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R  - do a check of the wiring from the ESS TR pin B/A to the first terminal 
R  block (Ref. ASM 24-34/01).
 (1) If there is no continuity: 
R  - repair the wiring.
 (2) If there is continuity: 
R  - replace the TR-ESS (1PE) (Ref. AMM TASK 24-34-51-000-001) and (Ref.
 AMM TASK 24-34-51-400-001).
 B. Do this test to make sure that the system operates correctly.
 -------------------------------------------------------------------------------
ACTION RESULT
 -------------------------------------------------------------------------------
1. On the ECAM control panel: On the lower ECAM DU:
 - push the ELEC key to get the - the ELEC page comes into view.
 ELEC page.
 - In the ESS TR box: 
R  - the voltage indication is shown in 
R  green.
 5. Close-up________ 
R  A. Put the aircraft back to its initial configuration. 
R 
R  (1) Do the EIS stop procedure 
R  (Ref. AMM TASK 31-60-00-860-002). 
R 
R  (2) De-energize the aircraft electrical circuits 
R  (Ref. AMM TASK 24-41-00-862-002). 
R

 TASK 24-34-00-810-802

 Failure of the Connection between the Essential TR Current 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 - amber crosses are shown instead of
R page. the value of the ESS TR current.
R
 「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 203
 Aug 01/00 CES

 4. Fault Isolation
_______________

 A. If the test confirms the fault: - do a check of the wiring from the essential transformer rectifier pins B/B and B/C to the first terminal block (Ref. ASM 24-34/01).
 (1) If there is no continuity: - repair the wiring.
 (2) If there is continuity: - replace the TR-ESS (1PE)> (Ref. AMM TASK 24-34-51-000-001) and (Ref. AMM TASK 24-34-51-400-001).
 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 R R  In the ESS TR box: - the value of the ESS TR 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). 
R R R (2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002). 

 

 DC ESSENTIAL & NORMAL GENERATION SWITCHING - FAULT ISOLATION PROCEDURES
_______________________________________________________________________
 TASK 24-35-00-810-801
 Failure of the Contactor (4PC) in Closed Position
 1. Possible Causes
_______________
 - CNTOR-DC ESS BUS SUPPLY (4PC)

 - CNTOR-DC NORM BUS 1 SWITCHING (1PC1)
　
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