YAK-52 Maintenance Manual

YAK-52 Maintenance Manual
CONTENTS
GENERAL INFORMATION
1.OPERATIONAL KINDS OF MAINTENANCEOF THE AIRPLANE AND ENGINE
1.1
1.2
1.2
1.3
1.4
Preliminary Preparation
After Flight Preparation
After Flight Preparation
Pre Flight Preparation
Airplane Preparation For The Repeated Flight
2. SHEDULED WORKS OF THE AIRPLANE AND POWER PLANT
2.1
2.2
2.3
2.4
2.5
Power Plant
Airframe
Airplane Control
Landing Gear
Air System
3. ENGINE REPLACEMENT PROCEDURE
4. MAINTENANCE AFTER THE FIRST TEST FLIGHT AND AFTER THE FIRST FIVE FLIGHT
HOURS WITH THE NEWLY INSTALLED ENGINE
5. AIRPLANE STORAGE MAINTENANCE
TABLES OF THE LUBRICATION POINTS
Main Landing Gear Leg
Front Leg Of The Landing Gear
Elevator, Ailerons And Elevator Trim Tab Control
Rudder And Landing Flaps Control
Engine Control
Pilot’s Seat
Canopy
GENERAL INFORMATION
1. The actual Temporary Schedule is the basic document, determining the amount of work and the
maintenance intervals for power plant, mainframe, systems and equipment of the YAK-52 aircraft with
M-14P engine.
Performing in time the quality maintenance jobs, foreseen by the Maintenance Schedule ensures
serviceability, high level of operation reliability of the airplane and its airworthiness.
2. The scope of work and intervals of its implementation according to the kinds of maintenance are
determined on the basis of Maintenance Manual for Yak-52 aircraft with M-14P engine, spare parts
sets and experience of maintenance of similar airplanes in other aviation divisions.
3. Airplane maintenance should be carried out by the technical staff that has good knowledge of the
construction, airplane special maintenance features, engine and its equipment, aware of actual
Scheduled Maintenance Manual, technological directions and has sufficient practice in works,
authorized to carry out maintenance of the airplane YAK-52 by the order of the authorities of the
operating organization and takes full responsibility for quality of work carried out.
The engineering staff, authorized for the maintenance of the airplane, is responsible for maintenance
organizing and also for control of the scope and quality of work carried out in accordance to the valid
regulations and directions of the Actual Scheduled Maintenance Manual.
4. Temporary Scheduled Maintenance Manual includes maintenance of the mainframe, power plant,
airplane systems and equipment.
5. The regulations foresee the following kinds of maintenance :
preliminary preparation;
post-flight preparation;
pre-flight preparation;
aircraft preparation for the repeated flight;
scheduled maintenance.
6. Scheduled works for airplane, engine and other units are carried out in the same periods of time,
determined by the flight hours of the airplane, i.e. after every 50±5, 100±10, 200±15 flight hours of the
airplane. After carrying out 100-hour scheduled works, 50-hour scheduled works should be carried out
simultaneously and after carrying out 200-hour, 50-hour and 100-hour scheduled works should be
carried out.
Scheduled works on storage battery 12-ACAM-23 to be carried out in the periods of time, indicated in
the Technical Description and Maintenance Manual FDZ.532.015TO, edition 6-78.
7. After engine or other unit replacement in the airplane, their scheduled works are carried out in terms
of the regular scheduled works for the airplane. In this case it is allowed to carry out ahead of
schedule the nearest regular scheduled works on the replaced engine or unit.
8. For airplanes, carrying out training flights the scheduled works on landing gear are carried out in the
following periods:
after every 150±10 landings in the scope of 50-hour scheduled works.
fter every 300±20 landings in the scope of 100-hour scheduled works.
fter every 600±20 landings in the scope of 200-hour scheduled works.
9. When carrying out the maintenance of the airplane the works, indicated in the Scheduled
Maintenance Manual should be carried out and also all the malfunctions, having appeared either in
flight and indicated in the log book or having appeared during maintenance should be eliminated.
10. All the works, determined by the Scheduled Maintenance Manual and also other works on the
airplane must be carried out, using means of mechanization, ground equipment, instruments and
checkout equipment in good working order and intended for the above mentioned proceeding in
accordance with instructions and technical directions for airplane YAK-52 maintenance with an engine
M-14P, ready-made parts, included in complete set, bulletins and instructions of the manufacturers.
The units, joints and rubbing surfaces should be lubricated by the lubricant CIATIM-201 (excluding
places, specially mentioned in the Actual Scheduled Maintenance Manual).
PRECAUTION: During the maintenance of the airplane it is not allowed:
to walk on the surface of the airplane and also on the places not foreseen for walking;
to make possible damage of the airplane and paintwork by the ladder, filling hoses or by other
airfield equipment;
to put tools or parts on the surface of the airplane;
to allow people staying in the plane of propeller rotation or in front of the airplane with the
running engine at the distance less than 15 m.
11. In order to ensure good operation of the aviation technique under various climatic conditions
(excessive dampness, dustiness, etc.) and also if there are big periods of time between the flights or
in case the engine is replaced, the Deputy Commander of Aeronautical Engineering Service has the
right to give an order to carry out extraordinary works on the airplane in accordance with the Actual
Scheduled Maintenance Manual.
NOTE: after the first flight with the new engine and after the operation of 10 hours, the nuts of the
screw fastening should be drawn up tight. Tightening torque of the nuts is 10-2 kg·m.
12. Any kind of aircraft maintenance and any additional works, carried out on the airplane should be
indicated in the technical documentation in accordance with the valid regulations of the maintaining
organization.
13. After every case when maximum operating overload in is reached in flight and also after a rough
landing before runway or running out of it the inspection of the mainframe and engine should be
carried out. Make sure that:
there is no residual strain or cracks on the surface, framing, landing flaps, control surfaces
and ailerons, fuel leakage and that air system is pressure tight;
airplane controls, landing gear, engine mount, bosses on engine case, wing attachment to
fuselage, landing gear and tail plane are in good operable condition;
mounting of electric equipment instruments, navigational and radio equipment, boards,
instrument panels, are in good operable condition.
Inspection results should be recorded to airplane log book.
14. The inspections for various kinds of airplane preparation should be carried out in order, shown in
Fig. 1.
Fig. 1. Airplane inspection order
1.propeller; 2.cowling; 3.engine and systems on the frame o; 4.main legs of the landing gear; 5.front leg of the
landing gear; 6.right wing panel; 7.starboard of the fuselage; 8.tail unit; 9.port side of the fuselage; 10.landing flap;
11.canopy; 12.first cockpit; 13.second cockpit; left wing panel.
1.OPERATIONAL KINDS OF MAINTENANCE OF THE AIRPLANE AND ENGINE
1.1 PRELIMINARY PREPARATION
1. Take off the covers, take off the plug from the tunnel intake of the oil cooler, open the covers of the
hatches, necessary for inspection; make sure that the cocks of the extension and retraction of the
landing gear, landing flaps in the both cockpits are in the neutral position and are fixed by the safety
devices, all the switches and automatic circuit breakers, switches of magneto and electric feeding of
board supply line are switched off.
2. Inspect the propeller:
make sure of the working order of the blades, their fastening in the transition barrels and that
there are no mechanical damages. The covering of the blades should be smooth and even;
make sure that there are no end play and angular displacement of the blades with respect to
the transition barrel (the arrow on the blade must coincide with the scale calibration on the
face of the barrel corresponding to the determined angle);
make sure of the trustworthiness of the screw fastening on the shaft nose shaft of the
reduction gear
make sure of the working order of threaded and bolted connections and their locking.
WARNING: Blades with big and deep surface damage are not accepted to operation.
3. Inspect cowling and gills:
Open the cowling and check the attachment points of the cowling to the fuselage brackets,
working order of the swivels and studs with the fixed detects;
inspect the covers of the cowling, make sure, that there are no cracks, abrades, rivet
loosening and bolted connections ;
make sure of the working order of the gills, the integrity of the axis locking, flaps and that there
are no failures in the mobile connections; check the fastening of the gills to the engine,
reliability of covering and locking of the removing door seam;
make sure of the cleanness, good working order and safe fastening of the intake and tubing of
the cockpit ventilation, cooling of generator and compressor.
4. Carry out the internal inspection of the constant revolution regulator in order to make sure that there
are no external damage, oil flow in the joint, make sure of the safe fastening to the engine, of safe and
reliable fastening of the control wiring.
5. Inspect the connection of the case flanges of the units, blanks and plugs if there are no trace of the
petrol or oil, eliminate the flow by tightening the nuts tight.
6. Inspect the cylinders of the engine, inlet pipes, make sure of the reliability and sealing of the
connections, that there are no abrades of the inlet pipes. Make sure of the working order of the baffles
reliability of their fastening and that there are no trace of the overheating of the cylinders.
7. Check the state and the fastening of the starting valves, spreading of the compressed air the
working order and reliability of the air tubes and connection points.
NOTE: Check tightening of nuts, securing units, threaded connections and spark plugs tightening on
cool engine.
8. Check by hand and by choice using wrench tightening of spark plugs.
9. Inspect the exhaust manifold and air heater housing, make sure, that there are no cracks, burned
areas, traces of exhaust gases escaping through the seal. By choice, using wrench, check the
tightening of the nuts, fastening the branch pipes of the exhaust manifold to engine cylinders.
10. Check condition of rocker valve box covers and fastening cables. Make sure that there are no oil
leakage under the covers.
