Sennheiser SI 234 - ANNEXE 802 Operations Instructions download pdf (Page 384)

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Airplane Description DA 42 NG AFM

Page 7 - 36 Rev. 3 01-Apr-2014 Doc. No. 7.01.16-E

Fuel is stored in the tanks which are located in the wings.

Normally fuel for the right engine is taken from the right wing main tank and for the left

engine from the left wing main tank.

On each engine fuel is injected with high pressure directly into the cylinders. The injection

nozzles (one per cylinder) are supplied with fuel by the common rail. Pressure inside the

rail is generated by a high pressure pump which receives fuel from two independent low

pressure fuel pumps. Both pumps are powered electrically. Depending on the power

setting the rail pressure is controlled by the ECU through an electric metering valve. Fuel

that is not injected is fed back into the appropriate wing tank.

Both sides of the fuel system are interconnected by crossfeed lines.

In each engine nacelle an auxiliary fuel tank may be installed.

Fuel Pumps

Each engine is feed by two parallel installed independent electrically driven low pressure

fuel pumps. During normal operation one of the two fuel pumps is working. In case of

a low fuel pressure failure the ECU switches automatically to the second fuel pump. During

landing and take-off, or in case of a fuel pressure failure both fuel pumps can be activated

by the FUEL PUMP switch. If both fuel pumps are activated the fuel pressure increases.

Each fuel pump is electrically connected to the LH/RH ECU BUS and protected by a 7.5 A

circuit breaker.

NOTE

By switching between ECU A and B the two independent

electrically driven fuel pumps are switched over as well. In

case of an emergency both pumps can be activated

simultaneously by using the fuel pump switch.

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Sennheiser SI 234 - ANNEXE 802 Operations Instructions Page 384

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