.
rigging
MM(L) Rotax 912 S2
112 12–20–20Cleaning Checkingtheairfilter.
the dry air filter
Inspect of the GENUINE ROTAX® exhaust system included in the
MM(L) Rotax 912 standard delivery.
113 S212–20–20Visual NOTE
inspection If there is no standard/genuine exhaust system in use, the
specifications of the manufacturer must be observed.
Auxiliary alternator
MM(L) Rotax 912 S2
On configurations with auxiliary alternator, check the attachment and
the V-belt tension.
the V-belt tension
MM(L) Rotax 912 S2
115 12–20–20Check the Checking the idle speed.
idle speed
MM(L) Rotax 912 S2
12–20–20Checking Check for free movement of the carburetor actuation (throttle lever
116 and starting carburetor).Check that the Bowden cable allows the full
carburetor actuation
travel of the throttle lever from stop to stop.
MM(L) Rotax 912 S2
12–20–20Checking Check carburetor synchronization. Mechanical and pneumatic
117
carburetor synchronization.
synchronization
Engine cleaning
MM(L) Rotax 912 S2
118 12–20–20 Engine cleaning.
Engine cleaning
Checking the air intake system
MM(L) Rotax 912 S2
119 12–20–20Checking Checking the air filter.
air intake system
Liquid level check
MM(L) Rotax 912 S2
120 12–10–00 Verify liquid level, replenish as necessary.
Fluid capacities
Checking the idle speed
MM(L) Rotax 912 S2
121 12–20–00Checking Checking the idle speed.
the idle speed
Engine test run
Observe the safety instructions!Start the engine and run to operating
temperature.Limits see in Operators manual 912 series.
Ignition check at _____________ rpm engine speed.
Speed drop without ignition circuit:
A (Off) ______________ rpmB (Off) ______________ rpm
MM(L) Rotax 912 S2 A/B (difference) ______________ rpm
122 12–20–00 Inspect carb heat system.
Test run of Hit the preheating and make a note of speed drop.
engine Speed drop ____________ rpm.
Preheating “OFF”, engine idle running and make a note of idle speed
running __________ rpm.
After engine test run, re-tighten the oil filter by hand (only at cold
engine).
Check for leaks.
SB 108 – CS – Rev0
123 SB 108 – CS – Rev0 See SB 108 – CS – Rev0.


Differential pressure check
1 MM(L) Rotax 912 S2 Check the compression by the differential pressure method.
12–20–20Checking Test pressure________hPa (psi).
the compression
Spark plug
MM(L) Rotax 912 S2
Check that resistance spark plug connectors fit tightly on the spark
2 12–20–20Inspection
of spark plugs plugs. Minimum pull-off force is 30 N (7 lb).
MM(L) Rotax 912 S2
3 12–20–20Installation Replacing spark plugs.
of spark plug
Checking the ventilation of the float chambers. Any trouble with the
MM(L) Rotax 912 S2 float chamber ventilation impairs engine and carburetor function and
4
must therefore be avoided. Check that the passage of the ventilation
lines is free and that no kinks can arise.
MM(H) Rotax 912 S2
5 Removal/assembly of the two carburetors for carburetor inspection.
73-00-003.3
MM(L) Rotax 912 S2
6 12–20–20Check Check weight of floater.
weight of floater
Inspecting carburetor sockets and drip tray
MM(H) Rotax 912 S2 Inspect the carburetor sockets for damage and abnormalities, checking
7 73-00-003.4.3 for cracks, wear and good condition. Take note of changes caused by
SB-912-030 temperature influence. See SB-912–030 — latest edition.
Exhaust
P2002-JF-AMM
8 Remove and inspect heat exchanger.
78TOC
2.7 600 hours / 3 years inspection.

P2002-JF-AMM
1 Examine the wheel axles. Look especially for corrosion and cracks.
32TOC: 32:10; 32:30
Disassemble the wheels and check for cracks, corrosion, dents,
P2002-JF-AMM
2 distortion, and faulty bearings. Clean, check and repack MLG wheel
32TOC: 32:10; 32:30
bearings with fresh grease and replace the NLG Ones if necessary.
Disassemble and inspect the brake assemblies and examine the parts
P2002-JF-AMM
3 (lining, disc and plates) for wear, cracks, warpage, corrosion, elongated
32TOC: 32:10; 32:30
holes, etc. Replace brake lining if required.
ATA 53 – Fuselage
P2002-JF-AMM
4 Inspect cabin truss for deformations and corrosion.
53TOC
P2002-JF-AMM Check internal condition of tail cone structure and cabin rear truss for
5
53TOC cracks corrosion and deformation.
2.8 800 hours or 3 years inspection.

P2002-JF-AMM
1 Replace brake system hydraulic fluid.
32:30


Checking the propeller gear box
MM(H) Rotax 912 S2
1 Check gear set (pittings).
72-10-00
MM(H) Rotax 912 S2
2 Check wear on tooth of overload clutches.
72-10-00
MM(L) Rotax 912 S2
05-50-00 Checking
3 overload clutch; 12- Gearboxes with overload clutch, Inspect overload clutch.
20-00Checking the
propeller gearbox
2.10 1200 hours / 5 years inspection.