11. Inspect the boss of the engine case make sure that there are no cracks. Check the engine
fastening to the engine bed, the engine bed to the fuselage and the state of shock absorbers of the
wing fastening to the engine bed ring. The souring of rubber is not allowed. The dimensions of the
shock absorber packet, when the engine is installed and when the nuts are drawn up normally are
equal to 35 mm.
Inspect the ring and the struts of the engine bed, make sure that there are no corrosion, cracks and
deformation.
12. Check the state of the flexible hoses and tubing of the fuel system, locking of their nuts, fastening.
Make sure, that there are no rubbings, traces of faulty sealing and touching other units.
13. Check the state and fastening of the carburettor to the engine and working order of joint coupling
of its control.
14. Check the fastening of the fuel pump to the engine, additional tank, fuel emergency shut-off cock,
fuel filter, oil dilution valve to the firewall. Check the fastening of the filter by the fine fuel cleaning.
15. Making the pressure of 0,4 - 0,5 kg/cm2 by the grease gun, check the sealing of the fuel system
and its units, pay attention to the carburettor sealing, its connections, plugs and blanks if there are no
flow at the filter joins by the fine fuel cleaning.
NOTE: When operating in summer, take off the sleeve, supplying fuel to the valve, of oil dilution
(edition 772), block connection point of the engine and valve by the covers 2842A and nuts 2704A-4,
painted in red. Lock the nuts. The taken off sleeve should be muffled by the safety plugs 3OSTI 10474-72 and give for storage.
16. Check the magneto fastening to the engine, conductors to the magneto and spark plugs the state
of the cable braid or the ignition system. Check all the places of the-cable braid contact with the
engine and unit parts, paying attention to the obligatory clearance between the ignition cable braids
and edge of the cylinders.
17. Make sure of the working order of the compressor and the reliability of its fastening to the engine.
18.Make sure of the control drafts for the engine and gills, their manufacturing reliability, flanging and
fastening to the unit levers.
19. Inspect the oil system, venting and drainage pipe lines:
check the sealing of pipe lines connections and units (for leak-proofness), paying special
attention to the closing of the flexible hoses and to the cleanness of the drainage tube line
openings;
check the state and fastening of the oil system units. Drain 0,5 litres of oil from the oil sump
through the separating funnel with the narrow-meshed net. In case there are metal particles
found, state the reason of their occurring in the oil. Check the working order of the electric
circuit of the filter indicator.
20. Check the working order of the air carburettor collector for cleanness and fastening to the dust
filter. Take off the dirty filter clean it in the pure petrol and reinstall.
21. Inspect the front part of the fuselage. Make sure that there are no sheathing damages, rivet
loosening, operable condition and good fit of access door covers, leak-proofness of the fuel system
drain cock.
22. Inspect the main legs of the landing gear:
Check the outer state of the wheels, their brake equipment and aviation tires.
According to the marks on the tire and wheel flange, check, if the tire haven’t turned in respect
with the wheel flange;
Check the air charge of the aviation wheel tires (the compression at the normal charge
3±0,5 kg/cm2 should be 25-30 mm);
Check the state and hoses attachment of the air system to the leg struts;
Check the state and the lock fastening in the retracted position;
Check the state of the attachment units of the shock absorbing struts and folding bracing
struts;
Check the state of the shock absorbing struts, bracing struts, cylinders of landing gear
extension and retraction, oil flow through the seal of the struts, not tolerable backlashes in the
flexible connections and leak-proofness of joint parts and units;
Visually check the shock absorbers charge by nitrogen (the output of the mirror surface rod at
the normal nitrogen pressure 19+1 kg/cm2 must be 200-205 mm)
Check the sealing and integrity of the charging connection point;
Make sure of the working order of the main landing gear position indicators;
23 Inspect the front leg of the landing gear:
Check the outer state of the wheel and tire;
According to the marks on tire and wheel flange check if the tire haven’t turned in respect of
the wheel flange;
Check the air charge of the aviation tires (compression when charged normally 3±0.5 kg/cm2
should be 15-20mm);
Check the state and fastening of the lock in the retracted position;
Check the state of the attachment units of the shock absorbing strut and folding bracing strut;
Make sure of the damper working order, that there are no backlashes in the connections and
oil AMG -10 flow through the seal;
Visually check the shock absorbers charge by nitrogen (the output of the mirror surface rod at
the normal nitrogen pressure 26±1 kg/cm2 should be 140-145 mm). Check the sealing and
integrity of the charging connection point;
Check the state of shock absorbing strut, bracing struts, cylinders of extension and retraction
and make sure, that there are no deformation and cracks, oil flow through the seal of the
struts and not tolerable backlashes in the connections and joint places and reliability of joint
parts and units;
make sure, that there are no damages in the filling in recess of the front landing gear leg;
24. Check the charging of the air cylinders (manometer must show the pressure in the system of
50±5 kg/cm2.
25. Make sure of the seat fastening to fuselage frame reliability and leak-proofness of the safety belts
and their fastening, make sure of the reliability of locking handle operation
of the fastening belts in the plate spring.
26. During winter-spring operation period the sealing of dilution valve P/N 772 when the storage
battery is switched on, for that:
Disconnect the fuel pipe from the dilution valve outlet;
Using primer build up the pressure of 0,20,5 kg/cm2 in the fuel line and keep it for three
minutes.
Don’t allow the leakage of the fuel.
27. Inspect the engine control levers:
Make sure, that there are no seizing and additional noises when the control levers work in all
the movement range;
Make sure that the end positions of the levers in the cockpits correspond the end positions of
the levers on the units and on controlled throttle;
NOTE: the checking of full opening and closing of the throttle should be carried out when the fire cutoff valve is closed
Make sure of the stopper-rod device of the engine control levers.
28. make sure of the air-tightness of the air system according to the pressure reducing range in the
network during the not operating time of the airplane.
29. Inspect the left wing and aileron:
Make sure that there are no residual strain, sheathing damage, rivet loosening, fuel leakage
and fillet snug fit against the hatches covers;
make sure of the hinge units of ailerons and connecting control draft with the arm on aileron;
make sure of the storage battery fastening, that there are no traces of electrolyte and
cleanness of the drainage pipe;
make sure of the cleanness of the inlet openings of the pressure head;
through the hatch in the sheathing, check the state of the filling neck of the fuel tank,
cleanness of the cup and drain pipe.
30. After clearing all the faults, notified by the pilot, and having revealed the defects during the
inspection, make sure that:
the cocks of landing gear extension and retraction and of the landing flaps are in the neutral
position and are fixed by the locks;
all the switches and circuit breakers are switched off;
magneto and electric feeding switches of board power supply are in the position ВЫКЛ
(switched off) (the airplane is de-energized);
all the cockpits are clean without foreign articles in them.
31. Carry out works for preliminary preparation of electric and radio equipment (see the part 6 of this
book).
make sure of the working order of the mechanical place indicator of the front landing gear leg.
32. Inspect the right wing and aileron:
make sure that there are no residual strain, sheathing damages, rivet loosening fuel flow
under the sheathing and fillet snug fit against the hatches covers and the cleanness of the
drainage fuel tanks.
make sure of the sealing and attachment reliability of the oil cooler and its tubing.
make sure of the control draft proper attachment to the air cooler outlet pipe.
make sure of the aileron hinge unit working order and control drafts connection to the arm on
the aileron;
through the hatch on the sheathing, check the state of the filling neck of the fuel tank,
cleanness of the cup and the drain pipe.
33. Inspect the aft part of the fuselage and support:
make sure that there are no sheathing damage, rivet loosening and that there is tail hatch
cover snug fit;
make sure, that there are no damages of the cloth sheathing of elevator and rudder;
make sure of the aileron hinge unit and elevator TRIM TAB working order;
make sure through the hatch, that there are no foreign articles in the fuselage;
In. Check extension and retraction of the landing gear, inspect the cable laying, check the
reliability of turn buckle locking, termination and fastening to the control surface levers
airplane control cables, make sure, that there are no cable rubbing.
34. Make sure of the landing flaps working order, hinges and flap control parts.
35. Inspect the canopy of the airplane, make sure of its cleanness, transparency, fastening reliability
and transparency integrity. Check if it is easy to move and that the canopy mobile parts are snug fit to
the frame, state and fastening of the shock absorbers, operation of the canopy locks. Make sure of the
cleanness of the drainage openings, guiding rails of the moving canopy parts, good working order and
reliability of the back view mirror fastening.
36. make sure that the control handles, pedals and control wheel are moving easily and till the end.
Make sure, that control surfaces, ailerons, elevator TRIM TAB are deflecting freely (without knocking
and seizing) and fully to the needed direction and to the sides and that there are no backlashes,
bigger than allowed in the controls;
37. Check the extension and retraction of the landing flaps.
38. Inspect the state and fastening of the cylinders of the main and emergency air systems.
39. Check the state of the units, tube lines and all hoses and units and unit rubbing hoses and tube
lines and their sealing.
make sure of the gill working order, the integrity of the flap axis locking and that there are no
intolerable wears out of true in the flexible joints; check gill fastening to the engine and reliability of
removed flap lock opening and locking;
make sure of the cleanness, working order and reliability of fastening of collectors and tube lines of
the cockpit ventilation system, blowing over of the generator and compressor.
40. Inspect the RPM governor, make sure of it’s fastening to the engine, that there is no oil flow in the
joints and working order of control wiring fastening.
41. Inspect the joints of the case and accessories as well as the engine, if there are no traces of oil or
fuel flow.
42. Inspect the cylinders of the engine, inlet pipes, make sure, of the fastening reliability air tightness
of the connections, that there are no traces of overheating. Make sure of the baffle working order and
their fastening reliability.
43. Inspect the starting valves, air compression distributor, air pipes and connection point. Make sure
of the working order, air tightness and fastening reliability.
