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D. Location Zones
Zone Area
133 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Left
134 Main Landing Gear Wheel Well, Body Station 663.75 to Body Station
727.00 - Right
E. Procedure
SUBTASK 27-11-00-480-021
WARNING: MAKE SURE THE DOWNLOCK PINS ARE INSTALLED ON ALL THE LANDING GEARS.
WITHOUT THE DOWNLOCK PINS, THE LANDING GEARS COULD RETRACT AND
CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(1) If the downlock pins are not installed on all the landing gears, do this task: Landing Gear
Downlock Pins Installation, TASK 32-00-01-480-801.
SUBTASK 27-11-00-020-003
(2) Make sure you can freely install and remove rig pin A/S-15 in the aileron trim actuator.
SUBTASK 27-11-00-860-102
(3) To remove power from hydraulic systems A and B, do this task: Hydraulic System A or B
Power Removal, TASK 29-11-00-860-805.
SUBTASK 27-11-00-280-002
(4) Do a functional test of the system A (lower) pogo:
(a) Install the tool, SPL-1749 on system A (lower) aileron PCU piston.
NOTE: Make sure that tool, SPL-1749 is installed correctly to prevent damage to the
lockwire.
(b) Turn the Captain’s control wheel clockwise from the neutral position until system A (lower)
pogos extend.
NOTE: Approximately 100 pounds (444.9 newtons) force is necessary to turn the control
wheel.
(c) Make sure the pogos extend approximately 0.20 inches (5.1 millimeters) minimum.
NOTE: Approximately 7 units of wheel required.
(d) Return the Captain’s control wheel to the neutral position.
(e) Make sure that all four pogos retract to the original position.
(f) Remove the tool, SPL-1749 from the system A (lower) aileron PCU piston and install on
system B (upper) aileron PCU piston.
NOTE: Make sure that tool, SPL-1749 is installed correctly to prevent damage to the
lockwire.
SUBTASK 27-11-00-280-003
(5) Do a functional test of the system B (upper) pogo:
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-11-00
Page 572
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
(a) Turn the Captain’s control wheel clockwise from the neutral position until system B (upper)
pogos extend.
NOTE: Approximately 100 pounds (444.9 newtons) force is necessary to turn the control
wheel.
(b) Make sure that the pogos extend approximately 0.20 inches (5.1 millimeters) minimum.
NOTE: Approximately 7 units of wheel required.
(c) Return the Captain’s control wheel to the neutral position.
(d) Make sure that the pogos retract to the original position.
(e) Remove the tool, SPL-1749 from the system B (upper) aileron PCU piston.
(f) Do this task, do this task: Landing Gear Downlock Pins Removal, TASK 32-00-01-080-801.
SUBTASK 27-11-00-020-004
(6) Put the airplane back to its usual condition.
------------------------- END OF TASK ---------------------------
TASK 27-11-00-750-801
21. Flight Test to Find and Correct Asymmetrical Flight Control Forces
A. General
(1) An aileron system flight test is necessary after these maintenance procedures:
(a) Installation of a replacement aileron.
(b) Installation of an aileron which was on-jig rebalanced (see Structure Repair Manual,
Chapter 51, for maintenance actions which require aileron on-jig rebalancing).
(c) Removal or replacement of the aileron front spar hinge bearing nearest to the tab control
rods.
(d) Installation of a replacement aileron front spar hinge bearing support fitting.
NOTE: Installation of new aileron hinge bearings (except the one nearest the tab control
rods) does not make a flight test necessary if the original bearing support fittings
are installed in their original locations.
(e) Installation of a replacement aileron rear spar tab hinge bearing support fitting.
NOTE: Installation of new tab hinge bearings does not make a flight test necessary if the
original bearing support fittings are installed in their original locations.
(f) Installation of a replacement aileron balance tab or a repaired aileron balance tab with a
non-flush surface patch.
NOTE: If you did the Aileron Balance Tab Adjustment, TASK 27-11-00-820-803 and both
control rods were adjusted, then flight test is necessary. If only one rod was
adjusted, and you can verify that the remaining rod had not been replaced or
adjusted since the last flight test, then flight test is not necessary. If only one
rod was adjusted, and you can not verify that the remaining rod had not been
replaced or adjusted since the last flight test, then flight test is necessary
(g) Installation of a replacement front spar hinge of the aileron balance tab.
　
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