AEROPRAKT AEROPRAKT-22LS User manual

AEROPRAKT-22LS
Airplane Maintenance Manual
A22LS-AMM-02
Airplane Model: AEROPRAKT-22LS (A-22LS)
Airplane Registration Number: N22FC
Airplane Serial Number: 373
Date of issue: 19.02.2020
Approved by: Yuriy Yakovlyev
Position: Chief designer
Date of approval: 19.02.2020
This manual must be carried in the airplane at all times.

AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
This airplane is to be serviced and maintained in compliance with information and instructions
contained herein.
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
RECORD OF REVISIONS
No part of this manual may be reproduced or changed in any manner without a written
consent of the Manufacturer.
Any revision of the present manual must be recorded by the Manual holder in the following
table according to information from the Manufacturer.
New or amended text in the revised pages must be marked by a black vertical line on the
left hand margin. The Revision No. and the date must be shown on the bottom left hand
side of the page.
Rev. No.
Notice/Bulletin No.
Affected Pages
Date Issued
Date Inserted
Signature
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
Contents
1 General 4
1.1 S OURCES TO PURCHASE PARTS 5
1.2 E QUIPMENT LIST 5
1.3 L IST OF DISPOSABLE REPLACEMENT PARTS 5
1.4 E NGINE SPECIFICATIONS 6
1.5 W EIGHT AND BALANCE INFORMATION 7
1.6 T IRE INFLATION PRESSURE 7
1.7 A PPROVED FUEL , OILS AND CAPACITIES 8
1.8 R ECOMMENDED FASTENER TORQUE VALUES 8
1.9 G ENERAL SAFETY INFORMATION 9
1.10 R EP ORTING MAINTENANCE , SERVICE , AND SAFETY DIFFICULTIES 9
2 Inspections 10
3 Structures 13
4 Landing gear 17
5 Braking system 22
6 Engine and its control system 26
7 Cooling system 31
8 Lubrication system 33
9 Fuel system 34
10 Exhaust system 36
11 Propeller 38
12 Airplane control system 39
13 Electrical system 45
14 Cockpit heating system 55
15 Instruments, avionics, full and static pressure system 56
16 Pilot seats and harness belts 60
17 Cockpit doors 61
18 Recovery system 62
19 Glider and banner towing system 63
20 Structural repair 64
20.1 G ENERAL 64
20.2 C OCKPIT GLAZING REPAIR 64
20.3 F ABRIC COVERING REPAIR 65
20.4 C OMPOSITE P ARTS ’ REPAIR 66
20.5 R ESTORING OF DAMAGED PAINT / COATING 68
21 Feedback Form 69
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
1 General
NOTE: Notifications, service bulletins and safety alerts are published at the official website
of Aeroprakt company http://www.aeroprakt.kiev.ua .
This manual describes the procedures of proper aircraft handling and servicing
recommended by the aircraft manufacturer. It also contains certain inspection and
maintenance requirements that must be met to maintain flight performance and safe
operation of the aircraft. It is recommended to adhere to the scheduled periods of
greasing/lubrication and preventive maintenance taking into account the climate and
operating conditions.
Each of the inspection or service/maintenance action outlined in this manual specifies:
recommended special tools (if any) to accomplish the task,
the parts needed to perform the task,
type of maintenance, for example, line, heavy, or overhaul,
the level of certification needed to accomplish the task, for example, owner, A&P,
LSA repairman with inspection (or maintenance) rating, and repair station,
detailed instructions and diagrams as needed to perform the task,
method to test/inspect to verify the task was accomplished properly.
The types of the maintenance ( TM ) tasks specified in this manual are marked with the
following one-letter abbreviation and are defined as follows:
Line maintenance (L) – any repair, maintenance, scheduled checks, servicing,
inspections, or alterations not considered heavy maintenance that is approved by the
manufacturer and is specified in this maintenance manual.
Heavy maintenance (H) – any maintenance, inspection, repair, or alteration which
manufacturer has designated that requires specialized training, equipment, or facilities.
Overhaul (O) – maintenance, inspection, repair, or alterations that are only to be
accomplished by the manufacturer or a facility approved by the original manufacturer of the
product.
The levels of certification ( LC ) needed to accomplish the maintenance tasks specified in this
manual are marked with the following three-letter abbreviation and are defined as follows:
OWN (owner) – items that can be expected to be completed by a responsible owner who
holds a pilot certificate but who has not received any specific authorized training.
