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Garmin GFC 600 Pilot’s Guide

190-01488-00 Rev. B

24

AFCS

GI 285 Overspeed Indication

UNDERSPEED PROTECTION

NOTE:

While underspeed protection is active, the aircraft will deviate from

the selected reference.

Underspeed Protection is designed to discourage aircraft operation below minimum

established airspeeds and is available when the autopilot is on.

When the aircraft is decelerating to within six seconds of reaching a predetermined

minimum airspeed (specified in the AFMS), the AIRSPEED aural will sound to alert the
pilot of the impending underspeed condition.

If the aircraft continues to decelerate, Underspeed Protection functionality depends

on which vertical mode is selected. For the purpose of this discussion, the vertical
modes can be divided into two categories: Those in which it is important to maintain
altitude for as long as possible (altitude-critical modes), and those in which maintaining
altitude is less crucial (non-altitude critical modes).

ALTITUDE-CRITICAL MODES (ALT, GS, GP, GA)

If the aircraft decelerates to stall warning for at least one second, the vertical and

lateral modes will change from active to armed. IAS and ROL will become the active
vertical and lateral modes and flash for five seconds, and the autopilot will provide
input causing the aircraft to pitch down and wings to level.

The AIRSPEED aural will sound every five seconds and a MINSPEED annunciation

will be displayed on the GMC 605.

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Summary of Contents for GFC 600

Page 1: ...GFC 600 Pilot s Guide ...

Page 2: ......

Page 3: ...anual may be reproduced copied transmitted disseminated downloaded or stored in any storage medium for any purpose without the express written permission of Garmin Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed for personal use provided that such electronic or printed copy...

Page 4: ...practice basic operation prior to actual use During flight operations carefully compare the Flight Director commands and autopilot response to all available navigation indications attitude displays and air data information For safety purposes always resolve any discrepancies before continued operation CAUTION The system does not contain any user serviceable parts Repairs should only be made by an ...

Page 5: ...armin GFC 600 Pilot s Guide 190 01488 00 Rev B RR 1 Part Number Change Summary 190 01488 00 Initial release Rev Date Description A June 2017 Production Release B July 2017 Removed software version number ...

Page 6: ...Garmin GFC 600 Pilot s Guide 190 01488 00 Rev B RR 2 Blank Page ...

Page 7: ...on 8 1 4 AFCS Controls 9 GMC 605 9 External Controls 10 1 5 System Indications 11 GMC 605 11 GI 285 Indications 12 Garmin PFD AFCS Indications 13 Section 2 Automatic Flight Control System 15 2 1 AFCS Operation 15 AFCS Pre Flight 15 Engaging the Autopilot 16 Flight Director Modes 16 Disengaging the Autopilot 17 2 2 Basic Autopilot Features 17 Flight Director 17 Control Wheel Steering 19 Yaw Damper ...

Page 8: ...43 Navigation Modes GPS VOR LOC 45 Approach Modes GPS VOR LOC 48 Flying A DME Arc With A GPS Navigator 51 Backcourse Mode BC 52 2 5 Electronic Stability Protection ESP 53 Roll Engagement 54 Pitch Engagement 56 Airspeed Protection 58 Section 3 Annunciations Alerts 59 3 1 Visual Annunciations and Alerts 59 3 2 Aural Alerts 62 Voice Alerts 62 Autopilot Disconnect Alert 62 Section 4 Abnormal Operation...

Page 9: ...tor function provides pitch and roll commands needed to guide the aircraft toward the active reference selected by the pilot If a compatible Primary Flight Display PFD is installed these pitch and rolls commands are displayed on the PFD as Command Bars When the Flight Director is active the pitch and roll commands can be hand flown by the pilot When the Autopilot is engaged the autopilot servos dr...

Page 10: ...elope While ESP utilizes the same sensors processors and actuators as the GFC 600 autopilot it is a separate mutually exclusive function ESP can be easily overpowered by the pilot and can be disabled using the AP DISC TRIM INT button 1 2 AFCS EQUIPMENT The basic GFC 600 system is comprised of the following equipment GMC 605 MODE CONTROLLER The panel mounted GMC 605 serves as the primary user inter...

Page 11: ... if it does not have an interface to an Air Data Computer a small Air Data Module must be attached to the back of the GMC s mounting tray to provide basic air data information to the AFCS The GMC 605 features a covered USB port on the front face of the unit allowing a convenient means of updating software and downloading diagnostics information to aid in troubleshooting CAUTION The USB port is not...

