Engine power control : Set the power as required by
using either the engine power
lever or the ENG TRIM toggle
switch on the collective control.
Engine oil pressure : Check.
CROSS FEED switch : NORM (bar vertical)
ENGINE CONTROL UNIT MALFUNCTIONS
There are two levels of control system malfunctions: ″non-critical″ and
″critical″.
″Non-critical″ malfunction is defined every fault condition which allows the
control system to continue operating in AUTO mode with minimal operational
impact.
Major non-critical malfunctions (i.e. PMS failure, thermocouple failure, etc.)
are announced by specific caution messages (i.e. #1 PMS, #1 TOT LIMITER,
TRQ LIMITER, etc.) in order to make the pilot aware of the relative
degradation and to let him take the necessary precautions.
All other non-critical malfunctions are announced by ECU MAINT message
only on ground, before starting or after engine shutdown, while in flight they
are automatically accommodated by the logic of the system to provide
continued AUTO mode function.
″Critical″ malfunction is defined every fault condition, announced by ECU
FAIL warning message and MAN legend, that cannot be accommodated and
having as a consequence the ECU reversion to MANUAL mode.
In this case the FMM tracking system will maintain N1 ±2%.
Following an ECU FAIL the engine with the serviceable ECU will maintain
rotor governing within its limits.
Both ECU malfunctions, ″non-critical″ and ″critical″, can be cleared by
cycling the ENG GOV switch from AUTO to MANUAL and back to AUTO
if the source of the fault has been eliminated.
RFM A109E
3-28 R.A.I. Approved
Rev. 18
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