R **ON A/C 401-499,
R A. If the test confirms the fault:
R - replace the P/BSW-ELEC/GEN 2 (3XU2).
R (1) If the fault continues:
R - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref.
R AMM TASK 24-22-34-400-001).
R (a) If the fault continues:
R - do a check and repair the wiring between:
R . the pin AA/1C of the GCU 2 and the pin D3 of the ELEC/GEN 2
R pushbutton switch (3XU2)
R . the pins AA/2G and AA/4E of the GCU 2 and the pins D1 and D2
R of the ELEC/GEN 2 pushbutton switch
R . the pin AB/10J of the GCU 2 and the pin C3 of the ELEC/GEN 2
R pushbutton switch
R . the pin C1 of the ELEC/GEN 2 pushbutton switch and the ground
R (Ref. ASM 24-22/03).
R **ON A/C ALL
B. Do the test given in Para. 3.
5. Close-up________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 2 (Ref. AMM TASK 71-00-00-710-028).
(2) Put the aircraft back to its initial configuration.
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
TASK 24-22-00-810-813
Failure of the Connection between the EGIU2 and the APU Generator Line
Contactor (GLC)
1. Possible Causes
_______________
- EGIU-2 (22XU2)
- C/B - APU GEN/EGIU2/115VAC (23XS)
- wiring between the pin AB/1D of the EGIU2 (22XU2) and the pin A/D of the APU GLC (3XS)
- wiring between the pin AB/1D of the EGIU2 (22XU2) and the pin 9 of the module 29XN.
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the APU AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the APU
AMM 31-60-00-860-001 EIS Start Procedure
ASM 24-23/01
3. Fault Confirmation
__________________
A. Job Set-up
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits from the APU (Ref. AMM TASK 24-41-00-861-002).
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-22-00∞∞∞∞∞∞∞∞∞∞Page 237
201-299, 301-399, Aug 01/05 CES
B. Test
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: On the lower ECAM display unit:
- push the ELEC key to get the - in the APU GEN box, the electrical
ELEC page. parameters come into view as follows: . normal AC load, . no voltage, . no frequency.
4. Fault Isolation
_______________
**ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
A. If the test confirms the fault:
- do a check of the status of the C/B - APU GEN/EGIU2/115VAC (23XS).
(1) If it is open:
- close it.
(a) If it trips:
- do a check and repair the wiring between the pin AB/1D of the EGIU2 (22XU2) and the pin A/D of the APU GLC (3XS).
(b) If it does not trip:
- do a check for continuity of the wiring between the circuit breaker (23XS) and the pin A/D of the APU GLC (3XS). (Ref. ASM 24-23/01).
(2) If the fault continues: 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 電源 2(143)
