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The FMU also supplies the high-pressure fuel to actuate the VG inlet guide vanes and compressor stator vanes.
FUEL SYSTEM OPERATION
The main fuel ejectors or DC powered boost pumps deliver fuel from the collector tanks via fuel feed manifolds to the en-gines. Engine fuel shutoff valves (SOVs) are installed in the manifold to interrupt the supply of fuel to the engines during a fire. The L (R) ENGINE FIRE switches control the SOVs.
At the engine, the fuel is pressurized, heated, filtered, metered, and distributed to the combustion chamber. All fuel sched-uling is controlled by the FADEC.
Volume 2 Flight Crew Operating Manual May 06/2005 CSP 100-6 REV 2
18-01-04 ENGINE CONTROL SYSTEM
DESCRIPTION
The Honeywell AS907 powerplant is controlled by the full authority digital electronic control (FADEC) system. The FADEC provides a full range of engine control, including thrust reverser control under all steady state and transient engine conditions. The FADEC controls the operation and performance of the engine through three subsystems: fuel con-trol, compressor airflow management, and engine starting/ignition control.
COMPONENTS AND OPERATION FADEC UNIT
Critical functions of the FADEC include:
-Control of engine thrust within the required limits, including control of bleed valves, compressor guide vanes
(CGVs), and nacelle anti-ice bleed flow
-Validates N1, N1 limits, and interstage turbine temperature (ITT)
-Thrust reverser operation
-Overspeed circuits
Each powerplant has its own dual-channel FADEC computer. One FADEC channel operates as the in-control channel and processes information to provide engine control outputs. The other channel operates in standby. The standby channel pro-cesses all the input information but does not provide control output with one exception. Both the in-control and standby channels will respond to an engine overspeed by commanding the shutoff valve in the fuel metering unit to close in order to return the engine to an on-speed condition.
The in-control and standby channels continuously share command and status data through a crosstalk data bus. Should the designated in control channel become unserviceable, the standby channel assumes the in control role.
During normal operations with two serviceable FADEC channels, FADEC software directs the channels to alternate in-con-trol and standby roles on each successive engine start.
FADEC malfunctions are presented as either caution or advisory messages. Each message has a different impact on the dispatch ability of the aircraft.
ELECTRICAL POWER
The PMA ensures FADEC supply when N2 is greater than 45%. For engine starting and whenever N2 is below 45%, the aircraft electrical system supplies power to the FADEC system.
ENGINE IDLE
When the thrust lever is placed at IDLE, the minimum N2 idle rpm is programmed by the FADEC. Idle rpm is dependent upon atmospheric information, bleed-air loading and phase of flight.
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