(2)
Continue rotating control wheel to 20 degrees from neutral. Force required shal1 not exceed 220 pound-inches torque or 33.8 pounds.
(3)
Continue rotating to 40 degrees. Force required shal1 not exceed 256 pound-inches torque or 39.4 pounds.
(4)
Continue rotating to 75 degrees. Force required shal1 not exceed 310 pound-inches torque or 47.7 pounds.
(5)
Repeat steps (l) through (4) in a counterclockwise direction.
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. 405.
(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. 405.
R. Return airplane to normal.
(1)
Remove control surface protractor and protractor mount from aileron control wheel.
(2)
Remove control wheel torque and force test adapter from captain's aileron control wheel.
(3)
Replace medallion on captain's aileron control wheel.
(4)
Replace seats, carpets and floor panels removed (Ref Chapter 25, Equipment and Furnishings).
501
27-11-91 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/81
T52462
523 Aileron Deflection Diagram
Aug 01/95 Figure 405 27-11-91
Page 409
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON BODY QUADRANT - INSPECTION/CHECK
1. General
A. This data consists of illustration and wear limits charts. No procedure is given for gaining access to permit inspection. For this information, refer to component removal/installation.
2. Aileron Body Quadrant Wear Limits
G03906 G44600
500 Aileron Body Quadrant Wear Limits
Aug 15/73 Figure 601 (Sheet 1) 27-11-91
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Aileron Body Quadrant Wear Limits 500
27-11-91 Figure 601 (Sheet 2) Aug 15/73
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON POWER CONTROL UNIT LINKAGE - REMOVAL/INSTALLATION
1. General
A. System A and system B linkage may be removed separately. The following procedure can be used for either linkage.
B. Prior to removing either aileron power control unit linkage, both power control units must be removed.
2. Equipment and Material
A. Grease - MIL-G-23827 (Ref 20-30-21)
B. Corrosion Preventive Compound - MIL-C-11796, Class 3 (Ref 20-30-21)
C. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
A/S-3 A/S-4 -8 -11 0.309 - 0.311 0.309 - 0.311 3.7 + 0.25 6.7 + 0.25 Spoiler Control Quadrant Lower Lever Aileron Bus Drum
3. Remove Aileron Power Control Unit Linkage
A. Remove aileron power control units (Ref 27-11-71 R/I).
B. Disconnect cables ABSA and ABSB at turnbuckles (Fig. 401).
C. Remove nuts, washers, and screws securing retaining plates to aileron bus drum.
D. Disengage cables ABSA and ABSB from aileron bus drum.
E. Secure disconnected cables.
F. On system B, disconnect spring cartridge at inboard end by removing cotter pin, nut, washer, and bolt.
G. Remove alignment pins between support assemblies.
H. Disengage diagonal support from structure by removing nuts, washers, and bolts.
I. Disconnect safety link from outboard end of reaction link by removing nut, washer, spacer, and bolt.
J. Disconnect support from structure by removing nuts, washers, and bolts.
K. Remove linkage from airplane.
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-101 Page 401
G03916G03949
Aileron Power Control Linkage Installation 500
27-11-101 Figure 401 (Sheet 1) Nov 01/75
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Aileron Power Control Linkage Installation
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