757
MAINTENANCE MANUAL
S 024-019
(3) Remove the bottom compensating rod.
TASK 27-21-19-424-020
3. Rudder Thermal Compensating Linkage and Its Components - Installation_____________________________________________________________________
A. General
(1) This task contains these procedures:
-
Install the Input Crank Assembly
-
Install the Top Compensating Rod
-
Install the Multiplier Crank
-
Install the Bottom Compensating Rod.
Because this task contains four procedures, do only the applicable groups of steps.
To start one of these procedures, do the group of steps that is necessary to install the component. Then, do the "Put the Airplane Back to Its Usual Condition" group of steps.
B. Equipment
(1)
Rig Pins from Set B20003-XX (Ref 20-10-24):
(a)
R7 - P/N B20003-13
(b)
R8 - P/N B20003-13
(2)
Power Drill, Commercially Available
C.
Consumable Materials
(1)
Rivet - NAS1398D-2 (6 are necessary)
(2)
C00308 Compound, Corrosion Preventive -MIL-C-11796, Class 3
D.
References
(1)
06-42-00/201, Empennage Access Doors and Panels
(2)
20-10-24/201, Rig Pins
(3)
22-21-00/501, Yaw Damper System
(4)
24-22-00/201, Electrical Power - Control
(5)
27-21-00/501, Rudder and Rudder Trim Control System
E.
Access
(1)
Location Zone 324 Vertical Stabilizer - Rear Spar to Trailing Edge
(2)
Access Panels 311AL Tailcone Compartment 322BZ Bottom Forward Torque Box 324AL Body to Fin Seal 324BL Aft Side of Rear Spar and Rudder Hinge 324CL Rudder Hinge and PCAs
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-19
ALL ú ú 04 Page 408 ú Sep 20/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
F. Install the Input Crank Assembly (Fig. 401)
S 624-021
(1)
Apply some of the corrosion preventive compound to the bolts, bushings, washers, and nuts before you install them.
S 434-022
(2)
Install the bolts, bushings, washers, and nuts that connect the input crank to its support brackets.
S 434-023
(3)
Install the bolts, bushings, spring retainers, washers, nuts, and springs that connect the summing lever to the input crank.
S 434-024
(4)
Connect these components:
(a)
The servo summing link to the yaw damper servos
(b)
The control rods from the power control actuators to the summing lever
(c)
The control rod from the right ratio changer crank to the summing lever and do this step: 1) Tighten the control rod jamnuts.
S 824-025
(5)
Adjust the ratio changer pogo rod until rig pin R7 can be easily installed in the pogo (Fig. 402).
S 094-026
(6)
Tighten the pogo rod jamnuts and remove rig pin R7.
S 824-027
(7)
Adjust the bias pogo until rig pin R8 can be easily installed in the pogo (Fig. 402).
S 094-028
(8)
Tighten the pogo rod jamnuts and remove rig pin R8.
S 824-029
(9)
Adjust the top compensating rod and do these steps:
(a)
Make sure the top and bottom gaps at the input crank hammer are not more than 0.09 inch (2.3 mm).
(b)
Make sure the top and bottom gaps at the input crank hammer are the same (use a tolerance of |0.01 inch (+/- 0.25 mm)).
(c)
Tighten the jamnuts for the top compensating rod and lock them with a wire.
(d)
Connect the top compensating rod to the input crank.
(10)
Do a test of the Yaw Damper System (Ref 22-21-00).
S 724-030
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：757 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(76)
