AEROPRAKT-32L Pilot Operating Handbook
A32L-FO-POH
7.6 Fuel system
The fuel system (see Fig. 3) includes two wing fuel tanks (1,2), fuel lines
(5,6,9,10,12,14,16,18,19,20,), two shut-off valves (7,8), fuel sediment collector (11), fuel
filter (13), fuel pump (17), return line (24), drain line (25) and drain valve (25). The fuel
tanks (11.9 (15.05) US gal each) are located at the wing root between the spar and aft web.
The fuel inlet 3(4) is located at the front outboard corner of the tank. The inlet cover has
vent fitting 27(28) connecting the tank volume free of fuel to the atmosphere. The fuel shut-
off valves (7,8) are located on the vertical beams of the frame No.3, on the left and right
sides respectively. The shut-off valve is open when its handle is set vertically and closed
when the handle is set horizontally. The left and right fuel tank is connected with the fuel
lines to the left and right fuel shut-off valve respectively. Further two fuel lines are joined
into a single one with the T-connector, which is located near the web of the frame No.4 at
its bottom part. Then fuel goes to the fuel sediment collector (12). The top outlet of the fuel
sediment collector is connected to the fuel filter (14) located on the right side behind the
main landing gear beam. The fuel filter can be inspected visually through a window in the
protecting cover of the aileron control cables. The bottom outlet of the fuel sediment
collector is connected to the drain valve (25) with a fuel line. The drain valve alows draining
fuel through the hole in the bottom rear panel of fuselage. The valve handle is accessible
outside of the fuselage. After the fuel filter the fuel line (14) runs throught the main landing
gear beam, seat beam along the right-hand side of fuselage to the firewall where it is
connected with a 90° bulkhead fitting (15), that is passing through the hole in the firewall, to
the fuel line of the engine (16) and is connected to the inlet of the fuel pump (17) located on
the right-hand side of the engine gearbox. The pump outlet is connected with the fuel lines
(18,19,20) to the carburettors (21, 22). The excessive fuel is returned through the line (24)
to the sediment collector (11).The fuel system optionally may contain fuel pressure sensor
(24) and fuel flow sensor (26).
Standard
Optional
Capacity of tanks:
2x45 I (11.9 US gal)
2x57 I (2x15.05 US gal)
Total fuel capacity:
90 I (23.8 US gal)
114 I (30.1 US gal)
Total usable fuel:
89.5 I (23.6 US gal)
113.5 I (30.0 US gal)
Non-usable fuel:
0.5 I (0.1 US gal)
0.5 I (0.1 US gal)
NOTE: When both tanks are full, fuel may flow from one tank to the other (e.g. due to the
lateral forces during side slipping or when wings are not level on parking or during taxiing),
overfill it and spill out through the vent line. To prevent this close one of the fuel valves.
CAUTION! At all times during the flight ensure fuel coming to the engine by opening the
valve(s) of the tank(s) WITH fuel. If one of the tanks is empty, close its valve
to prevent air getting into the fuel line and causing engine malfunction or
even failure.
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