- Replace the engine.
NOTE : If the high N2 vibes reported are greater than 5.5 CPU but
____ in order of more than a minute and repeatable during flight or subsequent flights and trouble shooting have not found any defect, engine has to be scheduled for immediate removal. CFM is to be contacted to allow an aircraft dispatch for returning to the main base or base suitable for engine change.
NOTE : HP unbalance is the first cause of core vibration, not
____ perceptible through trouble shooting actions. The presence of high N2 requires the engine removal for root cause identification at shop level.
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Vibration Indications Fault
1. Possible Causes
_______________
- EVMU (2EV)
- aircraft wiring
- C/B-ENGINE/ENG1 AND 2/EVMU (1EV)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 77-32-34-000-042 Removal of the Engine Vibration Monitoring Unit (EVMU) AMM 77-32-34-400-042 Installation of the Engine Vibration Monitoring Unit
(EVMU) AMM 77-32-34-710-040 Operational Check of EVMU through CFDS ASM 77-32/02
3. Fault Confirmation
__________________
A. Do the operational test of the Engine Vibration Monitoring Unit (EVMU) through the Centralized Fault Display System (CFDS) (Ref. AMM TASK 77-32-34-710-040).
4. Fault Isolation
_______________
A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------
121VU ENGINE/ENG1 AND 2/EVMU 1EV R44
B. If the fault symptom is identified by ENG VIB SYS FAULT message on the upper ECAM warning display unit:
- do a check of the circuit breaker 1EV status.
(1) If the circuit breaker is open:
- close the circuit breaker 1EV.
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- do a check for 115VAC on the EVMU (Ref. ASM 77-32/02).
(a) If there is 115VAC:
- replace the EVMU (2EV), (Ref. AMM TASK 77-32-34-000-042) and (Ref. AMM TASK 77-32-34-400-042).
(b) If there is no 115VAC:
- do a check and repair the aircraft wiring between the breaker 1EV to the EVMU (2EV) (Ref. ASM 77-32/02).
1 If the fault continues:
_
- replace the C/B-ENGINE/ENG1 AND 2/EVMU (1EV)
C. Do the check given in Para. 3.A.
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TASK 77-00-00-810-874
Loss of the Channel A of the FADEC on Engine 1
1. Possible Causes
_______________
- EIU-1 (1KS1)
- ECU (4000KS)
- harness J1
- aircraft wiring
- C/B-ENGINE/1/FADEC A/AND EIU 1 (2KS1)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 71-00-00-710-006 Minimum Idle Check AMM 73-21-60-000-001 Removal of the Electronic Control Unit (ECU)(4000KS) AMM 73-21-60-400-001 Installation of the Electronic Control Unit
(ECU)(4000KS) AMM 73-25-34-000-040 Removal of the Engine Interface Unit (EIU) (1KS1,1KS2) AMM 73-25-34-400-040 Installation of the Engine Interface Unit (EIU) (1KS1,1KS2) AMM 73-29-00-710-040 Operational Test of the FADEC on the ground (with
Engine Motoring)
ASM 73-25/05
ASM 73-25/08
3. Fault Confirmation
__________________
A. Test
(1) Do the operational test of the FADEC 1A on the ground (with engine motoring) (Ref. AMM TASK 73-29-00-710-040).
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