Page 12: ...smooth reliable operation The GSA 87 design incorporates an internal engagement solenoid and a gear train that allows the motor to be backdriven by the pilot in case the solenoid fails to disengage This eliminates the need for a mechanical slip clutch along with the associated performance limitations and maintenance requirements GSA 87 GI 285 ANNUNCIATOR PANEL The GI 285 Annunciator Panel provides...

Page 13: ...ank limit indications for the ESP function The PFD displays AFCS reference values and bugs for Vertical Speed VS and Indicated Airspeed IAS modes Nav source selection can be performed on the PFD and the GFC 600 will couple to the selected source for guidance The G500 G600 systems include an Air Data Computer which provides airspeed and baro corrected altitude to the AFCS This is particularly benef...

Page 14: ...path commands and older models that provide only basic lateral course deviation for guidance The WAAS enabled Garmin GNS and GTN series navigators also provide an interface to the GMC 605 that supports improved aircraft attitude computation thereby enhancingAFCS performance and increasing the availability of basic modes in the event of an air data failure The GTN 650 is an example of a compatible ...

Page 15: ...in an aircraft HORIZONTAL SITUATION INDICATORS HSI The GFC 600 can accept Heading commands and Course inputs from a variety of HSIs including mechanical instruments such as the Bendix King KI 525A and Century NSD360A and electronic HSI displays such as the Sandel SN3500 4500 DIRECTIONAL GYROS DG If GFC 600 is installed in an aircraft without an HSI the system can accept Heading commands from a var...

Page 16: ... Sonalert aural tone generator must be included with most GFC 600 installations to ensure the AP Disconnect aural is heard by the pilot if the audio panel fails or suffers a loss of power The GMA 345 is an example of a compatible audio panel GMA 345 GTX 335 345 R WITH GPS OPTION The GTX 335 345 R transponders with GPS Option can provide an interface to the GMC 605 that supports improved aircraft a...

Page 17: ...ng again deactivates the Flight Director and removes the Command Bars If the autopilot is engaged the key is disabled 3 YD Key Engages disengages the yaw damper if installed 4 LCD Display Displays AFCS modes references and annunciations 5 LVL Key Engages the autopilot in Level Mode or selects Level Mode if autopilot is already engaged 6 ALT Key Selects deselects Altitude Hold Mode 7 HDG Key Select...

Page 18: ...not found on the GMC 605 Control Common Name Typical Location Purpose AP DISC TRIM INT button Autopilot Disconnect Pilot control yoke stick Disengages the autopilot yaw damper and interrupts pitch trim operation or acknowledges an autopilot disconnect alert and mutes the associated tone Holding the AP DISC TRIM INT button down for five seconds will also disable Electronic Stability Protection GA b...

Page 19: ...AP FD and YD keys The left side of the LCD displays lateral Flight Director modes the center portion of the display provides vertical modes and references and the right side of the display serves as a message area for status and alerts Active modes and references are depicted in large letters along the upper portion of the display with armed modes in a smaller font along the lower portion The mess...

Page 20: ...utomatically by the AFCS The AP LED is illuminated in yellow when a trim failure has occurred or when a mistrim condition has developed AP Autopilot LED GMC 605 LEDs FD Flight Director LED YD Yaw Damper LED Refer to section 3 1 for more information about specific GMC 605 messages and LED annunciations GI 285 INDICATIONS The GI 285 Mode Annunciator is required in installations where the GMC 605 is ...

Page 21: ...ailure condition The TRIM annunciation is illuminated in yellow when a trim failure has occurred or when a mistrim condition has developed The pilot should reference the GMC 605 message area for more information regarding failures and mistrim conditions GI 285 Annunciator Refer to section 3 1 for more information about specific AP YD and TRIM annunciations on the GI 285 GARMIN PFD AFCS INDICATIONS...

Page 22: ...Rev B 14 System Overview Autopilot info on Garmin GDU 620 PFD Selected Altitude GPS is Selected Navigation Source Command Bars AFCS Status Annunciations Yaw Damper Status Lateral Modes Active Auto pilot Status Active Armed Vertical Modes Armed ...

