22-13-00
ALL ú
ú 01 Page 5
ú Oct 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
COMMANDPROCESSING ELECTRICAL AUTOPILOTDIGITAL
ANALOG
MECHANICALCOMMANDS PRODUCESYNCHRONIZATION
HYDRAULICALLY ACTUATED PRE ENGAGE TEST
MECHANICAL OUTPUTS
ROLLOUT POWER CONTROL PKG-LFCC-L (E1-1)
FUNCTIONALLY
IDENTICAL AS
AUTOPILOT
FCC-L
ENGAGEMENT
MODE
SELECTION
ROLLOUT POWER CONTROL PKG-CFCC-C (E1-3)
MCP (P10) ROLLOUT POWER CONTROL PKG-RFCC-R (E1-4)
Yaw Component Functional Interface Figure 2 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-00
ALL ú
ú 01 Page 6
ú Oct 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
INPUTS OUTPUTS
FLIGHT DIRECTOR ON HEADING SELECTED BANK ANGLE LIMITS HEADING SELECT MODE REQUEST HEADING HOLD MODE REQUEST LNAV MODE REQUEST APPROACH MODE REQUEST LOCALIZER MODE REQUEST
MODE CONTROL PANEL
MODE CONTROL PANEL
FLIGHT MANAGEMENT COMPUTER
ILS RECEIVER
ALONG-TRACK HORIZONTAL ACCELERATION CROSS-TRACK HORIZONTAL ACCELERATION BODY LATERAL ACCELERATION BODY PITCH RATE BODY YAW RATE ROLL ATTITUDE MAGNETIC HEADING TRUE HEADING MAGNETIC TRACK TRACK ANGLE (TRUE & MAG) GROUND SPEED
INERTIAL REFERENCE UNIT
CENTRAL LATERAL CONTROL PKG
OR LATERAL AUTOPILOT SERVO
ROLLOUT POWER CONTROL PKG
ROLL/YAW
AXIS
CONTROL
FUNCTIONS
FLIGHT CONTROLCOMPUTER
AILERON HYDRAULIC ARM AILERON SERVO DETENT ENGAGE AILERON SERVO COMMAND (EHSV) SERVO LVDT EXCITATION SURFACE LVDT EXCITATION
CENTRAL LATERAL CONTROL PKG. OR LATERAL AUTOPILOT SERVO
RUDDER HYDRAULIC ARM RUDDER SERVO DETENT ENGAGE RUDDER SERVO COMMAND (EHSV) SERVO LVDT EXCITATION SURFACE LVDT EXCITATION
ROLLOUT POWER CONTROL PKG
FCC Roll and Yaw Axes - Control Inputs and Outputs
Figure 3
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
22-13-00
ALL ú
ú 01 Page 7
ú Oct 10/88
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
I. Servo position refers to the position of the autopilot actuator within each servo as sensed by the attached LVDT. Surface position refers to the position of the main actuator or output of the servo as sensed by the attached output LVDT.
2. Component Details
_________________
A. The CLCP, LAS, and RPCP have identical functional components and so will only be described once. The LAS, RPCP, electrohydraulic servovalves and solenoid valves are considered as autopilot LRUs, the CLCP is considered a flight control LRU (chapter 27). The Linear variable differential transducers are not considered LRUs.
(1)
Solenoid Valves
(a)
There are two solenoid valves installed on each servo; the ARM solenoid valve and the ENGAGE solenoid valve. The valves are identical and interchangeable. Each valve is an electrically operated open-close valve which completes hydraulic pressure through a portion of the servo when the appropriate signal is received from the FCC.
(b)
The valve is installed with four bolts and sealed with a gasket plate. Electrical pins are mated when the solenoid valve is bolted in position.
(2)
Electrohydraulic Servovalves
(a)
One EHSV is installed on each servo, and is the means by which the electrical commands from the FCC become hydraulic commands. The EHSV contains a sealed torque motor, a feedback spring, a projector jet, and a piston. Hydraulic pressure through the valve can be applied to either of two output ports. When no error signal is applied to the torque motor, a small amount of hydraulic fluid flows through a flexpipe attached to the torque motor armature and out of the projector jet. From the jet, equal pressure is applied to opposite ends of the piston, holding it at center and closing both output ports.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 空調 AUTO FLIGHT(107)
