FUEL PUMP 702ML - DESCRIPTION AND OPERATION
1. GENERAL
The 702ML fuel pump (referred to hereinafter as "pump" is intended, to supply fuel from the airplane fuel
tanks through the filters to the engine carburetor.
The pump features a reducing chamber detachable housing accommodating two valves;a reducing valve
and a priming valve. Repositioning of the reducing chamber through 180° relative to the pump housing ensures
operation of the pump for RH or LH direction of rotation without changing the position of the pumping unit.
To connect to the' engine, the pump has a special flange and a square drive shank.
2. DESCRIPTION
2.1. Specifications
Pump drive ........................................... .............................................. From engine
Pump rotor direction of rotation ..................... ..................................... LH
Pump speed of rotation:
Maximum (permissible for 30 s) .......................................................... 3000 r/min
Minimum at which continuous jet is ensured. ......... ........................... 200 r/min
Nominal ............................................ .................................................. 2200 r/min
Fuel line inlet and outlet diameter .................. .................................... At least 8 mm
Total delivery of pump (with reducing valve engaged)
without backpressure at 2200 r/min and fuel suction
height of 1 m ........................................ .............................................. At least 400 1/h
Pump delivery at 2200 r/min,backpressure of o
P = 0.1 kgf/cm in delivery line and fuel suction height of 1 m ......... ... At least 175 1/h
Pump delivery at 200 r/min,backpressure of
P = 0.1 kgf/cm in delivery line anf fuel suction height of 1 m ......... .... At least 10 1/h
Maximum permissible pressure in delivery line ........ ......................... Up to 1 kgf/cm
Dry pump mass ........................................ .......................................... Up to 580 g
Pump power consumption ................................ ................................. Up to 0.5 hp
NOTES: 1. In the course of operation seepage of oil to return line from the fuel pump drive should
not exceed 5 droplets per hour.
2. It is allowed to run the pump on foreign-made fuels (Ref. 072.00.00, Appendix 1).
Summary of Contents for M-14P
Page 6: ...19 Engine M 14P Front View Figure 1...
Page 7: ...20 Engine M 14P Rear View Figure 2...
Page 27: ...40 Arrangement of Airborne Tools in Case Figure 1...
Page 39: ......
Page 44: ...57 Engine M 14P Test Run Chart Figure 201...
Page 67: ...80...
Page 163: ...176 Crankshaft Thrust Ball Bearing Front Cover Figure 1 Intermediate Crankcase Figure 2...
Page 166: ...179 Intermediate Grankcase Front Portion Figure 3 Intermediate Crankcase Rear Portion Figure 4...
Page 173: ...186 Front view Cylinder Figure 1 Rear view...
Page 180: ...193 Timing Mechanism Schematic Diagram Figure 6 Cam Plate Figure 7...
Page 189: ...Blower Longitudinal Section View Figure 1...
Page 191: ...Rear view Mixture Collector Figure 2 Diffuser Figure 3...
Page 194: ...1 Plate 2 Spring 3 Plate 4 Gear 5 Accessory Drive Shaft Blower Coupling Figure 4...
Page 204: ...Oil Sump Figure 4...
Page 216: ...Engine M 14P Gear Train Figure 1...
Page 247: ...Carburetor AK 14P Operation Diagram Figure 1...
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Page 288: ...T t en 0 CO 0 T K D fi h0 Ol f 01 3 0 F4...
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Page 344: ...Generator Electrical Connection Diagram Commutator Side View Figure 3 1 Main Pole 2 Interpole...
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