SEE B ALCS CONTROL ROD
FITTING AFT BEARING SEE CQUADRANT AUTOPILOT WASHER
CRANK
WING NUT
BOLT
CABLE COTTER PIN
WASHERA1B NUT (2 LOCATIONS) FWD INBD
FEEL, CENTERING, AND TRIM MECHANISM
A
Lateral Feel, Centering, and Trim Mechanism Installation
Figure 201 (Sheet 1)
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A
757
MAINTENANCE MANUAL
TOP NUT ACTUATOR LINK
BOTTOM NUT EYEBOLT
CAM LEVER FEEL SPRING (TOP ARM)
ROLLER
FEEL CAM
CAM LEVER
(BOTTOM ARM)
INBD
FEEL SPRINGS
B
AUTOPILOT
CRANK ROD END
ADJUSTMENT AUTOPILOT
SEE D INSPECTION SERVO
4HOLES SERVO AUTOPILOT
CONTROL ROD CRANK CRANK
3LENGTH 1 JAMNUT CONTROL ALCS
ROD
INBD
ALCS CONTROL ROD
(CENTER ALCS SHOWN, LEFT ALCS IS FORWARD)
C
1
DO NOT DISCONNECT THE ROD END FROM THE SERVO CRANK 1.34-1.36 INCHES
22
ADJUST THE ROD END FOR THE AUTOPILOT CRANK AS SHOWN, THEN ADJUST THE CONTROL ROD LENGTH ROD END ADJUSTMENT
3 TURN THE CONTROL ROD BODY UNTIL THE LENGTH OF THE CONTROL ROD IS APPROXIMATELY 12.51 INCHES
D 4
MAKE SURE YOU CANNOT PUT A 0.063 INCH DIAMETER RODTHROUGH THE INSPECTION HOLES AFTER YOU DO THE ALCS ADJUSTMENT
Lateral Feel, Centering, and Trim Mechanism Installation Figure 201 (Sheet 2)
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MAINTENANCE MANUAL
AILERON QUADRANT AND
OVERRIDE MECHANISM BUS ROD
SEE B (TO THE FEEL, CENTERING, AND
TRIM MECHANISM)
FWD
LATERAL CONTROL
OVERRIDE MECHANISM
SEE A
RIG PIN
HOLES A2
INBD FWD
LATERAL CONTROL OVERRIDE MECHANISM
A
RIG PIN HOLE A3
AILERON QUADRANT AND OVERRIDE MECHANISM (ONE MECHANISM ON EACH WING)
B
Lateral Feel, Centering, and Trim Mechanism Installation
Figure 202
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757 MAINTENANCE MANUAL
S 012-071
(2)
Open access panel 561AB (Ref 06-44-00/201).
S 032-019
(3)
Disconnect these components:
(a)
The electrical connector from the trim actuator.
(b)
Body cables A1A and A1B and wing cables A1A and A1B from the quadrant. Tag the cables for identification.
NOTE: The turnbuckles for body cables A1A and A1B are behind
____ the ceiling panel that is inboard of the ceiling panel adjacent to the forward cargo door (AMM 25-50-01/401). The turnbuckles for wing cables A1A and A1B are outboard of the feel, centering, and trim mechanism.
(c) The trim actuator from the actuator link.
S 032-020
(4)
Remove these components:
(a)
The bolts that connect the support bracket to the airplane (4 locations).
(b)
The bolts that connect the support fitting to the airplane (4 locations).
S 022-021
(5) Remove the feel, centering, and trim mechanism.
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