500 
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506 
Oct 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-61-31 Page 503 

(a)  Using spring scale at the tip of the speed brake control lever, check that maximum lever loads are as follows: 1) DOWN to FLIGHT DETENT - 20 pound maximum 2) FLIGHT DETENT to UP - 28 pounds maximum 3) UP to FLIGHT DETENT - 28 pounds maximum 4) FLIGHT DETENT to DOWN - 20 pounds maximum
D.  Return Airplane to Normal
(1)  
Remove systems A and B hydraulic power (Ref 27-61-0).

(2)  
Remove protractor and protractor mount from captain's control wheel.

(3)  
Remove electrical power if no longer required.

(4)  
Remove protractors and protractor stands from spoiler panels.

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SPOILER RATIO CHANGER - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and a wear limit chart. There is no procedure given for gaining access to the component for removal or replacement after inspection for wear. Refer to Component Removal/Installation for this information.
2.  Spoiler Ratio Changer Input Rod Wear Limits

G18267
501  Spoiler Ratio Changer Input Rod Wear Limits 
Feb 01/75  Figure 601  27-61-31 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

SPOILER CONTROL QUADRANT - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Cable Tensiometer - 0- to 150-pound range for 1/8-inch cable
B.  Rigging Pins Kit - F70207-3, -52, -61, or -84:
Ref No.  F70207-( )  Diameter (inches)  Length (inches)  Function 
A/S-1 A/S-1A A/S-3 A/S-4 A/S-14  -13 -11 -8 -11 -11  0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311 0.309-0.311  2.35 +0.06 6.7 +0.25 3.7 +0.25 6.7 +0.25 6.7 +0.25  Transfer mechanism Transfer mechanism Spoiler control quadrant lower lever Aileron bus drum Spoiler mixer 

C.  Cement - BMS 5-14 (Ref 20-30-11)
D.  Control Wheel Straightedge - SE 27-0001
2.  Prepare Spoiler Control Quadrant for Removal
A.  Remove systems A and B hydraulic power (Ref 27-61-0 MP).
B.  Set aileron in neutral. Aileron is in neutral when rigging pin A/S-4 can be freely inserted and removed.
C.  Open lower nose compartment access door.
D.  Insert rigging pins A/S-1 and A/S-1A in first officer's transfer mechanism (Fig. 401).
NOTE:  Rigging pin A/S-1 must be fully put into transfer mechanism and held to keep it from falling out.
E.  Remove seats and floor covering as required to expose right floor panel between seat tracks at second window aft of wing escape hatch. Remove floor panel to gain access to spoiler control quadrant (Ref Chapter 25, Equipment and Furnishings).
3.  Remove Spoiler Control Quadrant
A.  Disconnect right-hand aileron control cables.
(1)  
Secure cables to maintain a slight cable tension when turnbuckles are disengaged.

(2)  
Disengage turnbuckles located in lower nose compartment.

Jun 20/90 27-61-41 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

G34793G34385
Spoiler Control System Cable Location and Cable Tension  500 
27-61-41  Figure 401 (Sheet 1)  Aug 15/68 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

500  Spoiler Control System Cable Location and Cable Tension 
Aug 15/69  Figure 401 (Sheet 2)  27-61-41 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

(3)  
Identify cables for subsequent installation.

(4)  
Remove cables from spoiler control quadrant.

B.  Remove two bolts attaching spoiler control quadrant to quadrant shaft (Fig. 402).
C.  Disconnect bolt attaching ratio changer input rod to upper control crank.
D.  Disconnect bolt attaching aileron spring cartridge to aileron input crank.
E.  Remove two bolts attaching quadrant shaft support bracket to wheel wel1 forward wall.
F.  Break pressure seal and remove four bolts attaching quadrant shaft to wheel well ceiling.
G.  Disengage quadrant shaft from quadrant, lower shaft through wheel wel1 ceiling, and remove shaft from airplane.
　
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