A320飞机维护手册 AMM FUEL 燃油3(65)

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R  (8) Remove the EXTRACTOR TOOL from the fuel pump (2) and the slide valve. 
R R  (9) Push the fuel pump (2) and the slide-valve up and fully into the fuel pump canister.
 (10) Install the bolts (3).
 (11) TORQUE the bolts (3) to 1.13 m.daN (99.99 lbf.in).
 (12) Do the steps that follow:
 (a) Do a visual inspection of the electrical harness you can see, for signs of wear and electrical arcing. If you find damage, replace the electrical harness.
 (b) Do a visual inspection of the aircraft structure (in the area adjacent to the electrical harness), for signs of damage caused by arcing. If you find damage refer to the (Ref. SRM 51-73-00) for the correct repair procedure.
 (13) Remove the blanking caps from the electrical connector and receptacle (14).
 (14) Connect the electrical connector to the electrical receptacle (14).

 

 (15) Do a check of the electrical bonding between the fuel pump (2) and the wing structure (Ref. TASK 20-28-00-720-006).
 Subtask 28-21-51-860-050
 C. Aircraft Maintenance Configuration
 (1)
 Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

 (2)
 Refuel the applicable wing tank to a minimum of 1000 kg (2204.6220 lb), (Ref. TASK 12-11-28-650-003).

 Subtask 28-21-51-790-054
 D. Leak Test
 (1)
 Examine the fuel pump (2), the slide valve and the fuel pump canister for fuel leaks.

 (2)
 If signs of fuel leakage are found, examine the applicable landing light assembly for fuel contamination (Ref. TASK 33-42-11-000-001).

 Subtask 28-21-51-865-118
 E. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
 -
FOR 21QA, 25QA
 1QA, 7QA, 11QA

 -
FOR 22QA, 26QA
 2QA, 8QA, 12QA.

 

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 Subtask 28-21-51-710-051
 F. Operational Test
 (1) Do this test:
 -------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On panel 40VU:
1. Start the applicable fuel pump:
 -
for 21QA, push (in) the L TK PUMPS 1 pushbutton switch (P/BSW)

-
for 25QA, push in the L TK PUMPS 2 P/BSW

-
for 22QA, push in the R TK PUMPS 1 P/BSW

-
for 26QA, push in the R TK PUMPS 2 P/BSW.

2. Stop the applicable main fuel pump:
 -
for 21QA, release (out) the L TK PUMPS 1 P/BSW

 -
for 25QA, release (out) the L TK PUMPS 2 P/BSW

 -
for 22QA, release (out) the R TK PUMPS 1 P/BSW

 -
for 26QA, release (out) the R TK PUMPS 2 P/BSW.

On panel 40VU:
-
the P/BSW OFF light goes off

-
the L TK PUMPS 1 P/BSW FAULT lightcomes on momentarily

-
the P/BSW OFF light goes off

-
the L TK PUMPS 2 P/BSW FAULT light comes on momentarily

-
the P/BSW OFF light goes off

-
the R TK PUMPS 1 P/BSW FAULT light comes on momentarily

-
the P/BSW OFF light goes off

-
the R TK PUMPS 2 P/BSW FAULT light comes on momentarily.

-
the P/BSW OFF light comes on

-
the P/BSW OFF light comes on

-
the P/BSW OFF light comes on

-
the P/BSW OFF light comes on.

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 Subtask 28-21-51-420-055
 G. Installation of the Fuel Pump (Completion)
 (1)
 If applicable, use a clean MISCELLANEOUS (Material No. 19-003) made moist with CLEANING AGENTS (Material No. 11-026) to clean all the remaining sealant from

 -
the front fairing (7)

 -
the under-wing skin interface.

 

 (2)
 Install the front fairing (7) and the cover-plate (5) assembly as follows:

 NOTE : Sealant is not used between the front fairing (7) and the
____
 under-wing skin.

 (a)
 Install the front fairing (7) and the cover-plate (5) assembly. Make sure that the fuel pump cables are not caught.

 (b)
 Hold the front fairing (7) and the cover-plate (5) assembly in position and install it with the bolts (6).

 (c)
 TORQUE tighten the bolts (6) to 1.13 m.daN (99.99 lbf.in).

 5. Close-up
________ Subtask 28-21-51-860-051
 A. Aircraft Maintenance Configuration
 (1)
 Refuel, defuel or transfer fuel as necessary (Ref. TASK 12-11-28-650-003), (Ref. TASK 28-25-00-650-001) or (Ref. TASK 28-25-00-869-001).
　
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