Page 23: ...ht Test PFT to check internal GMC 605 functions interfaces and servo status While the test is in progress the GMC displays the message PFT The GMC s three LEDs are illuminated in yellow for 1 second and then in red for 1 second The GI 285 if installed will illuminate all lateral mode annunciations in yellow for 1 second followed by the AP YD TRIM annunciations in yellow for 1 second then the verti...

Page 24: ...ht Director reverts to the default pitch and or roll modes Active modes are annunciated on the GMC 605 s screen in large text Armed modes are annunciated in smaller text below the active modes and are queued to take effect as soon as capture criteria is met Automatic transition from armed to active mode is indicated by the armed mode annunciation moving up to the active mode field and flashing for...

Page 25: ...disconnect button Automatic disengagement is indicated by an aural alert and theAP LED on the GMC 605 flashing red The AP indication on the GI 285 also flashes red The aural alert and flashing annunciations continue until acknowledged by pressing the AP key or the autopilot disconnect button Automatic disengagement may occur due to a failure within the GFC 600 system loss of both GPS and air data ...

Page 26: ...gaged an additional press of the FD key will turn off the Flight Director and remove the command bars from the PFD NOTE The FD Key is disabled when the autopilot is engaged COMMAND BARS ON GARMIN PFD Upon activation of the Flight Director Command Bars are displayed in magenta on the PFD If the aircraft is being flown by hand the Command Bars are displayed hollow The Command Bars do not override th...

Page 27: ...g the CWS button if installed disengages the pitch and roll servos from the flight control surfaces and allows the aircraft to be hand flown Releasing the CWS button reengages the servos Depending on the active mode the Flight Director may be synchronized to a new reference upon CWS release Refer to the descriptions of vertical and lateral modes for specific CWS behavior in each mode Control Wheel...

Page 28: ...the AP key to turn on the autopilot If the autopilot is disengaged using the AP key or the MET switch the Yaw Damper will remain engaged and can be separately turned off by pressing the YD key If the autopilot is disengaged using the AP DISC TRIM INT button on the control yoke stick the Yaw Damper will also be disengaged NOTE In an installation that does not have a Yaw Damper servo pressing the YD...

Page 29: ...w for five seconds and then steady illumination A message is displayed indicating the trim axis and the direction ELE TRM UP indicates that the pitch servo is holding excessive nose up force and the pilot must manually trim the aircraft in the nose up direction to alleviate the load and restore the aircraft to an in trim condition Once the aircraft is in trim the yellow AP LED is extinguished and ...

Page 30: ...ntrol stick switch The MET switch is split into two adjacent parts which must be moved together to arm and activate the trim command AUTOTRIM NOTE Autotrim is available in aircraft that have an autopilot servo connected to the pitch trim system The same servo provides both the MET and Autotrim functions Autotrim will automatically adjust the pitch trim to keep the aircraft trimmed while the autopi...

Page 31: ...airspeed When an overspeed condition occurs the Flight Director will deviate from the active vertical reference and produce a pitch up command to slow the aircraft Engine power should be reduced and or the NOSE UP DN wheel moved in the UP direction to adjust the PIT or VS reference When Overspeed Protection becomes active the GMC 605 displays a MAXSPEED message the active vertical mode annunciatio...

Page 32: ...peed Protection functionality depends on which vertical mode is selected For the purpose of this discussion the vertical modes can be divided into two categories Those in which it is important to maintain altitude for as long as possible altitude critical modes and those in which maintaining altitude is less crucial non altitude critical modes ALTITUDE CRITICAL MODES ALT GS GP GA If the aircraft d...

Page 33: ...xiting Underspeed Protection When airspeed increases to 5 KIAS above the minimum speed the AIRSPEED aural and MINSPEED message will be turned off and the armed vertical and lateral Flight Director modes will change back to active The autopilot will resume tracking the previously selected vertical and lateral references NON ALTITUDE CRITICAL MODES VS LVL PIT IAS ALTS VNAV If the aircraft decelerate...

Page 34: ...ower has already been applied the pilot can move the NOSE UP DN wheel in the DN direction to reduce the pitch attitude or vertical speed reference When airspeed increases to 5 KIAS above the minimum speed the MINSPEED message will be removed and the armed vertical Flight Director mode will change back to active The autopilot will resume tracking the previously selected vertical reference NOTE When...

