(2)  
Install drill jig and spacer over coupler.

NOTE: Spacer is part of drill jig assembly.

(3)  
Install coupler on cable drum shaft. Slide coupler up and instal1 splined shaft in trim gearbox.

(4)  
Engage coupler with splined shaft with 0.20-inch spacer between shaft and coupler.

(5)  
With coupler resting on spacer, drill holes through coupler and shaft to a 0.250 +0.004/ -0.000 inch dimension.

(6)  
Remove drill jig by sliding coupler up and removing splined shaft from gearbox.

(7)  
Reinstall splined shaft in gearbox, engage coupler with splined shaft and install bolts.

G.  Remove phenolic faced clamps and reconnect cables ATA and ATB at turnbuckles. Maintain zero tension on cables.
H.  Ensure rigging pin A/S-13 is installed in aileron trim gearbox.
I.  Ensure aileron trim control knob is set in zero trim position. Tape aileron trim control knob (Fig. 402).
J.  Adjust cables ATA and ATB at turnbuckles so that rigging pin A/S-13 fits freely and cable tension is within values specified in Fig. 403.
K.  Remove rigging pin A/S-13 and tape from aileron trim control knob.
27-11-131 May 15/77 Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G03989
500  Aileron System Cable Tension Requirements 
Aug 15/73  Figure 403  27-11-131 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

L.  Rotate aileron trim control knob through several complete cycles to obtain constant rigging tension.
M.  Install rigging pin A/S-13. Check that aileron trim control knob indicator is in zero trim position. Check that cable tension is within values specified in Fig. 403.
N.  Remove rigging pin A/S-13.
O.  Install turnbuckle locking clips.
P.  Provide systems A and B hydraulic power (Ref 27-11-0).
Q.  Install control wheel protractor mount and protractor on first officer's aileron control wheel.
R.  Remove medallion from captain's aileron control wheel and install control wheel torque and force test adapter (Fig. 404).
S.  Measure effect of aileron trim knob operation (Fig. 405).
(1)  
Operate aileron trim knob clockwise to 10-unit position.

(2)  
Measure movement of captain's and first officer's aileron control wheels from neutral position. Check that control wheels rotate clockwise per degrees specified in 27-11-0, Adjustment/Test.

(3)  
Check that left aileron moves down and right aileron moves up per dimensions specified in 27-11-0.

(4)  
Using control wheel torque and force test adapter and torque wrench, measure force required to rotate aileron control wheel 75 degrees counterclockwise. If a torque wrench adapter is not available, force may be applied tangentially to captain's aileron control wheel at 6.5 inch-radius. Force should not exceed 18.5 pounds or 120.25 pound-inches torque

G04000F19589
Control Wheel Torque and Force Test Adapter  506 
27-11-131  Figure 404  Jun 20/85 
Page 406 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Aileron Deflection Diagram 
Aug 01/95  Figure 405  27-11-131 
Page 407 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(5)
Release aileron control wheel from 75 degree counterclockwise position. Check that control wheel returns to the clockwise position of degrees specified in 27-11-0.

(6)  
Operate aileron trim knob counterclockwise to 10 unit position.

(7)  
Measure movement of captain's and first officer's aileron control wheels from neutral position. Control wheels should have rotated counterclockwise per degrees specified in 27-11-0.

(8)  
Check that left aileron moves up and right aileron moves down per dimensions specified in 27-11-0.

(9)  
Measure force required to rotate aileron control wheel 75 degrees clockwise. Force should not exceed 117 pound-inches torque or 18 pounds.

(10)
Release aileron control wheel from 75 degrees clockwise position. Check that control wheel returns to the degree counterclockwise position of degrees specified in 27-11-0.

(11)
Place aileron trim control knob in zero trim position.

6.  Restore Airplane to Normal
A.  Turn off systems A and B hydraulic power.
B.  Remove control wheel protractor mount, and protractor from first officer's control wheel.
　
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