(2) If the circuit breaker is closed:
- do a check of the wiring for open circuit: . from the GCU 2 pin B/2D to successively the GLC 2 pin B/3, EGIU 2 pin A/12A, GCU 2 pin A/5B, . from the GCU 2 pin A/12D to the EGIU 2 pin A/13A, . from the GCU 2 pin A/12C to the pin X/1 of the current transformer 4XU2, . from the pin X/2 of the current transformer 4XU2 to the ground, . from the GLC2 pin B/5 to the ground (Ref. ASM 24-22/02).
(3) If there is no continuity:
- repair the above defective wiring.
(4) If there is continuity:
- do a check of the EGIU 2 wiring for open circuit from pin A/12A to pin A/13A.
(a) If there is no continuity:
- replace the EGIU-2 (22XU2) (Ref. AMM TASK 24-22-33-000-001) and (Ref. AMM TASK 24-22-33-400-002).
(b) If there is continuity:
- replace the GLC-2 (9XU2) (Ref. AMM TASK 24-22-55-000-001) and (Ref. AMM TASK 24-22-55-400-002).
(c) If the fault continues:
- replace the RELAY-GLC2 AUX CTL (4XU2).
(d) If the fault continues:
- replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
B. Do this operational test to make sure that the system operates correctly.
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits (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, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 283
201-299, 301-399, Aug 01/05 CES
(2) On the ELEC panel 35VU:
- push, release and push again the GEN 2 pushbutton switch (3XU2).
(3) Do the operational test of the GPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
C. Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM display unit:
- get the ELEC page. - the correct electrical parameters of GEN 2 are shown and AC 2 busbar is supplied by GEN 2.
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) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
「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, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 284
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TASK 24-20-00-810-832
Loss of the GEN2 (Failure of the GLC 2)
1. Possible Causes
_______________
- GLC-2 (9XU2)
- GCU-2 (1XU2)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-22-34-000-001
AMM 24-22-34-400-001
AMM 24-22-55-000-001
AMM 24-22-55-400-002
AMM 24-41-00-740-002
AMM 24-41-00-861-002
AMM 24-41-00-862-002
AMM 31-60-00-860-001
AMM 31-60-00-860-002
AMM 71-00-00-710-003
AMM 71-00-00-710-028
ASM 24-22/03
3. Fault Confirmation
__________________
A. Test Not applicable.
Removal of the GCU-1(2) (1XU1, 1XU2)Installation of the GCU-1(2) (1XU1, 1XU2)Removal of the Contactors (9XU1, 9XU2, 11XU1, 11XU2)Installation of the Contactors (9XU1, 9XU2, 11XU1, 11XU2)Operational Test of the Ground power Control Unit (GPCU)Energize the Aircraft Electrical Circuits from Engine 1(2)De-energize the Aircraft Electrical Circuits Supplied from the External PowerEIS Start ProcedureEIS Stop ProcedureEngine Automatic StartEngine Shutdown
NOTE : As the GEN2 was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
「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, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 285
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 電源 1(127)
