Garmin GFC 600 User manual

GFC 600 Autopilot Installed in Piper PA-46-310P/350P 190-02011-11 Rev. 2
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Telephone: [phone]
www.garmin.com

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Garmin International, Inc
Log of Revisions
FAA Approved Airplane Flight Manual Supplement for
GFC 600 Autopilot
Installed in Piper PA46-310P/350P
REV
NO. PAGE NO(S) DESCRIPTION DATE OF
APPROVAL
FAA APPROVED
1 ALL Original Issue 8/5/2019 Robert G. Murray
Garmin ODA STC
Unit Administrator
2 ALL Added PA-46-310P Flap Limitation See Cover See Cover

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Table of Contents
Section 1 – General....................................................................................................... 7
USE OF THE SUPPLEMENT ................................................................................................................... 7
ABBREVIATIONS AND TERMINOLOGY................................................................................................ 8
INSTALLED EQUIPMENT INTERFACES................................................................................................ 9
INSTALLED FEATURES CHECKLIST .................................................................................................. 10
Section 2 – Limitations ............................................................................................... 11
Section 3 – Emergency Procedures .......................................................................... 13
AUTOPILOT MALFUNCTION / PITCH TRIM RUNAWAY..................................................................... 13
AUTOPILOT FAILURE / ABNORMAL DISCONNECT .......................................................................... 14
ESP ACTIVATION .................................................................................................................................. 14
OVERSPEED PROTECTION (MAXSPEED).......................................................................................... 15
UNDERSPEED PROTECTION (MINSPEED)......................................................................................... 15
ENGINE FAILURE .................................................................................................................................. 16
Section 3A – Abnormal Procedures .......................................................................... 17
AUTOPILOT PRE-FLIGHT TEST FAIL.................................................................................................. 17
LOSS OF AIR DATA............................................................................................................................... 17
MANUAL AUTOPILOT DISCONNECT .................................................................................................. 17
LOSS OF NAVIGATION INFORMATION............................................................................................... 18
YAW DAMPER FAILURE (if installed).................................................................................................. 18
ELEVATOR MISTRIM............................................................................................................................. 19
AILERON MISTRIM ................................................................................................................................ 20
RUDDER MISTRIM ................................................................................................................................. 21
PITCH TRIM FAILURE ........................................................................................................................... 22
Section 4 – Normal Procedures ................................................................................. 23
GFC 600 Power Up ................................................................................................................................ 23
Flight Director / Autopilot Normal Operating Procedures................................................................. 23
VERTICAL MODES ............................................................................................................................. 25
LATERAL MODES............................................................................................................................... 29
APPROACHES .................................................................................................................................... 31
DISABLING ESP.................................................................................................................................. 34
Section 5 – Performance ............................................................................................ 35
Section 6 – Weight and Balance ................................................................................ 37
Section 7 – System Description................................................................................. 39

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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 600 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:
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.
WARNING

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ABBREVIATIONS AND TERMINOLOGY
The following glossary is applicable within the airplane flight manual supplement
AFCS Automatic Flight Control System
AGL Above Ground Level
AFM Airplane Flight Manual
AFMS Airplane Flight Manual Supplement
AP Autopilot
BC Back Course Approach
CDI Course Deviation Indicator
CWS Control Wheel Steering
DA Decision Altitude
ESP Electronic Stability and Protection
FAA Federal Aviation Administration
GA Go Around
GFC 600 Garmin Autopilot
GI 285 Garmin Remote Autopilot Mode Annunciator Panel
GMC 605 Autopilot Mode Control Panel
GPS Global Positioning System
HDG AFCS heading mode
HSI Horizontal Situation Indicator
ILS Instrument Landing System
KIAS Knots Indicated Airspeed
KTS Knots
LED Light Emitting Diode
LNAV Lateral Navigation
LNAV + V 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
MDA Minimum Descent Altitude
N/A Not Applicable
POH Pilot’s Operating Handbook
STC Supplemental Type Certificate
VHF Very High Frequency
VNAV Vertical Navigation
VOR VHF Omni-directional Range

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INSTALLED EQUIPMENT INTERFACES
The following is the list of installed equipment and functions associated with the GFC 600 Autopilot
installation in this airplane.
DEVICE TYPE Manufacturer / Model
If not installed, note N/A
Additional Information
GPS Navigator #1 Roll Steering Capable?
YES NO
Is GPS #1 MapMX data provided to
GFC 600 internal attitude source?
YES NO
GPS Navigator #2 Roll Steering Capable?
YES NO
Is #2 GPS navigation interfaced to GFC
600?
YES NO
Is GPS #2 MapMX data provided to
GFC 600 internal attitude source?
YES NO
ADS-B Out Transponder
with internal GPS MapMX data
provided to GFC 600 internal
attitude source
Primary Flight Display
HSI
DG
Air Data Computer OR;
Air Data Module
Is air data provided to GFC 600 internal
attitude source?
YES NO
VHF Nav Radio #1
VHF Nav Radio #2 Is #2 NAV interfaced to GFC 600?
YES NO

