CAUTION:  DEFLECT SPRINGS ONLY AS FAR AS REQUIRED. PERMANENT SET IN SPRINGS MAY OCCUR.

(b)  
On airplanes with single hook and spring seal door, open and remove spring hook fastened to fixed leading edge structure.

(c)  
Slide seal door along seal guide and spacer until clear.

(d)  
Replace seal door assembly as necessary.

(2)  
Install seal door assembly as follows:

(a)  
Slide seal door inside seal guide and spacer.

(b)  
On airplanes with single hook and spring seal door, fasten spring hook to fixed leading edge structure and close.

(c)  
Press flat spring upward and slide seal door forward sufficient enough to hook flat spring to auxiliary track.

CAUTION:  DEFLECT SPRINGS ONLY AS FAR AS REQUIRED. PERMANENT SET IN SPRINGS MAY OCCUR. ENSURE THAT FLAT SPRING HOOKS PROPERLY TO AUXILIARY TRACK DURING LEADING EDGE SLAT EXTENSION.
4.  Restore Airplane to Normal Configuration
A.  Close access doors and install access panels.
B.  Provide system A hydraulic power (Ref 27-81-0 MP).
C.  Remove leading edge slat locks from leading edge slat actuators (Ref 27-81-0 MP).
D.  Remove tag or placard from flap control lever and position flap control lever to FLAP UP detent to retract leading edge devices.
E.  Depressurize hydraulic system A (Ref 27-81-0 MP).
500 
Oct 20/86  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-51 Page 405 

LEADING EDGE FLAP AND SLAT HYDRAULIC FUSE - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Hydraulic Fluid, Fire Resistant - BMS 3-11
B.  Skydrol Assembly Lube - MCS 352
2.  Remove Hydraulic Fuse
A.  Depressurize hydraulic systems (Ref 27-81-0 MP).
B.  Disconnect inlet and outlet hydraulic lines and remove hydraulic fuse (Fig. 401).
3.  Install Hydraulic Fuse
CAUTION:  MAKE SURE YOU USE THE 160 CUBIC INCH FUSE. MISPLACEMENT OF FUSES CAN CAUSE PARTIAL AND ASYMMETRICAL EXTENSION OF THE LEADING EDGE SURFACES.
A.  Remove reducer from each end of removed fuse and install on replacement fuse using new 0-rings. Lubricate 0-rings with hydraulic fluid or Skydrol Assembly Lube prior to installation.
NOTE:  Make sure you install the applicable hydraulic fuse (160 cubic inch) in the correct position for flow as shown in adjacent placards.
B.  Place fuse in position being sure flow direction arrow points outboard (Fig. 401).
C.  Tighten inlet and outlet line.
D.  Pressurize hydraulic systems (Ref 27-81-0 MP).
E.  Make sure there are no leaks.
F.  Depressurize hydraulic systems (Ref 27-81-0 MP).
G.  Check hydraulic reservoirs and service if required (Ref Chapter 12, Hydraulic Servicing).
H.  Do a check of the leading edge flap and slat alternate system operation (AMM 27-81-0/501).
500 
Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-61 Page 401 

G42616
Leading Edge Flap Hydraulic Fuse  500 
27-81-61  Figure 401  May 15/67 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

LEADING EDGE FLAP FLOW LIMITING VALVE - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Hydraulic Fluid, Fire Resistant - BMS 3-11
B.  Skydrol Assembly Lube - MCS 352
2.  Remove Flow Limiting Valve
A.  Depressurize hydraulic systems. Refer to 27-81-0, Leading Edge Flaps and Slats -Maintenance Practices.

B.  Disconnect inlet and outlet hydraulic lines and remove flow limiting valve (Fig. 401).
3.  Install Flow Limiting Valve
A.  Remove reducer from each end of removed valve and install on replacement valve using new 0-rings. Lubricate 0-rings with hydraulic fluid or Skydrol Assembly Lube prior to installation.
B.  Place valve in position being sure the regulated flow direction arrow points forward (Fig. 401).
C.  Tighten inlet and outlet line.
D.  Check hydraulic reservoirs and service if required. Refer to Chapter 12, Hydraulic Servicing.
E.  Test flap flow limiting valve. Refer to Leading Edge Flap Flow Limiting Valve - Adjustment/Test.
500 
May 15/81  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-71 Page 401 

G43005
Leading Edge Flat Flow Limiting Valve  500 
27-81-71  Figure 401  May 15/67 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 
　
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