FLIGHT MANUAL TSA-M, VARIANT S6
Doc.-No.: P400-006.000 E Page: 7-20 Revision: 9
Date of Issue: 07. October 2008 Date of Rev.: 01.10.2012
7.11 Propulsion-System and Engine ____________________
7.11.1 Engine and General Information
The installed engine is a model ROTAX 914 F2:
• 4-cylinder 4-stroke Otto-engine in opposed-cylinder design including
turbocharger with electronic manifold-air-pressure (MAP) control and
integrated reduction-gear
• Liquid-cooled cylinder-heads and ram-air-cooled cylinders
• Electronic dual magneto-capacitator-ignition
• Two CD-carburator, one on each engine-side
• Flanged reduction-gear and overload-clutch
The engine is mounted in the mid-section of the fuselage with the engine-
suspension connecting it to the steel-tube-framework. There, the engine causes
low noise-emissions for the cabin and the aircraft’s surroundings.
Specifications of the ROTAX 914 F2:
• Max. T/O-power (MTOP):
113 HP / 84.5 kW at 5800 RPM
(Takeoff RPM limited to 5600 RPM by const.
speed propeller control)
• Max. continuous power
(MCP):
98 HP / 73.4 kW at 5500 RPM
• Engine-displacement:
73.9 in
/ 1211 cm
• Transmission-ratio of
engine-gear
i=2.428
• Compression-ratio:
9.0 : 1
Fuel and fuel-consumption:
• Fuel to be used:
MOGAS (unleaded gasoline according to EN
228, min. ROZ 95)
or AVGAS 100LL
• Fuel Consumption at MCP
7.0 US gal/h / 26.6 l/h
• Fuel Consumption at 75%
5.4 US gal/h / 20.4 l/h
• Fuel Consumption at 55%
3.4 US gal/h / 13 l/h
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