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334 Left Horizontal Stabilizer - Elevator
343 Right Horizontal Stabilizer - Rear Spar to Trailing Edge
344 Right Horizontal Stabilizer - Elevator
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D. Access Panels
Number Name/Location
318BR Tailcone Access Door
333BB Horizontal Stabilizer, Access Panel, Trailing Edge
343BB Horizontal Stabilizer, Access Panel - T.E. Area
E. Prepare for the Removal
SUBTASK 27-31-34-860-007
(1) Remove pressure from the elevator hydraulic systems A and B. To remove it, do this task:
Remove Pressure from the Elevator Hydraulic Systems A and B, TASK 27-31-00-800-802.
SUBTASK 27-31-34-010-011
(2) To get access to the aft control quadrant, do this task:
Remove this access panel:
Number Name/Location
318BR Tailcone Access Door
SUBTASK 27-31-34-010-012
(3) For the left elevator, remove this access panel:
Number Name/Location
333BB Horizontal Stabilizer, Access Panel, Trailing Edge
SUBTASK 27-31-34-010-013
(4) For the right elevator, remove this access panel:
Number Name/Location
343BB Horizontal Stabilizer, Access Panel - T.E. Area
SUBTASK 27-31-34-480-004
(5) Install the rig pin E-5 from rig pin kit, SPL-1585 in the aft control quadrant (Figure 401).
SUBTASK 27-31-34-220-003
(6) If you will change the adjustment of the elevator tab pushrods, then you need to measure the
elevator tab position. To measure the tab position, do this task: Elevator Tab Pushrods -
Adjustment, TASK 27-31-00-820-805.
(a) Keep a record of the elevator tab position.
(b) If you will change the adjustment of both elevator tab pushrods, then you need to do an
elevator power-off flight test. Do this task:Elevator Power-Off Flight - Test,
TASK 27-31-00-710-803
F. Tab Lock Actuator Removal
SUBTASK 27-31-34-020-014
(1) Disconnect the hydraulic line [31] from the elevator tab lock actuator [78] and install caps and
plugs on the hydraulic line and port.
GUN 001-099, 101-122, 155, 157, 205, 207-999; GUN 156, 201-204, 206 POST SB 737-55A1080
NOTE: See Figure 403.
GUN ALL
NOTE: The spring should be at the neutral position when the hydraulic line is disconnected.
737-600/700/800/900
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EFFECTIVITY
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SUBTASK 27-31-34-020-015
(2) Remove the elevator tab lock actuator [78]:
(a) Remove the nut [80], washer [79], bushings [77], and bolt [76] from the elevator tab lock
actuator [78].
(b) Remove the nut [75], washer [74], bushing [73], washer [74], and bolt [71] from the elevator
tab lock actuator [78].
(c) Remove the elevator tab lock actuator [78] from the airplane.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
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EFFECTIVITY
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Elevator Tab Lock Actuator Installation
Figure 409/27-31-34-990-804
737-600/700/800/900
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EFFECTIVITY
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TASK 27-31-34-400-804
7. Elevator Tab Lock Actuator - Installation
(Figure 401, Figure 409)
GUN 156, 201-204, 206 PRE SB 737-55A1080; AIRPLANES WITH FOUR ELEVATOR TAB HINGES
NOTE: Also see Figure 402, Figure 404 and Figure 407.
GUN 001-099, 101-122, 155, 157, 205, 207-999; GUN 156, 201-204, 206 POST SB 737-55A1080; AIRPLANES
WITH THE SIX HINGE ELEVATOR TAB WITH RECTANGULAR HEAD BOLTS
NOTE: Also see Figure 403, Figure 405 and Figure 408.
GUN ALL
A. References
Reference Title
27-31-00-700-815 Elevator Tab Control System - Operational Test (P/B 501)
27-31-00-800-802 Remove Pressure from the Elevator Hydraulic Systems A and B
(P/B 201)
B. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
SPL-1585 Kit - Rigging Pins, All Systems
(Part #: F70207-109, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
　
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