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).
 「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 265
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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.

 「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 266
 May 01/04 CES

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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