3. Fault Confirmation
__________________
A. Do the operational test of the FADEC 2A on the ground (with engine motoring) (Ref. AMM TASK 73-29-00-710-040).
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
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B. If the test gives the maintenance message EIU, ECU (CR3 DIODE):
- disconnect the connectors J1 and J2 from the ECU (4000KS) and do a check for 28VDC at pins J1/13 and J2/13 with the FADEC GND PWR pushbutton switch released (the ON legend is on) (Ref. ASM 73-25/05).
(1) If there is 28VDC:
- replace the EIU-2 (1KS2) (the most possible failure is the EIU 28V relay) (Ref. AMM TASK 73-25-34-000-040) and (Ref. AMM TASK 73-25-34-400-040)
- replace the ECU (4000KS) (the most possible failure is an ECU diode) (Ref. AMM TASK 73-21-60-000-001) and (Ref. AMM TASK 73-21-60-400-001).
(2) If there is no 28VDC:
- do a check for 28VDC at EIU 2 (1KS2) pins AC/9, 11 (Ref. ASM 73-25/05).
(a) If there is no 28VDC:
- do a check for open or short to ground at the aircraft wiring from the circuit breakers (2KS2) and (4KS2) to EIU 2 (1KS2) pins AC/9, 11.
1 If there is a short to ground:
_ - repair the above wiring.
2 If there is no short to ground:
_
- replace the defective C/B-ENGINE/2/FADEC A/AND EIU 2 (2KS2) or C/B-ENGINE/ENG 2/FADEC B (4KS2).
(b) If there is 28VDC:
- do a check for open or short to ground at the harnesses J1 and J2 between the EIU 2 (1KS2) and the ECU (4000KS), pins AC/2, 7 to pins J1/13, J2/13. Replace the harness J1 or J2 if necessary (Ref. ASM 73-25/05).
(c) If the fault continues:
- make sure that there is no ground signal at EIU 2 (1KS2) pin AA/5B (Ref. ASM 73-25/08).
(d) If the fault continues:
- replace the EIU-2 (1KS2) (Ref. AMM TASK 73-25-34-000-040) and (Ref. AMM TASK 73-25-34-400-040).
C. Do the test given in Para. 3.A.
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Loss of the Zone Controller Data on the ARINC Bus from the EIU to the FADEC on Engine 1
1. Possible Causes
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- EIU-1 (1KS1)
- harness J3 from the EIU-1 (1KS1) to the ECU (4000KS)
- CONT-ZONE TEMPERATURE (8HK)
- ECU (4000KS)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 21-63-34-000-001 Removal of the Zone Controller (8HK)
AMM 21-63-34-400-001 Installation of the Zone Controller (8HK)
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 73-25-34-710-043 Operational Test of the Engine Interface Unit AMM 73-29-00-710-040 Operational Test of the FADEC on the Ground (with
Engine non Motoring) ASM 73-25/06
3. Fault Confirmation
__________________
A. Do the operational test of the FADEC 1B on the ground (with engine non motoring) (Ref. AMM TASK 73-29-00-710-040).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 發動機燃油和控制 2(69)
