025-00-16C M16C FLIGHT MANUAL, Issue G
02 March 2016
Page 27
2.8.2 FUEL QUANTITY DATA
Maximum capacity of fuel tank 72 litres
Usable fuel quantity 69 litres
Not usable fuel quantity 3 litres
2.9 COOLING SYSTEM
(see fig. 2.9/1)
The engine is equipped with an air-water type cooling system.
The heads of the ROTAX 914 engine are water-cooled by a cooling system equipped with a vacuum pump
(connected to the shaft) that sucks the coolant from the radiator. This coolant flows through the heat
exchanger, cools the oil and then reaches the engine.
The cylinders of the ROTAX 914 engine are cooled by the air that strikes the engine. As the engine is
configured and installed in an area without cowlings, there is no need for air intakes or conveyors of any
type.
The combined cooling action of both systems guarantees the correct preservation of the temperatures within
the limits indicated in the engine's operators manual.
1 - Cooling radiator
2 - Heat exchanger
3 - Water pump
4 - to the LH engine
5 - to the RH engine
6 - Thermal expansion valve
7 - Expansion tank
8 - Backflow from engine
9 - Overflow bottle
10 - Expansion tank cap
11 - Expansion tank cap
12 - Lubrication system line
Summary of Contents for M-16 C
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Page 91: ...Page 91 025 00 16C M16C FLIGHT MANUAL Issue G 02 March 2016 APPENDIX 1 CG DATA...
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Page 96: ...Page 96 025 00 16C M16C FLIGHT MANUAL Issue G 02 March 2016 APPENDIX 3 HEIGHT VELOCITY DIAGRAM...
Page 98: ...Page 98 025 00 16C M16C FLIGHT MANUAL Issue G 02 March 2016 APPENDIX 4 MANOEUVRE LIMITATIONS...
Page 100: ...Page 100 025 00 16C M16C FLIGHT MANUAL Issue G 02 March 2016 APPENDIX 5 ENGINE PARAMETERS...
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Page 103: ...Page 103 025 00 16C M16C FLIGHT MANUAL Issue G 02 March 2016 APPENDIX 6 VOLTMETER DEVICE...
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