Garmin | GFC™ 600 Digital Autopilot | Garmin GFC™ 600 Digital Autopilot Airplane Flight Manual Supplement, GFC600, Daher Aerospace TBM 700/700N

Garmin GFC™ 600 Digital Autopilot Airplane Flight Manual Supplement, GFC600, Daher Aerospace TBM 700/700N
© 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 is strictly prohibited.
Garmin International, Inc.
1200 E. 151st Street
Olathe, KS 66062 USA
Telephone: 913-397-8200
www.garmin.com
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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190-02011-08 Rev. 1
FAA APPROVED
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
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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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190-02011-08 Rev. 1
FAA APPROVED
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:
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.
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ABBREVIATIONS AND TERMINOLOGY
The following glossary is applicable within the Airplane Flight Manual Supplement:
AFCS
AGL
AFM
AFMS
AP
BC
CDI
CWS
DA
EDM
ESP
FAA
GA
GFC 600
GMC 605
GPS
HDG
HSI
ILS
KIAS
KTS
LED
LNAV
LNAV + V
LNAV/VNAV
LOC
LP
LP+V
LPV
MDA
MPH
N/A
POH
RVSM
SSEC
STC
VHF
VNAV
VOR
Automatic Flight Control System
Above Ground Level
Airplane Flight Manual
Airplane Flight Manual Supplement
Autopilot
Back Course Approach
Course Deviation Indicator
Control Wheel Steering
Decision Altitude
Emergency Descent Mode
Electronic Stability and Protection
Federal Aviation Administration
Go Around
Garmin Autopilot
Autopilot Mode Control Panel
Global Positioning System
AFCS heading mode
Horizontal Situation Indicator
Instrument Landing System
Knots Indicated Airspeed
Knots
Light Emitting Diode
Lateral Navigation
Lateral Navigation with Advisory Vertical Guidance
Lateral Navigation / Vertical Navigation Approach
Localizer (no glideslope available)
Localizer Performance
Localizer Performance with Advisory Vertical Guidance
Localizer Performance with Vertical Guidance
Minimum Descent Altitude
Miles Per Hour
Not Applicable
Pilot’s Operating Handbook
Reduced Vertical Separation Minimum
Static Source Error Correction
Supplemental Type Certificate
Very High Frequency
Vertical Navigation
VHF Omni-directional Range
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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FAA APPROVED
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
GPS Navigator #1
Manufacturer / Model
If not installed, note N/A
Additional Information
Roll Steering Capable?
 YES
 NO
Vertical Navigation 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
Vertical Navigation Capable?
 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
Air Data Computer
Is air data provided to GFC 600 internal
attitude source?
 YES
 NO
VHF Nav Radio #1
VHF Nav Radio #2
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Is #2 NAV interfaced to GFC 600?
 YES
 NO
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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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
 Control Wheel Steering
 Yaw Damper
 Manual Electric Pitch Trim
 Auto Pitch Trim
 Auto Rudder Trim
 Overspeed Protection
 Underspeed Protection
 Pitch/Roll Attitude
 High Speed Protection
 Low Speed Protection
Vertical Autopilot Modes
Lateral Autopilot Modes
 Pitch (PIT)
 Level (Zero vertical speed)
 Go Around (GA)
 Altitude Hold
 Vertical Speed
 Altitude Capture via Altitude Preselect
 Indicated Airspeed (IAS)
 Vertical Navigation (VNV)
 VNAV Target Alt Capture
 GPS Approach Glidepath
 ILS Glideslope
 Roll (ROL)
 Level (Wings Level)
 Go Around (GA)
 Heading
 GPS Navigation
 Roll Steering
 VHF Navigation
 VOR
 Approach Mode
 GPS
 VOR
 LOC
 LOC BC
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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Emergency Descent Mode
 Manual Activation
 Automatic Activation
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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
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.
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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 -------------------------------------
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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.
WARNING
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.
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FAA APPROVED
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 reengaged 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
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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.
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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FAA APPROVED
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
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FAA APPROVED
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.
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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
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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FAA APPROVED
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.
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 ELE TRIM UP or ELE TRIM DN 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, 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.
With autopilot inoperative, perform appropriate RVSM contingency procedures for the loss of automatic
altitude hold capability.
CAUTION
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.
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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 15 gallon maximum fuel imbalance limitation.
1.
Rudder Trim ................................................................................................. Verify slip / skid indicator is centered
2.
