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R  the wiring passes through the junction box (bracket 
R  assembly), by a splice(s) (Ref. ESPM 20-53-21). 
R  h_  Make sure that the length of the new supply cable when
R  assembled, between the front face of the connector 26QA-A 
R  and the forward face of the cable guide (that shows outside 
R  the wing-skin) is 1345 mm (52.9527 in.). 
R  i_  If necessary, make a final adjustment in the length of the
R  supply cable across the lower surface of the wing during 
R  the installation of the rear fairing. 
R  j_  Feed the surplus cable (small amount only) back up the
R  flexible conduit to the junction box (bracket assembly) on 
R  the rear spar. 
R  k_  Make sure that the supply cable is held tight by the P-clip
R  at the cable guide. 
R  NOTE : It is important that the fuel pump supply cable is____ 
R  installed correctly as given in steps g_ thru k_. 
R  Incorrect installation of the cable can cause it to 
R  get damaged. If the cable is too short it will put 
R  tension on the wires and plug. If the cable is too 
R  long you will not be able to install the fairings 
R  correctly. This is because the unwanted cable 
R  (excess length) will become looped and get trapped 
R  during the installation of the intermediate and rear 
R  fairings. 
R  l_  Install the front cover of the contactor box 107VU.
R  m_  Connect the connector 26QA-A to the fuel pump receptacle.
R  n_ Do the test given in Para. 3.A.(2)(b).

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R (3) If the fuel transfers:
R (a) During the fuel transfer, disconnect the electrical free R connector 28QA-A from the PRESS SW-FUEL PUMP No. 2, R WING TK R (28QA) (Ref. AMM TASK 28-21-15-000-003).
R (b) If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend stays on go to R step (d). If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend goes R off: R - do a check of and replace, if necessary, the PRESS SW-FUEL PUMP R NO 2, R WING TK (28QA) (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 28QA.
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 4QM and the pressure switch 28QA.
R NOTE : The pressure switch 28QA fuel supply pipe-line is also
____ R connected to the CHECK VALVE (225QM). R The check valve 225QM is in one of the fuel supply R pipe-lines that go to the right 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/R TK PUMPS/2 (16QA) 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 28QA-A, pin C and the FLSCU-2 rack R connector 9QJ-AA, terminal 13D R - pressure switch connector 28QA-A, pin C and the SDAC-1 rack R connector 1WV1-AD, terminal 2K R - pressure switch connector 28QA-A, pin C and the SDAC-2 rack R connector 1WV2-AD, terminal 2K R - pressure switch connector 28QA-A, pin C and the BOARD-ANN LT R TEST & INTFC connector 20LP-A, terminal 14 R - BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 13 and the R P/BSW-FUEL/R TK PUMPS/2 connector 16QA-A, terminal 7.
R NOTE : A short circuit to ground on one of these lines can cause:
____

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 - 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)
　
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