TRAINING MANUAL CFM56-5B FAULT DETECTION & ANNUNCIATION 培训手册 CFM56-5B 故障探测与指示(14)

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The SDAC’s digitalize systems data and transmit it to the DMC’s. The SDAC’s receive systems information concerning amber cautions and transmit it to the FWC’s.
The FWC’s receive systems data concerning red warnings and memos, generate messages and activate attention getters. Both FWC’s have the same engine monitoring capability.
The DMC’s use outputs from the FWC’s to display information on the lower part of the EWD.
 
The EVMU provides vibration information to the SDAC’s for real time monitoring on the ECAM and to the DMU for condition monitoring.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION INTERFACES
FAULT DETECTION
& ANNUNCIATION Page 6
Nov 02
  
 
  CFM56-5B TRAINING MANUAL

ECU
CTC-231-009-00 ENGINE DATA DISPLAY PROCESSING
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION INTERFACES
FAULT DETECTION
& ANNUNCIATION Page 7
Nov 02
  
 
  CFM56-5B TRAINING MANUAL

 
ON-BOARD MAINTENANCE SYSTEM
Acquisition of aircraft system data is performed by the Centralized Fault Display System (CFDS). This includes the ECAM to display warnings and system information, the DFDRS, which is an obligatory recording system, the CFDIU and the DMU, which is the main component of the Aircraft Integrated Data System (AIDS).
In each aircraft system computer, a BITE monitors the system and memorizes the failures. After failure detection, the BITE is able to identify the possible failed LRU’s and give a ‘snapshot’ of the system environment when the failure occurred. All information necessary for maintenance and troubleshooting is memorized in NVM.
The ECU is able to distinguish between faults external and internal to the FADEC system. External faults are defined as those detected on aircraft interfaces not dedicated to the FADEC system. External functions include the ADIRU’s, the EIU and aircraft power supplies. All other faults in the system (ECU, HMU, sensors, cables, components, etc..) are considered internal faults.
The main components of the CFDS are the CFDIU, which has a main channel and a standby channel, and the aircraft system BITES. The CFDIU continuously scans the buses from the aircraft systems and if a failure message from a system BITE is present on a bus, the CFDIU copies and stores it.
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION
 
  CFM56-5B TRAINING MANUAL

 

 
DMU (AIDS)
CTC-231-010-00 ON-BOARD MAINTENANCE
EFFECTIVITY
ALL CFM56-5B ENGINES FOR A319-A320-A321
CFMI PROPRIETARY INFORMATION INTERFACES
FAULT DETECTION
　
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