44. Check the fastening reliability of the spark plugs and cylinder heads.
45. Inspect the exhaust manifold and cockpit air heater. Make sure of the reliability of manifold
fastening to the engine cylinders and that there are no traces of exhaust gases, getting through the
sealing.
46. Inspect the bosses of the engine case make sure of the engine fastening to the engine bed and
engine bed fastening to the fuselage. Inspect the ring and bracing struts of the engine bed.
47. Inspect the state of the flexible hoses and pipe lines of the fuel system, locking their nuts,
fastening. Make sure that there are no rubbings, touching other units and traces of air tightness
failure.
48. Check the state and carburettor fastening to the engine, working order of the control joint coupling.
49. Check the fastening of the fuel pump to the engine of the additional tank, fuel emergency shut-off
cock, fuel filter, cock for oil dilution by the fuel to the frame 0. Check the fastening of the fine cleaning
filter.
50. Making the pressure of 0,4-0,5 kg/cm2 with the fill in injector, check the leak-proofness of the fuel
system, paying attention to the system units leak-leak-proofness.
51. Check the fastening of magneto to the engine, the state of ignition system cable braiding,
fastening of conductors to magneto and spark plugs. Make sure of conductors flanging and that
conductors do not touch the cylinder edges.
52. Inspect the compressor and make sure of the reliability of its fastening to the engine.
53. Inspect engine and gills control drafts. Make sure of their working order and fastening reliability to
the unit levers.
54. Close the cowling, canopy and all the inspection holes.
55. Carry out the last works (taking out the instruments of the on ground maintenance, control surface
locks, cover the airplane etc.), seal the airplane.
56. After carrying all the works, execute service records in the airplane documentation.
1.2 AFTER FLIGHT PREPARATION
1. Accept the airplane on the ground. Make sure, that there are no additional noises, when the engine
is throttled down. When the engine is stopped, put blocks at the main landing gear wheels, make sure,
that there is no wheel overheating and that the cable grounding is touching the ground (concrete).
Put on the cover and air pressure receiver pipe. Make sure, that storage battery and magneto are
switched off.
2. Get the notes from the crew about all malfunctions of the airplane, engine and equipment and write
them down in the airplane operation log.
3. If any malfunctions occurred during the flight, eliminate the cause of the malfunction and eliminate
malfunction. If the temperature in the outside is going to drop lower than +5°, make oil dilution by the
fuel.
4. Clean the fuselage from dust, mud (ice) canopy hinge, wing, tail support, cowling of the engine,
propeller of the wheel, shock absorbing struts, locks, landing gear arches, air collector, engine and its
accessories, tunnel of the air cooler, gills.
5. Drain the condensate from the filter sump of the air system. Close and lock the tap of the filter
sump.
6. Charge the airplane by the fuel, oil and compressed air.
7. Open the cowling of the engine and hatches covers, necessary for maintenance and inspection.
8. Inspect the propeller. Check the state of the air screw blades, their fastening in the transition cups
that there is no axial backlash and angular displacement of the blades of the main transition cup
(arrow on the blade must coincide with the scale gradation on the face of the cup, according to the
determined angle), reliability of the propeller fastening on the shaft gear box lip, the state of all cut,
bolt connections of the propeller and their locking.
CAUTION: It is not allowed to operate blades with big and deep surface damages.
9. Inspect the cowling and gill:
Inspect the fastening units of the cowling to the arms of the fuselage, working order of the
swivels;
Inspect the cowling covers make sure, that there are no cracks of the rubbing, rivet loosening
and bolted connections and that swivels are of working order;
10. Inspect the oil system and breathing pipe check the leak-leak-proofness of pipe lines connections
and units, paying special attention to the termination places of flexible hoses; check the state and
fastening of the oil system units; check the cleanness of the drainage pipe opening.
11. Check the working order cleanness and fastening of the carburettor dust filter collector.
12. Inspect the front part of the fuselage. Make sure that there are no sheathing damages, rivet
loosening and hatches covers snug fit and leak-proofness of the drain cock of the fuel system.
13. Inspect the main legs of the landing gear:
check the outer state of the wheels, their brake equipment and aviation tires.
According to the marks on the tire and wheel flange, check, if the tire haven’t turned in respect
with the wheel flange;
Check the air charge of the aviation wheel tires according to the strut compression
(compression at the normal charge 3 ± 0,5 kg/cm2 should be 25-30mm);
check the state and hoses attachment of the air system to the leg struts;
clean, inspect and lubricate the lock of the retracted landing gear;
check the state of the attachment units of the shock absorbing struts and folding bracing struts
to the wing;
check the state of the shock absorbing struts, cylinders of landing gear extension and
retraction, oil flow through the seal;
visually check the shock absorbers charge by nitrogen (the output of the mirror surface rod at
the normal nitrogen pressure 19+1 kg/ cm2 must be 200-205 mm) check the sealing and
integrity of the charging connection point;
lubricate the rod of the shock absorbing struts and cylinders lifting platform by thin layer of the
lubricant CIATIM-201;
make sure of the working order of the main landing gear position indicators.
14. Inspect the front leg of the landing gear:
check the outer state of the wheel and tire;
according to the marks on tire and wheel flange check if the tire haven’t turned in respect of
the wheel flange;
according to the strut compression, check the air charge of the aviation tire (compression
when charged normally 3±0.5 kg/cm2 should be 15-20mm);
clean, inspect and lubricate the lock of the retracted position;
check the state of the attachment units of the shock absorbing strut and folding bracing strut;
make sure of the damper working order, its fastening and hinge couplings with the fixed
member that there is no oil AMF -10 flow through the seal;
visually check the shock absorbers charge by nitrogen (the output of the mirror surface rod at
the normal nitrogen pressure 26±1 kg/cm2 should be 140-145 mm);
lubricate the rod by a thin layer of lubricant CIATIM-201;
check the state of shock absorbing strut, bracing struts, cylinders of extension and retraction
and make sure, that there is no oil flow through the seal and not tolerable backlashes in the
connections;
make sure, that there are no damages in the filling in of recess of the front landing gear leg;
make sure of the working order of mechanical place indicator of the front landing gear leg.
15. Inspect the right wing and aileron:
make sure that there are no residual strain, sheathing damages, rivet loosening fuel flow
under the sheathing and the fillet snug fit against the hatches covers;
make sure of the sealing and attachment reliability of the oil cooler and its tubing.
make sure of the control draft proper attachment to the air cooler outlet pipe.
make sure of reliability of control drafts connection to the arm on the aileron and proper
aileron hinge angles;
16. Inspect the aft part of the fuselage and support:
make sure that there are no sheathing damage, rivet loosening and that there is tail hatch
cover snug fit;
make sure, that there are no damages of the cloth sheathing of elevator and rudder;
make sure of the aileron hinge unit and elevator TRIM TAB working order;
17. Make sure of the landing flaps working order.
18. Inspect the canopy of the airplane, make sure of its cleanness, transparency, fastening reliability
and transparency integrity. Check the moving easiness of the mobile parts, the operation of shock
absorbers and canopy locks.
19. Make sure that the control handles, pedals, control wheel, control surfaces, ailerons and elevator
TRIM TAB are moving easily and till the end.
20. Check the state of the units, tube lines and all hoses of air system. Make sure, that there are no
weakening in the tube line, hoses and units, rubbing of hoses and pipelines and in their sealing.
21. Check the charging of the air cylinders (manometer must show the pressure in the system of
50±5 kg/cm2. Charge additionally if necessary.
22. Inspect the engine control levers, make sure, that there are no seizing and additional noises when
the control levers work in all the movement range, make sure that the end positions of the levers in the
cockpits correspond the end positions of the levers on the units and of controlled throttles;
NOTE: If the engine before operation must be heated by the ground heater, the cover should be taken
off after the heating and the blank from the air cooler collector should be taken out only after the
starting and heating the engine.
23. If necessary, remove dust, snow, ice and hoar-frost:
from the aircraft surface, canopy glass, outside antenna;
from the control units and from hinge of control surface, flaps, ailerons, elevator TRIM TAB between
the wing stitches, stabilizer, fin and front aileron edge and control surfaces;
from the shock absorbing struts, wheels, locks of the retracted landing gear position and also from the
arch of the front leg, from the intake and exhaust passage of the air cooler.
24. Inspect the propeller and make sure of its working order.
25. Inspect the cowling of the engine:
open the cowling and check the coupling joints of the cowling to the fuselage, the working order of the
swivels;
make sure that the gills and the collectors of cockpit ventilation, generator and compressor blowers
are clean.
26. Inspect the power plant and make sure of the working order and reliability of the engine, engine
bed and exhaust manifold make sure of the good working order of fuel, oil and air tube lines and
hoses.
27. Make sure of the fastening of the engine control drafts, draft connections with the carburettor,
RPM governor, gill control levers and air heating valve at the carburettor intake.
28. Inspect the front part of the fuselage, make sure that there are no sheathing damages and hatches
covers snug fit and leak-proofness of the drain cock of the fuel system.
29. Inspect the main legs of the landing gear:
check the outer state of the wheels, their brake equipment and aviation tires.
make sure, that there are no defects of struts, bracing struts, extension and retraction cylinders and
coupling joints;
make sure of the working order and fastening reliability of the tube lines and hoses of the wheel air
brake arrangement.
Check the air charge of the aviation wheel tires according to the strut compression (compression at
the normal charge 3 ± 0,5 kg/cm2 should be 25-30mm);
make sure, that the lock of the retracted landing-gear is clean;
visually check the shock absorbers charge by nitrogen (the output of the mirror surface rod at the
normal nitrogen pressure 19+1 kg/cm2 must be 200-205 mm);
make sure, that the brake surface of the rod is not damaged and that there is no oil AMG-10 leakage.
