6 If the fuel pump supply cable between the connector 26QA-A and
_ the related junction box (bracket assembly) on the rear spar is seen to be damaged, repair as follows:
CAUTION : DO NOT USE IN-LINE SPLICES TO REPAIR SECTIONS OF
_______ ELECTRICAL CABLE THAT ARE BEHIND A FAIRING OR IN A CONDUIT. THIS WILL MAKE SURE THAT IT IS POSSIBLE TO SEE THE REPAIR FOR AN INSPECTION (REF. ESPM 20-53-29).
a If necessary, replace the unserviceable:
_
- protective sleeve
- wire(s)
- connector.
b Connect the new wire(s) of the fuel pump supply cable where
_ the wiring passes through the junction box (bracket assembly), by a splice(s) (Ref. ESPM 20-53-21).
c Make sure that the length of the new supply cable when
_ assembled, between the front face of the connector 26QA-A and the forward face of the cable guide (that shows outside the wing-skin) is 1345 mm (52.9527 in.).
d If necessary, make any final adjustment in the length of
_ the supply cable across the lower surface of the wing during the installation of the rear fairing.
e Feed the surplus cable (small amount only) back up the
_ flexible conduit to the junction box (bracket assembly) on the rear spar.
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f Make sure that the supply cable is held tight by the P-clip
_
at the cable guide.
NOTE : It is important that the fuel pump supply cable is
____ installed correctly as given in steps b_ thru f_. Incorrect installation of the cable can cause it to get damaged. If the cable is too short it will put tension on the wires and plug. If the cable is too long you will not be able to install the fairings correctly. This is because the unwanted cable (excess length) will become looped and get trapped during the installation of the intermediate and rear fairings.
7 In the cockpit (right rear) do a visual inspection as
_ specified in step (j)2_ of the items that follow, replace if necessary:
a The C/B-FUEL/R WING TK/PUMP 2 SPLY (8QA) at the C/B panel
_
121VU (Ref. AWM 93-01-21).
b The connector 2216VC-A and related receptacle at the panel
_
120VU (Ref. AWM 93-01-20).
8 Release the front face of the C/B panel 121VU and lower to the
_
open (horizontal) position.
9 Use a multimeter and make sure that each of the 115VAC three
_ phases are available at the C/B-8QA input and output terminals (Ref. ASM 28-21/02).
10 If the 115VAC supply to the C/B-8QA, is not available at
__ terminals A1, B1 and C1 trouble shoot the AC supply (Ref. TSM 24 PB 101).
11 If, with the C/B-8QA closed, the 115VAC supply is not
__ available at the terminals A2, B2 and C2, replace the C/B-FUEL/R WING TK/PUMP 2 SPLY (8QA).
12 Raise the front face of the C/B panel 121VU to the closed
__ (vertical) position and secure.
13 In the forward avionics bay remove the front cover of the
__ contactor box 107VU (Ref. AWM 93-01-07).
14 Do a visual inspection as specified in step (j)2_ and replace,
__ if necessary:
a The CNTOR-R WING TK PUMP 2 SPLY (20QA).
_
b The connector 1262VC-A and related receptacle.
_
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15__ Remove the contactor 20QA.
16__ Use a multimeter and make sure that each of the 115VAC three phases are available at the contactor base input sockets (8, 6 and 2) (Ref. ASM 28-21/02).
17__ If the 115VAC supply to the contactor 20QA is not available, do a test of the aircraft wiring (three phase supply) between the C/B-FUEL/R WING TK/PUMP 2 SPLY (8QA) and the CNTOR-R WING TK PUMP 2 SPLY (20QA) (Ref. ASM 28-21/02). Do the test as follows:
a_ Continuity test, with a multimeter, of each three phase wire (from end to end) (Ref. ESPM 20-52-21).
b_ Insulation test, with a 500VDC insulation tester, between each phase wire (pole) and ground (Ref. ESPM 20-52-24).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) FUEL 燃油1(111)
