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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(b) Install the bolt [21] with the bolt head inboard, washer [22], washer [23], and nut [24] to
connect the elevator control pushrod to the elevator.
(c) Close this access panel:
Number Name/Location
318BR Tailcone Access Door
or
Close this access panel:
Number Name/Location
317AL Tail Cone Access Door
SUBTASK 27-41-11-420-004
(8) Connect the hydraulic line [25] (that is installed just aft of the stabilizer rear spar) of the elevator
tab mechanism actuator.
SUBTASK 27-41-11-420-005
(9) Connect the following electrical connectors:
(a) Flight recorder position sensor
(b) Exterior logo light (if installed).
SUBTASK 27-41-11-410-001
(10) For the left horizontal stabilizer, do this step:
Close these access panels:
Number Name/Location
331A Horizontal Stabilizer, Gap Cover
331AZ Horizontal Stabilizer, Access Panel, Inboard L.E.
Closure Rib
332AB Horizontal Stabilizer, Gap Cover, Horizontal
Stabilizer to Body
333AB Horizontal Stabilizer, Gap Cover, Horizontal
Stabilizer to Body
333AZ Horizontal Stabilizer, Access Panel, Inboard T.E.
Closure Rib
SUBTASK 27-41-11-410-002
(11) For the right horizontal stabilizer, do this step:
Close these access panels:
Number Name/Location
341A Horizontal Stabilizer, Gap Cover
341AZ Horizontal Stabilizer, Access Panel - Inbd L.E.
Closure Rib
342AB Horizontal Stabilizer, Gap Cover - H. Stab. to Body
343AB Horizontal Stabilizer, Gap Cover - H. Stab. to Body
343AZ Horizontal Stabilizer, Access Panel - Inbd T.E.
Closure Rib
SUBTASK 27-41-11-080-002
(12) Remove the lock, SPL-1672 from the stabilizer trim wheel at the control stand.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-41-11
Page 421
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
SUBTASK 27-41-11-820-001
(13) Adjust the stabilizer-to-body seals (Figure 406):
(a) Set the horizontal stabilizer to a zero degree trim (four units of trim).
(b) Make sure that the clearance between the stabilizer-to-body blade seals and the airplane
body surface along the upper and lower horizontal edge is 0.01 in. (0.3 mm) -- 0.03 in.
(0.8 mm).
1) Adjust the stabilizer-to-body blade seals in or out, if it is necessary.
(c) Make sure the stabilizer-to-body bulb seals touch and push against the airplane body
surface.
(d) Move the stabilizer leading edge to the full down position (the ball nut is against the
downstop).
(e) Make sure that the clearance is 0.01 in. (0.3 mm) -- 0.03 in. (0.8 mm) between the airplane
body surface and the stabilizer-to-body blade seals at these locations:
1) The blade seals installed at the leading edge of the stabilizer from the upper to the
lower surface.
a) Adjust the stabilizer-to-body blade seals in or out, if it is applicable.
2) The blade seal adjacent to the gap cover of the upper spar.
a) Adjust the blade seal in or out, if it is applicable.
SUBTASK 27-41-11-860-005
(14) Set the stabilizer trim cutout switches to the NORMAL position.
SUBTASK 27-41-11-820-007
(15) If the same stabilizer, elevator, and elevator tab that was removed was re-installed (without
elevator or elevator tab rework or adjustment - and the tailcone was not removed), then the
following check will determine if a flight test is necessary:
NOTE: If the tailcone was removed, or its position adjusted during the stabilizer or elevator
removal procedure, the left and right elevator index plate positions will be in a different
position when the tailcone is re-installed. The elevator cannot be properly measured
with the elevator index plate in a different location, therefore, you must do a power-off
flight test.
(a) Do this task: Elevator Hydraulic System A and B - Pressurization,
TASK 27-31-00-800-801.
(b) Do this task: Null Procedure - Mach Trim Actuator, TASK 27-31-00-700-801.
(c) Use the bar, SPL-1677 to set the horizontal stabilizer to 39.89 +/- 0.01 inches (1013.2 +/-
0.3 mm) (this is the neutral stabilizer position or zero degrees (4 units of trim)).
(d) Move the control column forward and aft several times and then let it go at the neutral
position.
(e) Verify that the right elevator position, ‘‘Z’’, is within +/- 0.06 inch (1.5 millimeters) of the
neutral mark on the right elevator index plate, Figure 403.
1) If necessary, adjust the PCU input rods to achieve the +/- 0.06 inch (1.5 millimeters)
measurement on the right elevator index plate, do this task: Input Rods of the Elevator
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737-600-700-800-900 AIRCRAFT MAINTENANCE MANUAL飞机维护手册3(129)
