曝光臺(tái) 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)者

(WARNING PRECEDES)
CAUTION: DO NOT TURN THE MANUAL DRIVE WITH MORE THAN 350 POUND-INCHES (39.5
NEWTON-METERS) TORQUE OR FASTER THAN 1000 RPM. YOU CAN CAUSE
DAMAGE TO THE POSITION SENSOR GEARBOX AND THE TORQUE TUBES.
(4) Use a 3/8 inch square drive to turn the manual drive on the PDU to extend the trailing edge flaps
to the applicable position.
NOTE: Refer to the cover [4] for the correct direction to turn the manual drive.
NOTE: Look at the number 4 or 5 ballscrew to find the position of the flaps.
SUBTASK 27-51-00-980-006
WARNING: MAKE SURE THE POSITION OF THE FLAPS AGREE WITH THE POSITION OF THE FLAP
CONTROL LEVER. WHEN YOU SUPPLY HYDRAULIC POWER THE FLAPS WILL MOVE
AUTOMATICALLY TO THE POSITION OF THE FLAP CONTROL LEVER. THIS CAN
CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(5) To retract the trailing edge flaps, turn the manual drive in the retract direction until the flaps are
in a position which agrees with the flap control lever.
SUBTASK 27-51-00-410-009
(6) Install the cover [4] on the flap power drive unit [1]:
(a) Apply fluid, D00467 to the packing [5] on the cover [4].
(b) Apply a thin layer of compound, C00913 to the mating surface of the cover [4] and the flap
power drive unit [1].
(c) Put the cover [4] in its position on the flap power drive unit [1].
(d) Apply compound, C00913 to the shank and threads of the bolts [3].
(e) Install the bolts [3] and washers [2] to attach the cover [4].
SUBTASK 27-51-00-440-004
(7) Do this task: Trailing Edge Flap System Reactivation, TASK 27-51-00-440-801.
L. Put the Airplane Back to Its Usual Condition
SUBTASK 27-51-00-480-004
(1) Remove the DO-NOT-OPERATE tags from the flap control lever, the ALTERNATE FLAPS
switches and the hydraulic control switches if they are installed.
SUBTASK 27-51-00-020-006
(2) Remove the rig pin from the manual override lever on the LE cruise depressurization valve
(Figure 205).
(a) Make sure the manual override lever moves from the OFF position to the ON position.
(b) Install lockwire on the manual override lever.
SUBTASK 27-51-00-410-010
(3) Below the main equipment center, do this task.
Close this access panel:
Number Name/Location
117A Electronic Equipment Access Door
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 220
Jun 10/2005
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Flap/Slat Electronics Unit
Figure 204 (Sheet 1 of 2)/27-51-00-990-810
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 221
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Flap/Slat Electronics Unit
Figure 204 (Sheet 2 of 2)/27-51-00-990-810
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 222
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Leading Edge Flap and Slat Deactivation
Figure 205 (Sheet 1 of 3)/27-51-00-990-811
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 223
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Leading Edge Flap and Slat Deactivation
Figure 205 (Sheet 2 of 3)/27-51-00-990-811
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 224
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Leading Edge Flap and Slat Deactivation
Figure 205 (Sheet 3 of 3)/27-51-00-990-811
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-51-00
Page 225
Oct 10/2003
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TRAILING EDGE FLAP SYSTEM - ADJUSTMENT/TEST
1. General
A. This procedure has these tasks:
(1) An operational test of the trailing edge flap system
(2) An adjustment of the trailing edge flap control system
(3) An adjustment of the trailing edge flap drive system
(4) A functional test of the trailing edge flap system
(5) A BITE test of the FSEU display and existing faults
(6) A BITE test of the trailing edge flap asymmetry and skew systems
(7) A BITE test of the trailing edge flap load relief system
(8) A test of flap priority valve
(9) A test of flap control lever force
(10) An functional test of the alternate control system for the trailing edge flaps
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飛機(jī)維護(hù)手冊(cè)4(39)