BOMBARDIER CHALLENGER 604 Setup guide

Table of Contents
For Training Purposes Only
Sept 04 4-i
AUTOMATIC FLIGHT CONTROL SYSTEM
PILOT TRAINING GUIDE
Introduction.........................................................................................................................4-1
Flight Control Computers (FCCs) .......................................................................................4-2
Description....................................................................................................................4-2
Operation ......................................................................................................................4-2
Autopilot..............................................................................................................................4-4
Description....................................................................................................................4-4
Operation ......................................................................................................................4-4
Autopilot Engagement.............................................................................................4-4
Autopilot Servomotors.............................................................................................4-6
Autopilot Pitch Trim.................................................................................................4-6
Autopilot Mistrim Conditions....................................................................................4-6
Turbulence (TURB) Mode.............................................................................................4-8
Autopilot Disengagement........................................................................................4-9
Yaw Damper System........................................................................................................4-10
Description..................................................................................................................4-10
Components and Operation........................................................................................4-10
Yaw Damper Engagement....................................................................................4-10
Yaw Damper Disengagement...............................................................................4-10
Flight Directors (FDs)........................................................................................................4-12
Description..................................................................................................................4-12
Operation ....................................................................................................................4-12
Flight Director Selection........................................................................................4-12
Flight Director Command Bars..............................................................................4-15
Flight Control Panel (FCP)....................................................................................4-16
FD Failure .............................................................................................................4-19
Flight Director Lateral Modes......................................................................................4-20
Roll Mode..............................................................................................................4-21
Heading Select Mode............................................................................................4-22
Half Bank Mode.....................................................................................................4-23
NAV Mode.............................................................................................................4-24
Approach Mode.....................................................................................................4-28
Localizer Back Course Mode................................................................................4-32
Lateral Takeoff ......................................................................................................4-33
Lateral Go-Around Mode.......................................................................................4-34
Flight Director Vertical Modes.....................................................................................4-35
Pitch Mode............................................................................................................4-36
Altitude Preselect Mode........................................................................................4-38
Altitude Alert System.............................................................................................4-40
Altitude Hold Mode................................................................................................4-42
Vertical Speed Mode.............................................................................................4-43

AUTOMATIC FLIGHT CONTROL SYSTEM
4-ii For Training Purposes Only
Sept 04
PILOT TRAINING GUIDE
Flight Level Change Mode....................................................................................4-44
Vertical Takeoff Mode...........................................................................................4-46
Vertical Go-Around Mode......................................................................................4-47
Glideslope Mode...................................................................................................4-48
Vertical Navigation................................................................................................4-49
Controls and Indicators.....................................................................................................4-50
General.......................................................................................................................4-50
Reversionary/Inhibit Panel....................................................................................4-50
Flight Control Panel (FCP) - Autopilot/Flight Director Modes................................4-51
Flight Control Panel (FCP) - Lateral Modes..........................................................4-52
Flight Control Panel (FCP) - Vertical Modes.........................................................4-53
AFCS Cockpit Switches........................................................................................4-54
PFD Annunciations ...............................................................................................4-55
PFD Messages......................................................................................................4-56
EICAS Messages........................................................................................................4-59

