(3)
Remove six bolts (12) and washers (13) securing outboard frame attach bracket (16) to elevator front spar (3). Remove bracket from airplane.
(4)
Remove four-hinge mounting bolts (7) securing hinge (1) to elevator front spar (3).
(5)
Remove cotter pin (10), then remove hinge bearing bolt (11), nut (8), and washers (9) to separate hinge assembly.
(6)
Remove elevator hinge (1) from airplane. If structural interference prevents removal of hinge, remove elevator (Ref 27-31-11, Removal/Installation).
D. Prepare for Installation
(1)
Position flight controls hydraulic systems A and B switches to OFF.
(2)
Check hinge bearing and hinge bearing bolt for allowable wear (Ref 27-31-11,
Inspection/Check).
E. Install Elevator Hinge No. 2
(1)
If elevator was removed, install elevator and hinge No. 2 (Ref 27-31-21,
Removal/Installation). Adjust and test elevator per 27-31-0, Adjustment/Test.
(2)
If elevator was s not removed, install hinge No. 2 as follows:
(a)
Position thrust hinge against elevator front spar (3, Detail B, Fig. 401) and loosely install four hinge mounting bolts (7) and washers (6). Hinge should be installed with grease fitting down (below hinge centerline).
(b)
Install hinge bearing bolt (11) as follows: 1) Lightly coat shank and threads of bolt with corrosion preventive compound.
513
Aug 15/77 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-21 Page 407
2) Install bolt with head inboard, a washer (9) under bolthead and a washer (9) under nut (8).
3) Tighten nut 90 to 100 pound-inches. Align nut with cotter pin hole without exceeding 190 pound-inches, then install cotter pin (10).
(c)
Tighten the four hinge mounting bolts (7) 70 to 80 pound-inches.
(d)
Install outboard frame attach bracket (16) to elevator front spar (3). Secure bracket with six bolts (12) and washers (13).
(e)
Secure aft end of frame assembly (18) to frame attach bracket (16) at elevator front spar (3). Install bolt (17) with head inboard and a washer (15) under nut (14).
(f)
Perform test procedure (Ref 27-31-21, A/T).
(g)
Install bolt retainer shield on tab lock mechanism (Ref 27- 31-121, R/I).
F. Restore Airplane to Normal Configuration
(1)
Install tab lock mechanism access panels.
(2)
Remove tags from control columns.
4. Removal/Installation Elevator Hinges No. 3 thru 6
NOTE: The following procedure describes the removal and installation of an individual elevator hinge. This procedure is identical for all hinges No. 3 thru 6, except where stated otherwise.
A. Equipment and Materials
(1) Same as par. 2.A.
B. 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 elevator surfaces.
(3)
Remove elevator hinge access plates (at each location requiring hinge removal).
506
27-31-21 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/84
C. Remove Elevator Hinges No. 3 thru 6
(1)
At elevator hinge location No. 3, 4, or 5, remove hinge seals (24, Details C and D, Fig. 401) from both sides of elevator hinge (1).
(2)
Remove four hinge mounting bolts (7) securing hinge to elevator front spar (3).
(3)
Remove plate bolts (19), nuts (23) and washers (22) attaching elevator hinge to stabilizer trailing edge rib (21), (three bolts at hinges No. 3 and 4, two bolts at hinges No. 5 and 6).
(4)
Remove hinge assembly from airplane.
(5)
Separate hinge assembly by removing cotter pin (10), nut (8), washers (9), and at hinge No. 6 location, a bonding jumper (5).
D. Prepare for Installation
(1)
Position flight controls hydraulic systems A and B switches to OFF.
(2)
Check that inner race of bearing may be manually rotated in either direction with the fingers. Also check that race can be manually misaligned in either direction at any position. Also check bearing and hinge bearing bolt for allowable wear (Ref 27-21-11, I/C).
E. Install Elevator Hinges No. 3 thru 6
(1)
Assemble elevator hinge as follows:
(a)
Lightly coat shank and threads of hinge bearing bolt (11, Details C and D, Fig. 401) with corrosion preventive compound.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(86)
