528  Aileron and Tab Control Linkage 
Nov 15/77  Figure 404  27-11-11 
Page 407 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aileron Bus Drum Rigging Pin Location  500 
27-11-11  Figure 405  Aug 15/67 
Page 408 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(2)  
Adjust turnbuckle to align index plates and maintain cable tension. See Fig. 407 for temperature-tension chart.

(3)  
Install turnbuckle locking clips.

Y.  Check that aileron outboard trailing edge is below wing trailing edge 0.08 to 0.48 inch.
Z. Remove rigging pin A/S-4. AA. Use aileron control wheel and manually operate the aileron through several cycles, to full travel, while checking for binding and chafing. AB. Check that gap between aileron nose and wing trailing edge is 0.30 to 0.50 inch when aileron is
in faired position (Fig. 402).
AC. Check that gaps at both ends of aileron are per Fig. 401.
AD. Install four hinge access panels on aileron (Fig. 406) and four aileron access panels on trailing edge of wing surface adjacent to aileron.
AE. Set aileron trim knob in neutral. Operate control wheel to move replaced aileron to full up and down positions. Check that aileron travel is within specified limits as measured between index plate on aileron and index plate on wing structure (Fig. 403).
NOTE:  Aileron is in neutral (zero) position when index mark on aileron lines up with index mark on wing structure within 0.03 inch. See Fig. 403 for index plate locations.
AF.  Provide Systems A and B hydraulic power (Ref 27-11-0, MP).
AG.  Rotate aileron trim control knob clockwise to 10 unit position.
AH. Check that left aileron moves down and right aileron moves up per dimensions specified in  27-11-0, A/T.
501 
Jun 20/85  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-11 Page 409 

G03537
Hinge Access Panels Location  500 
27-11-11  Figure 406  May 15/67 
Page 410 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AI.  Rotate aileron trim control knob counterclockwise to 10-unit position.
AJ.  Check that left aileron moves up and right aileron moves down per dimensions specified in 27-11-0 A/T.
AK.  Set aileron trim control knob in neutral position.
AL.  Operate aileron control wheel through full travel in both directions from neutral. Check ailerons for smooth operation throughout entire range of travel.
AM. Remove systems A and B hydraulic power (AMM 27-11-0 MP).
AN. Do a check on the aileron/balance tab mismatch and on the movement of the balance tab (AMM 27-11-0 A/T).
AO.  Remove electrical power from airplane if no longer required.
AP. Perform a flight test to determine and correct asymmetrical flight control forces (AMM 27-11-0 A/T).
500 
Feb 01/96  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-11 Page 411 

G03568
Aileron System Cable and Tension Location  543 
27-11-11  Figure 407 (Sheet 1)  Feb 15/73 
Page 412 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

543  Aileron System Cable and Tension Location 
Jun 20/85  Figure 407 (Sheet 2)  27-11-11 
Page 413 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AILERON - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to Component Removal/Installation for this information.
2.  Aileron Wear Limits

G03581 G08798
500  Aileron Wear Limits 
May 15/68  Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-11 Page 601 

 Aileron Wear Limits  500 
27-11-11 Page 602  Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Apr 01/97 

AILERON AND AILERON TRIM CONTROL SYSTEM – APPROVED REPAIRS
1. General
A.  This repair procedure covers replacement of index plate on wing rib facing the inboard end of the aileron. For replacement of index plate on ailerons, refer to OHM 57-50-21.
　
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