Remove the lubricant from the brake struts rods of the air cylinders with a clean napkin.
30. Inspect the front leg of the landing gear:
carburettor throttle should be carried out when the fire cut-off valve is closed.
31. Make sure of the seat fastening reliability to the fuselage frame and leak-proofness of the safety
belts and their fastening, make sure of the reliability of locking handle operation of the fastening belts
in the plate spring.
During every after flight checking inspect the spines, locks and the wholeness of the pilot’s fastening
belts stitching up. If the defects of the spinning locks and of the wholeness of the stitching up are
found and also if there is rubbing of the belt tape, change the belts.
NOTE: When carrying out works in the cockpit, put the belts of the lashing system along the side
boards in order to exclude a possibility of their spoiling by feet or soiling.
32. Inspect the left wing and aileron:
make sure that there are no residual strain, sheathing damages, rivet loosening, fuel leakage and
fillet snug fit against the hatches covers;
make sure of the hinge units of ailerons and connecting control draft with the arm on aileron;
make sure of the storage battery fastening, that there are no traces of electrolyte and cleanness of the
drainage pipe;
make sure of the cleanness of the inlet openings of the air pressure system.
33. After clearing out all the faults, noticed by the pilot and revealed during the inspection, make sure
that:
cocks of landing gear extension and retraction and of the landing flaps are in the neutral position and
are fixed by the locks;
all the switches and circuit breakers are switched off:
magneto switches and electric feeding switches of board power supply are in the position BbIKЛ
(switched off) (the airplane is de-energized);
all the cockpits are clean without foreign articles in them.
34. Close the cowling, hatches covers and mobile parts of the canopy. Install the blanks in the
collector of the air cooler and on the branch pipe of the exhaust manifold.
35. By the outer inspection, make sure once more that there are no damages on the sheathing of the
airplane, elevator TRIM TAB is in the neutral position, landing flaps are removed and that supporting
blocks are reliably put at the wheels of the main landing gear and grounding cable is touching the
ground (concrete), the airplane is reliably tied down.
36. Carry out the final works(taking out the instruments of the on ground maintenance, control surface
locks,
cover the airplane etc.), seal the airplane.
1.3 PRE FLIGHT PREPARATION
1. Take off the covers of the airplane, take off the blanks from the air cooler collector and from the
branch pipe
of the exhaust manifold, take off control surface locks and tie
2. Check the leak-leak-proofness of the membrane mechanism fuel cock of the carburettor fuel
passage, in order to check that it is necessary to make a pressure of 0.12-0.15 kg/cm2. in the fuel
system by the filling injector and keep it for three minutes. The leak-proofness of the atomisation pipe
testify the working order of the membrane mechanism. Making the pressure of 0.4-0.5 kg/cm2, check
the leak-proofness of the fuel system.
3. Check the control of the engine, fire cut-off valve, gill and air cooler flap, make sure, that there are
no seizing of the control wiring in all the ranges of positions of the levers.
NOTE: the checking of full opening and closing of the carburettor throttle should be carried out when
the fire cut-off valve is closed.
4. Make sure of the leak-proofness of the safety belts and their fastening, make sure of the reliability
of handle locking in the plate spring.
During every after flight checking inspect the spines, locks and the wholeness of the pilot’s fastening
belts stitching up. If the defects of the spinning locks and of the whole-ness of the stitching up are
found and also if there is rubbing of the belt tape, change the belts.
NOTE: When there is one pilot flying in the first cockpit, the fastening belts of the second cockpit
should be put into the lock of the right waist belt according to the standard diagram, tighten two lower
shoulder belts and the middle belt, taking up the slack fully. Then the fastening link of the middle belt
must tightly snug against the cup of the seat.
5. Check the airplane charge with fuel, oil and air. The airplane charging with fuel and oil must
correspond the flight task.
6. Make sure, that in the both cockpits:
the circuit breakers, switches on the instrument panels and desks are in the switched off
position;
magneto is switched off;
that cocks of landing gear extension and retraction and of the landing flaps are in the neutral
position and are fixed by the locks;
the fire cut-off valve is closed;
the cock of the air system is closed;
there are no foreign articles;
7.Inspect the aileron of the left wing:
make sure, that there are no sheathing damages, fuel leakage and make sure of the hatches
covers opening;
make sure of the hinge units of ailerons and connecting control draft with the arm on aileron;
make sure of the storage battery fastening and cleanness of the drainage pipe;
make sure of the cleanness of the inlet openings of the air pressure system.
check the outer state of the wheel and tire;
make sure, that there are no defects of strut, bracing strut, in the extension and retraction
cylinder, at the coupling joints and in the leg joint.
according to the strut compression, check the air charge of the aviation tire (compression
when charged normally 3±0.5 kg/cm2 should be 15-20mm);
make sure, that the lock of the retracted position is clean;
visually check the shock absorbers charge by nitrogen (the output of the mirror surface rod at
the normal nitrogen pressure 26±1 kg/cm2 should be 140-145 mm);
make sure of the damper working order, its fastening and hinge couplings with the fixed
member that there is no oil AMG-10 leakage through the seal;
make sure, that the brake surface of the rod is not damaged and that there is no oil AMG-10
leakage. Remove the lubricant from the brake strut rod of the lifting and extending cylinder
with a clean napkin.
8. Inspect the right wing and aileron:
make sure that there are no sheathing damages, weakening of the rivets fuel flow under the
sheathing and under the fillet and the reliability of hatches covers opening;
make sure that there is no oil leakage from the oil cooler ;
make sure of reliability of control drafts connection to the arm on the aileron and proper
aileron hinge angles;
9. Inspect the aft part of the fuselage and support:
make sure that there are no sheathing damage and that there is tail hatch cover snug fit;
make sure, that there are no damages of the cloth sheathing of elevator and rudder;
make sure of the aileron hinge unit and elevator TRIM TAB working order;
10. Make sure of the landing flaps working order.
11. Inspect the canopy of the airplane, make sure of the cleanness of the drainage openings, canopy
guiding rails, of the cleanness and transparency integrity. Check the moving easiness of the mobile
parts, the operation of shock absorbers and canopy locks.
12. Make sure that the control handles, pedals, control wheel deflect easily and till the end. Make sure
that control surfaces, ailerons and elevator TRIM TAB deflect freely (without knocking and seizing)
and fully to the needed direction and side and that there are no backlashes, bigger than allowed in the
controls;
13. Check the extension and retraction of the landing flaps.
14. Check the charging of the air cylinders (manometer must show the pressure in the system of 50 ±
kg/cm2). Charge additionally, if necessary.
15. Check the working order of the landing gear indicators, landing flaps and fuel-quantity indicator.
16. Drain 0.2-0.3 litre of fuel from the filter sump make sure, that there is no water, crystals, ice and
mechanical contaminants in the fuel.
NOTE: In case of finding free water, ice crystals, mechanical impurities in the poured out fuel, draw
the sediment from all the drawing points until the fuel, being drawn is clean. If is not successful to
eliminate the impurity of the fuel at the additional drawing, it is necessary to draw all the fuel, to clean
tanks and charge with condensed fuel.
17. Close the cowling, hatches covers and mobile parts of the canopy, close and lock all drain cocks.
18. Prepare the engine for starting. Start and run the engine in accord to the Instructions of engine
operation.
NOTE:1. If the engine hadn’t operated for more than three days, before starting, it is necessary to
carry out works, preventing hydro shock in the cylinders and of additional lubrication of mirrors of the
cylinders for excluding the possibility of half dry friction between the pistons and cylinder mirrors.
2. When the temperature of surrounding air is lower than +5°C, heat the engine by on ground heater
during 15-30 min., but in such a way, that the temperature of the cylinder heads is not lower than
30°C.
3. If, because of the low ambient temperature (minus 30°C and lower), before starting the engine the
oil hadn’t diluted but drained out after the switching off before starting, it is necessary to charge the oil
tank with oil, heated till 70-80°C. When charging, drain through the oil filter cock 2,5-3 litres of oil for
filling and heating oil tube lines.
19. After engine test run make sure that there are no oil and fuel leakage.
20. Fill in the control page of the airplane readiness to the flight and give it in to the pilot for carrying
pre-flight inspection.
1.4 AIRPLANE PREPARATION FOR THE REPEATED FLIGHT
1. Get the information from the crew about the operation of the aviation technique.
Charge the airplane with the fuel, oil and compressed air according to the flight task and pour out the
sediment of fuel after 5-10 minutes. Drain the condensate from the filter sump of the air system, close
and lock cock of the filter sump.
2. If necessary, clean the airplane, engine cowling, air screw, canopy glass and landing gear from
mud (snow, ice).
3. From the outer inspection of engine cowling, propeller, fuselage canopy, wing, landing flaps,
ailerons and tail support, make sure that:
there are no residual strain of the power plant, nicks or drifts on the sheathing, rivet loosening.
Make sure of the reliability of locks of coverings of hatches covers and cowling;
of the moving nimbleness of the mobile parts of the canopy and good condition of their locks;
that the hinge units of aileron, control surfaces and landing flaps are not damaged;
that the openings of drainage, fuel and oil system are clean;
that the inlet openings of the air pressure receiver are clean;
that there are no damages and soiling of the cockpit canopy;
that there is no leakage of oil and fuel from beneath the engine cowling and on the sheathing
of the fuselage and wing;
that there are no damages of the propeller blades that the blades are reliably fastened in the
sleeve, the cylinder to the screw sleeve and that the propeller itself is reliably fastened on the
engine shaft.
