(6)  
Repeat steps (1) thru (5) in a counterclockwise direction.

E.  Measure effect of aileron trim wheel operation (Ref 27-11-0 A/T).
F.  Turn off hydraulic system B pumps No. 1 and 2
G.  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. 502.

(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. 502.

H.  Return airplane to normal.
(1)  
Turn off Systems A and B hydraulic power.

(2)  
If no longer required, remove electrical power from airplane.

(3)  
Remove control wheel protractor and protractor mount from aileron control wheel.

(4)  
Remove torque wrench adapter tool from aileron control wheel.

(5)  
Replace medallion on control wheel.

501 
May 01/98  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-81 Page 505 

AILERON CENTERING SPRING AND TRIM MECHANISM - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limits charts. No procedure is given in this section for gaining access to permit inspection. For this information, refer to Component Removal/Installation.
2.  Aileron Centering Spring and Trim Mechanism Wear Limits

G11021 G11054G44598
500  Aileron Centering Spring and Trim Mechanism Wear Limits 
Aug 15/73  Figure 601 (Sheet 1)  27-11-81 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aileron Centering Spring and Trim Mechanism Wear Limits  500 
27-11-81  Figure 601 (Sheet 2)  May 01/76 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Aileron Centering Spring and Trim Mechanism Wear Limits 
Aug 15/73  Figure 601 (Sheet 3)  27-11-81 
Page 603 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AILERON BODY QUADRANT - REMOVAL/INSTALLATION
1.  General
A.  Removal of the aileron body quadrant cannot be accomplished until the aileron centering spring and trim mechanism has been removed.
2.  Equipment and Materials
A. Cement - BMS 5-14 (Ref 20-30-11)
B Rigging Pins Kit - F70207-84, or -98:

REF NO.  F70207-( )  DIAMETER (INCHES)   LENGTH (INCHES)  FUNCTION 
A/S-1 A/S-1A A/S-4 A/S-13  -13 -19 -11 - 8  0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311  2.35 +0.06 8.25 +0.25 6.7 +0.25 3.7 +0.25  Aileron Transfer Mechanism Aileron Transfer Mechanism Aileron Bus Drum Aileron Trim Gearbox 

C.  Control Wheel Straightedge SE27-0001
D.  Control Column Protractor Assembly-4MIT65B80307-1 (Preferred) or F52485-500 (Optional) which is used with the following adapters:
(1)  
Control Wheel Protractor Mount-F72790

(2)  
Forward Thrust Lever Protractor Adapter-F72952-2

E.  Control Wheel Torque and Force Test Adapter-F72867-1
F.  Sealant-BMS 5-95 (Ref 20-30-11)
3.  Prepare to Remove Aileron Body Quadrant
A.  Remove aileron centering spring and trim mechanism (Ref 27-11-81 R/I).
B.  Remove seats, carpets and floor panels above aileron body quadrant (Ref Chapter 25, Equipment/Furnishings).
4.  Remove Aileron Body Quadrant
A.  Place ailerons in neutral, and insert rigging pin A/S-4 in aileron bus drums (Fig. 401).
B.  Disconnect left cables AA and AB at turnbuckles.
C.  Remove retaining plates and secure disconnected cables with clamps.
542 
May 01/99  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-11-91 Page 401 

G42347
Aileron Body Quadrant Installation  500 
27-11-91  Figure 401  May 15/68 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

D.  Separate cables AA and AB from aileron body quadrant, and tag cables to facilitate
reassembly.
　
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