Garmin | GFC™ 500 Digital Autopilot | Garmin GFC™ 500 Digital Autopilot Airplane Flight Manual Supplement, GFC 500 Autopilot in Textron (Cessna) (T)210 K/L/M/N

Garmin GFC™ 500 Digital Autopilot Airplane Flight Manual Supplement, GFC 500 Autopilot in Textron (Cessna) (T)210 K/L/M/N
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Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
190-02291-14 Rev. 2
Garmin International, Inc
Log of Revisions
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GFC 500 Autopilot with ESP
Installed in
Textron (Cessna) 210 K/L/M/N
and
Textron (Cessna) T210 K/L/M/N
REV
NO.
PAGE NO(S)
DESCRIPTION
DATE OF
APPROVAL
FAA APPROVED
1
ALL
Original Issue
10/16/18
JR Brownell
Garmin ODA STC
Unit Administrator
2
ALL
Add G3X Information and Yaw Damper
Disconnect in Section 3A
See Cover
See Cover
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page ii
190-02291-14 Rev. 2
Table of Contents
Section 1 – General ....................................................................................................... 1
USE OF THE SUPPLEMENT ................................................................................................................... 1
ABBREVIATIONS AND TERMINOLOGY ................................................................................................ 2
INSTALLED EQUIPMENT INTERFACES ................................................................................................ 3
INSTALLED FEATURES CHECKLIST .................................................................................................... 4
Section 2 – Limitations ................................................................................................. 1
Section 3 – Emergency Procedures ............................................................................ 1
AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY....................................................................... 1
AUTOPILOT FAILURE / ABNORMAL DISCONNECT ............................................................................ 2
YAW AXIS FAILURE / ABNORMAL YAW DAMPER DISCONNECT ..................................................... 2
PITCH TRIM FAILURE ............................................................................................................................. 2
ESP ACTIVATION .................................................................................................................................... 3
OVERSPEED PROTECTION (MAXSPD)................................................................................................. 3
UNDERSPEED PROTECTION (MINSPD) ............................................................................................... 3
Section 3A – Abnormal Procedures ............................................................................ 5
AUTOPILOT ABNORMAL DISCONNECT ............................................................................................... 5
AUTOPILOT PREFLIGHT TEST (PFT) FAIL ........................................................................................... 5
LOSS OF NAVIGATION INFORMATION................................................................................................. 5
LOSS OF AIRSPEED DATA .................................................................................................................... 6
LOSS OF ALTITUDE DATA ..................................................................................................................... 6
LOSS OF GPS INFORMATION ................................................................................................................ 6
HEADING DATA SOURCE FAILURE ...................................................................................................... 7
ELEVATOR MISTRIM ............................................................................................................................... 7
YAW DAMPER DISCONNECT ................................................................................................................. 8
Section 4 – Normal Procedures ................................................................................... 1
GFC 500 POWER UP ............................................................................................................................... 1
FLIGHT DIRECTOR / AUTOPILOT NORMAL OPERATING PROCEDURES ........................................ 1
MANUAL AUTOPILOT DISCONNECT .................................................................................................... 2
VERTICAL MODES .................................................................................................................................. 3
VERTICAL SPEED (VS) MODE ............................................................................................................ 3
INDICATED AIRSPEED (IAS) MODE ................................................................................................... 3
ALTITUDE HOLD (ALT) MODE, MANUAL CAPTURE ......................................................................... 3
VERTICAL NAVIGATION (VNAV) ......................................................................................................... 4
GO AROUND ......................................................................................................................................... 5
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page iii
MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED ....................................................................... 5
LATERAL MODES.................................................................................................................................... 6
HEADING MODE (HDG) ....................................................................................................................... 6
TRACK MODE (TRK) ............................................................................................................................ 6
NAVIGATION (VOR).............................................................................................................................. 6
NAVIGATION (GPS) .............................................................................................................................. 6
APPROACHES ......................................................................................................................................... 7
ILS APPROACH .................................................................................................................................... 7
LOC APPROACH (GS out) .................................................................................................................... 8
GPS APPROACH (LPV, LNAV/VNAV, LP+V, or LNAV+V) .................................................................. 9
GPS APPROACH (LP, LNAV) ............................................................................................................. 10
LOC BC APPROACH .......................................................................................................................... 11
VOR Approach ..................................................................................................................................... 12
DISABLING ESP ..................................................................................................................................... 12
Section 5 – Performance ...............................................................................................1
Section 6 – Weight and Balance ...................................................................................1
Section 7 – System Description....................................................................................1
AFCS OVERVIEW .................................................................................................................................... 1
AUTOPILOT CONTROL UNIT AND DISPLAY ........................................................................................ 4
PREFLIGHT TEST .................................................................................................................................... 7
MESSAGES AND ANNUNCIATIONS ...................................................................................................... 7
LIGHTING.................................................................................................................................................. 9
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page iv
190-02291-14 Rev. 2
SECTION 1 – GENERAL
The information in this supplement is FAA-approved material and must be attached to the Pilot’s Operating
Handbook and FAA Approved Airplane Flight Manual (POH/AFM) when the airplane has been modified by
installation of the Garmin GFC 500 Autopilot system in accordance with Garmin International, Inc. approved data.
The information in this supplement supersedes or adds to the basic POH/AFM only as set forth below. Users of
the manual are advised to always refer to the supplement for possibly superseding information and placarding
applicable to operation of the airplane.
USE OF THE SUPPLEMENT
The following definitions apply to WARNINGS, CAUTIONS and NOTES found throughout the supplement:
WARNING
Operating procedures, techniques, etc., which may result in personal injury or loss of life if not
carefully followed.
CAUTION
Operating procedures, techniques, etc., which may result in damage to equipment if not
carefully followed.
NOTE
Operating procedures, techniques, etc., which is considered essential to emphasize.
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 1–1
ABBREVIATIONS AND TERMINOLOGY
The following glossary is applicable within the airplane flight manual supplement
AFCS
AFM
AFMS
AGL
AHRS
Automatic Flight Control System
Airplane Flight Manual
Airplane Flight Manual Supplement
Above Ground Level
Attitude and Heading Reference
System
ALT
Altitude
AP
Autopilot
APR
Approach
ATC
Air Traffic Control
BC
Back Course Approach
CDI
Course Deviation Indicator
DA
Decision Altitude
DISC
Disconnect
DWG
Drawing
ESP
Electronic Stability and Protection
FAA
Federal Aviation Administration
FAF
Final Approach Fix
FD
Flight Director
GA
Go Around
GFC 500
Garmin Autopilot
GMC 507
Autopilot Mode Control Panel
GNSS
Global Navigation Satellite System
GPS
Global Positioning System
GS
Glideslope
GSA
Garmin Servo Actuator
HDG
AFCS heading mode
IAS
Indicated Airspeed
ILS
Instrument Landing System
INT
Interrupt
KIAS
Knots Indicated Airspeed
KT
Knot
LNAV
Lateral Navigation
LNAV+V
Lateral Navigation with Advisory
Vertical Guidance
LNAV/VNAV Lateral Navigation / Vertical
Navigation Approach
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 1–2
LOC
LP
LP+V
LPV
LVL
MDA
PFT
POH
STC
TO
TRK
VHF
VNAV
VOR
VS
YD
Localizer (no glideslope available)
Localizer Performance
Localizer Performance with Advisory
Vertical Guidance
Localizer Performance with Vertical
Guidance
Level
Minimum Descent Altitude
Preflight Test
Pilot’s Operating Handbook
Supplemental Type Certificate
Takeoff
Track
Very High Frequency
Vertical Navigation
VHF Omni-directional Range
Vertical Speed
Yaw Damper
190-02291-14 Rev. 2
INSTALLED EQUIPMENT INTERFACES
The following is the list of installed equipment and functions associated with the GFC 500 Autopilot installation in
this airplane.
Table 1-1: Table of Installed Equipment Interfaces
DEVICE TYPE
GPS Navigator #1
Manufacturer / Model
If not installed, note N/A
Additional Information
Is Navigator #1 interfaced to GFC 500?
 NO
 YES
VHF Nav Radio #1
Is VHF Nav Radio #1 interfaced to GFC 500?
 NO
 YES
VHF Nav Radio #2
Pitch Trim Servo
Yaw Damper
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 1–3
INSTALLED FEATURES CHECKLIST
The checked autopilot modes and features are available on this aircraft.
Basic AP Features
 Flight Director
Electric Pitch Trim
Yaw Damper
 Overspeed Protection
 Underspeed Protection


