(i)  
Place alternate flaps arming switch to ARM position.

(j)  
Check that standby hydraulic system low pressure light is off.

(k)  
Observe leading edge flaps and slats for 60 seconds. Verify that flaps and slats do not extend.

(l)  
Place alternate flaps arming switch in OFF position.

NOTE:  Leading edge flaps may slowly extend due to gravity.
531 
Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-0 Page 521 

(12) Check for leading edge flap droop.
(a)  
Pressurize hydraulic system A.

(b)  
Place flap control lever in FLAP UP position to fully retract leading edge devices.

(c)  
Depressurize hydraulic system A. Bleed off hydraulic pressure to zero psi.

(d)  
After a one-minute wait, measure gap between lower surface of flap trailing edge and adjacent wing skin lower surface at outboard end of inboard flap and inboard end of outboard flap.

(e)  
Check that gap does not exceed 2.0 inches for new or overhauled actuators or 4.0 inches for inservice units.

C.  Restore Airplane to Normal Configuration
(1)  
Remove system A hydraulic power (Ref 29-11-0 MP).

(2)  
Close hydraulic ground interconnect valve.

(3)  
Lockwire alternate flap master arming switch.

(4)  
Determine if there is any further need for electrical power on airplane. If not, disconnect power.

(5)  
Install all access panels.

531 
27-81-0 Page 522  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/87 

LEADING EDGE FLAPS - REMOVAL/INSTALLATION
1. General
A.  The following procedure applies to the inboard and outboard leading edge flaps. If both flaps are being replaced, the inboard flap should be installed and adjusted first.
2.  Equipment and Materials
A.  Leading Edge Flap Lock - F80048-84 (preferred), -36 (optional)
B.  Corrosion Preventive Compound - MIL-C-11796, Class 3 or MIL-C-16173, Grade 2 (Ref 20-30-21)
C.  Aerodynamic Smoother - BMS 5-79, Class B (Ref 20-30-11)
D.  Chemical and Solvent Resistant Finish - BMS 10-11, type 1 (Ref 20-30-41)
E.  Protractor Assembly - 4MIT65B80307-1 (preferred), F52485-500 (optional)
3.  Remove Leading Edge Flap (Fig. 401)
A.  Provide system A hydraulic power (Ref 27-81-0 MP).
B.  Extend leading edge flaps.
C.  Remove system A hydraulic power (Ref 27-81-0 MP).
D.  Install leading edge flap actuator lock on actuator of flap adjacent to flap being removed.
WARNING:  INSTALL LEADING EDGE FLAP ACTUATOR LOCK WHEN FLAP IS IN EXTENDED POSITION. FLAPS ARE FAST ACTING AND CAN CAUSE SERIOUS INJURY TO PERSONNEL.
E.  At all flap nose operating linkages except inboard linkage of inboard flap, disconnect flap nose links from lugs in wing leading edge.
531 
Feb 20/87  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-81-12 Page 401 

G42416
Leading Edge Flap Installation  521 
27-81-12  Figure 401  Feb 15/73 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

521  Leading Edge Flap Installation 
Feb 15/73  Figure 401 (Sheet 2)  27-81-12 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

G44219G44231
Leading Edge Flap Installation  521 
27-81-12  Figure 401 (Sheet 3)  Sep 20/81 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

504  Leading Edge Flap Installation 
Jan 20/83  Figure 401 (Sheet 4)  27-81-12 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

F.  At inboard linkage of inboard flap, if existing flap nose rod can be used, disconnect rod from operating crank on flap panel and leave installed in wing (Details A and B, Fig. 401). If existing flap nose rod cannot be used, remove landing light lens on wing leading edge for access and disconnect flap nose rod from lug in wing.
G.  Disconnect flap actuator from flap panel.
H.  Disconnect bonding jumpers.
I.  At inboard hinge of inboard flap, if existing hinge fitting can be used, disconnect hinge fitting from flap panel by removing two bolts and leave hinge fitting installed in wing. If existing hinge fitting cannot be used, remove landing light lens from wing leading edge and forward wing to body fairing for access and remove hinge bolt (detail B).
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 3(158)