(2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
B. Test
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: On the lower ECAM DU, ELEC page: R - push the ELEC key to get the - amber crosses are shown instead of R ELEC page. the value of the TR1 current.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞24-32-00∞∞∞∞∞∞∞∞∞∞Page 205
Aug 01/00 CES
4. Fault Isolation
_______________
A. If the test confirms the fault: - do a check of the wiring from the TR1 pins B/B and B/C to the first terminal block (Ref. ASM 24-32/02).
(1) If there is no continuity: - repair the wiring.
(2) If there is continuity: - replace the TR-1 (1PU1) (Ref. AMM TASK 24-32-51-000-001) and (Ref. AMM TASK 24-32-51-400-001).
B. Do this test to make sure that the system operates correctly:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: - push the ELEC key to get the ELEC page. On the lower ECAM DU:- the ELEC page comes into view.
R R In the TR1 box: - the value of the TR1 current is shown in green.
5. Close-up________
A. Put the aircraft back to its initial configuration.
R R R (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
(2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
TASK 24-32-00-810-804
Failure of the Connection between the TR2 Current Output and the SDAC1 and
SDAC2
1. Possible Causes
_______________
- TR-2 (1PU2)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 24-32-51-000-001 Removal of the Transformer Rectifier (1PU1, 1PU2) AMM 24-32-51-400-001 Installation of the Transformer Rectifier (1PU1, 1PU2) AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
AMM 31-60-00-860-001 EIS Start Procedure
AMM 31-60-00-860-002 EIS Stop Procedure
ASM 24-32/01
3. Fault Confirmation
__________________
A. Job Set-up
R (1) Energize the aircraft electrical circuits
R (Ref. AMM TASK 24-41-00-861-002).
R
R (2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
R (Ref. AMM TASK 31-60-00-860-001).
R
B. Test
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: On the lower ECAM DU, ELEC page: R - push the ELEC key to get the - amber crosses are shown instead of R ELEC page. the value of the TR2 current.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞24-32-00∞∞∞∞∞∞∞∞∞∞Page 207
Aug 01/00 CES
4. Fault Isolation
_______________
A. If the test confirms the fault: - do a check of the wiring from the TR2 pins B/B and B/C to the first terminal block (Ref. ASM 24-32/01).
(1) If there is no continuity: - repair the wiring.
(2) If there is continuity: - replace the TR-2 (1PU2) (Ref. AMM TASK 24-32-51-000-001) and (Ref. AMM TASK 24-32-51-400-001).
B. Do this test to make sure that the system operates correctly:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: - push the ELEC key to get the ELEC page. On the lower ECAM DU:- the ELEC page comes into view.
R R In the TR2 box: - the value of the TR2 current is shown in green.
5. Close-up________
R R A. Put the aircraft back to its initial configuration.
R R R (1) Do the EIS stop procedure (Ref. AMM TASK 31-60-00-860-002).
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