BOMBARDIER Primus 2000XP Setup guide

For Training Purposes Only
Sept 04
2-i
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
Chapter 2: Automatic Flight Con trol System
TABLE OF CONTENTS
Page
Introduction ......................................................................................................................... 2-1
Description .......................................................................................................................... 2-1
Guidance Panel............................................................................................................. 2-1
AFCS Schematic........................................................................................................... 2-3
Autopilot ........................................................................................................................ 2-4
Autopilot Engagement................................................................................................... 2-6
Autopilot Disengagement .............................................................................................. 2-7
Yaw Damper ................................................................................................................. 2-8
PFD Annunciation ......................................................................................................... 2-9
Flight Director (FD)...................................................................................................... 2-10
Guidance Panel........................................................................................................... 2-12
Flight Director Modes .................................................................................................. 2-14
Lateral Modes ............................................................................................................. 2-15
Bearing (BRG) Source ................................................................................................ 2-27
VOR/LOC Nav Source ................................................................................................2-28
FMS Nav Source.........................................................................................................2-29
Vertical Modes ............................................................................................................ 2-30
Multi-Axis Modes......................................................................................................... 2-35
Takeoff (TO) Mode...................................................................................................... 2-38
Go Around (GA) Mode ................................................................................................2-38
Windshear Guidance (WSHR) Mode ..........................................................................2-39
Automatic Emergency Descent Mode................................................................... 2-41
Autopilot – Flight Director EICAS Messages...............................................................2-42
EMS Circuit Protection ................................................................................................ 2-44

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-ii For Training Purposes Only
Sept 04
PAGE INTENTIONALLY LEFT BLANK

For Training Purposes Only
Sept 04
2-1
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
INTRODUCTION
The Primus 2000XP includes an Automatic Flight Control System (AFCS) that
provides dual channel autopilots, dual yaw dampers, dual flight directors and
automatic pitch trim. The autopilot and yaw damper functions operate in an active
standby mode, with only one channel active at a time. All computations are performed
by two Flight Guidance Computers (FGC), located in the Integrated Avionics
Computer (IAC). The FGC receives inputs from the Electronic Flight Instrument
System (EFIS), the Air Data Computers (ADC), the Inertial Reference System (IRS),
the Flight Management System (FMS), the Fault Warning Computer (FWC) and the
Data Acquisition Unit (DAU).
DESCRIPTION
All computations are performed by the FGCs which are located in IAC1 and IAC2.
The FGCs receive inputs from the following through the Avionics Standard
Communications Bus:
• Flight Management System
• Electronic Flight Instrument System
• Inertial Reference System
• Fault Warning Computer
• Data Acquisition Units
• Micro Air Data Computers
GUIDANCE PANEL
The AFCS functions controlled by the FGC include:
• Flight director modes
• Pitch wheel references
• Engagement of the autopilot and yaw damper functions
• Selection of left or right Primary Flight Display (PFD) data to be used by FGC

PILOT TRAINING GUIDE
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.
SPD
MAN
FMS
CRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG 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
BARO Hpa RAD IN
BARO SETNAV SRC
BRG V/L BRGFMS
HSI
Honeywell PUSH STD

For Training Purposes Only
Sept 04
2-3
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
AFCS SCHEMATIC
SPD MAN
FMS
CRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
MAX
THRUST
IDLE
REV
MAX REV
ENG
RUN
OFF OFF
RL
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
N
O
S
E
D
N
N
O
S
E
U
P
D
I
S
C
M
A
S
T
E
R
T
C
S
IC
R/T

