SPEED-ATTITUDE CORRECTION
MACH TRIM SYSTEM................................................................................................ 22-21-0 Description and Operation
Mach Trim Components
Mach Trim Actuator
Mach Trim Controls
Mach Trim Coupler
Mach Trim Operation
Trouble Shooting
Adjustment/Test
Mach Trim Actuator.................................................................................................. 22-21-11 Removal/Installation Adjustment/Test
Mach Trim Coupler ................................................................................................. . 22-21-21 Removal/Installation
Mach Trim Flap Switch. ........................................................................................... 22-21-31 Removal/Installation Adjustment/Test
AUTOTHROTTLE
AUTOTHROTTLE SYSTEM ....................................................................................... *[1] 22-31-0 Description and Operation Subject Subject No.
512
Contents 22 Page 6 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/99
AUTO THROTTLE SYSTEM ...................................................................................... *[2] 22-31-0 Description and Operation
Autothrottle Components
Accelerometer
AFCS Mode Control Panel
AFCS Annunciator
Angle of Airflow Vane
Attitude Director Indicator (ADI)
Autothrottle Computer
Disengage Switches
Drive Assemblies
EPR Indicators
Servo
Thrust Lever Position Transmitters
Operation
Trouble Shooting
Maintenance Practices
Deactivation Procedure
Adjustment/Test
AUTO THROTTLE CLUTCH ASSEMBLY ..................................................................... *[1] 22-31-51 Removal/Installation Inspection/Check
Autothrottle Accelerometer ......................................................................................... *[2] 22-31-71 Removal/Installation
Thrust Lever Position Transmitter............................................................................... *[2] 22-31-81 Removal/Installation Adjustment/Test
Autothrottle Servomechanism..................................................................................... *[2] 22-31-91 Removal/Installation
Autothrottle Computer................................................................................................. *[2] 22-31-101 Removal/Installation
*[1] GJ All Except B-2509 and B-2510
*[2] GJ B-2509 AND B-2510
*[3] All Except Yaw Damper Coupler P/N 4084042 (before SB 27A1206)
*[4] Aircraft with Yaw Damper Coupler P/N 4084042 (after SB 27A1206)
5C8
May 01/99 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Contents 22 Page 7
AUTO FLIGHT - GENERAL - DESCRIPTION AND OPERATION
1. General
A. The auto flight systems consist of an Autopilot and Yaw Damper System and a Mach Trim System. Partial provisions for an Auto Throttle System are also installed on the airplane.
B. Autopilot and Yaw Damper Systems
(1)
The autopilot system controls the airplane about the pitch and roll axes and provides automatic airplane stabilization whenever the pitch and roll channels are engaged. Automatic stabilizer trim, which is a function of the pitch channel, compensates for changes in airplane trim due to fuel burnoff etc. Each autopilot channel may be engaged separately and, in some modes, are not dependent upon each other. Various mode selections enable the pilots to command the autopilot to fly the airplane onto a selected heading, maintain altitude, or fly to a selected VOR, localizer or OMEGA course as well as make automatic approaches to runways equipped with ILS facilities. The pilots may also manually control the airplane in a normal manner with the control wheel/column (control wheel steering) without disengaging the pitch or roll axes of the autopilot system. Pilots can then assist the autopilot system in flying to a selected heading or course. Use of control wheel steering does not disengage either channel of the autopilot system.
(2)
The yaw damper system provides airplane stabilization about the yaw axis. Automatic damping of dutch roll is sensed and corrected for by the yaw damper system whenever the system is engaged. Rudder deflections are not felt by the pilots since the rudder pedals are not moved by the yaw damper system. No interlocks are provided between the yaw damper system and the autopilot system.
(3)
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本文链接地址：737 AMM 飞机维护手册 AUTO FLIGHT 自动飞行 1(5)
