曝光台 注意防骗
网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
feel system (one actuator failed).
PITCH FEEL FAULT
PITCH FEEL caution (amber)
Indicates a failure of the pitch feel system.
Status Page
Primary Page
Vol. 1 11--40--5
FLIGHT CONTROLS
Elevators REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
A. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
PFEEL 1 DC BUS 1 1 F2
Elevators Pitch Feel
PFEEL 2 RTL DC
ESSENTIAL 2 R5
Vol. 1 11--40--6
FLIGHT CONTROLS
Elevators REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 11--50--1
FLIGHT CONTROLS
Horizontal Stabilizer Trim REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
1. HORIZONTAL STABILIZER TRIM
Horizontal stabilizer trim system provides pitch trim by varying the angle of the horizontal
stabilizer. The horizontal stabilizer is positioned by a screw jack driven by two electric
motors and controlled by the spoiler and stabilizer control units (SSCUs) through selection of
the STAB TRIM engage switches. Each motor has a magnetic brake to prevent trim
runaway. Trim range is from +2_ (leading edge up) to --13_ (leading edge down).
The horizontal stabilizer trim is operated manually by the pilot control wheel trim switches or
automatically by the autopilot. Trim disconnect switches are provided on each control wheel.
The SFECU’s operate in one of four modes in the following priority:
S Manual trim -- Nose--up or nose--down trim commands (from the control wheel switches)
are sent to the the slat/flap electronic control unit (SFECU). The SFECU moves the
screw jack at a rate that is dependent on Mach airspeed.
S Autopilot trim -- When the AP is engaged and air loads begin to build up on the elevator,
the flight control computer, through the SSCU, sends signals to the screw jack motor
controllers to aerodynamically trim the aircraft.
S AUTO trim -- Auto trim occurs when the flaps are moving between 0 and 20_ in either
direction. When the flaps are extended or retracted, trim commands (via the SSCU’s) are
sent to the screw jack motor controllers to compensate for aircraft pitching caused by flap
configuration changes.
S Mach trim -- When the Mach Trim is engaged, the horizontal stabilizer trim is adjusted (at
a rate of 0.03_ to 0.06_ per second) to compensate for the aircraft tendency to pitch
down at increasing Mach numbers. The Mach Trim function is disabled when the autopilot
is engaged.
On every aircraft power--up, each SSCU performs a Computer Power--On--Self--Test
(CPOST). Following the CPOST, the computer performs a System Power--On--Self--Test
(SPOST). The SPOST is divided into two parts, SPOST1 and SPOST2. SPOST1 checks
the integrity of specific flight control system components and the check lasts up to 60
seconds. SPOST2 (Pilots SSCU Test) is performed automatically following aircraft
power--up, but only once per 50 flight cycles. The SPLR/STAB IN TEST advisory message
will only appear for up to 60 seconds during the SPOST2.
If required, SPOST2 may be manually initiated (after SPOST1 is complete) by depressing
one Stab Disconnect Switch and the Mach Trim engage switch simultaneously for 5
seconds.
Vol. 1 11--50--2
FLIGHT CONTROLS
Horizontal Stabilizer Trim REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Horizontal Stabilizer Trim Control System Schematic
Figure 11---50---1
AC BUS 2 OR ADG
(115 VAC)
GEARBOX
MOTOR 1 MOTOR 2
CMD CMD
BRAKE
BRAKE
BRAKE
AC BUS 1
(115 VAC) CH 1 CH 2
MCU
MOTOR CONTROL MOTOR CONTROL
SSCU 1
PSEU
CHA
SFECU 1
ADC
1 & 2
FCC 1
FCP
AHC 1
IOC
MDC LA
DFDR DCUs
SSCU 2
DCUs DFDR
PSEU
CHB
SFECU 2
ADC
1 & 2
FCC
FCP
AHC 2
IOC
LB
MDC
STAB TRIM SWITCHES
STAB TRIM DISCONNECT SWITCH
STAB TRIM SWITCHES
STAB TRIM DISCONNECT SWITCH
CH 1 CH 2 INOP
ENGAGE ENGAGE /
DISENGAGE
STAB TRIM MACH TRIM
Vol. 1 11--50--3
FLIGHT CONTROLS
Horizontal Stabilizer Trim REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Stabilizer/ Mach Trim Control Panel
Figure 11---50---2
ENGAGE/
CH 1 CH 2
ENGAGE
INOP
DISENGAGE
STAB TRIM MACH TRIM
MACH TRIM
Used to engage Mach trim
function.
INOP (amber) light
indicates that Mach trim
is inoperative.
Stabilizer/ Mach Trim Panel
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：
庞巴迪挑战者手册3(11)
