Vedeneyev M-14P User manual

TITLE
TABLE OF CONTENTS
INTRODUCTION
ENGINE M-14P
DESCRIPTION AND OPERATION
Description
Operation
Appendices:
Fuel and Lubricants
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
REMOVAL/INSTALLATION
List of Task Cards
Operation Procedure
STORAGE INSTRUCTIONS
ENGINE FRONT
DESCRIPTION AND OPERATION
General
Construction
CRANK MECHANISM ASSEMBLY
DESCRIPTION AND OPERATION
General
Construction
CYLINDER ASSEMBLY
DESCRIPTION AND OPERATION
General
Construction
TROUBLE SHOOTING
SUPERCHARGING
DESCRIPTION AND OPERATION
General
Construction
LUBRICATION
DESCRIPTION AND OPERATION
General
Description
Lubrication System Units
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
ACCESSORY DRIVES
DESCRIPTION AND OPERATION
General
Description
TROUBLE SHOOTING
FUEL SYSTEM
DESCRIPTION AND OPERATION
General

Description
FUEL PUMP 702ML
DESCRIPTION AND OPERATION
General
Description
Operation
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
FILTER 8D2.966.064
DESCRIPTION AND OPERATION
General
Description
Operation
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
CARBURETOR AK-14P
DESCRIPTION AND OPERATION
General
Description
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
IGNITION SYSTEM
DESCRIPTION AND OPERATION
General
Description
MAGNETO M-9F
DESCRIPTION AND OPERATION
General
Description
TROUBLE SHUOTIMG
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
STORAGE INSTRUCTIONS
SHIPMENT
SPARK DISTRIBUTION
DESCRIPTION AND OPERATION
General
IGNITION HARNESS
DESCRIPTION AND OPERATION
SPARK PLUG SD-49SMM
DESCRIPTION AND OPERATION
General
Description
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure

STARTING SYSTEM
DESCRIPTION AND OPERATION
General
AirborneAir Compressor AK-50A
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
SPINNING SYSTEM
DESCRIPTION AND OPERATION
General
Construction
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
ELECTRICAL POWER SYSTEM
DC ELECTRICAL POWER SYSTEM
GENERATOR GSR-3000M, SERIES 4
DESCRIPTION AND OPERATION
General
Description
Operation
TROUBLE SHOOTING
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
CONTROL
CONSTANT SPEED GOVERNOR R-2, SERIES 04
DESCRIPTION AND OPERATION
General
Description
Operation
MAINTENANCE PRACTICES
List of Task Cards
Operation Procedure
STORAGE INSTRUCTIONS
Storage
Preservation
SHIPMENT

17
INTRODUCTION
The M-14P engine Maintenance Manual is a one-book publication comprising description and operating
instructions, including data on the construction, purpose, arrangement and. operating principle of engine systems
(Ref. 073.00.00, 074.00.00, 080.00.00), as well as all the information necessary for proper operation, storage and
maintenance of the engine. The present Manual includes Maintenance Manuals of some accessories installed on
the engine (Ref. 024.30.01, 061.20.01).
The text uses the following abbreviations and symbols of technical values:
BDC (HMT) - bottom dead center.
TDC (SKIT) - top dead center.
POL (K!M) - petrol, oil, lubricants.
PP (BMT) - powerplant.
Pc- excessive pressure (or rarefaction) behind engine blower, mm Hg.
E - compression ratio, which is ratio of cylinder total volume to volume of combustion
chamber.
Ner- reduced engine power, i.e. power reduced to standard atmospheric conditions
(Pa= 760 mm Hg, t = 20 °C).
Pa- atmospheric pressure, mm Hg.
"Front view" implies that the observer is in front of the airscrew shaft of the engine assembly.
"Rear view" implies that the observer is at the rear cover of the engine.
"RH rotation" implies that the direction of rotation of the part coincides with that of clock hands for the
observer staying behind the engine.
"LH rotation" implies that the direction of rotation is opposite to that of clock hands for the observer staying
behind the engine.
"Left" and "right" relate to the observer staying in the pilot's cabin behind the engine.