List of Figures
Graphic Title Figure
For Training Purposes Only
Sept 04 4-iii
AUTOMATIC FLIGHT CONTROL SYSTEM
PILOT TRAINING GUIDE
Automatic Flight Control System Configuration..................................................................4-1
AP Engage Button ..............................................................................................................4-2
Autopilot Engagement.........................................................................................................4-3
Autopilot Elevator and Aileron Mistrim Annunciation ..........................................................4-4
Turbulence Mode Button.....................................................................................................4-5
Yaw Damper Panel.............................................................................................................4-6
Yaw Damper Disengage Annunciation...............................................................................4-7
Flight Director Couple Arrow...............................................................................................4-8
AP/FD Engagement............................................................................................................4-9
AP/FD Transfer.................................................................................................................4-10
Flight Director Command Bar ...........................................................................................4-11
Flight Mode Annunciator (FMA)........................................................................................4-12
Flight Control Panel ..........................................................................................................4-13
AP/FD Synchronization.....................................................................................................4-14
FD Failure Indications.......................................................................................................4-15
Roll Mode..........................................................................................................................4-16
Heading Mode...................................................................................................................4-17
Half Bank Mode ................................................................................................................4-18
Display Control Panel .......................................................................................................4-19
VOR Navigation Mode......................................................................................................4-20
LOC Navigation Mode.......................................................................................................4-21
FMS Navigation Mode ......................................................................................................4-22
ILS Approach Mode..........................................................................................................4-23
FMS Approach Mode........................................................................................................4-24
Back Course Mode ...........................................................................................................4-25
Lateral Takeoff Mode........................................................................................................4-26
Lateral Go-Around Mode ..................................................................................................4-27
Pitch Mode........................................................................................................................4-28
Altitude Capture Sequence...............................................................................................4-29
Altitude Alert Annunciations..............................................................................................4-30
Altitude Hold Mode............................................................................................................4-31
Vertical Speed Mode.........................................................................................................4-32
Flight Level Change Mode................................................................................................4-33
FLC Overspeed Protection Mode .....................................................................................4-34

AUTOMATIC FLIGHT CONTROL SYSTEM
4-iv For Training Purposes Only
Sept 04
PILOT TRAINING GUIDE
Vertical Takeoff Mode.......................................................................................................4-35
Vertical Go-Around Mode .................................................................................................4-36
Reversionary/Inhibit Panel................................................................................................4-37
Flight Control Panel (FCP) - Autopilot/Flight Director Modes ...........................................4-38
Flight Control Panel (FCP) - Flight Director Lateral Modes ..............................................4-39
Flight Control Panel (FCP) - Flight Director Vertical Modes .............................................4-40
Cockpit Switches - Autopilot / Flight Director Function.....................................................4-41
PFD Annunciations...........................................................................................................4-42

AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03 4-1
PILOT TRAINING GUIDE
CHAPTER 4: AUTOMATIC FLIGHT CONTROL SYSTEM
Introduction
The Automatic Flight Control System (AFCS) on the Challenger 604 is a subsystem of
the Collins Pro Line 4 Avionics System. It is a fully integrated flight control system
that includes dual two-axis autopilots, each with integrated dual flight directors, dual
yaw dampers, and automatic pitch trim control. The flight control system consists
primarily of the following equipment:
• four Flight Control Computers
• one Flight Control Panel
• aileron and elevator servos
• two linear actuators for the rudder (yaw damping)
The Flight Control Computers (FCCs) receive pilot input from the selections made on
the Flight Control Panel (FCP). Electronic signals from the FCCs send guidance
commands to the aileron and elevator servos, the yaw damper linear actuators, and the
Horizontal Stabilizer Trim Control Unit (HSTCU).
When the autopilot is engaged, the AFCS maneuvers the aircraft while the pilot
monitors the flight path by observing the flight guidance information presented on the
EFIS Primary Flight Display (PFD).
When the autopilot is disengaged, the pilot manually flies the aircraft in response to
guidance provided by the Flight Director (FD) command bars on the PFD.

AUTOMATIC FLIGHT CONTROL SYSTEM
4-2 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
Flight Control Computers (FCCs)
Description
The Integrated Avionics Processor System (IAPS) contains four Flight Control
Computers (FCCs) which provide the flight director, autopilot and yaw damper
functions.
The FCCs process information from the Inertial Reference System (IRS), Air Data
Computers (ADCs), navigational (NAV) systems and various cockpit control panels to
calculate flight path and flight guidance parameters.
Operation
The FCCs provide output data to the following:
• 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
PILOT TRAINING GUIDE
Automatic Flight Control System Configuration
Figure 4-1
FLC
SPEED
NAV HDG APPR
1/2 BANK HDG B/C
ALT
ALT
CRS1 CRS2
FD FDVS
VNAV
DOWN
UP
XFR
TURB AP DISC
AP ENG
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IAPS
LEFT
CHANNEL
RIGHT
CHANNEL
2A
2B
1A
1B
11
22
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
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1
1
M.187
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1.0
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10000 1.0
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MSG1
MSG2
VOR1
A
A
HDG
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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
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29.92 IN
ENGAGE
YAW DAMPER
DISC
YD 1 YD 2
INHIBIT PUSH
1-RTU-2 FMS TUNE
12
AFCS
SEL
STBY
12
ATC
SEL
FMS
TUNE
INHIB
RTU 1
INHIB
RTU 2
INHIB
12
12

