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 primer.
 S 424-013
 (3)  Put the fill port in the opening on the top wing skin.
 S 864-015
 (4)  Go into the tank (AMM 28-11-00/201).
 S 434-022
 (5)  Put the seal ring on the fill port.
 S 434-023
 (6)  Put the retaining nut on the fill port.
 S 434-024
 (7)  Tighten the retaining nut with a torque spanner.
 (a) Tighten the nut to 30-40 foot-pounds (41 - 54 newton-meters).
 S 284-029
 (8)  Measure the bonding resistance across these surfaces:
 NOTE: The total resistance across each bond must not be more than____
 0.010 ohm.
 (a) Retaining nut and seal ring
 (b) Seal ring and lower surface of the wing skin.
 S 434-016
 (9)  Attach a lockwire to the lug on the retaining nut and the structure.
 S 434-017

 (10)
 Attach the filler cap lanyard to the lug on the retaining nut. S 414-018

 (11)
 Get out of and close the fuel tank (AMM 28-11-00/201). S 864-032

 (12)
 Go to the overwing fill port on the wing.

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 ALL  ú ú 01 Page 405 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 S 284-030
 (13) Measure the bonding resistance across these surfaces: NOTE: The total resistance across the bond must not be more than
____
 0.010 ohm.
 (a)
Fill port and upper surface of the wing skin. S 394-036

 (14)
 Apply aerodynamic smoother (BAC 5030) around the periphery of the fill port.

 NOTE: Make sure the aerodynamic smoother is flush with the upper
____
 surface of the wing skin.

 S 864-033
 WARNING:_______MAKE SURE THE FILLER CAP IS FULLY CLOSED. IF THE FILLER CAP IS NOT FULLY CLOSED, FUEL CAN LEAK THROUGH THE FILL PORT IN FLIGHT.
 (15)
 Install and fully close the filler cap.

 F.  
Put the Airplane Back to the Usual Condition S 944-034

 (1)  
Remove the maintenance mats from the wing top surface.
 S 654-019

 (2)  
Fill the applicable fuel tank with fuel (AMM 12-11-01/301).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú 01 Page 406 ú Jun 18/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 CENTER WING TANK PURGE DOOR - REMOVAL/INSTALLATION
__________________________________________________
 1.  General_______
 A.  This section supplies instructions to remove and install the purge door for the center wing tank.
 B.  The purge door for the center wing tank is found in the right body gear wheel well. It is installed near the inboard end of the rear spar in the center wing tank.
 C.  The door locks for the wing and body gear must be installed when you are in the wheel well area.
 D.  Remove the electrical power on the airplane before you remove the access door.
 E.  Do not put back the electrical power on the airplane until the tank is closed and is safe.
 TASK 28-11-06-004-001
 2.  Center Wing Tank Purge Door Removal (Fig. 401)___________________________________
 A.  Equipment
 (1)  
Lanyard - to attach to purge door

 B.  
References

 (1)  
AMM 24-22-00/201, Manual Control

 (2)  
AMM 28-26-00/201, Defueling

 (3)  
AMM 32-00-30/201, Landing Gear Door Locks

 (4)  
AIPC 57-14-05 Fig. 1

 C.  
Access

 (1)  
Location Zone
 136 Wing Landing Gear Well, Right

 D.  
Procedure

 S 654-002
 (1)  
Defuel the center wing tank (AMM 28-26-00/201).

 (2)  
Remove the electrical power (AMM 24-22-00/201).

 (3)  
　
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