POWER UP
POWER UP TEST
FADEC TEST
THRUST REVERSER TEST
IGNITION TEST
CTC-231-003-00 TESTS
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION ARCHITECTURE
FAULT DETECTION
& ANNUNCIATION Page 7
Nov 02
CFM56-5B TRAINING MANUAL
ENGINE CONTROL SYSTEM Electronic Control Unit (ECU).
The ECU has two channels, A and B, and both channels are capable of controlling the engine.
The two channels are identical and permanently operational, but they operate independently from each other. Each channel has a full complement of sensors, interfaces to the engine and aircraft, central processor and output drivers.
As well as continuously checking and processing their own inputs, the channels compare each others data over a Cross Channel Data Link (CCDL), to ensure that there are no anomalies.
The two ECU channels operate their output drivers on an active/standby principle. Both channels always
receive inputs and process them, but only the channel in control, called the Active channel, delivers control
outputs (solenoids/torque motors). The other is called the Standby channel.
The purpose of the dual-redundant architecture is to minimize the effects of control system faults on the engine operation.
Channel selection and fault strategy.
Active and Standby channel selection is performed at ECU power-up and during operation.
Active and Standby selection is based upon the health of the channels and each channel determines its own health status. The healthiest is selected as the Active channel.
When both channels have an equal health status, active/ standby channel selection alternates with every engine start, if N2 was greater than 11,000 RPM during the last run.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION ARCHITECTURE
FAULT DETECTION
& ANNUNCIATION Page 8
Nov 02
CFM56-5B TRAINING MANUAL
CTC-231-004-00 ECU DESIGN 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：TRAINING MANUAL CFM56-5B FAULT DETECTION & ANNUNCIATION 培训手册 CFM56-5B 故障探测与指示(10)