4. Check the position of the levers, switches, circuit breakers in the both cockpits and make sure that
there are no foreign articles;
5. Inspect the legs of the landing gear and their arches:
make sure of the compression when the wheel tires are normally charged;
make sure, that there are no damages of the aviation tires, their inversion in respect with
flanges (according to the marks); make sure of the proper locking of the nuts of wheel and air
brake flange fastening;
make sure of the normal charge of the shock absorber, according to the inlet of rods mirror
surfaces;
inspect the shock absorbers, struts, lifting and leg extension cylinders and make sure, that
there is no damage, oil AMG-10 leakage on the strut rods and of working order of the flexible
connections, fixing locks of the legs in the retracted position, fastening units of the shock
absorbing struts, struts and cylinders of the landing gear extension and retraction,
mechanisms, indicating the position of the landing gear;
make sure of the working order of the front leg damper, that there is no oil AMG-10 leakage in
the fastening reliability and that there are no backlashes in the connections of shock
absorbing struts.
6. Carry out the final works: closing of the hatches, locking of the drain cocks, removing the instrument
and on ground equipment.
2. SHEDULED WORKS OF THE AIRPLANE AND POWER PLANT
Works content
POWER PLANT
2.1. Open the cowling, clean the engine; remove dirt from engine
compartment and cowlings
2.2. Inspect the power plant in the scale of beforehand
preparation. Eliminate the defects, revealed during the
inspection.
2.3. Change the filter element of the oil fine cleaning filter, for this
purpose:
− remove the locking and unscrew the cover of the filter;
− remove the filter element;
− mount the new filter element from the new single set;
− change the seal rings into new from the spare set;
− screw and tighten the cover of the filter;
− clean the taken off filter element in the ultrasonic
instrument according to the instruction No.63.
NOTES:
1.For filter element transportation to the place of ultrasonic
cleaning, put the filter element to the bag, made of cotton film
and pack to the carton box.
2. Put the cleaned filter element to the single set of spare parts
for future use.
3. When carrying out scheduled works, fully exclude the
possibility of inside filter soiling.
4. Filter disassembly, except for changing the filter element is
STRICTLY FORBIDDEN.
2.4. Remove the covers of the camshaft boxes and check
condition of the mechanism parts. Check the clearance between
the rollers of the rockers and faces of the valve stems if
necessary state clearances 0,3+0,15-0,1 mm.
Check the tightening of locking nuts, control screws and of all the
rockers.
Check the tension of all the cables of the fastening of valve box
covers, if necessary, regulate the tension of the cables.
NOTE :
1. While carrying out works, pay special attention to the reliability
of control screw rockers fastening.
2. If the clearance between the rollers of the rockers and faces of
the valve stems hadn’t changed after the first 100 hours of
engine operation, the future checks should be carried out after
every 200 operation hours.
To be carried out after each
50 ±5
100 ±10
200±15
hours
hours
hours
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2.5. Remove the filter indicator oil sump and oil filter of the back
cover, for this purpose:
a) switch off the power, disconnect the conductor, pour off the oil
from the oil sump and back cover through the filtering funnel with
the narrow meshed net.(Metal, other particles and traces of coke
on the wall are not tolerated).
unscrew three nuts of the bed and remove filter indicator together
with the cup. Inspect the filter and wall.
In case metal particles are found on the wall of the filter, state the
cause of their occurring in the oil;
b) clean the filter indicator with pure non-ethylated fuel, then
immerse it for one hour in the solution of glycerol and alcohol
(20% glycerine and 80% alcohol) and blow with the dry
compressed air with the pressure of 0,8-1 kg./sq.cm.
Before installing filter-indicator in the sump, connect feeding
conductor to it.
Check the working order of the internal circuit of the filter, for that
close on the mass of the filter net having closed block of the
indicator plates between each other before that.
After checking internal circuit of the filter, remove the strap from
the plate block;
c) put the cup with the filter-indicator to their place, fasten them
with three nuts, connect the conductor.
Check the working order of the external circuit of the filter
indicator, for that remove the rubber cap from the terminal of the
filter and close it on the mass, then the indicating lamp
CHIPPING IN OIL on the instrument panel must light up. The
lamp switches off when the circuit is open.
2.6. Drain oil from the oil tank. Remove, inspect clean and
reinstall filter element of the oil system filter sump, filter in the
back cover of the engine ( screen filter of the oil pump) and filter
supplying oil to the turn regulator. Fill in fresh oil to the oil tank.
NOTE :
Oil change on the dusty airfields should be carried out after every
50 hours of engine operation.
2.7. Remove, inspect, clean, and reinstall the filter element of the
oil system filter sump.
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2.8. Carry out the following works on the carburettor:
a) remove, inspect, wash in pure fuel filter of the carburettor with
the cap removed. Put on the cap after the cleaning and lock it by
the spring lock so that the folded ring would come into the
opening of the cap and filter frame.
NOTICE: In case the new tanks are installed, the inspection of
the fuel pipe lines and cleaning of the carburettor fuel filter should
be carried out after the first starting of the engine.
b) remove, inspect and clean with the pure petrol and blow with
the compressed air with the pressure not more than 0,5 kg/sq.cm
the air filter of the carburettor;
c) measure the initial position of the altitude corrector needle and,
if necessary, regulate according to barographical diagram ;
d) remove the breathing plug of the aneroid surface, check the
cleanness of the openings, clean with the pure fuel and blow with
the compressed air with the pressure not more than 0,5
kg./sq.cm;
e) remove, clean in the pure fuel and blow with the compressed
air the drawing off jet;
NOTICE.
Before installing filters and boxes to their places, check
the state of the sealed rings. The faulty ring should be changed
by a new one from the single set.
f) unscrew the lower outlet plug and poor off the sediment from
the fuel chamber;
NOTICE.
In case the air duct of the carburettor is soiled, it is allowed to
carry out the following works, without taking into account the
operating hours of the engine:
a) draw through the fuel at the pressure of 0,1 kg/sq.cm. After
that blow with the compressed air with the pressure not
more than 0,5 kg./sq.cm. the air system of the carburettor
through the opening of the plug of air pressure changing;
b) remove clean with the fuel and blow with the compressed air
the blowing off jet.
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2.9. Carry out the following works of magneto maintenance:
a) remove the screen with the distributor and the upper cap;
check the screw connection in the breaking mechanism and the
rotation of the little lever on the axis (screw connections must be
reliably tightened, little lever must rotate on the axis without
seizing); clean the contacts of the breaker, rub them with the
suede or with clean white calico, soaked in the pure rectified
alcohol, check, and, if necessary, regulate the clearance between
the contacts within the limits of 0,25 - 0,35 mm, indicate the
regulation of magneto in its passport;
In case the oil underflow or oil films are found on the metal
surfaces of the parts and units which are in the area of
interrupting mechanism, eliminate them with the bleached calico,
moistened in the pure rectified alcohol and wringed out; lubricate
the spring of the interrupter with the thin layer of turbine oil, mark
“A”, not allowing underflows and oil getting on the contacts of the
interrupter;
b) in the distributing mechanism, check the working order of the
contact spring in the jack of the high voltage outlet of the
distributor cover, the state of the angle piece with the spring;
change the faulty parts, from the single set of the spare parts. In
case the soiling on the distributor and on the traveller is found,
clean them with dry clean suede;
c) If necessary, change the terminal in the upper cap and high
voltage outlets, having taken the new parts from the single
magneto set;
d) check the transformer fastening, traveller attachment to the
cam. In case the separation of the thread is found on the screws,
change them into new from the single set of the spare parts;
e) inspect the cam, if it is soiled, rub it till shining with the suede
or clean white calico, moistened a little in the pure rectified
alcohol and with the thin brush, saturated a little in the turbine oil
mark “L” not allowing underflows of the oil or getting it on other
parts, lubricate the operating surface with it. Drop 5-6 drops of
the turbine oil mark “L” by the pipette in the cam lubricator
opening.
f) Unlock and unscrew the plugs of the magneto drive, pour off
the accumulated oil then screw the plugs. the works should be
carried out on the hot engine.
2.10. Check the fastening of the air compressor. Remove, clean
and dry with the dry compressed air with the pressure of 0,4 - 0,5
kg./sq.cm the felt filter of the compressor. Check if the inlet valve
moves freely.
NOTICE.
After cleaning the filter element, install it in the housing at the
same surface at which it was before cleaning and the lock should
be installed with the middle part, bent out to the filter wall.
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2.11. The following works should be carried out at the
maintenance of the spark plugs:
a) remove the spark plugs from the engine according to the
disassembly rules;
b) clean the spark plugs with the pure fuel and dry in the air ;
c) clean the chamber of the spark plugs from the carbon in the
sand streamed apparatus of the DM instrument with the dry
sand, passed through the sieve with 1 600 holes for 1 sq.cm. with
the air pressure of 6-8 kg./sq.cm after cleaning by sand blow the
chamber of the spark plugs with dry air at the pressure of 4-5
kg./sq.cm and clean in the pure fuel;
d) after cleaning the chambers of the spark plugs, carry out the
thorough inspection of the insulator tip. In case the cracks are
found on the insulator tip, the spark plug must be changed;
e) inspect the internal cavity of the spark plug screen and clean
with the clean rag, if it is soiled;
f) regulate the clearance between the electrodes, having
mounted them within the limits of 0,4-0,46 mm on the special
contrivance of the PM instrument.
NOTE:
1.When changing the spark clearance, apply only special feelers.
2. It is forbidden to make a pressure with the feelers on the
central electrode.
