(f)
Align the elevator trailing edge with the index mark on the rigging beam.
(g)
Hold the elevator at this position.
(b)
Remove rigging beam.
D. Install Index Plates
(1)
Position index plate against right side of tail cone aligning index mark with a theoretical extension of elevator trailing edge (Fig. 403).
(2)
Drill two 0.190 + 0.004/-0.000-inch diameter holes through tail cone from index plate. Countersink 100 degrees for bolt head.
(3)
Attach index plate to tail cone using two screws, washers and nuts. Install lockwire between the two nuts.
(4)
If using protractor, remove protractor from underside of stabilizer and install screws removed in step C.(7).
CAUTION: PROVIDE ADEQUATE SUPPORT FOR PROTRACTOR WHILE REMOVING ATTACHING SCREWS. ENSURE THAT ALL SCREWS ARE REMOVED BEFORE RELAXING SUPPORT.
(5)
Repeat steps 2. C.(7) thru 2.D.(4) to install index plate on left side of tail cone.
(6)
Adjust elevator control system (elevator control pushrods, elevator power control unit input rod, elevator tab pushrods and determine if neutral shift sensor must be adjusted.) (Ref 27-31-0, Elevator and Tab Control System - A/T).
E. Restore Airplane to Normal Configuration
(1)
Close aft compartment access door and replace tail cone access panel.
(2)
Remove tags from control columns.
(3)
Restore airplane to normal hydraulic configuration (Ref 27-31-0 - MP).
500
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-81 Page 403
G42362 G09558
Protractor Installation 500
27-31-81Page 404 Figure 402 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
500 Elevator Index Plate Installation
Jul 15/70 Figure 403 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-81 Page 405
ELEVATOR NEUTRAL SHIFT MECHANISM - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Rigging Pins Kit - F70207-3, -52, -61, or -84:
REF NO. F70207-( ) DIAMETER (INCHES) LENGTH (INCHES) FUNCTION
E-5 -11 0.309-0.311 6.7 +0.25 AFT CONTROL QUADRANT
B. Trammel Bar - F80055-1
C. Stabilizer Trim Lock - F71336-501
D. Primer - BMS 10-11, type 1 (Ref 20-30-41)
2. Prepare for Removal
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
B. Remove or open the following access panels (Ref Chapter 12, Access Doors and Panels):
(1)
Tail cone access panel 3802
(2)
Aft compartment access door 3701
C. Open stabilizer trim actuator, stabilizer trim control, and autopilot stabilizer trim servo circuit breakers in panel P6.
D. Disconnect stabilizer trim actuator and autopilot trim servo electrical connectors at the stabilizer trim actuator (Fig. 403).
E. Install stabilizer trim lock to stabilize trim wheel at the control stand (Fig. 404).
(1)
Rotate trim wheel to place handle at top of wheel.
(2)
Adjust height of trim lock to position trim wheel handle snugly in bottom of yoke.
(3)
Insert pin through yoke and install safety pin.
500
Feb 20/88 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-91 Page 401
F. Install rigging pin E-5 in aft control quadrant (Fig. 405).
3. Remove Elevator Neutral Shift Mechanism
A. Remove dualbolt and locknuts to disconnect neutral shift crank from mach trim actuator terminal (Fig. 402).
B. Disconnect aft ends of input rods from neutral shift crank.
C. Disconnect forward ends of input rods from horizontal stabilizer center section. Withdraw both input rods and remove from airplane.
D. Remove three bolts, nuts, and washers attaching each end of neutral shift crank to feel and centering unit support bracket. Remove neutral shift crank and spacers from airplane.
4. Prepare for Installation
A. Remove elevator systems A and B hydraulic power (Ref. 27-31-0, MP).
B. Check that rigging pin E-5 is installed in aft control quadrant (Fig. 405).
C. If neutral shift crank support bearings are to be replaced, proceed as follows:
(1)
Withdraw bearing complete with inner and outer bearing retainers from short end of neutral shift crank (Fig. 401).
(2) 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(101)
