E1-2
SEE D
MAIN EQUIP CTR
SEE B
L, R, STABILIZER TRIM/RUDDER RATIO MODULES M3136, M3137
CAPT, F/O
HORIZONTAL STABILIZER 117ARSTABILIZER TRIM SHUTOFF
POSITION VALVE SWITCHES,
INDICATORS, S627, S628 MAIN EQUIP CTR
N311, N312
B
ALTERNATE MANUAL AND AUTOPILOT ELECTRIC A DOWN LIMIT SWITCH, AUTOPILOT BSTABILIZER S816 DOWN LIMITTRIM SWITCHES, SWITCH, S815
S1953 CONTROL MANUAL AND AUTOPILOT STAND UP SWITCH, S814
AUTOPILOT B UP LIMIT SWITCH, S813
FWD
CONTROL STAND ELEVATOR CONTROL ACTUATED CUTOUT SWITCHES
C D
Horizontal Stabilizer - Component Location
Figure 102 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-40-00
ALL ú ú 01 Page 104 ú Oct 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 FAULT ISOLATION/MAINT MANUAL
HORIZONTAL
STABILIZER
CENTER, LEFT, RIGHT
STABILIZER POSITION HORIZONTAL
TRANSMITTERS, STABILIZER
M7883, M7884, M7882 JACKSCREW
SEE H SHT 3
STABILIZER TRIM LIMIT SWITCHES
SEE G STABILIZER HYDRAULIC
BRAKES SHT 3
JACKSCREW LEFT, RIGHTSEE E TRIM DRIVE
STABILIZER MECHANISM
TRIM CONTROL
MODULES, HYDRAULIC
B188, B189 MOTORS
RATE CONTROL SEE F FWD
SOLENOID VALVE, YM1V005, YM2V005
NOSE DOWN ARMING STABILIZER JACKSCREW
SOLENOID VALVE,
YM1V003, YM2V003 E
NOSE UP ARMING SOLENOID VALVE, YM1V001, YM2V001
NOSE DOWN CONTROL SOLENOID VALVE, YM1V004, YM2V004
NOSE UP CONTROL SOLENOID VALVE, YM1V002, YM2V002
HYDRAULIC PRESSURE SWITCH, YM1S001, YM2S001
FWD
MANUAL BRAKE
BYPASS VALVE MOTOR OPERATED SHUTOFF VALVE, YM1V006, YM2V006
LEFT, RIGHT STABILIZER TRIM CONTROL MODULE, B188, B189
F
Horizontal Stabilizer - Component Location Figure 102 (Sheet 2)
L05727
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-40-00
ALL ú ú 03 Page 105 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 FAULT ISOLATION/MAINT MANUAL
CONTROL ROD (REF)
STABLIZER CENTER BOX (REF) CRANKSHEAR DECK (REF)(REF)
FWD
ALTERNATE
NOSE UP - RIGHT,
LEFT, CENTER, RIGHT
S1961 STABILIZER POSITION TRANSMITTER, M7884, M7883, M7882
H
ALTERNATE
NOSE DOWN - RIGHT,
S1960
ALTERNATE NOSE UP - LEFT, S1955
ALTERNATE NOSE DOWN - LEFT, S1954
FWD
STABILIZER TRIM
LIMIT SWITCHES
G
Horizontal Stabilizer - Component Location (Details from Sht 2)
Figure 102 (Sheet 3)
L05728
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-40-00
ALL ú ú 02 Page 106 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
HORIZONTAL STABILIZER TRIM CONTROL SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________________________
1. General_______
A. The stabilizer trim control system trims the airplane longitudinally by varying the horizontal stabilizer angle of attack. The system pivots the stabilizer about its rear attachments to the empennage structure by driving a hydraulically powered trim drive mechanism. This mechanism consists of a linear ball screw actuator driven by two hydraulic motors. A gimbal mounting attaches the lower end of the mechanism to the empennage structure. A ball nut driven by the ball screw connects to the stabilizer through another gimbal attachment. Thus the actuator constitutes the stabilizer forward attachment. Two independent stabilizer trim control modules (STCMs) direct hydraulic power to the trim drive mechanism. Figure 2 illustrates the layout of the stabilizer trim control system and the locations of the principal controls and components.
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 3(117)
