1.8 Powerplant
1.8.1 Engine
Rotax is an Austrian engine manufacturer, founded in 1920 in Dresden, Germany. In 1970 Bombardier bought Rotax. The
company constructed only two-stroke engines until 1982, when it started building four-stroke engines. In 1989, Rotax
received Type Certification for its 912 A aircraft engine.
The Rotax 912 ULS engine is an ASTM compliant engine. The 912 is a four stroke, horizontally opposed, spark ignition
engine with single central camshaft with hydraulic tappets. The 912 has liquid cooled cylinder heads and ram air cooled
cylinders and engine. It is rated at 5800 RPM and can be run continuously at 5500 RPM.
The oil system is a dry sump, forced lubrications system. The oil tank is located on the passenger side of the engine
compartment and holds 3 liters (3.2 quarts) of oil.
The dual ignition system is a solid state, breakerless, capacitive discharge, interference suppression system instead of a
mechanical magneto system. Each ignition system is powered by individual and totally independent AC generators which are
not dependent on the aircraft battery.
The electrical system consists of an integrated AC generator with an external rectifier – regulator. An external alternator can
be installed. The Rotax engine is equipped with an electric starter.
The dual carburetors are constant depression carburetors that automatically adjust for altitude.
The fuel system is equipped with an engine driven mechanical pump and electrical back up FACET pump.
The cooling system is a mixture of liquid and air cooling.
The engine uses a reduction gearbox with a gear reduction ratio of 2.4286:1.
A central console located throttle in the cockpit controls the engine.
The owner can register and get important information from the following website: http://www.rotax-owner.com/.
1.8.2 Propeller
P92 LSA is equipped with a Sensenich Wood propeller. The model is W68T2ET-70J and is made by two wooden blades,
with fixed pitch. The diameter is 1730 mm.
1.8.3 Fuel system
A sketch of the fuel system is illustrated in Figure 1-3. It consists of two fuel tanks integrated in the wing leading edge and
having a 45t (11.8 US gal) capacity (total capacity is 90lt (23.7 US gal)). The engine is fed by means of an engine-driven
mechanical pump and, as backup, by an electric pump. The fuel system has a sediment bowl or chamber that is accessible
for drainage. A fuel selector is located in cabin. Two resistive type fuel quantity senders are installed in each tank and
provide the fuel indication on the A/C cockpit.
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