DA 62 AFM Airplane Description
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.
Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 7 - 43
To Next Page
Loading...
