Elevator Hinge Wear Limits 500
27-31-12 Figure 601 (Sheet 2) Oct 20/85
Page 602
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500 Elevator Hinge Wear Limits
Oct 20/85 Figure 601 (Sheet 3) 27-31-12
Page 603
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INDEX NO. PART NAME DIM DESIGN LIMITS WEAR LIMITS REPLACE WORN PART REPAIR WORN PART REPAIR INSTR.
DIAMETER MAX WEAR DIM. MAX DIAM CLEAR- ANCE
MIN MAX
1 BEARING ID 0.3120 0.3125 0.3146 0.0054 X
BOLT OD 0.3110 0.3120 0.3070 X *[1]
2 BUSHING ID 0.3120 0.3130 0.3170 0.0072 X
BOLT OD 0.3110 0.3120 0.3170 X *[1]
3 BEARING ID 0.3120 0.3125 0.3146 0.0054 X
BOLT OD 0.3110 0.3120 0.3070 X *[1]
4 BUSHING ID 0.3120 0.3130 0.3170 0.0072 X
BOLT OD 0.3110 0.3120 0.3070 X *[1]
5 BEARING ID 0.3745 0.3750 0.3772 0.0054 X
BOLT OD 0.3735 0.3745 0.3695 X *[1]
6 BUSHING ID 0.3745 0.3755 0.3815 0.0072 X
BOLT OD 0.3735 0.3745 0.3695 X *[1]
7 BEARING ID 0.3745 0.3750 0.3772 0.0054 X
BOLT OD 0.3735 0.3745 0.3695 X *[1]
8 BUSHING ID 0.3745 0.3755 0.3815 0.0072 X
BOLT OD 0.3735 0.3745 0.3695 X *[1]
*[1] REF OVERHAUL MANUAL FOR REPAIR
NOTE: ELEVATOR TRAILING EDGE PLAY LIMITS (REF 27-09-600) TAKE PRECEDANCE OVER ABOVE WEAR LIMITS.
Elevator Hinge Wear Limits 500
27-31-12 Figure 601 (Sheet 4) Oct 20/85
Page 604
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ELEVATOR HINGES -REMOVAL/INSTALLATION
EFFECTIVITY
Airplanes with Aluminum/Fiberglass Elevators
1. General
A. Each of the elevator hinges, including the thrust hinge, may be replaced individually. It is recommended that two or more adjacent hinges be replaced one at a time. Also, not more than two nonadjacent hinges should be removed at any one time.
2. Removal/Installation Elevator Hinge No. 1
A. Equipment and Materials
(1)
Solvent – Final Cleaning of Metal Prior to Painting (Series 84) (Ref AMM/SOPM 20-30-84)
(2)
Adhesive - Epon 901 (Ref 20-30-11)
(3)
Primer - BMS 10-11, type 1 (Ref 20-30-41)
(4)
Corrosion Preventive Compound - MIL-C-11796, class 3 (Ref 20-30-21)
B. References
(1) CMM 55-20-16, Composite Type Elevator Hinge Removal/Installation.
C. Prepare for Removal
(1)
Position flight controls hydraulic systems A and B switches to OFF.
(2)
Tag control columns to avoid injury to personnel by unexpected movement of the elevator surfaces.
(3)
Remove tab lock mechanism upper and lower access panels located at elevator inboard leading edge.
D. Remove Elevator Hinge No. 1.
(1)
Remove four-hinge mounting bolts (7) securing elevator hinge (1) to elevator front spar (3) (Detail A, Fig. 401).
(2)
Remove cotter pin (10), then remove hinge bearing bolt (11), nut (8), washers (9), and bonding jumper (5) to separate hinge assembly.
(3)
If hinge bolt will not clear rib on elevator front spar, a 0.75-inch hole can be drilled in rib. Hole should be 4.02 inches up from bottom of rib and 1.06 inches from elevator spar. Hole will over lap edge of rib stiffener. Hole should be left unplugged for future use.
(4)
Remove elevator hinge (1) from airplane.
E. Prepare for Installation
(1) Position flight controls hydraulic systems A and B switches to OFF.
May 01/03 27-31-21 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G09286E40100 G09432
Elevator Hinge Installation 500
27-31-21 Figure 401 (Sheet 1) Aug 15/69
Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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