18
ENGINE M-14P - DESCRIPTION AND OPERATION
1. DESCRIPTION
1.1. GENERAL
The M-14P airplane engine (Ref., Figs 1 and 2) is a piston, fourstroke, air-cooled gasoline, nine-cylinder
carburetor, single-row radial engine.
The M-14P engine is not of a high-altitude type, but to improve performance it is provided with one-speed
centrifugal blower.
The engine is cooled by air fed through the intake in the front part of the airplane cowling. Uniform cooling
of the cylinders is ensured by deflectors located on each cylinder. Main assemblies and parts of the engine are
lubricated by oil under pressure.
The engine is started by compressed air. Air is distributed among the cylinders according to the required
sequence by the compressed air distributor.
Puel-air mixture is ignited in the cylinders by high-tension electric spark generated in two magnetos
operating in parallel. Two spark plugs and a starting valve are installed in each cylinder.
The engine is secured to the engine frame ring by eight bolts extending through the holes of the mixture
collector bosses.
The M-14P engine carries the following accessories:
The V530TA-D35 variable-pitch airscrew - on the airscrew shaft
The R-2, series 04, speed governor - on the gearbox housing
The AK-14P carburetor - on the mixture collector
Two M-9P magnetos, generator GSR-3000M,
series 4 (Ref. 024.30.01), compressed air
distributor, compressor AK-50A, series 3,
DTE-1 tachometer generator, MM-14A oil
pump, 702ML fuel pump - on the crankcase rear cover
The engine gearbox decreases the crankshaft speed relative to the speed of rotation of the airscrew shaft.

19
Engine M-14P. Front View Figure 1

20
Engine M-14P. Rear View Figure 2

21
1.2. SPECIFICATIONS
1.2.1. Engine
Designation................................................................................M-14P
Cooling system ..........................................................................Air-type
Engine starting system ..............................................................Air-type
Engine continuous operation time:
At take-off rating ..............................……..…………..................Up to 5 min
At maximum permissible speed, of rotation .......... ...................Up to 1 min
At other ratings .................................. ......................................Not limited
Iverted engine operation:
Ratings ........................................... ..........................................Nominal
Continuous operation time ......................... ..............................Up to 2 min
Total time within service life ...................................................... Up to 18 %
Maximum permissible speed of rotation ............... ...................2950 (101 %) r/min
Acceleration (pickup) from 760 r/min (idle) to take-off
rating on stationary airplane .............. .......................................Up to 3 s
Maximum permissible crankshaft speed drop when
changing over to one-magneto operation at nominal
rating II and cruise rating I (low-pitch airscrew) ........................ 85 r/min (3 %)
Number and arrangement of cylinders ..................................... 9, radial, single-row
Cylinder numbering .................................. ................................Countercio ckwise if viewed from
rear cover side, top cylinder is Ho. 1
Cylinder bore .............................................................................105 mm
Piston stroke:
Cylinder No. 4 ...........................................................................130 mm
Cylinders Nos 3 and 5 ...............................................................130.15 mm
Cylinders Nos 2 and 6 ............................. .................................130.23 mm
Cylinders Nos 8 and 9 ............................. .................................130.39 mm
Cylinders Nos 1 and 7 ............................. .................................131.25 mm
Total displacement .................................. .................................10.161 1
Compression ratio ................................... .................................6.3±0.1
Direction of rotation of crankshaft and airscrew shaft ...............LH
Engine dry mass ..................................... 214 kg+2%
NOTE: Engine dry mass does not include mass of the generator, compressor, fine
filter with pipelines, engine frame ring, exhaust manifold parts, tachometer generator.
Engine overall dimensions:
Diameter (over valve mechanism case covers) ....... ...............(985±3) mm
length ............................................ ...........................................(924±3) mm