AUTOMATIC FLIGHT CONTROL SYSTEM
4-4 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
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
FD
XFR
TURB AP DISC
AP ENG
P
U
S
H
C
A
N
C
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P604_04_029
AP Engage Button

AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03 4-5
PILOT TRAINING GUIDE
Autopilot Engagement Criteria
The autopilot can be engaged provided the following conditions exist:
• at least one yaw damper is engaged (normally, both YDs are engaged)
• AP DISC switch-bar on the FCP is in the normal position
• no faults detected in the active Flight Control Computers (FCCs)
• no significant instability exists, including:
- adverse pitch / roll / yaw rates
- G-loads exceeding predetermined values
- adverse pitch / roll attitudes exceeding predetermined values
Autopilot Engagement
Figure 4-3
7000
10000 1.0
10
10
MDA
A
A
HDG
A
DR ALTS
A
AP
2500M 4
4
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1
1
M.454
280
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260
10
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000
29.92 IN
P604_04_033
AP Engage
Annunciation

AUTOMATIC FLIGHT CONTROL SYSTEM
4-6 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
Autopilot Servomotors
When the autopilot is engaged, the active pair of FCCs direct roll and pitch commands
to the aileron and elevator servos, and stabilizer trim commands through the HSTCU.
When a change in roll or pitch is required, the FCCs signal the aileron servo or
elevator servo to bias the control cables and displace the associated control surface.
The aileron servo is located on the control cable run for the right aileron. Since the left
and right ailerons are normally interconnected, the servo is capable of moving both
ailerons.
The elevator servo is located in the left elevator control cable run. The servo moves
both elevators when the elevators are interconnected.
Autopilot Pitch Trim
Automatic pitch trim is enabled whenever the autopilot is engaged. The autopilot
issues commands to the Horizontal Stabilizer Trim Control Unit (HSTCU) to remove
continuous loads from the elevator servomotor.
Protracted trim operation causes the trim clacker aural to sound. Autopilot pitch trim
failure is annunciated by an AP PITCH TRIM caution EICAS message.
Autopilot Mistrim Conditions
The AFCS continuously monitors both axes of the autopilot when it is engaged. Any
significant elevator or aileron mistrim condition causes an amber E (elevator) or A
(aileron) to be displayed on the upper left of the PFD. In conjunction with the PFD
annunciations, the EICAS will display an AP TRIM IS NU or AP TRIM IS ND
caution EICAS message (autopilot is counteracting a significant nose-up or nose-
down mistrim) for a significant elevator mistrim condition, or an AP TRIM IS LWD or
AP TRIM IS RWD caution EICAS message (indicating left or right wing down) for an
aileron mistrim.
When the autopilot is disengaged during a mistrim condition,
expect an abrupt change in control force.
NOTE

AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
Sept 04 4-7
PILOT TRAINING GUIDE
Autopilot Elevator and Aileron Mistrim Annunciation
Figure 4-4
Autopilot monitors aileron mistrim conditions but cannot change
aileron trim settings
NOTE
7 000
20 000 1.0
10
10
MDA
A
A
HDG
A
DR ALT
A
AP
2500M 4
4
2
2
1
1
M.454
280
240
220
250
260
10
100
200
900
800
000
29.92 IN
P604_04_062
EA