PILOT TRAINING GUIDE
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 12
FGC 21
1
3
2
MFD CONTROL PANEL
MFD
Honeywell
WX
AUTOTHROTTLE
SYSTEM 2/2
12
SAT
GSPD
-56
TAT
TAS
-40
234
345
LX
HDG
315
ETE0+02
2.5
DVT
NM
FMS1
000
N
55
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
PILOT TRAINING GUIDE
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
from selected PFD symbol generator. The data received includes:
IRS:
Roll angle Normal acceleration
Pitch angle Ground speed
Roll rate True track angle
Pitch rate Flight path angle
Yaw rate Magnetic heading
Longitudinal acceleration True heading
Lateral acceleration Inertial vertical speed
ADC:
Baro-corrected altitude True airspeed
Pressure altitude Dynamic pressure
Vertical speed VMO
Mach MMO
Calibrated airspeed
FMS:
Lateral steering command and flags VNAV submode selection flags
VNAV targets
FWC:
Preselected altitude
Display Controller (DC):
Speed references

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-6 For Training Purposes Only
Sept 04
AUTOPILOT ENGAGEMENT
Autopilot is engaged via the AP button on the guidance panel. When there are no
vertical or lateral mode active, the autopilot will engage in (PIT) and (ROL) FD
modes.
Autopilot control authority:
• Roll rate is limited to ± 7.5°/sec.
• Pitch rate
• ± 0.3 g’s in straight and level flight
• maximum 0.7 g’s 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
Autopilot control limits:
• Roll = ± 35° except in Approach (APP) mode. When in APP mode, the roll limits
are reduced linearly from ± 25°, above 200 feet radio altitude, to ± 5° at zero feet
radio altitude
• Pitch = ± 20°. In APP mode, the nose-down pitch limit is reduced below 300 feet,
programmed by vertical rate and radio altitude
CRS 2
PUSH DCT
Honeywell
FDAP
CPL
YD
AP
AP
CRS 2
PUSH DCT
Honeywell
FDAP
CPL
YD
GX_02_004
AP1
AP2
When selected, or will flash for
approximately 5 seconds, then steady.
AP1 AP2
20 20
10 10
20
ROL PITAP1
0.88 30000
23500
220
200

For Training Purposes Only
Sept 04
2-7
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
AUTOPILOT DISENGAGEMENT
Autopilot disengagement is accomplished by activating any of the following:
• AP button on guidance panel
• Autopilot quick-disconnect (DISC) button on either control wheel
• Manual stabilizer trim when touch control steering (TCS) not active
• YD button on FGC panel
• TCS button on either control wheel (while depressed).When the TCS button on
either control wheel is activated, the aileron and elevator servo clutches are
released, the autopilot is disengaged and the flight director is resynchronized.
Releasing the TCS button reengages the servo clutches and autopilot is engaged, if
within normal pitch and roll limits. Where applicable, the flight director modes
will react as if the autopilot had just been engaged
• Takeoff/Go Around (TOGA) buttons on thrust levers
• Motor trip/failure or AFCS failure
• Stick shaker acuation
The AP1 or AP2 annunciator will flash red continually and an aural “cavalry charge”
will sound repeatedly. The annunciation and aural can only be canceled by depressing
DISC on either control wheel.
N
O
S
E
D
N
N
O
S
E
U
P
D
I
S
C
M
A
S
T
E
R
T
C
S
GX_02_005
Stabilizer
Trim
Autopilot Quick
Disconnect Button
(DISC)
Touch Control
Steering (TCS)
PILOT’S CONTROL WHEEL
IC
R/T
GX_02_006
Takeoff/Go Around
(TOGA) Buttons

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-8 For Training Purposes Only
Sept 04
YAW DAMPER
The yaw damper provides stability augmentation and turn coordination for the
airplane yaw axis via two 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 power-up 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 yaw damper must be engaged for autopilot operation. Autopilot engagement
without YD will occur only when both YDs have failed in flight.
For more information on yaw damper, please refer to Chapter 10, FLIGHT
CONTROLS.
GX_02_007
CRS 2
PUSH DCT
Honeywell
FDAP
CPL
YD

