5. Close-up
________
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
(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 ∞∞24-60-00∞∞∞∞∞∞∞∞∞∞Page 210
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TASK 24-60-00-810-807
Unwanted Warning from the DC 2 Busbar
1. Possible Causes
_______________
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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 24-61/01 ASM 31-54/08
3. Fault Confirmation
__________________
A. Job Set-up
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
B. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------121VU EIS/SDAC1 AND 2/BUS2/28VDC 44WV P03 124VU 202PP/SPLY 1PN2 BG01
「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 ∞∞24-60-00∞∞∞∞∞∞∞∞∞∞Page 211
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C. Do this Test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the upper ECAM DU:
- push the ELEC key. - the DC BUS2 FAULT warning comes into
view. On the lower ECAM DU, on the ELEC page:
- the normal configuration comes into view with the DC 2 busbar shown in amber.
4. Fault Isolation
_______________
A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------121VU EIS/SDAC1 AND 2/BUS2/28VDC 44WV P03 124VU 202PP/SPLY 1PN2 BG01
**ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
B. If the test confirms the fault:
- do a check and repair the wiring: . between the 28VDC BUS 2 (202PP) and the first branch point, the circuit breaker (44WV) included, . then between the 28VDC BUS 2 (202PP) and the pin E of the TR2 contactor (5PU2), the circuit breaker (1PN2) included (Ref. ASM 31-54/08) and (Ref. ASM 24-61/01).
R **ON A/C 063-099, 106-149, 153-199, 206-299, 301-399, 401-499,
B. If the test confirms the fault:
- do a check and repair the wiring: . between the 28VDC BUS 2 (202PP) and the first branch point, the circuit breaker (44WV) included, . then between the 28VDC BUS 2 (202PP) and the pin 4 of the module 14PN, the circuit breaker (1PN2) included (Ref. ASM 31-54/08) and (Ref. ASM 24-61/01).
R **ON A/C ALL
C. Do this Test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM DU, on the ELEC page:
- push the ELEC key. - the normal configuration comes into view.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
TASK 24-60-00-810-808
Failure of the Connection between the Busbar 2XP and the TR2
1. Possible Causes
_______________
- CNTOR-TR 2/AC SVCE BUS NORM SPLY (14PU)
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