E.  Remove nuts, washers and bolts retaining aileron body quadrant to aileron body quadrant shaft.
F.  Remove bearing housing from aileron body quadrant shaft by removing nuts, washers and bolts.
G.  Remove aileron body quadrant shaft from structure.
4.  Install Aileron Body Quadrant
A.  Reassemble bearing housing assembly if disassembled. (Detail A, Fig. 401).
(1)  
Insert inner sphere in bearing housing and secure with pin.

(2)  
Insert bearing, seal housing, ring seal, and packing into bearing housing (OHM 27-17-02).

B.  Install aileron body quadrant.
(1)  
If used bolts, bushings, bearings or other components with wear limits are being installed, check for allowable wear (AMM 27-11-91/601).

(2)  
Insert aileron body quadrant shaft into bearing housing.

(3)  
Pressure seal shaft and bearing housing by applying a fillet seal between bearing housing and pressure deck (Ref Chapter 51, Seals and Sealing).

(4)  
Locate and slide aileron body quadrant shaft through pressure deck, engaging aileron body quadrant with shaft.

(5)  
Insert four mounting bolts through pressure deck and bearing housing.

(6)  
Secure bolts with washer and locknut. Tighten locknut to 20-25 pound-inches.

(7)  
Check that sealant on seal disk at aileron body quadrant shaft top is not damaged. If damage has occurred apply cement to shaft shoulder and push seal disk down firmly on shaft shoulder.

(8)  
Place aileron body quadrant in position and install bolts, washers, and nuts to secure quadrant to aileron body quadrant shaft. Tighten nuts to 30-35 pound-inches.

500 
May 01/01  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-91 Page 403 

C.  Install aileron centering spring and trim mechanism (Ref 27-11-81 R/I).
D.  Reconnect cables AA and AB to aileron control quadrant and remove clamps. Secure with cable retaining plates.
E.  Prepare cables AA and AB for installation.
(1)  
Position aileron control wheels in neutral by clamping straightedge across the upper ends of each control wheel. One end of first officer's control wheel may be out of contact by

0.20 inch maximum.

(2)  
Position aileron trim control knob indicator in zero trim position.

(3)  
Ensure that trim roller is seated in cam detent.

(4)  
Remove rigging pin A/S-4.

F.  Adjust cable tension within values specified in table 1 on Fig. 402.
G.  Remove straightedge from control wheels. Move captain's aileron control wheel through several complete cycles.
H.  Check that rigging pins A/S-1, A/S-1A and A/S-13 can be inserted and removed without binding.
NOTE:  Rigging pin A/S-1 must be fully put into transfer mechanism and held to keep it from falling out.
I.  Check that cable tension is within specified value range on table 1.
J.  Install turnbuckle locking clips.
K.  Insert rigging pin A/S-4 in aileron bus drums. If rigging pin A/S-4 cannot be inserted without binding, adjust Aileron Power Control Unit (Ref 27-11-71 A/T).
L.  Remove rigging pins A/S-1, A/S-1A, A/S-4 and A/S-13.
M.  Install protractor and protractor mount on first officer's aileron control wheel.
N.  Remove medallion from captain's aileron control wheel.
O.  Install torque wrench adapter tool (Fig. 404).
506 
27-11-91 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 01/96 

G03826 G03885 G03888
500  Aileron System Cable Tension Requirements 
Jun 20/85  Figure 402  27-11-91 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aileron Control Wheel and Trim Knob Neutral Positions  506 
27-11-91Page 406   Figure 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/69 

500  Control Wheel Torque Wrench Adapter 
May 15/68  Figure 404  27-11-91 
Page 407 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

P.  Using control wheel torque and force test adapter, measure force required to manually rotate captain's aileron control wheel clockwise and counterclockwise from neutral. If torque wrench adapter tool is not available, apply force tangentally to captain's control wheel at a 6.5-inch radius.
(1)  
Measure force required to rotate control wheel clockwise until ailerons begin to move. Force required shall not exceed 192 pound-inches torque or 29.5 pounds.
　
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