Control Wheel ........................................................................................................................................Grip firmly
3.
CWS Button ...................................................................................................................................... Press and hold
WARNING
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.
4.
Aileron Trim ............................................................... Actuate manual electric roll trim to re-establish lateral trim
CAUTION
If manual electric roll trim is used while the autopilot is engaged and the CWS Button is NOT
held, the autopilot will disengage.
If unable to manually re-established lateral trim:
5.
AP DISC / TRIM INT Switch ......................................................................................................................... Press
6.
With autopilot inoperative, perform appropriate RVSM contingency procedures for the loss of automatic
altitude hold capability.
CAUTION
The autopilot should be considered inoperative until the cause of the mistrim has been investigated
and corrected.
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
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190-02011-08 Rev. 1
FAA APPROVED
RUDDER MISTRIM
(Amber AP LED flashes for 10 seconds, RUD TRM LF or RUD TRM RT displayed in message window on GMC
605 display)
Indicates a mistrim of the rudder while the yaw damper is engaged. During large power changes, or quick accelerations
/ decelerations, display of this message may occur. If the yaw damper is disconnected while this message is displayed,
high rudder pedal forces and yawing motion are possible.
1.
Rudder Pedals and Control Wheel ......................................................................................................... Hold firmly
WARNING
Be prepared for significant sustained control forces in the direction of the mistrim annunciation.
For example, RUD TRM RT indicates right rudder pedal force will be required upon yaw damper
disconnect.
2.
YD Button / Rudder Trim switch .................................................................................................................... Press
3.
Rudder Trim .............................................................Actuate manual electric rudder trim to re-establish yaw trim.
4.
With autopilot inoperative, perform appropriate RVSM contingency procedures for the loss of automatic
altitude hold capability.
CAUTION
The autopilot should be considered inoperative until the cause of the mistrim has been investigated
and corrected.
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Page 23 of 48
PITCH TRIM FAILURE
(Amber AP LED, P TRIM FAIL in message window on GMC 605 display)
Indicates a failure of the pitch trim servo of the autopilot. The autopilot may remain engaged, but after disengagement
it cannot be re-engaged until the problem is resolved. The yaw damper will remain operative.
1.
Control Wheel ........................................................................................................................................Grip firmly
2.
AP DISC / TRIM INT Button ....................................................................................................... Press and release
(Be prepared for possible high elevator control forces)
3.
Elevator Trim ....................................................................................Re-trim if necessary using Pitch Trim Wheel
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 reengaged with this annunciation present.
4.
Yaw Damper.............................................................................................................................. Engage as required
5.
With autopilot inoperative, perform appropriate RVSM contingency procedures for the loss of automatic
altitude hold capability.
RUDDER TRIM FAILURE
(Amber YD LED, Y TRIM FAIL in message window on GMC 605 display)
Indicates a failure of the rudder trim adapter. The yaw damper may be engaged and disengaged normally. Manual
electric rudder trim will be inoperative. The autopilot will remain operative.
1.
Rudder Pedals and Control Wheel ..........................................................................................................Grip firmly
2.
AP DISC / TRIM INT Button ....................................................................................................... Press and release
(Be prepared for possible high rudder pedal forces)
3.
AP / TRIMS MASTER Switch .................................................................................................................. AP OFF
4.
Rudder Trim ....................................................................... Re-trim if necessary using manual electric rudder trim
5.
With autopilot inoperative, perform appropriate RVSM contingency procedures for the loss of automatic altitude
hold capability.
NOTE
The AP / TRIMS MASTER Switch must be in the AP OFF position in order to restore manual
electric rudder trim.
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Section 4 – Normal Procedures
GFC 600 Power Up
During power-up of the GFC 600 system, an initialization splash screen displays on the GMC 605 Mode Selection
Panel. The splash screen displays the following information:
• GFC 600 title
• Electronic Stability and Protection (ESP)
• Software version number
When this information has been reviewed, the pilot is prompted to continue (CONT) by pressing the HDG key and
the GFC 600 enters preflight test.
During the preflight test the GMC 605 will display PFT in the Message Window. LED fault lights on the GMC 605
autopilot mode panel cycle through a test sequence, three amber lights followed by three red lights, then extinguish if
the preflight test successfully passes. The autopilot disconnect tone sounds at the completion of the preflight test. If
the GFC 600 passes preflight test, the display on the GMC 605 will be blank and all LED fault lights extinguished.