ATA 28 – Fuel system
P2002-JF-AMM
1 Check and Rinse the fuel tanks.
28TOC
P2002-JF-AMM
2 Clean Finger Screen Filters, replace if needed.
28TOC
ATA 57 - Wings
Disconnect wings from fuselage, raise them enough to allow for
P2002-JF-AMM
3 checking
57TOC
condition of attachments and for the absence of mechanical play.
2.11 48 months inspection.

ATA 34 - Navigation
P2002-JF-AMM
1 Check calibration of airspeed indicator and altimeter. Perform leak test.
34TOC
Perform Magnetic compass compensation procedure.
For N 30 60 E 120 150

P2002-JF-AMM
2 Steer
34TOC
For S 210 240 W 300 330
Steer
2.12 propeller annual inspection.

OMM No. E 0110.74
1 Same as daily inspection from para 4.1.1 through para 4.1.9.
4.1

SECTION 2 –SERVICING.
Servicing the aircraft includes the replenishment of fuel, oil, hydraulic fluid, tyre pressures,lubrication
requirements and other items required to completely service the aircraft.
The information in the following sections pertains to general maintenance procedures.
Detailed information on the engines will be found in the engine Maintenance Manual.
The chapter includes the following procedures:
1. Storage.
2. Fuel system – Servicing practices.
3. Oil system – Servicing practices.
4. Coolant system – Servicing practices.
5. Seats.
6. Airplane cleaning instructions.
7. Wheels - Servicing practices.
8. Brake system - Servicing practices.
9. Control cables - Servicing practices.
10. Towing.
11. The list of places subject to greasing.
12. Torque data.
13. Safetying.
1. Storage
№ Section Reference Maintenance Task Description Mechanic
Airplane
P2002-JF-AMM Park airplane in hangar, if practical. If airplane is parked outside,
1
10:10 position on leveled surface and head it into the prevailing wind.
2 Center nose wheel.
3 Apply wheels chocks.

P2002-JF-AMM
4 Remove the battery
12:60
P2002-JF-AMM
5 Drain the fuel from the fuel tanks
12:10
6 Deactivate ELT.
7 Ensure flaps are retracted.

Electrically ground airplane by connecting ground cable to the engine
8
muffle.
9 Ensure that all inspection caps are closed and secured.
10 Close and lock canopy.
11 Secure the airplane to ground by mooring cables.

Each 7 days remove the wheel chocks and move the aircraft forward
12
and backward
Engine
Operate the engine until the temperatures have stabilizedfor a period of
13
5 min (engine oil temperature between 50 to70 °C (122 to 160 °F).
14 Switch the engine OFF.
15 Allow the engine to cool down.

MM(L) Rotax 912 S2
12–20–20
16 Change oil.
Oil change,Flushing
the oil circuit
SECTION 2 – SERVICING Issue 3 /rev. 0 / 18-03-2022 2-1

Remove the top spark plugs and spray all openings withcorrosion
17
inhibiting oil.
Turn the propeller several times by hand in direction of theengine
18 rotation, so that the corrosion inhibiting oil all necessary points
reaches.
MM(L) Rotax 912 S2
19 12–20–20Installation Install the spark plug.
of spark plug
Close all openings on the cold engine, such as exhaustend pipe, venting
20
tube, air filter etc. against entry of dirtand humidity.
21 Spray all steel external engine parts with corrosion inhibiting oil.
Propeller
No propeller should be stored standing on the blade tips. The best is to
store the propeller in the original packing. Special preservation of
OMM No. E 0110.74
22 HOFFMANN fixed pitch propellers is notnecessary, the existing
6.2
surface protection is sufficient. The propeller should not be stored near
heating systems or in rooms with extreme temperature changes.
p) Restoration from storage

№ Section Reference Maintenance Task Description Mechanic
Airplane
P2002-JF-AMM
1 Install the battery.
12:60
P2002-JF-AMM Check the wheels pressure.
2
12:70 MLG wheels 2.8 bar/40 psi and NLG wheel 2.2 bar/32 psi)
P2002-JF-AMM
3 Check oil and cooling system.
12:20; 12:30
4 Reactivate ELT.
5 Remove chocks from wheels.
P2002-JF-AFM
6 Make an engine start test (see AFM, engine start procedure).
4.2
Engine
7 Remove all plugs and caps.
8 Clean spark plugs with plastic brush and solvent.
MM(L) Rotax 912 S2
9 12–20–20Installation Reinstallspark plugs.
of spark plug
2. Fuel system – servicing practices.
Each fuel tank is filled through a single filler cap located on the wing upper skin. Each tank has a
capacity of 50 Lt (100 Lt total fuel capacity), 0.5 Lt are unusable(1 Lt total fuel unusable).
Observe all required safety precautions.

WARNING
Do not refuel the aircraft near flames or sparks; direct contact of fuel with the skin can cause
disease. During refueling apply grounding and make sure that a fire extinguisher is available in
the area. Master switch has to be turned OFF. Do not refuel with passengers on board.
CAUTION
Use only clean fuel servicing equipment.
CAUTION
Prolonged use of Aviation Fuel Avgas 100LL results in greater wear of valve seats and greater
combustion deposits inside cylinders due to higher lead content. It is therefore suggested to
avoid using this type of fuel unless strictly necessary.

