(2)  
AIPC 28-22-01 Fig. 2

 (3)  
SSM 28-22-01

 (4)  
WDM 28-22-11, WDM 28-22-12, WDM 28-22-13, WDM 28-22-14

 B.  
Access

 (1)  
Location Zones
 521 Leading Edge to Front Spar, Left
 621 Leading Edge to Front Spar, Right

 (2)  
Access Panels
 521EB Lower Skin Leading Edge Access Panel
 621EB Lower Skin Leading Edge Access Panel

 C.  
Procedure

 S 864-002
 (1)  
Open the circuit breaker for the applicable engine and attach a DO-NOT-CLOSE tag:

 (a)  
P6 Main Power Distribution Panel
 1) 6G1 FUEL SHUTOFF VALVE ENG 1
 2) 6G2 FUEL SHUTOFF VALVE ENG 2
 3) 6G3 FUEL SHUTOFF VALVE ENG 3
 4) 6G4 FUEL SHUTOFF VALVE ENG 4

 S 014-003
 (2)  For the removal of the No. 1 or 4 engine spar valve actuator, do these steps:
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 28-22-01
 ALL  ú ú 01 Page 401 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
 WARNING: DO THE PROCEDURE IN AMM 27-81-00/201 TO DEACTIVATE THE
_______ LEADING EDGE FLAPS. THE LEADING EDGE FLAPS MOVE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (a)  
Do this task: Retracted Leading Edge Flaps Deactivation (AMM 27-81-00/201).

 (b)  
Remove access panel, 521EB or 621EB.

 S 014-053
 (3)  For the removal of the No. 2 or 3 engine spar valve actuator, do these steps:
 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE
_______ LEADING EDGE AND TRAILING EDGE FLAPS AND FLAP DRIVE MECHANISMS BEFORE YOU MOVE THE FLAP CONTROL LEVER. WITH HYDRAULIC POWER REMOVED, THE FLAPS WILL MOVE AUTOMATICALLY BY ELECTRICAL POWER WHEN YOU MOVE THE FLAP CONTROL LEVER.
 (a)  Extend the leading edge flaps (AMM 27-81-00/201).
 WARNING: DO THE PROCEDURE IN AMM 27-81-00/201 TO DEACTIVATE AND
_______ INSTALL LOCKS ON THE LEADING EDGE FLAPS. THE LEADING EDGE FLAPS MOVE QUICKLY AND CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (b)  Do this task: Extended Leading Edge Flaps Deactivation and Safety Locks Installation (AMM 27-81-00/201).
 S 034-007
 (4)  Disconnect the electrical connector (2) from the actuator (1).
 NOTE: Refer to the table that follows for the equipment numbers.
____
 ~................................................................. | | Equipment Number | | Location ............................ | | Valve | Connector | ................................................................... | No. 1 Engine Fuel Shutoff Valve | V13 | DV13 | | No. 2 Engine Fuel Shutoff Valve | V14 | DV14 | | No. 3 Engine Fuel Shutoff Valve | V15 | DV15 | | No. 4 Engine Fuel Shutoff Valve | V16 | DV16 | 2......................................…...........…..............1
 S 864-008
 (5)  Make sure the manual override lever on the actuator is in the closed position.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 28-22-01
 ALL  ú ú 01 Page 402 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 747-400 MAINTENANCE MANUAL
 (6)  S 034-009Remove the screw (8), washers (6), and nut (5) which attach the bonding jumper (7) to the actuator (1).
 (7)  S 034-064Remove the lockwire from the screws (3).
 (8)  S 034-010Remove the screws (3) and washers (4) which attach the actuator (1) to the index plate.
 (9)  S 024-011Remove the actuator (1).
 NOTE:____ Pull the actuator straight to disengage the actuator shaft from the adapter plate.

 TASK 28-22-01-404-012
 3. Engine Spar Valve Actuator Installation (Fig. 401)
_______________________________________
 A. Equipment
 (1)
Bonding Meter (SWPM 20-20-00) Approved for use in fuel vapor areas

 B.
Parts