R b_ Connect the new wire(s) of the fuel pump supply cable where
R the wiring passes through the junction box (bracket
R assembly), by a splice(s) (Ref. ESPM 20-53-21).

R c_ Make sure that the length of the new supply cable when
R assembled, between the front face of the connector 25QA-A
R and the forward face of the cable guide (that shows outside
R the wing-skin) is 1320 mm (51.9685 in.).

R d_ If necessary, make any final adjustment in the length of
R the supply cable across the lower surface of the wing
R during the installation of the rear fairing.

R e_ 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 f_ 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 b_ thru f_. 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 7_ In the cockpit (right rear) do a visual inspection asR specified in step (j)2_ of the items that follow, replace if R necessary:
R a_ The C/B-FUEL/L WING TK/PUMP 2 SPLY (7QA) at the C/B panelR 121VU (Ref. AWM 93-01-21).
R b_ The connector 2216VC-A and related receptacle at the panelR 120VU (Ref. AWM 93-01-20).
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R  8_  Release the front face of the C/B panel 121VU and lower to the
R  open (horizontal) position. 
R  9_  Use a multimeter and make sure that each of the 115VAC three
R  phases are available at the C/B-7QA input and output terminals 
R  (Ref. ASM 28-21/02). 
R  10__  If the 115VAC supply to the C/B-7QA, is not available at
R  terminals A1, B1 and C1 trouble shoot the AC supply (Ref. TSM 
R  24 PB 101). 
R  11__  If, with the C/B-7QA closed, the 115VAC supply is not
R  available at the terminals A2, B2 and C2, replace the 
R  C/B-FUEL/L WING TK/PUMP 2 SPLY (7QA). 
R  12__  Raise the front face of the C/B panel 121VU to the closed
R  (vertical) position and secure. 
R  13__  In the forward avionics bay remove the front cover of the
R  contactor box 107VU (Ref. AWM 93-01-07). 
R  14__  Do a visual inspection as specified in step (j)2_ and replace,
R  if necessary: 
R  a_  The CNTOR-L WING TK PUMP 2 SPLY (19QA).
R  b_  The connector 1266VC-A and related receptacle.
R  15__  Remove the contactor 19QA.
R  16__  Use a multimeter and make sure that each of the 115VAC three
R  phases are available at the contactor base input sockets (8, 6 
R  and 2) (Ref. ASM 28-21/02). 
R  17__  If the 115VAC supply to the contactor 19QA is not available,
R  do a test of the aircraft wiring (three phase supply) between 
R  the C/B-FUEL/L WING TK/PUMP 2 SPLY (7QA) and the CNTOR-L WING 
R  TK PUMP 2 SPLY (19QA) (Ref. ASM 28-21/02). 
R  Do the test as follows: 
R  a_  Continuity test, with a multimeter, of each three phase
R  wire (from end to end) (Ref. ESPM 20-52-21). 
R  b_  Insulation test, with a 500VDC insulation tester, between
R  each phase wire (pole) and ground (Ref. ESPM 20-52-24). 
R  c_  Insulation test, with a 500VDC insulation tester, between
R  each phase wire and the other two wires (pole to pole) 
R  (Ref. ESPM 20-52-24). 
R  d_ Repair/replace the unserviceable wiring and connectors.

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R  e_  Install the contactor 19QA.
R  f_  Install the the front cover of the contactor box 107VU.
R  18__  If the 115VAC supply is available, replace the CNTOR-L WING TK
R  PUMP 2 SPLY (19QA) with a serviceable item. 
　
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