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NOTE: The inboard bolt is installed with the head inboard and the outboard bolt is
installed with the head outboard.
NOTE: If you loosened or removed the nuts [47], they need to be replaced and not reinstalled.
Using new nuts will ensure that they have the required run-on torque
of 3.5 in-lb (0.4 N
m).
(c) Install the pin assemblies [40] with the heads at the inside of the tab mechanism [32],
washers [51], and nuts [52] to connect the tab mechanism [32] to the elevator [21].
NOTE: You must use a special tool to hold the heads of the pin assemblies [40] while
tightening the nuts [52].
(d) Rotate the pin retainer [48] arms down and install the screws [48] to attach the pin retainers
[49] to the tab mechanism [32].
(e) Install the bushings [38], bolts [39], washers [34], and nuts [35] to connect the tab
mechanism [32] to the horizontal stabilizer [33].
NOTE: The bolts are installed with the heads at the outside of the tab mechanism.
1) Tighten the nuts [35] to 50 - 60 pound-inches (5.7 - 6.8 newton-meters).
CAUTION: DO NOT TIGHTEN THE NUTS [35] AGAIN AFTER YOU TIGHTEN THE NUT [37]. YOU
CAN CAUSE DAMAGE TO EQUIPMENT.
(f) Install the washers [36] and nuts [37].
1) Tighten the nuts [37] to 12 - 15 pound-inches (1.4 - 1.7 newton-meters).
GUN ALL
SUBTASK 27-31-34-700-002
(4) Adjust the tab rods to the approximate position that you measured before removing the
mechanism. To adjust the tab rods, do this task: Elevator Tab Pushrods - Adjustment,
TASK 27-31-00-820-805.
SUBTASK 27-31-34-730-005
(5) Do this task: Elevator Travel Limit - Test, TASK 27-31-00-700-804.
SUBTASK 27-31-34-730-006
(6) Do this task: Elevator Tab Linkage - Test, TASK 27-31-00-700-806.
SUBTASK 27-31-34-730-007
(7) Do this task: Control Column Power Force - Test, TASK 27-31-00-700-809.
E. Put the Airplane Back to Its Usual Condition
SUBTASK 27-31-34-410-004
(1) Install this access panel:
Number Name/Location
318BR Tailcone Access Door
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-34
Page 405
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-31-34-410-005
(2) For the left elevator, install this access panel:
Number Name/Location
333BB Horizontal Stabilizer, Access Panel, Trailing Edge
SUBTASK 27-31-34-410-006
(3) For the right elevator, install this access panel:
Number Name/Location
343BB Horizontal Stabilizer, Access Panel - T.E. Area
SUBTASK 27-31-34-730-008
(4) Do this task: Elevator Power-Off Flight - Test, TASK 27-31-00-710-803.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-34
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D633A101-GUN
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Elevator Aft Quadrant Rig Pin Installation
Figure 401/27-31-34-990-801
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-31-34
Page 407
Jun 10/2006
D633A101-GUN
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Elevator Tab Control Mechanism Installation
Figure 402/27-31-34-990-803
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 156, 201-204, 206 PRE SB 737-55A1080 27-31-34
Page 408
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Elevator Tab Control Mechanism Installation
Figure 403/27-31-34-990-802
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-099, 101-122, 155, 157, 205, 207-999; GUN 156, 201-
204, 206 POST SB 737-55A1080
27-31-34
Page 409
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Elevator Tab Control Mechanism Installation
Figure 404/27-31-34-990-809
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 156, 201-204, 206 PRE SB 737-55A1080 27-31-34
Page 410
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Elevator Tab Control Mechanism Installation
Figure 405/27-31-34-990-807
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-099, 101-122, 155, 157, 205, 207-999; GUN 156, 201-
204, 206 POST SB 737-55A1080
27-31-34
Page 411
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Elevator Tab Control Mechanism Installation
　
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