(1)
Secure tab shaft (21) to coupling shaft (18) by installing bolts (20) and collars (19).
(2)
Place mechanical stop rings (17) on coupling shaft (18) and instal1 lockring (16).
(3)
Secure retaining plate (13) to upper bearing housing (10) by installing washers (14) and screws (15).
(4)
Secure coupling shaft (18) to upper bearing housing (10) with washer (9) and nut (10).
(5)
Manually rotate coupling shaft to align mechanical stop rings as shown in detail A.
B. Place upper bearing housing (10), and attached components into position in control stand.
C. Install washers (11), screws (12) and nuts (12A) to secure upper bearing housing (10) to control stand (7).
D. Slide lower bearing housing (23) on tab shaft (21), and secure housing to structure (22) with washers (35) and screws (34).
E. Slide spacer (33) and cable drum (32) on tab shaft (21), and secure with screws (31), washers (30 and 27), and nut (26).
F. Engage cables RTA and RTB on cable drum. (See detail B.) Wrap cable RTA 5-1/4 turns counterclockwise, and cable RTB 6-1/4 turns clockwise. Secure cables to drum with phenolic faced clamps.
G. Secure cable guards (24) to lower bearing housing (23) with screws (25).
H. Visually check mechanical stop rings for position shown in detail A.
I. If mounting plate (36) is not installed on trim knob, secure plate to trim knob with three screws (38). Orient plate to knob per figure 401.
J. Position trim knob to indicate neutral (zero) trim.
K. Position trim knob over cutout in control stand and mate trim knob splines (2) with splines in coupling shaft (18). With splines engaged, rotate trim knob mounting plate as necessary so that heads of screws (38) drop into three mating holes in control stand and upper bearing housing.
NOTE: The coupling shaft and rudder trim control wheel are each equipped with a blind spline.
Nov 15/68 27-21-121 Page 407 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
L. Secure trim knob to control stand by installing three screws (37) through mounting plate lugs and mating holes on control stand.
M. Reconnect wire to electrical terminal (3).
N. Remove cable clamps.
O. Reconnect cables RTA and RTB at turnbuckles, but maintain zero cable tension.
P. Disconnect control rod between torque tube and feel and centering unit at torque tube.
Q. Remove rigging pin R-5.
R. Tighten cables RTA and RTB equally to tension specified in Fig. 401, so that rigging pin R-5 may be freely inserted; then remove rigging pin.
S. Connect control rod between torque tube and feel and centering unit. Tighten nut on outer bolt to 50-60 pound-inches, then tighten nut on inner bolt to 12-15 pound-inches.
CAUTION: AFTER TIGHTENING NUT ON INNER BOLT, DO NOT RESET TORQUE FOR BOLT ON OUTER NUT. NUT ON INNER BOLT MAY BECOME LOOSE.
T. Install turnbuckle locking clips.
U. Replace control stand and rudder centering-feel mechanism access panels.
V. Provide rudder hydraulic systems A and B power (Ref 27-21-0).
W. Using rudder trim knob torque adapter, 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.
X. Rotate trim knob in both directions until indicator is at 10. Check that rudder travel is 10.22 +0.50 inches in each direction.
Y. Restore airplane to normal hydraulic configuration (Ref 27-21-0).
Z. Close all access doors and install access panels.
AA. Close ELECTRONIC PANELS LIGHT circuit breaker C284 on P6 panel.
27-21-121 Feb 15/81 Page 408
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
STANDBY RUDDER ACTUATOR SHUTOFF VALVE -REMOVAL/INSTALLATION
1. General
A. The standby rudder actuator shutoff valve and the leading edge standby drive shutoff valve (figure 401) are identical units. This procedure provides instructions for replacement of the standby rudder actuator motor and valve, and for the motor only. Both replacement procedures may be accomplished without removing the valve body from the modular package. The motor drive and valve cam have been indexed to aid in correct motor installation.
2. Removal/Installation Standby Rudder Actuator Valve
NOTE: Use this procedure when replacing assembly of motor and valve. When replacing the motor only use the procedure in paragraph 3.
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(45)