Flight Director / Autopilot Normal Operating Procedures
Autopilot/Flight Director mode annunciations on the GMC 605 displayed in bold fonts indicate active autopilot/flight
director modes. Armed modes are indicated in smaller fonts. Normal mode transitions will flash inverse video for 10
seconds before becoming steady. Abnormal mode transitions will flash for 10 seconds before the default mode is
annunciated as the active mode. Default autopilot/flight director modes are Roll (ROL) and Pitch (PIT) modes.
The GMC 605 display panel is divided into three sections. From left to right the sections are, lateral autopilot modes,
vertical autopilot modes, and the message window.
GMC 605 Autopilot Mode Control Panel
Autopilot Engagement — The autopilot may be engaged by pushing the AP Key on the GMC 605 Mode Control
Panel. A green LED will illuminate indicating the autopilot is engaged in the active modes as shown on the display.
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.
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Autopilot Disengagement — The most common way to disconnect the autopilot is to press and release the AP DISC
/ TRIM INT Switch located on the control stick. An autopilot disconnect tone will sound and annunciated on the GMC
605. Other ways to disconnect the autopilot include:
– Pressing the AP Key on the GMC 605 Mode Controller
– Operating either side of the Electric Pitch Trim Switch (located on the control wheel)
– Operating either side of the Electric Roll Trim Switch (located on the center pedestal)
– Pulling the AUTOPILOT circuit breaker
In the event of unexpected autopilot behavior, press and hold the AP DISC / TRIM INT switch to disconnect the
autopilot and remove all power to the servos.
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VERTICAL MODES
VERTICAL SPEED (VS) MODE
1.
Press VS Button, autopilot synchronizes to the airplane’s current vertical speed.
2.
Vertical Speed Reference ............................................................................... Adjust using NOSE UP / DN Wheel
INDICATED AIRSPEED (IAS) MODE
1.
Press IAS Button, autopilot synchronizes to the airplane’s current indicated airspeed.
2.
Airspeed Reference ........................................................................................ Adjust using NOSE UP / DN Wheel
3.
Power ........................................................................................................................................... Adjust as required
ALTITUDE HOLD (ALT) MODE
1.
When at the desired altitude, press the ALT Key. The autopilot will hold the altitude at which the ALT key was
pressed.
NOTE
If climbing or descending at a high rate when the ALT button 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 button is pressed.
2.
To capture a selected altitude:
a) Altimeter Setting ................................................................................................... Adjust to appropriate value
b) Altitude Preselect ........................................................................................................... Set to desired altitude
c) Vertical Mode and Reference ............................................................................................ Select on GMC 605
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GO AROUND (GA)
1.
GO AROUND Button ..................................................................................Press – Verify GA / GA on GMC 605
(autopilot will not disengage)
2.
Autopilot.......................................................... Verify airplane pitches up following flight director command bars
3.
Power ................................................................................................................................ Apply Go Around power
4.
GMC 605 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 goaround 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.
VERTICAL NAVIGATION (VNV)
(Optional Feature)
1.
Navigation Source ...........................................................................................................................Set CDI to GPS
2.
Vertical Navigation Profile ........................................................................ Load into the GPS navigator flight plan
3.
Altitude Preselect ......................................................................... Adjust to desired altitude below current altitude
4.
GMC 605 VNV Key........................................................................................................................................ Press
5.
Bold or subdued font VPTH annunciation ...............................................................................Verify on GMC 605
(Verify aircraft flight path will intercept the vertical navigation profile)
NOTE
If the altitude preselect is not set at least 75ft below the current aircraft altitude, the autopilot will
not capture the vertical navigation path. The autopilot will capture the vertical navigation path
from above or below.
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TRANSITION to ILS APPROACH from VERTICAL NAVIGATION
(Optional Feature)
1.
Navigation Source ...........................................................................................................................Set CDI to GPS
2.
Approach Procedure .................................................................................. Load into the GPS navigator flight plan
3.
CDI ........................................................................................................................................... Verify desired track
4.
Altitude Preselect ......................................................................... Adjust to desired altitude below current altitude
5.
GMC 605 VNV Key........................................................................................................................................ Press
6.
Bold or subdued font VPTH annunciation ...............................................................................Verify on GMC 605
(Verify aircraft flight path will intercept the vertical navigation profile)
7.
GMC 605 APR Key......................................................................................................................................... Press
8.
