R 4. Fault Isolation_______________
R A. If the test confirms the fault:
R - do a check of the connector A of the TR-2 (1PU2) for correct condition.
R (1) If the connector is not in the correct condition (burned contacts,
R damaged contacts...):
R - replace it.
R (2) If the connector is in the correct condition:
R - do a check of the wiring between pins A2, B2 and C2 of the TR-2
R SPLY circuit breaker (2PU2) and pins A/A, A/B and A/C of the TR-2
R (1PU2). (Ref. ASM 24-32/01)
R (a) If the fault continues:
R - do a check of the connector B of the TR-2 (1PU2) for correct
R condition.
R 1_ If the connector is not in the correct condition:
R - replace it.
R 2_ If the connector is in the correct condition:
R - do a check and repair the wiring from the TR-2 pins B/A, B/B
R and B/C to the first terminal block (Ref. ASM 24-32/01).
R B. Do this test
R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------
R 1. On the ECAM control panel: On the lower ECAM DU, ELEC page:
R - push the ELEC key to get the - the TR2 indication is shown in white,
R ELEC page. - the voltage and current parameters
R are shown in green.
R 5. Close-up________
R A. Put the aircraft back to its initial configuration.
R (1) Do the EIS stop procedure
R (Ref. AMM TASK 31-60-00-860-002).
R (2) De-energize the aircraft electrical circuits
R (Ref. AMM TASK 24-41-00-862-002).
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May 01/98 CES
DC EMERGENCY GENERATION (TR) - FAULT ISOLATION PROCEDURES
_________________________________________________________
TASK 24-34-00-810-801
Failure of the Connection between the Essential TR Voltage Output and the SDAC1 and SDAC2
1. Possible Causes
_______________
- TR-ESS (1PE)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 24-34-51-000-001 Removal of the Essential Transformer Rectifier (1PE) AMM 24-34-51-400-001 Installation of the Essential Transformer Rectifier (1PE) 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 24-34/01
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 -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM DU, ELEC page:
R - push the ELEC key to get the ELEC - the ESS TR voltage indication is 0V.
R page.
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Aug 01/00 CES
4. Fault Isolation
_______________
A. If the test confirms 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 3(49)
