AEROPRAKT-22LS Pilot Operating Handbook
A22LS-POH-04
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3.2 Service ceiling
Service ceiling of A-22LS with Rotax-912ULS (100 hp) engine is equal to at least 5000 m.
However A-22LS has neither pressurized cockpit, no oxygen equipment and therefore may
not be used for high-altitude flight.
3.3 Maneuvering load factors
Limit load factors for the airplane at gross weight of 600 kg (1320 lb.) are as follows:
Maximum positive limit load factor +4.0
Maximum negative limit load factor -2.0
3.4 Approved maneuvers
A-22LS airplane belongs to a non-aerobatic category. All maneuvers shall be done within
its airspeed and maneuvering load factor limits (G limits). Approved maneuvers include:
- turns with bank angles up to 60°,
- side-slipping with angles up to 15°,
- level and accelerated stalls without spinning,
- diving at a speed below V
NE
of 229 km/h (142 mph, 124 kts) IAS.
Any aerobatics including intentional spinning is prohibited!
3.5 Fuel capacity and type
standard
optional
Capacity of tanks: 2×45 l (2×11.9 US gal) 2×57 l (2×15.05 US gal)
Total fuel capacity:
90 l
(23.8 US gal) 114 l
(30.1 US gal)
Total usable fuel:
89 l
(23.5 US gal) 113 l
(29.8 US gal)
Non-usable fuel:
1 l
(0.3 US gal)
1 l
(0.3 US gal)
Approved fuel types: unleaded Mogas min. RON 95 or avgas 100LL.
3.6 Engine
This aircraft is equipped with a four-cylinder four-stroke Rotax-912iS (100 hp) combined
cooling engine produced by BRP-Powertrain GmbH&Co KG. (Austria).
The engine is has the flat-four layout, dry sump lubrication system with a separate oil tank
of 3 l (0.8 US gal) capacity, automatic valve clearance adjustment, two carburetors,
mechanical membrane fuel pump, double electronic ignition system, integrated water
pump, electrical starter, integrated gearbox of 2.43 reduction ratio.
All engine systems (fuel, electrical, cooling) are assembled in accordance with Rotax-
912iS engine operation and installation manuals.