Refueling Procedure:
WARNING
Take care that no foreign objects are inadvertently
introduced into the
1. Apply aircraft’s and refueling vehicle’s ground, through the engine muffle
2. Place a container under the fuel sump drain valve
3. Open the drain valve (refer to Figure 1)
4. Wait for complete water/moisture defueling
5. Close drain valve
6. Open the filler cap
7. Fill as required
8. Close the filler cap
9. Clean up any fuel spilled
10. Repeat the procedure for the other tank
11. Remove aircraft’s ground
Fuel Contamination Check Procedure:
1. Apply aircraft’s ground
2. Place a glass container under the drain valve
3. Open the drain valve
4. Fill the glass container and close the drain valve
5. Check fuel sample:
a. must be clear and clean
b. there should be no water inside
c. there should be no deposits inside

Fuel System Drainage Procedure:

1. Apply aircraft’s ground
2. Place a container under the Gascolator
3. Open the Gascolator drain valve
4. Wait for complete defueling
5. Place a container under the fuel sump drain valve
6. Open the drain valve (refer to Figure 1)
7. Wait for complete defueling
8. Close the drain valve
9. Repeat for the other fuel tank
3. Oil system – servicing practices.
Following paragraphs shows the procedures for oil level checking, filling and change.
CAUTION
Make certain that fluids and fluid containers are protected from contamination of any kind.. If
there is any doubt regarding the cleanliness of the fluid, do not use it. Containers for fluid must
never be left open to air longer than necessary.
WARNING
Allow the engine to cool down to the ambient temperature before start of any work.
Oil Level Checking and Filling Procedure

1. Open Engine cowling to access to oil tank (refer to Figure 2.)
2. Remove the filler cap; remove and clean the dipstick
3. Turn the propeller several times by hand in the direction of engine rotation to pump all the oil from
the engine to the oil tank (the process is complete when air flows back to the oil tank, perceived by a
gurgling)
4. Soak the dipstick in the oil tank
5. Read the oil level (refer to Figure 2): the level must be between the two marks
6. If necessary, replenish oil
7. Fit dipstick and filler cap
8. Clean up any spilled oil
9. Close oil tank and engine cowling

Oil Change Procedure

1. Remove upper and lower engine cowling
2. Run engine to warm oil before beginning oil change procedure
3. Engage parking brake, master switch OFF, disconnect battery
4. Crank engine by hand to transfer the oil from the crankcase, then apply “oil level checking” procedure
to record oil consumption
5. Remove safety wire and oil drain plug (refer to Figures 4. And 5.) and apply “Oil change” procedure
addressed on Rotax Engine Maintenance Manual P/N 899191 disposing used oil as per environmental
regulations
6. Install oil drain plug with safety wire
7. Re-install upper and lower engine cowling
NOTE
Remove and replace engine oil filter at each oil change. Refer to Rotax Engine Maintenance Manual
P/N 899191 – last issue, for detailed instructions
CAUTION
In event of heavy oil contamination, it is necessary to perform the oil tank cleaning operation.
Refer to Par 12.22

Oil Tank Cleaning

In event of heavy oil contamination apply the following procedure:
1. Engage parking brake, master switch OFF, disconnect battery
2. Remove upper and lower engine cowling
3. Refer to Rotax Engine Maintenance Manual P/N 899191 – last issue, for detailed instructions for oil
tank cleaning
4. Reinstall upper and lower engine cowling
4. Coolant system – servicing practices.
In order to equalize the pressure inside the engine cooling system, an expansion tank is provided in the
highest point of the cooling system and it is fitted with a filler cap. The procedure for coolant
replenishing is described below.

Coolant System Level Check
WARNING
Do not remove the expansion tank radiator cap when the engine is hot:
escape of boiling coolant can cause injury to persons.
Procedure
1. Wait for the engine to cool down
2. Open engine cowling
3. Refer to Figures 6. and 7. for coolant tank location
4. Visual inspect of expansion tank level (always max) : replenish if necessary
5. Visual inspect of overflow bottle (between two marks of coolant tank, min. & max)
6. If necessary, replenish with coolant of same composition both the tanks (repeat filling procedure)
7. Close engine cowling

5. Seats.
The P2002 has two seats, each seat is horizontally adjustable..

They are mounted on two parallel tracks, attached to the compartment floor structure, which allow the
seat to move forward or rearward.
Each seat consists of the following main components:
(1) Primary Structure Assembly consisting of the sitting and backrest assemblies.
(2) Horizontal Position Adjustment System allowing for the horizontal position adjustment.
The device consists of a lever located in the lower side of the structure.

