757
MAINTENANCE MANUAL
BIAS POGO
RIG PIN HOLE R4
RIG PIN HOLE R8
BOLT BUSHING WASHER NUT
YAW DAMPER BIAS POGO MIDDLE POWER CONTROL ACTUATOR
C D
POGO
RIG PIN
HOLE R7
FWD
RATIO CHANGER POGO ROD
E
Rigging Pin Installation Figure 402 (Sheet 2)
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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757
MAINTENANCE MANUAL
E. Prepare for the Removal
S 864-002
(1)
Supply electrical power (Ref 24-22-00).
S 864-003
(2)
Move the FLT CONTROL SHUTOFF L, R, and C switches on the right side panel, P61, to OFF. Attach DO-NOT-OPERATE tags and make sure the switch position lights come on.
S 864-004
(3)
Open these circuit breakers on the overhead panel, P11, and attach DO-NOT-CLOSE tags:
(a)
11H17, FLT CONT SHUTOFF TAIL LEFT
(b)
11H18, FLT CONT SHUTOFF TAIL CTR
(c)
11H28, FLT CONT SHUTOFF TAIL RIGHT
S 494-005
(4)
Move the towing lever on the metering valve module to the tow position and install the towing lever lockpin in the nose gear (Fig. 403).
S 014-007
(5)
Open access panels 324AL, 324BL, and 324CL (Ref 06-42-00).
NOSE GEAR TOWING LEVER LOCKPIN
TOWING LEVER (IN THE TOW POSITION)
TOWING LEVER SEE A
TOWING LEVERA
Nose Gear Steering Isolation Figure 403
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27-21-19
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
F.
G.
H.
I.
A
757
MAINTENANCE MANUAL
S 014-050
WARNING:_______ STAY OFF THE SERVICE ACCESS DOOR, 311AL, AND THE ACCESS DOOR
FOR THE CONTROLS BAY, 313AL. YOUR WEIGHT CAN CAUSE THE
SPRING-LOADED LATCHES TO RELEASE. IF YOU FALL THROUGH THE
DOOR, INJURY CAN OCCUR.
(6)
Open access doors 311AL and 322BZ (Ref 06-42-00).
S 494-008
(7)
Install these rig pins (Fig. 402):
(a)
R3 (for the rudder feel, centering, and trim mechanism)
(b)
R4 (for the middle power control actuator linkage)Remove the Input Crank Assembly (Fig. 401)
S 024-009
(1)
Remove the Yaw Damper Summing Lever (Ref 27-21-17).
S 034-010
(2)
Disconnect the input crank from its support brackets (3 locations).
S 024-011
(3)
Remove the input crank.
Remove the Top Compensating Rod (Fig. 401)
S 034-012
(1)
Disconnect the top compensating rod from the input crank.
S 034-013
(2)
Disconnect the top compensating rod from the multiplier crank.
S 024-014
(3)
Remove the top compensating rod.Remove the Multiplier Crank (Fig. 401)
S 034-015
(1)
Disconnect these components:
(a)
The top compensating rod from the multiplier crank
(b)
The bottom compensating rod from the multiplier crank
(c)
The multiplier crank from its support bracket.
S 024-016
(2)
Remove the multiplier crank.
Remove the Bottom Compensating Rod (Fig. 401)
S 034-017
(1)
Disconnect the bottom compensating rod from the multiplier crank.
(2)
Disconnect the bottom compensating rod from the support bracket.
S 034-018
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-21-19
ALL ú ú 04 Page 407 ú Sep 20/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
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