Aeropro A220 - 1.1 Engine; 1.3 Fuel and Fuel Capacity

Aeropro CZ - A220 taildragger - Pilot Operating Handbook and Flight Training Supplement
March 21, 2020
9
1.1 Engine
The A220 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. coolant temperature...................................................... 248 F (EIS warning at 228 F)
Min. oil temperature………………………………………….… 122 F for full-throttle operation
Normal operating temperature……………………………..… 190 – 230 F
Max. oil temperature............................................................ 266 F (EIS warning at 242 F)
Minimum oil pressure……………...................…...........…….. 12 psi min oil pressure below 3,500 rpm
maximum oil pressure (cold start only)…………………..……. 102 psi (EIS warning at 92 psi)
normal oil pressure range..................................................... 29 – 73 psi (EIS warning below 29 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
2. For many more details see Operator’s Manual for 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-
17 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.
2.1 Propeller
The propeller is manufactured by DUC Helices in France. 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.
2.2 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 specifications………...... premium unleaded auto fuel (Standard Spec. for Automotive
Spark-Ignition Engine, Fuel, ASTM D 4814) or AVGAS 100 LL