Seats Removal and Installation Procedure

Procedure
1. Remove seats locking device
(unscrew and remove, refer to
Figure 9.)
2. Pull seat lever then slide seat all
forward (refer to Figure 10.)
3. Pull Up seat and remove it from
his location
4. Apply procedure for both seats
5. To reinstall seats, reverse these
steps
6. Airplane cleaning instructions.
The aircraft should be washed with soapy water. Abrasive detergents or alkaline soaps used on painted
or plastic surfaces could lead to scratches or cause corrosion of metal surface. Cover areas where
cleaning solution could cause damage.
NOTE
How often the a/c should be cleaned depends on the environment in which it has been operating. It is
important that the airplane be kept in a clean condition and repeated cleaning should be
accomplished as often as necessary. The necessity for cleaning is indicated whenever there is any
appreciable amount of soil accumulation, by the presence of salt deposits or other contaminants, by
evidence of paint surface deterioration and by the presence of excessive oil or exhaust deposits or
spilled electrolyte and deposits around battery area. Cleaning is required immediately after exposure
to adverse weather conditions, salt spray, after repairs or service which left stains, smudges or other
gross evidence of maintenance.
External Surfaces Cleaning Procedure

To wash the aircraft the following procedure may be used:
1. Flush out dirt
2. Apply cleaning solution with sponge or soft bristle brush
3. To remove stubborn oil and grease use a kerosene moist cloth
4. Where exhaust stains exist, allow solution to remain longer on the surface
5. Any good automotive wax may be used to preserve the painted surface.
Soft cleaning cloths or chamois leathers should be used to prevent scratches when cleaning or polishing.
A heavier coating of wax on the leading surfaces will reduce the abrasion problem in these areas.
CAUTION
Avoid entry of solutions and flooding of soap into a/c openings such static vents: it is
recommended that openings and vents be plugged as a precaution. Install protective caps if
practical.
Windows Cleaning Procedure
1. Remove with water dirt, mud, etc. from external surfaces
2. Wash with warm soapy water or with an aircraft plastic cleaner, employ a
soft cloth or sponge using a straight rubbing motion. Do not harshly rub surfaces.
3. Remove oil and grease with a alcohol moist cloth.
Internal Surfaces Cleaning
The aircraft interiors should be washed with a mild soap and water, never use alcohol
based or flammable products.
The instrumentation as a whole must be cleaned with a humid cloth; plastic surfaces
can be cleaned with suitable products.
For not easily accessible parts, perform cleaning with a small brush; for seats
cleaning make reference to P2002JF AMM Section 12-40.
Engine Cleaning Procedure
For engine cleaning procedures, refer to Rotax Engine Maintenance Manual P/N 899191 – last issue.
7. Wheels - Servicing practices.

Nose and main tires must always be inflated to the correct pressure. Before the flight, check
for damages, cuts, wear, etc.
CAUTION
As safety general rule, when servicing aircraft tires, personnel should stand either in the front
or rear of the wheel and avoid approaching from either side of the tire.
Procedure
1. Unscrew the valve dust cap
2. Connect a pressure gauge
3. Read the pressure. If required, adjust the pressure (MLG wheels 2.8 bar/40 psi and NLG
wheel 2.2 bar/32 psi)
4. Fit the valve dust cap
8. Brake system - Servicing practices.

Overall oil quantity in the brake system is 400ml (order of magnitude). Fluid is drawn from the
reservoir by the brake cylinders to maintain the fluid volume required for maximum braking efficiency.
The oil level check procedure is addressed below; refer to Chapter 32 for bleeding and filling brake
system procedures.
CAUTION
The brake system operation with low oil level could affect the brakes’
performances and could cause permanent damage
WARNING
Make certain that hydraulic fluids and fluid containers are protected from contamination of any kind.
Dirt particles may cause hydraulic units to become inoperative, cause seal damage, etc. If there is any
question regarding the cleanliness of the fluid, do not use it. Containers for hydraulic fluid must never
be left open to air longer than necessary.
Oil level check procedure

1. Remove the baggage compartment panel (Rear seats, baggage compartment, refer to Figure 13);
2. Check oil reservoir for oil level (must be between the two marks);
3. If necessary, remove reservoir filler cap and replenish oil ;
4. Refit reservoir filler cap;
5. Refit the inspection cap.
9. Control cables - Servicing practices.

Inspection Technique
Aircraft control cable systems are subject to a variety of environmental conditions and forms of
deterioration that, with time, may be easy to recognize as wire/strand breakage or the not so-readily
visible types of wear, corrosion, and/or distortion. The following data may help in detecting the
presence of these conditions.

Cable damage
Critical areas for wire breakage are sections for the cables which pass through fairleads and around
pulleys. To inspect each section which passes over a pulley or through a fairlead, remove cable for
broken wires by passing a cloth along length of cable. This will clean the cable for a visual inspection,
and detect broken wires, if the cloth snags on cable. When snags are found, closely examine cable to
determine full extent of damage. The absence of snags is not positive evidence that broken wires do not
exist. The figure below view A shows a cable with broken wires that were not detected by wiping, but
were found during a visual inspection. The damage became readily apparent (View B) when the cable
was removed and bent using the techniques depicted in View C.
External wear patterns

Wear will normally extend along cable equal to the distance cable moves at location. Wear may occur on
one side of the cable only or on its entire circumference. Replace flexible and non-flexible cables when
individual wires in each strand appear to blend together (outer wires worn 40-50%) as depicted in in
the figure below.Cables tension:
Internal cable wear

As wear is taking place on the exterior surface of a cable, the same condition is taking place
internally, particularly in the section of the cable which pass over pulleys and quadrants. This
condition, shown in Figure 3, is not easily detected unless the strands of cable are separated.
Wear of this type is a result of the relative motion between inner wire surfaces. Under certain
condition the rate of this type wear can be greater than that occurring on the surface. The
figures below are indicative.