Page 35: ... Increments of change and acceptable ranges of values for each of these references using the NOSE UP DN wheel are also listed in the table Vertical Mode Description Control Annunciation Reference Change Increment Ref Range Pitch Hold Holds the current aircraft pitch attitude may be used to climb descend to the Selected Altitude default PIT 0 5 Varies by aircraft type see AFMS Level Mode Commands a...

Page 36: ...d Altitude IAS nnn kt 1 kt Varies by aircraft type see AFMS Glidepath Captures and tracks the SBAS GPS glidepath on approach GP Glideslope Captures and tracks the ILS glideslope on approach GS When the GFC 600 is receiving a Selected Altitude value from a Garmin PFD ALTS is armed automatically when PIT VS IAS or GA modes are active Autopilot Vertical Mode Summary PITCH HOLD MODE PIT When the autop...

Page 37: ...justed by pressing the CWS button hand flying the aircraft to establish a new pitch reference and then releasing the CWS button If the aircraft pitch attitude exceeds the autopilot pitch command limitations the Flight Director commands a pitch angle equal to the nose up down limit GMC 605 AND GI 285 ANNUNCIATIONS Both the GMC 605 and GI 285 show the PIT annunciation in their active vertical mode s...

Page 38: ...t per minute and a lateral reference of zero bank angle When the LVL key is pressed all armed and active modes are cancelled and theAFCS reverts to LVL mode for pitch and roll While in level mode all other modes are available by pressing the corresponding button NOTE The Level Mode may be helpful if the aircraft encounters strong turbulence making it impractical to maintain normal references such ...

Page 39: ...Use Height MUH specified in the Airplane Flight Manual Supplement AFMS Pressing the GA button while in the air allows the execution of a missed approach or a go around without disconnecting the autopilot i e Coupled Go Around Go Around mode arms Selected Altitude Capture mode automatically and any attempts to modify the aircraft attitude i e with the CWS button or the NOSE UP DN wheel result in re...

Page 40: ...ing the CWS button hand flying the aircraft to a different altitude and then releasing the CWS button Without Garmin PFD When there is no Garmin PFD installed the Altitude Reference is not displayed on the GMC 605 and the autopilot cannot automatically compensate for small altitude changes introduced when the altimeter setting is updated The NOSE UP DN wheel may be used to adjust the Altitude Refe...

Page 41: ...5 Annunciating Alt Hold Mode SELECTED ALTITUDE CAPTURE MODE ALTS NOTE SelectedAltitude Capture Mode is available in aircraft with a Garmin PFD Selected Altitude Capture mode is a transitional mode used in conjunction with other vertical modes It is not directly selectable by the GMC 605 panel or other equipment Instead Selected Altitude Capture when supported by a GDU interface is automatically ar...

Page 42: ...erence altitude As Altitude Hold mode becomes active the ALT annunciation moves to the active vertical mode field and flashes for 10 seconds to indicate the automatic transition GMC 605 Annunciating Selected Altitude Capture Mode Changing the Selected Altitude on the PFD while Selected Altitude Capture mode is active causes the AFCS to revert to Pitch Hold mode with Selected Altitude Capture mode ...

Page 43: ...lue in FPM and can be adjusted via the controls on the GDU WhenVertical Speed mode is active the GMC 605 also displays the Vertical Speed Reference and provides a means of adjustment via the wheel The system will function as follows With the Flight Director FD and Autopilot AP off the Vertical Speed bug on the PFD can be adjusted using the controls on the GDU When the Flight Director FD is on rega...

Page 44: ... The IAS reference can be changed using the NOSE UP DN wheel Moving the knob in the NOSE UP direction decreases the reference by 1 knot per click and the NOSE DN direction increases the reference by 1 knot per click The airspeed reference can also be adjusted by pressing the CWS button hand flying the aircraft to establish a new airspeed and then releasing the CWS button Engine power must be adjus...

Page 45: ...oach with vertical guidance LPV LNAV VNAV LNAV V LP V is loaded into the active flight plan The active waypoint must be part of the flight plan cannot be a direct to a waypoint not in the flight plan 2 Ensure that GPS is the selected navigation source 3 GMC 605 Press the APR key The AFCS maintains the current mode but arms Glidepath mode 4 Upon reaching the glidepath the AFCS vertical mode transit...