22
1.2.2. Gearbox
Type ................................................ .........................................six-sateliite, planetary,
single-stage
Transmission ratio .................................. ..................................0. 658
1.2.3. Airscrew
Designation ......................................... .....................................V530TA-D35
Type ................................................ .........................................Variable-pitch, push-type
1.2.4. Blower
Type ................................................ .........................................Centrifugal, single-stage,
single-speed, mechanical drive
Drive transmission ratio ............................ ................................8.16
1.2.5. Carburetor
Designation ......................................... .....................................AK-14P
Type ................................................ .........................................Floatless
Humber per engine ................................... ...............................1
Carburetor fuel inlet pressure:
At operating ratings .............................. ....................................(0.2 to 0.5) kgf/cm
At minimum speed of rotation ...................... ............................Hot less than 0.15 kgf/cm
Air temperature at carburetor inlet ................. ..........................10 to 45 °C
Fuel grade and octane rating ........................ ...........................Gasoline B91/115 GOST 1012-72,
octane rating at least 91 (Ref. Appendix 1)
NOTE: Foreign-made fuel and oil grades allowed for use witn the engine and their physical and chemical
properties are given in Appendix 1.
1.2.6. Fuel Pump
Designation ......................................... .....................................70ML
Type ................................................ .........................................Rotary-type
Number per engine ................................... ...............................1
Drive transmission ratio ............................ ...............................1.125
Drive direction of rotation ......................... ................................LH
1.2.7. Fine Fuel Filter
Designation ......................................... .....................................8D2.966.064
Type ................................................ .........................................Sump-type

23
Number per engine .................................. ................................ 1
Working fluid ...................................... ...................................... Gasoline B91/115 GOST 1012-72
g Working pressure ................................... .............................. 0.2 to 0.5 kgf/cm
Maximum throughput ................................................................ 5 1/min
Filtering fineness ................................. .................................... 36 to 40//m
1.2.8. Oil Pump
Designation ..................…................... ..................................... W-14A
Type ............................................... .......................................... Gear-type, with delivery and
scavenging sections
Number per engine .................................. ................................ 1
Drive transmission ratio ........................... ................................ 1.125
Drive direction of ro tation ........................ ................................ LH
Main line oil pressure (measured through special connection on oil pump):
Operating ratings ................................ ..................................... 4 to 6 kgf/cm
Minimum speed of rotation ........................ .............................. Hot less than 1 kgf/cm
Engine inlet oil temperature:
Recommended ......................................................................... 50 to 65 °C
Minimum permissible .............................. ................................. 40 °C
Maximum at prolonged operation ................... ......................... Up to 75 °G
Maximum permissible for up to 15 min of
continuous operation ............................. .................................. Up to 85 °C
Maximum permissible engine outlet oil
temperature ...................................... ....................................... Up to 125 °C
Maximum temperature difference between engine
inlet and outlet oil ............................. ........................................ 50 °C
Cylinder head temperature measured by thermocouples installed under rear spark plugs of hottest
and coldest cylinders:
Recommended ...................................... .................................. 140 to 190 °C
Minimum permissible for normal operation of
engine ........................................... ........................................... 120 °C
Minimum at prolonged operation ................... .......................... 140 °C
Maximum at prolonged operation ................... ......................... 220 °C
Maximum permissible at take-off and climbing for
up to 15 min and not more than 5 % of service
life ............................................. ............................................... 240 °C
Oil flow rate through engine at inlet oil temperature
of 50 to 65 °C at nominal rating I ............ ................................. Up to 13.5 kg/min
Heat transfer to oil at nominal rating I ........... .......................... 225 kcal/min
Summer and winter oil grades ....................... .......................... MS-20 GOST 21743-76

