I. Disassemble wing quadrant as follows:
(1)
Remove bushings from aileron control rod attachment point, if required.

(2)
Remove bearing and spacer from quadrant attachment point, if required.

4. Install Aileron Wing Quadrant
A. Check aileron wing quadrant for wear. Refer to Aileron Wing Quadrant - Inspection/Check.
B. Install bearings and spacer in wing quadrant attachment point, if previously removed (Fig. 401).
C. Install bushing in aileron control rod attachment point, if previously removed.

G05678
500  Aileron Rigging Pin Locations 
Oct 20/84  Figure 402  27-11-111 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

D.  Place bushing in wing quadrant retaining structure, if previously removed.
E.  Place wing quadrant in position and secure with bolt, washer, and nut. Tighten nut 160 to 200 pound-inches and install cotter pin.
F.  In left wing, place cable ABSA in bottom groove of quadrant and cable ABSB in top groove. In right wing, place cable ABSB in bottom groove of quadrant and cable ABSA in top groove. Secure cable retaining plates with screws, washers, and nuts.
G.  Install cable guard on structure at forward edge of wing quadrant.
H.  Adjust cable guard gap to 0.03 +0.05/-0.03 inch as shown in Detail B.
I.  Connect aileron control rod to wing quadrant by installing bolt , washer, and nut. Tighten nut 60 to 85 pound-inches, then install cotter pin.
J.  Connect cables ABSA and ABSB to turnbuckles, but maintain zero cable tension.
K.  Ensure rigging pin A/S-4 is installed (Fig. 402).
L.  
Tighten turnbuckles for each cable (ABSA and ABSB) to permit positioning of ailerons so that index point B on inboard end of each aileron aligns vertically within士0.03 inch of index point A on adjacent wing structure (Fig. 403).

M.  
Continue to tighten cables in equal increments until correct tension is obtained as specified in Fig. 404.

N.  
Install turnbuckle locking clips.

O.  
Install upper and lower access panels removed for wing quadrant replacement.

P.  
Install control wheel protractor mount and control wheel protractor on captain’s aileron control wheel.

Q.  
Measure relationship of aileron control wheel movement as compared with aileron surface deflection.

(1)  
Rotate captain’s aileron control wheel 87 degrees minimum counterclockwise from neutral.

(2)  
Check that left aileron moves up and right aileron moves down within limits specified in Fig. 403.

(3)  
Rotate captain’s aileron control wheel 87 degrees minimum clockwise from neutral.

(4)  
Check that left aileron moves down and right aileron moves up within limits specified in Fig. 403.

R.  
Remove control wheel protractor and mount from captain’s aileron control wheel.

27-11-111 Oct 20/84 Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

T52450 G05681
523  Aileron Deflection Diagram 
Aug 01/95  Figure 403  27-11-111 
Page 405 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aileron System Cable Tension Requirements  500 
27-11-111  Figure 404  May 01/01 
Page 406 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AILERON WING QUADRANT- INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limit charts. No procedure is given in this section for gaining access to permit inspection for this information, refer to Removal/Installation.
2.  Aileron Wing Quadrant Wear Limits

G05694
500  Aileron Wing Quadrant Wear Limits 
Aug 15/73  Figure 601 (Sheet 1)  27-11-111 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

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  BUSHING  ID  0.3125  0.3140  0.3140  0.0034  X 
BOLT  OD  0.3110  0.3120  0.3106  X 
2  CONTROL ROD BEARING  ID  - - - *[2]  X 
BOLT  OD  - - - X 
　
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