(2) 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).
(3) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-22-00∞∞∞∞∞∞∞∞∞∞Page 255
201-299, 301-399, Aug 01/05 CES
B. Test
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel, push
the ELEC key (on the lower ECAM
DU, the ELEC page comes into
view).
On the lower ECAM DU:
- the GEN2 does not supply the AC2 busbar. On the upper ECAM DU:
- GEN2 OFF message does not come into view with the GEN2 pushbutton switch pushed (ON configuration).
4. Fault Isolation
_______________
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-228, 301-302,
A. If the test confirms the fault:
(1) Do a check of the resistance of the IDG2 MPU coil between pin B/1 and pin B/2 (17.5 Ohms plus or minus 3.5 Ohms at 25 deg.C 77 deg.F.).
(2) If the resistance values are out of the specified limits:
- replace the IDG2 (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
B. Do the test given in para. 3.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 2 (Ref. AMM TASK 71-00-00-710-043).
(2) Put the aircraft back to its initial configuration.
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002)
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-22-00∞∞∞∞∞∞∞∞∞∞Page 256
201-299, 301-399, Aug 01/05 CES
R **ON A/C 401-499,
R TASK 24-22-00-810-819 R Failure of the Current Transformer 1 R 1. Possible Causes
_______________
R - IDG (4000XU) R - CT (51XU1) R - GCU-1 (1XU1) R - wiring
R 2. Job Set-up Information
______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION R -------------------------------------------------------------------------------
R AMM 24-21-51-000-040 R R AMM 24-21-51-400-040 R R AMM 24-22-17-000-001 R R AMM 24-22-17-400-001 R R AMM 24-22-34-000-001 R AMM 24-22-34-400-001 R AMM 24-41-00-740-002 R AMM 24-41-00-861-002 R R AMM 24-41-00-862-002 R R AMM 31-60-00-860-001 R AMM 31-60-00-860-002 R AMM 71-00-00-710-003 R AMM 71-00-00-710-028 R ASM 24-22/01
R 3. Fault Confirmation
__________________
R A. Test
R 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, 51XU1, 51XU2) Installation of the AC Current Transformers (41XU1, 41XU2, 51XU1, 51XU2) Removal of the GCU-1(2) (1XU1, 1XU2) Installation of the GCU-1(2) (1XU1, 1XU2) Operational Check of GAPCU via CFDS Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure Engine Automatic Start Engine Shutdown
R NOTE : As the GEN 1 was set to OFF because of a true failure, the fault
____ R confirmation is not necessary.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : 401-499, ∞∞24-22-00∞∞∞∞∞∞∞∞∞∞Page 257
Aug 01/05 CES
R 4. Fault Isolation
_______________
R A. If the fault symptom is identified by the CFDS message CTA (51XU1)/ IDG1
R (E1-4000XU)/ GCU1 (1XU1) and the upper ECAM-DU warning GEN 1 FAULT:
R - read the EPGS GROUND REPORT or POST FLIGHT REPORT to see if there is
R one or two of the CFDS messages that follow:
R . IDG1 (E1-4000XU) LOW OIL PRESSURE
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