Page 46: ...n is valid The CDI is at less than full scale deviation Automatic sequencing of waypoints has not been suspended no SUSP annunciation on the HSI NOTE Pressing the CWS button while Glidepath mode is active does not cancel the mode Upon release of the CWS button the autopilot will guide the aircraft back to the glidepath GMC 605 AND GI 285 ANNUNCIATIONS The GMC 605 and GI 285 annunciate GP for Glide...

Page 47: ... Ensure that LOC is the selected navigation source 3 GMC 605 Press the APR key This simultaneously arms LOC and GS Glideslope modes Once the localizer has been captured LOC is annunciated as the active lateral mode the glideslope can also be captured NOTE Pressing the CWS button while Glideslope mode is active does not cancel the mode Upon release of the CWS button the autopilot will guide the air...

Page 48: ...ode and Go Around mode Lateral Mode Description Control Annunciation Roll Hold Holds the current aircraft roll attitude or rolls the wings level depending on the bank angle at the time of Roll mode activation default ROL Level Mode Commands wings level zero bank angle and also commands a pitch attitude necessary to establish a vertical speed of 0 fpm LVL Go Around Commands zero bank angle and also...

Page 49: ...e Track Captures and tracks a localizer signal for backcourse approaches BC Approach GPS Capture Track Glidepath mode automatically armed Captures and tracks the selected approach navigation source GPS VOR LOC GPS VAPP Approach VOR Capture Track Approach LOC Capture Track Glideslope mode automatically armed LOC The AFCS limits turn rate to 3 degrees per second standard rate turn The GMC 605 displa...

Page 50: ...ctor is activated Roll Hold mode is selected by default The current aircraft bank angle at the time of activation is held as the reference unless the bank angle is greater than 20 deg or less than 6 deg as defined in the following table Bank Angle Flight Director Response 6 Rolls wings level 6 to 20 Maintains current aircraft roll attitude 20 Limits bank to 20 Roll Hold Mode Responses When operati...

Page 51: ...000 display unit a compatible Horizontal Situation Indicator or a compatible Directional Gyro Heading Select mode is activated by pressing the HDG key Heading Select mode acquires and maintains the Selected Heading Turn the HDG Knob on the HSI or DG to set the Selected Heading When using a Garmin PFD turns are commanded in the same direction as Selected Heading Bug movement even if the Bug is turn...

Page 52: ...ft heading or 180 deg to the current heading may result in the autopilot not turning in the expected direction Holding the CWS button if equipped and hand flying the aircraft does not change the Selected Heading The autopilot guides the aircraft back to the Selected Heading upon release of the CWS button GMC 605 AND GI 285 ANNUNCIATIONS The GMC 605 and the GI 285 display the HDG annunciation when ...

Page 53: ...on source the Flight Director will follow GPS Roll Steering commands when available Some older GPS navigators do not provide Roll Steering commands to the AFCS in which case the Flight Director creates steering commands using course and deviation inputs When the navigation source is VOR or LOC the Flight Director creates roll steering commands from the Selected Course and deviation Navigation mode...

Page 54: ... Localizer approach The AFCS does not support automatic transition from a Navigation mode to an Approach mode and will revert to ROL mode if it senses that the navigation source has changed CAUTION Navigators or PFDs with automatic CDI source switching capability should be configured with automatic switching disabled If Navigation mode is active and any of the following occur the AFCS reverts to R...

Page 55: ...05 AND GI 285 ANNUNCIATIONS The GMC 605 and GI 285 will annunciate the appropriate lateral mode as GPS VOR or LOC depending on the selected navigation source when the NAV key was pressed GMC 605 Annunciating Various NAV Modes GI 285 Annunciating Various Nav Modes ...

Page 56: ... inputs to fly the approach Pressing the APR key when the CDI deflection is greater than half scale arms the selected approach mode GMC 605 Annunciating GPS Approach Mode Armed If the CDI deflection is less than half scale the approach is automatically captured when the APR key is pressed When the AFCS is interfaced to a Directional Gyro as opposed to an HSI Approach mode cannot be armed The pilot...

Page 57: ... active waypoint must be part of the flight plan cannot be a direct to a waypoint not in the flight plan 2 EXTERNAL NAVIGATOR Ensure that GPS is the selected navigation source 3 GMC 605 Press the APR key VORApproach mode VAPP provides greater sensitivity for signal tracking thanVOR Navigation mode Selecting VOR Approach Mode 1 EXTERNAL NAVIGATOR Ensure a valid VOR frequency is tuned 2 EXTERNAL NAV...