LRI (LSA repairman inspection) – items that can be expected to be completed on an
ELSA by a responsible owner, which holds an FAA repairman certificate (light sport aircraft),
with an inspection rating or equivalent.
LRM (LSA repairman maintenance) – items that can be expected to be completed on a
SLSA by a responsible individual, which holds a FAA repairman certificate (light sport
aircraft), with a maintenance rating or equivalent.
A&P (airframe and powerplant mechanic) – items that can be expected to be completed
by a responsible individual who holds a mechanic certificate with airframe or powerplant
ratings, or both, or equivalent.
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
TSP (task specific) – items that can be expected to be completed by a responsible
individual who holds either a mechanic certificate or a repairman certificate and has
received task specific training to perform the task.
1.1 Sources to purchase parts
For purchasing any parts or spares for this airplane contact your local dealer/distributor or
address the aircraft Manufacturer: AEROPRAKT Manufacturing Sp. z o.o., ul. Zadziele 10,
32-406 Zakliczyn, POLAND, e-mail: : [e-mail] .
1.2 Equipment list
This aircraft has the following equipment:
Flight instruments:
Garmin G5 EFIS,
Garmin GTN-650,
Dynon SkyView system flight instruments.
Engine instruments:
Dynon SkyView system engine instruments,
2 fuel level indicators.
Avionics:
Transponder, radio with intercom,
ADS-B,
Emergency locator transmitter.
Miscellaneous equipment
Garmin GMA-345,
Strobe & navigation lights,
Windshield air fans,
Landing light.
1.3 List of disposable replacement parts
The manual (see Sections 3 through to 16) contains the check lists with information about
check periods, recommended change out (RCO) times as well as references to inspection
and servicing/maintenance instructions for the airplane components and systems.
Before expiration of the recommended change out time of separate airplane parts or when it
is not specified their operation shall be performed on condition (OC). Such parts must be
inspected and replaced, if necessary, before expiration of the RCO (if specified).
If inspections and checks arouse any issues not covered in this manual contact the
Manufacturer for additional information.
Upon detecting corrosion on airplane structural elements contact the Manufacturer for the
required technical support. In this case further operation of the airplane may be dangerous!
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
1.4 Engine specifications
WARNING! On all issues of engine operation see Rotax engine Operator's Manual.
Follow its instructions to ensure safe and efficient operation of the engine.
Engine data and operational limitations are given in the table below:
Engine manufacturer
BRP-Rotax GmbH & Co KG (Austria)
Engine model
Rotax-912UL
Rotax-912ULS
Engine type
Flat-four, four-stroke
Take-off performance
59.6 kW (80 h.p.)
73.5 kW (100 h.p.)
Max. continuous performance
58 kW (77.8 h.p.)
69 kW (92.5 h.p.)
Take-off speed
5800 rpm (max. 5 minutes)
Max. continuous speed
5500 rpm
Idle speed
min. 1400 rpm
Oil pressure, maximum
minimum
normal
7 bar (102 psi) (for a short period at cold start)
0,8 bar (12 psi) (below 3500 RPM)
2,0 to 5,0 bar (29-73 psi) (above 3500 RPM)
Oil temperature, maximum
minimum
normal
140 °C (285 °F)
50 °C (120 °F)
90-110 °C (190-230 °F)
130 °C (266 °F)
50 °C (120 °F)
90-110 °C (190-230 °F)
Exhaust gas temperature
max. 880 °C (1616 °F)
Coolant temperature
(coolant exit temperature)
max. 120 °C (248 °F)
Cylinder head temperature
max. 150 °C (300 °F)
max.135 °C (275 °F)
Engine start, operating
temperature
max. 50 °C (120 °F) (ambient temperature)
min. -25 °C (-13 °F) (oil temperature)
Fuel pressure, maximum
minimum
0.4 bar (5.8 psi)
0.15 bar (2.2 psi)
Fuel antiknock properties
min. RON 90 (min. AKI 91)
1
min. RON 95 (min. AKI 91)
European standard of fuel
EN 228 normal, EN 228
super, EN 228 super plus
EN 228 super, EN 228
super plus
Aviation Standard of fuel
AVGAS 100 LL (ASTM D910)
Oil specification
Use only oil with Rotax norm RON 424 classification
1 Anti-Knock Index (RON+MON)/2
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
1.5 Weight and balance information
The airplane CG position must be between 1.500 m [59.06 in] and 1.751 m [68.94 in] (x)
CG
or between 19% and 37% of the wing MAC (mean aerodynamic chord) see Fig. 1 .