Bold or subdued font LOC and GS annunciations ...................................................................Verify on GMC 605
NOTE
If the altitude preselect is not set at least 75ft below the current aircraft altitude, the autopilot will
not capture the vertical navigation path. The autopilot can capture the vertical navigation path
from above or below.
Under certain display conditions, VPTH and GS armed modes are combined into a single “GS/V”
annunciation.
If the Course Deviation Indicator (CDI) is greater than half-scale deflection, the autopilot will
arm the LOC mode. The pilot must ensure that the current heading will result in a capture of the
selected course. If the CDI is within half scale deflection, the autopilot will enter the capture mode
when the APR key is pressed.
When the selected navigation source is an ILS, glideslope coupling is automatically armed when
the APR key is pressed. The glideslope cannot be captured until the localizer is captured. The
autopilot can capture the glideslope from above or below the glideslope.
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TRANSITION to GPS APPROACH from VERTICAL NAVIGATION
(Optional Feature)
1.
Navigation Source ...........................................................................................................................Set CDI to GPS
2.
Approach Procedure .................................................................................. Load into the GPS navigator flight plan
3.
CDI ................................................................................................................................. / Set / Verify desired track
4.
Altitude Preselect ..................................................................... ADJUST to desired altitude below current altitude
5.
GMC 605 VNV Key........................................................................................................................................ Press
6.
Bold or subdued font VPTH annunciation ...............................................................................Verify on GMC 605
7.
GMC 605 APR Key......................................................................................................................................... Press
8.
Bold or subdued font GPS and GP annunciations ....................................................................Verify on GMC 605
(Verify aircraft flight path will intercept the vertical navigation profile)
NOTE
If the altitude preselect is not set at least 75ft below the current aircraft altitude, the autopilot will
not capture the vertical navigation path. The autopilot can capture the vertical navigation path
from above or below.
Under certain display conditions, VPTH and GP armed modes are combined into a single “GP/V”
annunciation.
If the Course Deviation Indicator (CDI) is greater than half-scale deflection, 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 within half scale deflection, the autopilot will enter the capture mode
when the APR key is pressed.
When the selected GPS approach includes vertical guidance (LPV, LNAV/VNAV, LNAV+V,
LP+V), glidepath coupling is automatically armed when the APR key is pressed. The glidepath
cannot be captured until the lateral approach path is captured. The autopilot can capture the
glidepath from above or below the glidepath.
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LATERAL MODES
HEADING MODE (HDG)
1.
HDG Key ....................................................................................................................................................... Press
2.
HDG Knob ....................................................................................... Rotate to set heading bug to desired heading
NOTE
If heading bug is rotated quickly, the airplane could turn in the opposite direction as the heading
bug’s movement.
3.
When the airplane reaches the heading bug, the autopilot will roll the wings level to track the heading reference.
NAVIGATION (VOR)
1.
Navigation Source ................................................................................................................ Set CDI to VHF NAV
Tune and identify the station frequency
2.
CDI ............................................................................................................................................. Set / Verify course
3.
Intercept Heading ............................................................................. Establish in HDG or ROL mode (if required)
4.
GMC 605 NAV key......................................................................................................................................... Press
5.
Bold or subdued font VOR annunciation .................................................................................Verify on GMC 605
NOTE
If the Course Deviation Indicator (CDI) is greater than half scale deflection, 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 within half scale deflection, the autopilot will enter the capture mode
when the NAV key is pressed.
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NAVIGATION (GPS)
1.
Navigation Source .................................................................................................................... Select CDI to GPS
2.
Flight Plan ......................................................................................................................... Load in GPS navigator
3.
CDI ................................................................................................................................. Set / Verify desired track
4.
Intercept Heading ........................................................................... Establish in HDG or ROL mode (if required)
5.
GMC 605 NAV key ....................................................................................................................................... Press
6.
Bold or subdued font GPS annunciation .................................................................................Verify on GMC 605
NOTE
If the Course Deviation Indicator (CDI) is greater half scale deflection, 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 within half scale deflection, the autopilot will enter the capture mode when
the NAV key is pressed.
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APPROACHES
ILS
1.
Navigation Source .................................................................................................................. Set CDI to VHF Nav
Tune and Identify an ILS station frequency
2.
CDI ............................................................................................................................................. Set / Verify course
3.
Intercept Heading ............................................................................. Establish in HDG or ROL mode (if required)
4.
