G38974
500 Aileron Balance Tab Adjust Weights Location Apr 01/97 Figure 401 27-11-21 Page 402A/402B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

500  Aileron Balance Tab Installation 
Aug 01/96  Figure 402 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-21 Page 403 

F94297
Aileron Balance Tab Installation  500 
27-11-21 Page 404  Figure 492 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/89 

K.  Install forward portion of tab fairing.
NOTE:  It may be necessary to adjust forward portion of tab fairing by loosening the three attachment screws and shifting fairing position to provide clearance with aileron fairing at all tab positions.
L.  Operate aileron control wheel through full travel and check that tab moves in opposite direction to aileron without binding.
M.  With index mark on aileron aligned with index mark on wing within 0.03 inch, check mismatch between aileron trailing edge and aileron tab trailing edge. Using straightedge or aileron tab alignment protractor, measure mismatch from trailing edge of tab to theoretical extension of aileron bottom surface at three locations as follows:
(1)  
Take measurement 1/2 inch in from inboard end of tab. Tab trailing edge must align with an extension of aileron bottom surface within +0.00 to +0.14 inch.

(2)  
Take measurement 3-3/4 +1/4 inch in from outboard end of tab. Tab trailing edge must align with an extension of aileron bottom surface within +0.00 to +0.14 inch.

(3)  
Take measurement at midpoint along tab. Tab trailing edge must align with an extension of aileron bottom surface within +0.05 to +0.09 inch.

(4)  
Sum up dimensions taken and recorded in step M. Sum must be between +0.12 and +0.30 inch.

N.  Check aileron tab deflection (Ref 27-11-0 A/T).
O.  Perform a flight test to determine and correct asymmetrical flight control forces (Ref 27-11-0 A/T).
Feb 20/89 27-11-21 Page 405
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

AILERON BALANCE TAB - 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 Balance Tab Wear Limits

G06115 G06123
500  Aileron Balance Tab Wear Limits 
May 15/68  Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-21 Page 601 

Aileron Balance Tab Wear Limits  500 
27-11-21 Page 602  Figure 601 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Apr 01/97 

500  Aileron Balance Tab Wear Limits 
Apr 01/97  Figure 601 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-21 Page 603 

BALANCE PANEL AND SEALS - REMOVAL/INSTALLATION
1.  General
A.  The removal/installation of balance panel does not effect the static balance of the aileron. However, the aileron tab static balance is effected as the tab balance adjust weights are attached to the balance panel. Therefore, whenever a balance panel is replaced, the same quantity of adjust weights must be installed on the replacement panel. The data plate on each balance tab states the number of adjust weights required.
B.  Seals may be replaced with balance panel assembly installed.
2.  Equipment and Materials
A.  Corrosion Preventative Compound - MIL-C-11796
3.  Remove Balance Panel and Seals
A.  Remove access panel on lower wing surface at balance panel.
B.  Remove aft hinge pin retaining bolt and remove hinge pins (Fig 40l).
C.  Remove forward hinge pin retaining bolt and remove hinge pins.
D.  Remove bolts and seals at inboard and outboard ends of balance panel.
E.  Remove balance panel assembly from wing structure.
F.  Separate forward hinge seal by removing bolts, and seal retainers.
4.  Install Balance Panel and Seals
A.  If used bolts, bushings, bearings or other components with wear limits are being installed, check for allowable wear (Ref 27-11-31, Inspection/Check).
B.  Lubricate forward hinges and hinge pins with corrosion preventive compound.
　
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