Fig. 1 CG location of the empty airplane, pilots, fuel and baggage
Compute the airplane CG position using the example in the table below:
Item
Weight,
kg/lbs
×
CG arm,
m/inch
=
Moment,
kg×m/lbs×inch
Empty airplane
346.7/764.5
×
1.564/61.6
=
542.3/47 082
Crew (2×80.0 kg)
160.0/352.8
×
1.600/63.0
=
256.0/22 224
Baggage
10.0/22.1
×
2.300/90.6
=
23.0/1 997
Fuel (2×57 l)
82.1/181.0
×
2.000/78.7
=
164.2/14 251
Total:
598.8/1 320.3
985.5/85 553
X
CG
= Total moment / Total weight
=
1.646/64.8
1.6 Tire inflation pressure
Normal inflation pressure:
Main wheels – 1.6 bar (22.7 psi) for 6.00×6 wheels;
– 1.3 bar (19.0 psi) for 8.00×6 wheels;
Front wheel – 1.0 bar (14.5 psi) for both 6.00×6 and 8.00×6 wheels.
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
1.7 Approved fuel, oils and capacities
WARNING! On all issues of engine operation see Rotax engine Operator's Manual.
Follow its instructions to ensure safe and efficient operation of the engine.
Fuel
Approved grades: antiknock properties – min. RON 95 (min. AKI 91 )
2
European standard – EN 228 super, EN 228 super plus
Aviation standard – AVGAS 100 LL (ASTM D910)
Maximum capacity of the fuel tanks: standard tanks – 2 × 45 = 90 liters (23.8 US gal)
optional tanks – 2 × 57 = 114 liters (30.1 US gal).
“Fuel Low” warning light ignites at approximately 4.5 liters (1.2 US gal) of fuel left per tank.
Unusable fuel: approximately 1 liter (0.3 US gal) per tank.
Oil
Approved grades: with RON 424 classification.
Oil tank capacity: 3 liters (NOTE: check correct oil level in the tank using the oil probe.)
Coolant
Approved grade: TELKO Polar Premium Long Life Antifreeze.
Quantity: 3 liters (NOTE: check the correct level using the overflow bottle marks.)
Braking fluid
Approved grade: Mobil ATF 220
Quantity: 0.2 liter (NOTE: check the correct level using the overflow bottle marks.)
1.8 Recommended fastener torque values
In A-22LS all fasteners forward of the firewall and in the electrical system is metric, and rear
of the firewall – inch. The bolts, screws and nuts (unless specified otherwise) must be
tightened (using appropriate torque wrenches) to the following torque:
1. For the static joints with spacing inserts (spacers, spherical bearings, etc.) according
to the table:
Metric
fasteners
Inch
fasteners
Torque, N·m (lb·ft)
М5
10-32
6 (4.4)
М6
1/4
10 (7.4)
М8
5/16
15 (11.0)
М10
3/8
25 (18.4)
2. For the movable joints where bolts serve as hinge axle the nuts tightening must be
done only to remove the axial play (gap) while preserving the rotational freedom in the
joint.
2 Anti-Knock Index (RON+MON)/2
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
WARNING! All bolts, nuts (except for self-locking ones), pins, turnbuckles must be locked
reliably.
1.9 General safety information
Aircraft owner/operator responsibilities:
Each owner/operator of the Aeroprakt LSA must read and comply with the maintenance and
continued airworthiness information and instructions provided by the Manufacturer.
Each owner/operator of the Aeroprakt LSA is responsible for providing the Manufacturer
with current contact information where the Manufacturer may send the owner/operator
supplemental notification bulletins.
The owner/operator of the Aeroprakt LSA is responsible for notifying the Manufacturer of
any safety of flight issue or significant service difficulty upon discovery.
The owner/operator of the Aeroprakt LSA is responsible for complying with all notices of
corrective action issued by the Manufacturer and for complying with all applicable aviation
authority regulations in regard to maintaining the airworthiness of the LSA.
The owner/operator of the Aeroprakt LSA must ensure that any needed corrective action be
completed as specified in a notice, or by the next scheduled annual inspection.
Should the owner/operator of the Aeroprakt LSA not comply with any mandatory service
requirement, the LSA shall be considered not in compliance with applicable ASTM
standards and may be subject to regulatory action by the presiding aviation authority.
1.10 Reporting maintenance, service, and safety difficulties
In case of encountering any maintenance or service or safety difficulties not covered by this
Manual report about it to the aircraft Manufacturer by e-mail or by fax using the Feedback
Form (see Appendix A). If necessary enclose sketches or photos showing the problem items
in sufficient detail.
