737 AMM 飞机维护手册飞行操纵 FLIGHT CONTROLS 2(43)_航空信息_民用航空_通用航空

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F. Apply a coat of grease to actuator to structure mounting bolt and bushing.
G. Install bushing and actuator to structure mounting bolt to secure upper end of trim actuator to structure.
H. Install nut on actuator to structure outer mounting bolt, and tighten nut 45 to 60 pound-inches.
I. Install nut on actuator to structure inner mounting bolt, and tighten nut 12 to 15 pound-inches. Install cotter pin.
CAUTION: AFTER TIGHTENING NUT ON INNER BOLT, DO NOT RESET TORQUE FOR NUT ON OUTER BOLT. NUT ON INNER BOLT MAY BECOME LOOSE.
J. Reconnect cables RTA and RTB at turnbuckles. Maintain zero tension on cables.
K. Disconnect control rod between torque tube and feel and centering unit output crank at torque tube.
L. Remove rigging pin R5 from feel and centering unit.
M. Tighten turnbuckles equally to tension cables RTA and RTB to values shown in Fig. 401. Check that rudder trim control wheel is in neutral position, and rigging pin R5 fits without binding into feel and centering unit.
NOTE: If rigging pin R5 cannot be inserted or binds, readjust cables RTA and RTB until requirements are met.
If turnbuckle travel is inadequate for complete adjustment, additional adjustment is possible using turnbuckles located in ceiling in forward cargo compartment at fuselage station 451.
N. Connect control rod between torque tube and feel and centering unit output crank. Tighten nut on outer bolt 45 to 60 pound-inches, then tighten nut on inner bolt 12 to 15 pound-inches.
CAUTION: AFTER TIGHTENING NUT ON INNER BOLT, DO NOT RESET TORQUE ON
OUTER BOLT. NUT ON INNER BOLT MAY BECOME LOOSE.

O. Install turnbuckle locking clips and coat exposed turnbuckle threads with corrosion preventive compound.
P. Remove rigging pin R-5.
Q. Provide rudder systems A and B hydraulic power (Ref 27-21-0).
501
Oct 20/83 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-111 Page 405

R. Use rudder trim knob torque adapter to rotate trim knob from neutral to full right, and from full right to neutral. Then from neutral to ful1 left and return. Maximum force required shall be 28 pound-inches.
S. Rotate trim knob in both directions until indicator is at 10. Check that rudder travel is 10.22 (+ 0.50) inches in each direction.
6. Restore Airplane to Normal
A. Restore airplane to normal hydraulic configuration. Refer to 27-21-0.
B. Close all access doors and install panels.
500
27-21-111 Page 406 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73

RUDDER TRIM ACTUATOR - INSPECTION/CHECK
1. General
A. This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component for inspection after wear. Refer to component removal/installation for this information.
2. Rudder Trim Actuator Wear Limits

G08543
501 Rudder Trim Actuator Wear Limits
Aug 15/69 Figure 601 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-21-111 Page 601

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 0.3140 0.0020 X
BOLT OD 0.3115 0.3120 0.3085 X
2 ACTUATOR HOUSING ID 0.4700 0.4706 0.4721 0.0021 X
BOLT OD 0.4695 0.4700 0.4665 X
3 ADJUST-MENT PLUG ID 0.4355 0.4365 0.4385 0.0030 X
BUSHING OD 0.4345 0.4355 0.4325 X
4 BUSHING ID 0.3120 0.3130 0.3150 0.0030 X
BOLT OD 0.3110 0.3120 0.3090 X

Rudder Trim Actuator Wear Limits 501
27-21-111 Page 602 Figure 601 (Sheet 2) B
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