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INSTALLED FEATURES CHECKLIST
The checked autopilot modes and features are available on this aircraft.
Basic AP Features Electronic Stability and Protection
Flight Director Pitch/Roll Attitude
Control Wheel Steering High Speed Protection
Yaw Damper Low Speed Protection
Manual Electric Pitch Trim
Auto Pitch Trim
Overspeed Protection
Underspeed Protection
Vertical Autopilot Modes Lateral Autopilot Modes
Pitch (PIT) Roll (ROL)
Level (Zero vertical speed) Level (Wings Level)
Go Around (GA) Go Around (GA)
Altitude Hold Heading
Vertical Speed GPS Navigation
Altitude Capture via Altitude Preselect Roll Steering
Indicated Airspeed (IAS) VHF Navigation
Vertical Navigation (VNV) VOR
VNAV Target Alt Capture Approach Mode
GPS Approach Glidepath GPS
ILS Glideslope VOR
LOC
LOC BC

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Section 2 – Limitations
This AFMS is applicable to the software versions shown below:
Software Item Software Version (or later FAA Approved version for this STC)
GFC 600 Software Version V361000
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 600 AFCS preflight test must complete successfully prior to use of the autopilot, flight director or
manual electric trim.
Autopilot maximum engagement speed is 172 KIAS.
Autopilot minimum engagement speed is 80 KIAS.
The autopilot must be disengaged below 200 feet AGL during approach operations and below 800 feet
AGL during all other operations.
The GFC 600 autopilot is approved for Category 1 precision approaches and non-precision approaches
only.
Maximum fuel imbalance with autopilot engaged is 10 gallons.
For PA-46-310P, s/n 46-8408001 thru 46-8508109, autopilot engagement is limited to flaps up.
Automatic GPS-to-LOC CDI switching must be disabled when using NAV/APR modes unless the
following conditions are met:
GMC 605 software version 2.21 or later
AND
GTN 6XX/7XX software version 6.50 or later
AND
G500/600 with software version 7.30 or later OR G500/600 TXi with software version 2.20 or
later.
For installations which do not include GPS roll steering capability (see installed features checklist):
During GPS approaches, HDG mode must be selected to manually track the desired course during
course changes over 30°. Select APR mode once the aircraft is established on the new course.
NOTE
The GFC 600 installation does not change the previously approved kinds of operation. Refer to the aircraft
POH/AFM.

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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
3. Aircraft Attitude ............................................................ MAINTAIN / REGAIN AIRCRAFT CONTROL
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 and yaw
damper (if installed) inoperative.
4. Elevator Trim ................................................................. RE-TRIM if necessary using Pitch Trim Wheel
5. AUTOPILOT Circuit Breaker .......................................................................................................... PULL
6. AP DISC / TRIM INT Button ................................................................................................... RELEASE
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.
WARNING

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AUTOPILOT FAILURE / ABNORMAL DISCONNECT
(Red LED, AP FAIL in Message Window on GMC 605 display, Continuous aural 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 an AP FAIL on the GMC 605 Status
message window, indicating the automatic flight control system has failed. The autopilot
cannot be re-engaged with this annunciation present.
ESP ACTIVATION
1. Power............................................................................................................................. AS REQUIRED
2. Aircraft Attitude ............................................................ MAINTAIN / REGAIN AIRCRAFT CONTROL
3. LVL key ....................................................................................................... PRESS to engage autopilot
NOTE
If ESP is active for at least 50% of the last 20 seconds, the autopilot will automatically
engage in LVL mode, an aural ‘ENGAGING AUTOPILOT’ will be played, and the
autopilot will roll the wings level and fly at zero-vertical speed. Refer to Section 7 –
System Description for further information.
4. SELECT desired autopilot modes

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OVERSPEED PROTECTION (MAXSPEED)
(MAXSPEED in Message Window on GMC 605 display)
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
Overspeed protection mode provides a pitch up command to decelerate the airplane at or
below the maximum autopilot operating speed. Overspeed protection will not activate in
altitude hold (ALT), glideslope (GS), or glidepath (GP) modes.
UNDERSPEED PROTECTION (MINSPEED)
(AIRSPEED Aural sounds, MINSPEED in Message Window on GMC 605 display)
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 2
KIAS above stall warning airspeed if the selected vertical mode is ALT, GS, GP, or GA.
Otherwise, Underspeed Protection will maintain 80 KIAS.
If the autopilot was in ALT, GS, GP, or GA modes when Underspeed Protection was
entered, the autopilot will roll wings level.
The autopilot will not enter Underspeed Protection Mode unless the indicated airspeed
is 85 KIAS or lower