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
2 Inspections
This section contains the instructions and checklist for inspection and servicing for the
completion of periodic and annual condition/100-h inspections with references to the
sections containing detailed instructions for the inspection/servicing action.
 Inspection/Servicing action and its interval in hours 
10
0
20
0
50
0
10
00
20
00
Structures (section 3)
Inspect fuselage for damage (fatigue cracks, loose rivets, etc.)
X
Inspect fuselage glazing for damage (silvering, cracks, etc.)
X
Inspect wings for damage (fatigue cracks, loose rivets, torn fabric covering, etc.)
X
Inspect wing attachment points for play
X
Remove the wings and inspect its spherical bearings for axial and radial play, and wing
and strut attachment brackets for fatigue cracks
X
Inspect the wing struts for fatigue cracks, deformation and loose rivets
X
Inspect the sealing fabric tape of the wing strut fairings
X
Check the wing attachment bolts’ torque and locking
X
Inspect the stabilizer for fatigue cracks, deformation, loose rivets and play in joints
X
Check the stabilizer attachment bolts/nuts torque and locking
X
Inspect the tail wheel for damage and play
X
Check the tail wheel attachment bolt/nut torque and locking
X
Inspect engine cowlings for damage (cracks, ruptures, damaged paint, etc.)
X
Landing gear (section 4)
Inspect the front leg for fatigue cracks, deformation and play
X
Check the front leg steering bellcrank bolt/nut torque and locking
X
Check the shock absorber condition and pressure
X
Inspect the MLG legs and attachment beam for fatigue cracks , deformation and play
3
X
Check the MLG legs attachment bolts/nuts torque and locking
X
Remove the wheel fairings and inspect the wheel tires for cracks, cuts and wear
X
Inspect the wheel fairings for cracks, ruptures and damaged paint
X
Check the torque and locking of the fairing attachment bolts/nuts
X
Inspect the mud-screens for fatigue cracks and deformation
4
X
Check the torque and locking of the mud-screen attachment bolts/nuts
4
X
Inspect the skis for damage
5
X
Check the torque and locking of the ski attachment bolts/nuts
5
X
Braking system (section 5)
Inspect expansion tank for leaks, cracks, secure attachment. Check the braking fluid
level.
X
Inspect the master cylinder for leaks of braking fluid
X
Inspect the parking brake valve for leaks of the braking fluid
X
Inspect the brake unit for the leaks of the braking fluid
X
Check the form and amount of the brake disk wear
X
Inspect the braking system tubing and joints for leaks and damage
X
3 Af ter 5000 landings the MLG legs must be removed and inspected caref ully for fatigue cracks
4 For an aircraf t version on w heels w ith mud-screens
5 For an aircraf t version on skis
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
Engine and its control system (section 6)
Inspect the engine mount for fatigue cracks and deformation
X
Check the torque of the engine mount attachment bolts
X
Inspect the shock absorbers for damage (deep cracks, disintegration, etc.)
X
Inspect the engine attachment fitting for the fatigue cracks
X
Check the intake airbox function, condition and attachment
6
X
Check the throttle and choke cables and cable sheath for functioning, wear, damage,
kinks
X
Check the torque of the throttle lever bolt (axle)
X
Cooling system (section 7)
Check integrity and torque of the clamps attaching radiator to engine mount
X
Inspect the overflow bottle for leaks of coolant, cracks in cap and bottle; check coolant
level
X
Inspect the coolant lines for leaks, damage (chaffing, cracks), check tightness of joints
X
Check torque of the water inlet elbow hose clamps, tighten if necessary
X
Lubrication system (section 8)
Inspect the oil tank plug for oil leaks; verify vent line is intact and secured
X
Inspect oil lines for leaks and damage (chaffing, cracks), check tightness of joints
X
Fuel system (section 9)
Remove fuel tanks and inspect them for fuel leaks and damage
X
Inspect the shut-off and drain fuel valves for leaks of fuel
X
Check condition and replace fuel filter (if necessary)
X
Inspect fuel lines for leaks, damage (chaffing, cracks), loose joints
X
Check condition and replace fuel lines (if necessary)
X
Exhaust system (section 10)
Inspect exhaust pipes and muffler for cracks
X
Verify attachment springs are intact and secured
X
Propeller (section 11)
Inspect propeller hub for fatigue cracks; check pitch angles of the blades
X
Check torque and locking of the propeller attachment bolts/nuts
X
Check torque of the spinner attachment bolts
X
Airplane control system (section 12)
Inspect control surfaces for fatigue cracks, deformation, loose rivets, damaged fabric
skin
X
Check the play in the hinges of control surfaces/linkages
X
Check tightness/locking of the nuts of control surfaces/linkages
X
Check tightness/locking of the nuts and play in hinges of control rods/shafts
X
Extend flaps and inspect flap extension mechanism (play in hinges, bolt/nut
tightness/locking)
X
Grease the sliding bearings of all control surfaces/linkages (where necessary)
X
Inspect rudder control cables for wear, check cable tension
X
Inspect rudder pedals for fatigue cracks and deformation
X
Check tightness/locking of the nuts of the front leg control rods
X
Check condition of the control cable pulleys and fairleads
X
Check trim tab attachment bolts/nuts for corrosion. Replace corroded fasteners
X
6 For all aircraft variants equipped w ith intake airbox
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
Inspect the trim tab control cables and sheath for damage (wear, kinks, etc.)
