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The transfer pump is switched off automatically when the auxiliary tank is empty or the main tank is full.
If fuel transfer with the transfer pump becomes impossible for any reason, fuel can also be taken directly from the AUX tank (right wing). As the return line goes back into the MAIN tank (left wing), fuel will be transferred from right to left.
The rail pressure is controlled by an electrical valve using the return flow as parameter.
CAUTION
Switching the emergency fuel valve to the EMERG. TRANSFER position will start the transfer of fuel with the help of the engine driven fuel pump from the auxiliary tank through the fuel return line to the main tank at a rate of approximately 18 to 21 US gal/h (70 to 80 liters/h). The emergency fuel valve must be switched back to the NORMAL position before the auxiliary tank indication reads zero. If the emergency fuel valve is not switched back to the NORMAL position, the engine will stop during flight when the auxiliary tank is empty.
Doc. No. 6.01.05-E Revision 3 26-May-2003 Page 7 - 31
Emergency fuel valve
The emergency fuel valve is situated on the center console. Its positions are NORMAL, EMERG. TRANSFER and OFF. The desired position is reached by turning the valve handle while pulling up the safety catch on the valve handle. This is to ensure that a selection is not made unintentionally.
Fuel tanks
Main tank (left wing):
The main tank consists of an aluminum chamber and a filler tube which are connected by a flexible hose. There are two tank vents. One includes a check valve with a capillary and one includes a relief pressure valve, which operates at 150 mbar (2 psi) and allows fuel and air to flow to the outside with higher internal pressure. The relief pressure valve protects the tank against high pressure, if the tank will be overfilled in case of a fuel transfer failure. The check valve with capillary allows air to enter the tank but prevents flowof fuel to the outside. The capillary equalizes the air pressure during climb. The hose terminations are situated on the underside of the wing, approximately 2 meters (7 ft) from the wing tip.
Auxiliary tank (right wing):
The auxiliary tank consists of an aluminum chamber and a filler tube which are connected by a flexible hose. There are two tank vents. One includes a check valve with a capillary and one includes a capillary. The check valve with capillary allows air to enter the tank during descent but prevents flow of fuel to the outside. The capillary equalizes the air pressure during climb. The second capillary is installed for additional safety. The hose terminations are situated on the underside of the wing, approximately 2 meters (7 ft) from the wing tip.
In each tank a coarse filter (finger filter) is fitted before the outlet. To allow draining of the tank, there is an outlet valve at its lowest point.
Doc. No. 6.01.05-E Revision 3 26-May-2003 Page 7 - 32
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本文链接地址：钻石40飞机飞行手册 DA 40 Airplane Flight Manual(65)
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