(2)
Check that left aileron moves down and right aileron moves up per dimensions specified in 27-11-0, Aileron and Aileron Trim Control System - Adjustment/Test.
(3)
Operate aileron trim knob counterclockwise to 10 unit position.
(4)
Check that left aileron moves up and right aileron moves down per dimensions specified in 27-11-0.
(5)
Place aileron trim control knob in zero trim position, and ensure left and right ailerons are in neutral position.
J. Turn off systems A and B hydraulic power.
K. If no longer required, remove electrical power from airplane.
506
May 15/69 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-141 Page 403
F19593
Aileron Deflection Diagram 500
27-11-141 Figure 402 Aug 01/95
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON TRIM GEARBOX - INSPECTION/CHECK
1. General
A. This data consist of illustrations and wear limit 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 Component Removal/Installation for this information.
2. Aileron Trim Gearbox Wear Limits
G04018
500 Aileron Trim Drum Wear Limits
May 15/68 Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-11-141 Page 601
INDEX NO. PART NAME DIM DESIGN LIMITS WEAR LIMTS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR-ANCE
MIN MAX
1 SHAFT ID X X X 1 0.12 X
COUPLER OD X X X X
2 SHAFT ID X X X 1 0.12 X
WORM GEAR SHAFT OD X X X X
3 WORM GEAR SHAFT ID X X X 0.016 2 X
OUTPUT ARM OD X X X X
SPLINE BACKLASH
GEAR BACKLASH: ± 1/2 DEGREE MEASURED AT 3.75 INCH RADIUS ON OUTPUT ARM
Aileron Trim Gearbox Wear Limits 500 27-11-141 Figure 601 (Sheet 2) May 15/68 Page 602
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G10686
AILERON TAB CONTROL RODS - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Protractor-Aileron Tab Alignment-F80222-1 which consists of a -2 protractor assembly (Ref 27-09-700, MP).
2. Remove Aileron Tab Control Rods
A. Remove two aileron access panels at hinge locations 2 and 3 on lower wing surface adjacent to leading edge of aileron (Ref 27-11-11, Removal/Installation).
B. Remove aft balance panel seal retaining bolts and retaining strip.
C. Remove hinge pin retainer bolt and extract hinge pins from aft balance panel hinge.
D. Remove aileron hinge access panel at hinge location 2.
E. Lift aileron trailing edge up and remove two nuts, bolts and washers connecting tab control rods to forward fittings (Fig. 401).
F. Remove three screws attaching forward portion of tab fairing to tab and remove fairing (Ref 27-11-21, Removal/Installation).
G. Remove two nuts, bolts, and washers connecting tab control rods to tab mast.
H. Remove aileron tab hinge bolts and withdraw tab to clear aileron.
I. Carefully withdraw tab control rods, remove from aileron and record lengths.
3. Install Aileron Tab Control Rods
A. If used bolts, bushings, bearings or other components with wear limits are being installed, check for allowable wear (Ref 27-11-151, Inspection/Check).
B. Lift aileron trailing edge up and place the two tab control rods in mounting position aligning rod ends with attach fittings. Rod lengths must be the same as those recorded. Position tab in place and install tab hinge bolts. Connect tab controls rods to tab mast by installing two bolts, washers, and nuts. Tighten nuts to 50-70 pound-inches (Fig. 401).
NOTE: Bolts for tab rods must be inserted with fingers only to ensure there is no binding between rod and bolt or deflection of rods. Readjust length of rod if binding or deflection occurs.
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