曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
(a) If the rudder trailing edge is greater than 0.50 in. (12.7 mm) from the neutral position, then
do this coarse adjustment to the control rod [34]:
WARNING: MAKE SURE YOU SET THESE SWITCHES TO THE OFF POSITION
BEFORE YOU DISCONNECT THE CONTROL ROD FROM THE STANDBY
RUDDER PCU. THE CONTROL ROD CAN MOVE QUICKLY AND CAUSE
INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
1) Set the FLT CONTROL A and B switches to OFF.
2) Loosen the two checknuts [31] on the control rod [34].
3) Remove the nut [50], washer [49], washer [48], and bolt [47] to disconnect the control
rod [34] from the upper crank [46] of the torque tube [33].
4) Turn the control rod end for half a turn relative to the sleeve [32]; and turn the sleeve
[32] and the control rod end together for half a turn.
NOTE: The sum of half turn of each is equal to 0.67 in. (17.0 mm) at the rudder trailing
edge.
5) Keep number of threads that you can see in the two parts are approximately same.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 006-099, 101-122; GUN 001-005, 155-157, 201-999
POST SB 737-27-1253
27-21-00
Config 2
Page 542
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
GUN 006-099, 101-122; GUN 001-005, 155-157, 201-999 POST SB 737-27-1253; AIRPLANES WITHOUT
251A3495-1 OR -7 CONTROL ROD (Continued)
6) Install the bolt assembly [47] with the bolt head end up, washer [48] (under bolt),
washer [49] (under nut), and nut [50] to connect the control rod [34] to the upper crank
[46].
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF THE
RUDDER. THE RUDDER CAN MOVE QUICKLY WHEN YOU PUSH THE
‘YES‘ BUTTON ON THE SMYD NO. 2. THIS CAN CAUSE INJURY TO
PERSONS AND DAMAGE TO EQUIPMENT.
7) Set the FLT CONTROL A and B switches to the STANDBY RUD position.
(b) If the rudder trailing edge is less than 0.50 in. (12.7 mm) from the neutral position, then do
this fine adjustment to the control rod [34]:
1) Loosen the checknuts [31] on the control rod [34].
2) Turn the adjustable sleeve [32] until the two sides of the rudder trailing edge are in the
width of the rudder index tab.
3) Tighten the two checknuts [31].
(c) Do a check for minimum thread engagement of the rod. Make sure that you can see the rod
from the inspection hole in the tube.
(d) Set the YAW DAMPER switch to the OFF position.
GUN 006-099, 101-122; GUN 001-005, 155-157, 201-999 POST SB 737-27-1253
SUBTASK 27-21-00-820-025-002
(4) Make sure that you can install and remove the rig pin R-5 freely.
SUBTASK 27-21-00-860-097-002
(5) Remove the safety tag and close this circuit breaker:
F/O Electrical System Panel, P6-2
Row Col Number Name
D 19 C00787 FLIGHT CONTROL TRIM CONT RUD
SUBTASK 27-21-00-820-026-002
(6) Set the FLT CONTROL A and B switches to ON.
(a) Make sure that the STBY RUD ON light is not illuminated after 5 seconds.
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-21-00-480-022-002
(1) Remove the rig pin R-5.
SUBTASK 27-21-00-860-098-002
(2) Do this task: Put the Rudder Hydraulic systems A, B, and Standby Back to the Condition
Before the Pressurization, TASK 27-21-00-840-801.
SUBTASK 27-21-00-410-014-002
(3) Close these access panels:
Number Name/Location
324CL Vertical Fin, Access
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 006-099, 101-122; GUN 001-005, 155-157, 201-999
POST SB 737-27-1253
27-21-00
Config 2
Page 543
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(Continued)
Number Name/Location
324DL Trailing Edge Access
------------------------- END OF TASK ---------------------------
TASK 27-21-00-700-813-002
7. Rudder Pedal Adjustment and Limit Travel Test
A. General
(1) Use this test to make sure the rudder pedals can move through their full travel and the pedal
adjustment crank operates correctly.
B. References
Reference Title
27-21-00-800-801 Rudder Hydraulic System A, B, or Standby Pressurization (P/B 201)
27-21-00-840-801 Put the Rudder Hydraulic systems A, B, and Standby Back to the
Condition Before the Pressurization (P/B 201)
C. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
D. Procedure
SUBTASK 27-21-00-860-099-002
(1) Do this task: Rudder Hydraulic System A, B, or Standby Pressurization,
TASK 27-21-00-800-801.
SUBTASK 27-21-00-730-015-002
(2) Do the captain’s rudder pedal adjustment and the limit travel:
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册2(63)
