EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-08-07
ALL ú ú 01 Page 403 ú Jun 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400 MAINTENANCE MANUAL
FLIGHT CONTROLS ELECTRONICS (FCE) - DESCRIPTION AND OPERATION
_____________________________________________________________
1. General (Fig. 1)_______
A. The Flight Controls Electronics (FCE) System is a collection of black box modules which provide control, indication, and fault detection functions for the primary and secondary flight controls. The modules are located on the E1-2 and E2-2 electronics shelves.
B. The FCE modules interface with airplane systems to provide indication, control, and fault detection functions for flap control (Ref 27-51-00, 27-81-00), stabilizer trim (Ref 27-41-00), rudder ratio control authority (Ref 27-21-00), aileron lockout (Ref 27-11-00), and yaw damping system (Ref 22-21-00). The FCE contains four power supply modules which provide power to all FCE modules.
C. The FCE consists of the following modules:
(1)
Flap Control Unit (FCU) (AMM 27-51-00, 27-81-00)
(a)
FCU - left M7881
(b)
FCU - center M7880
(c)
FCU - right M7879
(2)
Stabilizer Trim/Rudder Ratio Module (SRM) (AMM 27-41-00, 27-21-00)
(a)
SRM - left M3136
(b)
SRM - right M3137
(3)
Yaw Damper Module (YDM) (AMM 22-21-00)
(a)
YDM - upper M7362
(b)
YDM - lower M7363
(4)
Power Supply Module (PSM)
(a)
PSM - left No. 1 M7358
(b)
PSM - left No. 2 M7359
(c)
PSM - right No. 1 M7360
(d)
PSM - right No. 2 M7361
2. Flap Control Unit_________________
A. The three Flap Control Units provide control, protection, and indication for the leading edge and trailing edge flaps. The FCU's receive input information from flight deck controls, flap and stabilizer position sensors, air data computers, hydraulics sytem, and air/ground relays. These inputs are used to generate output signals to the primary and alternate flap actuators, flap position indicator displays, and other airplane systems.
B. Each FCU contains built in test equipment (BITE) for fault detection and isolation. Faults detected are transmitted to EICAS where a caution or status message will be displayed. Specific fault information will be stored in the Central Maintenance Computer (CMC) for retrieval during later maintenance. Tests of the FCU's may be initiated by the CMC.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-09-00
ALL ú ú 01 Page 1 ú Feb 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
RIGHT FCE: FLAP CONTROL UNIT (FCU)
STABILIZER TRIM/RUDDER RATION MODULE (SRM) YAW DAMPER MODULE (YDM) POWER SUPPLY MODULE (PSM)
LEFT FCE: FLAP CONTROL UNIT (FCU) STABILIZER TRIM/RUDDER RATION MODULE (SRM) YAW DAMPER MODULE (YDM) POWER SUPPLY MODULE (PSM)
FCE Power Supply Module
Figure 1
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-09-00
ALL ú ú 01 Page 2 ú Feb 10/95
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
E77953
A
747-400
MAINTENANCE MANUAL
115V AC STDBY BUS
28V DC BAT. BUS
28V DC BAT. BUS
115V AC STDBY BUS
115V AC
BUS 1
28V DC
BUS 1
28V DC
BUS 2
115V AC
BUS 2
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：747-400 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 1(38)