AUTOMATIC FLIGHT CONTROL SYSTEM
4-8 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
Turbulence (TURB) Mode
Turbulence mode is available when the autopilot is engaged and can be selected by
pressing the TURB button on the FCP. The green status indicator lights on each side of
the TURB button illuminate when turbulence mode is selected. There is no indication
of TURB mode selection on the PFDs.
When turbulence mode is active, the FCC reduces autopilot gains for turbulent flight
conditions. This prevents the FCC from instantaneously responding to pitch and roll
changes brought about by flight through turbulent air.
TURB mode is cleared by any one of the following:
• pushing the TURB button again
• on-side LOC capture, or
• autopilot disengagement
Turbulence Mode Button
Figure 4-5
The maximum IAS or MACH for turbulent air penetration is 280
KIAS or 0.75 MACH.
NOTE
ALT
ALT CRS2
FD
XFR
TURB AP DISC
AP ENG
P
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ALT
ALT CRS2
FD
XFR
TURB AP DISC
AP ENG
P
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A
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P604_04_030
Turbulence Mode Button

AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03 4-9
PILOT TRAINING GUIDE
Autopilot Disengagement
Manual (Pilot Action) Disengagement
The autopilot is normally disengaged by pressing the red autopilot/stick pusher (AP/
SP DISC) disconnect button on the outboard horn of either control wheel.
The autopilot may also be manually disengaged by any one of the following actions:
• lowering the AP DISC switch-bar on the FCP
• pushing the AP ENG button on the FCP
• selecting Takeoff or Go-Around (TOGA) button
• operating either stabilizer trim switch
• pressing the Yaw Damper DISC switch, or
• switching the AFCS SEL selector to the other AFCS (1 or 2)
Whenever the autopilot is manually disengaged (by pilot action) the PFD green
engage annunciation turns red and flashes for 5 seconds, the green status indicator
lights beside the AP button extinguish, and the autopilot disconnect (cavalry charge)
aural sounds. The autopilot disconnect warning will automatically cancel, after a few
repetitions of the cavalry charge.
Monitored Disengagement
The FCCs continually monitor aircraft sensors, servo data, the automatic pitch trim
system and internal parameters for faults. The autopilot will automatically disengage if
any of the following conditions occur:
• internal monitors detect a failure in any axis
• any power source to the FCCs is lost
• loss of either inertial reference system (IRS) system input
• dual yaw damper failure
• aircraft is at an excessive attitude (pitch angle beyond +25° or -17°, roll angle
beyond ± 45°), or
• either stick shaker activates
A monitored disengagement is annunciated in the same manner as a manual
disengagement with the exception that the flashing on the PFD and the aural warning
will continue until canceled by the flight crew. Pressing either pilot’s AP/SP DISC
switch or TOGA button, or reengaging the autopilot will cancel the flashing on the
PFD and the aural warning.

AUTOMATIC FLIGHT CONTROL SYSTEM
4-10 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
Yaw Damper System
Description
Each yaw damper is a dual-channel, fully independent yaw damper system providing
yaw damping, turn entry, steady-state turn coordination, and turn exit for the full flight
envelope.
The yaw dampers operate independently of the autopilot.
The yaw damper will not compensate for a sustained adverse
yaw created by an engine power asymmetry or improper rudder
inputs.
Components and Operation
Yaw Damper Engagement
The yaw dampers are engaged by pushing both YD 1 and YD 2 switch/lights on the
YAW DAMPER Panel. Selective engagement of the switch/lights activates the
corresponding yaw damper channel. Yaw damper engagement is indicated by the
absence of yaw damper (status and caution) EICAS messages and PFD indications.
Normally, both yaw dampers are engaged for all phases of flight. One yaw damper
channel will provide adequate yaw damping and turn coordination during flight.
Yaw Damper Disengagement
The DISC button on the YAW DAMPER Panel disengages both yaw damper channels
when pressed. When both yaw damper channels are disengaged, an amber YD
annunciation is displayed on the upper left side of the PFDs, and a YAW DAMPER
caution EICAS message appears.
A single disengaged (or inoperative) yaw damper channel is indicated by a YD 1(2)
INOP status EICAS message.
NOTE

AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
Jan 04 4-11
PILOT TRAINING GUIDE
Yaw Damper Panel
Figure 4-6
Yaw Damper Disengage Annunciation
Figure 4-7
ENGAGE
YAW DAMPER
DISC
YD 1 YD 2
P604_04_032
7 000
5 000 1.0
10
10
MDA
A
A
HDG
A
DR ALTS
A
YD
2500M 4
4
2
2
1
1
200
29.92 IN
P604_04_034
0FT
60
40
VT 150
V2 133
VR121
V1 113
0
200
300
000
100
2
1
100

AUTOMATIC FLIGHT CONTROL SYSTEM
4-12 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
Flight Directors (FDs)
Description
The flight directors (FDs) are the visual representation of the commands generated by
the flight control computers.
The flight directors provide pitch and roll guidance by means of inverted V-shaped
command bars on the attitude director indicator (ADI) of the PFD. The pilot can
manually fly the aircraft by following the command bar guidance cues. When
autopilot is engaged, the FCCs issue steering commands to the aileron and elevator
servos according to the flight director guidance instructions.
Operation
Flight Director Selection
There are two independent flight directors for each AFCS channel (AFCS 1 and
AFCS 2). FCC 1 of AFCS 1 and 2 is designated as FD 1 and FCC 2 of AFCS 1 and 2
is designated as FD 2.
In most flight director modes, only one FD provides guidance commands and flight
mode annunciations to both PFDs. The other FD operates as a standby. This ensures
that all FD mode annunciations and command cues displayed on the pilot’s and
copilot’s PFD remain synchronized.
At power-up, both flight directors are off. FD 1 defaults as the active flight director,
following selection of any lateral or vertical FD mode. When FD 1 is active and the
autopilot is disengaged, a white left-pointing arrow is displayed on the upper left side
of both PFDs. The copilot’s PFD also displays a green FD 1 annunciation below the
left arrow to indicate that copilot’s FD commands are being supplied by FD 1 (Figure
4-8).
Flight Director Couple Arrow
Figure 4-8
P604_04_035
PILOT PFD COPILOT PFD
7000
10000
10
10
MDA
A
A
HDG
A
DR ALTS
A
AP
2500M
M.452
280
240
220
250
260
29.92 IN
7000
10000
10
10
MDA
A
A
HDG
A
DR ALTS
A
AP
FD1
2500M
M.452
280
240
220
250
260
29.92 IN
10
100
200
900
800
000 10
100
200
900
800
000

AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03 4-13
PILOT TRAINING GUIDE
When the autopilot is engaged with FD 1 active, a green AP annunciation is displayed
on both PFDs over the left-pointing FD arrow (Figure 4-9).
When the pilot has control of the aircraft, FD 1 is normally selected and all flight
guidance commands are derived using the pilot’s side systems (ADC 1, IRS 1, pilot’s
navigation source selection).
AP/FD Engagement
Figure 4-9
AP/FD Transfer (XFR) Mode
Pressing the XFR (transfer) button on the Flight Control Panel allows FD 2 to become
the active flight director. When FD 2 is active and the autopilot is disengaged, a white
right-pointing arrow is displayed on the upper left side of both PFDs. The pilot’s PFD
will also display a green FD2 annunciation below the arrow to indicate that the pilot’s
FD commands are being supplied by FD 2. In addition, the green status indicator lights
beside the XFR button illuminate to indicate that transfer mode is active.
When the autopilot is engaged and FD 2 is active, a green AP annunciation is
displayed on both PFDs over the right-pointing FD arrow (Figure 4-10).
When the copilot has control of the aircraft, XFR mode is normally selected. When
FD 2 is active, the flight guidance commands are derived using the copilot’s side
systems (ADC 2, IRS 2, copilot’s navigation source selection).
P604
_
04
_
058
70007000
1000010000
1010
1010
MDAMDA
AA
AA
HDGHDG
AA
DRDR ALTSALTS
AA
AP
FD1
AP
2500M2500M
M.452M.452
280280
240240
220220
250250
260260
29.92 IN29.92 IN
PILOT PFD COPILOT PFD
10
100
200
900
800
000 10
100
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900
800
000

