「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 301-399, ∞∞28-21-00∞∞∞∞∞∞∞∞∞∞Page 268
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R (3) If the fuel transfers:
R (a) During the fuel transfer, disconnect the free connector 27QA-A R from the PRESS SW-FUEL PUMP No. 2, L WING TK (27QA) (Ref. AMM R TASK 28-21-15-000-003).
R (b) If the P/BSW-FUEL/L TK PUMPS/2 (15QA) FAULT legend stays on go to R step (d). If the P/BSW-FUEL/L TK PUMPS/2 (15QA) FAULT legend goes R off: R - do a check of and replace, if necessary, the PRESS SW-FUEL PUMP R NO 2, L WING TK (27QA) (Ref. AMM TASK 28-21-15-000-003) and R (Ref. AMM TASK 28-21-15-400-001).
R NOTE : If an ADAPTOR - SEQUENCE VALVE (99A28404000000) is
____ R available, the fuel-pump fuel pressure can be measured at R the sealing valve outlet. This can be installed in place R of the pressure switch 27QA.
R (c) If the fault continues, or if no fuel pressure is shown on the R gage of the ADAPTOR - SEQUENCE VALVE, make sure that these R components are in the correct condition: R - the pressure switch sealing valve R - the pressure switch plug (banjo adaptor attachment bolt) R - the pressure switch fuel supply pipe-line between the fuel pump R canister 2QM and the pressure switch 27QA.
R NOTE : The pressure switch 27QA fuel supply pipe-line is also
____ R connected to the CHECK VALVE (222QM). R The check valve 222QM is in one of the fuel supply R pipe-lines that go to the left wing Integrated Drive R Generator (IDG) cooling system. The fuel in this pipe-line R is at ambient temperature.
R 1_ Repair/replace the components that are unserviceable.
R 2_ Do the test given in Para. 3.B.(2)(b).
R (d) If the P/BSW-FUEL/L TK PUMPS/2 (15QA) FAULT legend stays on, do a R check of the aircraft wiring (low pressure lines) (Ref. ASM 28-R 21/02) between the: R - pressure switch connector 27QA-A, pin C and the FLSCU-1 rack R connector 7QJ-AA, terminal 13D R - pressure switch connector 27QA-A, pin C and the SDAC-1 rack R connector 1WV1-AA, terminal 2D R - pressure switch connector 27QA-A, pin C and the SDAC-2 rack R connector 1WV2-AA, terminal 2D R - pressure switch connector 27QA-A, pin C and the BOARD-ANN LT R TEST & INTFC connector 20LP-A, terminal 9 R - BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 44 and the R P/BSW-FUEL/L TK PUMPS/2 connector 15QA-A, terminal 7.
R NOTE : A short circuit to ground on one of these lines can cause:
____

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 301-399, ∞∞28-21-00∞∞∞∞∞∞∞∞∞∞Page 269
 May 01/04 CES

 - 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-1 (7QJ)

 - SDAC-1 (1WV1)/SDAC-2 (1WV2).

 (e) Repair the unserviceable wiring and connectors.

 (f) Do the test given in Para. 3.B.(2)(b).

R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 Post SB 28-1093 For A/C 001-049,051-099,101-105,151-154,201-207,
 A. Procedure
 (1) If a fuel low pressure indication is shown for the left wing tank fuel pump No. 2 (25QA):

 - do a fuel transfer (Ref. AMM TASK 28-21-00-710-007) use the left wing tank fuel pump No. 2 to do the fuel transfer.

 (2) If the fuel starts to transfer go to step (3). If the fuel does not start to transfer:

 (a) Set the L TK PUMPS 2 P/BSW (15QA) to OFF (release out). This will de-energize the contactor 19QA.

 (b) Before you do more steps, make sure that the wing area adjacent to the left inner fuel pump 25QA fairings and cover is not contaminated with fuel from a fuel leak or spillage.

 1 If necessary:
_ a Repair all the leaks:

_

 - (Ref. AMM TASK 51-76-12-300-001)

 - (Ref. AMM TASK 51-76-12-300-002)

 - (Ref. SIL 57-0086).

 b Clean the area of the fuel spillage.
_

 (c) Remove all the fuel pump 25QA cable fairings (Ref. AMM TASK 28-21-49-000-001) and cover assembly (Ref. AMM TASK 28-21-51-000-001).

 (d) Disconnect the supply cable end connector 25QA-A from the fuel pump receptacle.

 (e) If, in step (c) or (d), any damage can be seen on the supply cable or the aircraft structure, go to step (j) 1_.

 「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 ∞∞28-21-00∞∞∞∞∞∞∞∞∞∞Page 270
　
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