AEROPRAKT-32 Pilot Operating Handbook
A32-iS-129-POH
28
Landing gear data: wheel base
– 1.243 m (4 ft 1 in),
wheel track
– 1.729 m (5 ft 8 in),
min. turn radius ~ 2 m (7 ft).
Main wheels: size
– 6.00×6
pressure
– 1.6 bar (22.7 psi)
Nose wheel: size
– 6.00×6 brakeless wheel
steering angle ±30 degrees
pressure
– 1 bar (14.5 psi)
7.4 Engine and its controls
This aircraft is equipped with a four-cylinder four-stroke Rotax-912iS Sport (100 hp)
combined cooling engine produced by BRP-Rotax 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, integrated gearbox of
2.43 reduction ratio and fully redundant electronic engine management system (EMS) which
includes fuel injection, ignition, etc.
All engine systems (fuel, electrical, cooling) are assembled in accordance with Rotax-912 i
SERIES engine operation and installation manuals.
7.5 Propeller
A-32 airplane may be fitted with any propeller, approved by Aeroprakt Ltd.
7.6 Fuel system
) includes two wing fuel tanks 1 and 2 (each of 57 l capacity)
with filler inlets 3 and 4. Fuel comes from left and right fuel tanks via fuel lines 5 and 6 to
double fuel valves 7 and 8, each opening/closing the feed and return line simultaneously.
Then fuel is fed through fuel lines 9 and 10 to sediment separator 11. From the sediment
separator through the fuel line 12, coarse filter 13 and then through the fuel line 14 the fuel
is fed to inlet of the 1st (main) fuel pump 15 and then to the inlet of the 2nd (auxiliary) fuel
pump 17. The 1st and 2nd fuel pumps together with the return valves 16 comprise a single
module, located on the firewall on the right. From the outlet of the 2nd fuel pump the fuel is
supplied with pressure through the fine filter 20 to the rail injectors 21 of the cylinders 1 and
3. Then through the tube 22
– to the rail injectors 23 of the cylinders 2 and 4, outlet of which
is joined with fuel pressure regulator 24. The fuel pressure regulator ensures constant fuel
pressure in the range of 2.8-3.2 bar (42-45 psi) in rail injectors with regard to the air pressure
in the intake manifold. From the outlet of the fuel pressure regulator the excessive fuel is
returned through the low pressure fuel return line 25 and T-connector to the fuel tank 1 or 2
through the fuel line 27 or 28 depending upon which of the fuel valves 7 or 8 is opened. Fuel
pressure after the fuel pumps is controlled using the fuel pressure sensor 19, installed
immediately before the fine filter 20. The fuel tanks have vent tubes 31 and 32 installed in
the fuel tank inlet caps. Fuel can be drained from the tanks on the ground via the drain valve
29, handle of which is accessible outside fuselage.
Standard
Optional
Capacity of tanks:
2×45 l (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:
88 l (23.3 US gal)
112 l (29.6 US gal)
Non-usable fuel:
2 l (0.5 US gal)
2 l (0.5 US gal)
