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A CONFIG STAB TRIM (W) CAS will be displayed if the stabilizer trim is not in normal takeoff range.
OFF
SEC
TRIM
RUD
L
PRI
R
STAB
CFO1002002_006
CAS
CKLST SKIP
FRMT TFC TR/WX ENTER SUMRY
A/ICE FUEL HYD
L R
ECS
ABV
ELEC FLT
COM1 NAV1 ATC1/TCAS ADF1 HF1 COM3 COM2
118.000 108.00 1799.5 118.000 118.000
118.000 108.00 STBY 190.0 2.0000 118.000 118.000
TX 2.0000 AM
25 25
1200
MFD CONTROL
FLIGHT CONTROLS
AILERON AILERON
ELEVATOR ELEVATOR
RUDDER
AUTO PLAN
SHLDR SIDE
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-02-03
SECONDARY FLIGHT CONTROLS (Cont)
HORIZONTAL STABILIZER TRIM
The stabilizer trim can be moved manually by control wheel trim switches or automatically via computer-controlled inputs
from the autopilot, spoilers, or flaps.
Manual trim rates differ, depending on which channel is engaged. When the primary channel is engaged, the trim rate is a
function of airspeed (mach). When the pitch trim secondary channel is engaged, the trim rate is a constant 0.2 degrees per
second.
The primary channel trim rate limit is 0.4 degrees/second at airspeeds up to Mach 0.4, decreasing linearly to 0.1 degrees/
second at Mach 0.8, and 0.1 degrees/second above Mach 0.8. If Mach data is not available, the trim rate limit defaults to
0.2 degrees/second.
CONFIGURATION TRIM
The aircraft has configuration trim, which is automatic trim movement when the flaps are extended or retracted and the
spoilers are extended or retracted. The aircraft has a nose down pitching moment with flap extension and nose up pitching
moment with spoiler extension. When these control surfaces are deflected, the horizontal stabilizer trim moves so as
to reduce the control column forces.
MACH TRIM
The Mach trim function makes allowances for the rearward shift of the aerodynamic center of pressure as the Mach number
increases. Without correction, this shift in the center of pressure decreases longitudinal stability.
The horizontal stabilizer trim control unit automatically adjusts the stabilizer as a function of the Mach number when the
autopilot is not engaged.
The Mach trim system, using Mach information from the air data computers (ADCs), varies the angle of incidence of the
stabilizer by commanding movement of the horizontal stabilizer actuator.
When Mach trim is active, increasing speed from a trimmed condition results in Mach trim inputting slight nose up trim,
increasing the aircraft’s natural speed stability. Likewise, decreasing aircraft speed from a trimmed condition results in
Mach trim inputting slight nose down trim.
The Mach trim system is continuously monitored and any fault detected is displayed on the EICAS display.
FLIGHT CONTROLS
Volume 2 Flight Crew Operating Manual Sep 13/2004
10-02-04 CSP 100-6 REV 1
SECONDARY FLIGHT CONTROLS (Cont)
AILERON TRIM SCHEMATIC
CFO1001002_011
NOSE DOWN
NOSE
UP
RWD
LWD
MIC ID ID MIC
TRIM ACTUATOR
FGCS
ROLL
COMMANDS
ROLL
COMMANDS
M
TRIM MOTOR M
CABLE INPUT
MECHANICAL INPUT
ELECTRICAL INPUT
LEGEND
CONFIG AILERON TRIM
CONFIGURATION
CONFIGURATION
WARNING
LEFT AILERON
(POSITION TO EICAS
FLIGHT CONTROLS PAGE)
ROLL DISCONNECT SWITCH
TRIM POSITION
TO EICAS
MULTI-FUNCTION
SPOILERS
TRIM
STAB AIL
LWD RWD
RUD
L R
NU
ND
6.6
FLAPS 0 GEAR
DN
BALANCE
TAB
)
DN DN
FLIGHT CONTROLS
Sep 13/2004 Flight Crew Operating Manual Volume 2
REV 1 CSP 100-6 10-02-05
SECONDARY FLIGHT CONTROLS (Cont)
HORIZONTAL STABILIZER TRIM SCHEMATIC
FO1001002_002 STAB
MIC ID
HSTECU
PRIMARY CHANNEL
COMMAND
MONITOR
MCU
CHANNEL 1
CHANNEL 2
SECONDARY
CHANNEL
RIGHT ESS
28 VDC
HIGH
POWER
BREAKER
LEFT MAIN
28 VDC
HIGH
POWER
BREAKER
SECONDARY
ENGAGE
RELAY
PRIMARY
ENGAGE
RELAY
RIGHT
ESS
28 VDC
LEFT
MAIN
28 VDC
COPILOT
MASTER
DISC RELAY
PILOT
MASTER
DISC RELAY
BRAKE 3
BRAKE 4
MOTOR
COMM
LVDT 2
LVDT 1
BRAKE 1
BRAKE 2
MOTOR
COMM
HSTA GEARBOX
NO BACK
HORZONTAL
TO STABILIZER
FGP
HORIZONTAL
STABILIZER
TRIM
ACTUATOR
STALL
PUSHER
OFF
PRI
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Bombardier_Challenger_Global_00-Flight_Controls(6)
