W DOC AIRBUS | TSM A320F

Loss of the DC Busbars

TASK 24-60-00-810-803-A
Loss of the DC Busbars

1. Possible Causes
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
ASM 243201
ASM 243202
AMM 24-32-51-000-001
Removal of the Transformer Rectifier
AMM 24-32-51-400-001
Installation of the Transformer Rectifier
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
3. Fault Confirmation
Subtask 24-60-00-860-054-A
A. Job Set-up
   (1) Aircraft Maintenance Configuration
     (a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
     (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
     (c) On the MCDU, get the ELEC menu on the SYSTEM REPORT/TEST page.
Subtask 24-60-00-710-054-A
B. Test
ACTION
RESULT
1.On the ECAM control panel:
  • push the ELEC key to get the ELEC page.
On the upper ECAM display unit:
  • the ELEC DC BUS 1+2 FAULT and ELEC DC BAT BUS FAULT warnings come into view.
    On the lower ECAM display unit:
  • the amber DC 1 and DC 2 indications come into view
  • the DC ESS BUS is supplied by the ESS TR.
2.On the MCDU, ELEC page:
  • push the line key adjacent to the TR1 indication.
On the MCDU:
  • the TR1 page comes into view.
3.On the MCDU:
  • push the line key adjacent to the RESET indication.
On the MCDU:
  • if the NO FAULT indication comes into view, stop the trouble shooting
  • if the TR1 indication comes into view, do again the steps 2 and 3 to reset the TR2
  • if, on the MCDU, TR2 page, the TR2 indication comes into view, do the trouble shooting given in Para. 4.
4. Fault Isolation
Subtask 24-60-00-810-052-A
A. If the test confirms the fault:
   (1) If the fault continues:
  • do a check for a short to ground and repair the wiring between:
    . the TR1 SPLY circuit breaker (2PU1) and the pins A/A, A/B, A/C of the TR1 (1PU1)
    . the 28VDC outlet of the TR1 and the pin A/F of the contactor (5PU1)
    . the pins A/G and B/5 of the contactor (5PU1) ASM 243202
    . the TR2 SPLY circuit breaker (2PU2) and the pins A/A, A/B, A/C of the TR2 (1PU2)
    . the 28VDC outlet of the TR2 and the pin A/F of the contactor (5PU2)
    . the pin 12 of the contactor (14XX) and the pin B/3 of the contactor (14PU)
    . the pins A/G and B/3 of the contactor (5PU2) ASM 243201.
Subtask 24-60-00-710-055-A
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 display unit:
  • the normal configuration comes into view.
5. Close-up
Subtask 24-60-00-860-055-A
A. Put the aircraft back to its initial configuration.
   (1) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (2) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:58 UTC
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