F 『
E C F M E
E E
E 56 E
E E
B. If the fault symptom is identified by the upper ECAM warning ENG2 FADEC A FAULT and the test of the FADEC 2A gives no maintenace message:
- disconnect the connector J1 from the ECU (4000KS) and do a check for 28VDC at pin J1/13 with the FADEC GND PWR pushbutton switch released (the ON legend is on).
(1) If there is 28VDC:
- replace the ECU (4000KS) (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) pin AC/11 (Ref. ASM 73-25/05).
(a) If there is 28VDC:
- do a check for open or short to ground at the harness J1 between the EIU 2 (1KS2) and the ECU (4000KS), pin AC/7 to pin J1/13. Replace the harness J1 if necessary.
(b) If there is no 28VDC:
1_ If the fault continues:
- make sure that there is no ground signal at EIU 2 (1KS2) pin
AA/5B (Ref. ASM 73-25/08).
2_ 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).
- do a check for open or short to ground at the aircraft wiring between the circuit breaker (2KS2) and EIU 2 (1KS2) pin AC/11.
1 If there is a short to ground:
_
- repair the above wiring. 2 If there is no short to ground:
_ - replace the C/B-ENGINE/2/FADEC A/AND EIU 2 (2KS2).
(c) Make sure that 28VDC supplies the ESS bus (Ref. ASM 73-25/05).
C. Do a minimum idle check (Ref. AMM TASK 71-00-00-710-006).
F 『 EEFF : ALL E ∞∞77-00-00∞∞∞∞∞∞∞∞∞∞Page 279
E E Nov 01/04 ERE
ECES
F 『
E C F M E
E E
E 56 E
E E
TASK 77-00-00-810-879
Loss of the Channel A of the FADEC on Engine 2
1. Possible Causes
_______________
- harness J9
- ECU (4000KS)
- control alternator
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 71-00-00-710-006 Minimum Idle Check AMM 73-21-30-000-002 Removal of the Control Alternator AMM 73-21-30-400-002 Installation of the Control Alternator AMM 73-21-50-000-008 Removal of the J9 Harness AMM 73-21-50-400-008 Installation of the J9 Harness 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 73-29-00-710-040 Operational Test of the FADEC on the ground (with Engine Motoring) ASM 73-25/18
3. Fault Confirmation
__________________
A. Test
(1) 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
_______________
A. If the fault symptom is identified by:
- the upper ECAM warning ENG2 FADEC A FAULT
- no CFDS maintenance message after the test of the FADEC 2A
- the crew observation N2 higher than 15% on ground or in flight
(1) do a check for open or short to ground of the harness J9 between the ECU (4000KS) and the control alternator pins J9/4, 5, 13, 14, 15 to pins J9/2, 3, 4, 5 (Ref. ASM 73-25/18).
(a) If the wiring is not correct:
- repair the above wiring.
F 『 EEFF : ALL E ∞∞77-00-00∞∞∞∞∞∞∞∞∞∞Page 280
E E Nov 01/04 ERE ECES
F 『 E C F M E E E E 56 E E E (b) If the wiring is correct:
- disconnect the harness J9 from the ECU (4000KS) and do a check of the ECU cable resistance between: . pins 5 and 13 (< 1 Ohm) . pins 5 and 14 (< 1 Ohm) . pins 5 and 15 (< 1 Ohm) . pins 5 and 4 (> 10 Megohms) . pin 5 and the ground (> 10 Megohms).
1 If the resistance values are in the specified limits:
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 發動機指示(98)
