Shared May 3, 2018
In order to increase engine (CFM56-5B) reliability and efficiency, the Full Authority Digital Engine Control (FADEC) gives the full range of engine control to achieve steady state and transient engine performances when operated in combination with aircraft subsystems.
Each engine is controlled by an ECU, a dual channel computer located on the engine fan case. The ECU controls the engine during start and all operations. The ECU manages engine thrust and protects against overspeed and overtemperature by controlling the engine sub-systems. The ECU also monitors all engine subsystems and sensors for failure. When the engine is running, power for FADEC operation is supplied by a dual-output FADEC alternator driven by the gearbox.
The FADEC system has a dual channel ECU and the following peripherals:
- hydromechanical unit,
- dedicated FADEC alternator,
- compressor control systems,
- clearance control systems,
- start system (starter shutoff valve, ignition exciters),
- thrust reverser system,
- oil/fuel temperature control system,
- fuel return valve,
- engine sensors,
- electrical harnesses.
The ECU interfaces with various aircraft systems. Essential communication with the ECU (thrust lever position, air data, etc.) is direct to and from the applicable systems and controls. Non-essential communication (autothrust, Centralized Fault Display System (CFDS), etc) is routed through the Engine Interface Unit (EIU) of each engine. The EIUs interface with various aircraft circuits and systems. The data is then transmitted in a single stream to each ECU channel.
Engine vibration monitoring is accomplished by the Engine Vibration Monitoring Unit (EVMU). The EVMU collects vibration data from both engines. The vibration information is displayed on the ECAM and is also available through the CFDS for troubleshooting.
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