For Training Purposes Only
Sept 04
2-9
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
PFD ANNUNCIATION
220
LIM LNAV ALTTCS
SPD VAPP VNAV
23500
ATT2
ADC1
0.88 30000
GX_02_008
AP1
TCS
T
C
S
DN
UP
P
I
T
C
H
VNAV
VS
Pitch
Wheel
AP ENGAGE STATUS
TOUCH CONTROL STEERING (TCS) STATUS
VERTICAL SPEED REFERENCE
VS Target
Readout
VS
Pointer
1000
VS 1000
0
1
2
3
1
VS Target
Bug
VS Speed
Readout
AP
FMS1
HDG
330
1000
VS 1000
0
1
2
3
1
2
3
N
33
30
W
24
21
S
15
12
E
6
3
29.92 IN
220
LIM LNAV ALTAP1
SPD VAPP VNAV
23500
ATT2
ADC1
20 2020
0.88 30000

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-10 For Training Purposes Only
Sept 04
FLIGHT DIRECTOR (FD)
The Flight Director modes of operation can be divided into two major subgroups, the
Lateral modes and the Vertical modes. Only one lateral mode and one vertical mode
may be active (green) at any time; however, one lateral arm (white) mode and up to
two vertical arm (white) modes may be selected.
The armed and active modes are annunciated on both PFDs. Armed modes are
displayed in white below active modes, which are displayed in green. The lateral
modes are annunciated on the left side of the displays and the vertical modes on the
right side, above the attitude sphere. Low bank mode is annunciated via green
eyebrow on top of the attitude sphere.
300
LIM LNAV VPTHAP1
SPD VOR VPTH
23500
ATT2
ADC1
20 2020
0.84 300 00
300
LIM LNAV PITAP1
SPD VOR VPTH
23500
ATT2
ADC1
20 2020
0.84 300 00
300
LIM VOR PITAP1
SPD VOR VNAV
23500
ATT2
ADC1
20 2020
0.84 300 00
300
LIM ROL PITAP1
SPD VOR VNAV
23500
ATT2
ADC1
20 2020
0.84 300 00
VNAV
Active mode flashes
for 5 seconds upon
automatic mode
capture.
Active mode flashes
for 5 seconds upon
automatic mode
capture.
VOR
VPTH
GX_02_009
VPTH
VOR
ACTIVE LATERAL MODE
ARMED VERTICAL MODE
ACTIVE VERTICAL MODE
ARMED LATERAL MODE
HDG FLC
LNAV VNAV
Active modes
Armed modes
Low bank
300
280
190
180
LIM HDG FLCAP1
SPD LNAV VNAV
23500
10000
ATT2
ADC1
20 20
10 10
20
0.88
265
6
4
300 00
20
00
80
60
230
NAV

For Training Purposes Only
Sept 04
2-11
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
Flight director command bars appear on the PFD whenever a lateral mode is selected.
The FD switch is used to remove flight director command bars. If the AP is on, the off-
side button will remove the off-side flight director bar(s) only. If the AP is on, the on-
side button is not functional. Flight director command bars are always present on both
PFDs when Go Around (GA), Takeoff (TO) or Windshear Guidance (WS) modes are
active.
20 20
10 10
10 10
20 20
20
FD Switch:
Used to remove flight director
command bars from the non-
coupled PFD.
GX_02_010
20 20
10 10
10 10
20 20
20
HDG FLCAP1
LNAV VNAV
0.88 30000
23500
300
280
260
265
6
4
HDG FLCAP1
LNAV VNAV
0.88 30000
23500
300
280
260
240240
265
6
4
COPILOT’S PFD
CRS 1
PUSH DCT
FD
CRS 2
PUSH DCT
Honeywell
FD
PILOT’S PFD
23000
80
20 23000
80
20
20 2020
ROL GA
AP1
200
23500
220
30000
CPL
TOGA
buttons
FLIGHT DIRECTOR DATA SOURCE (CPL)
FLIGHT DIRECTOR COMMANDS AND STATUS
20 20
10 10
20
ROL GA
AP1
200 3000
1500
180
170
160
6
GX_02_011
TOGA
buttons