Pulleys
Inspect pulleys for roughness, sharp edges, and presence of foreign material embedded in the grooves.
Examine pulley bearings to assure proper lubrication, smooth rotation, freedom from flat spots, dirt,
and paint spray. Periodically rotate pulleys, which turn through a small arc, to provide a new bearing
surface for the cable. Maintain pulleys alignment to prevent the cable from riding on flanges and chafing
against guards, covers, or adjacent structure. Check all pulley brackets and guards for damage,
alignment and security.
Pulley wear patterns

Various cable system malfunctions may be detected by analyzing pulley conditions. These
include such discrepancies as too much tension, misalignment, pulley bearing problems, and
size mismatches between cables and pulleys. Examples of these conditions are shown in the
figure below.

Cable fittings
100 hours standard inspection: check swaged terminal reference marks for any indication of cable
slippage within fitting. Inspect fitting assembly for distortion and/or broken strands at the terminal.
Check that all bearings and swivel fittings (bolted or pinned) pivot freely to prevent binding and
subsequent failure. Check turnbuckles for proper thread exposure and broken or missing safety
wires/clips. Pay particular attention to corrosion and “pitting” on cable terminals, turnbuckles and
cable fittings. Any corrosion or pitting found, requires replacement of the corroded fitting and/or cable.
100 hours special inspection: for aircraft 15 years old or older, using a 10X magnifier, visually inspect the
entire surface of each cable terminal, turnbuckle, or other cable fitting for corrosion or cracking. Inspect
under safety wire or clips wrapped around the cable or fitting. Any evidence of corrosion or cracking,
however minute, is cause for replacement. A logbook entry documenting the replacement of a cable
terminal, turnbuckle, or other cable fitting relieves the inspection requirement for that fitting only, until
such time as that fitting has been in service for 15 years.
10. Towing.
Move the aircraft on ground by pulling on the propeller blades close to hub. A tow bar can be attached
to fittings. Aircraft can be steered using the rudder or, for sharp turns, by lowering the tail to raise nose
wheel off the ground. In this case, owing to the favorable CG location, a gentle push on the tail cone just
ahead of empennage surfaces is all that is needed. Avoid dragging nose wheel sideways and do not
attempt to counter any movement of the aircraft by handling it by its wing tips.

11. The list of places subject to greasing.
Refer to Rotax Engine Maintenance Manual P/N 899372 for lubricants approved to be used for engine parts.
Grease canopy’s ball bearings and adjustable seat rails when necessary.
- Do not lubricate cockpit controls.
- Do not apply lubricant to rubber parts.
- Do not lubricate control cables, this causes slippage.
Item no. Lubrication points Frequency

1 Rudder upper bushing 100 Hrs
2 Rudder lower bushing 100 Hrs
3 Teflon road-stop LH 100 Hrs
4 Teflon road-stop RH 100 Hrs
5 Stabilator rod end 100 Hrs
6 Stabilator support bushing LH 100 Hrs
7 Stabilator support bushing RH 100 Hrs
8 9 Hinges 100 Hrs
10 Flaps lower bushing 100 Hrs
11 Stabilator loop 100 Hrs
12 Stabilator rod end 100 Hrs
13 14 Hinges 100 Hrs
15 Aileron bushing 100 Hrs
16 Aileron rod end 100 Hrs
17 Aileron rod loop 100 Hrs
18 Flap rod end 100 Hrs
19 Flap rod attachment RH 100 Hrs
20 Flap rod attachment LH 100 Hrs
21 Flap actuator attachments 100 Hrs
22 LH Pedals attachments 100 Hrs
23 RH Pedals attachments 100 Hrs
24 Rudder cables attachments 100 Hrs
25 Steering attachments 100 Hrs
26 Brake pump/rod attachments 100 Hrs
27 28 Control column attachments 100 Hrs
29 Control axis to column attachments 100 Hrs
30 Ailerons pulleys RH 100 Hrs
31 Ailerons pulleys LH 100 Hrs
32 NLG Lower attachment 100 Hrs
33 Shock absorber attachments 100 Hrs
34 NLG Upper attachments 100 Hrs
35 Steering attachments 100 Hrs
36 Pedals attachments 100 Hrs
37 Upper brake pump attachments (if installed) 100 Hrs
38 Lower brake pump attachments (if installed) 100 Hrs
39 Steering control road 100 Hrs
40 Connection pedal-rudder 100 Hrs
41 Parking brake lever 100 Hrs
42 2 Main gear wheel bearings 100 Hrs

