NOTE : As the GEN 1 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 259
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4. Fault Isolation
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A. If the fault symptom is identified by the CFDS message CHECK GLC 1 AND/OR CONTROL CKT and the upper ECAM DU warning GEN 1 FAULT:
- do a check of the status of the GCU 1 circuit breaker.
(1) If the circuit breaker is open:
- refer to (Ref. TASK 24-20-00-810-804).
(2) If the circuit breaker is closed:
- do a check of the wiring for open circuit: . from the GCU1 pin B/2D to the pin A/D2 of the GLC1 AUX CTL relay, then the EGIU1 pin A/12A, then the GCU1 pin A/5B (the ELEC/GEN1 pushbutton switch must be pushed), . from the GCU1 pin A/12D to the EGIU1 pin A/13A, . from the GCU1 pin A/12C to the pin A/X1 of the GLC1 AUX CTL relay (the ELEC/GEN1 pushbutton switch must be pushed), . from the pin D1 of the GLC1 AUX CTL relay to the GLC1 pin B/3, . from the pin A/X2 of the GLC1 AUX CTL relay to the ground (Ref. ASM 24-22/02), . from the GLC1 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 1 wiring for open circuit from pin A/12A to pin A/13A.
(a) If there is no continuity:
- replace the EGIU-1 (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-1 (9XU1) (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-GLC 1 AUX CTL.
(d) If the fault continues:
- replace the GCU-1 (1XU1) (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).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 260
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(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).
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
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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).
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TASK 24-20-00-810-824
Loss of the GEN 1 (Failure of the GLC 1)
1. Possible Causes
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- GLC-1 (9XU1)
- GCU-1 (1XU1) 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 1(118)