24
NOTE: Foreign fuel and oil grades allowed for use with engine and their physical and chemical
properties are given in Appendix 1.
1.2.9. Magneto
Designation . ..................................... .......................................M-9F
Type .............................................. ...........................................Pour-spark, shielded
Number per engine ...................................................................2
Drive transmission ratio .......................... .................................1.125
Drive direction of rotation ....................... ..................................LH
Ignition cable system and type .................... .............................Shielded harness PVS-5
1.2.10. Spark Plug
Designation ....................................... .......................................SD-49SMM
Type .............................................. ...........................................Ceramic-insulator
Number per cylinder ............................... .................................2
Firing order ...................................... ........................................1-3-5-7-9-2-4-6-8
1.2.11. Compressed Air Distributor
Type .............................................. ...........................................Slide-valve
Drive transmission ratio .......................... .................................0.5
Drive direction of rotation ....................... ..................................LH
Compressed air distributor is adjusted with cylinder No. 4 piston being at 12° (with respect to
crankshaft angle) after TDC in expansion stroke
Distributor slide valve hole should open hole for supply of air to cylinder No. 4 by 1 mm, maximum,
(down slide valve rotation)
Timing angle (cylinder No. 4) (Ref. Fig. 3):
Beginning of admission before TDC ............... .........................(20±4)°
End of admission after BDC ...................... ..............................(54±4)°
Beginning of exhaust before BDC ................. ..........................(65±4)°
End of exhaust after TDC ........................ ................................(25±4)°
Clearance between rocker roller and valve stem
(adjusted on cold engine for checking timing):
Inlet valve ..................................... ............................................1.1 mm
Exhaust valve ................................... ........................................1.1 mm
Clearance between rocker roller and valve stem (adjusted on cold engine for operation):
Inlet valve ..................................... ............................................(0,3-0,1+0,15) mm
Exhaust valve ................................... ........................................(0,3-0,1+0,15) mm

25
Advance angle for LH and BH magneto
(before TDC at end of compression stroke) ......................... ...(23±1)°
1.2.12. Air Compressor
Designation ........................................ ......................................AK-50A
Type ............................................... ..........................................Piston-type
Number per engine .................................. ................................1
Drive transmission ratio ............................................................ 0.9
Drive direction of rotation ........................ .................................RH
1.2.13. Generator
Designation ........................................ ......................................GSR-3000M, series 4
Type ............................................... ..........................................DC
Number per engine .................................. ................................1
Drive transmission ratio ........................... ................................2.5
Drive direction of rotation ........................ .................................LH
1.2.14. Speed Governor
Designation ........................................ ......................................R-2, series 04
Type ............................................... ..........................................Centrifugal
Drive transmission ratio ........................... ................................1.045
Drive direction of rotation ........................ .................................RH
1.2.15. Engine Tachometer Generator
Designation ........................................ ......................................DTE-1
Type ............................................... ..........................................Electric
Number per engine .................................. ................................1
Drive transmission ratio ........................... ................................0.9
Drive direction of rotation ........................ .................................LH
1.2.16. Pilfer with Chip Detector
Type ............................................... ..........................................Electric with plate element
Number per engine .................................. ................................1
Operating voltage .................................. ...................................Up to 29 V
Current ............................................ .........................................0.15 to 0.25 A
Location ........................................... Oil pump
Chip warning device ..................................................................Warning lamp on pilot's instrument
board

