Full Authority Digital Engine Control (FADEC)
The
F
ADEC
is
a full dual-channel (Channel A and B), dual-processor digital
engine control system with segregated control, redundant interfaces and
protection signals.
The FADEC performs the full electrical control of the engine power by adjusting
the fuel flow through the Fuel Control Unit (FCU) and the propeller blade angle
through the Propeller Control Unit (PCU) based on:
- THROTTLE position,
- ambient conditions,
- information from engine sensors and airframe data.
The FADEC includes several control loops to control:
- engine torque (TRQ) at reference propeller speed,
- Ng at idle, during engine accelerations/decelerations, in reverse range or in
degraded mode.
The FADEC sends the engine parameters including fault messages to the
avionics.
The FADEC is installed in the front cargo compartment and is connected to the
engine accesories through the main engine harness.
When the engine is running, the FADEC is electrically supplied by the permanent
magnet alternator – refer to
Paragraph Engine Accessories .
If the permanent magnet
alternator cannot provide enough electrical power to the
FADEC, the airplane electrical system electrically supplies the FADEC as follows:
- Channel A is supplied by the ESS BUS 1 bar and protected by the FADEC
CH.A breaker,
- Channel B is supplied by the BUS 2 bar and protected by the FADEC CH.B
breaker.
Section 7
Description
Pilot's Information Manual
PIM TBM 960 - Edition 0
Rev. 02
Page 7.6.4
PIM - DO NOT USE FOR FLIGHT OPERATIONS
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