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).
「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 212
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.
「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 ∞∞24-34-00∞∞∞∞∞∞∞∞∞∞Page 201
Aug 01/00 CES
4. Fault Isolation
_______________
A. If the test confirms the fault: 中國航空網 m.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)
