(2)  
Check that left aileron moves down and right aileron moves up per dimensions specified in 27-11-0, Aileron and Aileron Trim Control System - Adjustment/Test.

(3)  
Operate aileron trim knob counterclockwise to 10 unit position.

(4)  
Check that left aileron moves up and right aileron moves down per dimensions specified in 27-11-0.

(5)  
Place aileron trim control knob in zero trim position, and ensure left and right ailerons are in neutral position.

J.  Turn off systems A and B hydraulic power.
K.  If no longer required, remove electrical power from airplane.
506 
May 15/69  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-141 Page 403 

F19593
 Aileron Deflection Diagram  500 
27-11-141  Figure 402  Aug 01/95 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AILERON TRIM GEARBOX - INSPECTION/CHECK
1.  General
A.  This data consist of illustrations and wear limit 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 Trim Gearbox Wear Limits

G04018
500  Aileron Trim Drum Wear Limits 
May 15/68  Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-141 Page 601 

INDEX NO.  PART NAME  DIM  DESIGN LIMITS  WEAR LIMTS  REPLACE WORN PART  REPAIR WORN PART  REPAIR INSTR. 
DIAMETER  MAX WEAR DIM.  MAX DIAM CLEAR-ANCE
MIN  MAX 
1  SHAFT  ID  X  X  X  1 0.12  X 
COUPLER  OD  X  X  X  X 
2  SHAFT  ID  X  X  X  1 0.12  X 
WORM GEAR SHAFT  OD  X  X  X  X 
3  WORM GEAR SHAFT  ID  X  X  X  0.016 2  X 
OUTPUT ARM  OD  X  X  X  X 

 SPLINE BACKLASH
GEAR BACKLASH: ± 1/2 DEGREE MEASURED AT 3.75 INCH RADIUS ON OUTPUT ARM
Aileron Trim Gearbox Wear Limits 500 27-11-141 Figure 601 (Sheet 2) May 15/68 Page 602
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G10686

AILERON TAB CONTROL RODS - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Protractor-Aileron Tab Alignment-F80222-1 which consists of a -2 protractor assembly (Ref 27-09-700, MP).
2.  Remove Aileron Tab Control Rods
A.  Remove two aileron access panels at hinge locations 2 and 3 on lower wing surface adjacent to leading edge of aileron (Ref 27-11-11, Removal/Installation).
B.  Remove aft balance panel seal retaining bolts and retaining strip.
C.  Remove hinge pin retainer bolt and extract hinge pins from aft balance panel hinge.
D.  Remove aileron hinge access panel at hinge location 2.
E.  Lift aileron trailing edge up and remove two nuts, bolts and washers connecting tab control rods to forward fittings (Fig. 401).
F.  Remove three screws attaching forward portion of tab fairing to tab and remove fairing (Ref 27-11-21, Removal/Installation).
G.  Remove two nuts, bolts, and washers connecting tab control rods to tab mast.
H.  Remove aileron tab hinge bolts and withdraw tab to clear aileron.
I.  Carefully withdraw tab control rods, remove from aileron and record lengths.
3.  Install Aileron Tab Control Rods
A.  If used bolts, bushings, bearings or other components with wear limits are being installed, check for allowable wear (Ref 27-11-151, Inspection/Check).
B.  Lift aileron trailing edge up and place the two tab control rods in mounting position aligning rod ends with attach fittings. Rod lengths must be the same as those recorded. Position tab in place and install tab hinge bolts. Connect tab controls rods to tab mast by installing two bolts, washers, and nuts. Tighten nuts to 50-70 pound-inches (Fig. 401).
NOTE:  Bolts for tab rods must be inserted with fingers only to ensure there is no binding between rod and bolt or deflection of rods. Readjust length of rod if binding or deflection occurs.
　
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