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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
G. Procedure
SUBTASK 27-21-00-710-070-002
(1) Do the rudder forward quadrant adjustment:
(a) Do these steps to set the jackshaft yoke to the middle position:
NOTE: The middle position of the jackshaft yoke is where the number of turns of the shaft
from the full forward and full aft adjustment are the same.
1) Turn the rudder pedal adjustment crank to move the rudder pedals full forward.
2) Turn the rudder pedal adjustment crank to move the rudder pedals full aft. Record the
number of turns.
3) Turn the rudder pedal adjustment crank half the recorded number of turns forward.
(b) Install the rig pin R-3 from the rig pin kit, SPL-1585 in the forward hole in the captain’s
rudder forward quadrant.
(c) Install the rig pin R-4 from the rig pin kit, SPL-1585 in the forward hole in the first officer’s
rudder forward quadrant.
(d) If you can not install rig pins R-3 or R-4, adjust the bus rod [6]:
1) Turn the turnbuckles to release the tension of rudder control cables RA and RB.
2) Remove the pin [5], nut [4], washer [3], spacers [2], bolt [1] to disconnect the bus rod [6]
from rudder forward quadrant. Discard the pin [5].
3) Install the rig pin R-3 from the rig pin kit, SPL-1585 in the forward hole in the captain’s
rudder forward quadrant.
4) Install the rig pin R-4 from the rig pin kit, SPL-1585 in the forward hole in the first
officer’s rudder forward quadrant.
5) Adjust the bus rod [6] until you can install the bolt [1] through the rudder forward
quadrant.
6) Install the spacers [2], washer [3], nut [4], and new pin [5].
7) If it is necessary, adjust the brake pushrods [12] to the nose wheel steering. To adjust
them, do this task: Nose Wheel Steering System Adjustment, TASK 32-51-00-820-802.
(e) Make sure the clearance between the cable guard blocks and the rudder forward
quadrants is 0.030 in. (0.76 mm) -- 0.050 in. (1.27 mm) through full travel.
(f) Remove the rig pins R-3 and R-4.
(g) Remove the nut [50], washer [49], washer [48], and bolt assembly [47] to disconnect the
standby rudder PCU control rod [34] from the rudder control torque tube [33].
(h) Remove the nut [45], washer [44], washer [43], and bolt assembly [42] to disconnect the
main rudder PCU control rod [36] from the rudder control torque tube [33].
(i) Move the captain’s rudder forward quadrant until you can install the rig pin R-3 in the aft rig
pin hole.
(j) Make sure there is no clearance between the captain’s forward quadrant and quadrant
stop. Add or subtract shims as needed to bring the clearance to zero.
(k) Remove the rig pin R-3.
(l) Move the first officer’s rudder forward quadrant until you can install the rig pin R-4 in the aft
rig pin hole.
(m) Make sure there is no clearance between the first officer’s forward quadrant and quadrant
stop. Add or subtract shims as needed to bring the clearance to zero.
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 503
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(n) Remove the rig pin R-4.
(o) Connect the control rod [36] to the center crank [41].
1) Install the bolt assembly [42] with the bolt head end up and washer [43].
2) Tighten the outer bolt of the bolt assembly [42] to 70 in-lb (7.9 N
m) -- 85 in-lb (9.6 N
m).
3) Install the washers [44] and nut [45].
CAUTION: DO NOT TIGHTEN THE OUTER BOLT OF THE BOLT ASSEMBLY [42]
AFTER YOU TIGHTEN THE NUT [45]. THIS CAN CAUSE DAMAGE TO
EQUIPMENT.
4) Tighten the nut [45] to 25 in-lb (2.8 N
m) -- 30 in-lb (3.4 N
m).
(p) 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].
H. Put the Airplane Back to Its Usual Condition
SUBTASK 27-21-00-820-006-002
(1) Do this task: Rudder Pedals Adjustment, TASK 27-21-00-820-807-002.
SUBTASK 27-21-00-820-007-002
(2) Do this task: Control Rod for Main Rudder Power Control Unit Adjustment,
TASK 27-21-00-820-809-002.
SUBTASK 27-21-00-410-010-002
(3) Close these access panels:
Number Name/Location
113AW Forward Nose Wheel Well Panel
113BW Forward Nose Wheel Well Panel
114AW Forward Nose Wheel Well Panel
114BW Forward Nose Wheel Well Panel
SUBTASK 27-21-00-010-019-002
(4) Close these access doors:
Number Name/Location
112A Forward Access Door
317AL Tail Cone Access Door
　
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本文鏈接地址：737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL飛機維護手冊2(49)