27-81-41
ALL ú ú 01 Page 604 ú Jul 15/93
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
C. Access
(1)
Location Zones
302 Wing Outboard Leading Edge with Slats, LH
402 Wing Outboard Leading Edge with Slats, RH
D.
Procedure
S 026-005
(1) Disconnect the actuator from the slat (AMM 27-81-41/401).
S 866-022
WARNING:_______KEEP PERSONS AND EQUIPMENT AWAY FROM THE SLATS. THE SLATS CAN MOVE WHEN HYDRAULIC POWER IS SUPPLIED AND MAY CAUSE INJURY TO A PERSON OR DAMAGE TO EQUIPMENT.
(2)
Pressurize hydraulic system B (AMM 27-81-00/201).
S 216-007
(3)
Do a visual check of the lock indicator (Fig. 602):
CAUTION: MAKE SURE THAT THERE IS SUFFICIENT CLEARANCE BETWEEN
_______ DISCONNECTED ACTUATOR AND STRUCTURE BEFORE MOVING FLAP CONTROL LEVER TO RETRACT OR EXTEND SLATS. DAMAGE TO AIRPLANE OR EQUIPMENT CAN BE CAUSED BY INTERFERENCE COLLISION.
(a)
Move the flap control lever to the FLAP UP detent to retract the slats.
(b)
Make sure the lock indicator hole is open.
(c)
Put a 0.115-0.125 inch diameter steel rod in the lock indicator hole.
CAUTION: MAKE SURE THAT THERE IS SUFFICIENT CLEARANCE BETWEEN
_______ DISCONNECTED ACTUATOR AND STRUCTURE BEFORE MOVING FLAP CONTROL LEVER TO RETRACT OR EXTEND SLATS. DAMAGE TO AIRPLANE OR EQUIPMENT CAN BE CAUSED BY INTERFERENCE COLLISION.
(d)
Move the flap control lever to the 1-unit detent to extend the actuator to the intermediate position.
(e)
Make sure the actuator is not locked and extends to the intermediate position.
(f)
Remove the steel rod.
(g)
Make sure the lock indicator hole is covered.
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27-81-41
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
S 426-009
(4) Install the actuator to the slat (AMM 27-81-41/401).
NOTE: Install a new locking nut at disconected end of actuator
____ (do not re-use the old nut you removed. Install a new nut of the same kind to keep optimal nut locking action on bolt.
S 866-028
CAUTION: MAKE SURE THAT THERE IS SUFFICIENT CLEARANCE BETWEEN
_______ DISCONNECTED ACTUATOR AND STRUCTURE BEFORE MOVING FLAP CONTROL LEVER TO RETRACT OR EXTEND SLATS. DAMAGE TO AIRPLANE OR EQUIPMENT CAN BE CAUSED BY INTERFERENCE COLLISION.
(5)
Move the flap control lever to the FLAP UP detent to retract the slats.
(6)
Release pressure from hydraulic system B (AMM 27-81-00/201).
S 866-008
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27-81-41
ALL ú ú 03 Page 606 ú Nov 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
LEADING EDGE SLAT ACTUATOR ROD END - REMOVAL/INSTALLATION
_________________________________________________________
1. General
_______
A. This procedure contains instructions for the replacement of the actuator rod end switch assembly or actuator rod ends without the removal of the slat actuators from the airplane.
TASK 27-81-44-004-046
2. Leading Edge Slat Actuator Rod End Replacement
______________________________________________
A. General
CAUTION: MAKE SURE THERE IS NO VIBRO-ENGRAVING IDENTIFICATION ON THE ROD
_______ ENDS. VIBRO-ENGRAVING CAUSES STRESS RISERS IN THE ROD ENDS AND CAN RESULT IN ROD END CRACKING. VIBRO-ENGRAVING IS NOT AN ACCEPTABLE METHOD FOR IDENTIFICATION.
(1)
Obey this CAUTION during all of this task.
B.
Special Tools and Equipment
(1)
C27012-1 - Leading Edge Slat Actuator Lockout Set ú (2) MIT65C38058-1 or C27071-1 (optional) Leading Edge Slat Actuator Rod ú End Replacement Tool
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本文鏈接地址：737-300 400 500 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 6(85)
