Aeropro CZ - A240 - Pilot Operating Handbook and Flight Training Supplement
September 1, 2014
1-9
1.1 Engine
The A240 is powered by the Rotax 912ULS 100-hp engine. It is a four-cylinder, four-stroke, horizontally-
opposed, center-camshaft engine with overhead valves. Engine cooling is of a combined type; cylinder
heads are water-cooled while cylinders are air-cooled. The engine has dry-sump lubrication. The ignition
system is a dual, electronic and capacitor flywheel magneto type. The engine is equipped with an electric
starter, AC generator and a mechanical fuel delivery pump. The propeller is driven by an integrated
reduction gearbox with mechanical damping.
Engine manufacturer
........................................ Rotax GmbH., Austria
Engine model...................................................... Rotax 912ULS
Max. power
- take-off.................. 100 hp
- continuous............. 94 hp
Max. engine speed (MSL) - take-off................ 5800 RPM (max. 5 min)
- continuous........... 5500 RPM
Max. cylinder head temperature............................................. 280
F
Min. o
il temperature………………………………………….….... 122
F for full-throttle operation
Normal ope
rating temperature………………………………....… 190 – 230
F
Max. oil temperature................................................................ 300
F
M
inimum oil pressure……………...................…...................… 12 psi min oil pressure below 3,500 rpm
Maximum oil pressu
re (cold start only)……………………........ 103 psi
Normal oil pressure range...................................................... 29
– 73 psi
Oil consumption
……………………………………………….... max 0.06 quarts/hour
Fuel pressure
- minimum............................................... .18 bar (2.2 psi)
- maximum.............................................. .4 bar (5.8 psi)
Propeller gearbox reduction ratio............................................. 2.43 : 1
For more details see
Operator’s Manual f
or all versions of
Rotax 912
supplied with the engine.
WARNING
This aircraft is equipped with a non-certified engine that meets the ASTM F-2339
engine standard.
Flying this aircraft must always be done with the possibility of a safe landing due
to loss of engine power. The pilot is fully responsible for consequences of such
failure.
1.2 Propeller
The standard propeller is manufactured by Woodcomp in the Czech Republic. The propeller is a 3-blade,
ground-adjustable prop. Propeller is 68" diameter.
For additional propeller information see
Operators Manual and Technical description
supplied with the
propeller.
1.3 Fuel and fuel capacity
Fuel tank capacity - wing tanks (two)................................. 10.6 U.S. gallons each
- central connecting tank (header tank)........................... 1.3 U.S. gallons
Max. fuel quantity............................................................. 22.5 U.S. gallons
Usable fuel quantity......................................................... 22.0 U.S. gallons
Unusable fuel quantity...................................................... 0.5 U.S. gallons
Fuel s
pecifications………...... premium unleaded auto fuel (Standard Spec. for Automotive
Spark-Ignition Engine, Fuel, ASTM D 4814) or AVGAS 100 LL