26
Operating ratings of the M-14P engine are given in the Table, the throttle characteristic is shown in Fig. 3, external
and altitude characteristics, in Figs 4 and 5, while the timing diagram is represented in Fig. 6.
Rating Reduced power near
ground Crankshaft speed of rotation, r/min Specific fuel consumption, g/hp•h Blower outlet pressure, mm Hg
Take-off
Nominal I
Nominal II
Cruise I
Cruise II
Idle
360 hp-2%
290 hp-2%
240 hp-2%
0.75 of measured power at
nominal rating II
0.6 of measured power at
nominal rating II
-
2900±1 (99%)
2400±1(82%)
2050±1(70%)
1860 ±1(64%)
1730 ±1(59%)
Up to 760 (26%)
285-315
280-310
265-300
210 to 230
215 to 235
-
125-15 (surplus)
95-15 (surplus)
75-15 (surplus)
735±15 (absolute)
670±15 (absolute)
-
NOTES: 1. Engine power and fuel specific consumption rates for all the ratings shall be ensured at non-
loaded generator and compressor.
2. Upper power limit and blowpr outlet supercharged pressure at take-off, nominal I and nominal II ratings
are not limited.
3. Given in brackets are nominal values of the crankshaft speed of rotation in percent against the unified
tachometer (99.4 % corresponds to 2900 r/min of the crankshaft).
1.3. CONSTRUCTION
For engine construction (its longitudinal section) refer to Fig. 7.
2 OPERATION
2.1. GENERAL
The engine should be operated by skilled personnel after special training in aviation equipment
maintenance.
rrior to operating the engine, check complezenesa of the technical publications and get familiar with the
documents.
All operations performed on the engine and its accessories in service shall be written in the engine Log
Book and in accessory Certificates.

27
1 - power curve
2 - specific fuel consumption curve
3 - per-hour fuel consumption curve
Throttle Characteristics Figure 3

28
1 - power line
2 - specific fuel consumption line
3 - per-hour fuel consumption line
External Characteristics Figure 4

29
1 - at take-off rating (n = 2900 r/min)
2 - at nominal rating I (n = 2400 r/min)
3 - at nominal rating II (n = 2050 r/min)
4 - at cruise rating I (n = 1860 r/min)
5 - at cruise rating II (n = 1730 r/min)
Design Altitude-Performance Characteristics Figure 5

30
Timing Diagram Figure 6
CAUTION: WHEN OPERATING THE ENGINE, IT IS PROHIBITED TO DO THE FOLLOWING:
(1) USE FUEL, OIL, GREASE GRADES AND COMPRESSED GASES WHICH ARE NOT
SPECIFIED IN THIS MANUAL.
(2) USE OTHER TOOLS THAN INDICATED IN APPENDIX 2. TO PERFORM MAINTENANCE OF
THE CARBURETOR, LAGNETO AND SPEED GOVERNOR USE THE TOOLS INCLUDED IN THE
INDIVIDUAL SPTA SETS FOR THESE UNITS.
(3) CHANGE THE SPECIFIED SEQUENCE OF OPERATION J PERFORMED ON THE ENGIin
(4) CUT OUT TWO MAGNETOJ SH ULTAHEOUSLY i/ITH THE CARBURETOR THROTTLE
OPEN FULLY ON THE OPERATING ENGINE,
(5) PERFORM FLIGHT 3 BEFORE DETECTION U'TD ELIMINATION OF THE CAUS'. OF
ILLUMINATION OF THE "CHIP IN LIIGIITE" YARNING LAI.IP. IF THE "CHIP IN .NC.INT' .
LAMP COMES ON, CONCENTRATE YOUR ATTENTION ON READINGS OF ENGINE IIirTKU
MENTS AND ACCORDING TO TIL. .jitlation, TAKE A DECISION FOR LANDING.
(6) ROTATE THE ENGINE AIR"CRE,/ SHAFT BEFORE DEPRESERVATION OF THE.SO
COMPRESSOR TO PRECLUDE DAMAGE TO I.IAGNETO PARIS AITO COMPRi.S,,CR COUPLING.
The carburetor air intake shall be provided, with a dust filter installed by the Supplier.

