R (1) If there is no continuity:
R - repair the wiring.

R (2) If there is continuity:
R - replace the RELAY-SWTG SPLY/TR 2 FAULT (8PC2).

 「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 ∞∞24-30-00∞∞∞∞∞∞∞∞∞∞Page 225
 Aug 01/00 CES

R  (3) If the fault continues: 
R  - replace the TR-2 (1PU2), (Ref. AMM TASK 24-32-51-000-001) and (Ref. 
R  AMM TASK 24-32-51-400-001). 
R  B. Do this test to make sure that the system operates correctly: 
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 normal configuration comes into 
R  ELEC page.  view. 
R  2. On the AC power center 123VU:  On the lower ECAM DU, ELEC page: 
R  - open the TR2 circuit breaker  - the TR2 and its parameters are shown 
R  (2PU2).  in amber 
R  - the TR2 does not energize the DC 2 
R  busbar 
R  - the DC BAT busbar supplies the DC 2 
R  busbar. 
R  On the upper ECAM DU: 
R  - the TR2 FAULT message comes into 
R  view. 
R  3. On the AC power center 123VU: 
R  - close the TR2 circuit breaker. 
R  4. On the TR2 front face:  On the lower ECAM DU, ELEC page: 
R  - push the TR2 RESET pushbutton  - the normal configuration is shown. 
R  switch. 
R  On the upper ECAM DU: 
R  - the TR2 FAULT message goes out of 
R  view. 
R  5. Close-up________ 

R  A. Put the aircraft back to its initial configuration. 
R  (1) Do the EIS stop procedure (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).

 DC MAIN GENERATION (TR) - FAULT ISOLATION PROCEDURES
____________________________________________________
 TASK 24-32-00-810-801
 Failure of the Connection between the TR1 Voltage Output and the SDAC1 and
 SDAC2
 1. Possible Causes
_______________
 - TR-1 (1PU1)

 - 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 24-32/02

 3. Fault Confirmation
__________________
 A. Job Set-up
R (1) Energize the aircraft electrical circuits
R (Ref. AMM TASK 24-41-00-861-002).

R (2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
R
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 - the TR1 voltage indication is 0V. ELEC 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 ∞∞24-32-00∞∞∞∞∞∞∞∞∞∞Page 201
 Aug 01/00 CES

 4. Fault Isolation
_______________

 A. If the test confirms the fault: - do a check of the wiring from the TR1 pin B/A 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:
　
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