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a high priority/low priority (active/standby) configuration.
Assignment of priority channel is alternated on powerup.
The high priority channel provides control
functions, while the low priority channel operates in a backup
mode. The autopilot/yaw damper
actuators and pitch trim interface can only be driven by the priority channel.
In the event of a channel failure, the priority will automatically switch to the other channel.
Each FGC shall determine which symbol generator is driving the selected PFD, as selected on the
reversion control panel located on the pedestal. The following guidance data is received from the
appropriate symbol generator, via the Avionics Standard Communications Bus (ASCB), for use in the
FGC:
Air data source identification
Attitude source identification
NAV source identification
Course error
Heading error
Lateral and vertical path deviations
Distance to station
TunedtoNAV
and To/From status
Inner, Middle and Outer marker data
Radio Altitude
The source of other guidance information is selected via the source identifier received from selected
PFD symbol generator. The data received includes:
· IRS:
Roll Angle
Pitch Angle
Roll rate
Pitch rate
Yaw rate
Longitudinal acceleration
Lateral acceleration
Normal acceleration
Ground speed
True track angle
Flight path angle
Magnetic heading
True heading
Inertial vertical speed
· ADC:
Barocorrected
altitude
Pressure altitude
Vertical speed
Mach
Calibrated airspeed (CAS)
True airspeed (TAS)
Dynamic pressure
VMO
MMO
· FMS:
Lateral steering command
VNAV targets
VNAV submode
selection flags
· FWC:
Preselected
altitude
· Display Controller (DC):
Speed references
AUTOMATIC FLIGHT CONTROL SYSTEM
REV 41, Jul 08, 2004 Flight Crew Operating Manual
CSP 700−6
Volume 2
04−10−5
AUTOPILOT (CONT'D)
Manual selection of the master AFCS channel is accomplished via the popup
menu on either
multifunctional
display (MFD), in conjunction with the MFD control panel located on the pedestal.
GF0410_011
FGC 1 2
AUTOTHROTTLE 1 1+36
12.5
KDVT
−40
234
345
WX −56
T5 . 0
LX
GSPD
TAT
TAS
ETE
NM
SAT
SYSTEM 2/3
2
315
HDG FMS1
MFD Control Panel
MFD
FGC 1 2
FGC 1 2
1
2
3
YAW DAMPER
The yaw damper provides stability augmentation and turn coordination for the airplane yaw axis, via
2 linear actuators, in series with the rudder control system.
The yaw damper function will automatically engage on the ground, within 3 seconds after successful
completion of AFCS powerup
test. As with the autopilot, the yaw damper operates in an
active/standby configuration. When engaged, the active yaw damper will center both linear actuators.
The YD will not automatically engage once the airplane is airborne. The YD button, located on the
guidance panel may be used to reengage
the YD. When YD is engaged, the associated arrow on
the guidance panel is illuminated.
One valid yaw damper must be engaged for autopilot operation. Autopilot engagement without YD
will occur only when YD has failed in flight.
GF0410_012
CRS 2
PUSH DCT
For more information on yaw damper see Chapter 10, FLIGHT CONTROLS.
AUTOMATIC FLIGHT CONTROL SYSTEM
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
04−10−6
AUTOPILOT ENGAGE
The autopilot cannot be engaged without flight director guidance modes active. When no vertical or
lateral mode is active, the autopilot will engage the pitch and roll FD modes. Autopilot is engaged via
the AP button on the guidance panel.
GF0410_013
When selected, AP1 or AP2 will flash for
approximately 5 seconds, then steady
0.88 ROL AP1 PIT 300 00
PFD
20 20
220 23500
AP
YD
CPL
FD
AP1
AP2 CRS 2
PUSH DCT
CRS 2
PUSH DCT
210
Autopilot control authority:
· Roll rate is limited to ± 7.5°/sec.
· Pitch rate is ±0.3 gs in straight and level flight and maximum 0.7 gs pitch up in a turn.
The autopilot can engage throughout the range:
· Pitch = ± 50°
· Roll = ± 75°
· Once engaged, the autopilot will reduce the pitch and roll angles below control limits.
　
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