Electronic Stability and Protection
 Pitch/Roll Attitude
 High Speed Protection
Low Speed Protection
Vertical Autopilot Modes
 Pitch (PIT)
 Level (LVL (zero vertical speed))
 Go Around (GA)
 Altitude Hold (ALT)
 Vertical Speed (VS)
 Altitude Capture via Altitude Preselect
 Indicated Airspeed (IAS)
Vertical Navigation (VNAV)
GPS Approach Glidepath
ILS Glideslope
Lateral Autopilot Modes
 Roll (ROL)
 Level (LVL (wings level))
 Go Around (GA)
Heading
 Track
GPS Navigation
VHF Navigation
Approach Mode
GPS
VOR/LOC



AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 1–4







190-02291-14 Rev. 2
SECTION 2 – LIMITATIONS
The Garmin G5 Electronic Flight Instrument Pilot’s Guide for Certified Aircraft, part number 190-01112-12 Rev B
(or later approved revisions), must be immediately available to the flight crew (when G5 is installed).
The Garmin G3X Touch Pilot’s Guide for Certified Aircraft, part number 190-02472-00, Rev A (or later approved
revisions) must be immediately available to the flight crew (when G3X EFIS system is installed).
This AFMS is applicable to the software versions shown below:
Software Item
Software Version
(or later FAA Approved version for this STC)
G5 Software Version
5.70
G3X Software Version
8.00
A pilot must be seated in the left pilot’s seat, with seatbelt fastened, during all autopilot operations.
Do not use autopilot during takeoff and landing.
The GFC 500 AFCS Preflight Test (PFT) must complete successfully prior to use of the autopilot, flight director or
manual electric trim.
The maximum fuel imbalance with the autopilot engaged is 10 gallons.
The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet AGL
during all other operations.
The GFC 500 autopilot is approved for Category 1 precision approaches and non-precision approaches only.
Autopilot Engagement Speed
190-02291-014 Rev. 2
Minimum
78 KIAS
Maximum
185 KIAS
GFC 500 Autopilot in Textron (Cessna) 210 Series
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GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
SECTION 3 – EMERGENCY PROCEDURES
Some emergency situations require immediate memorized corrective action. These steps are printed in bold in the
emergency procedures and should be accomplished without the aid of the checklist.
AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY
If the airplane deviates unexpectedly from the planned flight path:
1. Control Wheel ............................................................................................................ GRIP FIRMLY
2. AP DISC / TRIM INT Button ............................................................................. PRESS AND HOLD
CAUTION
Be prepared for high elevator control forces.
3. Aircraft Attitude ....................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
4. Elevator Trim ........................................................ RE-TRIM if necessary using Elevator Tab Wheel
5. AUTOPILOT Circuit Breaker ..................................................................................................... PULL
NOTE
Do not release the AP DISC / TRIM INT Button until after pulling the AUTOPILOT Circuit
Breaker.
Pulling the autopilot circuit breaker will render the autopilot, yaw damper (if installed), and
ESP inoperative.
6. AP DISC / TRIM INT Button .............................................................................................. RELEASE
CAUTION
In flight, do not overpower the autopilot. The trim will operate in the direction opposing
the overpower force, which will result in large out-of-trim forces.
Do not attempt to re-engage the autopilot or use manual electric pitch trim until the cause
of the malfunction has been corrected.
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 3–1
AUTOPILOT FAILURE / ABNORMAL DISCONNECT
(Red AP in autopilot status box on display, continuous aural disconnect tone.)
1. AP DISC / TRIM INT Button or G5 Knob or G3X Autopilot Status Bar ....... PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude ........................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
The autopilot disconnect may be accompanied by a red AFCS in the autopilot status box,
indicating the automatic flight control system has failed. The flight director will not be
available and the autopilot cannot be re-engaged with this annunciation present.
If the disconnect is accompanied by an amber AP with a red X, the autopilot will not be
available however the flight director will still be functional.
In the event of a GMC failure, pressing the G5 or G3X Autopilot Status barknob will
acknowledge the disconnect tone.
YAW AXIS FAILURE / ABNORMAL YAW DAMPER DISCONNECT
(Red YD in autopilot status box on display)
This procedure applies only if the optional yaw servo is installed:
1. AP DISC / TRIM INT Button, YD Button on GMC or G5 Knob ................... PRESS AND RELEASE
(to acknowledge the disconnect)
2. Aircraft Attitude ........................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
The yaw damper disconnect may be accompanied by an amber YD with a red X in the
autopilot status box. The YD is inoperative and will not be available. The autopilot may
be re-engaged and disengaged normally, but the yaw damper with remain inoperative.
PITCH TRIM FAILURE
(Red PTRIM on G5 or G3X display.)
This procedure applies only if the optional pitch trim servo is installed:
1. Indicates a failure of the pitch trim servo.
2. Control Wheel ............................................................................................................. GRIP FIRMLY
3. AP DISC / TRIM INT Button .......................................................................... PRESS and RELEASE
(Be prepared for high elevator control forces)
4. Elevator Trim ...................................................... AS REQUIRED USING ELEVATOR TAB WHEEL
NOTE
The autopilot may be re-engaged. Refer to the normal procedures section of this AFMS,
MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED.
5. Yaw Damper ........................................................................................... ENGAGE AS REQUIRED
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 3–2
