(9)
Check that cable tension is within required value range in temperature-tension chart.
(10)
Install turnbuckle-locking clips.
(11)
Remove rigging pins A/S-1, A/S-1A and A/S-3.
K. Test spoiler control quadrant (Ref Spoiler Control Quadrant - A/T).
5. Return Airplane to Normal
A. Close lower nose compartment access door.
B. Replace floor panel, floor covering and seats as required.
500
Aug 01/95 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-41 Page 407
SPOILER CONTROL QUADRANT - ADJUSTMENT/TEST
1. Spoiler Control Quadrant Test
A. Equipment and Materials
(1)
Control Surface Protractor -4MIT65B80307-1 (preferred), F52485-500 (optional) (3 required)
(2)
Control Surface Protractor Stand Assembly - F71292-17 (optional) (2 required)
(3)
Aileron Control Wheel Protractor Mount - F72790
(4)
Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
A/S-4 -11 0.309-0.311 6.7 +0.25 Spoiler mixer
B. Prepare Spoiler Control Quadrant for Test
(1)
Install protractor mount and protractor on captain's control wheel.
(2)
Install protractor stand and protractor on spoilers No. 2 and 6.
NOTE: Protractors may be hand-held on spoilers instead of using stands.
(3)
Provide systems A and B hydraulic power (Ref 27-61-0 MP).
(4)
Place speed brake control lever in DOWN position.
(5)
Set aileron in neutral. Aileron is in neutral when rigging pin A/S-4 can be freely inserted and removed. Remove rigging pin.
C. Test Spoiler Control Quadrant
(1)
Rotate captain's aileron control wheel 87 degrees counterclockwise. Check that spoiler No. 2 is 38 +2 degrees up from zero position.
(2)
Rotate captain's aileron control wheel 87 degrees clockwise. Check that spoiler No. 6 is 38 +2 degrees up from zero position.
D. Return Airplane to Normal
(1)
Remove systems A and B hydraulic power (Ref 27-61-0 MP).
(2)
Remove protractor and protractor mount from captain's control wheel.
(3)
Remove protractors, and protractor stands from spoilers No. 2 and 6.
(4)
Remove electrical power if no longer required.
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-41 Page 501
SPOILER CONTROL QUADRANT - 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 Spoiler Control Quadrant - Removal/Installation for this information.
2. Spoiler Control Quadrant Wear Limits
A. Aileron Spring Cartridge Wear Limits
G37867 G36769
500 Spoiler Control Quadrant Wear Limits
Aug 15/71 Figure 601 (Sheet 1) 27-61-41
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Spoiler Control Quadrant Wear Limits 500
27-61-41 Figure 501 (Sheet 2) Aug 15/71
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
SPOILER CONTROL QUADRANT - APPROVED REPAIRS
1. General
A. Shear rivets provide a means by which normal operation of essential flight systems can be maintained in the event of failure or jamming of related or interconnect secondary systems (Ref 27-09-500).
2. Equipment and Materials
A. Shear Rivets -MS20470D
B. Aluminum Foil Marker - BAC27DCT-13
3. Replace Sheared Rivets
A. Remove spoiler control quadrant shaft (Ref 27-61-41, Removal/Installation).
B. Remove sheared portions of rivet from holes (Fig. 801).
WARNING: DO NOT ENLARGE RIVET HOLES.
C. Install new rivets.
D. Check aluminum foil marker and replace if damaged or missing.
E. Install spoiler control quadrant shaft (Ref 27-61-41, Removal/Installation).
500
Aug 01/75 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-61-41 Page 801
G35311
Spoiler Control Quadrant Shaft 500
27-61-41 Figure 801 Aug 01/75
Page 802
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