EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-320-321
CFMI PROPRIETARY INFORMATION LEXIS Page 10
Nov 02
CFM56-5B TRAINING MANUAL
ARCHITECTURE
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION ARCHITECTURE
FAULT DETECTION
& ANNUNCIATION Page 1 Nov 02
ENGINE CONTROL SYSTEM System components.
The CFM56-5B engine incorporates a computer-based Full Authority Digital Engine Control (FADEC) system.
CFM56-5B TRAINING MANUAL
Electronic Control Unit (ECU).
The ECU is the prime component of the engine control system.
The engine control system is composed of the following elements :
- Electronic Control Unit (ECU), containing two identical computers, designated channel A & B.
- Hydro-mechanical Unit (HMU), which converts electrical signals from the ECU into hydraulic
pressures to drive the engine’s valves and actuators.
- ECU alternator.
- Engine Identification plug (ID plug).
- Engine pressure, temperature and speed sensors.
- Variable Stator Vane (VSV) actuators. - Variable Bleed Valve (VBV) actuators.
- High Pressure Turbine Clearance Control (HPTCC). - Low Pressure Turbine Clearance Control (LPTCC).
- Transient Bleed Valve (TBV).
- Burner Staging Valve (BSV).
- Fuel Return Valve (FRV).
- Thrust Reverser (TR) control.
- Starter Air Valve (SAV).
- Ignition components / control system.
The ECU governs the engine in response to thrust command inputs from the airplane and provides information to the airplane for flight compartment indication, maintenance reporting and, optionally, engine condition monitoring.
Control system maintenance is assisted by extensive ECU internal software called Built-In-Test-Equipment (BITE), which monitors engine data and ECU status flags to detect engine failures.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION ARCHITECTURE
FAULT DETECTION
& ANNUNCIATION Page 2
Nov 02
CFM56-5B TRAINING MANUAL
IGNITION
FUEL HYDRO
MECHANICAL
UNIT
REVERSER
SOLENOIDS
+ SWITCHES
CTC-231-001-00
STARTER AIR VALVE
STARTER
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