190-02291-14 Rev. 2
ESP ACTIVATION
1. Power........................................................................................................................ AS REQUIRED
2. Aircraft Attitude ....................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
If ESP is active for approximately 10 seconds, the autopilot will automatically engage in
LVL mode, an aural ‘ENGAGING AUTOPILOT’ will be heard (or a Sonalert tone will play
for installations without a supported audio panel), and the autopilot will level the wings
and maintain zero-vertical speed. Refer to Section 7, System Description, for further
information.
ESP will be disabled by pressing and holding the AP DISC / TRIM INT button. Releasing
the button will allow ESP to function again.
OVERSPEED PROTECTION (MAXSPD)
(MAXSPD displayed on G5 or G3X, AIRSPEED – AIRSPEED Aural sounds.)
1. Power.................................................................................................................................. REDUCE
2. Aircraft Attitude and Altitude ......................................................................................... MONITOR
After overspeed condition is corrected:
3. Autopilot .......................................RESELECT VERTICAL AND LATERAL MODES (if necessary)
4. Power ............................................................................................................. ADJUST as necessary
NOTE
Autopilot Overspeed Protection Mode provides a pitch up command to maintain 185
KIAS.
UNDERSPEED PROTECTION (MINSPD)
(MINSPD displayed on G5 or G3X, AIRSPEED – AIRSPEED Aural sounds.)
1. Power.................................. INCREASE POWER AS REQUIRED TO CORRECT UNDERSPEED
2. Aircraft Attitude and Altitude ......................................................................................... MONITOR
After underspeed condition is corrected:
3. Autopilot .........................................RESELECT VERTICAL AND LATERAL MODES (if necessary)
4. Power ............................................................................................................. ADJUST as necessary
NOTE
Autopilot Underspeed Protection Mode provides a pitch down command to maintain 78
KIAS.
190-02291-14 Rev. 2
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AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
SECTION 3A – ABNORMAL PROCEDURES
AUTOPILOT ABNORMAL DISCONNECT
(Red AP in the G5 or G3X autopilot status box, continuous aural disconnect tone.)
1. AP DISC / TRIM INT Button .........................................................................PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude........................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
The autopilot disconnect may be accompanied by a red AFCS in the autopilot status box,
indicating the automatic flight control system has failed. The flight director will not be
available and the autopilot cannot be re-engaged with this annunciation present.
If the disconnect is accompanied by an amber AP with a red X, the autopilot will not be
available however the flight director will still function.
AUTOPILOT PREFLIGHT TEST (PFT) FAIL
(Amber AP with a red X in G5 or G3X autopilot status box.)
1. Indicates the AFCS system failed the automatic PFT.
NOTE
The autopilot, yaw damper (if installed), ESP, and electric elevator trim will be
inoperative. Flight director will still function.
LOSS OF NAVIGATION INFORMATION
(Amber GPS, VOR, LOC, or BC flashes for 10 seconds on G5 or G3X.)
NOTE
If a navigation signal is lost while the autopilot is tracking it, the autopilot will roll the aircraft
wings level and default to roll mode (ROL).
1. GMC 507 Mode Panel............................................. SELECT HDG mode and SET desired heading
2. NAV Source ......................................................................................... SELECT a valid NAV source
3. NAV Key ................................................................................................................................. PRESS
If on an instrument approach at the time the navigation signal is lost:
4. Missed Approach Procedure .................................................................... EXECUTE (as applicable)
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 3–5
LOSS OF AIRSPEED DATA
(Red X through airspeed tape on the G5 or G3X display, amber AP with a red X in autopilot status box.)
NOTE
If airspeed data is lost while the autopilot is tracking airspeed, the flight director will
default to pitch mode (PIT).
1. AP DISC / TRIM INT Button ........................................................................ PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude ........................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
3. Manual Elevator Trim ............................................................................................. TRIM as required
NOTE
The autopilot cannot be re-engaged. The flight director is available however IAS mode
cannot be selected. Loss of airspeed will be accompanied by a red PTRIM indication
on the G5 or G3X (if a pitch trim servo is installed).
LOSS OF ALTITUDE DATA
(Red X through altitude tape on the G5 or G3X display.)
NOTE
If altitude data is lost while the autopilot is tracking altitude, the autopilot will default to
pitch mode (PIT).
1. Autopilot .......................................................................................... SELECT different vertical mode
LOSS OF GPS INFORMATION
This procedure applies only if the optional GPS navigator is installed:
(GPS position information is lost to the autopilot.)
NOTE
If GPS position data is lost while the autopilot is tracking a GPS, VOR, LOC or BC course,
the autopilot will default to roll mode (ROL). The autopilot will default to pitch mode if
GPS information is lost while tracking an ILS. The autopilot uses GPS aiding in VOR,
LOC and BC modes.
1. Autopilot ................................................ SELECT different lateral and vertical mode (as necessary)
If on an instrument approach:

AP DISC / TRIM INT button ................................... PRESS, Continue the approach manually
Or

