(a)
Turn the actuator (12) and the reaction link (3) until you can get access to the bolts (20).
(b)
Remove the bolts (20) that hold the actuator to the trunnion block (19).
S 022-019
(5)
Remove the actuator (12).
G.
Remove the Rudder Reaction Link (Fig. 201).
S 032-020
(1)
Disconnect these components:
(a)
The input rod (18) that is connected between the actuator shearout lever (17) and the torque tube (1)
NOTE: Do not remove the shearout lever from the PCA.
____
(b)
The electrical connector (25) from the rudder PCA monitor sensor (24)
(c)
The hydraulic lines (2) from the actuator (12) and do this step: 1) Seal the hydraulic lines with caps.
S 032-021
(2)
Remove the bolts (5) that connect the actuator (12) and reaction link (3) rod ends to the rudder front spar (4).
S 822-022
(3)
Do these steps to remove the remaining hydraulic pressure from the PCA:
(a)
Make sure the actuator return port does not have a cap installed.
(b)
Turn the shearout lever (17) in a counterclockwise direction to remove unwanted hydraulic pressure.
S 032-023
(4)
Remove these components:
(a)
The bolt (27), washer (28), and nut (29) that connect the hanger link (26) to the trunnion block (19)
(b)
The actuator (12), trunnion block (19), and reaction link (3) as an assembly from the airplane.
S 022-024
(5)
Do these steps to remove the reaction link (3) from the trunnion block (19):
(a)
Remove the bolt (30), washer (31), and nut (32) that connect the reaction link (3) to the end cap (33) (2 locations).
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27-21-20
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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757 MAINTENANCE MANUAL
(b) Remove the end cap (33), pin (34), and the reaction link (3) from the trunnion block (19).
TASK 27-21-20-422-025
3. Rudder PCA and Reaction Link - Installation
___________________________________________
A. General
(1) This task contains two procedures, one to install the rudder PCA, and one to install the rudder reaction link. Because this task contains two procedures, only the applicable group of steps must be done.
To start one of these procedures, do the group of steps that is necessary to install the component. Then, do the "Rudder PCA Adjustment and Test" and the "Put the Airplane Back to Its Usual Condition" groups of steps.
B. Equipment
(1)
Rig Pins from Set B20003-XX (Ref 20-10-24):
(a)
R3 - P/N B20003-16
(b)
R7 - P/N B20003-13
C.
Consumable Materials
(1)
D00015 Grease, Corrosion Preventive - BMS 3-24
(2)
C00308 Compound, Corrosion Preventive -MIL-C-11796, Class 3
(3)
D00153 Fluid, Hydraulic - BMS 3-11
D.
Parts
~.............................................................................. | AMM | | AIPC | ................. ............................ | FIG | ITEM | NOMENCLATURE | SUBJECT | FIG | ITEM | ................................................................................ | 201 | 5 | Bolt | 27-21-20 | 01 | 95 | | | 6 | Bushing | | | 110 | | | 7 | Washer | | | 100 | | | 8 | Nut | | | 105 | | | 12 | Actuator | | | 205 | | | 13 | Bolt | | | 5 | | | 14 | Washer | | | 25 | | | 15 | Washer | | | 30 | | | 16 | Nut | | | 35 | | | 20 | Bolt | | | 180 | | | 21 | Washer | | | 185 | | | 22 | Washer | | | 190 | | | 23 | Nut | | | 195 | 2.......….......…...................................…...........….....…........1
E. References
(1)
06-42-00/201, Empennage Access Doors and Panels
(2)
20-10-24/201, Rigging Pins
(3)
24-22-00/201, Electrical Power - Control
(4)
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