(a) Disconnect the:
- tank wall connector 4040VC1(2)-A
- fused connector 4043VC-A(4044VC-A).
(9) Remove the FQIC 3QT (Ref. AMM TASK 28-42-34-000-001).
「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, 101-149, 151-199, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page 256
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(10) Do a visual inspection and electrical tests of the aircraft wiring (Ref. AWM 28-42-11) ((Ref. AWM 28-42-10)) and (Ref. AWM 28-42-13) ( (Ref. AWM 28-42-12)) between the FQIC rack connector 3QT-A and the tank wall connector 4040VC1-A(4040VC2-A) as follows:
(a) Visual Inspection Make sure that good lighting is available. Do a visual inspection and look for distortion (bent, pinched or stretched), damage (broken, chafed or cut), discoloration, overheating (burnt, melted or arcing), liquid contamination, loose electrical connection, or incorrect assembly of the items that follow:
- FQIC rack connector 3QT-A, pins 8D(2J), 1C(6J) and 15D(15K)
- 92VU shelf receptacle 210VC (214VC) and connector 210VC-A(214VC-A)
- receptacle 1970VC (1521VC) and connector 1970VC-A(1521VC-A)
- receptacle (2973VC) and connector (2973VC-A) (right wing only)
- receptacle 7155VC(7110VC) and connector 7155VC-A(7110VC-A)
- pressure seal feedthrough 4017VP(4016VP)
- fused connector 4043VC-A(4044VC-A) and receptacle 4043VC(4044VC)
- connector 4040VC1(2)-A, pins R, <J and P
- adjacent and related connecting wires.
(b) Electrical Tests Do a continuity test (Ref. ESPM 20-52-21) and a test for a short circuit (Ref. ESPM 20-52-22) of the wires that follow (Ref. AWM 28-42-11) ((Ref. AWM 28-42-10)):
- FQIC rack connector 3QT-A, pin 8D(2J) to connector 4040VC1(2)-A, pin R (probe 2 signal)
- FQIC rack connector 3QT-A, pin 1C(6J) to connector 4040VC1(2)-A, pin <J (common drive return)
- FQIC rack connector 3QT-A, pin 15D(15K) to connector 4040VC1(2)-A, pin P (common drive).
(c) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-00-00).
(d) Connect the:
- fused connector 4043VC-A(4044VC-A) to the receptacle 4043VC-A(4044VC-A) (Ref. AMM TASK 28-42-43-400-008)
- tank wall connector 4040VC1-A(4040VC2-A) to the receptacle 4040VC1(4040VC2).
(e) Install the initial FQIC 3QT (Ref. AMM TASK 28-42-34-400-001).
(f) Do the test given in Para. 3.B.
(11) If the fault continues, drain and open the tank to the air (Ref. AMM TASK 28-10-00-910-001) and (Ref. AMM TASK 28-10-00-910-002).
「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, 101-149, 151-199, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page 257
201-299, 401-499, Aug 01/05 CES
(12) Do a check of the HARNESS-CHAN B, L WING TK INR (14QT1) (HARNESS-CHAN B, R WING TK INR (14QT2)) (Ref. AWM 28-42-11) ((Ref. AWM 28-42-10)) and replace, if necessary, (Ref. AMM TASK 28-42-43-000-007) and (Ref. AMM TASK 28-42-43-400-007).
(13) If the harness 14QT1(2) is serviceable, replace the PROBE-FUEL QTY NO 2, RIB 1-2 L WNG TK INR GROUP B (22QT1) (PROBE-FUEL QTY NO 2, RIB 1-2 R WNG TK INR GROUP B (22QT2)) (Ref. AMM TASK 28-42-15-000-001) and (Ref. AMM TASK 28-42-15-400-001).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
5. Close-up
________
A. Close-up and Removal of Equipment
(1) Do the EIS Stop Procedure (Ref. AMM TASK 31-60-00-860-002).
(2) If necessary, de-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).
(3) Make sure that the access panel 574BB (674BB) opened during this trouble-shooting procedure is closed.
(4) Make sure that the work area is clean, clear of tool(s) and other items.
(5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
「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, 101-149, 151-199, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page 258
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**ON A/C ALL
TASK 28-42-00-810-806
Fuel Quantity Probe 23QT1(2), Left(Right) Wing Tank
WARNING : OBEY THE FUEL SAFETY PROCEDURES.
_______
WARNING : WHEN YOU DO WORK ON THE FUEL SYSTEM WIRING, YOU MUST USE TEST
_______ EQUIPMENT THAT IS APPROVED (REFER TO INTERNATIONAL OR NATIONAL SPECIFICATIONS FOR INTRINSICALLY SAFE TEST EQUIPMENT, E.G. EN50-020, UL913 OR EQUIVALENT). TEST EQUIPMENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) FUEL 燃油2(132)