GMC 605 APR Key......................................................................................................................................... Press
5.
Bold or subdued font LOC and GS annunciations ...................................................................Verify on GMC 605
NOTE
If the Course Deviation Indicator (CDI) is greater than half scale deflection, the autopilot will arm
the LOC mode. The pilot must ensure that the current heading will result in a capture of the
selected course. If the CDI is within half scale deflection, the autopilot will enter the capture mode
when the APR key is pressed.
When the selected navigation source is an ILS, glideslope coupling is automatically armed when
the APR key is pressed. The glideslope cannot be captured until the localizer is captured. The
autopilot can capture the glideslope from above or below the glideslope.
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GPS
1.
Navigation Source ...........................................................................................................................Set CDI to GPS
2.
Approach Procedure .......................................................................................................... Select in GPS Navigator
3.
CDI ................................................................................................................................... Set / Verify desired track
4.
Intercept Heading ............................................................................. Establish in HDG or ROL mode (if required)
5.
GMC 605 APR Key......................................................................................................................................... Press
6.
Bold or subdued font GPS and GP annunciations ....................................................................Verify on GMC 605
7.
Vertical Mode and Reference ................................................................................................... Select on GMC 605
If required for GPS approach without vertical guidance
NOTE
If the Course Deviation Indicator (CDI) is greater than half scale deflection, 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 within half scale deflection, the autopilot will enter the capture mode
when the APR key is pressed.
When the selected GPS approach includes vertical guidance (LPV, LNAV/VNAV, LNAV+V,
LP+V), glidepath coupling is automatically armed when the APR key is pressed. The glidepath
cannot be captured until the lateral approach path is captured. The autopilot can capture the
glidepath from above or below the glidepath.
VOR
1.
Navigation Source .................................................................................................................. Set CDI to VHF Nav
Tune and Identify a VOR station frequency
2.
CDI ............................................................................................................................................. Set / Verify course
3.
Intercept Heading ............................................................................. Establish in HDG or ROL mode (if required)
4.
GMC 605 APR Key......................................................................................................................................... Press
5.
Bold or subdued font VAPP annunciation ................................................................................Verify on GMC 605
6.
Vertical Mode and Reference ................................................................................................... Select on GMC 605
NOTE
If the Course Deviation Indicator (CDI) is greater than half scale deflection, the autopilot will arm
the VAPP 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.
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BC
1.
Navigation Source .................................................................................................................. Set CDI to VHF Nav
Tune and Identify a LOC BC station frequency
2.
CDI ......................................................................................................................Set / Verify localizer front course
3.
Intercept Heading ............................................................................. Establish in HDG or ROL mode (if required)
4.
GMC 605 BC Key ........................................................................................................................................... Press
5.
Bold or subdued font BC annunciation ....................................................................................Verify on GMC 605
6.
Vertical Mode and Reference ................................................................................................... Select on GMC 605
NOTE
If the Course Deviation Indicator (CDI) is greater than half scale deflection, the autopilot will arm
the BC 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 BC key is pressed.
LOW BANK
The Low Bank function will limit the maximum bank angle to 17° in HDG, GPS, and VOR modes. When active,
LOW BANK is shown on the GMC 605 display. The Low Bank function is not available for GPS or VOR approaches.
To toggle Low Bank ON or OFF:
1. LOW BANK Button ........................................................................................................................................ Press
NOTE
Low Bank is automatically activated when above FL200 and deactivated when below FL200.
Low Bank mode can be toggled ON or OFF at any time and any altitude.
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DISABLING ESP
(ESP OFF message displayed in message window on GMC 605 display)
ESP can be disabled with the following procedure. ESP will be re-enabled when either the AP or FD key is pressed.
The GMC 605 Mode Control Panel will display the message “ESP OFF” when ESP is disabled.
1.
AP DISC / TRIM INT Switch ........................................................................................ Press and hold 5 seconds
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Section 5 – Performance
No Change.
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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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Section 7 – System Description
AFCS OVERVIEW
The Garmin GFC 600 Pilot’s Guide, part number 190-01488-00, may be referenced for a detailed system description.
The GFC 600 is a digital Automatic Flight Control System (AFCS). It is a three-axis autopilot and flight director
system which provides the pilot with the following features:
Flight Director (FD) — The flight director processing occurs in the GMC 605 mode panel. Selected modes for the
flight director are displayed on the GMC 605 display.
