3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the GEN2 was set to OFF because a true failure, the fault
____
confirmation is not necessary.
4. Fault Isolation
_______________
**ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
A. If the fault symptom is identified by the maintenance message CHECK BTC2 PIN D, E, F, R, P,N SHORT TO GROUND and by the upper ECAM DU warning GEN2 FAULT:
- do a check of the feeder for short to ground between respectively: . the pins A/R, A/P, A/N of the GLC2 and the main bus,
「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 233
201-299, 301-399, Aug 01/05 CES
. the pins A/M, A/L, A/K of the GLC2 and the pins A/D, A/E, A/F of the
BTC2,
. the pins A/G, A/H, A/J of the BTC2 and the pins A/J, A/H, A/G of the
APU GLC (Ref. ASM 24-22/02).
(1) If the wiring is not correct:
- repair it.
(2) If the wiring is correct:
- do a check of the IDG2 feeders for intermittent short to ground between respectively the pins A/T1, B/T2, C/T3 of the IDG2 and the pins A/D, A/E, A/F of the GLC2.
(3) If the wiring is not correct:
- repair it.
(4) If the wiring is correct:
- replace the engine IDG2 (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
(5) If the fault continues:
- do a check and repair the wiring between respectively the pins A1, A6, A7, A8 of the IDG2 and the pins B/13D, B/13A, B/13B, B/13C of the GCU2.
**ON A/C 063-099, 106-149, 153-199, 206-299, 301-399,
A. If the fault symptom is identified by the maintenance message CHECK BTC2 PIN D, E, F, R, P,N SHORT TO GROUND and by the upper ECAM DU warning GEN2 FAULT:
- do a check of the feeder for short to ground between respectively: . the pins 4, 5, 6 of the module 30XN2 and the main bus, . the pins 10, 11, 12 of the module 30XN2 and the pins 10, 11, 12 of the module 29XN (Ref. ASM 24-22/02).
(1) If the wiring is not correct:
- repair it.
(2) If the wiring is correct:
- do a check of the IDG2 feeders for intermittent short to ground between respectively the pins A/T1, B/T2, C/T3 of the IDG2 and the pins 1, 2, 3 of the module 30XN2.
(3) If the wiring is not correct:
- repair it.
(4) If the wiring is correct:
- replace the engine IDG2 (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
「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 234
201-299, 301-399, Aug 01/05 CES (5) If the fault continues:
- do a check and repair the wiring between respectively the pins A1, A6, A7, A8 of the IDG2 and the pins B/13D, B/13A, B/13B, B/13C of the GCU2.
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 panel 35VU:
- push, release and push again the GEN2 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).
(5) 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 GEN2 are shown and AC2 busbar is supplied by GEN2.
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 235 中國(guó)航空網(wǎng) m.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 1(108)