3. It is categorically forbidden to use non-standard instrument for
the regulation of spark clearances to avoid pressure on the
central electrode.
g) check the spark plugs for continuity of sparking on the
instruments PM or MCKPA at the pressure of 10 kg/sq.sm when
the clearance between the electrodes is 0,46 mm and the
pressure 11,5 kg/sq.cm when the clearance between the
electrodes is 0, 4 mm ;
h) check the spark plugs on the same instrument for air tightness
at the pressure of 25 kg./sq.cm during 30 sec., it is allowed to
make air percolation to the water, not more than 30 bubbles at
the abstraction horse with the inner diameter of 16 mm and of 50
cm length; when the spark plugs get moistened again, clean their
inside cavity with the dry napkin after that dry spark plugs at the
temperature of 160-180 C during 1 hour and 30 minutes and then
test for sparking.
NOTE:
The taken off spark plugs from the engine may be reinstalled
again for operating full service life if they work on the instrument
without regulating clearances at the pressure not lower than 8
kg./sq.cm.
2.12 After each 300 hours of engine operation check
compression in all cylinders using pressure gauge as follows:
a) screw in the pressure gauge into the spark plug opening of the
cylinder being checked;
b) by turning the propeller smoothly, follow the pressure gauge
readings, at the normal compression the indications of the
pressure gauge should be within the limits of 3,5-5 kg./sq.cm.
NOTE :
Compression should be checked on the warm engine, when the
temperature of the cylinder heads is 40-60°C
2.13. After oil draining, clean the oil manifold and oil tank with the
clean non-ethylated fuel.
ATTENTION:
The work should be carried out when the inlet and exhaust pipes
are disconnected from the engine fuel pump.
2.14. Disconnect the drainage pipes from the fuel tanks,
consumption tank and blow the pipe lines with the compressed
air with the pressure of 1-2 kg/sq.cm after that connect them to
the fuel tanks and to the consumption tank.
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2.15. Inspect the oil and fuel pipe lines in the fuselage and wing,
check the locking of the nuts, connection points in the passages,
flanging of the pipe lines. Pipe lines affected by corrosion and
with the rubbed surface should be changed.
2.16. Remove hatches of the wing fuel tanks and consumption
tank fastening. Make sure, that tank shells are not touching wing
construction, check the tension of the tank fastening tapes, turn
buckles locking and the reliability of pipe lines connection.
Inspect the fuel tanks and the consumption tank, make sure that
there are no cracks and rubbings of the tank shells.
2.17. Check the magnitude of the gill flaps backlashes
in the closed, middle and open positions. Eliminate big
backlashes of the flaps, changing the worn out parts. Lubricate
with a thin layer of lubricant CIATIM -201 the mobile gill
connections.
2.18. Open the hatches covers of the fuselage and inspect drafts,
cables, control cranks and engine control levers. Make sure that
there are no mechanical damages (deformations, cracks) worn
out cables; make sure of the reliability of draft connections with
the levers and control cranks. Clean, inspect and lubricate with
the lubricant CIATIM –201 all joint couplings of the engine control
cables and open bearings.
NOTE:
Check the tightening of the nuts securing the brackets, mounted
on R-2 and on the flange of M-14P engine reduction gear with a
calibrated wrench. Torque=1,5+0,3 kg·m
AIRFRAME
2.19. Inspect the fuselage of the airplane, its power plant,
covering, fillets, attachment points, rivet seams,
point-welded joints and bolted connections.
Make sure, that there are no cracks, deep scratches,
deformations, corrosion, weakening of the rivets and bolted
connections, faults of the lacquer-paint covering.
For inspecting tail part of the fuselage, remove the seat of the
pilot from the second cockpit and use the hatch in the area of
frame 17 on the port side.
2.20. Inspect the tail surfaces:
a) make sure, that there are no deformations, cracks of fin and
horizontal tail skin, weakening of the rivets and bolts of covering
fastening to the frames; Make sure of the working order of
bearings that there is no wear out of true in the sleeves of the
hinge units of elevator and rudder that there are no deformations,
cracks, corrosion of the control surfaces hinge arms, weakening
of the bolted and riveted arm fastenings to the fin and horizontal
tail;
b) make sure, that there are no traces of deformation of the
elevator and rudder frames, weakening of the tension and breaks
of their fabric covering, shallowness and damage of lacquer paint
covering of the covering. Make sure of the working order of the
hinge arms, control levers and their fastening to the control
surfaces frame, that the drainage openings are clean;
c) inspect the trim tab on the elevator and dip-rod loop of its
fastening, check the magnitude of the trim tab backlash.
2.21. Remove the fillets of the tail support, check the joint units of
fin and horizontal tail to the stabilizer, make sure, that there are
no cracks, corrosion of the working order of units fastening to the
fuselage, fin and horizontal tail, that there are no weakening of
the nuts, joint bolts and of the working order of their locking.
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2.22. Inspect the wing, ailerons and landing flaps:
a) make sure that there are no cracks, scratches, deformations,
weakening of the riveted and bolted connections of the metal
covering, breaks and loosing strength of the fabric covering and
its fastening, damage of the lacquer covering; make sure of the
cleanness of the drainage openings in the lower fabric cover of
ailerons; make sure of the working order of hatches covers and
locks of their fastening;
b) Inspect hinge units of the ailerons make sure of their working
order and that there are no intolerable backlashes in the
bearings, weakening of the fastening, deformations and cracks of
the arms. Check condition of the arm fastening to the wing and
ailerons.
Make sure of the working order and reliability of the control levers
fastening to the ailerons;
c) Inspect the fastening of the flaps, make sure of operability, that
there are no intolerable backlashes in the joint coupling. Check
condition of flap brackets. Lubricate the joint coupling with the
lubricant CIATIM-201.
d) remove the wing fillets and inspect attachment points of the
wing panel to the fuselage, make sure, that there are no cracks,
deformations, failures of locking, weakening of the rivet tightening
of the joint bolts and backlashes in the connections of wing
panels to the fuselage.
Make sure of the drainage pipes of the battery container
cleanness and of the working order of the hatches and their
locks.
2.23. Carry out the following works on the seats of the front and
back cockpits:
a) check the attachment points of the seat fastening to the
fuselage. Lubricate the mobile joins of the seat according to the
lubrication map:
b) inspect the safety harness, check the fastening and the
condition of the belts, lock functioning. Check the amount of
force, needed for opening the lock of the lashing system (the
force should be 6-10 kg).
2.24. Carry out the following works on the cockpit ventilation and
heating:
a) inspect the air ducts and units of the system: make sure that
there are no damage, traces of air leakage, that units and pipe
lines are fastened reliably, check the tightening of the clamps;
b) check the travel smoothness of the control rod of cockpit
heating / ventilation selector; the possibility of the firm locking of
the butterfly type valve in the three positions (open, half-open
and closed) and the possibility of free rotation of the turn nozzles
on the ends of the air ducts;
c) remove and check the heat resistant branch pipe;
d) when the engine is operating, check the air intake for heating
(the valve is open) and ventilation (the valve is closed) of the
cockpits.
2.25. Inspect the cockpit canopy of the airplane. Make sure of its
integrity, cleanness, transparency and reliability of glass
fastening of the frames and edging of the canopy, of the working
order of the canopy mobile parts locks, shock absorbers, cables
and their fastening to the mobile parts and fuselage, of the
operable condition and attachment reliability of the back view
mirror.
Clean the drainage pipes directing rails of the mobile parts of the
canopy.
Carry out works according to the lubrication maps.
Check the moving easiness and snug fit of the mobile parts of the
canopy against not mobile ones.
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AIRPLANE CONTROL
2.26. Inspect the airplane control handles in the cockpits, pedals
and control wheels of the elevator trim tab control.
While fully deflecting control handle, pedals and trim tab control
wheels in the both cockpits, check the deflection
angles and the neutral position of the ailerons, rudder, elevator
and trim tab; make sure of the travel smoothness of the controls,
that the efforts are not needed, that there are no seizing and
crunching in the bearings. Pay special attention to the condition
of the joint in the elevator draft.
ATTENTION:
If there will be noted increased friction force or seizing in the
airplane control connector, it is necessary to find the reason
immediately and eliminate it.
2.27. Make sure of the working order of the elevator trim tab
position indicator and the correspondence of their readings to the
position of the trim tab.
2.28. Open the hatches covers of the fuselage, wing, take off the
seat of the back cockpit and the floor covers which can be taken
off in the places where the airplane control connector is. Inspect
the drafts, rods, cables, direction indicators from the airplane
control handles, parts airplane control steering wheels and air
cylinder of the flap control till the aileron levers, landing flaps,
control surfaces and elevator trim tab.
Make sure, that there are no corrosion, mechanical damages
(deformations, cracks), weakening of the bearing termination,
worn out cables; make sure of the reliability of draft connection
with the control cranks and levers, integrity of the locking and
bonding, that the clearances are as required by technical
conditions between the mobile and not mobile and control parts
of the interconnected mobile, and also construction elements.
Check by the strain-measuring device the cable tightening (see
drawings 2, 3, 4)
Clean, inspect and lubricate with the lubricant CIATIM –201 all
the joint couplings of the control connectors, which have open
bearings.
2.29. Inspect the shafts of the airplane manual control, make
sure, that there are no mechanical damages of the housings,
pipes and shaft supports. Check all joint couplings of the shaft.
Change the lubricant in the rubbing parts.
2.30. Inspect the cylinder of the landing flaps control and the arm
of its fastening. Make sure that there are no damage in the
cylinder tight seal and pipe line connections of the pneumatic
system, make sure of the bolt connections and locking reliability.
