- repair it.
(2) If the wiring is correct:
- replace the SENSOR-TDC AC,1 (Ref. AMM TASK 24-22-18-000-001) and (Ref. AMM TASK 24-22-18-400-001).
**ON A/C 063-099, 106-149, 153-199, 206-299, 301-399,
A. If the fault symptom is identified by the CFDS message CHECK IDG 1 1999VT WIRING and the upper ECAM DU warning GEN 1 FAULT:
- do a check for open circuit on any of the two parallel cables between respectively the IDG 1 pins T/1, then T/2 and T/3 and the module 30XN1 pins 1, 2, 3 (Ref. ASM 24-22/01).
(1) If the wiring is not correct:
- repair it.
(2) If the wiring is correct:
- replace the SENSOR-TDC AC,1 (Ref. AMM TASK 24-22-18-000-001) and (Ref. AMM TASK 24-22-18-400-001).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
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).
(2) On the ELEC panel 35VU:
- push, release and push again the GEN 1 pushbutton switch (3XU1).
(3) Do the operational test of the GPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003).
「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 252
201-299, 301-399, Aug 01/05 CES
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 1 are shown and AC 1 busbar is supplied by GEN 1.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 1 (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 253
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-821
Loss of the GEN 1 (Failure of the Wiring of the Current Transformers 42XU1 and 42XU3)
1. Possible Causes
_______________
- IDG (4000XU)
- GCU-1 (1XU1)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-21-51-000-040
AMM 24-21-51-400-040
AMM 24-22-17-000-001
AMM 24-22-17-400-001
AMM 24-22-34-000-001
AMM 24-22-34-400-001
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 71-00-00-710-003
AMM 71-00-00-710-028
ASM 24-22/01
3. Fault Confirmation
__________________
A. Test Not applicable.
Removal of the Integrated Drive Generator -IDG
1(2),(4000XU)
Installation of the Integrated Drive Generator -IDG
1(2),(4000XU)
Removal of the AC Current Transformers (41XU1, 41XU2,
42XU1, 42XU2, 42XU3 and 42XU4)
Installation of the AC Current Transformers (41XU1,
41XU2, 42XU1, 42XU2, 42XU3 and 42XU4)
Removal of the GCU-1(2) (1XU1, 1XU2)
Installation of the GCU-1(2) (1XU1, 1XU2)
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
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 電源 1(115)