Missed Approach Procedure .......................................................... EXECUTE (as applicable)
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 3–6
190-02291-14 Rev. 2
HEADING DATA SOURCE FAILURE
This procedure applies only if the optional heading source to the navigator is installed:
1. Autopilot ............................................................................................ SELECT different lateral mode
NOTE
Track information will be displayed on the G5 or G3X.
GPSS will not be provided to the autopilot for heading legs.
ELEVATOR MISTRIM
(Amber TRIM UP or TRIM DOWN displayed on the G5 or G3X.)
This annunciation indicates a mistrim of the elevator while the autopilot is engaged. If an optional pitch trim
servo is installed, the autopilot will normally trim the airplane as required. However, during rapid acceleration,
deceleration, configuration changes, or near either end of the elevator trim limits, momentary illumination of this
message may occur. If the autopilot is disconnected while this message is displayed, high elevator control
forces are possible.
If the optional pitch trim servo is not installed:
1. Refer to the normal procedures section of this AFMS, MANUAL PITCH TRIM WITH AUTOPILOT
ENGAGED.
If the optional pitch trim servo is installed:
CAUTION
Do not attempt to overpower the autopilot in the event of a pitch mistrim. The autopilot servo
will oppose pilot input and will cause pitch trim to run opposite the direction of pilot input. This
will lead to a significant out-of-trim condition, resulting in large control wheel force when
disengaging the autopilot.
NOTE
Momentary display of the TRIM UP or TRIM DOWN message during configuration changes or
large airspeed changes is normal.
1. Control Wheel ............................................................................................................. GRIP FIRMLY
CAUTION
Be prepared for significant sustained control forces in the direction of the mistrim annunciation.
For example, TRIM DOWN indicates nose down control wheel force will be required upon
autopilot disconnect.
2. AP DISC / TRIM INT Button .........................................................................PRESS AND RELEASE
3. Manual Elevator Trim ....................................................................................... RE-TRIM as required
NOTE
Electric pitch trim should be considered inoperative until the cause of the mistrim has
been investigated and corrected.
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 3–7
YAW DAMPER DISCONNECT
(Amber YD displayed in autopilot status box on display)
This failure will only occur if the optional yaw servo is installed.
1. YD Button on GMC or G5 Knob .................................................................. PRESS AND RELEASE
(to cancel disconnect tone)
2. Aircraft Attitude ........................................................... MAINTAIN / REGAIN AIRCRAFT CONTROL
NOTE
A flashing amber ‘YD’ in the autopilot status box indicates that the yaw damper has disconnected. If the
disconnect was not pilot initiated, Refer to Section 3 – Emergency Procedures, YAW AXIS FAILURE /
ABNORMAL DISCONNECT, for further information.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 3–8
190-02291-14 Rev. 2
SECTION 4 – NORMAL PROCEDURES
GFC 500 POWER UP
During the preflight test the G5 or G3X will display PFT in the autopilot status box. When the GFC 500 passes
preflight test, PFT will be removed from the autopilot status box.
FLIGHT DIRECTOR / AUTOPILOT NORMAL OPERATING PROCEDURES
Autopilot/Flight Director mode annunciations are displayed at the top of the G5 Electronic Flight Instrument or the
top of the G3X Electronic Flight Instrument PFD.. Green text indicates active autopilot/flight director modes.
Armed modes are indicated in white text. Normal mode transitions will flash inverse video for 10 seconds before
becoming steady. Abnormal mode transitions will flash for 10 seconds in amber text before the default mode is
annunciated as the active mode in green text. Default autopilot/flight director modes are Roll (ROL) and Pitch
(PIT) modes.
The autopilot status box displays the autopilot engagement status as well as armed and active flight director
modes.
Autopilot Engagement with Flight Director Off — Upon engagement, the autopilot will be set to hold the
current attitude of the airplane if the flight director was not previously on. In this case, ‘ROL’ and ‘PIT’ will be
annunciated.
Autopilot Engagement with Flight Director On — If the flight director is on, the autopilot will smoothly pitch and
roll the airplane to capture the FD command bars. The prior flight director modes remain unchanged.
Autopilot Disengagement — The most common way to disconnect the autopilot is to press and release the AP
DISC / TRIM INT button located on the control wheel. An autopilot disconnect tone will sound and an amber AP
will be annunciated on the G5 or G3X autopilot status box. If the optional yaw damper is installed, the AP DISC /
TRIM INT button will also disconnect the yaw damper, and a disconnect tone will sound and an amber YD will be
annunciated on the G5 or G3X autopilot status box.
Other ways to disconnect the autopilot include:
– Pressing the AP Key on the GMC 507 Mode Controller. If the optional yaw damper is installed, it will remain
engaged until the YD button is pressed, or the red AP DISC / TRIM INT button is pressed.
– Operating the Electric Pitch Trim Switch (located on the control wheel). If the optional yaw damper is installed,
it will remain engaged until the YD button is pressed, or the red AP DISC / TRIM INT button is pressed.
– Pulling the AUTOPILOT circuit breaker
In the event of unexpected autopilot behavior, press and holding the AP DISC / TRIM INT button will disconnect
the autopilot and remove all power to the servos.
Yaw Damper Engagement with Autopilot On –- Upon engagement of the autopilot, if the yaw damper
is installed, it will automatically engage to provide yaw damping, and turn coordination. YD will be
annunciated in the autopilot status box.
Yaw Damper Engagement with Autopilot Off –- The yaw damper, if installed, may be engaged with the
autopilot disengaged. This will provide yaw damping and turn coordination. YD will be annunciated in the
autopilot status box.
High Altitude Operation with Autopilot On – For optimal autopilot performance, autopilot engagement should
be limited to airspeeds greater than 100 KIAS at altitudes greater than 18,000 feet.
Flap Deployment with Autopilot On – For optimal autopilot performance, flaps should be extended and
retracted in 10-degree increments when the autopilot is engaged.
190-02291-14 Rev. 2
GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–1
MANUAL AUTOPILOT DISCONNECT
If necessary, the autopilot may be manually disconnected using any one of the following methods:
1. AP DISC / TRIM INT Button .......................................................................... PRESS and RELEASE
(Pilot’s control wheel)
2. AP Key ................................................................................................................................... PRESS
3. Pitch Trim Switch ............................................................................................................. ACTIVATE
4. AUTOPILOT Circuit Breaker ..................................................................................................... PULL
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–2
190-02291-14 Rev. 2
VERTICAL MODES
VERTICAL SPEED (VS) MODE
1. Altitude Preselect ......................................................................................... SET to Desired Altitude
2. Press VS Key, autopilot synchronizes to the airplane’s current vertical speed.
3. Vertical Speed Reference ............................................................... ADJUST using UP / DN Wheel
4. Green ALT........................................................................................ VERIFY Upon Altitude Capture
INDICATED AIRSPEED (IAS) MODE
1. Altitude Preselect ......................................................................................... SET to Desired Altitude
2. Press IAS Key, autopilot synchronizes to the airplane’s current indicated airspeed.
3. AIRSPEED Reference ...................................................................... ADJUST using UP / DN Wheel
4. Adjust throttle as required ................................................................... INCREASE POWER to climb