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-12 For Training Purposes Only
Sept 04
GUIDANCE PANEL
FLC
SPD MAN
FMS
CRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
GX_02_012
Flight Director (FD) Switch
AP ON
AP OFF
Used to remove flight director command
bars.
– Onside button not function l
offside button removes offside FD.
– Onside button removes both FD
offside button removes offside FD.
a
Flight Level Change (FLC)
Switch
Used to climb or descend to a
new altitude reference, while
maintaining an airspeed or mach
reference.
Navigation (NAV) Switch
Used to arm lateral guidance
for capture of selected
navigation course or desired
track. NAV sources can be
FMS, LOC (only), VOR.
Heading (HDG) Switch
Used to activate the lateral
guidance to compute
steering commands, based
on selected heading.
Bank (BANK) Switch
Used to manually select
bank angle limit in HDG,
or VOR modes.
Heading (HDG) Button
Push Synchronize (PUSH
SYNC) Button
Used to move the heading
bug on PFD.
When pushed, causes
heading bug to synchronize
to airplane heading.
Approach (APP) Switch
Used to arm the lateral guidance
for localizer capture. When
localizer capture, vertical
guidance is armed for glideslope
capture. Also used to arm the
lateral guidance for VOR
approaches when VOR is NAV
source.
Course 1 (CRS 1)
Button
Push Direct (PUSH
DCT) Button
Used to move the
course pointer on
selected PFD.
When pushed,
causes course
pointer to indicate
direct course to
tuned VOR.
Back Course (BC) Switch
Used to select approach
mode guidance for capture
and tracking of back course
data.
Speed (SPD) Button
MAN
FMS
Used to set speed on PFD
(manually or by use of FMS).
- Airspeed reference set
by turning inner knob.
- Airspeed reference set
by FMS.
When
inner knob pushed, changes
IAS to Mach or Mach to IAS.
NOTE:
Annunciator, (on all flight
director mode switches),
illuminates when selected
mode is armed or active.
Annunciator
Light

For Training Purposes Only
Sept 04
2-13
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
GUIDANCE PANEL (Cont)
SPD MAN
FMS
CRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
GX_02_013
Altitude (ALT) Switch
Used to maintain
pressure altitude at time
of selection.
Yaw Damper (YD) Switch
Used to engage and
disengage the yaw damper.
Disengaging the yaw
damper also disengages the
autopilot.
Cours 2 (CRS 2) Button
Push Direct (PUSH DCT)
Button
Used to move the course
pointer on selected PFD.
When pushed, causes
course pointer to indicate
direct course to tuned
VOR.
e
AP and YD Pointers
Illuminate to indicate which AP guidance
computer or yaw damper channel is active.
Arrows to the left mean FGC No 1 is
controlling. Arrows to the right mean FGC
No 2 is controlling. Computers alternate
control at each power up.
Flight Director (FD) Switch
Used to remove flight
director command bars.
– Onside button not
functional offside button
removes offside FD.
– Onside button
removes both FD offside
button removes offside FD.
AP ON
AP OFF
Autopilot (AP) Switch
Used to engage and
disengage autopilot. When
autopilot engaged, the yaw
damper is engaged simul-
taneously. Disengaging the
autopilot does not
disengage the yaw
damper.
Vertical Navigation (VNAV)
Switch
Used to select the vertical
navigation mode, tracking
vertical flight profile from
selected FMS.
Speed/Pitch Wheel
DN
UP
Used to change vertical
reference value being used
by vertical speed (VS) or
pitch (PIT) modes.
- Rotate the wheel
forward to select pitch down
and speed increase.
- Rotate the wheel
backwards to select pitch up
and speed decrease.
Vertical Speed (VS)
Switch
Used to hold a vertical
speed. When pushed, the
vertical speed reference is
synchronized to current
vertical speed, displayed
on PFD. Use speed/pitch
wheel to change vertical
value.
CPL Pointer
Illuminates to indicate
whether the pilot's or
copilot’s PFD and ADC
are coupled to the
FGC. Both pointers will
illuminate during an
ILS approach. Defaults
to the left-side PFD on
power-up.
Altitude (ALT)
Preselect Button
Used to preselect
altitude, displayed
on PFD.
Coupled (CPL) Switch
(lateral and vertical
flight guidance)
Used to couple either
pilot's or copilot's PFD
and associated ADC
data to the FGC.

