DOC AIRBUS | AMM A320FCONTROLLING - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
1. General
The Full Authority Digital Engine Control (FADEC) gives full range of engine control to get stable condition and transient engine performance when operated together with the aircraft sub-systems. The FADEC consists of one EEC part per channel and the peripherals that follow:
** ON A/C NOT FOR ALL The Full Authority Digital Engine Control (FADEC) gives full range of engine control to get stable condition and transient engine performance when operated together with the aircraft sub-systems. The FADEC consists of one EEC part per channel and the peripherals that follow:
- Fuel Metering Unit (FMU)
- Split Control Unit (SCU)/Servo Valve Assembly (SVA)
- T12 sensor
- T25 sensor
- T3 sensor
- Fuel temperature transducer
- Fuel manifold pressure transducer
- Permanent magnet alternator
- Pressure Sub System (PSS) box and sensor
- Electronic Engine Control (EEC)
Control - Components2. Component Description
A. Fuel Metering Unit (FMU)
The FMU changes the EEC "channel in control" electrical signals to hydraulic flows through an internal electro-hydraulic servo valve (EHSV). The FMU consists of an EEC controlled sub-system to give thrust-control malfunction accommodation (TCMA).
The FMU is installed on the fan frame.
The FMU changes the EEC "channel in control" electrical signals to hydraulic flows through an internal electro-hydraulic servo valve (EHSV). The FMU consists of an EEC controlled sub-system to give thrust-control malfunction accommodation (TCMA).
The FMU is installed on the fan frame.
B. Split Control Unit (SCU)/Servo Valve Assembly (SVA)
The SCU/SVA has two main functions:
The SCU/SVA has two main functions:
- To change the EEC electrical signals to hydraulic flows
- To give PMV feedback to both the EECs.
The SCU/SVA is installed on the core case.
C. T12 Sensor
The T12 sensor measures the total air temperature at the engine inlet.
T12 sensor is installed in the flow path, on the air inlet duct at 12 degree ALF position below a specified access door.
The T12 sensor measures the total air temperature at the engine inlet.
T12 sensor is installed in the flow path, on the air inlet duct at 12 degree ALF position below a specified access door.
D. T25 Sensor
The T25 sensor measures the total gas temperature at the inlet of the high pressure compressor.
T25 sensor is installed in the primary flow path, on the fan hub between 3 and 4 O'clock ALF position.
The T25 sensor measures the total gas temperature at the inlet of the high pressure compressor.
T25 sensor is installed in the primary flow path, on the fan hub between 3 and 4 O'clock ALF position.
E. T3 Sensor
The T3 sensor gives the temperature of the compressor discharge airflow to both the EECs.
The T3 sensor is installed on the combustor diffuser nozzle (CDN) case.
The T3 sensor gives the temperature of the compressor discharge airflow to both the EECs.
The T3 sensor is installed on the combustor diffuser nozzle (CDN) case.
F. Fuel Temperature Transducer
The fuel temperature transducer gives fuel temperature signal information to both the EECs. The engine fuel temperature transducer is a dual channel resistive temperature device (RTD). One output signal is routed to EEC channel A and the second output signal is routed to EEC channel B.
The engine fuel temperature transducer is installed in a dry well fitting, which is a part of the fuel line.
The fuel temperature transducer gives fuel temperature signal information to both the EECs. The engine fuel temperature transducer is a dual channel resistive temperature device (RTD). One output signal is routed to EEC channel A and the second output signal is routed to EEC channel B.
The engine fuel temperature transducer is installed in a dry well fitting, which is a part of the fuel line.
G. Fuel Manifold Pressure Transducer
The fuel manifold pressure transducer senses the pilot enriched manifold pressure at the exit of the SCU/SVA.
The fuel manifold pressure transducer is installed on the SCU/SVA on the engine.
The fuel manifold pressure transducer senses the pilot enriched manifold pressure at the exit of the SCU/SVA.
The fuel manifold pressure transducer is installed on the SCU/SVA on the engine.
H. Permanent Magnet Alternator (PMA)
The PMA gives electrical power to each EEC.
The PMA stator is installed on the accessory gearbox.
The PMA gives electrical power to each EEC.
The PMA stator is installed on the accessory gearbox.
I. Pressure Sub-System (PSS) Box and Sensor
The PSS has two main functions:
The PSS has two main functions:
- To do signal conversions of the pressure system inputs and communicate with each EEC
- To give cross-channel data link (CCDL) backup.
The pressure sub system (PSS) box and sensor is installed with vibration isolators on the brackets on the fan case.
J. Rating Plug
The rating plug gives the engine rating, thrust bump and N1 trim levels.
The rating plug is installed on the PSS box.
The rating plug gives the engine rating, thrust bump and N1 trim levels.
The rating plug is installed on the PSS box.
K. Electronic Engine Control (EEC)
The EEC has two main functions:
The EEC has two main functions:
- To process system input information and do calculations and comparisons to stored memory information
- To adjust the fuel and air systems to give the thrust and engine airflow necessary for cooling.
The EECs are installed with vibration isolators on the brackets on the fan case. There are two identical EECs on each engine.