(3)
Back-off to loosen the rod end locknut located on the LVDT.
(4)
Rotate the outer casing of the LVDT just enough so that the part power trim stop can be engaged in the normal activated position (Fig. 501).
NOTE: Since the Autothrottle System is engaged and operating while the following LVDT adjustment is being made, whenever the LVDT case is turned the Autothrottle Servomotor will drive slowly and reposition the thrust lever and the FCU lever to a new position.
(5)
Rotate the part power trim stop CCW into the activated position (Fig. 501).
(6)
Rotate the LVDT casing until the Fuel Control Unit (FCU) lever is within 0.005 inch of the part power trim stop but does not make contact with the stop.
(7)
Tighten the rodend locknut on the LVDT.
(8)
In the cockpit, retard both throttle levers manually and release them and observe that they advance and stop at approximately a vertical position.
(9)
On the engine, verify that the Fuel Control Unit (FCU) lever is within 0.015 inch of the part power trim stop and does not contact the stop.
(10)
Repeat steps (1) thru (9) for second engine.
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Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 22-31-81 Page 503
D. Restore airplane to normal configuration.
(1)
Disengage the autothrottle and set throttle levers to idle (full aft). Page away from the Autothrottle BITE Test page on PDC CDU.
(2)
Install lockwire on LVDT rodend locknut. Lockwire nut to locking device. Lockwire tab on locking device to face away from cross shaft.
(3)
Restore the part power trim stop to the "stowed" (full CW) position and install lockwire in this position.
(4)
Repeat steps (2) and (3) for second engine.
(5)
Remove electrical power if no longer required.
(6)
Close engine cowl panels (Ref 71-11-11).
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22-31-81 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/85
AUTOTHROTTLE SERVOMECHANISM - REMOVAL/INSTALLATION
EFFECTIVITY
BA G-BKYA and on WA N236WA thru N241WA GJ B-2509 and B-2510
1. General
A. The autothrottle servomechanism is located in front of the electronics compartment and can be accessed directly without removing any airplane panels. One servomechanism is associated with each engine. Each servomechanism consists of three parts: a torque switch mechanism, an actuator assembly, and a torque limiter switch (Fig 401).
B. The torque switch mechanism is mechanically part of the engine control cable run. Removal/installation instructions for the torque switch mechanism are provided in 76-11-92.
C. The actuator assembly includes a servo motor, reduction gear train and electromagnetic clutch. The actuator assembly can be removed without disturbing the engine control cable system and removal/installation instructions are provided in par. 2.
D. The torque limiter switch is located on the upper face of the torque switch mechanism body. This switch can be replaced without requiring adjustment. R/I instructions are provided in par. 3.
2. Removal/Installation Actuator Assembly
A. Equipment and Materials
(1) Grease (MIL-G-23827)
B. Remove Actuator Assembly
(1)
Place thrust lever in idle position.
(2)
Open autothrottle system ac and dc circuit breakers on P6 panel.
(3)
Release four self-retaining attachment bolts (two on each side of actuator assembly).
(4)
Carefully detach actuator assembly from the torque switch mechanism.
(5)
Disconnect electrical cable from actuator assembly.
C. Install Actuator Assembly
(1)
Check shaft and gears for signs of wear.
(2)
Apply a thin coat of grease to pinion of actuator assembly.
(3)
Orient actuator assembly so that electrical connector is toward the aft end of airplane.
(4)
Connect electrical cable to actuator assembly.
(5)
Set actuator assembly in place (note alignment pins) against torque switch mechanism.
(6)
Tighten the four self-retaining attachment bolts (two on each side of actuator assembly).
(7)
Perform autothrottle system BITE test (Ref 22-31-01, A/T).
Oct 20/84 22-31-91 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H33340
Autothrottle Servomechanism Assembly Installation 5B8
22-31-91 Figure 401 Jan 20/83
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