- the aircraft wing structure at the rear spar, adjacent to the landing light, where the fuel pump supply cable leaves the conduit and passes through the cable guide (bottom skin).

 2 Make sure that good lighting is available.
_ Do a visual inspection and look for distortion (pinched or streched) damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination, loose electrical connection or incorrect assembly, of the items that follow:
 - the electrical receptacle

 - the supply cable end connector 21QA-A

 - the supply cable

 - the cable guide

 - the fuel pump fairings

 - the aircraft wing structure adjacent to the route of the supply cable (across the wing surface and at the rear spar)

 - junction box (bracket assembly) on the rear spar.

 NOTE : Incorrect installation of the fuel pump fairings can
____ damage the supply cable. This can cause electrical arcing and damage to the aircraft structure.
 3 If any damage (electrical wiring, fairing or structural) is
_ found, tell AIRBUS within 10 days.
 4 If the aircraft structure is damaged, refer to Skins and
_ R Plating - Allowable Damage, P. Block 101, (Ref. ASRM 57-21-11).
 5 If necessary, replace the damaged fairings with serviceable
_
 items.

 6 If the fuel pump supply cable between the connector 21QA-A and
_ the related junction box (bracket assembly) on the rear spar is seen to be damaged, repair as follows:
 「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 : 301-399, ∞∞28-21-00∞∞∞∞∞∞∞∞∞∞Page 212
 May 01/05 CES

R CAUTION : DO NOT USE IN-LINE SPLICES TO REPAIR SECTIONS OF
_______
R ELECTRICAL CABLE THAT ARE BEHIND A FAIRING OR IN A
R CONDUIT.
R THIS WILL MAKE SURE THAT IT IS POSSIBLE TO SEE THE
R REPAIR FOR AN INSPECTION (REF. ESPM 20-53-29).

R a_ If necessary, replace the unserviceable:
R - protective sleeve
R - wire(s)
R - connector.

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 21QA-A
R and the forward face of the cable guide (that shows outside
R the wing-skin) is 1345 mm (52.9527 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 1 SPLY (1QA) at the C/B panelR 121VU (Ref. AWM 93-01-21).
R b_ The connector 2212VC-A and related receptacle at the panelR 120VU (Ref. AWM 93-01-20).
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 May 01/04 CES

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-1QA input and output terminals 
R  (Ref. ASM 28-21/01). 
R  10__  If the 115VAC supply to the C/B-1QA, 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-1QA 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 1 SPLY (1QA). 
　
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