12. Torque data
This paragraph gives the standard practices for torque loading nut and bolt combinations.
The importance of correct torque application cannot be overemphasized.
Undertorque can result in unnecessary wear of nuts and bolts, as well as the parts they secure.
Overtorque can cause failure of a bolt or nut from overstressing the threaded areas. Uneven
oradditional loads that are applied to the assembly may result in wear or premature failure.
The following are a few simple, but important procedures, that should be followed to ensure that
correct torque is applied.
-Be sure that the torque applied is for the size of the bolt shank, not for the wrench size.
-Calibrate the torque wrench at least once a year, or immediately after it has been abused or dropped,
to ensure continued accuracy.
-Be sure the bolt and nut threads are clean and dry, unless otherwise specified
-Run the nut down to near contact with the washer or bearing surface and check the friction drag
torque required to turn the nut. Whenever possible, apply the torque to the nut and not the bolt. This
will reduce rotation of the bolt in the hole and reduce wear.
-Add the friction drag torque to the desired torque. This is referred to as “final torque,” which should
register on the indicator or setting for a snap-over type torque wrench.
-Apply a smooth even pull when applying torque pressure. If chattering or a jerking motion occurs
during final torque, back off the nut and retorque.
-When torque is applied to bolt heads or cap screws, apply the recommended torque plus friction drag
torque.
-Whenever possible, apply the torque to the nut and not the bolt. This will reduce rotation of the bolt in
the hole and reduce wear.
-If special adapters are used which will change the effective length of the torque wrench, the final
torque indication or wrench setting must be adjusted accordingly.
Determine the torque wrench indication or setting with adapter installed as shown in figure beloworsee
AMM P2002JF ATA20-10 Page 201.


Torque Values
Bolts used in aircraft structures are compliant with AN and ISO metric specifications. Standard torque
values for nut and bolt combination are given in following table, if not otherwise specified in the
Maintenance Manual procedures.
13. Safetying
Safety locking allows for securing by various means any nut, bolt, turnbuckle etc. on the aircraft so that
vibration will not cause it to loosen during operation.
When applied, it prevents the disengagement of screws, nuts, bolts, snap rings, oil caps, drain cocks,
valves, and parts.
Specific data for other types of safety locking are described in the individual maintenance practices.
Three basic methods are used in safetying; safety-wire, cotter pins, and self-locking nuts.
Wire, either soft brass or steel is often used on control cable turnbuckles and engine accessory
attaching bolts.
Cotter pins are used on any point where a turning or actuating movement takes place.
Self-locking nuts are used in applications where they will not be removed often. Repeated removal and
installation will cause the self-locking nut to lose its locking feature.
They should be replaced when removed.
Installation of Safety Wiring

When you remove a component always remember the size and type of wire used and the method of
locking used for assembly.
There are two methods of safety wiring; the double-twist method (that is most commonly used) and the
single-wire method used on screws, bolts, and/or nuts in a closely spaced or closed-geometrical pattern
such as a triangle, square, rectangle, or circle.
The single-wire method may also be used on parts in electrical systems and in places that are
difficult to reach. (See figures below.)
When using double-twist method of safety wiring, apply following guidelines:

-.032 inch minimum diameter wire should be used on parts that have a hole diameter larger than .045
inch.
- Safety wire of .020 inch diameter (double strand) may be used on parts having a nominal
holediameter between .045 and .062 inch with a spacing between parts of less than 2 inches.
-When using the single-wire method, the largest size wire that the hole will accommodate should be
used.
- Copper wire (.020 inch diameter), aluminium wire (.031 inch diameter), or other similar wire called
for in specific technical orders, should be used as seals on equipment such as first-aid kits, portable fire
extinguishers, or emergency valves.
There are many combinations of safety wiring with certain basic rules common to all applications.
These rules are as follows.
-Remove all pieces of the old lockwire from the component
- Use only new lockwire, never use lockwire more than once or damaged
-Do not drill additional safety wire holes
-When bolts, screws, or other parts are closely grouped, it is more convenient to safety wire them
inseries.
-Drilled boltheads and screws need not be safety wired if installed with self-locking nuts.
-Safety wire must never be overstressed. Safety wire will break under vibrations if twisted too tightly.
Safety wire must be pulled taut when being twisted, and maintain a light tension when secured.
-Safety-wire ends must be bent under and inward toward the part to avoid sharp or projecting ends,
which might present a safety hazard.
-Check the units to be safety wired to make sure that they have been correctly torqued, and that the
wiring holes are properly aligned to each other. When there are two or more units, it is desirable that
the holes in the units be aligned to each other. Never Overtorque or loosen to obtain proper alignment
of the holes. It should be possible to align the wiring holes when the bolts are torqued within the
specified limits. However, if it is impossible to obtain a proper alignment of the holes without
undertorquing or overtorquing, try another bolt which will permit proper alignment within the
specified torque limits.
-Never twist the wire ends off with pliers; and, when cutting off ends, leave at least four to six complete
turns (1/2 to 5/8 inch long) after the loop. When removing safety wire, never twist the wire off with
pliers. Cut the safety wire close to the hole, exercising caution.
-Install safety wire where practicable with the wire positioned around the head of the bolt, screw,
ornut, and twisted in such a manner that the loop of the wire fits closely to the contour of the unit being
safety wired.
-When securing caps and drain cocks, the safety wire should be anchored to an adjacent fillister-head
screw (see Figure below). This method of safety wiring is applied to wingnuts, filler plugs, single-drilled
head bolts, fillister-head screws, etc.; which are safety wired individually.
Although there are several safety wiring techniques used to secure aircraft hardware, practically all are
derived from the basic examples shown in figures below.




