(g) Use a multimeter to do a test, to make sure that each of the 115VAC three phases are available at the connector 26QA-A (Ref. ASM 28-21/02).
(h) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
1 Use a multimeter to do a test, to make sure that each of the
_ 115VAC three phases are not available at the connector 26QA-A.
NOTE : This is to make sure that the contactor 20QA does not
____ stay in the on position (stuck/held on).
(i) If the 115VAC three phase supply voltage measured in step (g) is correct:
1 Replace the PUMP-FUEL NO 2, R WING TK (26QA) (Ref. AMM TASK
_ 28-21-51-000-001) and (Ref. AMM TASK 28-21-51-400-001).
2 If the fault continues, replace the SEQUENCE VALVE of the
_ fuel-pump (26QA) (Ref. AMM TASK 28-21-45-000-001) and (Ref. AMM TASK 28-21-45-400-003).
(j) If the 115VAC three phase supply voltage measured in step (g) is not correct (no voltage, incorrect voltage or a phase is missing), do all the sub-steps that follow:
1 Clean and dry:
_
- all the fuel pump cable fairings
- the fuel pump cover assembly
- the fuel pump supply cable and the related end connector
- the aircraft wing structure adjacent to the route of the supply cable across the wing surface
- 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 26QA-A
- the supply cable
- the cable guide
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201-207, May 01/05 CES
- the fuel pump fairings
- the tape hooks (Velcro) on the intermediate and rear fuel pump fairings (Post (Ref. SB 24-1070))
- 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, AIRWORTHINESS DIRECTIVE (Ref. AD 2002-221(B)).
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 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.
「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 : 001-049, 051-099, 101-105, 151-154, ∞∞28-21-00∞∞∞∞∞∞∞∞∞∞Page 283
201-207, May 01/05 CES
e Feed the surplus cable (small amount only) back up the
_ flexible conduit to the junction box (bracket assembly) on the rear spar.
f Make sure that the supply cable is held tight by the P-clip
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