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P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
2-2 For Training Purposes Only
Sept 04
Through the flight computer, the AFCS will provide flight guidance outputs for
display on the Primary Flight Display (PFD). The flight director functions are as
follows:
• Mode selection
• Computation of guidance
• Data management and source selection
• Command bar output for display
If an autopilot or flight director mode is armed or active, the annunciator on the
appropriate button is illuminated.
CRS 1 FMS SPD MAN CRS 2
PUSH DCT PUSH DCT
HDG ALT
DN
UP
P
I
T
C
H
Honeywell
FD AP FD
CPL
YD
FLC NAV HDG BANK VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
GX_02_001
Indicates FLC mode
is active
Indicates HDG mode
is active
(The PFD control panels are located on each
side of the guidance panel)
Indicates NAV mode
is armed or active.
MINIMUMS
RAD BARO IN Hpa
NAV SRC BARO SET
BRG V/L FMS BRG
HSI
Honeywell PUSH STD
For Training Purposes Only
Sept 04
2-3
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
AFCS SCHEMATIC
CRS 1 FMS SPD MAN CRS 2
PUSH DCT PUSH DCT
HDG ALT
DN
UP
P
I
T
C
H
Honeywell
FD AP FD
CPL
YD
FLC NAV HDG BANK VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
MAX
THRUST
IDLE
REV
MAX REV
ENG
RUN
OFF OFF
L R
RUDDER
CONTROL SURFACE POSITION
CH 1 CH 2
TRIM SYSTEM
IAC 1 IAC 2
FGC 2
DUAL
ELEVATOR
SERVO
DUAL
AILERON
SERVO
YAW
DAMPER
ACTUATOR 1
YAW
DAMPER
ACTUATOR 2
FGC 1
DAU
MADC
FWC
IRS
EFIS
FMS
TOGA
BUTTONS
TRIM SWITCHES
CONTROL WHEEL
GUIDANCE PANEL
AP DISC
BUTTON
TOUCH
CONTROL
STEERING
(TCS)
GX_02_002
ASCB
AILERON ELEVATOR
NOSE
DN
NOSE UP
DISC
MASTER
TCS
IC
R/T
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
2-4 For Training Purposes Only
Sept 04
Manual selection of the master AFCS channel is accomplished via the pop-up menu
on either multifunctional display (MFD), in conjunction with the MFD control panel
located on the pedestal.
AUTOPILOT
The autopilot (AP) system automatically controls the airplane in pitch and roll attitude
via servo control of ailerons, elevator and aircraft pitch trim system. The two autopilot
computer channels operate in a high priority/low priority (active/standby)
configuration.
Assignment of priority channel is alternated on power-up. The high priority channel
provides control functions, while the low priority channel operates in a back-up 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 via the Avionics Standard Communications Bus (ASCB), for
use in the FGC:
MENU
GX_02_003
FGC 1 2
FGC 2 1
1
3
2
MFD CONTROL PANEL
MFD
Honeywell
WX
AUTOTHROTTLE
SYSTEM 2/2
1 2
SAT
GSPD
-56
TAT
TAS
-40
234
345
LX
HDG
315
ETE0+02
2 . 5
DVT
NM
000 FMS1
N
5 5
3
6
33
30
- 02
- 02
+ 12
- 04
KLAX
KPHX
TOC
SRP
LUF
DVT + 09
T5.0
FGC 1 2
TCAS MENU
EMER
TERR
MAP
PLAN
NAV
APT
NORM ABN
SKP
RCL
PAG
ENT
ENT
For Training Purposes Only
Sept 04
2-5
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
Air data source identification Lateral and vertical path deviations
Attitude source identification Distance to station
NAV source identification Tuned-to-NAV and To/From status
Course error Inner, middle and outer marker data
Heading error Radio altitude and flags
The source of other guidance information is selected via the source identifier received
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Bombardier global AUTOMATIC FLIGHT CONTROL SYSTEM(2)
