Garmin | GFC™ 500 Digital Autopilot | Garmin GFC™ 500 Digital Autopilot Airplane Flight Manual Supplement, GFC 500 Autopilot in Textron S35, V35, V35A, V35B

Garmin GFC™ 500 Digital Autopilot Airplane Flight Manual Supplement, GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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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 S35, V35, V35A, V35B
190-02291-09 Rev. 1
Garmin International, Inc
Log of Revisions
FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT
GFC 500 Autopilot with ESP
Installed in
Textron Aviation S35, V35, V35A, V35B
REV
NO.
PAGE NO(S)
DESCRIPTION
DATE OF
APPROVAL
FAA APPROVED
1
ALL
Original Issue
See Cover
See Cover
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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190-02291-09 Rev. 1
Table of Contents
Section 1 – General .................................................................................................... 1-1
USE OF THE SUPPLEMENT ................................................................................................................ 1-1
ABBREVIATIONS AND TERMINOLOGY ............................................................................................. 1-2
INSTALLED EQUIPMENT INTERFACES ............................................................................................. 1-3
INSTALLED FEATURES CHECKLIST ................................................................................................. 1-4
Section 2 – Limitations .............................................................................................. 2-1
Section 3 – Emergency Procedures ......................................................................... 3-1
AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY.................................................................... 3-1
AUTOPILOT FAILURE / ABNORMAL DISCONNECT ......................................................................... 3-2
YAW AXIS FAILURE / ABNORMAL YAW DAMPER DISCONNECT .................................................. 3-2
PITCH TRIM FAILURE .......................................................................................................................... 3-2
ESP ACTIVATION ................................................................................................................................. 3-3
OVERSPEED PROTECTION (MAXSPD).............................................................................................. 3-3
UNDERSPEED PROTECTION (MINSPD) ............................................................................................ 3-3
Section 3A – Abnormal Procedures ......................................................................... 3-5
AUTOPILOT ABNORMAL DISCONNECT ............................................................................................ 3-5
AUTOPILOT PRE-FLIGHT TEST FAIL ................................................................................................. 3-5
LOSS OF NAVIGATION INFORMATION.............................................................................................. 3-5
LOSS OF AIRSPEED DATA ................................................................................................................. 3-6
LOSS OF ALTITUDE DATA .................................................................................................................. 3-6
LOSS OF GPS INFORMATION ............................................................................................................. 3-6
HEADING DATA SOURCE FAILURE ................................................................................................... 3-7
ELEVATOR MISTRIM ............................................................................................................................ 3-7
YAW DAMPER DISCONNECT .............................................................................................................. 3-8
Section 4 – Normal Procedures ................................................................................ 4-1
GFC 500 POWER UP ............................................................................................................................ 4-1
FLIGHT DIRECTOR / AUTOPILOT NORMAL OPERATING PROCEDURES ..................................... 4-1
MANUAL AUTOPILOT DISCONNECT ................................................................................................. 4-2
VERTICAL MODES ............................................................................................................................... 4-2
VERTICAL SPEED (VS) MODE ......................................................................................................... 4-2
INDICATED AIRSPEED (IAS) MODE ................................................................................................ 4-2
ALTITUDE HOLD (ALT) MODE, MANUAL CAPTURE ...................................................................... 4-2
GO AROUND ...................................................................................................................................... 4-3
MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED .................................................................... 4-3
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page iii
LATERAL MODES................................................................................................................................. 4-4
HEADING MODE (HDG) .................................................................................................................... 4-4
TRACK MODE (TRK) ......................................................................................................................... 4-4
NAVIGATION (VOR) .......................................................................................................................... 4-4
NAVIGATION (GPS) ........................................................................................................................... 4-5
APPROACHES ...................................................................................................................................... 4-5
ILS APPROACH ................................................................................................................................. 4-5
LOC APPROACH (GS out) ................................................................................................................. 4-6
GPS APPROACH (LPV, LNAV/VNAV, LP+V, or LNAV+V) ............................................................... 4-6
GPS APPROACH (LP, LNAV) ............................................................................................................ 4-7
LOC BC APPROACH ......................................................................................................................... 4-8
VOR APPROACH ............................................................................................................................... 4-9
DISABLING ESP.................................................................................................................................... 4-9
Section 5 – Performance ........................................................................................... 5-1
Section 6 – Weight and Balance ............................................................................... 6-1
Section 7 – System Description ................................................................................ 7-1
AFCS OVERVIEW ................................................................................................................................. 7-1
AUTOPILOT CONTROL UNIT AND DISPLAY ..................................................................................... 7-4
PREFLIGHT TEST ................................................................................................................................. 7-7
MESSAGES AND ANNUNCIATIONS ................................................................................................... 7-7
LIGHTING .............................................................................................................................................. 7-9
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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190-02291-09 Rev. 1
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.
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 1–1
ABBREVIATIONS AND TERMINOLOGY
The following glossary is applicable within the airplane flight manual supplement
AFCS
AFM
AFMS
AGL
AHRS
ALT
AP
APR
ATC
BC
CDI
DA
DISC
DWG
ESP
FAA
FAF
FD
GA
GFC 500
GMC 507
GNSS
GPS
GS
GSA
HDG
IAS
ILS
INT
KIAS
LNAV
LNAV+V
Automatic Flight Control System
Airplane Flight Manual
Airplane Flight Manual
Supplement
Above Ground Level
Attitude and Heading Reference
System
Altitude
Autopilot
Approach
Air Traffic Control
Back Course Approach
Course Deviation Indicator
Decision Altitude
Disconnect
Drawing
Electronic Stability and Protection
Federal Aviation Administration
Final Approach Fix
Flight Director
Go Around
Garmin Autopilot
Autopilot Mode Control Panel
Global Navigation Satellite
System
Global Positioning System
Glideslope
Garmin Servo Actuator
AFCS heading mode
Indicated Airspeed
Instrument Landing System
Interrupt
Knots Indicated Airspeed
Lateral Navigation
Lateral Navigation with Advisory
Vertical Guidance
LNAV/VNAV Lateral Navigation / Vertical
Navigation Approach
LOC
Localizer (no glideslope available)
LP
Localizer Performance
LP+V
Localizer Performance with
Advisory Vertical Guidance
LPV
Localizer Performance with
Vertical Guidance
LVL
Level
MDA
Minimum Descent Altitude
PFT
Preflight Test
POH
Pilot’s Operating Handbook
STC
Supplemental Type Certificate
TO
Takeoff
TRK
Track
VHF
Very High Frequency
VOR
VHF Omni-directional Range
VS
Vertical Speed
YD
Yaw Damper
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 1–2
190-02291-09 Rev. 1
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
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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