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 pitch trim servos. It also provides servo
monitoring, and automatic flight control in response to flight director steering commands, attitude and rate
information, and airspeed.
Yaw Damper (YD) — The yaw servo is self-monitoring and provides Dutch roll damping and turn coordination in
response to yaw rate, roll angle, lateral acceleration, and airspeed.
Electric Pitch Trim — The pitch trim servo provides manual electric pitch trim capability when the autopilot is not
engaged. It provides automatic electric pitch trim capability when the autopilot is engaged.
Automatic Rudder Trim – The Garmin trim adapter (GTA 82) provides automatic rudder trim capability when the
YD is engaged.
Internal Attitude Source – The GMC 605 contains internal sensors which calculate the aircraft attitude, allowing the
GFC 600 to operate without relying on any external source of attitude. Internal monitoring detects attitude errors and
will automatically disconnect the autopilot in the unlikely event of internal attitude failure. The GMC 605 attitude
source requires either air data or GPS data for calculation of the aircraft attitude.
Airspeed and Altitude Information – The GFC 600 requires airspeed and altitude information. For GDU 620
installations, air data is provided directly from the air data computer to the GFC 600. For installations with a
G500/G600 TXi PFD, this information is provided by the pilot’s PFD to the GFC 600 and the GFC 600 will utilize
the same air data source selected on the pilot’s PFD.
Pilot commands to the AFCS are entered through the GMC 605 autopilot mode panel.
Other components of the AFCS include the GSA 87 pitch, roll, yaw, and pitch trim servos that also contain autopilot
processors, control wheel mounted elevator trim switch, control wheel mounted autopilot / yaw damper disconnect
and trim interrupt switch (AP DISC / TRIM INT), Control Wheel Steering switch (CWS), Go-Around (GA) switch,
and Low Bank switch.
The following conditions will cause the autopilot to automatically disconnect:
•
Electrical power failure, including pulling the AUTOPILOT circuit breaker, or setting the AP / TRIMS MASTER
switch to the AP OFF or OFF position.
•
Internal autopilot system failure (including internal attitude source failure)
The internal attitude source will fail with the loss of both air data and GPS to the GMC 605 internal attitude source.
See installed equipment interface checklist on page 9 of this AFMS for information for installed interfaces.
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The following pilot actions will cause the autopilot to disconnect:
•
Pressing the red AP DISC / TRIM INT switch on the pilot’s control wheel
•
Actuating either half of the manual electric trim split switch
•
Actuating the manual electric roll trim switch without holding the CWS button
•
Pushing the AP key on the GMC 605 mode controller when the autopilot is engaged
•
Setting the AP / TRIMS MASTER switch to the AP OFF or OFF position
•
Pulling the AUTOPILOT circuit breaker
The red AP DISC / TRIM INT switch on the pilot’s control wheel will interrupt power to the manual electric trims
for as long as the switch is depressed.
AFCS CONTROL UNIT
The following tables list the available AFCS vertical and lateral modes with their corresponding controls and
annunciations. The NOSE UP/DN Wheel can be used to change the vertical mode reference while operating in Pitch
Hold, Vertical Speed, Altitude Hold, or Indicated Airspeed mode. Increments of change and maximum ranges of
values for each of these references using the NOSE UP/DN Wheel are also listed in the table.
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AFCS VERTICAL MODES
Control
Annunciation
Reference Range
Reference Change
Increment
(default)
PIT
20° Nose up
15° Nose Down
0.5°
*
ALTS
Altitude Hold
ALT Key
ALT nnnnn FT
Vertical Speed
VS Key
VS nnnn FPM
-4000 to +3000 fpm
100 fpm
IAS Hold
IAS Key
IAS nnn KTS
80 to 266 kt
1 kt
Vertical Path
Tracking (VNAV)
VNV Key
VPTH
Vertical Mode
Pitch Hold
Selected Altitude
Capture
Glidepath
10 ft
GP
APR Key
Glideslope
GS
Go Around
GA Switch
GA
7°
Level (LVL)
LVL Key
LVL
Zero Vertical Speed
ESP High Pitch
ESP High Pitch Attitude engages at 20° nose up
Engagement
ESP Low Pitch Attitude engages at 22° nose down
ESP Low Pitch
Engagement
ESP High Airspeed
ESP High Airspeed engages at 268 KIAS
Engagement
When above 200 ft AGL, ESP Low Airspeed engages
ESP Low Airspeed
when stall warning activates.
