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edge surface.
GUN 001-099, 155-157, 201-999
(q) Make sure the aileron is in the rig position (Figure 506).
NOTE: The aileron rig position is when the outboard edge of the aileron lower surface is
0.245 ±0.03 inch (6.2 ±0.8 millimeters) below the adjacent fixed lower trailing
edge surface.
1) If the aileron is not in the rig position, adjust the cables ABSA and ABSB. To adjust the
cables, do this task: Aileron Cables Adjustment, TASK 27-11-00-820-801.
GUN ALL
(r) Make sure the aileron balance tab aligns with the aileron:
1) Measure the distance between the rig position of the aileron balance tab [1] to the
aileron lower surface (dimension A) at these three positions (Figure 504):
NOTE: You must measure from the lower aft most point of the aileron balance tab [1].
GUN 101-122
a) At the outboard end of the aileron balance tab, make sure the dimension A is 0.12
±0.07 inch (3.1 ±1.8 millimeters) or 1.64 ±0.50 degrees.
b) At the middle point along the aileron balance tab, make sure the dimension A is
0.13 ±0.07 inch (3.3 ±1.8 millimeters) or 1.21 ±0.50 degrees.
c) At the inboard end of the aileron balance tab, make sure the dimension A is 0.14
±0.07 inch (3.6 ±1.8 millimeters) or 0.68 ±0.50 degrees.
GUN 001-099, 155-157, 201-999
d) At the outboard end of the aileron balance tab, make sure the dimension A is 0.06
±0.07 inch (1.5 ±1.8 millimeters) or 0.82 ±0.25 degrees.
e) At the middle point along the aileron balance tab, make sure the dimension A is
0.065 ±0.070 inch (1.7 ±1.8 millimeters) or 0.60 ±0.25 degrees.
f) At the inboard end of the aileron balance tab, make sure the dimension A is 0.07
±0.07 inch (1.8 ±1.8 millimeters) or 0.34 ±0.25 degrees.
GUN ALL
2) If the aileron balance tab does not align with the aileron, do this task: Aileron Balance
Tab Adjustment, TASK 27-11-00-820-803.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-11-00
Page 539
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
G. Put the Airplane Back to Its Usual Condition
SUBTASK 27-11-00-410-002
(1) Close this access panel:
Number Name/Location
112A Forward Access Door
SUBTASK 27-11-00-860-028
(2) Do this task: Retract the Trailing Edge Flaps, TASK 27-51-00-860-804.
SUBTASK 27-11-00-860-029
(3) Remove power from hydraulic systems A and B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
------------------------- END OF TASK ---------------------------
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-11-00
Page 540
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Aileron System Adjustment
Figure 506 (Sheet 1 of 3)/27-11-00-990-807
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN ALL 27-11-00
Page 541
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Aileron System Adjustment
Figure 506 (Sheet 2 of 3)/27-11-00-990-807
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 101-122 27-11-00
Page 542
Oct 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Aileron System Adjustment
Figure 506 (Sheet 3 of 3)/27-11-00-990-807
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-099, 155-157, 201-999 27-11-00
Page 543
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TASK 27-11-00-700-801
7. Aileron Surface Friction and Motion Test
(Figure 506, Figure 507)
A. References
Reference Title
27-11-00-860-801 Remove Pressure from the Aileron Hydraulic Systems A and B
(P/B 201)
27-11-00-860-802 Put the Aileron Hydraulic Systems A and B Back to the Condition
Before Pressure Removal (P/B 201)
B. 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
211 Flight Compartment - Left
212 Flight Compartment - Right
C. Prepare for the Test
SUBTASK 27-11-00-860-030
(1) Do this task: Remove Pressure from the Aileron Hydraulic Systems A and B,
TASK 27-11-00-860-801.
SUBTASK 27-11-00-020-001
(2) Disconnect the aileron control rod [81] from the aileron [32]. (Figure 507)
　
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