X
Take out and inspect the aft elevator control rod for wear. Replace if necessary.
X
Check control surfaces' deflection angles
X
Electrical system (section 13)
Verify battery charges/discharges properly, otherwise replace
X
Inspect starter terminals and starter relay connector, remove corrosion from contacts, if
any
X
Verify starter relay and cables are connected and attached reliably
X
Verify power cables have good contact with battery, starter and ground
X
Clean rectifier-regulator and condenser terminals/connectors of corrosion, if any
X
Check condition of electric switches and warning lights
X
Clean fuse block terminals of corrosion, if any. Check fuses
X
Verify correct function of the fuel level sensors/indicators (check readings)
X
Check landing light function and attaching nut torque
X
Clean engine sensors' terminals and connectors of corrosion, if any
X
Inspect electrical harness for damage (chaffing, broken wires, bad insulation)
X
Cockpit heating system (section 14)
Inspect warm air scoop for damage. Repair or replace if necessary
X
Inspect warm air shutter and its housing for damage. Repair or replace if necessary
X
Inspect warm air duct for damage. Replace if necessary
X
Check condition and operation of the warm air shutter actuator. Replace if necessary
X
Instruments, avionics, full and static pressure system (section 15)
Check condition of the switches and lights. Replace defective ones, if any
X
Check operation of the instruments and avionics. Replace defective ones, if any
X
Check condition of the full and static pressure system
X
Pilot seats and harness belts (section 16)
Inspect the seats framework for the fatigue cracks and loose rivets
X
Inspect the seat cushions upholstery for damage
X
Verify harness belts’ locks function properly
X
Cockpit doors (section 17)
Inspect door glass, framework, hinges and fasteners for fatigue cracks, mechanical
damage
X
Verify the gas struts function properly
X
Recovery system (section 18)
Check attachment of the suspension cables to fuselage structure and to parachute
lanyard
X
Glider and banner towing system (section 19)
Inspect the tow release control cable for damage/corrosion. Replace if necessary.
X
Clean, lubricate and check the tow release for operation. Replace if necessary.
7
X
7 Tow release must be returned to the manufacturer for complete reconditioning after 10000 operations (approx. 2000
starts).
The manufacturer recommends general overhaul after 4 years .
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
3 Structures
The airframe of A-22LS airplane includes the following parts: fuselage with glazing and
cockpit doors, wings, wing struts, horizontal and vertical tail units, wing root and strut
fairings and engine cowling. Fuselage with fin, wing struts and stabilizer are made of
aluminum alloys. Wing framework including leading edge section and top skin are all-metal
and bottom skin is fabric. Flaperons, elevator and rudder have metal framework and fabric
skin aft of spar. Rear fuselage panels (on top and on both sides) depending upon
customer-selected options may be made of transparent plastic glass, all-metal or combined.
Wing root /tip fairings, wheel fairings and engine cowling are made of glass fiber
composites. Wing strut fairings are made of transparent plastic using vacuum forming.
When servicing the airplane a special care shall be taken to keeping the paint coating intact
which prevents the airframe from corrosion. Care of the fabric skin consists mainly of care
of its paint coating. Correct care of the paint coating is one of the conditions of preserving
the airplane strength and aerodynamic characteristics. To keep the paint coating of the
airplane in good condition the dust and moisture must be removed in time, scratches,
spilling oil products, solvents, alkalis and acids on paint must be avoided.
INSPECTION CHART
Description
Interva
l
RCO
Instr.
No.
