G03990 W02067 T52445 T52446
500 Aileron Power Control Unit Linkage Wear Limits
Feb 15/81 Figure 601 (Sheet 1) 27-11-101
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aileron Power Control Unit Linkage Wear Limits 501
27-11-101 Figure 601 (Sheet 2) May 01/03
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Aileron Power Control Unit Linkage Wear Limits
Feb 15/81 Figure 601 (Sheet 3) 27-11-101
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aileron Power Control Unit Linkage Wear Limits 500
27-11-101 Figure 601 (Sheet 4) Feb 15/81
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON POWER CONTROL UNIT LINKAGE - APPROVED REPAIRS
1. General
A. Shear bolts 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. Lockbolt Installation Gun - Model 245
Huck International Inc. (or equivalent)
22121 17th Ave. S.E. - Suite 101
Bothell, Wa.
B. Nose Assembly - 99-2557
(used with Gun Model 245)
C. Shear Lockbolts - BACB30GP6-5
D. Aluminum Foil Marker - BACM10L1EKH
3. Replace Sheared Bolts
A. Remove and disassembly aileron power control unit linkage (Ref 27-11-101, Removal/ Installation).
B. Remove sheared portions of bolts from holes (Fig. 801).
WARNING: DO NOT ENLARGE BOLT HOLES.
C. Install new bolts.
D. Check aluminum foil marker and replace if damaged or missing.
E. Assemble and install Aileron Power Control Unit Linkage (Ref 27-11-101, Removal/Installation).
500
Aug 01/96 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-101 Page 801
G42351
Aileron Bus Drum Control Shaft 500
27-11-101Page 802 Figure 801 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/81
AILERON WING QUADRANTS - REMOVAL/INSTALLATION
1. Equipment and Materials
A. 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 Aileron Bus Drum
B. 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
2. Prepare to Remove Aileron Wing Quadrants
A. Depressurize hydraulic systems A and B (Ref 27-11-0 MP).
B. Insert rigging pin A/S-4 through aileron bus drums (Fig. 402).
C. Remove access panels.
(1)
For access to left wing quadrant, remove wing lower access panel 7218 and upper access panel 8108.
(2)
For access to right wing quadrant, remove wing lower access panel 7418 and wing upper access panel 8808.
3. Remove Aileron Wing Quadrants
A. Remove cotter pin, nut, washer, and bolt retaining aileron control rod to aileron wing quadrant.
B. Disconnect cables ABSA and ABSB at turnbuckles.
C. Secure disconnected cables.
D. Remove retaining plates from wing quadrant by removing nuts, washers, and screws.
E. Remove cable guard from forward edge of wing quadrant.
F. Disengage cables ABSA, and ABSB from wing quadrant.
G. Remove cotter pin, nut, washer and bolt retaining wing quadrant to structure and remove quadrant.
H. Separate bushing from wing quadrant retaining structure if required.
542
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-111 Page 401
G05672
Aileron Wing Quadrants Installation 500
27-11-111 Figure 401 Oct 20/84
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