(2)
Check that leading edge flaps and slats fully extend.
K. Position alternate flap drive control switch to OFF. Check that leading edge flaps and slats do not move.
L. Position flap control lever to FLAP UP detent. Check that leading edge flaps and slats do not respond.
M. Position alternate flap arming switch to OFF.
(1)
Check that manual override lever on valve moves to position No. 1.
(2)
Check that leading edge flaps and slats fully retract.
NOTE: Retraction is due to hydraulic system A being pressurized.
N. Repeat steps H, I, J, K, L and M to bleed standby hydraulic system by actuating leading edge devices.
O. Check leading edge standby drive shutoff valve hydraulic fittings for leakage.
P. Close TE ALT FLAP DRIVE MOTOR circuit breaker.
Q. Depressurize hydraulic systems (Ref 27-81-0).
R. Lockwire alternate flap master arming switch.
S. Remove electrical power if no longer required.
500
Feb 20/87 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-81-91 Page 501
LEADING EDGE SLAT ACTUATOR SWITCH - REMOVAL/INSTALLATION
1. General
A. The following procedure provides instructions for replacement of reed switch assembly on leading edge slat actuators without removing actuators from airplane.
2. Equipment and Materials
A. Leading Edge Slat Locks - F80048-57, F80048-79
B. Silicone Adhesive Sealant - RTV 174 (BAC5010 TYPE 60) (Ref 20-30-11).
C. Heat-Shrinkable Sleeve - Thermofit RNF-100-2 (Rayclad Tubes, Inc.)
D. Tying Braid, Flat Woven Dacron - Airtex 417X, 0.012 X 0.090 inch (Eon Corp.)
E. Connector Pin Insertion Tool - ST2220-2-4
F. Connector Pin Removal Tool - ST2220-3-14
G. Electrical Wire, Single Conductor, Insulated - BMS 13-16, Type I, Class I (22 gage)
H. Sleeve, Braided Shield (Inner) - GS080 (Thomas and Betts)
I. Sleeve, Braided Shield (Outer) - GS149 (Thomas and Betts)
J. Wire Rope - MIL-W-83420, Type II, 3/64-Inch Diameter
K. Heat Shrink Tubing - RT-876-1/8, 0.12 x 4.0 inch (Raychem Corp.)
L. Heat Shrink Tubing - RT-876-3/16, 0.19 x 1.0 inch (Raychem Corp.)
3. Remove Leading Edge Slat Actuator Switch
A. Remove access panels adjacent to slat actuator and panel aft of actuator door.
B. Provide system A hydraulic power (Ref 27-81-0, - Maintenance Practices).
C. Position flap control lever to fully extend flaps and slats.
531
Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-81-111 Page 401
G43283G43297
Leading Edge Slat Actuator Switch Installation 527
27-81-111 Figure 401 (Sheet 1) Jun 20/85
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
527 Leading Edge Slat Actuator Switch Installation
Jun 20/85 Figure 401 (Sheet 2) 27-81-111
Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Remove system A hydraulic power (Ref 27-81-0).
E. Install locks on slat actuators adjacent to slat where switch is being replaced.
F. Remove seal and access door from slat for access to electrical connector and rod end attach bolt.
G. Remove slat rod end attach bolt (Detail A, Fig. 401).
H. Disconnect electrical connector.
I. Provide system A hydraulic power (Ref 27-81-0).
J. Place flap control lever to FLAP UP detent to fully retract actuator.
K. Remove system A hydraulic power (Ref 27-81-0).
L. Mark a point on actuator housing close to outer piston, but not on piston. Measure as accurately as possible, the distance from this point to centerline of rod end bolt. Record measurement and retain for use in reinstallation of rod end.
NOTE: This dimension will be used to set rod end length on installation if inside calipers are not available or clearance prevents their use.
M. Cut switch leads between rod end and connector plug.On rod end assemblies with wire rope hole, cut wire rope joining rod end and connector plug (Detail C, Fig. 401).
N. Remove sealant from rod end and locknut. Remove lockwire from nut and locking key.
O. Back off locknut and remove rod end assembly.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(172)