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-14 For Training Purposes Only
Sept 04
FLIGHT DIRECTOR MODES
LATERAL MODES
SWITCH (GUIDANCE PANEL) MODE ANNUNCIATION
HDG Heading Select HDG
NAV Based on displayed navigation source
(VOR, FMS, or localizer) VOR / LNAV / LOC
APR Based on VOR navigation source VAPP
BC Back Course BC
BANK High/Low Bank (HDG or VOR mode only) Eyebrow on attitude sphere (low
bank only)
VERTICAL MODES
SWITCH (GUIDANCE PANEL) MODE ANNUNCIATION
VS Vertical Speed Hold VS
None Automatic Altitude Capture ASEL
ALT Altitude Hold ALT
FLC Flight Level Change FLC
VNAV Vertical Navigation Modes requested by
FMS
VFLC
VASEL
VALT
VPTH
MULTI-AXIS MODES
SWITCH (GUIDANCE PANEL) MODE ANNUNCIATION
Lateral Field Vertical Field
APR Based on localizer navigation source LOC GS
Switch (Throttles)
TOGA Go Around ROL GA
TOGA Takeoff ROL TO
TOGA Windshear Guidance ROL WSHR

For Training Purposes Only
Sept 04
2-15
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
LATERAL MODES
Roll (ROL) Mode
Roll mode is automatically selected, when no other lateral mode is active, and the
autopilot is engaged. Roll mode generates commands to hold the heading that exists
when the mode is initiated, unless the bank angle upon initiation is over 6° (commands
are then generated to hold the bank angle). The roll mode reference is reset to the
current heading, or current roll angle, upon AP engagement.
Roll mode is annunciated in the lateral capture field on the PFD. Roll mode is cleared
by selecting another lateral mode. ROL will flash for approximately 5 seconds, when
active.
BASIC MODES
SWITCH (GUIDANCE PANEL) MODE ANNUNCIATION
None Roll Hold ROL
None Roll Hold Submode (wings level) ROL
Roll Hold Submode (heading hold) ROL
None Pitch Hold PIT
300
LIM ROL PITAP1
SPD VOR VPTH
23500
ATT2
ADC1
20 2020
0.88 300 00
AP
GX_02_014

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-16 For Training Purposes Only
Sept 04
Heading Select (HDG) Mode
The heading select mode is activated via the HDG switch on the guidance panel.
If the heading bug is turned through more than 180° but less than 360° (airborne), the
FGC will follow the bug all the way around to the target and not turn in the shortest
arc. The FGC provides guidance to the selected target using the shortest arc when on
the ground. The on-ground logic will prevent the airplane from turning in the wrong
direction following takeoff, due to maneuvering the airplane may have done on the
ground.
Bank Mode
While in BANK mode, the roll rate commanded by the heading or VOR modes is
limited to 4°/sec. If the roll angle is less than or equal to 6° when ascending through an
altitude of 35,050 feet, the FGC automatically transitions to the low bank limit of 17°.
If the roll angle is greater than 6°, an automatic bank limit transition will not occur
until the roll angle is reduced to less than or equal to 6°.
When descending through 34,950 feet, the bank limit shall revert to the high bank
limit of 27°, if the roll angle is less than or equal to 6°. If the roll angle is greater than
6°, high bank limit reversion will not occur until the roll angle is reduced to less than
or equal to 6°.
SPD MAN
FMS
CRS 1 CRS 2
PUSH DCT PUSH DCT
ALTHDG
DN
UP
P
I
T
C
H
Honeywell
FD FDAP
CPL
YD
FLC NAV BANKHDG VNAV ALT
APR VS
BC
PUSH CHG PUSH SYNC
HDG
PUSH SYNC
GX_02_015
N
33
30
6
3
N
33
3
HDG Knob:
Turn to set the heading
bug on the HSI.
HDG Switch:
When selected, activates
heading mode.
PUSH SYNC:
Used to synchronize heading
bug to present heading.
20 20
10 10
10 10
20 20
20
HDG
VOR
29.92 IN
VS
AP2
200 30000
9500
10500
220
200
190
180
170
160
150
185
6
4
10000
80
20