DECREASE POWER to descend
5. Green ALT........................................................................................ VERIFY Upon Altitude Capture
ALTITUDE HOLD (ALT) MODE, MANUAL CAPTURE
1. When at the desired altitude ....................................................................................PRESS ALT key
NOTE
The autopilot will hold the altitude at which the ALT key was pressed.
If climbing or descending at a high rate when the ALT key is pressed, the airplane will
overshoot the reference altitude and then return to it. The amount of overshoot will
depend on the vertical speed when the ALT key is pressed.
The altitude reference is displayed in the autopilot status box. The reference may be
changed by +/- 200 FT using the UP / DN wheel.
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GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–3
VERTICAL NAVIGATION (VNAV)
1. Navigation Source ............................................................................................ SELECT CDI to GPS
2. Vertical Navigation Profile ................................................ LOAD into the GPS navigator’s flight plan
3. Altitude Preselect ......................................................................... SET to the vertical clearance limit
When ATC clearance received
4. GMC 507 Mode Panel......................... PRESS VNAV within 5 minutes of the top of descent (TOD)
NOTE
Vertical navigation will not function for the following conditions:
• Selected navigation source is not GPS.
• VNAV is not enabled on the GPS Navigator.
• No waypoints with altitude constraints are programed in the flight plan.
• Active lateral autopilot mode is not GPS.
• OBS mode is active
• Dead Reckoning mode is active
• Parallel track is active
• Aircraft is on the ground
Vertical navigation is not available between the final approach fix (FAF) and the missed
approach point (MAP)
ALTV will be the armed vertical mode during the descent if the altitude preselect is set to
a lower altitude than the VNAV reference altitude. This indicates the autopilot / flight
director will capture the VNAV altitude reference. ALTS will be the armed mode during the
descent if the altitude preselect is set at or above the VNAV reference altitude, indicating
that the autopilot / flight director will capture the altitude preselect altitude reference.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
GO AROUND
1. GO AROUND button ........................................................... PRESS – Verify GA / GA on G5 or G3X
autopilot will not disengage
2. Autopilot (if engaged) ............... VERIFY airplane pitches up following flight director command bars
3. Throttle ...................................................................................................... APPLY Go Around power
4. GMC 507 Mode Panel.................................... PRESS NAV to couple to selected navigation source
OR
PRESS HDG to Fly ATC Assigned Missed Approach Heading
5. Altitude Preselect .................................................................................................................. VERIFY
Set to appropriate altitude.
CAUTION
Flap retraction should be limited to 10-degree increments with the autopilot engaged. A
continuous, full flap retraction during a go around can significantly reduce the initial climb rate.
NOTE
The pilot is responsible for initial missed approach guidance in accordance with published
procedure. When the GA button is pressed the Flight Director command bars will command a
go-around pitch attitude and wings level. The pilot must select the CDI to the appropriate
navigation source and select the desired lateral and vertical flight director modes.
MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED
(Amber TRIM UP or TRIM DOWN displayed on G5 or G3X.)
NOTE
If the aircraft is not equipped with a pitch trim servo, the pilot must manually adjust the pitch
trim when airspeed and aircraft configuration changes are made.
A message will be displayed on the G5 or G3X display to indicate the pitch servo is holding sustained force, and
the pilot must manually trim the aircraft.
1. If TRIM UP message is displayed ........................................................... MANUALLY TRIM nose up
2. If TRIM DOWN message is displayed ............................................... MANUALLY TRIM nose down
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GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–5
LATERAL MODES
HEADING MODE (HDG)
1. HDG/TRK Knob ......................................................... Rotate to set heading bug to desired heading.
2. HDG Key ................................................................................................................................ PRESS
The autopilot will turn the airplane in the direction of the heading bug.
TRACK MODE (TRK)
1. HDG/TRK Knob ................................................................... Rotate to set track bug to desired track.
2. TRK Key ................................................................................................................................. PRESS
The autopilot will turn the airplane in the direction of the track bug.
NAVIGATION (VOR)
This mode will only be available if the optional VHF navigation navigator is installed.
1. Navigation Source. ................................................................................. SELECT CDI to VHF NAV
Tune and identify the station frequency.
2. Course Pointer ...............................................................................SET CDI to the Desired Course
3. Intercept Heading ............................................................ ESTABLISH in HDG, TRK or ROL mode
4. NAV Key ................................................................................................................................. PRESS
NOTE
If the Course Deviation Indicator (CDI) is greater than one dot from center, the autopilot
will arm the VOR mode. The pilot must ensure that the current heading will result in a
capture of the selected course. If the CDI is one dot or less from center, the autopilot
will enter the capture mode when the NAV key is pressed.
NAVIGATION (GPS)
This mode will only be available is the optional GPS navigator is installed.
1. Navigation Source ............................................................................................ SELECT CDI to GPS
2. Waypoint .......................................................................................... SELECT on Navigation Source
3. Course Pointer ..................................................................... VERIFY CDI set to the Desired Course
4. Intercept Heading ........................................................................ESTABLISH in HDG or ROL mode
5. NAV Key ................................................................................................................................. PRESS
NOTE
If the Course Deviation Indicator (CDI) is greater than one dot from center, the autopilot will arm
the GPS mode. The pilot must ensure that the current heading will result in a capture of the
selected course. If the CDI is one dot or less from center, the autopilot will enter the capture mode
when the NAV key is pressed.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
APPROACHES
ILS APPROACH
This procedure applies only if the optional VHF and GPS navigator are installed.
1. Navigation Source. .................................................................................... SELECT CDI to VHF Nav
Tune and Identify an ILS station frequency.
2. CDI ............................................................................................................. SET to front LOC course
NOTE
Ensure that the current heading will result in a capture of the selected course.
3. Press APR Key ................................................................................. VERIFY LOC and GS ARMED
NOTE
When VNAV is enabled prior to an ILS approach, the APR mode must be armed for VNAV to
properly transition. If APR is not armed when VNAV ends and the navigator switches from the
GPS to LOC source, the autopilot will revert to PIT and ROL mode.
4. LOC and GS Mode.......................................... VERIFY airplane Captures and Tracks LOC and GS
5. Missed Approach Altitude .......................................................................... SET in Altitude preselect
6. At Decision Altitude (DA),