2.31. Check the time for extension and retraction of the landing
flaps, it should not exceed 5 seconds. Pour 5-10 sq.cm of the
lubricant 132-25 GOST 10957-74 to the working cavity of the
cylinder flaps through the connection point, after that carry out
the extension and retraction of the landing flaps.
2.32. Check the radial backlash of the flap and support control
rods. The backlash should be within the limits of
0,01-0,3 mm.
LANDING GEAR
2.33. Inspect wheels and tire of the front and main legs of the
landing gear. Make sure, that there are no traces of the
overheating of the wheels that drums and their flanges work well;
that the wheels are reliably fastened on the semi-axles of the
shock absorbing fixed members, make sure of the connection of
flexible horses of the pneumatic system with wheel brake
equipment of the main legs wheels, that there are no cuts,
punctures, not tolerable wear, local swelling, displacement of tire
covers in respect to the wheel drums (according to the marks).
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2.45. Take of the tires of the landing gear wheels, take off the
inner tubes from the tire cover, inspect and make sure that there
are no folding, rubbing, cracks and defects of charging tube
mounting. Check if there are no defects of the inner surface of
the tire covers. Eliminate old talc from the tire covers and from
the surface of the tire cover with talc powder and mount the
aviation tire on the wheel drum.
2.46. Carry out control extension and retraction of the landing
gear from the main and from the emergency pneumatic systems
at the normal air pressure in the systems and check:
a) operation of the locks of extended and retracted positions;
b) operation of mechanical indicators and the. indication of
landing gear position;
c) time for landing gear retraction should not exceed 8 seconds
and inequality of the legs extension time should not exceed 1
min.
Note :
Operations No 34-47 should be carried out when the airplane is
lifted onto the ground jacks
2.47. Remove the brake posts and folding struts of the landing
gear front and main legs. Disassemble folding struts and spline
joins. Wash the parts of landing gear hinge units and joint
couplings with the dehydrated kerosene. Clean the lubrication
passages with soft wire. Inspect all rubbing surfaces. Replace the
faulty parts.
Lubricate all the rubbing surfaces with the lubricant CIATIM -201.
Assemble the folding struts and spline-joins, install shock
absorbing posts into their places. Fill lubricant to all press
lubricators according to the lubrication map. Carry out works,
indicated in point 2.46.
Note:
Aircraft lifting and lowering down should be carried with unbraked
main leg wheels.
AIR SYSTEM
2.48. Inspect the units and pipe lines of the air system. Make
sure that units and pipe line are fastened reliably that the
connections arc- air tight, that units do not touch each other and
units of the construction.
2.49. Pour of condensate from the main and emergency
cylinders.
2.50. Remove the direct flow filter of the air system, take apart,
check condition of the parts, wash with the petrol B-70 and dry
the washer, collect the filter, blow with dry compressed air and
reinstall.
2.51. Blow with the compressed air with the pressure of 50 kg/sq.
cm. the pipe lines of the air system having disconnected them
from the consumers and units.
2.52. Check the air tightness of the main and emergency air
system.
2.53. Check the operation of the brakes from the main and
emergency system;
a) the air pressure in the brakes should be 8+1 kg/sq. cm.
b) The time for pulling the brakes on and off should not be more
than 1,5 seconds.
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2.54. Check the regulation of pressure relief valve and the
automatic pressure machine of air system.
NOTE: Referring point 2.51. For blowing pipe lines of the air
system it is allowed to use dry (with dew point not higher than 45C) compressed air from the ground bottle.
The compressed air should be sent to the pipe lines of the
system through the stand, engaging filter with the filtering
fineness not more 5 micro metres, moisture separator and
reducer. In the blowing process of the pipe line parts, control the
cleanness of the internal cavities of the passages with the help of
cotton napkin. In case the napkin is soiled, proceed on blowing till
the final dirt elimination.
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2.34. Inspect the fixed members of the shock absorbers and the
units of their fastening to the airframe. With the help of the
magnifier make sure that there are no cracks on the welded
seams and in the attachment points. Inspect the joint slots and all
mobile and not mobile joint couplings of the shock absorbing
struts, make sure of their working order and reliability of locking
that there are no work outs in the mobile connections.
Check the fastening of the baffle of the front leg, make sure that
there is no oil AMG-10 leakage, backlashes and other defects in
the connections.
Check condition of the working surfaces, flaps of the shock
absorbing struts and that there is no oil AMG-10 leakage.
2.35. Check the pressure of nitrogen by the manometer in the
shock absorbing strut wells. The pressure should be equal to the
pressure indicated on the placard on the shock absorbers.
2.36. Check the level of the oil AMG-10 in the shock absorbers of
the landing gear.
2.37. Inspect the landing gear jacks and their attachment points.
Make sure that there are no damage, that there is tight seal of
the cylinders and connections with the hoses of the pneumatic
system of the reliability of bolt connections and locking.
2.38. Take apart, clean, inspect, lubricate with the lubricant
CIATIM-201 and install to their places locks of the retracted
position.
2.39. Pack lubricant CIATIM-201 in the lubricator of the landing
gear.
2.40. Pour 15-20 cm3. of lubricant 132-25 GOST 10957-74 in the
working cavities of landing gear jacks.
2.41. Pour 2-3 cubic cm. of lubricant 132-25 into the working and
emergency cavities of every cylinder of leg retracted position
locks opening. After carrying out works according to 2.40, 2.41,
carry out the extension and retraction of the landing gear. Make
sure of the air-tightness of the cylinder connections with the
passages of the air system.
2.42. Remove wheels of the landing gear and carry out the
following works:
a) eliminate the old lubricant from the wheel bearings and wash
with dehydrated kerosene;
b) clean the drum of the wheels from soiling, blow the brake
equipment with the compressed air, inspect the drums, parts of
the wheels and brake equipment; make sure that there are no
traces of overheating, cracks wears out deformations, not
tolerable wears out of the brake blocks at the inner tubes;
c) inspect the semi-axles of the wheels;
d) fill the wheel bearings with a new lubricant NK-50 GOST 537367;
Note :
1. Lubricant NK-50 should be used only for filling in the space
between the rollers and iron rings.
2. The wheel should be replaced together with the bearings.
2.43. Check the presence of the clearances between the
construction of wing fuselage and landing gear elements.
Measure longitudinal and perpendicular backlashes and the
backlash of landing gear turn according to the wheel axis faces.
The longitudinal and perpendicular backlash should be not more
than 2 mm, the total backlash of leg turn (in the hinge axis and
spline-joint) not more than 3mm.
2.44. Check the size of the clearance with probing rod between
the support of the folding struts middle joins of the landing gear
front and main legs. The clearance should be 0,10, 2 mm. The
inspection should be carried out with the extended landing gear,
in the “neutral” position.
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3. ENGINE REPLACEMENT PROCEDURE
1.The oil filter should be taken off from the engine, which is being taken off after the end of the service
life or before it. The oil filter should be inspected and made sure that there are no metal chips, then it
should be reinstalled.
NOTE: In case the metal chips are found on the oil filter of the taken off engine, the oil cooler and oil
tank should be changed and tubing, hoses and units of the oil system should be carefully inspected.
The taken off oil tank and oil cooler should be sent to repairing department for cleaning in the
stationary equipment.
2. The inside preservation of the taken off engine in accordance with Maintenance Instructions of the
engine M-14P should be carried out. Pour out the oil from the oil tank and system.
3. Take off the propeller, from the contamination, inspect the blades, sleeve and cylinder unit; make
sure that there are no damages of the parts and screw.
4. Disassemble and take off the engine. Clean the compartment: fire wall, drafts, tubing.
5. Take off the oil tank, filter element of the oil filter sump and oil cooler, clean them inspect and install
them to their places.
6. Clean and inspect the engine bed, make sure that there are no damages, cracks in the welding
seams and units, inspect the engine studs, joins, bolts, make sure that there are no wears out of true,
drawing and cutting damages.
7. Inspect fuselage arm fastenings of the engine bed and cowling, make sure that there are no wears,
cracks and other defects.
8. Inspect the opposite wall, the state of unit fastening to it, sealing gaskets, dislodging control drafts
by the engine, tubing and electric lines.
9. Inspect control drafts and then tips, fuel, oil and air hoses and tubing; change the faulted ones.
10. Inspect the cowling of the engine make sure that there are no rubbings, cracks and rigidity in the
sheathing, that swivels are in working order and that there is no wear out of true, preventing further
operation of the mobile joints of the gills.
11. According to the guidance of maintenance instructions for the engine M-14P and airplane YAK-52,
install the new engine in the airplane and carry out mounting of the unit tubing, gills, propeller covers
of the cowling.
Carry out regulation works, fill up the airplane with fuel and oil, make sure of the leak - leak-proofness
of the fuel and oil system and in the leak- leak-proofness of the oil dilution valve.
De-preserve and run the newly installed engine.
12. After operating, take off the engine, check it, clean and install back all the fuel and oil filters.
13. After changing the engine, carry out the test flight of the airplane in the period of 30 min. in
accordance with the instructions of the crew.
14. After the test flight, the following works, indicated in chapter 4 should be carried out in the first five
flight fours of the airplane with the newly installed engine.
NOTE: In case the engine is changed, carry out works for electric and instrument equipment, indicated
in chapter 8.
4. MAINTENANCE AFTER THE FIRST TEST FLIGHT AND AFTER THE FIRST
FIVE FLIGHT HOURS WITH THE NEWLY INSTALLED ENGINE
1. Carry out all the works, foreseen by the first beforehand inspection.
2. Drain the oil from the engine, oil tank and oil cooler, take off, inspect and clean the screen filter at
the end cover (screen filter of the oil pump) filter-indicator and filter sump of the oil system and filter of
the turn indicator. Fill in fresh oil.
