TRAINING MANUAL CFM56-5B FAULT DETECTION & ANNUNCIATION 培训手册 CFM56-5B 故障探测与指示(18)

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The 115Vac, 400Hz supply to each of the ignition exciters is routed from the aircraft, through the EIU and then the ECU, where it is switched on and off to control the operation of the exciters.
The ARINC429 databuses and some aircraft discretes are wired to the engine as simplex connections and split into duplex connections on the engine. The actual split is implemented within the ECU.
 
The aircraft provides the ECU with :
- Altitude.
- Total Air Temperature (TAT).
- Total Air Pressure (Pt).
- Mach number (M0).
From the ADC’s, via ARINC429 serial databuses.
- General aircraft data.
- Idle setting data.
- Engine starting data.
- Autothrust function data.
- Maintenance function data.
From the EIU, via an ARINC429 serial databus.
- Throttle lever position in terms of electrical resolver angle. The resolver is mechanically linked to the throttle levers in the cockpit.
 
Selected hardwired discrete signals.
- Engine position discretes, which are used by the
ECU to assign the SDI on ARINC outputs.
- Autothrust engagement and disconnect.
- Master lever reset.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION ECU SIGNALS
FAULT DETECTION
& ANNUNCIATION Page 12
Nov 02
  
 
  CFM56-5B TRAINING MANUAL

 

 
CTC-231-016-00 AIRCRAFT INPUTS TO THE ECU
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION ECU SIGNALS
FAULT DETECTION
& ANNUNCIATION Page 13
Nov 02
  
 
  CFM56-5B TRAINING MANUAL

 
ECU OUTPUTS
Each ECU channel has 2 independent ARINC429 serial databuses, which interface with the aircraft. There are no differences in the bus outputs, but data which is specific to a channel, such as fault and maintenance data, may differ from channel to channel. Sensor values that are output by the two separate ECU channels will also be slightly different, but within signal tolerance requirements.
Cockpit indication data is output to the aircraft to keep the flight crew informed of the operational status of system components and FADEC system controlled engine parameters.
Maintenance data is output, via the ARINC429 buses to the aircraft maintenance computer. This data provides information to help the ground crew identify system faults and isolate the faults to the correct LRU, or system interface.
Engine condition monitoring parameters are output to the aircraft, via the ARINC buses, as digital equivalents of all sensor inputs to the ECU.
 
Channels A and B deliver constant outputs, irrespective of which channel is in control. Channel switch-over does not affect the output data of the ECU, except for the status indication for the channel in control, items specific to the channel in control and whatever faults caused the switch-over.
　
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