3. Fault Confirmation
__________________
A. Table of the circuit breakers referred to in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------
121VU FUEL/L WING TK/PUMP2 SPLY 7QA N26
B. Test
WARNING : DO NOT CLOSE AN OPEN (TRIPPED) CIRCUIT BREAKER RELATED TO A
_______ FUEL-PUMP. IF YOU CLOSE THE CIRCUIT BREAKER, THERE IS A RISK:
- OF FIRE OR OF AN EXPLOSION
- OF DAMAGE TO THE AIRCRAFT WIRING AND STRUCTURE.
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(1) Examine the C/B-FUEL/L WING TK/PUMP 2 SPLY (7QA).
(2) If the C/B-7QA:
(a) Is open (tripped), do Fuel - L(R) Wing Tank Pumps 2, Power Supply
- C/B-7QA(8QA) Tripped (Ref. TASK 28-21-00-810-828).
(b) Is closed (set), do the Operational Test of the Wing-Tanks Fuel Control (Ref. AMM TASK 28-21-00-710-001).
4. Fault Isolation
_______________
R **ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
A. Procedure
(1) If a fuel low pressure indication is shown for the left wing tank fuel pump No. 2 (25QA):
- do a fuel transfer (Ref. AMM TASK 28-21-00-710-007) use the left wing tank fuel pump No. 2 to do the fuel transfer.
(2) If the fuel starts to transfer go to step (3). If the fuel does not start to transfer:
(a) Set the L TK PUMPS 2 P/BSW (15QA) to OFF (release out). This will de-energize the contactor 19QA.
(b) Before you do more steps, make sure that the wing area adjacent to the left inner fuel pump 25QA fairings and cover is not contaminated with fuel from a fuel leak or spillage.
1 If necessary:
_ a Repair all the leaks:
_
- (Ref. AMM TASK 51-76-12-300-001)
- (Ref. AMM TASK 51-76-12-300-002)
- (Ref. SIL 57-0086).
b Clean the area of the fuel spillage.
_
(c) Remove all the fuel pump 25QA cable fairings (Ref. AMM TASK 28-21-49-000-001) and cover assembly (Ref. AMM TASK 28-21-51-000-001).
(d) Disconnect the supply cable end connector 25QA-A from the fuel pump receptacle.
(e) If, in step (c) or (d), any damage can be seen on the supply cable or the aircraft structure, go to step (j) 1_.
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(f) Set the L TK PUMPS 2 P/BSW (15QA) to ON (push in). This will energize the contactor 19QA and the 115VAC three phases will be supplied to the fuel pump connector 25QA-A.
(g) Use a multimeter to do a test, to make sure that each of the 115VAC three phases are available at the connector 25QA-A (Ref. ASM 28-21/02).
(h) Set the L TK PUMPS 2 P/BSW (15QA) to OFF (release out). This will de-energize the contactor 19QA.
1 Use a multimeter to do a test, to make sure that each of the
_ 115VAC three phases are not available at the connector 25QA-A.
NOTE : This is to make sure that the contactor 19QA does not
____ stay in the on position (stuck/held on).
(i) If the 115VAC three phase supply voltage measured in step (g) is correct:
1 Replace the PUMP-FUEL NO 2, L WING TK (25QA) (Ref. AMM TASK
_ 28-21-51-000-001) and (Ref. AMM TASK 28-21-51-400-001).
2 If the fault continues, replace the SEQUENCE VALVE of the
_ fuel-pump (25QA) (Ref. AMM TASK 28-21-45-000-001) and (Ref. AMM TASK 28-21-45-400-003).
(j) If the 115VAC three phase supply voltage measured in step (b) is not correct (no voltage, incorrect voltage or a phase is missing), do all the sub-steps that follow:
1 Clean and dry:
_
- all the fuel pump cable fairings
- the fuel pump cover assembly
- the fuel pump supply cable and the related end connector
- the aircraft wing structure adjacent to the route of the supply cable across the wing surface
- the aircraft wing structure at the rear spar, adjacent to the landing light, where the fuel pump supply cable leaves the conduit and passes through the cable guide (bottom skin). 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 FUEL 燃油1(90)
