(2)  
Check that following switches are in OFF position:

(a)  
ALT FLAP Master Arming Switch

(b)  
System A Control Switch

(c)  
System B Control Switch

(3)  
Position ALT FLAP arming switch to ARM.

(4)  
Repeat steps (N) and (O).

5.  Restore Airplane to Normal Configuration
A.  Retract flaps.
CAUTION:  TO PRECLUDE STRUCTURAL DAMAGE, MONITOR FLAP NOSE CLEARANCE DURING RETRACTION.
B.  Disconnect electrical power.
C.  Depressurize hydraulic system (Ref 27-81-0 MP).
D.  Check hydraulic reservoirs and service if required (Ref Chapter 12, Hydraulic Servicing).
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LEADING EDGE FLAP ACTUATORS - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limit charts. There will be no procedure given for gaining access to the component, for removing it, or for replacing it after inspection for wear. Refer to Leading Edge Flap Actuators - Removal/Installation for this information.
2.  Leading Edge Flap Actuators Wear Limits (Fig. 601)

G42918 E80984
505  Leading Edge Flap Actuators Wear Limits 
Feb 20/90  Figure 601 (Sheet 1)  27-81-31 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Leading Edge Flap Actuators Wear Limits  505 
27-81-31  Figure 601 (Sheet 2)  May 01/98 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

LEADING EDGE SLAT ACTUATOR - REMOVAL/INSTALLATION
1.  General
A.  The slat actuator contains blocking valves which hydraulically lock the actuator piston in position when hydraulic pressure is removed. The actuator must be retracted to remove it from the wing. This makes it necessary to have hydraulic pressure available to retract the actuator.
2.  Equipment and Materials
A.  Leading Edge Slat Actuator Locks - F80048-57, F80048-79
B.  Corrosion Preventive Compound - MIL-C-11796 class 3 (Ref 20-30-21)
3.  Remove Leading Edge Slat Actuator
A.  Remove access panels adjacent to slat actuator and panel aft of actuator door.
B.  Provide system A hydraulic power (Ref 27-81-0, MP).
C.  Position flap control lever to 1-unit detent to extend slats.
D.  Depressurize hydraulic systems (Ref 27-81-0, MP).
E.  Install locks on adjacent leading edge slats.
F.  Remove slat actuator door and seal door strap angles from actuator (Detail B, Fig, 401).
NOTE: Due to spring tension, release seal door straps slowly.
G.  Remove seal and access panel from slat at actuator rod end for access to electrical connector and rod end attach bolt.
531 
Feb 20/86  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-41 Page 401 

G42903
Leading Edge Slat Actuator Installation  525 
27-81-41  Figure 401  Feb 20/86 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

H.  Disconnect slat actuator from slat (Detail A).
I.  Disconnect actuator switch leads at electrical connector.
J.  Pressurize hydraulic system A (Ref 27-81-0).
K.  Place flap lever in FLAP UP detent to retract actuator.
L.  Depressurize hydraulic systems (Ref 27-81-0).
M.  Disconnect wire bundle conduit clamps, as necessary.
N.  Remove bolts from inboard rib at actuator and remove rib lower chord.
O.  Remove clamps securing hydraulic lines to wing structure.
NOTE: Tag all hydraulic lines and ports to ensure correct replacement.
P.  Disconnect hydraulic lines from actuator and swivel joints. Instal1 plugs in hydraulic lines and cap all ports.
Q.  Disconnect actuator from support fitting in wing and remove actuator.
4.  Install Leading Edge Slat Actuator
A.  If existing bushings, bearings and balls are being installed, check for allowable wear (Ref 27-81-41).
B.  Ensure that hydraulic systems are depressurized (Ref 27-81-0).
C.  Connect actuator to support fitting in wing with bolt, clamp-up bushing, and washer on each side. Install locknut and tighten to 800-1000 pound-inches (Section A-A, Fig. 401).
D.  Connect hydraulic lines to actuator and swivel joints and install clamps securing lines to wing structure.
CAUTION:  TO PREVENT POSSIBLE DAMAGE TO ACTUATOR, ENSURE LINES ARE MATED TO THEIR PROPER PORTS AND FITTINGS; THEN REMOVE IDENTIFYING TAGS.
　
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