Garmin GFC™ 600 Digital Autopilot Owner's manual

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Owner's manual

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GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
Page 2 of 48 FAA APPROVED
© Copyright 2019
Garmin Ltd. or its subsidiaries
All Rights Reserved
Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated,
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Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a
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hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this
copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision
hereto is strictly prohibited.
Garmin International, Inc.
1200 E. 151
st
Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
190-02011-08 Rev. 1 GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
FAA APPROVED Page 3 of 48
Garmin International, Inc
Log of Revisions
FAA Approved Airplane Flight Manual Supplement for
GFC 600 Autopilot
Installed in Daher Aerospace TBM 700/700N
REV
NO.
PAGE NO(S)
DESCRIPTION
DATE OF
APPROVAL
FAA APPROVED
1
ALL
Original Issue
See Cover
See Cover
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
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Table of Contents
Section 1 General ........................................................................................................................6
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 ............................................................................................12
AUTOPILOT MALFUNCTION / PITCH, ROLL, OR RUDDER TRIM RUNAWAY ................................. 13
AUTOPILOT FAILURE / ABNORMAL DISCONNECT ................................................................................ 15
ESP ACTIVATION ............................................................................................................................................... 15
OVERSPEED PROTECTION (MAXSPEED) ................................................................................................... 16
UNDERSPEED PROTECTION (MINSPEED) .................................................................................................. 16
ENGINE FAILURE .............................................................................................................................................. 17
EMERGENCY DESCENT MODE (EDM) ......................................................................................................... 17
Section 3A Abnormal Procedures ...........................................................................................18
AUTOPILOT PRE-FLIGHT TEST FAIL .......................................................................................................... 19
LOSS OF AIR DATA ............................................................................................................................................ 19
LOSS OF MAGNETIC HEADING ..................................................................................................................... 19
MANUAL AUTOPILOT DISCONNECT ........................................................................................................... 20
LOSS OF NAVIGATION INFORMATION....................................................................................................... 20
YAW DAMPER FAILURE .................................................................................................................................. 20
ELEVATOR MISTRIM ....................................................................................................................................... 21
AILERON MISTRIM ........................................................................................................................................... 22
RUDDER MISTRIM ............................................................................................................................................. 23
PITCH TRIM FAILURE ...................................................................................................................................... 24
RUDDER TRIM FAILURE ................................................................................................................................. 24
Section 4 Normal Procedures ...................................................................................................25
GFC 600 Power Up ................................................................................................................................................ 25
Flight Director / Autopilot Normal Operating Procedures ................................................................................ 25
VERTICAL MODES .......................................................................................................................................... 27
LATERAL MODES ............................................................................................................................................ 31
APPROACHES ................................................................................................................................................... 33
DISABLING ESP ................................................................................................................................................ 36
Section 5 Performance ..............................................................................................................37
Section 6 Weight and Balance ..................................................................................................39
Section 7 System Description ...................................................................................................41
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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.
Aircraft equipped with this modification have been evaluated in accordance with 14 CFR Part 91, Appendix G,
“Operations in Reduced Vertical Separation Minimum (RVSM) Airspace,” and FAA Advisory Circular 91-85B,
“Authorization of Aircraft and Operators for Flight in Reduced Vertical Separation Minimum Airspace,” and are
qualified for RVSM operations as a group aircraft. This finding does not constitute approval to conduct RVSM
operations. Additional approval to conduct RVSM operations may be required by the local aviation authority.
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
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
Page 8 of 48 FAA APPROVED
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
EDM Emergency Descent Mode
ESP Electronic Stability and Protection
FAA Federal Aviation Administration
GA Go Around
GFC 600 Garmin Autopilot
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
MPH Miles Per Hour
N/A Not Applicable
POH Pilot’s Operating Handbook
RVSM Reduced Vertical Separation Minimum
SSEC Static Source Error Correction
STC Supplemental Type Certificate
VHF Very High Frequency
VNAV Vertical Navigation
VOR VHF Omni-directional Range
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FAA APPROVED Page 9 of 48
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
GPS Navigator #1
GPS Navigator #2
ADS-B Out Transponder
with internal GPS MapMX data
provided to GFC 600 internal
attitude source
Primary Flight Display
Air Data Computer
VHF Nav Radio #1
VHF Nav Radio #2
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
Page 10 of 48 FAA APPROVED
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 Emergency Descent Mode
Auto Rudder Trim
Overspeed Protection
Manual Activation
Underspeed Protection
Automatic Activation
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
190-02011-08 Rev. 1 GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
FAA APPROVED Page 11 of 48
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
v356700
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 266 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 15 gallons.
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.
NOTE
The GFC 600 installation does not change the previously approved kinds of operation. Refer to
the aircraft AFM.
Reduced Vertical Separation Minima (RVSM) are met pending airplane compliance with the GFC 600 Installation
Manual. Airworthiness Approval alone does not authorize flight into airspace for which an RVSM Operational
Approval is required by an ICAO Regional Navigation Agreement.
NOTE
Only the configurations approved in Appendix G of the G600 TXi Installation Manual are
compliant with TBM 700/700N operation in RVSM airspace.
