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The fuel supply connection attaches to a finger filter mounted at the rear of the auxiliary fuel tank. Each auxiliary fuel tank has a fuel transfer pump which pumps fuel into the related main fuel tank.
The vent line for the auxiliary fuel tank has a check valve with capillary. It allows air to enter the tank but prevents flow of fuel to the outside. The capillary equalizes the air pressure during climb. A fuel drain valve is located at the rear of each auxiliary tank.
Operation
Two FUEL TRANSFER switches in the cockpit are used to activate the fuel transfer pumps. The switches are located behind the elevator trim wheel on the center console. Both swithes are intended to be used simultaneously to prevent the airplane from additional lateral imbalance. The fuel transfer pump pumps the fuel from the auxiliary fuel tank into the related main fuel tank. Fuel level switches shut this pump off automatically when the auxiliary fuel tank is empty or when the main fuel tank is full. During operation of the pumps an advisory alert on the Garmin G1000 indicates that the fuel transfer is in progress.
If the auxiliary fuel tank is empty, a caution alert appears on the Garmin G1000. In this case the fuel pumps must be switched OFF.
When one fuel transfer pump is defective, the fuel stored in the related auxiliary fuel tank is not available. For use of the remaining fuel pump refer to to Section 4B.10 - L/R FUEL TRANSFER FAIL. The flight plan must be amended accordingly.
The fuel transfer pumps are electrically connected to the LH Main Bus and protected by a 5A circuit breaker, if no Ice Protection System (O.M 42-053) is installed.
If the Ice Protection System is installed, both Systems are protected by a 10 A circuit
' breaker and an additional 7A fuse for the fuel transfer pumps. The circuit breaker is labeled XFER PUMP/DE ICE.
Doc. No. 7.01.05-E Rev. 5 15-Nov-2007 Page 7 - 41
Alternate means for fuel quantity indication for the fuel tank:
The alternate means for fuel quantity indication allows the fuel quantity in the tank to be determined during the preflight inspection. It functions according to the principle of communicating containers. The fuel quantity measuring device has a recess which fits the airfoil of the wing in front of the fuel tank drain, which lies approximately 10 cm (4 in) outboard of the engine nacelle. The metal connector is pressed against the drain of the tank. The amount of fuel in the tank can now be read off from the vertical ascending pipe.
For an exact indication the airplane must stand on level ground and the measuring device must be held vertically.
The designated location for the fuel quantity measuring device is a bag on the rear side of the pilot seat.
Fuel temperature
A fuel temperature sensor measures the fuel temperature in each main tank. The indication is provided by the G1000 flight display. Information about fuel temperature limitations can be found in Chapter 2 - OPERATING LIMITATIONS.
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