- repair it.
(2) If the wiring is correct:
- replace the SENSOR-TDC AC,2 (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 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).
「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 275
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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 276
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-829
Loss of GEN 2 (Failure of the Wiring of the Current Transformers 42XU2 and 42XU4)
1. Possible Causes
_______________
- IDG (4000XU)
- GCU-2 (1XU2)
- 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
from the External Power
EIS Start Procedure
Engine Automatic Start
Engine Shutdown
NOTE : As the GEN 2 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 277
201-299, 301-399, Aug 01/05 CES
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message CHECK CT 42XU2 42XU4 GCU 1 PIN B11A TO B11D WIRING and the upper ECAM DU warning GEN 2 FAULT:
- Do a check of the wiring for open circuit between respectively: . the pins A/1, A/2, A/3, A/4 of the current transformer 42XU4 and: .. the pins B/11A, B/11B, B/11C, B/11D of the GCU 2, .. the pins A/1, A/2, A/3, A/4 of the current transformer 42XU2, . the pins A/1, A/6, A/7, A/8 of the IDG 2 and the pins B/13D, B/13A, B/13B, B/13C of the GCU 2 (Ref. ASM 24-22/01).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 1(124)