AP DISC / TRIM INT button .......................... PRESS, Continue visually for a normal landing
Or

GO AROUND (GA) button.............................. PRESS, Execute Missed Approach Procedure

Apply GA power.

Set missed approach altitude in the altitude preselect.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
If the Course Deviation Indicator (CDI) is greater than half scale deflection, the autopilot
will arm the LOC mode. The pilot must ensure that the current heading will result in a
capture of the selected course. If the CDI is within half scale deflection, the autopilot
will enter the capture mode when the APR key is pressed.
When the selected navigation source is an ILS, glideslope coupling is automatically
armed when the APR key is pressed. The glideslope cannot be captured until the
localizer is captured. The autopilot can capture the glideslope from above or below the
glideslope.
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GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–7
LOC APPROACH (GS out)
This procedure applies only if the optional VHF and GPS navigator are installed.
1. Navigation Source ..................................................................................... SELECT CDI to VHF Nav
Tune and Identify an ILS station frequency.
2. Course Pointer ........................................................................................... SET to front LOC course
NOTE
Ensure that the current heading will result in a capture of the selected course.
3. NAV Key ................................................................................................ PRESS, verify LOC ARMED
4. LOC Mode ....................................................... VERIFY airplane Captures and Tracks LOC Course
5. Altitude Preselect ................................................................ SET to next required step down altitude
6. Missed Approach Altitude ......................................................... SET when in ALT mode at the MDA
7. At Missed Approach Point,

AP DISC / TRIM INT button .......................... PRESS, Continue visually for a normal landing
Or

GO AROUND (GA) button.............................. PRESS, Execute Missed Approach Procedure

Apply GA power.

Set missed approach altitude in the altitude preselect.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
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190-02291-14 Rev. 2
GPS APPROACH (LPV, LNAV/VNAV, LP+V, or LNAV+V)
This procedure applies only if the optional GPS navigator is installed.
1. Navigation Source ............................................................................................ SELECT CDI to GPS
2. Course Pointer ..................................................................... VERIFY CDI set to the Desired Course
NOTE
Ensure that the current heading will result in a capture of the selected course.
3. APR Key .................................................................................. PRESS, verify GPS and GP ARMED
4. GPS and GP Mode .........................................VERIFY airplane Captures and Tracks GPS and GP
5. ALT Key ....................................... PRESS to level off at the MDA for a LP+V or LNAV+V approach
6. At DA (LPV or LNAV/VNAV approach), or MDA and Missed Approach Point (LP+V or LNAV+V)

AP DISC / TRIM INT button .......................... PRESS, Continue visually for a normal landing
Or

GO AROUND (GA) button.............................. PRESS, Execute Missed Approach Procedure

Apply GA power.

Set missed approach altitude in the altitude preselect.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
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GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–9
GPS APPROACH (LP, LNAV)
This procedure applies only if the optional GPS navigator is installed.
1. Navigation Source ..................................................................................... SELECT GPS on the CDI
2. Course Pointer .................................................................... VERIFY CDI set on the Desired Course
NOTE
Ensure that the current heading will result in a capture of the selected course.
3. NAV Key ............................................................................................... PRESS, verify GPS ARMED
4. GPS Mode ....................................................... VERIFY airplane Captures and Tracks GPS Course
5. Altitude Preselect ................................................................ SET to next required step down altitude
6. Missed Approach Altitude ....................................................... SET when in ALT mode at the MDA
7. At Missed Approach Point,

AP DISC / TRIM INT button .......................... PRESS, Continue visually for a normal landing
Or

GO AROUND (GA) button.............................. PRESS, Execute Missed Approach Procedure

Apply GA power.

Set missed approach altitude in the altitude preselect.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
LOC BC APPROACH
This procedure applies only if the optional CHF and GPS navigator is installed.
1. Navigation Source. .................................................................................... SELECT CDI to VHF Nav
Tune and Identify an ILS station frequency
2. Course Pointer .................................................................................. SET CDI to LOC Front Course
NOTE
Ensure that the current heading will result in a capture of the selected course.
3. NAV Key .................................................................................................. PRESS, verify BC ARMED
(when heading is within 75 degrees of BC course)
4. BC Mode ............................................................ VERIFY airplane Captures and Tracks BC Course
5. Altitude Preselect ................................................................ SET to next required step down altitude
6. Missed Approach Altitude ......................................................... SET when in ALT mode at the MDA
7. At Missed Approach Point:

AP DISC / TRIM INT button .......................... PRESS, Continue visually for a normal landing
Or

GO AROUND (GA) button.............................. PRESS, Execute Missed Approach Procedure

Apply GA power.

Set missed approach altitude in the altitude preselect.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
190-02291-14 Rev. 2
GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 4–11
VOR Approach
This procedure applies only if the optional VHF navigator is installed.
1. Navigation Source. .................................................................................... SELECT CDI to VHF Nav
Tune and identify the station frequency
2. Course Pointer .................................................................................SET CDI to the Desired Course
NOTE
Ensure that the current heading will result in a capture of the selected course.
3. NAV Key ............................................................................................... PRESS, verify VOR ARMED
4. VOR Mode....................................................... VERIFY airplane Captures and Tracks VOR Course
5. Missed Approach Altitude ................................................... SET to next required step down altitude
6. Missed Approach Altitude ............................................................... SET when in ALT mode at MDA
7. At Missed Approach Point:

AP DISC / TRIM INT button .......................... PRESS, Continue visually for a normal landing
Or

GO AROUND (GA) button.............................. PRESS, Execute Missed Approach Procedure

Apply GA power.

