(4) If the message 284616 L(R) SURGE SENSOR 28QJ1(2):
 - 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 28-46/04). You can get more Trouble-shooting data from the CFDS(FUEL):

 - Input Parameters Page 3 (Ref. P. Block 301)

 - Trouble-shooting Data (Ref. P. Block 301).

 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
_______________
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
 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 4047VC1(2)-A (for the vent surge tank harness 34QJ1(2)) (Ref. AMM TASK 28-46-43-000-001).
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 295
 Aug 01/05 CES

 (4) Disconnect the free connector 4047VC1(2)-A from the receptacle 4047VC1(2).

 (5) Do a resistance check of the sensor 28QJ1(2) at the tank wall connector 4047VC1(2) between pins A and B (Ref. AWM 28-46-11) and (Ref. AWM 28-46-12). Make sure the resistance is between 330 and 480 ohms. If there is:

 - continuity as specified above, go to Step (6)

 - no continuity as specified above (resistance check out of range), go to Step (8).

 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) (FLSCU-2 (9QJ)) (Ref. AMM TASK 28-46-34-000-001) and (Ref. AMM TASK 28-46-34-400-001).

 (7) If the fault continues:

 (a) Get access to the tank wall connector 4047VC1(2)-A (for the vent surge tank harness 34QJ1(2)) (Ref. AMM TASK 28-46-43-400-001).

 (b) Disconnect the free connector 4047VC1(2)-A from the receptacle 4047VC1(2).

 (c) Do a check (Ref. AWM 28-46-11), and (Ref. AWM 28-46-12) of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 14A and the tank wall free connector 4047VC1(2)-A, pin A.

 (d) Do a check (Ref. AWM 28-46-11), and (Ref. AWM 28-46-12) of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 14B and the tank wall free connector 4047VC1(2)-A, pin B.

 (e) Do a check (Ref. AWM 28-46-01) of the aircraft wiring (FLSCU-1 BITE 1 test command line) between the FLSCU-1 rack connector AA, pin 15B and the FQIC rack connector AB, pin 7H or the (aircraft wiring (FLSCU-2 BITE 1 test command line) between the FLSCU-2 rack connector AA, pin 15B and the FQIC rack connector AB, pin 10H).

 (f) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-1 LS4 output line) between the FLSCU-1 rack connector AB, pin 1B and the FQIC rack connector AB, pin 2K or the (aircraft wiring (FLSCU-2 LS4 output line) between the FLSCU-2 rack connector AB, pin 1B and the FQIC rack connector AB, pin 10K).

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 296
 201-299, 401-499, Aug 01/05 CES

 (g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-00-00).

 (h) Connect the free connector 4047VC1(2)-A to the receptacle 4047VC1(2).

 (i) Do the test in Para. 3.A.

 (8) If the fault continues or if there is no continuity in Step (5):
 (a) Drain, open and vent the tank (Ref. AMM TASK 28-10-00-910-001) and (Ref. AMM TASK 28-10-00-910-002).
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油4(76)