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2)  Check that captain's control wheel has rotated 138 degrees minimum (incremental travel from restrained position).
3)  Observe, during rotation of control wheel, that there is no binding or other evidence of roughness in the transfer mechanism.
4)  Repeat steps 1), 2), and 3) for movement of captain's control wheel in clockwise direction with first officer's control wheel held at 80 degrees in counterclockwise direction from neutral.
5)  With first officer's control wheel held at 80 degrees in clockwise direction from neutral, rotate captain's control wheel 130 degrees in counterclockwise direction (incremental travel from restrained position).
6)  Force required to rotate captain's control wheel shall not exceed 800 pound-inches torque or 123 pounds.
7)  Repeat steps 5) and 6) for movement of captain's control wheel in clockwise direction with first officer's control wheel held at 80 degrees in counterclockwise direction from neutral.
8)  Release pressure from hydraulic systems A and B (AMM 27-11-0/201).
(13) Test autopilot authority.
(a)  
Ensure that entire roll channel of autopilot system is operational (Ref Chapter 22).

(b)  
Remove all hydraulic power (Ref 27-11-0, Maintenance Practices).

(c)  
Connect voltmeter to test points TP 3 and TP 4 on the front panel of the autopilot roll control channel (Fig. 509) to measure Linear Variable Displacement Transducer (LVDT) output.

(d)  
Set autopilot system select switch on glare shield to B.

(e)  
Ensure right aileron is in rigged position with Point B on aileron index plate aligning vertically with Point A on wing index plate within 士0.03 inch (Fig. 506).

501 
27-11-0 Page 530  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/98 

G03478
500  Autopilot Control Component Location 
Aug 15/80  Figure 509  27-11-0 
Page 531 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(f)  
Position right aileron to obtain best null. Record LVDT output voltage. Check that voltage is less than 0.175 volts when index plates (Fig. 506) are aligned vertically within士0.12 inch.

(g)  
Position right aileron by hand in up position to 1.16 士0.12 inches (airplanes with 4.12 inches full travel) or 1.01 士0.10 inches (airplanes with 4.01 inches full travel) between Points A and B.

(h)  
Record LVDT output voltage.

(i)  
Check that algebraic sum of voltages obtained in steps (f) and (h) equals +5.0士0.50 volts.

(j)  
Position right aileron by hand in down position to 1.16士0.12 inches (airplanes with

4.12 inches full travel) or 1.01 士0.10 inches (airplanes with 4.01 inches full travel) between Points A and B.

(k)  
Record LVDT output voltage.

(l)  
Check that algebraic sum of voltages obtained in steps (f) and (k) equals -5.0士0.50 volts.

(m)  
On airplanes with dual autopilot modes (no INOP decal on autopilot system select switch on glare shield), position switch to A and repeat steps (e) thru (l) with left aileron.

E.  Return Airplane to Normal
(1)  
Turn off systems A and B hydraulic power (Ref 27-11-0, MP).

(2)  
If no longer required, remove electrical power from airplane.

(3)  
Remove control surface protractor and protractor mount from aileron control wheel.

(4)  
Remove torque wrench adapter from aileron control wheel.

(5)  
Replace aileron control wheel medallion.

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2A.  Operational Test -Control Wheel and Control Column
A.  General
(1)  This test is to check for binding of the control wheel and control column at extreme positions. The cause of the resistance was interference between the control column fitting and the fork in the aileron bus drum. The interference is caused by the buildup of tolerances in the assemblies.
B.  Procedure
(1)  Do a check for full range of surface travel and for free movement of control column and control wheel. Do the steps that follow:
(a)  
Move the control column in the longitudinal direction between the stops. At the same time, move the control wheel left and right between the stops.

(b)  
Make sure the elevators and ailerons move smoothly through their full range of travel.

(c)  
Hold the control wheel left (counterclockwise from the neutral position)against the stop, and do the steps that follow: 1) Make sure the trailing edges of the left aileron moves fully up and the aileron tab
　
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