(2) Examine the FLSS STATUS page on the MCDU:
(3) If a fault message(s) for one or more of the other FLSS sensors and/or the FLSCU-1 (7QJ) is shown:
- do (Ref. TASK 28-46-00-810-818).
(4) If the message 284615 C LO LEVEL SENSOR 21QJ:
- is shown, do Para. 4.A.
- is not shown: no work steps are necessary.
NOTE : You can get more data from the:
____
- Aircraft Maintenance Manual (AMM) Chap. 28-46-00, the Fuel Level Sensing System, Description and Operation (D and O)
- Trouble Shooting Manual (TSM) - Task Supporting Data (Ref.
P. Block 301)
- Aircraft Schematic Manual (ASM) (Ref. ASM 28-46/03). You can get more Trouble-shooting data from the CFDS(FUEL):
- Input Parameters Page 3 (Ref. P. Block 301), used with the Fuel Level Sensors Operating (Changeover) Values (Ref. P. Block 301)
- Trouble-shooting Data (Ref. P. Block 301).
「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 245
Aug 01/05R CES
NOTE : OPTIONAL TESTING:
____ Where a PSDA321-1 Test Set is available, a check can be made before a decision is made to go into or close up a fuel tank. The Test Set enables a GO/NOGO check to be made of the tank mounted components and wiring from the tank wall connectors.
**ON A/C ALL
4. Fault Isolation
_______________ **ON A/C 001-049, 051-061, 101-105, 201-203,
A. Procedure
(1) Do the steps applicable to the test equipment available.
(2) Test Equipment 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.
(a) If there is:
- approved test equipment available, go to Step (3)
- no approved test equipment available, go to Step (6).
(3) Get access to the tank wall connector 7509VC (for the center tank harness 17QT) in the right MLG bay (Ref. AMM TASK 32-12-00-010-001).
(4) Disconnect the free connector 7509VC-A from the receptacle 7509VC.
(5) Do a resistance check of the sensor 21QJ at the tank wall connector 7509VC between pins L and Y (Ref. AWM 28-46-09). Make sure the resistance is between 330 and 480 ohms. If there is:
- continuity as specified, go to Step (6)
- no continuity as specified (resistance check out of range), go to Step (9).
「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 246
Aug 01/05R
CES NOTE : The sensor status (wet or dry) and fuel/air temperature will
____ have an effect on the resistance value.
(6) Replace the FLSCU-1 (7QJ) (Ref. AMM TASK 28-46-34-000-001) and (Ref. AMM TASK 28-46-34-400-001).
(7) If the fault continues:
R (a) Get access to the tank wall connector 7509VC (for the center tank R harness 17QT) in the right MLG bay (Ref. AMM TASK 32-12-00-010-
001).
(b) Disconnect the free connector 7509VC-A from the receptacle 7509VC.
(c) Do a check (Ref. AWM 28-46-09) of the aircraft wiring (sensor input wire - H) between the FLSCU-1 rack connector AB, pin 12A and the tank wall free connector 7509VC-A, pin L.
(d) Do a check (Ref. AWM 28-46-09) of the aircraft wiring (sensor input wire - L) between the FLSCU-1 rack connector AB, pin 12B and the tank wall free connector 7509VC-A, pin Y.
(e) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-1 BITE 2 test command wire) between the FLSCU-1 rack connector AA, pin 15A and the FQIC rack connector AB, pin 7J.
(f) Do a check (Ref. AWM 28-46-09) of the aircraft wiring (FLSCU-1 LS6 output wire) between the FLSCU-1 rack connector AB, pin 2B and the FQIC rack connector AB, pin 3H.
R (g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-R 00-00).
(h) Connect the free connector 7509VC-A to the tank wall receptacle 7509VC.
(i) Do the test given in Para. 3.B.
(8) If the fault continues, do a test (Ref. AWM 28-21-07) with a multimeter to see if 28VDC is available at the FLSCU-1 (7QJ) rack connector AA, pin 1D.
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