31
2.2. IN-PLIGHT OPERATION OF ENGINE
2.2.1. Taxiing
After starting, warming up and test running the engine and. in the course of taxiing, watch engine
instruments to avoid, overheating or overcooling of the engine.
When air temperature at carburetor inlet is below zero, perform taxiing with heater engaged so that the
carburetor inlet air temperature is not less than 10 °C.
To avoid overheating, perform taxiing at engine low ratings with cowling and oil cooler shutters fully open.
2.2.2. Take-Off and Climbing
Prior to taking off, make sure the engine is warmed up, operates without pops or vibration, and the
instruments read normally. It is recommended to start taking off at cylinder head temperature of 140 to 190 °C and
engine inlet oil temperature of
40 to 65 °C.
Make sure the speed governor control lever is in the LOW PITCH (A3) position. Prior to taking off« check
operation of the airscrew by shifting it from low pitch to high pitch at a speed of 70 % (2050 r/min) till the speed
drops to 53 % (1550 r/min) and back.
If the powerplant is in good repair and everything is ready for take-off, smoothly open the carburetor
throttle, bring the rotation speed and boost to nominal or take-off ratine (depending on the selected rating) and
start taking off.
The take-off rating may be engaged for up to 5 min running.
It is allowed to take off with the heater disengaged if the carburetor inlet air temperature is not less than 10
°C After taking off (in climbing), select nominal rating 1 or nominal rating 11 hy the speed governor control
lever and climb to the desired altitude (climbing may be also performed at cruise rating I).
If when climbing the oil and cylinder head temperature exceeds the permissible limits, lower the rating or
level the airplane (flatten out).
If after levelling the airplane the engine temperature keeps on increasing, discontinue the flight, detect the
cause and eliminate the defects.
To change the engine rating to cruise one in flight, first decrease boost, bring the engine speed to the
desired one by simultaneously moving the carburetor throttle and speed governor control levers. Do not set the
airscrew to higher pitch before decreasing boost, otherwise the crank mechanism of the engine may be heavily
overloaded.
To increase engine rating, first increase its speed to the desired one (relieve the airscrew) and then
increase boosting.
Rotational speed rise to 109 % for up to 1 s can be tolerated in flight, the total time of operation at a speed
of 109 % shall not exceed 30 min during service life.
2.2.3. Level Flight
Level flight can be performed at the following ratings:
Nominal rating I Nominal rating II Cruise rating I Cruise rating II.
Optimal engine ratings in level flight depending on loading, speed and altitude of flying are indicated in the
special Instructions for calculating distance and endurance of flight.
When performing prolonged flight under steady conditions at low ambient temperatures, change over the
airscrew from low pitch to high pitch in every 20 to 30 min of flight by varying the speed of rotation within 67 to 55
% (1950 to 1650 r/min) and then returning it back to the original value to preclude thickening of oil in the air
screw cylinder. A short-time drop of engine inlet oil pressure to 2 kgf/cm is tolerable (followed by
restoration for 8 to 11 s).
Check oil pressure in flight which should be not less than 4 kgf/cm .
When the CHIPS IN ENGINE (CTPTSKA B JWTATME) warning lamp cornea on, concentrate on readings
of engine instruments and depending on the situation, take a decision to land.
CAUTION: IT IS PROHIBITED TO PLY BEFORE DETECTING AND ELIMINATING THE CAUSE OF IL-
LUMINATION OF THE WARNING LAMP.
2.2.4. Diving, Glinding and Landing
Engine speed at diving, steep gliding should not exceed 86 % (2500 r/min) at continuous operation of the
engine for up to 1 min.
Cylinder head minimum temperature should be not below 120 °C, oil temperature, not below 40 °C.
When gliding at idle rating or flaring out from dive, it is not recommended to give full throttle by abrupt
shifting of the throttle quadrant. Change over from idle to full throttle smoothly (during 2 to 3 s) since abrupt
acceleration may lead to airscrew spinning and high dynamic loading of the engine parts.

