1(2) AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2) ASM 24-23/01
3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the APU GEN was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message CHECK CT 42XS GCU APU PIN B11A TO B11B WIRING and the upper ECAM DU warning APU GEN FAULT:
- Do a check of the wiring for open circuit between respectively: . the pins 1 to 4 of the APU generator AC current transformer and the APU GCU pins B/11A to B/11D . the pins B/13A to B/13D of the APU GCU and the pins A/6, A/7, A/8, A/1 of the APU GEN (Ref. ASM 24-23/01).
(1) If the wiring is not correct:
- repair it.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page A208
201-299, 301-399, Aug 01/05 CES (2) If the wiring is correct:
- Do an impedance check of the internal wiring of the AC current transformer between pins A/1 and successively pins A/2, A/3 and A/4 then do a check for open circuit between pins A/6 and successively A/1, A/2, A/3, A/4.
NOTE : The normal impedance between pin A/4 and each other pin is
____ 10.15 Ohms plus or minus 3.45 Ohms at 25.C.
(a) If the values are out of the specified limits:
- repair the CT-AC, APU GEN (42XS) (Ref. AMM TASK 24-23-17-000-001) and (Ref. AMM TASK 24-23-17-400-001).
(b) If the values are in the specified limits:
- Do an impedance check of the internal wiring of the APU generator between pin A/1 and successively pins A/6, A/7 and A/8, then do a check for open circuit between pins A/1, A/6, A/7, A/8 and the case.
NOTE : The normal impedance between pin A/1 and each other pin is
____
24.1 Ohms plus or minus 2.41 Ohms at 25.C.
1_ If the values are out of the specified limits:
- replace the GEN-APU (8XS) (Ref. AMM TASK 24-23-51-000-001)
and (Ref. AMM TASK 24-23-51-400-001) .
2_ If the values are in the specified limits:
- replace the GCU-APU (1XS) (Ref. AMM TASK 24-23-34-000-001)
and (Ref. AMM TASK 24-23-34-400-001) .
B. Make sure that the aircraft electrical circuits operate correctly in APU configuration.
(1) Energize the aircraft electrical circuits from the APU (Ref. AMM TASK 24-41-00-861-002).
(2) De-energize the aircraft electrical circuits from the APU (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 A209
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-844
Failure of the APU Generator
1. Possible Causes
_______________
- GEN-APU (8XS)
- GCU-APU (1XS)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-23-34-000-001 Removal of the GCU-APU (1XS) AMM 24-23-34-400-001 Installation of the GCU-APU (1XS) AMM 24-23-51-000-001 Removal of the APU Generator 8XS AMM 24-23-51-400-001 Installation of the APU Generator 8XS AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
APU AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the APU AMM 49-91-41-200-001 Remove and discard Alternator Scavenge Filter Element (8069KM) (GTCP 36-300) AMM 49-91-41-920-001 Remove and Discard Pressure Oil Filter-Element (8076KM) (APS 3200) AMM 49-91-41-920-002 Replace AC-Generator Scavenge Filter-Element (8069KM)
(APS 3200) AMM 49-91-45-200-002 Remove and discard Lube Filter Element (GTCP 36-300) ASM 24-23/01
3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the APU GEN was set to OFF because of a true failure, the fault 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 1(136)
