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R (7) If the fault continues:
R (a) Get access to the tank wall connector 4040VC1(2)-A (for the wing R tank harness 63QT(64QT) (Ref. AMM TASK 28-42-43-000-008).
R (b) Disconnect the free connector 4040VC1(2)-A from the receptacle R 4040VC1(2).
R (c) Do a check (Ref. AWM 28-46-04), and (Ref. AWM 28-46-05) of the aircraft wiring (sensor input line - H) between the FLSCU-2(1) rack connector AB, pin 8A and the tank wall free connector 4040VC1(2)-A, pin <G.
R (d) Do a check (Ref. AWM 28-46-04), and (Ref. AWM 28-46-05) of the aircraft wiring (sensor input line - L) between the FLSCU-2(1) rack connector AB, pin 8B and the tank wall free connector 4040VC1(2)-A, pin <W.
R (e) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-2 BITE 3 test command line) between the FLSCU-2 rack connector AA, pin 15C and the FQIC rack connector AB, pin 13F, or the (aircraft wiring (FLSCU-1 BITE 3 test command line) between the FLSCU-1 rack connector AA, pin 15C and the FQIC rack connector AB, pin 15F).
R (f) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-2 LS5 output line) between the FLSCU-2 rack connector AB, pin 5B and the FQIC rack connector AC, pin 1J, or the (aircraft wiring (FLSCU-1 LS5 output line) between the FLSCU-1 rack connector AB, pin 5B and the FQIC rack connector AC, pin 3B).
R (g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-R 00-00).
R (h) Connect the free connector 4040VC1(2)-A to the receptacle R 4040VC1(2).
R (i) Do the test in Para. 3.A.
R (8) If the fault continues or if there is no continuity in Step (5):
R (a) Drain, open and vent the tank (Ref. AMM TASK 28-10-00-910-001) R and (Ref. AMM TASK 28-10-00-910-002).
R (b) Do a wiring check of the HARNESS - GROUP B, L WING TK (63QT) ( R HARNESS - GROUP B, R WING TK (64QT)) (Ref. AWM 28-46-05) and R replace, if necessary (Ref. AMM TASK 28-42-43-000-005) and R R (Ref. AMM TASK 28-42-43-400-005).
 「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 : 301-399, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 207
 May 01/05 CES

R  (c) If the harness is serviceable, replace the SENSOR-LOW LEVEL 
R  (1500KG), L WNG TK INR FWD CHANNEL B (15QJ1) (SENSOR-LOW LEVEL 
R  (1500KG), R WNG TK INR FWD CHANNEL B (15QJ2)) (Ref. AMM TASK 28-
R  46-15-000-001) and (Ref. AMM TASK 28-46-15-400-009). 
R

 「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 : 301-399, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 208
 May 01/05 CES

 **ON A/C ALL
 TASK 28-46-00-810-802
 L(R) Low Level Sensor 16QJ1(2)
 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.
 1. Possible Causes
_______________
 - FLSCU-1 (7QJ)

 - SENSOR-LOW LEVEL (750KG), L WNG TK INR REAR CHANNEL A (16QJ1)

 - SENSOR-LOW LEVEL (750KG), R WNG TK INR REAR CHANNEL A (16QJ2)

 - FLSCU-2 (9QJ)

 - aircraft wiring

 - HARNESS-GROUP A, L WING TK INR (13QT1)

 - HARNESS-GROUP A, R WING TK INR (13QT2)

 - HARNESS - GROUP A, L WING TK (57QT)

 - HARNESS - GROUP A, R WING TK (58QT)

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
28-46-00-810-818 FLSCU1(2) 7QJ(9QJ) R ESPM 20-00-00 AMM 28-10-00-910-001 Safety Procedures When You Do Work in a Fuel Tank R AMM 28-10-00-910-002 Access to the Fuel Tanks and the Work Areas AMM 28-42-43-000-005 Removal of the Wing Tank Harness 57QT(58QT), 63QT(64QT)
 AMM 28-42-43-000-006 Removal of the Wing-Tank Inner-Cell Group A Harness R 13QT1(13QT2) R AMM 28-42-43-000-008 Removal of the Wing Tank Fuel Quantity Indicating R Probe Fused/Shorting Plug Connectors
 AMM 28-42-43-400-005 Installation of the Wing Tank Harness 57QT(58QT), 63QT(64QT) AMM 28-42-43-400-006 Installation of the Wing-Tank Inner-Cell Group A
 Harness 13QT1(13QT2) AMM 28-46-00-740-001 Functional (BITE) Test AMM 28-46-15-000-001 Removal of the Wing-Tank Fuel-Level Sensors AMM 28-46-15-400-009 Installation of the Wing-Tank Fuel-Level Sensors
 「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 ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 209
　
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油4(42)