AUTOMATIC FLIGHT CONTROL SYSTEM
4-14 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
AP/FD Transfer
Figure 4-10
Dual Independent FD Operation
Both FDs become active and supply independent flight guidance commands to their
associated PFD (dual independent operation) when in the following flight director
modes:
• takeoff mode
• go-around mode
• approach (APPR) mode
When operating independently, the coupled side channel supplies steering commands
to the autopilot, and dual independent flight guidance computations are supplied to the
flight directors (“split” flight directors). The pilot’s channel supplies flight guidance
commands to the pilot’s flight director, and the copilot’s channel supplies flight
guidance commands to the copilot’s flight director.
In the above modes, the FD1 and FD2 annunciations are not displayed on the PFDs.
ALT
ALT CRS2
FD
XFR
TURB AP DISC
AP ENG
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29.92 IN29.92 IN
PILOT PFD COPILOT PFD
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AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03 4-15
PILOT TRAINING GUIDE
Flight Director Command Bars
The flight directors provide integrated pitch and roll control guidance by means of
magenta inverted V-shaped command bars on the ADI of the PFD.
The command bars are always in view when the flight director is being used or when
the autopilot is engaged. The command bars are out of view when the flight director is
turned off or flagged, or when the aircraft’s attitude is extreme.
Flight Director Command Bar
Figure 4-11
Flight Mode Annunciator (FMA)
Lateral and vertical FD modes are presented in the Flight Mode Annunciator (FMA)
displayed on each PFD. The FMA is located above the PFD ADI display.
The FMA is divided into two fields separated by vertical cyan lines. The left field
displays the active/captured and armed lateral flight director modes. The right field
displays the active/captured and armed vertical FD modes.
FMA Active/Captured Mode Display
The active/captured lateral and vertical modes are displayed in steady green text.
Lateral and vertical modes that are capturing are displayed in flashing green text for 5
seconds, then change to steady green text.
If the active lateral or vertical mode becomes invalid (sensor data), the flight control
system removes the invalid steering commands from the affected flight director. A red
horizontal line is superimposed over the affected active mode annunciation.
7 000
5 000 1.0
10
10
MDA
A
A
TO
A
DR TO
ALTS
YD
2500M 4
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29.92 IN
P604_04_037
0FT
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40
VT 158
V2 139
VR124
V1 120
0
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FD Command Bar

AUTOMATIC FLIGHT CONTROL SYSTEM
4-16 For Training Purposes Only
May 03
PILOT TRAINING GUIDE
FMA Armed Mode Display
The armed lateral and vertical modes are normally displayed in steady white text in the
lower portion of the lateral or vertical field. Up to two vertical modes may be armed
simultaneously.
Flight Mode Annunciator (FMA)
Figure 4-12
Flight Control Panel (FCP)
The Flight Control Panel (FCP) is the mode selection panel that controls the flight
director and autopilot functions. The FCP is located on the glareshield and is
accessible to both pilots.
Flight Control Panel
Figure 4-13
7000
12000 1.0
10
20
10
MDA
A A
A
HDG
LNV1
DR VS
ALTS
AP
2500M 4
4
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M.454
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29.92 IN
P604_04_038
Lateral Active/Captured Field Vertical Active/Captured Field
Lateral Arm Field Vertical Arm Field
FLC
SPEED
NAV HDG APPR
1/2 BANK HDG B/C
ALT
ALT
CRS1 CRS2
FD FDVS
VNAV
DOWN
UP
XFR
TURB AP DISC
AP ENG
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