Set missed approach altitude in the altitude preselect.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
DISABLING ESP
ESP can be disabled on the G5 attitude indicator with the following procedure. ESP will default to “Enabled” on
the next power cycle.
1. G5 Knob. ................................................................................................................................ PRESS
2. ESP ...................................................................................................................................... SELECT
3. G5 Knob ................................................................................................................................. PRESS
ESP can be disabled on the G3X with the following procedure. ESP will default to “Enabled” on the next power
cycle.
1. Autopilot Status Box .............................................................................................................. TOUCH
2. ESP Button ............................................................................................................................ TOUCH
3. Back Button ............................................................................................................................ PRESS
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
SECTION 5 – PERFORMANCE
No Change.
190-02291-14 Rev. 2
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190-02291-14 Rev. 2
SECTION 6 – WEIGHT AND BALANCE
No change to loading information. Refer to current weight and balance report and equipment list for changes to
empty weight/moment and installed equipment.
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190-02291-14 Rev. 2
SECTION 7 – SYSTEM DESCRIPTION
AFCS OVERVIEW
The GFC 500 is a digital Automatic Flight Control System (AFCS). It is a two-axis autopilot and flight director
system which provides the pilot with the following features:
G5 Outputs to Autopilot — The G5 flight instrument (when installed) provides attitude, rate, and acceleration
information to the servos. Additionally, indicated airspeed, vertical speed, pressure altitude and GPS information
are sent to the autopilot for mode control.
G3X Outputs to Autopilot — The G3X electronic flight instrument system provides attitude, rate, and
acceleration information to the servos. Additionally, indicated airspeed, vertical speed, pressure altitude and
GPS information are sent to the autopilot for mode control.
Flight Director (FD) — The flight director processing occurs in the G5 or G3X instrument. Selected modes for
the flight director are displayed on the G5 or G3X autopilot status box.
The flight director provides:
 Command Bars showing pitch/roll guidance
 Vertical / lateral mode selection and processing
Autopilot (AP) — Autopilot operation occurs within the pitch, roll, and optional pitch trim servo. It also provides
servo monitoring, and automatic flight control in response to flight director steering commands, attitude and rate
information, and airspeed.
Optional Electric Pitch Trim — The pitch trim servo provides manual electric pitch trim capability when the
autopilot is not engaged. The trim servo provides automatic pitch trim when the autopilot is engaged and the
airplane is in the air. Automatic trim functionality is disabled on the ground.
GMC 507 — Pilot commands to the autopilot and flight director are entered through the GMC 507 autopilot mode
panel. The GMC 507 contains internal sensors which calculate the aircraft attitude, attitude rate and
accelerations. These inertial sensors are completely independent from the sensors within the G5 or G3X and
the rest of the autopilot system, and are not used for the flight director, autopilot, trim or ESP functions. They are
used solely to provide independent monitoring of the GFC 500.
Airspeed and Altitude Information — The GFC 500 requires airspeed and altitude information from the G5 or
G3X instrument.
Other components of the AFCS include the GSA 28 pitch, roll, optional yaw servo, and optional pitch trim servo
that also contain autopilot processors, control wheel mounted elevator trim switch (if trim servo is installed),
control wheel mounted autopilot disconnect and trim interrupt button (AP DISC / TRIM INT), and a Go-Around
(GA) button.
Underspeed Protection (USP) — The GFC 500 will provide Underspeed Protection when the autopilot is
engaged.
When the minimum airspeed of 78 KIAS is reached, a visual MINSPD message will appear above the airspeed
tape and the autopilot will lower the nose to maintain 78 KIAS. An aural “AIRSPEED, AIRSPEED” voice alert will
sound for installations connected to an audio panel.
Underspeed Protection is inhibited when the airspeed exceeds 83 KIAS.
Overspeed Protection (OSP) — The GFC 500 will provide Overspeed Protection when the autopilot is engaged.
When the maximum airspeed of 185 KIAS is reached, visual MAXSPD message will appear above the airspeed
tape and the autopilot will raise the nose of the aircraft to avoid exceeding 185 KIAS. An aural “AIRSPEED,
AIRSPEED” voice alert will sound for installations connected to an audio panel.
Overspeed Protection is inhibited when the airspeed is below 180 KIAS.
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AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 7–1
Coupled Go-Around — Pressing the GA button will not disengage the autopilot. Instead, the autopilot will
attempt to capture and track the flight director command bars. If insufficient airplane performance is available to
follow the commands, the autopilot will enter Underspeed Protection mode at the minimum airspeed.
Electronic Stability and Protection (ESP) — The GFC 500 will provide Electronic Stability and Protection when
the autopilot is not engaged.
Electronic Stability and Protection (ESP) uses the autopilot servos to assist the pilot in maintaining the airplane in
a safe flight condition within the airplane’s normal pitch, roll and airspeed envelopes.
Electronic Stability and Protection is activated when the pilot allows the airplane to exceed one or more conditions
beyond normal flight as defined below:

Pitch attitude beyond normal flight (+20°, -15°)

Roll attitude beyond normal flight (45°)

High airspeed beyond normal flight (above 196 KIAS)

Low airspeed below normal flight (below 73 KIAS)
ESP requires:

Pitch and Roll servos are installed and functioning

Autopilot not engaged

The GPS altitude above ground is more than 200 feet (for low airspeed mode)

Aircraft is within the autopilot engagement envelope (+/-50° in pitch and +/-75° in roll)
Protection for excessive Pitch, Roll, and Airspeed is provided when the limit thresholds are first exceeded, which
engages the appropriate servo in ESP mode at a nominal torque level to bring the airplane back within the normal
flight envelope. If the airplane deviates further from the normal flight envelope, the servo torque will increase
until the maximum torque level is reached in an attempt to return the airplane into the normal flight envelope.
Once the airplane returns to within the normal flight envelope, ESP will deactivate the autopilot servos.
When the normal flight envelope thresholds have been exceeded for more than 10 seconds, ESP Autolevel Mode
is activated. Autolevel Mode engages the autopilot to bring the airplane back into straight and level flight based
on 0° roll angle and 0 FPM vertical speed. An aural, “ENGAGING AUTOPILOT” (or a Sonalert tone), sounds
and the Flight Director mode annunciation will indicate LVL for the pitch and roll modes.
Any time an ESP mode is active, the pilot can interrupt ESP by using the Autopilot Disconnect (AP DISC / TRIM
INT) switch, or simply override ESP by overpowering the autopilot servos. The pilot may also disable ESP
through the G5 menu.
The engagement and disengagement attitude limits are displayed with double hash marks on the roll indicator
depending on the airplane attitude and whether or not ESP is active in roll. When ESP is inactive (roll attitude
within nominal limits) only the engagement limit indications are displayed in order to reduce clutter on the roll
indicator.
Display symbology implemented for ESP is illustrated in the following figures.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
Engagement Limit
Indication at 45°
Figure 7-1: Nominal Roll Attitude ESP Engagement Limit Indications
Once ESP becomes active in roll, the engagement limit indication that was crossed (either Left or Right) will move
to the lower disengagement limit indication. The opposite roll limit remains at the engagement limit.
Lower Disengagement Limit
Indication depicted at 30° after ESP
activation
Figure 7-2: Engagement Limit Indications Upon ESP Activation
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AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 7–3
Disconnect Methods
The following conditions will cause the autopilot to automatically disconnect:

Electrical power failure, including pulling the AUTOPILOT circuit breaker.