32
Figure7.
1. Nut
2. Sealing Ring
3. Exhaust Pipe Connection
4. Satellite
5. Satellite Pivot
6. Sun Gear
7. Sealing Ring Bushing
8. Thrust Bearing Cover
9. Shipping Shackle
10. Speed Governor
11. Speed Governor Manual
Control Shaft
12. Nut
13. Cam Plate
14. Speed Governor and Cam
Plate Drive Shaft
15. Spark Plug
16. Gasket
17. Gasket
18. Adapter
19. Drive Gear
20. Cotter Pin
21. Airscrew Shaft
22. Nut
23. Bolt
24. Nut
25. Gearbox Housing
26. Bolt
27. Bellows
28. Oil Sump
29. Gap
30. Filter with Chip Detector
31. Locking Wire
32. Nut
33. Inlet Valve
34. Tappet Push Rod
35. Starting Valve
36. Tappet Push Rod Casing
37. Lock
38. Nut
39. Rubberized Fabric Hose
40. Clamp
41. Guide Bushing
42. Tappet Roller
43. Gasket
44. Nut
45. Lock
46. Cover
47. Bearing
48. Gasket
49. Front Cover
50. Stud
51. Ring
52. Gasket
53. Crankcase
54. Oil Baffle
55. Crankshaft
56. Gasket
57. Gasket
58. Lock
59. Gasket
60. Carburetor
61. Strainer
62. Bolt
63. Gasket
64. Cylinder Head
65. Piston
66. Cylinder Deflector
67. Starting Pipe Mounting Stud
68. Rubber Sealing Ring
69. Starting Pipe
70. Attachment Nut
71. Intake Pipe
72. Spark Plug Cable
73. Mixture Collector Priming
Connection Attachment Clamp
74. Ignition Harness
75. Connection for Pilling
fuel into Mixture Collector
76. Nut
77. Blower Breather
78. Engine Frame Ring
79. Locking Seal
80. Locking Wire
81. Generator
82. Mixture Collector
83. Nut
84. Rear Cover
85. Generator Drive Gear
86. Blower Drive Coupling
87. Oil Pump Filter
88. Oil Pump
89. Fuel Pump
90. Fine Fuel Filter
91. Generator Drive Housing
92. Drive Shaft
93. Generator Drive Friction
Coupling
94. Driven Shaft
95. Rubber Insert
96. Adapter Shaft
97. Adapter
98. Bushing

33
To preclude overcooling of the engine in cold weather or at prolonged gliding, close shutters of the
cowling and oil cooler or periodically warm up the engine by giving throttle.
When gliding before landing shift the speed governor control lever to the LOW PITCH poaition so that in
case of necessity (faulty landing planning, etc. ) it would be possible to select take-off rating.
When gliding at idle rating, oil pressure should not drop below 1 kgf/cm , Short-time
(up to 0.5 s) engine inlet oil pressure drop to 0.5 to 1 kgf/cm at near-zero and
negative accelerations as well as to a pressure of 1.8 kgf/cm for up to 5 s is allowed in flight. The total
time of engine operation under such conditions shall not exceed 5 min during service life.
To preclude overheating, taxi at low ratings with shutters of the cowling and oil cooler fully open.
2.2.5. In-Flight engine Operation at Low Ambient Temperatures
Engine ratings at take-off, climbing, level flight and descent in winter are similar to those of summer time;
however, when operating the engine in winter, it is necessary to take into account the following notes:
(1) Take-off and climbing may be performed with air heater disengaged when the carburetor inlet air
temperature is from 10 to 45 °C. If icing is possible, fully engage carburetor inlet air heating.
(2) To preclude freezing of oil in the airscrew cylinder during level flight periodically (in 20 to 30 min)
change over the airscrew from low pitch to high one and back and then reset the original speed of rotation.
(3) When gliding from high altitude in cold weather, engage the carburetor inlet air heating and close the
cowling shutters to preclude overcooliiif; of the cylinders and periodically warm up the engine so that the cylinder
head temperature does not drop below 120 °C.