(8) If any damage (electrical wiring, fairing or structural) is found, tell AIRBUS within 10 days, AIRWORTHINESS DIRECTIVE (Ref. AD 2002-221(B)).
(9) If the aircraft structure is damaged, refer to Skins and Plating -Allowable Damage, P. Block 101 (Ref. ASRM 57-21-11).
(10) If necessary, replace the damaged fairings with serviceable items.
(11) If the fuel pump supply cable between the connector 21QA-A(22QA-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 21QA-A(22QA-A) and the forward face of the cable guide (that shows outside the wing-skin) is: - 1345 mm (52.95 in) for the left (outer) wing tank pump No. 1 -
21QA
- (1320 mm (51.97 in) for the right (inner) wing tank pump No. 1
- 22QA).
(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) into 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 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
「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 A285
201-207, May 01/05 CES the unwanted cable (excess length) will become looped and get trapped during the installation of the intermediate and rear fairings.
(12) Do an insulation test, with a 500VDC insulation tester, of the fuel pump stator windings as follows:
(a) Connect one lead, of the insulation tester, to pin D of the fuel pump receptacle.
(b) Connect the pins A, B and C, of the fuel pump receptacle, together (at the same time).
(c) Connect the other lead, of the insulation tester, to the pins A, B and C that were connected together in the previous step.
(d) If the insulation resistance of the fuel pump stator windings:
1 Is more than 1 Mohm, go to step (13).
_
2 Is less than 1 Mohm, replace the PUMP-FUEL NO 1, L WING TK
_ (21QA) (PUMP-FUEL NO 1, R WING TK (22QA)) (Ref. AMM TASK 28-21-51-000-001) and (Ref. AMM TASK 28-21-51-400-001).
(13) In the cockpit (right rear) do a visual inspection as specified in step (7) of the items that follow, replace if necessary:
(a) The C/B-FUEL/L WING TK/PUMP 1 SPLY (1QA) (C/B-FUEL/R WING TK/PUMP 1 SPLY (2QA)) at the C/B panel 121VU (Ref. AWM 93-01-21).
(b) The connector 2212VC-A and related receptacle at the panel 120VU (Ref. AWM 93-01-20).
(14) In the forward avionics bay, at the contactor box 107VU (Ref. AWM 93-01-07) do a visual inspection as specified in step (7) and replace, if necessary:
(a) The CNTOR-L WING TK PUMP 1 SPLY (17QA) (CNTOR-R WING TK PUMP 1 SPLY (18QA)).
(b) The connector 1264VC-A (1260VC-A) and related receptacle.
(15) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) (Ref. ASM 28-21/01) between the:
- C/B-FUEL/L(R) WING TK/PUMP 1 SPLY 1QA(2QA) and the CNTOR-L(R) WING TK PUMP 1 SPLY 17QA(18QA)
- CNTOR-L(R) WING TK PUMP 1 SPLY 17QA(18QA) and the PUMP-FUEL No. 1, L(R) WING TK connector 21QA-A(22QA-A) 中國航空網 m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油1(148)