Vertical Autopilot Modes
 Pitch (PIT)
 Level (Zero vertical speed)
 Go Around (GA)
 Altitude Hold
 Vertical Speed
 Altitude Capture via Altitude Preselect
 Indicated Airspeed (IAS)
GPS Approach Glidepath
ILS Glideslope


Electronic Stability and Protection
 Pitch/Roll Attitude
 High Speed Protection
Low Speed Protection

Lateral Autopilot Modes
 Roll (ROL)
 Level (Wings Level)
 Go Around (GA)
Heading
 Track
GPS Navigation
VHF Navigation
Approach Mode
GPS
VOR/LOC




AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 1–4


190-02291-09 Rev. 1
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.
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
5.20
A pilot must be seated in the left pilot’s seat, with seatbelt fastened, during all autopilot operations.
Do not use autopilot or yaw damper during takeoff and landing.
The GFC 500 AFCS preflight test must complete successfully prior to use of the autopilot, flight director or
manual electric trim.
The maximum fuel imbalance with the autopilot engaged is 15 gallons.
Autopilot maximum engagement speed is 187 Knots (215 MPH).
Autopilot minimum engagement speed is 75 Knots (86 MPH)
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.
190-02291-09 Rev. 1
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190-02291-09 Rev. 1
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
WARNING
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.
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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 .....................................................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 knob 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 will remain inoperative.
PITCH TRIM FAILURE
(Red PTRIM on G5 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 S35, V35, V35A, V35B
Page 3–2
190-02291-09 Rev. 1
ESP ACTIVATION
1. Throttle ..................................................................................................................... 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 played, (or a Sonalert tone will
sound for installations without a supported audio panel) and the autopilot will roll the
wings level and fly at 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.
OVERSPEED PROTECTION (MAXSPD)
(MAXSPD displayed on G5, AIRSPEED – AIRSPEED Aural sounds)
1. Throttle ............................................................................................................................... REDUCE
2. Aircraft Attitude and Altitude ......................................................................................... MONITOR
After overspeed condition is corrected:
3. Autopilot .......................................RESELECT VERTICAL AND LATERAL MODES (if necessary)
4. Throttle ........................................................................................................... ADJUST as necessary
NOTE
Overspeed protection mode provides a pitch up command to decelerate the airplane at
or below the maximum autopilot operating speed.
UNDERSPEED PROTECTION (MINSPD)
(MINSPD displayed on G5, AIRSPEED – AIRSPEED Aural sounds)
1. Throttle ............................... 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. Throttle ........................................................................................................... ADJUST as necessary
NOTE
Autopilot Underspeed Protection Mode provides a pitch down command to maintain 75
KIAS.
190-02291-09 Rev. 1
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190-02291-09 Rev. 1
SECTION 3A – ABNORMAL PROCEDURES
AUTOPILOT ABNORMAL DISCONNECT
(Red AP in the G5 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 be functional.
AUTOPILOT PRE-FLIGHT TEST FAIL
(Amber AP with a red X in G5 autopilot status box)
1. Indicates the AFCS system failed the automatic Pre-Flight test.
NOTE
The autopilot, yaw damper (if installed), ESP, and electric elevator trim are inoperative.
Flight director will still function.
LOSS OF NAVIGATION INFORMATION
This procedure applies only if the optional GPS and/or VHF navigator installed:
(Amber GPS, VOR, LOC, or BC flashes for 10 seconds on G5.)
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)
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 3–5
LOSS OF AIRSPEED DATA
(Red X through airspeed tape on the G5 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 (if a pitch trim servo is installed).
LOSS OF ALTITUDE DATA
(Red X through altitude tape on the G5 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 Back
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:
1. AP DISC / TRIM INT button ............................................. PRESS, Continue the approach manually
Or
2. Missed Approach Procedure .................................................................... EXECUTE (as applicable)
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 3–6
190-02291-09 Rev. 1
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
Without a heading source to the navigator, the following features will not operate:

GPSS will not be provided to the autopilot for heading legs.

Map cannot be oriented to Heading Up.

Track information will be displayed on the G5.
ELEVATOR MISTRIM
(Amber TRIM UP or TRIM DOWN displayed on the G5)
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.
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 3–7
If the optional pitch trim servo is installed:
WARNING
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
WARNING
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.
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 S35, V35, V35A, V35B
Page 3–8
190-02291-09 Rev. 1
SECTION 4 – NORMAL PROCEDURES
GFC 500 POWER UP
During the preflight test the G5 will display PFT in the autopilot status box. The autopilot disconnect
tone sounds at the completion of the preflight test. 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. 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 yoke. An autopilot disconnect tone will sound and
an amber AP will be annunciated on the G5 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 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 Key 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 Key is pressed, or the red AP DISC / TRIM INT button is
pressed.
– Pulling the autopilot circuit breaker.
In the event of unexpected autopilot behavior, pressing 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.
190-02291-09 Rev. 1
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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
VERTICAL MODES
VERTICAL SPEED (VS) MODE
1. Altitude Preselect ......................................................................................... SET to Desired Altitude
2. VS Key ............................... PRESS, 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. Throttle ................................................................................ ADJUST, 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
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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190-02291-09 Rev. 1
GO AROUND
1. GO AROUND button ....................................................................... PRESS – Verify GA / GA on G5
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.
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 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)
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 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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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.
NOTE
If heading bug is reset too quickly, the airplane could turn in the opposite direction as the
heading bug’s movement.
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.
NOTE
If track bug is reset too quickly, the airplane could turn in the opposite direction as the
track bug’s movement.
NAVIGATION (VOR)
This mode will only be available 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
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.
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190-02291-09 Rev. 1
NAVIGATION (GPS)
This mode will only be available if 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.
APPROACHES
ILS APPROACH
This mode will only be available if the optional VHF and GPS navigator is 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. APR Key .................................................................................. PRESS, verify LOC and GS ARMED
4. LOC and GS Mode.......................................... VERIFY airplane Captures and Tracks LOC and GS
5. Missed Approach Altitude ......................................................................... SET in Altitude preselect.
At Decision Altitude (DA),
6. AP DISC / TRIM INT button .................................... PRESS, Continue visually for a normal landing
Or
7. GO AROUND (GA) button ....................................... PRESS, Execute Missed Approach Procedure
8. Apply GA power.
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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.
LOC APPROACH (GS out)
This procedure applies only if the optional VHF and GPS navigator is 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
At Missed Approach Point,
7. AP DISC / TRIM INT button .................................... PRESS, Continue visually for a normal landing
Or
8. GO AROUND (GA) button ....................................... PRESS, Execute Missed Approach Procedure
9. Apply GA power.
NOTE
Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to
fly the missed approach procedure.
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.
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190-02291-09 Rev. 1
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
At DA (LPV or LNAV/VNAV approach), or MDA and Missed Approach Point (LP+V or LNAV+V),
6. AP DISC / TRIM INT button .................................... PRESS, Continue visually for a normal landing
Or
7. GO AROUND (GA) button ....................................... PRESS, Execute Missed Approach Procedure
8. Apply GA power.
9. 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.
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
At Missed Approach Point,
7. AP DISC / TRIM INT button .................................... PRESS, Continue visually for a normal landing
Or
8. GO AROUND (GA) button ....................................... PRESS, Execute Missed Approach Procedure
9. Apply GA power.
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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Page 4–7
LOC BC APPROACH
This procedure applies only if the optional VHF 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 Back Course)
4. BC Mode ......................................................... VERIFY airplane Captures and Tracks Back Course
5. Altitude Preselect ................................................................ SET to next required step down altitude
6. Missed Approach Altitude ......................................................... SET when in ALT mode at the MDA
At Missed Approach Point:
7. AP DISC / TRIM INT button .................................... PRESS, Continue visually for a normal landing
Or
8. GO AROUND (GA) button ....................................... PRESS, Execute Missed Approach Procedure
9. Apply GA power.
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 S35, V35, V35A, V35B
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190-02291-09 Rev. 1
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. Altitude Preselect ................................................................ SET to next required step down altitude
6. Missed Approach Altitude ......................................................... SET when in ALT mode at the MDA
At Missed Approach Point,
7. AP DISC / TRIM INT button .................................... PRESS, Continue visually for a normal landing
Or
8. GO AROUND (GA) button ....................................... PRESS, Execute Missed Approach Procedure
9. Apply GA power.
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
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SECTION 5 – PERFORMANCE
No Change.
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190-02291-09 Rev. 1
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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190-02291-09 Rev. 1
SECTION 7 – SYSTEM DESCRIPTION
AFCS OVERVIEW
The GFC 500 is a digital Automatic Flight Control System (AFCS). It is a two-axis autopilot, with optional
3rd axis yaw damper, and flight director system which provides the pilot with the following features:
G5 Outputs to Autopilot — The G5 flight instrument 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 instrument. Selected modes for
the flight director are displayed on the G5 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.
Optional Yaw Damper (YD) — The yaw servo provides Dutch roll damping and turn coordination in
response to yaw rate, roll angle, lateral acceleration, and airspeed.
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 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 instrument.
Other components of the AFCS include the GSA 28 pitch, roll, and optional pitch trim servo, optional yaw
servo, that also contain autopilot processors, control wheel mounted elevator trim switch (if trim servo is
installed), control wheel mounted autopilot / yaw damper 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 75 KIAS is reached, a visual MINSPD message will appear above the
airspeed tape and the autopilot will lower the nose to maintain 75 KIAS. An aural “AIRSPEED,
AIRSPEED” voice alert will sound for installations connected to an audio panel.
Underspeed Protection is exited automatically when airspeed exceeds 80 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 the maximum
configured airspeed. An aural “AIRSPEED, AIRSPEED” voice alert will sound for installations connected
to an audio panel.
Overspeed Protection is exited automatically when airspeed is reduced below 180 KIAS.
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AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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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 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 invoked when the pilot allows the airplane to exceed one or more
conditions beyond normal flight defined below:

Pitch attitude beyond normal flight (+20°, -15°)

Roll attitude beyond normal flight (45°)

High airspeed beyond normal flight (above 198 KIAS)

Low airspeed below normal flight (below 65 KIAS)
The conditions that are required for ESP to be available are:

Pitch and Roll servos available

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” alert (or a Sonalert tone) sounds and the Flight Director mode annunciation will indicate
LVL for the pitch and roll modes.
Anytime 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 a G5 menu option.
The engagement and disengagement attitude limits are displayed with double hash marks on the roll
indicator according to 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 S35, V35, V35A, V35B
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190-02291-09 Rev. 1
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 S35, V35, V35A, V35B
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 S35, V35, V35A, V35B
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190-02291-09 Rev. 1
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
60 to 150 KT
1 KT
VNV Key
N/A
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)
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 198 KIAS
When above 200 FT AGL, ESP Low Airspeed
engages at 65 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.
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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°
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190-02291-09 Rev. 1
PREFLIGHT TEST
During the preflight test the G5 will display PFT in the autopilot status box. The autopilot disconnect tone
sounds at the completion of the preflight test and the PFT annunciation is removed. If GFC 500 fails the
PFT, a yellow AP with a red X is displayed in the autopilot status box on the G5.
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 S35, V35, V35A, V35B
Page 7–7
Autopilot Messages
YD
Yaw Damper abnormal disconnect.
YD
Yaw Damper has failed. The Yaw Damper is inoperative.
AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
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190-02291-09 Rev. 1
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.
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AFMS – GFC 500 Autopilot in Textron S35, V35, V35A, V35B
Page 7–9
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