TM
LC
Fuselage
500 h
OC
3.1
L
LRI
Windscreen glass
100 h
OC
3.2
L
OWN
Rear fuselage skin panel, top
100 h
OC
Rear fuselage skin panel, right
100 h
OC
Rear fuselage skin panel, left
100 h
OC
Wing, right
500 h
OC
3.3
L
OWN
Wing, left
500 h
OC
3.3
L
OWN
Spherical bearings, 4 pcs.
2000 h
OC
3.4
L
LRI
Wing strut, right
500 h
OC
3.5
L
LRI
Wing strut, left
500 h
OC
Wings strut fairing, top, right
200 h
OC
3.6
L
LRI
Wings strut fairing, top, left
200 h
OC
Wings strut fairing, bottom, right
200 h
OC
Wings strut fairing, bottom, left
200 h
OC
Wing attachment bolts, 4 pcs.
100 h
OC
1.8
L
OWN
Wing strut attachment bolts, 4 pcs.
100 h
OC
Stabilizer
100 h
OC
3.7
L
LRI
Stabilizer attachment bolts, 2 pcs.
100 h
OC
1.8
L
OWN
Stabilizer attachment nut
100 h
OC
Tail wheel
100 h
OC
3.8
L
LRI
Tail wheel bolt
100 h
OC
1.8
L
OWN
Engine cowling panel, top
100 h
OC
3.9
L
LRI
Engine cowling panel, bottom
100 h
OC
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AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
Instructions:
3.1 Remove the engine cowling, doors, lower wing strut fairings (undo the screws fixing the
fairings and 'slide' them along the strut), pilot seats, and rugs. Inspect the fuselage for
cracks and deformation, paying special attention to primary structural elements, areas
of their connection and rivet joints.
Inspection for fatigue cracks:
Use torch or any other suitable source of light. When detecting very thin cracks remove the
paint in the area of the suspected crack for a closer flaw detection. If possible apply
load in this area in a manner that will 'open up' the crack. If the closer inspection
confirmed the presence of crack contact the manufacturer for required technical
support. If the suspected crack was not detected repaint this area.
Inspection for loose rivets:
When inspecting rivet joints look at the area around river heads. The paint around the rivet
heads must have no cracks or black stains that indicate a loose and corroded rivet
joint. When detecting such flaws contact the manufacturer for the required technical
support.
If no flaws were detected, reinstall everything in reverse order. Apply Loctite 222 on the
thread of the attachment screws of the wing strut fairings before reinstalling them.
Recommended special tools: magnifying glass, electric torch.
Necessary parts/materials: paint, Loctite 222.
3.2 Inspect the glass inside and outside for cracks. If any crack protruding from under the
glass attachment strips is detected the glass must be replaced. Contact the local
dealer for glass replacement instructions.
WARNING! The glazing material is not resistant to fuels, oils and solvents. Spilling
those liquids on glazing may cause its dimness and cracking. Washing
the glass with any agents that may damage PET-G glass is strictly
forbidden!
Recommended special tools: none.
Necessary parts/materials: none.
3.3 Drain fuel from the fuel tanks. Remove the upper wing strut fairings and fuel tanks.
Inspect the outer surface and, as much as possible, internal structure of the wing for
fatigue cracks, deformation and loose rivets as described in 3.1 (2
nd and 3 rd
paragraph). Pay special attention to the strut-to-wing attachment points, rivet joints of
the wing leading edge section and top skin.
Inspect the fabric skin for damage and detachment from the wing framework. It is allowed to
repair small cuts/ruptures (shorter 50 mm or 2 in) covering them with ORACAL
permanent sticking film. Upon detecting bigger damages and detachment of the fabric
skin from the framework contact manufacturer for the required technical support.
Verify that there is no play in attachment points of the wing and strut by holding the wingtip
gently and moving it up and down with an amplitude of 300 mm (1 ft). No movement in
the attachment points due to loose joint (play) is allowed. When detecting insignificant
radial play (less than 0.2 mm or 0.01 in) in the strut attachment points it must be
16

AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
eliminated by tightening its attachment bolt. In case if the play is more than 0.2 mm
(0.01 in) contact the manufacturer for the required technical support.
In case if no defects are found re-assemble everything in reverse order. Before re-installing
the screws attaching the fuel tanks and strut fairings apply Loctite 222 on the thread.
Recommended special tools: magnifying glass, electric torch.
Necessary parts/materials: ORACAL permanent sticking film, Loctite 222.
