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• Flight Control Panel
• flight directors on the PFDs
• autopilot servomotors (elevator, aileron)
• yaw damper actuators
• pitch trim, Horizontal Stabilizer Trim Control Unit (HSTCU)
The AFCS SEL switch on the REVERSIONARY/INHIBIT panel selects the active
pair of FCCs (AFCS 1 or AFCS 2) that provide steering commands to the aileron and
elevator servos, and to the HSTCU.
Each AFCS uses the following FCCs:
• AFCS 1 - FCC 1A and 2A
• AFCS 2 - FCC 1B and 2B
Only one system of FCC pairs (AFCS 1 or AFCS 2) can be active at any time. The
inactive system is on standby and a manual selection is required to switch from AFCS
1 to AFCS 2, or vice versa.
Each FCC is capable of generating independent flight director commands.
AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03
4-3
P I LOT T R A I N I N G GU I D E
Automatic Flight Control System Configuration
Figure 4-1
FLC
SPEED
NAV HDG APPR
1/2 BANK
HDG
B/C
ALT
CRS1 ALT CRS2
FD VS FD
VNAV
DOWN
UP
XFR
TURB AP DISC
AP ENG
PUSH
DIRECTIAS/MACH
PUSH
SYNC
PUSH
CANCEL
PUS
H
DI
RECT
LEFT IAPS
CHANNEL
RIGHT
2A CHANNEL
2B
1A
1B
1 1
2 2
IRS 1
NAV 1
ADC 1
IRS 2
NAV 2
ADC 2
ELEVATOR
AILERON
PITCH
TRIM
MACH
TRIM
HSTCU
TRIM MOTOR
LEFT YAW
DAMPER
ACTUATOR
RIGHT YAW
DAMPER
ACTUATOR
SERVOS
YAW DAMPER PANEL
REVERSIONARY / INHIBIT PANEL
COPILOT
PRIMARY FLIGHT DISPLAY
PILOT
PRIMARY FLIGHT DISPLAY
FLIGHT CONTROL PANEL
P604_04_002
7000
10000 1.0
6
E
12
15
3
N
33
10
10
MDA
MSG1
MSG2
VOR1
A
A
HDG
A
DR ALTS
A
AP
FD1
FMS1
25
DTK 037
.6NM
YUL
ADF2
2500M 4
4
2
2
1
1
M.187
280
240
220
250
260
1.0
10
100
900
800
000
29.92 IN
7000
10000 1.0
6
E
12
15
3
N
33
10
10
MDA
MSG1
MSG2
VOR1
A
A
HDG
A
DR ALTS
A
AP
FD1
FMS2
25
DTK 037
.6NM
YUL
ADF2
2500M 4
4
2
2
1
1
M.188
280
240
220
250
260
1.0
10
100
900
800
000
29.92 IN
ENGAGE
YAW DAMPER
DISC
YD 1 YD 2
INHIBIT PUSH
1-RTU-2 FMS TUNE
1 2
AFCS
SEL
STBY
ATC
SEL
FMS
TUNE
INHIB
RTU 1
INHIB
RTU 2
INHIB
1 2
AUTOMATIC FLIGHT CONTROL SYSTEM
4-4 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Autopilot
Description
The Challenger 604 is equipped with a dual-channel, two-axis, fail-passive autopilot
system. The autopilot provides an interface between the AFCS and flight controls for
roll and pitch commands. Yaw dampers provide turn coordination and yaw damping.
The autopilot is integrated with the flight director to automatically control and direct
the flight path of the aircraft. When engaged, the autopilot controls the aircraft’s pitch
and roll axes in accordance with the coupled flight director commands.
Operation
Autopilot Engagement
The autopilot is engaged by pressing the AP ENG button located on the Flight Control
Panel (Figure 4-2). Autopilot engagement is indicated by the illumination of a green
indicator light along each side of the AP button. In addition, an AP Engage
Annunciation is provided on the upper left of the attitude display portion of each PFD
(Figure 4-3).
AP Engage Button
Figure 4-2
Once engaged, the autopilot will couple to and follow the guidance commands from
the selected flight director. If no FD modes are commanded prior to autopilot
engagement, the autopilot automatically activates and follows guidance from the basic
lateral (ROLL) and vertical (PTCH) modes.
When the autopilot is not engaged, a left- or right-pointing arrow, in white, indicates
which flight director the autopilot will couple to upon engagement.
ALT
ALT CRS2
XFR FD
TURB AP DISC
AP ENG
PUSH
CANCEL
PUSH
DIRECT
　
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本文鏈接地址：CL_604-AUTOMATIC_FLIGHT_CONTROL_SYSTEM(4)