R (6) Replace the FLSCU-1 (7QJ) (FLSCU-2 (9QJ)), (Ref. AMM TASK 28-46-34-000-001) and (Ref. AMM TASK 28-46-34-400-001).
R (7) If the fault continues:
R (a) Get access to the tank wall connector 4039VC1(2)-A (for the wing R tank harness 57QT(58QT)) (Ref. AMM TASK 28-42-43-000-008).
R (b) Disconnect the free connector 4039VC1(2)-A from the receptacle R 4039VC1(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-1(2) rack connector AB, pin 15A and the tank wall free connector 4039VC1(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-1(2) rack connector AB, pin 15B and the tank wall free connector 4039VC1(2)-A, pin <W.
R (e) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-1 BITE 2 test command line) between the FLSCU-1 rack connector AA, pin 15A and the FQIC rack connector AB, 14E, or the (aircraft wiring (FLSCU-2 BITE 2 test command line) between the FLSCU-2 rack connector AA, pin 15A and the FQIC rack connector AB, 12E).
R (f) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-1 LS1 output line) between the FLSCU-1 rack connector AB, pin 1A and the FQIC rack connector AC, 4D, or the (aircraft wiring (FLSCU-2 LS1 output line) between the FLSCU-2 rack connector AB, pin 1A and the FQIC rack connector AC, 2G).
R (g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-R 00-00).
R (h) Connect the free connector 4039VC1(2)-A to the receptacle R 4039VC1(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 A, L WING TK (57QT) ( R HARNESS - GROUP A, R WING TK (58QT)) (Ref. AWM 28-46-04) 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 215
May 01/05 CES
R (c) If the harness is serviceable, replace the SENSOR-LOW LEVEL
R (750KG), L WNG TK INR REAR CHANNEL A (16QJ1) (SENSOR-LOW LEVEL
R (750KG), R WNG TK INR REAR CHANNEL A (16QJ2)) (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 216
May 01/05 CES
**ON A/C ALL
TASK 28-46-00-810-803
L(R) High Level Sensor 17QJ1(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)
- FLSCU-2 (9QJ)
- SENSOR-HI LEVEL, LEFT WING TANK INNER CHANNEL A (17QJ1)
- SENSOR-HI LEVEL, RIGHT WING TANK INNER CHANNEL A (17QJ2)
- 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
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本文链接地址：A320 Trouble Shooting Manual 排故手册 FUEL 燃油4(45)
