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 WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE LE AND TE
_______ 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. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (4)  Move the flap control lever to the 5 unit detent to extend the LE flaps pneumatically.
 S 494-006
 WARNING: YOU MUST CAREFULLY DO THE STEPS IN THE TASK BELOW TO INSTALL
_______ THE LE FLAP SAFETY LOCKS. THE LE FLAPS CAN MOVE QUICKLY IF YOU DO NOT INSTALL THE SAFETY LOCKS CORRECTLY. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
 (5)  
Do this task: "Extended Leading Edge Flap Deactivation and Safety Lock Installation" (AMM 27-81-00/201).

 S 864-007

 (6)  
Do this task if hydraulic power is not necessary for hydraulic systems No. 1 and 4: "Hydraulic Power Depressurization" (AMM 29-11-00/201).

 S 864-008

 (7)  
Do this task if pneumatic power is not necessary: "Pneumatic Power Removal" (AMM 36-00-00/201).

 S 864-009

 (8)  
Do this task if electrical power is not necessary: "Electrical Power Removal" (AMM 24-22-00/201).

 E.
Procedure

 S 024-010
 (1)  
Remove the rotary actuator (Fig. 401):

 (a)  
Remove the nuts (8), washers (7), bushing (9) and bolts (6) that attach the rotary actuator (1) to the actuator link (10).

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747-400 MAINTENANCE MANUAL
 (b)
Disengage the drive shafts (5) from the rotary actuator (1).

 1)  Hold the drive shafts to prevent adjustment changes to the other rotary actuators.

 (c)
Remove the nuts (4), washers (3) and mounting bolts (2).

 (d)
Remove the rotary actuator (1) from the airplane.

 TASK 27-81-06-404-011
 3.  Krueger Flap Rotary Actuator Installation_________________________________________
 A.  Special Tools and Equipment
 (1)
G27013-9 Inboard Krueger Flap No. 11 thru 16 Rigging Set (Preferred)

 (2)
12MIT65B04017 Krueger Flaps Rigging Tool (Optional)

 (3)
17MIT65B04017 Leading Edge Flap Drive Unit Lock

 B.  
Consumable Materials

 (1)
D00013 Grease - MIL-G-23827

 (2)
C00308 Corrosion Preventive Compound - MIL-C-11796, Class 3

 C. Parts ~............................................................................... | AMM | | AIPC | ................. ................................| | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ................................................................................| | 401 | 1 | Actuator | 27-81-06 | 01 | 40 | | | 2 | Bolt | | | 15 | | | 3 | Washer (Under Head) | | | 25 | | | 3 | Washer (Under Nut) | | | 30 | | | 4 | Nut | | | 35 | | | 6 | Bolt (RH) | 27-81-01 | 01,05,| 115 | | | 6 | Bolt (LH) | | 10 | 120 | | | 7 | Washer (Under Head) | | | 125 | | | 7 | Washer (Under Nut) | | | 130 | | | 8 | Nut | | | 135 | | | 9 | Bushing | | | 140 | 2......…........…...............................…...........…........…..........1
 D.  References
 (1)
AMM 24-22-00/201, Manual Control

 (2)
AMM 27-81-00/201, Leading Edge Flap System

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 (3)  
AMM 29-11-00/201, Main Hydraulic Supply System

 (4)  
AMM 36-00-00/201, Pneumatic System

 (5)  
SSM 27-81-01, SSM 27-81-02, SSM 27-81-03, SSM 27-81-04,
 SSM 27-81-05, SSM 27-81-06

 (6)  
WDM 27-51-21, WDM 27-51-22, WDM 27-81-11, WDM 27-81-12,
 WDM 27-81-21, WDM 27-81-22, WDM 27-81-31, WDM 27-81-32,
　
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