Securing With Cotter Pins
Cotter pins are used to secure such items as bolts, screws, pins, and shafts. The diameter of the cotter
pins selected for any application should be the largest size that will fit consistent with the diameter of
the cotter pin hole and/or the slots in the nut. Cotter pins must not be reused on aircraft.
In using the method of cotter pin safetying, as shown in Figures below, ensure the prong, bent over the
bolt, is seated firmly against the bolt shank, and does not exceed bolt diameter. Also, when the prong is
bent over the nut, ensure the bent prong is down and firmly flat against the nut and does not contact the
surface of the washer.
Turnebuckles
All turnbuckles must be safetied with safety wire using either the double or single-wrap method herein
shown, or with any appropriately approved special safetying device complying with the requirements
of FAA Technical Standard Order TSO-C21.
Do not reuse safety wire.

Before securing turnbuckles, threaded terminals should be screwed into the turnbuckle barrel until no
more than three threads of either terminal are outside the barrel. After that, the turnbuckle has been
adjusted for proper cable tension.
All lock wire used in the safetying of turnbuckles should be carbon steel, corrosion- resistant steel,
nickel-chromium iron alloy (inconel), nickel-copper alloy (monel) or aluminium alloy.
For safety cable diameter of safety wire size and material, refer to the table below (dimension in
inches):


More than a satisfactory method for turnbuckle safetying can be adopted: hereinafter are reports the
common ones.

SECTION 3 - REPETITIVE AIRWORTHINESS DIRECTIVES AND

SERVICE BULLETINS.
1. Airplane
SB number SB number Subject Time intervals
EASA AD ATA 55:

SB 108-CS 100 hrs.
2013-0019 Stabilizers – Stabilator trim tab hinge supports – inspection
2. Engine
AD number SB number Subject Time intervals
- - - -
3. Propeller
AD number SB number Subject Time intervals
- - - -
SECTION 3 – REPETITIVE AIRWORTHINESS DIRECTIVES

Issue 3 /rev. 0 / 18-03-2022 3-1
AND SERVICE BULLETINS
SECTION 4 - COMPONENT TIME LIMITS.

NOTE
Life limit is counted starting from the date when component is installed on the aircraft (i.e.: the date when
Certificate of release to service is issued).
Component Part number Requirement Life limit

Electri trim actuator stabilator MAC6A orT2-10A life limit 1000 hrs or 10 yrs
Shock absorber pads 92-8-200-1(7pz) Life limit 1200 hrs or 10 yrs
22-9-120-1(2pz)
22-9-122-1
Fuel hose flexible line 22-9-124-000 Life limit 5 years
22-9-130-000*
22-9-132-000
22-11-910-001
22-11-910-002
Oil system flexible hose Life limit 5 years
22-11-910-003
22-11-910-4
Kemet-ALS30A223DB025 Or 1000 hrs/4 years
Capacitor Life limit
BHC 105-408 WOF
800 hrs/3 years
Brake fluid Life limit
WOF
92-11-105-02 Rev.B
92-11-105-01
Coolant hose flexible line Life limit 5 years
92-11-105-03
92-11-105-04
22-10-911-000
If applied MOD2002/53 22-10-912-000
Life limit 5 years
‘Thermostatic water valve 22-10-913-000
22-10-914-000
22-9-6051-000
If applied MOD2002/215 22-9-6052-000
Life limit 5 years
‘New Coolant hoses’ 22-9-6004-000
22-9-6005-000
Venting hose of the carburetors - 860660 or equivalent Replace 5 years
- 922250;
All rubber hoses of the cooling system Replace 5 years
- 922192 or equivalents.
- 874337;- 874347;
All rubber hoses of the fuel system Replace 5 years
- 874911 or equivalents.
All rubber hoses of the lubrication
system which are part of the engine
supply volume and if they are not in the Listed in “Airframe components” Replace 5 years
maintenance schedule of aircraft
manufacturer
Venting hose of the fuel pump Replace 5 years
Carburetor sockets - 267789 or equivalent Replace 5 years
Connecting hose of the air intake system - 860985 or equivalent Replace 5 years
Diaphragm on both carburetors - 861116 or equivalent Replace 5 years
V-belt - 980400 Replace 5 years
Fuel pump - 893115 or equivalent Overhaul or replace 5 years
Coolant must be
replaced as per
Replace (flushing of
manufacturers
- Refer to Operator’s manual and SI- cooling system
Coolant instructions, at the
912-016, latest issue before replacement
latest during overhaul
is required)
or when the engine is
replaced.
2000 hours or 15
Engine - Rotax 912S Overhaul or replace
years
Spark plugs - 297940 or equivalent Replace 200 hrs.
SECTION 4 - COMPONENT TIME LIMITS Issue 3 /rev. 0 / 18-03-2022 4-1

SECTION 5–BATTERY SERVICING.

