7 - 12 Page Date: 20. April 2002
Section 7
Description and Operation of Aircraft and Systems
Pilot´s Operating Handbook
EXTRA 200
7.10.8 FUEL SELECTOR VALVE
Dual control. A rotary fuel selector valve is mounted behind the firewall on the right side of
the fuselage. A torque tube connects the valve to both cockpit handles. Pull and turn the
handle 90° to open the valve to the Acro & Center tank. A further 90° turn switches to the
Wing tank fuel supply.
Position down: "OFF"
Position left: "ACRO & CENTER"
Position up: "WING TANK"
7.10.9 EXHAUST SYSTEM (OPTIONAL)
The EXTRA 200 can be equipped with a complete 4 in 1 System including silencer.
7.11 FUEL SYSTEM
The fuel system consists of two separate, independent tanks:
- "Acro & Center tank" in the fuselage
- "Wing tank" in the wing
Wing tank:
The root section of each wing in front of the main spars forms an integral fuel tank providing
two interconnected tanks with 86 liters (22.7 US Gal.) total capacity. Each side of the wing
has a 2" diameter filler cap for gravity refuelling. Due to the interconnection the fuel level of
the left and right integral tank will equalize during refuelling within reasonable time. For max.
fuel capacity, the first filled side have to be filled once again! Furthermore the wing tank is
connected directly to the engine by the fuel selector valve. Unusable fuel is approximately 1
liter (0.3 Us Gal.).
Acro & center tank:
The Acro tank of 9 liters (2,3 US Gal.) is mounted under the Center tank. This Center tank
of 27 liters (7.1 US Gal.) is mounted in front of the main spar of the wing. The Acro tank is
connected with the Center tank in a gravity feed system. The Center tank has a 2" diameter
filler cap for gravity refuelling. Unusable fuel is approximately 4 liters (1.1 US Gal.)
Adequate venting is provided in each tank by a main ventilation-tube, ending outside the
fuselage at the right side.
Fuel pump
In addition to the engine driven fuel pump an electrically driven auxiliary fuel pump (boost
pump) with by-pass, having sufficient capacity to feed the engine at takeoff power, is fitted
as a safety device against failure of the engine-driven pump. The boost pump switch is
located on the instrument panel.
A fuel filter with drain is installed between the fuel selector valve and the boost pump.
Separate drains are located at the lowest point of each tank system.
Normal float type transducers and electrically operated fuel indicators are used.
Datum der Seite: 28. April 2006
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