Page 58: ...Pressing the CWS button and hand flying the aircraft does not change the selected course while in Approach mode Upon release of the CWS button the autopilot will guide the aircraft back to the selected course or GPS flight plan GMC 605 AND GI 285 ANNUNCIATIONS The GMC 605 will annunciateVORApproach mode asVAPP LOCApproach mode as LOC and GS and GPS Approach mode as GPS and GP The annunciation disp...

Page 59: ...izer approach the pilot must manually change the navigation source from GPS to VOR LOC when the arc segment is completed The Flight Director will revert to ROL mode and the pilot must press the APR key to capture and track the VOR or Localizer approach If the pilot decides to intercept the arc at a location other than the published IAF i e ATC provides vectors to intercept the arc and subsequently...

Page 60: ...nd deviation when in Backcourse mode If the Course Deviation Indicator CDI shows greater than half scale when the BC key is pressed the mode is armed If the CDI is less than half scale Backcourse mode is automatically captured NOTE When the AFCS is interfaced to a DG Backcourse mode cannot be armed Set the Selected Heading on the DG to the same value as the Selected Course when Backcourse mode is ...

Page 61: ...tations Stability protection for each flight axis is provided by the autopilot servos which apply force to the appropriate control surface s to discourage pilot control inputs that would cause the aircraft to exceed the normal or protected flight envelope This is perceived by the pilot as resistance to control movement in the undesired direction when the aircraft approaches a steep attitude and or...

Page 62: ...y the aircraft ROLL ENGAGEMENT NOTE This section describes ESP indications displayed on a Garmin PFD If a Garmin PFD is not installed the AFCS will still provide the same Roll ESP function but without any displayed indications or annunciations Roll Limit Indicators are displayed on the roll scale of a Garmin PFD at 45 deg to indicate where ESP will engage As roll attitude exceeds the limit ESP wil...

Page 63: ...sing to ESP Engagement Before ESP Engage After ESP Engage ESP Engage 45 Aircraft Roll Attitude 44 ESP Disengage 30 Aircraft Roll Attitude 46 Once engaged ESP force will be applied between bank angles of 30 and 75 The force increases as roll attitude increases and decreases as roll attitude decreases The applied force is intended to encourage pilot input that returns the airplane to a more normal r...

Page 64: ...ttitudes Most aircraft are configured such that the torque applied by ESP increases to its maximum value when pitch attitude has exceeded the configured nose up or nose down pitch limits by 5º The opposing force increases or decreases depending on the pitch angle and the direction of pitch travel This force is intended to encourage movement in the pitch axis in the direction of the normal pitch at...

Page 65: ...d Force Increases as Pitch Increases Decreases as Pitch Decreases NOTE The Pitch ESP operating range may vary for each airframe type The specific values depicted in the figure above are only to illustrate the Pitch ESP function Reference the AFMS for the Pitch ESP limits for a specific aircraft ...

Page 66: ...the force will smoothly be reduced to zero and ESP will disengage Low Speed Protection is inhibited when the aircraft is below 200 above ground level If the AFCS is not receiving height above ground information from an external source Low Speed Protection is not available HIGH AIRSPEED PROTECTION Exceeding the airspeed limit configured for each airframe type and usually set below Vne will result i...

Page 67: ... associated with the annunciations and alerts NOTE A Garmin PFD when installed with GFC 600 will provide similar annunciations and alerts to those listed below Refer to the G500 G600 Pilot s Guide for a description of the PFD indications related to AFCS GMC 605 Message GMC 605 LED GI 285 Indication Description PFT Preflight Test is in progress PFT FAIL AP Preflight Test has failed AP FAIL AP Autop...

Page 68: ...d ALT modes Overspeed Underspeed Protection and High Speed ESP may not be supported and AFCS performance may be degraded ESP OFF Electronic Stability Protection ESP has been turned Off ESP FAIL Electronic Stability Protection ESP function has failed CWS ON AP Control Wheel Steering is active the GMC 605 s AP LED flashes green continuously during CWS SET HDG CRS Pilot action required to set the Sel...

Page 69: ...key on the GMC 605 is stuck in the active state APR KEY STK The APR key on the GMC 605 is stuck in the active state BC KEY STK The BC key on the GMC 605 is stuck in the active state VNV KEY STK The VNV key on the GMC 605 is stuck in the active state IAS KEY STK The IAS key on the GMC 605 is stuck in the active state VS KEY STK The VS key on the GMC 605 is stuck in the active state ALT KEY STK The ...

