27-41-00
ALL ú ú 20 Page 5 ú Feb 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
STABILIZER CENTER SECTION SEE A
SEE C SEE D STABILIZER LEADING EDGE STABILIZER OUTBOARD SECTION
HINGE ATTACHMENT CENTER BOX STABILIZER HORIZONTAL FITTING ADJUSTMENT PIVOT PIN SCREW INNER NUT PIN PIVOT NUT PIN PIVOT OUTER FITTING OUTBOARD HINGE SUPPORT SUPPORT BUSHING OUTBOARD HINGE HINGE FITTING STABILIZER INBOARD HINGE SUPPORT FITTING PIVOT ADJUSTMENT SCREW ANTI-ROTATION PLATE
SEE B HINGE STABILIZER SPACER INTERNAL LOCKBOLT NUT LOCKBOLT INTERNAL
WASHER OUTER PIVOT PIN PIN INNER PIVOT
(LEFT OPPOSITE) RIGHT HINGE ASSEMBLY
A B
Figure 3 (Sheet 1) Horizontal Stabilizer - Mechanism Components
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-41-00
ALL ú ú 01 Page 6 ú Jun 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
STABILIZER CENTER SECTION (TOP SURFACE)
SLIDING BLADE SEAL (HIGHER)
FWD
C
SLIDING
BLADE SEAL
(LOWER) STABILIZER CENTER SECTION
FITTING HINGE FITTING DRIVE MAST (BOTTOM SURFACE)
HINGE FITTING
SHIMS
YOKE BONDING JUMPER
LOWER SEAL DOOR
(EXTENDED) BELL WASHER (2 LOCATIONS)
SPURFWD
MAST-TO-CRANK LINK ROD
CRANK-TO-DOOR CRANKLINK ROD
D
NOTE:THE RIGHT SIDE IS SHOWN; THE LEFT SIDE IS OPPOSITE. STABILIZER SHOWN WITH THE LEADING EDGE IN ZERO DEGREE POSITION.
Horizontal Stabilizer - Mechanism Componnents
Figure 3 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-41-00
ALL ú ú 05 Page 7 ú Feb 10/92
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A04715
4.
5.
6.
A
747-400 MAINTENANCE MANUAL
B. Alternate electric stabilizer trim control switches are located on the control stand. These switches bypass the stabilizer trim/rudder ratio changer control module (SRM) and provide inputs directly to the STCMs. The alternate electric stabilizer trim switches are also used to position the stabilizer when maintenance is required.
Stabilizer Trim/Rudder Ratio Changer Control Module (SRM)
___________________________________________________
A. The Stabilizer Trim/Rudder Ratio Module (SRM) contains a reset switch, located on the front panel. The purpose of the switch is to reset latched faults on the ground, which may have been set by airplane maintenance activity. Depressing the switch for approximately 1 second will initiate an SRM power-up and reset all faults.
B. The left and right SRMs are located on the E1-2 and E2-2 shelves respectivly. The SRMs are the interface for the manual electric, automatic stabilizer trim, and speed trim systems. The SRMs contain logic to determine which trim system has authority under all conditions, and monitors all trim commands for proper coincidence. Additionally the SRM controls many other functions: speed trim, stabilizer trim limit changes, stabilizer trim rate control, automatic motor operated valve (MOV) shutdown, rudder ratio changer computations, outboard aileron lockout , and with interfaces to the system EIU's provide system EICAS messages. Speed trim operation is described in 22-24-00/001.
Stabilizer Trim Control Module
______________________________
A. Two identical STCMs are mounted in the empennage at the bottom of the stabilizer actuator bulkhead. Each STCM is an integrated assembly of hydraulic, electrical and mechanical components. Hydraulic pressure is applied to each STCM from its associated hydraulic system. An electrical command for stabilizer trim positions two directional selector valves called arming and control valves. Both of these valves must be positioned to command trim in the same direction before fluid can flow from the STCM. With the valves correctly positioned, separate outlet ports supply fluid to the trim drive mechanism. Pressure is applied sequentially to the hydraulic brake and to the nose up or nose down port on the actuator hydraulic motor.
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 3(120)