Engagement
* ALTS arms automatically when PIT, VS, IAS, or GA is active.
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AFCS LATERAL MODES
Lateral Mode
Annunciation
(default)
ROL
25°
HDG Key
HDG
25°
GPS
30°
VOR
25°
LOC
25°
BC
25°
GPS
30°
VAPP
25°
LOC
25°
Roll Mode
Heading Select
Navigation, GPS Arm/Capture/Track
Navigation, VOR Enroute Arm/Capture/Track
Maximum Roll
Command Limit
Control
NAV Key
Navigation, LOC Arm/Capture/Track (No
Glideslope)
Backcourse Arm/Capture/Track
BC Key
Approach, GPS Arm/Capture/Track (Glidepath
Mode Automatically Armed, if available)
Approach, VOR Arm/Capture/Track
APR Key
Approach, ILS Arm/Capture/Track (Glideslope
Mode Automatically Armed)
Go Around
GA Switch
GA
Wings Level
LVL (Level)
LVL Key
LVL
Wings Level
Low Bank
(HDG, VOR NAV, and GPS NAV modes only)
Low Bank
Button
LOW BANK
17°
ESP Roll Attitude Engagement
ESP Roll Attitude
engages at 45°
The CWS Button does not change lateral references for Heading Select, Navigation, Backcourse, or Approach modes.
The autopilot guides the aircraft back to the Selected Heading/Course upon release of the CWS Button.
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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PREFLIGHT TEST
During the preflight test the GMC 605 will display PFT in the Message Window. LED fault lights on the GMC 605
autopilot mode panel cycle through a test sequence, three amber lights for one second, followed by three red lights for
one second, then extinguish if the preflight test successfully passes. The autopilot disconnect tone sounds at the
completion of the preflight test. If the GFC 600 passes preflight test, the display on the GMC 605 will be blank and
all LED fault lights extinguished. If GFC 600 fails the PFT, PFT FAIL is displayed in the message window the AP
LED in red illuminates.
MESSAGES
GMC 605 Messages
AIL TRM LF
Aileron Trim Left - Autopilot is holding left wing down roll force. Amber AP LED
flashes amber for 5 seconds then remains steady amber.
AIL TRM RT
Aileron Trim Right - Autopilot is holding right wing down roll force. Amber AP
LED flashes amber for 5 seconds then remains steady amber.
AIRDAT FAIL
Air data input to the GFC 600 has failed. Vertical modes that require air data input
are failed.
ALT KEY STK
ALT key stuck – System has sensed ALT key input for 30 seconds or longer.
AP FAIL
Autopilot Failed – The autopilot is inoperative. Red AP LED will flash until the
pilot presses the AP key. Once AP FAIL acknowledged, the Red AP LED will be
steady.
AP KEY STK
Autopilot key stuck – System has sensed AP key input for 30 seconds or longer.
APR KEY STK
Approach key stuck – System has sensed APR key input for 30 seconds or longer.
BC KEY STK
Back Course key stuck – System has sensed BC key input for 30 seconds or longer.
CWS
System is in Control Wheel Steering mode.
DISABLD KEY
Disabled Key – The pressed key is inactive; it has no associated mode. This message
will extinguish after 3 seconds.
EDM ON
Emergency Descent Mode – Emergency Descent Mode is active.
ELE TRM DN
Elevator Trim Down – Autopilot is holding elevator nose down force. The pitch trim
needs to be adjusted nose down. Amber AP LED flashes amber for 5 seconds then
remains steady amber.
ELE TRM UP
Elevator Trim Up – Autopilot is holding elevator nose up force. The pitch trim
needs to be adjusted nose up. Amber AP LED flashes amber for 5 seconds then
remains steady amber.
ESP FAIL
Electronic Stability and Protection Has Failed – ESP function is not available.
ESP OFF
Electronic Stability and Protection is OFF – The pilot has turned ESP OFF.
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GMC 605 Messages
FD KEY STK
Flight Director key stuck – System has sensed FD key input for 30 seconds or
longer.
HDG KEY STK
Heading key stuck – System has sensed HDG key input for 30 seconds or longer.
IAS KEY STK
Indicated Airspeed key stuck – System has sensed IAS key input for 30 seconds or
longer.
LOW BANK
Low Bank mode – Low Bank mode is active and will limit the maximum bank angle
for HDG, VOR NAV, and GPS NAV modes.