For Training Purposes Only
Sept 04
2-17
PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
The bank angle can also be toggled between high and low bank limits by means of the
BANK switch on the guidance panel.
When heading or VOR mode are active with the low bank limit, an “eyebrow” is
displayed between ± 17° on top of the attitude sphere on the PFD.
Lateral Navigation Modes
Lateral navigation mode is activated by selecting the NAV button on the guidance
panel. The following navigation sources may be activated:
• Very high frequency Omnidirectional Range (VOR)
• Localizer (LOC)
• FMS Lateral Navigation (LNAV)
If in (ROL) mode when (NAV) is selected, heading select mode is automatically
activated. A capture of any armed lateral navigation mode will cancel the heading
mode.
Lateral navigation guidance and automatic transitions are computed based on the
following data, received from the selected PFD:
• Lateral path deviation (VOR and LOC)
• Course or heading error
• NAV source identification (VOR, LOC, FMS)
• VOR radio frequency retuned flag
• To-From flag
• Distance to station (DME) and tuned -to-NAV flag
• Radio altitude
20 20
10 10
20
300
280
LIM HDG FLCAP1
SPD LNAV VNAV
23500
ATT2
ADC1
20 20
10 10
20
0.88
6
41000
BANKHDG
GX_02_016
BANK Switch
Used to limit bank
angle.
“eyebrow”

PILOT TRAINING GUIDE
AUTOMATIC FLIGHT CONTROL SYSTEM
2-18 For Training Purposes Only
Sept 04
VOR Mode
VOR mode provides for automatic intercept, capture and tracking of a selected VOR
radial. This mode is used to navigate on an airway between two VOR stations. This
mode is NOT to be used to intercept and track a VOR radial for a VOR approach.
Approach mode must be used for that purpose.
If Distance Measuring Equipment (DME) information is not available, the FGC uses
FMS range to the VOR station. If FMS range is not available, the FGC estimates a
distance of 30 NM.
Capture and tracking will occur, provided that:
• The intercept angle is less than 60°. The optimum intercept angle should be less
than 45°. If greater than 45°, course cut limiting may occur to limit steering
commands to 45° which forces flight path to get to radial sooner to prevent
overshooting beam center
• The bank angles required do not exceed the roll limits
FD roll commands are limited to ± 24° when in VOR capture and roll rate commands
are 5.5°/sec. When VOR track is active, FD roll commands are ± 14° and roll rate
commands 4°/sec.
If selected VOR is retuned to another VOR frequency, while in VOR capture, track or
overstation, VOR mode cancels and rearms automatically.
When the airplane is passing over the VOR transmitter (cone of confusion), VOR
mode will fly towards selected course reference (overstation passage). If selected
course is unchanged prior to entry into cone of confusion, previously computed wind
correction is applied and VOR mode will not command a turn towards selected course
pointer. Changes of course pointer setting when overstation will cause a change in
course hold reference.
If DME is available, the cone of confusion entry boundary is estimated based on
distance to transmitter and altitude, or VOR TO/FROM transition. When over the
VOR station, VOR will follow a course change of up to 120°. The cone of confusion
exit boundary is based on altitude, airspeed and time. If DME information is not
available, the cone of confusion boundaries are determined by level of beam noise or
VOR TO/FROM transition. When in VOR overstation, the flight director roll
commands are limited to ± 24° and roll rate commands are 7°/sec. The overstation
sensor (OSS) monitors entry into zone of confusion and removes radio deviation from
the roll command.