Internal autopilot system failure (including internal AHRS failure).
The following pilot actions will cause the autopilot to disconnect:

Pressing the red AP DISC / TRIM INT button on the pilot’s control wheel.

Actuating the manual electric trim switch (if installed).

Pushing the AP Key on the GMC 507 mode controller when the autopilot is engaged.

Pulling the AUTOPILOT circuit breaker.
The red AP DISC / TRIM INT button on the pilot’s control wheel will interrupt power to the manual electric trim for
as long as the switch is depressed.
AUTOPILOT CONTROL UNIT AND DISPLAY
Figure 7-3: GMC 507 Control Unit (Reference Only)
Figure 7-4: G5 Display (Reference Only)
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 7–4
190-02291-14 Rev. 2
The following tables list the available AFCS vertical and lateral modes with their corresponding controls and
annunciations. The UP/DN wheel can be used to change the vertical mode reference while operating in Pitch
Hold, Vertical Speed, Altitude Hold, or IAS mode. Increments of change and maximum ranges of values for
each of these references using the UP/DN wheel are also listed in the table.
AFCS VERTICAL MODES
Control
Annunciation
Reference Range
Reference Change
Increment
(default)
PIT
20° Nose Up
15° Nose Down
0.5°
*
ALTS
ALT Key
ALT nnnnn
Vertical Speed
VS Key
VS nnnn
-2000 to +2000
FPM
100 FPM
IAS Hold
IAS Key
IAS nnn
78 to 185 KIAS
1 KT
VNAV
Key
VNAV
**
ALTV
APR Key
GP
GS
GA Button
TO or GA
7°
LVL Key
LVL
Zero Vertical
Speed
Vertical Mode
Pitch Hold
Selected Altitude
Capture
Altitude Hold
Vertical Path
Tracking (VNAV)
VNAV Target
Altitude Capture
Glidepath
Glideslope
Takeoff or Go
Around
Level (LVL)
ESP High Pitch
Engagement
ESP Low Pitch
Engagement
ESP High
Airspeed
Engagement
ESP Low
Airspeed
Engagement
10 FT
ESP High Pitch Attitude engages at 20° nose up
ESP Low Pitch Attitude engages at 15° nose
down
ESP High Airspeed engages at above VNE + 1
KIAS
When above 200 FT AGL, ESP Low Airspeed
engages at below Vs + 5 KIAS. (This mode only
available if height above terrain is available from
a compatible Garmin GPS).
* ALTS arms automatically when PIT, VS, IAS, or GA is active.
** ALTV arms automatically if the VNAV Target Altitude is to be captured instead of the Selected
Altitude.
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Page 7–5
AFCS LATERAL MODES
Lateral Mode
Maximum Roll
Command Limit
Control
Annunciation
Roll Mode
(default)
ROL
30°
Heading Select
HDG Key
HDG
30°
Track Select
TRK Key
TRK
30°
Navigation, GPS Arm/Capture/Track
GPS
30°
Navigation, VOR Enroute and Approach
Arm/Capture/Track
VOR
30°
LOC
30°
BC
30°
GPS
30°
LOC
30°
Navigation, LOC Arm/Capture/Track (No
Glideslope)
NAV Key
Backcourse Arm/Capture/Track
Approach, GPS Arm/Capture/Track
(Glidepath Mode Automatically Armed, if
available)
APR Key
Approach, ILS Arm/Capture/Track
(Glideslope Mode Automatically Armed)
Takeoff or Go Around
LVL (Level)
ESP Roll Attitude Engagement
GA Button
TO or GA
Wings Level
LVL Key
LVL
Wings Level
ESP Roll
Attitude
engages at 45°
The autopilot may be engaged within the following ranges:
Pitch 50° nose up to 50° nose down
Roll ±75°
If the above pitch or roll limits are exceeded while the autopilot is engaged, the autopilot will disconnect. Engaging
the autopilot outside of its command limits, but within its engagement limits, will cause the autopilot to return the
aircraft within command limits. The autopilot is capable of commanding the aircraft in the following ranges:
Pitch 20° nose up to 15° nose down
Roll ±30°
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
PREFLIGHT TEST
During the preflight test the G5 or G3X will display PFT in the autopilot status box. The PFT annunciation is
removed at the completion of the preflight test. If GFC 500 fails the PFT, a yellow AP with a red X is displayed in
the autopilot status box on the G5 or G3X.
MESSAGES AND ANNUNCIATIONS
Autopilot Messages
AFCS Controller Key
Stuck
The system has sensed a key input on the GMC 507 for 30 seconds or
longer.
AFCS Controller Audio
Database Missing
The audio database is missing from the GMC 507. The aural voice alerts
will not be heard.
Servo Clutch Fault
One or more autopilot servos has a stuck clutch. The servo needs service.
Servo Trim Input Fault
The inputs to the trim system are invalid. The trim system needs service.
Autopilot Annunciations
AFCS
Autopilot has failed. Autopilot and trim are inoperative and flight director is
not available.
AP
Autopilot normal disconnect.
AP
Autopilot abnormal disconnect.
AP
Autopilot has failed. The autopilot is inoperative. FD modes may still be
available.
MAXSPD
Autopilot Overspeed Protection mode is active. Autopilot will raise the nose
to limit the aircraft’s speed.
MINSPD
Autopilot Underspeed Protection mode is active. Autopilot will lower the
nose to prevent the aircraft’s speed from decreasing.
PFT
Autopilot preflight test is in progress.
PTRIM
Pitch Trim Fail – Manual Electric Pitch Trim is inoperative.
TRIM DOWN
Elevator Trim Down – Autopilot is holding elevator nose down force. The
pitch trim needs to be adjusted nose down.
TRIM UP
Elevator Trim Up – Autopilot is holding elevator nose up force. The pitch
trim needs to be adjusted nose up.
YD
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Yaw Damper normal disconnect.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 7–7
Autopilot Messages
YD
Yaw Damper abnormal disconnect.
AP
Yaw Damper has failed. The Yaw Damper is inoperative.
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
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190-02291-14 Rev. 2
LIGHTING
When the aircraft’s dimming bus is selected off, or full dim, GMC 507 mode control panel lighting is controlled by
integrated photocells which sense the ambient cockpit lighting. When the aircraft’s dimming bus is used to control
cockpit lighting, the GMC 507 mode control panel lighting is controlled by the dimming bus.
190-02291-14 Rev. 2
AFMS – GFC 500 Autopilot in Textron (Cessna) 210 Series
Page 7–9
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