3. Change the filter element, filter of the fine fuel cleaning. After installing new filter element, change
the sealing rings.
CAUTION: When changing the filter element, strange things occurring in the inside of the filter should
be excluded
4. Inspect and clean fuel filter of the carburettor in the pure fuel with the cap, taken off.
NOTE: Oil and filter element of the fuel fine cleaning filter should be changed only after the first five
hours of the engine operation.
5. Carry out the cleaning of the taken off filter element in the ultrasound equipment in accordance with
instruction No 63. The cleaned filter element should be put into the spare set of the engine.
5. AIRPLANE STORAGE MAINTENANCE
1. In case the airplane is not allowed to fly for more than 7 days, because of any reasons, it is
necessary to carry out its preservation for that required period in accordance with the requirements for
the airplane and engine technical operation.
2. If the airplane is not flying and if it is not
preserved, it is necessary to carry out the following works
after every 7 days:
• clean the dust and mud from the airplane clean the
drainage openings at the lower fabric sheathings of the control
surfaces and ailerons;
• carry out works of departure check out procedure maintenance .
NOTE: Places, affected by corrosion should be scrapped bright by the fine glass-paper, sanded with
the paste roil , cleaned with the pure petrol B-70 and lubricated with the technical petroleum jelly.
• run-up the engine in all modes according to the schedule of engine run-up;
• eliminate the defects, found out during the pre-flight maintenance and engine run-up;
• change the lubricant for the working surfaces of the landing gear fixed members of the rod and
jacks.
• In summer time take off the covers, open the covers of the airframe hatches, inspect the airplane
and dry the covers.
3. After every 30 ± 5 days of not operating of not preserved airplane, the following works should be
carried on:
• carry out works, foreseen after not operating for 7 days;
• switch on the radio equipment for 10-15 minutes for drying it;
• put the airplane on the lifts and carry out control extension
and retraction of the landing gear;
• after airplane preparation for flight after not operating for 15 days and more, carry out works,
foreseen for the pre-flight maintenance including the checking of the landing gear extension and
retraction system operation and the pressure in the wheel brakes.
4. After every 3 months and ±7 days of not operating of not preserved airplane the following works
should be carried out:
• lubricate systems and units after every 200 flight hours according to the lubrication drawings.
• carry out works, foreseen after every 30±5 days of non
operation.
• carry out the test flight of the airplane for 30 min. according to the instruction for the crew.
NOTE: Airplane and engine preservation for long storage, their re-activation and preservation care
should be inspected to accord with the requirements of the subpart 2.7 “Temporal Instruction for
maintenance. Training sporting airplane YAK - 52” and to the Maintenance instruction for the aviation
engine M-14P”.
MAIN LANDING GEAR LEG
Table, of the lubrication points
Contents Of The
Works
Rub with clean cotton
cloth
Terms Of Carrying Out Works At Every
50±5h.
100±10h.
200±15h.
5,10
5,10
5,10
Wash with kerosene
If necessary
Lubrication
Means
-
Lubricate with the lubricant
CIATIM-201
5,10
5,10
5,10
Brush
Spray lubricantCIATIM-201
3,6,7,9,10
3,6,7,9,10
3,6,7,9,10
Syringe
1-5 -10 cubic cm
2-1-2 cubic cm
4-15-20 cubic cm
Spray lubricant 132-25
Syringe
Clean with pure fuel
-
8
8
Charge the labyrinths
between the rollers and
roller cages with the
lubricant HK-50
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8
8
Brush
Naming Of The Points
1- cylinder lock opening operating cavity of the retracted position of the main landing gear leg; 2- cylinder lock
opening emergency cavity of the retracted position of the main landing gear leg; 3- joint coupling of the liftcylinder; 4- internal cavities of the jack; 5- joint coupling of the. landing gear leg position mechanical indicator;
6- hinge axis of the landing gear main leg; 7- axis of the spline- joint; 8- wheel bearings; 9- rotation axis of the
folding strut; 10-hook and catching axis of the rubbing surfaces of the retracted position lock of the front landing
gear leg;
APPENDIX
Lubrication charts
FRONT LEG OF THE LANDING GEAR
Table of the lubrication points
Contents Of The
Works
Rub with clean cotton
cloth
Terms Of Carrying Out Works At Every
50±5h.
100±10h.
200±15h.
4.9
4.9
4.9
Wash with kerosene
Lubricate with the
lubricant CIATIM-201
Spray lubricant
CIATIM-201
If necessary
Lubrication
Means
-
4.9
4.9
4.9
brush
2,3,5,6,8,9
2,3,5,6,8,9
2,3,5,6,8,9
syringe
1-15 –20 cubic cm
10-5-10 cubic cm
11-1-2 cubic cm.
Spray lubricant 132-25
syringe
Clean with pure fuel
-
7
7
Charge the labyrinths
between the rollers and
roller cages with the
lubricant HK-50
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7
7
brush
Point Description
1- internal cavities of the jack;
2- joint couplings of the jack;
3- hinge bolts of the landing gear front le
4- joint couplings of the damper;
5- rim of the shock absorbing cup of
front strut;
6- axis of the spline- joint;
7- wheel bearings;
8- rotation axis of the folding strut;
9- hook and catching axis of the rubbing surfaces of the retracted position lock of the front landing gear leg;
10- cylinder lock opening operating cavity of the retracted position of the front landing gear leg;
11- cylinder lock opening emergency cavity of the retracted position of the front landing gear leg;
ELEVATOR, AILERONS AND ELEVATOR TRIM TAB CONTROL
Table of lubrication points
Terms Of Carrying Out Works At
Every
Contents Of The Works
Rub with clean cotton
cloth
50±5h.
50±5h.
50±5h.
1-15
1-15
1-15
Wash with kerosene
Lubricate with the
lubricant CIATIM-201
lubricate with
oil MC-20 or MK-22
Lubrication
Means
if necessary
-
1-6-8-15
1-6-8-15
1-6-815
Brush
7
7
7
Syringe
Point Description
1- ball bearings in the control handle pivots;
2- ball bearings in the control wheels;
3- steering connection, connecting control handle and sector ;
4- cable laying in the area of touching with rollers and sectors;
5- outward pressure sleeves of the guide rollers;
6- joint couplings on the lever of the TRIM TAB;
7- dip rod loop of elevator TRIM TAB hinge;
8- TRIM TAB control mechanism;
9- ball bearings of the sectors;
10- ball bearings of the aileron control levers;
11- ball bearings of aileron hinge units;
12- ball bearings of levers connection with control drafts;
13- control shaft support bearings;
14- joint couplings of mechanism utilization with levers and units;
15- rudder and elevator turn sleeves.
RUDDER AND LANDING FLAPS CONTROL
Table of the lubrication points
Contents Of The Works
Rub with clean cotton
cloth
Terms of carrying
out works at every
50±5h.
100±10h.
200±15h.
1,2,3
4,5,6
8.10
1,2,3
4,5,6
8.10
1,2,3
4,5,6
8.10
if necessary
Wash with kerosene
Lubricate with the
lubricant CIATIM-201
Spray lubricant 132-25
5-10 cubic cm.
lubricate with 7
oil MC-20 or MK-22
Lubrication
means
-
1,2,3
4,5,6
8.10
1,2,3
4,5,6
8,10
1,2,3
4,5,6,
8,10
brush
9
9
9
syringe
7
7
7
brush
Point Description
1- ball bearings in the pedal adjusting plate;
2- joint couplings of the drafts, rods and turn buckles;
3- ball bearing of the lower hinge unit Pn ;
4- bearings in the rudder arm;
5- cable laying and rods in the area of touching rollers support and sectors;
6- ball bearings of rod support;
7- dip rod loops of landing flaps;
8- bearings of drafts and rods;
9- internal working cavities of the cylinder flaps;
10- joint couplings of the adjustment of pedals.
ENGINE CONTROL
Terms of carrying
out works at every
Contents of the works
Rub with clean cotton
cloth
50±5h.
100±10h.
200±15h.
1,2,3,4,5
1,2,3,4,5
1,2,3,4,5
Wash with kerosene
Lubricate with the
lubricant CIATIM-201
if necessary
1,2,3,4,5
Point Description
1- ball bearings of gill ring;
2- joint couplings of gill flaps and of mixture heating;
3- cable ends of flexible horses of engine control;
4- all joint couplings of levers and drafts;
5- joint couplings of oil cooler exhaust valve flap;
1,2,3,4,5
Lubrication
means
-
1,2,3,4,5
brush
PILOT’S SEAT
Table of lubrication points
Terms of carrying
out works at every
Contents of the works
Rub with clean cotton
cloth
50±5h.
100±10h.
200±15h.
-
-
1,2
Wash with kerosene
Lubricate with the
lubricant CIATIM-201
if necessary
-
Point Description
1- joint couplings of seat hinge units;
2- joint couplings of spinnings and safety belts lock
-
Lubrication
means
-
1,2
brush
CANOPY
Table of lubrication points
Contents of the works
Rub with clean cotton
cloth
Wash with kerosene
Lubricate with the
lubricant CIATIM-201
Spray lubricant
CIATIM-201
Terms of carrying
out works at every
50±5h. 100±10h. 200±15h.
7,8
-
1,2,3
4,5,6
if necessary
Lubrication
means
-
8
-
1,2,3
4,5,6
brush
7
-
-
syringe
Point Description
1- ball bearings of the mobile canopy parts;
2- joint couplings of the levers;
3- canopy lock;
4- break down sleeves of the rollers;
5,6- directing rails of the mobile canopy parts;
7- pipe;
8- ball with bolt.
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