737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(42)

曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者

C.  Grease - MIL-G-23827 (Ref 20-30-21)
D.  Line - two lines to guide rudder trim actuator cables RTA-3 and RTB-3 through cable run when installing rudder trim actuator (Ref 27-09-111 MP for cable specifications).
E.  Rudder Trim Knob Torque Adapter - SE27-2011
F.  Scale - 0 to 2 feet (in inches, tenths and hundredths of an inch)
G.  Lubricant - MIL-L-23699 or BMS 3-24 grease (Ref 20-30-21)
H.  Lubricant - MIL-L-23699 or PWA 521 Turbine Engine Lubricating Oil (Ref 20-30-21)
2.  Prepare for Removal
A.  Remove rudder systems A, B, and standby hydraulic power (Ref 27-21-0 MP).
B.  Place rudder pedals and trim control wheel in neutral position.
C.  Insert rigging pin R5 in feel and centering unit (Fig. 401).
D.  Remove access panels 9509L, 9512, 9514, and 3701.
3.  Remove Rudder Trim Actuator
A.  Disconnect cables RTA and RTB at aft turnbuckles and tie a line of suitable length (Ref par. 1) to each of the actuator cables (RTA-3 and RTB-3) at the terminals. Clamp cables at actuator end to maintain cable wrap when removing actuator.
NOTE:  Lines are to be pulled through with actuator cables when removing actuator so as to be used as a guide for pulling through cables on actuator being installed.
B.  Remove actuator to structure mounting bolt and bushing.
C.  Remove actuator to feel and centering unit mounting bolts.
D.  Remove actuator (including cables) from airplane.
(1)  
Remove by pulling actuator and cables out and aft from airplane being careful to avoid damage to cables.

(2)  
When cables are pulled through, disconnect lines from cable ends and connect to terminal end fittings of actuator being installed or secure in place until actuator is to be installed.

525 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-111 Page 401 

G08369 G43159
Rudder Trim Actuator Installation  500 
27-21-111 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 15/68 

526  Rudder Trim Actuator Installation 
Aug 01/95  Figure 401 (sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-21-111 Page 403 

4.  Prepare for Installation
A.  Apply lubricant, MIL-L-23699, by oil can, between outside diameter of actuator screw and inside diameter of drum, with actuator screw in extended position. Apply oil at drain holes in cable drum. BMS 3-24 grease may be used intead of MIL-L-23699 oil. Extend and retract actuator screw several times to assure lubricant coats screw threads.
B.  Apply lubricant, MIL-L-23699 or PWA 521 turbine engine lubricating oil, by oil can to outside diameter of actuator cable drum.
C.  Remove rudder systems A, B, and standby hydraulic power (Ref 27-21-0).
D.  Check that rigging pin R-5 is installed in feel and centering unit.
E.  Check for allowable wear at rudder trim actuator installation points (Ref Rudder Trim Actuator -Inspection/Check).
F.  Prior to positioning cables and actuator in airplane, ensure that cables RTA and RTB are equally wrapped 4-3/4 turns on cable drum per Detail C, Fig. 401. Secure cables to hold in place during installation.
5.  Install Rudder Trim Actuator
A.  Connect lines pulled through with old cable to ends of cables RTA-3 and RTB-3 on ruddder trim actuator being installed. Using two men, one man support actuator and the other man pull cables through from stabilizer jackscrew compartment by pulling on the lines connected to the cables. Untie lines from cables when cables are in place.
B.  Align center of painted index mark on cable drum extension with cotter pin hole on side of actuator housing (installed position) to place rudder trim actuator drum in neutral.
C.  Place trim actuator in position and install actuator to feel and centering unit mounting bolts (if bearing sleeve is not flush with bearing, install washer between actuator and bearing). Tighten bolts to torque value of 35 to 45 pound-inches and lockwire.
D.  Manually rotate actuator screw until dimension of 1.92 +0.03/-0.02 inches is obtained as shown in Fig. 401.
27-21-111 Jun 20/85 Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

E.  Using only threaded adjustment plug in upper end of actuator screw, adjust until mounting holes align.
NOTE:  If nearest increment of adjustment with plug is insufficient to align mounting bolt holes, trim drum may be rotated a small amount. Cotter pin hole on actuator housing must not be off paint index mark on trim actuator drum at 0-degree trim.
　
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(42)