Page 70: ...cond time period the autopilot engages automatically in Level Mode and the ENGAGING AUTO PILOT aural is played AUTOPILOT DISCONNECT ALERT Autopilot disengagement is accompanied by an aural bee boop alert tone which is played through the audio panel and also through a separate Sonalert device when installed The Sonalert is a small speaker that plays a tone heard in the cockpit above the ambient noi...

Page 71: ...econds after power in removed 5 Release the AP DISC TRIM INT button 4 2 OVERPOWERING AUTOPILOT SERVOS In the context of this discussion overpowering refers to any pressure or force applied to the controls when the autopilot is engaged In an emergency the pilot can forcibly overpower the servos and move the controls throughout their full range of motion without disengaging the autopilot however eve...

Page 72: ...pen EFD 1000 HSI DG VHF Nav Radio Add l GSA 87 Servo Basic Autopilot Features Flight Director Command Bar Display OR Control Wheel Steering 1 Yaw Damper 2 Manual Electric Trim 3 4 Autotrim 4 Overspeed Protection 6 Underspeed Protection 6 Electronic Stability and Protection ESP Features Pitch Roll Engagement High Speed Protection 6 Low Speed Protection 7 OR 7 ...

Page 73: ...quires valid air data input to the GMC 605 via an Air Data Module or Air Data Computer 7 Requires a Garmin GTN or PFD with a valid Terrain Database 8 WAAS and Roll Steering not required for basic lateral GPS guidance 9 Requires VHF Nav Radio that includes a glideslope receiver Basic GMC 605 Function WAAS GPS Nav Garmin PFD Aspen EFD 1000 HSI DG VHF Nav Radio Add l GSA 87 Servo Vertical Autopilot M...

Page 74: ...ction WAAS GPS Nav Garmin PFD Aspen EFD 1000 HSI DG VHF Nav Radio Add l GSA 87 Servo Lateral Autopilot Modes Roll Hold Heading OR OR OR GPS Navigation 8 VOR Navigation OR OR OR LOC Navigation OR OR OR BC Navigation OR OR OR GPS Approach VOR Approach OR OR OR LOC Approach OR OR OR ...

Page 75: ...s 17 Autotrim 22 Control Wheel Steering 19 Manual Electric Trim 22 Manual Trim 21 Overspeed Protection 23 Underspeed Protection 24 Yaw Damper 20 Flight Director 17 Malfunction 63 Autopilot Disconnect Alert 62 Autotrim 22 B Backcourse Mode 52 BC See Backcourse Mode BC Key 10 C Command Bars 18 Control Wheel Steering 19 Control Wheel Steering CWS 19 CWS switch 10 D DG See Directional Gyros Dimmer kno...

Page 76: ...otection 58 Horizontal Situation Indicators 7 HSI See Horizontal Situation Indicators I IAS 36 IAS Key 10 Indicated Airspeed Mode 36 L Lateral Modes 40 Approach GPS 41 Approach LOC 41 Approach Modes GPS and LOC 48 Approach VOR 41 Backcourse Mode 52 Go Around 40 Heading Select Mode 43 Level Mode 40 Navigation Backcourse 41 Navigation Modes GPS VOR LOC 45 Roll Hold Mode 42 LCD Display 9 Level Mode 3...

Page 77: ...e 28 30 R ROL See Roll Hold Mode Roll Engagement 54 Roll Hold Mode 42 S Selected Altitude 28 33 Selected Altitude Capture Mode 28 31 33 Selected Heading 43 System Controls 9 U Underspeed Protection 24 25 V Vertical Modes 27 Altitude Hold 27 Glidepath 28 Glideslope 28 Go Around 27 Indicated Airspeed 28 Level Mode 27 Pitch Hold 27 Selected Altitude Capture 28 Vertical Speed 28 Vertical Speed Mode 33...

Page 78: ...erty House Hounsdown Business Park Southampton Hampshire SO40 9LR U K Garmin Corporation No 68 Zhangshu 2nd Road Xizhi District New Taipei City Taiwan Contact Garmin Product Support at www flygarmin com For warranty information refer to https fly garmin com fly garmin support warranty information 190 01488 00 Rev B 2017 Garmin Ltd or its subsidiaries ...

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