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L-GPBUS-5 (HS)
HSTECU-1 (HS)
NDRM TRIM AVAILABLE
AP TRIM ENABLE
L-AHC-1 (HS) L-ADC-1
L-ADC-6
L-GPBUS-5 (HS)
L-AHC-4
A-SPC-2
A-SPC-1
L-IOC-3
L-FGC-3
R-AHC-4
HSTECU-2 (HS) R-ADC-6
R-GPBUS-5 (HS)
STAB 1 POSITION
STAB 2 POSITION
R-GPBUS-5 (HS)
B-SPC-2
STALL WARN DISCONNECT
B-SPC-1
FGP-2 (RS-422)
R-FGC-2 (RS-422)
STALL WARN
DISCON
AP DISC SW A
TO/GA SW A
AP/FD SYNC SW A
AP DISC SW B
TO/GA SW B
AP/FD SYNC SW B
A-SPC-2
A-SPC-1
L-ADC-6 FCU-1
FGP-1 (RS-422)
L-FGC-2 (RS-422)
R-IOC-3
R-FCC-1
TO DCU
TO DCU
ICC
AP TRIM ENABLE
NORM TRIM AVAILABLE
R-ADC-1
R-AHC-1 (HS)
1 2 1 2
AUTOMATIC FLIGHT CONTROL SYSTEM
May 06/2005 Flight Crew Operating Manual Volume 2
REV 2 CSP 100-6 04-01-23
AUTOPILOT (Cont)
OUT-OF-TRIM INDICATIONS
The FGC continuously monitors all three axes of the autopilot when it is engaged. If a control surface is detected to be
significantly out of trim, a CAS caution message is displayed. The amber CAS message identifies whether it is the aileron
or elevator that is affected and in which direction the control surface is out of trim.
MASTER DISCONNECT SWITCH
The master disconnect switches are installed on the outboard horn of each control wheel. When the switches are pressed
with the autopilot engaged, the PFD red flashing AP indication appears and the autopilot audio warning sounds for approximately
1 1/2 seconds.
If a system fault causes the autopilot to disengage, pressing either master disconnect switches will cancel the red flashing
AP message and silence the aural warning.
AUTOPILOT AND YAW DAMPER DISCONNECT LEVER
Pressing the AP/YD DISC lever down disengages the autopilot and yaw damper simultaneously. With the autopilot engaged
and the disconnect switch pressed down, a flashing red AP message appears on the PFD and the autopilot audio
warning sounds for approximately 1 1/2 seconds.
A red line is visible on the top edge of the switch when the switch has been moved to the disengage position.
AUTOPILOT DISENGAGEMENT
When the autopilot is manually disengaged, the AP symbols on each PFD flash red and an aural warning sounds
for approximately 1 1/2 seconds.
The autopilot can be manually disengaged by:
- Pressing either master disconnect push button on the control wheels
- Activating the stab trim switches on the control wheels
- Pressing the AP push button on the FGP
- Selecting the AP/YD DISC on the FGP
- Pressing either TOGA switch
- Pressing the YD push button
If a system fault causes the autopilot to automatically disengage, the pilot must press the control wheel master disconnect
switch to cancel the red flashing AP message and silence the aural warning. If the autopilot warning sounds because the
TOGA switch is selected, a second press of the TOGA switch clears the warnings.
The autopilot automatically disengages upon stall warning.
AUTOPILOT TAKEOFF CONFIGURATION WARNING
If a takeoff is attempted with the autopilot on, the takeoff configuration warning system presents an EICAS warning message
and sounds an voice alert. The warning sounds when the thrust lever is advanced for takeoff.
YAW DAMPER
DESCRIPTION
The yaw damper provides automatic turn coordination and yaw oscillation damping. The yaw damper actuator is a mechanically
limited linear actuator.
Yaw damping improves the aircraft’s stability by damping out oscillations in yaw. These oscillations, if not corrected leads
to the phenomenon called dutch roll.
The turn coordination function helps the aircraft into and out of turns. The flight guidance computers (FGCs) provide signals
to operate the yaw damper actuators.
The AP/YD DISC switch, YD switch and control wheel disconnect switches will disengage the yaw damper. When a yaw
damper channel fails or disconnects, the amber YAW DAMPER FAIL CAS message is displayed.
AUTOMATIC FLIGHT CONTROL SYSTEM
Volume 2 Flight Crew Operating Manual Feb 22/2006
04-01-24 CSP 100-6 REV 5
CONTROLS AND INDICATIONS
DESCRIPTION
The flight guidance panel (FGP) is the mode selection panel that selects and controls the flight director and autopilot functions.
The PFD presents the FGP modes to the pilot through the use of flight mode annunciations and command bars. Autopilot
engagement and system malfunctions are presented on the PFD.
An autopilot synchronization switch on the control wheel allows the FD command bars to be synchronized with the actual
aircraft vertical and lateral reference when the autopilot is engaged. The AP/YD DISC switch disconnects the autopilot.
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