ECU will continue to operate in an alternative control mode,
which will transfer the control of ignition and injection to the er-
ror- free Lane.
Regular operation as well as alternative control modes of the
ECU are able to represent the full engine power. Differences
arise only in the efficiency of the engine.
4.1.1) Failure of internal generators
Failure of
Generator 1
If during normal operation (Generator 1 is supplying the EMS)
Generator 1 fails, the ECU automatically switches over to sup-
ply the EMS by using Generator 2.
If the engine is supplied by Generator 2 the engine is able to de-
liver full performance. No performance drop can be recognized
while the engine switches the supply from Generator 1 to Gen-
erator 2.
ATTENTION
If Generator 2 is used for supplying the EMS, the airframe will
not be supplied with electrical power by an internal generator.
This failure condition will be detected by the EMS. Therefore
see section “Failures detected by the EMS” for appropriate
action.
Failure of
Generator 2
If during normal operation (Generator 1 is supplying the EMS)
Generator 2 fails, the ECU is not able to detect this condition.
ATTENTION
If Generator 2 fails the Airframe will not be supplied with electri-
cal power by an internal generator
Aircraft Manufacturer is responsible for defining a procedure for
the failure condition.
Failure of both
Generators
A failure of both Generators (Generator 1/Generator 2) will re-
sult in engine stoppage unless the EMS is not powered by an
external power source (12 V voltage drop between X3 Terminal
1 and Aircraft ground).
Aircraft Manufacturer is responsible for defining a procedure for
this failure condition.
Page 4-4
December 01 2017
BRP-Rotax Effectivity: 915 i A Series
Edition 0 / Rev. 0
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