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ENGINE FAILURE
1. AP DISC / TRIM INT Switch............................................................................... PRESS and RELEASE
2. ENGINE INOPERATIVE PROCEDURES in POH/AFM……...... COMPLETE appropriate procedures
3. Trim Tabs ......................................................... Manually ADJUST Elevator, Aileron, and Rudder Trim
4. Autopilot ................................................................................ PRESS ‘AP’ key to re-engage (if desired)
5. Rudder Trim………………..……Manually ADJUST as required after power and configuration changes

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Section 3A – Abnormal Procedures
AUTOPILOT PRE-FLIGHT TEST FAIL
(Red LED illuminated next to AP key, AP FAIL in Message Window on GMC 605 display)
Indicates the AFCS system failed the automatic Pre-Flight test. The autopilot, yaw damper (if installed),
ESP, and electric elevator trim are inoperative. Flight Director may still function.
LOSS OF AIR DATA
(AIRDAT FAIL in Message Window on GMC 605 display)
If pressure altitude, indicated airspeed, or true airspeed is invalid or missing, AIRDAT FAIL is displayed in
the message window. This indicates that any mode dependent on air data may not be supported such
as ESP high speed, ESP low speed, OSP, USP, IAS, VS, or ALT modes.
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 Button (GMC 605 mode control panel) ................................................................................. PRESS
(Yaw damper remains engaged)
3. Pitch Trim Switch………………...…............................................ ACTIVATE either half of the split switch
(Yaw damper remains engaged)
4. AUTOPILOT Circuit Breaker .......................................................................................................... PULL

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LOSS OF NAVIGATION INFORMATION
(Amber FD LED flashes for 10 seconds, GPS, VOR, LOC, VAPP, or BC flashes for 10 seconds on GMC
605 mode panel display)
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 605 Mode Panel..................................................... SELECT HDG mode and SET desired heading
2. NAV Source………………………………………………………………………SELECT a valid nav source
3. GMC 605 Mode Panel…………………………………………………………………………..SELECT NAV
If on an instrument approach at the time the navigation signal is lost:
4. Missed Approach Procedure ……………………………………………………..EXECUTE (as applicable)
YAW DAMPER FAILURE (if installed)
(Amber YD LED, YD FAIL in Message Window on GMC 605 display)
1. Indicates a failure of the yaw damper. The yaw damper will disconnect. The autopilot may be re-
engaged and disengaged normally, but the yaw damper will remain inoperative.
2. Autopilot ............................................................................................................................ AS DESIRED

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ELEVATOR MISTRIM
(Amber AP LED flashes for 10 seconds, ELE TRM UP or ELE TRM DN displayed in Message Window on
GMC 605 display)
Indicates a mistrim of the elevator while the autopilot is engaged. 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.
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 ELE TRIM UP or ELE TRIM DN message during
configuration changes or large airspeed changes is normal.
1. Control Wheel……………………………………………………………………………………GRIP FIRMLY
Be prepared for significant sustained control forces in the direction of the mistrim
annunciation. For example, ELE TRM DN indicates nose down control wheel force will
be required upon autopilot disconnect.
2. AP DISC / TRIM INT Switch ……………………………………………………..…PRESS AND RELEASE
3. Manual Elevator Trim …………………………………………………………………..RE-TRIM as required
4. The autopilot should be considered inoperative until the cause of the mistrim has been investigated
and corrected. Yaw damper may be re-engaged and used normally.
WARNING
WARNING

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AILERON MISTRIM
(Amber AP LED flashes for 10 seconds, AIL TRM LF or AIL TRM RT displayed in Message Window on
GMC 605 display)
Indicates a mistrim of the ailerons while the autopilot is engaged. If the autopilot is disconnected while this
message is displayed, high aileron control forces are possible.
NOTE
Observe the 10 gallon maximum fuel imbalance limitation.
1. RUDDER TRIM……………………………………………………..VERIFY slip / skid indicator is centered
If annunciation remains:
2. CONTROL WHEEL………………………………………………………………………….…..GRIP FIRMLY
Be prepared for significant sustained control forces in the direction of the mistrim
annunciation. For example, AIL TRM RT indicates right wing down control wheel force
will be required upon autopilot disconnect.
3. AP DISC / TRIM INT switch ……………………………………………………………………………PRESS
4. AUTOPILOT…………………………………………………..If lateral trim is re-established, RE-ENGAGE
WARNING