5.1. Battery use and recharge
Check the voltage in open circuit mode, if the voltage is 10,60 (or higher) the battery is proper charged and ready
to install on aircraft. If the voltage is lower than 10,60 in one of the following situations:
- Dry charge new battery 10-12 hours after having filled up with acid;
- Battery already in use, which as remained inactive for long time battery recharge.
Perform battery charge procedure:
- Constant voltage range = 14,40-15,00 V
- Charging time = min. 6 hours – max 12 hours
NEVER CHARGE THE BATTERY OVER 24 Hours
5.2. Battery capacity test
Step Battery capacity test Additional info &

no. Task description References
See Chapter 12-60P2002-JF-AMM
1 Remove the battery from the airplane
Refer to Par. 4 – Battery
2 Charge battery according to par 4
servicing
Connect the fully charged battery to a capacity tester that
3
incorporates a load resistance, amp meter, volt meter and a timer.
Discharge the battery at the one hour capacity rate
4
to 10 volts. Record the discharge time.
The battery is considered airworthy if it meets 80% of the one hour
5
capacity rating (48 minutes to the cut-off voltage).
If the battery fails to meet the minimum run-time, recharge using
the constant current method until the specific gravity reading Refer to Par. 4 – Battery
6
stabilizes over three consecutive readings. Allow the battery to servicing
stand on open circuit for one hour
Repeat the discharge test as indicated. If the failure persists, Refer to Par. 4 – Battery
7
replace the battery. servicing
If the battery is found to be airworthy, it must be recharged prior
8
to re-installing it in the aircraft.
See Chapter 12-60P2002-JF-AMM
9 Install the battery on the airplane
SECTION 5 – BATTERY SERVICING Issue 3 /rev. 0 / 18-03-2022 5-1

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Kazakhstan Association of Small

Approved on behalf of the Owner:

«Falcon Avia» LLP;

Issue 3 / rev 0 / 18-03-2022

Table of content........................................................................................................................................................................... 0-2

TABLE OF CONTENT Issue 3 /rev. 0 / 18-03-2022 0-2

LIST OF EFFECTIVE PAGES

Approved on behalf of the Owner: Kazakhstan Association of Small Aviation

LIST OF EFFECTIVE PAGES Issue 3 /rev. 0 / 18-03-2022 0-3

LIST OF REVISIONS Issue 3 /rev. 0 / 18-03-2022 0-4

REVISION DESCRIPTION PAGE

Removed Inserted Revised

Prepared by: Checked by:

Position: ______________________________________________ Position: ______________________________________________

Signature: ____________________________________________ Signature: ____________________________________________

Name and Surname: ________________________________ Name and Surname: ________________________________

Date: _________________ Date:_________________

REVISION DESCRIPTION PAGE Issue 3 /rev. 0 / 18-03-2022 0-5

LIST OF ANNUAL REVIEWS

No. Date of review Name Signature Next due date

LIST OF ANNUAL REVIEWS Issue 3 /rev. 0 / 18-03-2022 0-6

LIST OF ABBREVIATIONS Issue 3 /rev. 0 / 18-03-2022 0-7

1. The AIRCRAFT MAINTENANCE PROGRAM (AMP) is applied for AIRCRAFT:

2. Information about Operator:

3. Identification of the program:

3.2. The AMP is developed on the basis of following documents:

4. The Operator statement:

Signed on behalf of the aircraft owner (operator):

Name and Surname: _________________ Signature:__________________

OBLIGATIONS OF OPERATOR Issue 3 /rev. 0 / 18-03-2021 0-8

STANDARDS AND RESPONSIBILITIES

1.1. The owner is responsible for the aircraft continuing airworthiness.

2. Certificate of release to service (CRS):

3. Airworthiness life limitations:

4. Airworthiness directives (AD’s):

5. Overhaul, additional inspection and test periods:

6. Instructions for continued airworthiness:

7. Changes (modifications or repairs):

STANDARDS AND RESPONSIBILIETIES Issue 3 /rev. 0 / 18-03-2022 0-9

10. Performance of maintenance:

11. Corrosion control program:

STANDARDS AND RESPONSIBILIETIES Issue 3 /rev. 0 / 18-03-2022 0-10

1) Line Maintenance Inspection.

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-1

6 Inspect for damages, leakage and general condition.

The erosion tipping (Type A) of the propeller blades ends in

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-2

Radial crack, is less critical if it is limited to the outer

Tangential crack is critical and an indication of overload.

A hair crack at the end of a short lamella (see para. 2.2.1) is

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-3

1.2 Pre-Flight check.

U Visual inspection of the Landing and Strobe Light.

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-4

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-5

ATA 32: Landing gear

2.2First 25 hours of engine.

MM(L) Rotax 912 S2

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-6

SECTION 1 – INSPECTION Issue 3 /rev. 0 / 18-03-2022 1-7

Position: Position:

Signature: Signature:

Name and Surname: Name and Surname:

Date: _ Date:_

Name and Surname: _ Signature:__