3.4 To detach the wings do the following:
- detach the doors;
- drain fuel from the fuel tanks;
- disconnect the fuel lines from the fuel valves, close the valves, plug the fuel lines
and pull them out of cockpit through the rubber sealing rings in fuselage beams;
CAUTION! Be careful while working with the fuel system, the fuel remaining in the fuel
lines is highly fire-hazardous and when spilled on the cockpit glass may
cause glass dimness and cracking.
- disconnect the electric connectors of the navigation lights and fuel level probes at
wing root and take the cables out of fuselage;
- detach the strut fairings (undo the screws attaching the fairings and slide fairings
along the struts);
- detach the Cardan rings of the flaperon shafts by removing the vertical bolts;
- remove the locking pins and undo the nuts from wing and strut attachment points;
- while holding the wing by the tip and strut carefully take out the strut attachment
bolts and remove the struts;
- while holding the wing by the tip and at the root take out the wing attachment bolts
and slowly move the wing away from fuselage carefully pulling the navigation light
cables from the wing fillets.
Inspect the wing and strut attachment fittings for fatigue cracks. Check the spherical
bearings of the wing attachment fittings for axial and radial play. When detecting play
in the bearings, as well as corrosion and fatigue cracks in the attachment fittings
contact the manufacturer for the required technical support. If no defects were
detected re-assemble everything in reverse order. Before reinstalling the screws
attaching the fuel tanks and strut fairings apply Loctite 222 on the thread.
Recommended special tools: magnifying glass, electric torch.
Necessary parts/materials: screw clamps, Loctite 222.
3.5 Remove the strut fairings (undo the screws attaching the fairings and slide fairing
along the strut). Inspect the struts for fatigue cracks, deformation (bend) and loose
rivets as described in 3.1 (2
nd
and 3
rd
paragraph).
If no defects were found re-install the fairing applying Loctite 222 on the thread of the
attaching screws.
Recommended special tools: none.
Necessary parts/materials: none.
3.6 Undo the screws attaching the fairings and slide the fairings along the strut. Inspect
outer and inner surface of the fairings for cracks. If the crack length does not exceed
17

AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
20 mm drill the crack end with  3 mm drill bit. The fairing with longer cracks must be
replaced.
Upon inspection re-install the fairings applying Loctite 222 on the thread of the attaching
screws.
3.7 Inspect the stabilizer for fatigue cracks, deformation and loose rivets as described in
3.1 (2
nd and 3 rd paragraph). Pay special attention to the areas near the stabilizer
attachment fittings and leading edge near the hole for elevator trim tab cable.
Verify that there is no play in the stabilizer attachment joints by gently moving the stabilizer
by its tip up and down with an amplitude not more than 50 mm (2 in).
CAUTION! The applied load may not exceed 30 N (7 lb).
There must be no movement due to the play in the attachment joints. When detecting
insignificant play (less than 0.2 mm or 0.01 in) it must be eliminated by tightening the
relevant bolted joint. In case if the play exceeds 0.2 mm (0.01 in) contact the
manufacturer for the required technical support.
Recommended special tools: magnifying glass, electric torch.
Necessary parts/materials: none.
3.8 Inspect the tail wheel for integrity and play. When detecting a serious damage replace
the wheel. When detecting an axial play below 0.5 mm (0.02 in), tighten the tail wheel
axle nut. If the play exceeds 0.5 mm (0.02 in), remove the wheel and install back
inserting a washer of appropriate thickness between the wheel hub and fuselage.
Tighten the tail wheel axle nut to ensure that the wheel can be rotated with an effort.
Recommended special tools: none.
Necessary parts/materials: none.
3.9 Remove the top and bottom engine cowling and inspect for cracks, ruptures, as well
as damaged paint coating. When detecting damaged paint coating sand the damaged
area with sandpaper and re-paint. When detecting cracks and ruptures sand the
damaged area from inside with sandpaper and cover it with a patch of fiberglass cloth
with epoxy resin. After the resin solidifies properly, sand the damaged area outside
with sandpaper and re-paint.
Recommended special tools: rubber gloves.
Necessary parts/materials: fiberglass cloth, epoxy adhesive, paint.
18

AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
4 Landing gear
A-22LS may have the landing gear (LG) of one of the following three types: wheels, skis or
floats. This manual contains the information for servicing the wheel and ski LG. The float
type LG is not included in this manual. For obtaining additional information contact the
manufacturer. When put on wheels the airplane is equipped with wheels of Matco mfg.
NOTE! When installing wheels tighten the axle nut as follows: first tighten the nut to remove
the axial play, then turn it back until its slots aligns with the hole for the split pin in
the axle. Then lock the nut using the split pin.
