DA 62 AFM Airplane Description
Distribution
Electrical power is distributed via the HOT BATTERY BUS, the BATTERY BUS, the LH
(RH) ECU BUS, the LH (RH) MAIN BUS, and the AVIONIC BUS.
HOT BATTERY BUS:
The HOT BATTERY BUS is directly connected to the main battery and cannot be
disconnected from the main battery. The HOT BATTERY BUS provides power to the pilot
map/reading light which is protected by its own fuse.
BATTERY BUS:
The BATTERY BUS is connected to the main battery via the battery relay which can be
controlled by the ELECT. MASTER switch. The BATTERY BUS provides power to the
LH (RH) MAIN BUS and heavy duty power to both starters.
ECU BUS:
The LH (RH) ECU BUS is connected to the LH (RH) MAIN BUS via a diode and connected
to the power output line of the alternator via diode and a 30 Ampère circuit breaker and
provides power directly to ECU A and its fuel pump. ECU B and its fuel pump derive their
electrical power from their associated ECU BUS via an additional diode and fuse.
Additionally, each ECU B and its fuel pump is supplied with electrical power from the
opposite engine side ECU BUS via a diode and fuse.
The LH (RH) ENGINE MASTER switch must be set to ON to activate the engine ECU.
To support the alternator electrical power supply to the ECUs in case of a malfunction
of the main battery, additional sealed-lead-acid batteries (ECU backup battery) are
connected to the RH and LH ECU bus.
These batteries are able to provide 30 minutes of engine operation in case of a complete
airplane electrical failure. Both engines may stop if the 30 minutes have elapsed.
Doc. No. 11.01.05-E Rev. 0 11-Jan-2019 Page 7 - 65
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