4. Fault Isolation
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A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU ENGINE/1/FADEC A/AND EIU 1 2KS1 A04 121VU ENGINE/ENG1/FADEC B/AND EIU 1 4KS1 R41
B. If the test gives the maintenance message EIU 1:
- do a check for 28VDC at EIU 1 (1KS1) pins AC/9, 11.
(1) if there is 28VDC:
- replace the EIU-1 (1KS1) (Ref. AMM TASK 73-25-34-000-040) and (Ref. AMM TASK 73-25-34-400-040).
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(2) If there is no 28VDC:
- do a check for open or short to ground of the aircraft wirings between the EIU 1 (1KS1) and the circuit breakers (2KS1) and (4KS1) pins AC/9, 11.
(a) If there is a short to ground:
- repair the defective wiring(s)
(b) If there is no a short to ground:
- replace the defective C/B-ENGINE/1/FADEC A/AND EIU 1 (2KS1) or the C/B-ENGINE/ENG1/FADEC B/AND EIU 1 (4KS1) (Ref. ASM 73-25/05).
(3) If the fault continues:
- replace the ECU (4000KS) (Ref. AMM TASK 73-21-60-000-001) and (Ref. AMM TASK 73-21-60-400-001).
R C. Do the operational test of the Engine Interface Unit (EIU) through the
R Centralized Fault Display System (CFDS) (Ref. AMM TASK 73-25-34-710-043).
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TASK 73-25-00-810-854
Failure of the EIU on Engine 2
1. Possible Causes
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- EIU-2 (1KS2)
- aircraft wirings
- C/B-ENGINE/2/FADEC A/AND EIU 2 (2KS2)
- C/B-ENGINE/ENG2/FADEC B (4KS2)
- ECU (4000KS)
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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) R AMM 73-25-34-710-043 Operational Test of the Engine Interface Unit ASM 73-25/05
3. Fault Confirmation
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R A. Do the operational test of the Engine Interface Unit (EIU) through the
R Centralized Fault Display System (CFDS) (Ref. AMM TASK 73-25-34-710-043).
4. Fault Isolation
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A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU ENGINE/2/FADEC A/AND EIU 2 2KS2 A05 121VU ENGINE/ENG2/FADEC B 4KS2 Q40
B. If the test gives the maintenance message EIU 2:
- do a check for 28VDC at EIU 2 (1KS2) pins AC/9, 11.
(1) if there is 28VDC:
- replace the EIU-2 (1KS2) (Ref. AMM TASK 73-25-34-000-040) and (Ref. AMM TASK 73-25-34-400-040).
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(2) If there is no 28VDC:
- do a check for open or short to ground of the aircraft wirings between the EIU 2 (1KS2) and the circuit breakers (2KS2) and (4KS2) pins AC/9, 11.
(a) If there is a short to ground:
- repair the defective wiring(s)
(b) If there is no a short to ground:
- replace the defective C/B-ENGINE/2/FADEC A/AND EIU 2 (2KS2) or the C/B-ENGINE/ENG2/FADEC B (4KS2) (Ref. ASM 73-25/05).
(3) If the fault continues:
- replace the ECU (4000KS) (Ref. AMM TASK 73-21-60-000-001) and (Ref. AMM TASK 73-21-60-400-001).
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本文链接地址：A320 Trouble Shooting Manual 排故手册 发动机燃油和控制 2(40)
