DA 42 NG AFM Airplane Description
Doc. No. 7.01.16-E Rev. 3 01-Apr-2014 Page 7 - 31
ECU VOTER
There are two VOTER switches, one for each engine. For normal operation both switches
are set to AUTO. Each engine is controlled by either ECU A or ECU B. In case of a failure
of the active electrical engine control unit (ECU) there should be an automatic switch-over
to the other ECU. If the automatic switch over fails, switch over can be done manually
by switching to ECU A or ECU B. This procedure should only be applied in an emergency.
ECU TEST
There are two ECU TEST buttons, one for each engine.
Power Lever at IDLE and RPM Below Approximately 900:
By pushing and holding the button until the end of the procedure, the self-test of each
engine control unit is started. The procedure is possible on the ground only. Otherwise
the test will not start. During the procedure the ECU performs a switch from ECU A
to ECU B or ECU B to ECU A, whichever is active at the moment, with the propeller
cycling. The propeller RPM is monitored automatically by the ECU. When switching
from one ECU to the other, a slight shake of the engine may occur. Finally the ECU
switches back. After that both caution lights must extinguish and the engine must run
without a change.
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