LVL KEY STK
Level Mode key stuck – System has sensed LVL key input for 30 seconds or longer.
MAXSPEED
Autopilot Overspeed Protection mode is active.
MINSPEED
Autopilot Underspeed Protection mode is active.
NAV KEY STK
Nav Mode key stuck – System has sensed NAV key input for 30 seconds or longer.
P TRIM FAIL
Pitch Trim Fail – Autopilot and Manual Electric Pitch Trim is inoperative. Amber
AP LED flashes for 10 seconds and becomes steady.
PFT FAIL
Preflight Test Failed – Autopilot failed the preflight test. The autopilot is
inoperative. FD modes may still be available. Red AP LED illuminates steady.
PFT
Preflight Test is in Progress.
RUD TRM LF
Rudder Trim Left – Yaw Damper is holding left rudder force. Amber AP LED
flashes amber for 5 seconds then remains steady amber.
RUD TRM RT
Rudder Trim Right – Yaw Damper is holding right rudder force. Amber AP LED
flashes amber for 5 seconds then remains steady amber.
SET HDG=CRS
When the GFC 600 is configured to use a DG (not an HSI), the heading bug must be
set to the desired track or navigation course when in NAV or APPROACH modes.
This message will be displayed continuously when NAV or APPROACH modes are
active.
TRK MODE
Reversionary GPS Track Mode – Automatically activates when in HDG mode and
magnetic heading information is lost. Autopilot will follow a GPS ground track
based on the selected heading.
VNV KEY STK
Vertical Navigation Mode key stuck – System has sensed VNV key input for 30
seconds or longer.
VS KEY STK
Vertical Speed Mode key stuck – System has sensed VS key input for 30 seconds or
longer.
Y TRIM FAIL
Rudder Trim Fail – Manual Electric Rudder Trim is inoperative. Amber YD LED
flashes for 10 seconds and becomes steady.
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
Page 46 of 48
190-02011-08 Rev. 1
FAA APPROVED
GMC 605 Messages
YD FAIL
Yaw Damper has failed. Amber YD LED flashes for 10 seconds and becomes
steady.
YD KEY STK
Yaw Damper key stuck – System has sensed YD key input for 30 seconds or longer.
Yaw damper is inoperative.
LED ANNUNCIATOR LIGHTS
GMC 605 GREEN LED LIGHTS
AP
FD
YD
Steady Green AP LED - Autopilot is engaged and functioning.
Steady Green FD LED - Flight Director is displayed and functioning.
Steady Green YD LED - Yaw Damper is operating
GMC 605 AMBER LED LIGHTS
Flashing Amber AP LED for 5 seconds, then extinguish – Normal AP disconnect
OR;
AP
Flashing Amber AP LED displayed on the GMC for 10 seconds then steady, accompanied by a
GMC 605 message for ELE, AIL, or RUD mistrim message – See abnormal procedure for
mistrim message.
GMC 605 AMBER LED LIGHTS (continued)
FD
Flashing Amber FD LED for 10 seconds, then extinguish – The coupled lateral or vertical mode
has been lost, and the GMC has reverted to ROL mode (if lateral mode was lost) or PIT mode (if
vertical mode was lost).
Amber flashing YD LED for 10 seconds, then extinguished - Normal YD disconnect
Flashing Amber YD LED for 10 seconds, then steady – Abnormal YD disconnect
YD
Flashing Amber YD LED for 10 seconds, then steady, accompanied by a GMC 605 message for
ELE or AIL mistrim message – See abnormal procedure for mistrim message.
Steady Amber YD LED – Failed Yaw Damper – YD FAIL in message window
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GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
Page 47 of 48
GMC 605 RED LED LIGHTS
Continuous Flashing Red AP LED – Abnormal AP disconnect
AP
FD
Steady Red AP LED – Autopilot Fail. Cause of the failure will be annunciated in the message
window.
Not used
NO ILLUMINATED LED LIGHT
AP
Autopilot is OFF
FD
Flight Director is OFF
YD
Yaw Damper is OFF
LIGHTING
GMC 605 mode panel lighting may be controlled by an aircraft dimming bus if the system is configured for
dimming bus operation. If not controlled by dimming bus, lighting is controlled by integrated photocells which
sense the ambient cockpit lighting.
GFC 600 Autopilot Installed in Daher Aerospace TBM 700/700N
Page 48 of 48
190-02011-08 Rev. 1
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