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
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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, ROLL, OR RUDDER TRIM RUNAWAY
If the airplane deviates unexpectedly from the planned flight path:
1. Rudder Pedals and Control Wheel ................................................................................................... Hold 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 turning the AP / TRIMS MASTER
Switch OFF.
4. AP / TRIMS MASTER Switch .........................................................................................................................OFF
5. AP DISC / TRIM INT Button ..................................................................................................................... Release
6. Elevator Trim .................................................................................... Re-trim if necessary using Pitch Trim Wheel
7. Airspeed .......................................................................................... Reduced as necessary to reduce control forces
------------------------------------- CONTINUED ON NEXT PAGE -------------------------------------
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
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AUTOPILOT MALFUNCTION / PITCH, ROLL, OR RUDDER TRIM RUNAWAY
------------------------------------------------- CONTINUED -------------------------------------------------
If pitch trim runaway:
8. AP / TRIMS MASTER Switch .................................................................................................................. AP OFF
9. With autopilot inoperative, perform appropriate RVSM contingency for the loss for automatic altitude hold
capability.
NOTE
Pitch trim may be used manually. Roll and rudder trim may be used again electrically.
If roll or rudder trim runaway:
8. Circuit breaker corresponding to the defective trim ....................................................................................... PULL
9. AP / TRIMS MASTER Switch .......................................................................................................................... ON
NOTE
Other two (2) electric trims may be used again.
In flight, do not overpower the autopilot. The pitch and rudder 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 or rudder trim until the
cause of the malfunction has been corrected.
WARNING
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AUTOPILOT FAILURE / ABNORMAL DISCONNECT
(Red LED illuminated next to AP key, 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
3. With autopilot inoperative, perform appropriate RVSM contingency for the loss for automatic altitude hold
capability.
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. After Recovery ........................................................................................................ Select desired autopilot modes
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
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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.
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ENGINE FAILURE
1. AP DISC / TRIM INT Switch ................................................................................................... Press and release
2. ENGINE INOPERATIVE PROCEDURES in POH ................................. Complete appropriate procedures
3. Trim Tabs .................................................................................. Manually adjust elevator, aileron, and rudder trim
4. Autopilot .................................................................................................... Press ‘AP’ key to re-engage (if desired)
EMERGENCY DESCENT MODE (EDM)
(Optional Feature)
NOTE
Refer to the G500/600 TXi AFMS for details on how to activate or inhibit EDM.
(EMERGENCY DESCENT aural sounds, EDM ON in message window on GMC 605 display)
1. Emergency Descent .................................................................................................................................. Monitor
CAUTION
While EDM is active, the autopilot cannot be disengaged by actuating either half of the manual
electric trim split switch. Only the AP DISC / TRIM INT Switch or AP button will disengage the
autopilot.
NOTE
When EDM activates, the autopilot will enter HDG and IAS modes, perform a left, 90° turn, and
set the airspeed reference to 256 KIAS. ALTS will be armed with a pre-select altitude of 15,000
ft. Altitude pre-select and airspeed references are locked out and cannot be changed while in EDM
via any cockpit control.
To exit EDM
2. AP DISC / TRIM INT Switch or AP Button ................................................................................. Press and release
3. Autopilot ..................................................................................... Reselect vertical and lateral modes (if necessary)
4. Autopilot ....................................................................................................................................................... Engage
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
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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, ESP, electric elevator
trim, and electric rudder trim are inoperative. Flight Director may still function.
LOSS OF AIR DATA
(AIRDAT FAIL in message window on GMC 605 display)
If AIRDAT FAIL is displayed in the message window on the GMC 605 display, a partial or full loss of air data input
to the GFC 600 has occurred. With loss of air data, one or more modes dependent on air data may not be supported
such as ESP high speed, OSP, USP, IAS, VS, or ALT modes. With loss of redundancy of primary altimetry systems,
perform appropriate RVSM contingency procedures for the loss of primary altimetry systems.
CAUTION
Autopilot performance is affected if airspeed is invalid or inaccurate. Use of the autopilot with
invalid or inaccurate airspeed should be discontinued.
For installations with a G500/G600 TXi PFD and dual air data sources, refer to the G500/G600 TXi AFMS abnormal
procedures for loss of air data. The GFC 600 will use the air data source that is selected on the pilot’s PFD. If air data
is restored on the pilot’s PFD, verify AIRDAT FAIL is removed from the GMC 605 display. Removal of AIRDAT
FAIL on the GMC 605 display indicates normal autopilot function is restored. The GFC 600 will not utilize air data
from a co-pilot’s PFD.
LOSS OF MAGNETIC HEADING
(TRK MODE in message window on GMC 605 display)
If magnetic heading information is lost, TRK MODE is displayed in the message window on the GMC 605 display.
This indicates the autopilot is no longer receiving magnetic heading information and has reverted to GPS track
information (if available). HDG mode will continue to function, but will fly a GPS track set by the heading bug on the
PFD.
For installations with a G500/G600 TXi PFD and dual AHRS sources, refer to the G500/G600 TXi AFMS abnormal
procedures for loss of magnetic heading. The GFC 600 will use the magnetic heading source that is selected on the
pilot’s PFD. If magnetic heading is restored on the pilot’s PFD, verify TRK MODE is removed from the GMC 605
display. Removal of TRK MODE on the GMC 605 display indicates normal autopilot function is restored.
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N 190-02011-08 Rev. 1
Page 20 of 48 FAA APPROVED
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. Roll Trim Switch ........................................................................................................... Activate in either direction
(Yaw damper remains engaged)
5. AP / TRIMS MASTER Switch .........................................................................................................................OFF
6. AUTOPILOT Circuit Breaker ........................................................................................................................ PULL
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
(Amber YD LED, YD FAIL in message window on GMC 605 display)
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 and rudder autotrim will remain inoperative.
1. Autopilot .................................................................................................................................................. As desired
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Garmin GFC™ 600 Digital Autopilot Owner's manual

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