The front LG leg is steerable, of the trailing link type with spring shock absorber. The leg
structure consists of a strut, steering bellcrank, trailing link with wheel fork, spring shock
absorber, axle, spacing sleeves, wheel/ski and fairing/mud-screen (if installed). The
steering is achieved using the rudder pedals via the rods connected to the steering
bellcrank on the strut. The leg is attached to the firewall at two points – lower and upper
supports. The upper support is made of aluminum alloy plate, the lower support is an
assembly. The supports contain bronze bushings.
The main landing gear (MLG) is of cantilever spring type. The MLG consists of 2 flexible
legs each with wheel axle, wheel (or ski), brake unit with supporting plate, and wheel fairing
(or mud-screen). The MLG leg is made of aluminum alloy. It is attached with bolts at two
points to the lower beam of the frame No.2.
Maintenance of the brake unit with supporting plate is described in "Braking system"
section.
INSPECTION CHART
Description
Interva
l
RCO
Instructio
n
T
M
LC
Front LG leg strut
100 h
OC
4.1
L
LRI
Steering bellcrank bolt
100 h
OC
1.8
L
OWN
ROCK SHOX shock absorber
100 h
OC
4.2
L
LRM
Main LG leg, right
100 h
OC
4.3
H
LRM
Main LG leg, left
100 h
OC
Leg attachment bolts, upper, 2 pcs.
100 h
OC
1.8
L
OWN
Leg attachment bolts, lower, 2 pcs.
100 h
OC
Front wheel assembly
200 h
OC
4.4
L
LRI
Right wheel assembly
200 h
OC
Left wheel assembly
200 h
OC
Front wheel fairing*
100 h
OC
4.5
L
LRI
Right wheel fairing*
100 h
OC
Left wheel fairing*
100 h
OC
Front wheel mud-screen**
100 h
OC
4.6
L
LRI
Right wheel mud-screen**
100 h
OC
Left wheel mud-screen**
100 h
OC
Front ski***
100 h
OC
4.7
L
LRI
Right ski***
100 h
OC
19

AEROPRAKT-22LS Airplane Maintenance Manual A22LS-AMM-02
Left ski***
100 h
OC
* for wheel LG version with fairings;
** for wheel LG version with mud-screens
*** for ski LG version.
Instructions:
4.1 To inspect the front LG leg put the airplane on the tail wheel and secure it in this
position. The parking brake must be switched to ON.
Check the front LG leg supports for play. The radial play in the supports may not exceed 1
mm (0.04 in). No axial play is allowed.
If the radial play in the upper support exceeds the above specified value then the bronze
bearing in the support must be replaced. If the radial play in the lower support exceeds
the above specified value then the support with bearing must be replaced. Contact
manufacturer to obtain the instructions on replacement of the bearing and support.
Upon detecting any axial play in the supports tighten the upper support nut until the play is
eliminated, if necessary, insert a washer of an appropriate thickness.
WARNING! Tightening the nut must eliminate the play while ensuring free rotation of
the leg in the supports. Do not over-tighten the nut!
Check for play the joint of the wheel fork to the strut and the shock absorber joints to the
strut and to the wheel fork. If the play exceeds 0.5 mm replace the bronze bearings in
the joints.
Inspect the strut for deformation and fatigue cracks paying special attention to the welded
seams.
To remove the front LG leg (if necessary) do the following
- disconnect the control rods from the front leg steering bellcrank;
- remove the split pin and undo the nut of the upper support of the front leg;
- undo the nut and take out the bellcrank bolt;
- carefully take out the front LG leg from the supports simultaneously removing the
bellcrank from it.
CAUTION! Do not put the fuselage nose down while the front leg is removed! This may
cause damage to the airframe and propeller.
To inspect the wheel fork remove the wheel fairing (if installed) by doing the following:
- take out the bolts attaching the wheel fork and shock absorber to the strut;
- remove the wheel fork together with wheel fairing;
- detach the wheel fairing from the wheel fork by removing three attachment bolts.
Inspect the wheel fork for cracks. Make sure there is no axial play in the joint of the wheel
fork and the wheel axle and the wheel rotates freely.
Inspect the wheel tire for cracks and cuts. Estimate degree and uniformness of the tire wear.
In case of normal operation the tire wear must be uniform over entire contact surface
of the wheel. It is allowed to use the tires until the first wheel cords become visible. If
the cords are visible, or there are any deep cuts or cracks in the tire, the tire must be
replaced.
If the front wheel must be repaired or its tire must be replaced see instruction 4.4.
20