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(1) Not applicable. 4. Fault Isolation _______________ R **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207, A. Procedure NOTE : This procedure is written for the C/B-FUEL/L WING TK/PUMP 2 SPLY ____ 7QA with the C/B-FUEL/R WING TK/PUMP 2 SPLY 8QA given in parenthesis, if different. (1) Do all the steps (2) thru (20) before you close the C/B-FUEL/L(R) WING TK/PUMP 2 SPLY 7QA(8QA) in step (21).
(2) Make sure that the L(R) TK PUMPS 2 P/BSW 15QA(16QA) shows OFF (released out).
(3) Before you do more steps, make sure that the wing area adjacent to the left inner fuel pump 25QA (right outer fuel pump 26QA) fairings and cover are not contaminated with fuel from a fuel leak or spillage.
「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 : ALL ∞∞28-21-00∞∞∞∞∞∞∞∞∞∞Page A295 May 01/05 CES (a) If necessary:
1 Repair all the leaks: _
- (Ref. AMM TASK 51-76-12-300-001)
- (Ref. AMM TASK 51-76-12-300-002)
- (Ref. SIL 57-0086).
2 Clean the area of the fuel spillage. _
(4) Remove all the fuel pump 25QA(26QA) fairings (Ref. AMM TASK 28-21-49-000-001) and cover assembly (Ref. AMM TASK 28-21-51-000-001).
(5) Disconnect the supply cable end connector 25QA-A(26QA-A) from the fuel pump receptacle.
- all the fuel pump 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).
(7) Make sure that good lighting is available. Do a visual inspection and look for distortion (pinched or stretched), damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination or incorrect assembly, of the items that follow:
- the electrical receptacle
- the supply cable end connector 25QA-A(26QA-A)
- the fuel pump fairings
- the tape hooks (Velcro) on the intermediate and rear fuel pump fairings (post 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. (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).
「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 A296 201-207, May 01/05 CES
(10) If necessary, replace the damaged fairings with serviceable items.
(11) If the fuel pump supply cable between the connector 25QA-A(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
(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 25QA-A(26QA-A) and the forward face of the cable guide (that shows outside the wing-skin) is: - 1320 mm (51.97 in) for the left (inner) wing tank pump No. 2 -
- (1345 mm (52.95 in) for the right (outer) wing tank pump No. 2 - 26QA). (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. www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 FUEL 燃油2
