- pressure switch connector 28QA-A, pin C and the SDAC-1 rack connector 1WV1-AD, terminal 2K
- pressure switch connector 28QA-A, pin C and the SDAC-2 rack connector 1WV2-AD, terminal 2K
- pressure switch connector 28QA-A, pin C and the BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 14
- BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 13 and the P/BSW-FUEL/R TK PUMPS/2 connector 16QA-A, terminal 7.
NOTE : A short circuit to ground on one of these lines can cause:
____
- a false LO PR warning to be generated within the FWC
- the FAULT legend/lamp to come on incorrectly. It is possible that a short circuit to ground on one of these lines can come from one of the LRUs as follows:
- BOARD-ANN LT TEST & INTFC (20LP)
- FLSCU-2 (9QJ)
- SDAC-1 (1WV1)/SDAC-2 (1WV2).
(e) Repair the unserviceable wiring and connectors.
(f) Do the test given in Para. 3.B.(2)(b).
**ON A/C 301-399,
A. Procedure
(1) If a fuel low pressure indication is shown for the right wing tank fuel pump No. 2 (26QA):
- do a fuel transfer (Ref. AMM TASK 28-21-00-710-007) use the right wing tank fuel pump No. 2 to do the fuel transfer.
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201-207, 301-399, May 01/05 CES
R (2) If the fuel starts to transfer go to step (3). If the fuel does not
R start to transfer:
R (a) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will
R de-energize the contactor 20QA.
R (b) Before you do more steps, make sure that the wing area adjacent
R to the right outer fuel pump 26QA fairings and cover is not
R contaminated with fuel from a fuel leak or spillage.
R 1_ If necessary:
R a_ Repair all the leaks:
R - (Ref. AMM TASK 51-76-12-300-001)
R - (Ref. AMM TASK 51-76-12-300-002)
R - (Ref. SIL 57-0086).
R b_ Clean the area of the fuel spillage.
R (c) Remove all the fuel pump 26QA cable fairings (Ref. AMM TASK 28-R 21-49-000-001) and cover assembly (Ref. AMM TASK 28-21-51-000-R 001).
R (d) Disconnect the supply cable end connector 26QA-A from the fuel
R pump receptacle.
R (e) If, in step (c) or (d), any damage can be seen on the supply
R cable or the aircraft structure, go to step (j) 1_.
R (f) Set the R TK PUMPS 2 P/BSW (16QA) to ON (push in). This will
R energize the contactor 20QA and the 115VAC three phases will be
R supplied to the fuel pump connector 26QA-A.
R (g) Use a multimeter to do a test, to make sure that each of the
R 115VAC three phases are available at the connector 26QA-A (Ref.
R ASM 28-21/02).
R (h) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will
R de-energize the contactor 20QA.
R 1_ Use a multimeter to do a test, to make sure that each of the
R 115VAC three phases are not available at the connector 26QA-A.
R NOTE : This is to make sure that the contactor 20QA does not
____ R stay in the on position (stuck/held on).
R (i) If the 115VAC three phase supply voltage measured in step (g) is R correct, replace the PUMP-FUEL NO 2, R WING TK (26QA) (Ref. AMM R TASK 28-21-51-000-001) and (Ref. AMM TASK 28-21-51-400-001).
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(j) If the 115VAC three phase supply voltage measured in step (g) is not correct (no voltage, incorrect voltage or a phase is missing), do all the sub-steps that follow:
1 Clean and dry:
_
- all the fuel pump cable fairings
- the fuel pump cover assembly
- the fuel pump supply cable and the related end connector
- the aircraft wing structure adjacent to the route of the supply cable across the wing surface
- the aircraft wing structure at the rear spar, adjacent to the landing light, where the fuel pump supply cable leaves the conduit and passes through the cable guide (bottom skin).
2 Make sure that good lighting is available.
_ Do a visual inspection and look for distortion (pinched or streched) damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination, loose electrical connection or incorrect assembly, of the items that follow:
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