Home

Garmin Part 23 AML STC Airplane Flight Manual Supplement

1. JoyeoIpul Aqpueys OY JO UONE E SU paiqeus 5 LAS J0 pue SMV L 1 LSNW 5141 029 Aq payeiouab jeune s uo 51 029 s Juawidinbs jeuondo y ay jeuondo Aq jou si jeuondo puodo dnyoeq YIM Aew Aqpueis Apease u wdinbg Aju 14614 1614 leuondo 59 19212207 Z ON ON SVES Sd9 Z ON SVES Sd
2. 49 733 TAWS ANNUNCIATIONS ON THE PFD FROM GARMIN NAVIGATOR 49 7 6 STORMSCOPE 49 7 7 ADS B TRAFFIC SYSTEM INTERFACE 50 7 8 5555 5 ee 50 7 9 GWX 70 WEATHER 20 0 0000 0 50 7 10 DEPICTION OBSTACLES AND 5 51 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 10 of 51 Section 1 GENERAL 11 G500 G600 Primary Flight Multi Function Display System The G500 G600 System consists of a Primary Flight Display PFD and Multi Function Display MFD housed in a single Garmin Display Unit GDU plus an Air Data Computer ADC Attitude and Heading Reference System AHRS and optional signal adapter GAD The G500 G600 interfaces with other installed systems in the aircraft including Garmin GPS SBAS navigators VHF navigation radios datalinks traffic systems weather radars audio panels video sources radar altimeters ADF receivers DME receivers and autopilots The G500 G600 system can optionally provide Terrain Alerting functions and display of Terminal Procedures The primary function of the PFD is to provide attitude heading air data and navigation information to the pilot The primary function of the MFD is to provide data which will facilitate the pilot s awareness with respect to surrounding factors that may affect the
3. For IFR flight a fully functional G500 G600 system shall not generate system alerts which indicate faults within the system or any interfaced equipment 2 21 275 325 Altitude Preselect When the altitude preselect option is installed with KFC 275 325 autopilots SOFT RIDE SR mode shall be disengaged during altitude capture mode ALTC The following placard must be installed near the autopilot mode controller or above PFD 1 DISENGAGE SOFT RIDE DURING ALTITUDE CAPTURE ALTC 2 22 Type Ratings Unless otherwise authorized by this section operations are prohibited in aircraft that require a type rating under 14 CFR 61 31 a AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 25 of 51 2 23 Electronic Standby Instrument Power The independent power source for the electronic standby instrument s shall be verified to be operational before flight or the electronic standby s must be considered inoperative For the verification procedure refer to the approved Airplane Flight Manual and or Instructions for Continued Airworthiness for the independent power source 2 24 Electronic Flight Bag EFB Applications Class 3 EFB applications have not been evaluated as part of this STC Use of the system for EFB applications such as the moving map or electronic charts is not authorized if additional evaluation or operational approval is required unless that approval has been obtained 2 25 Surface Operation
4. cssessssesececsessssececececeesessececeeeceesenssaeeeesens 12 1 3 NAVIGATION SOURCES 12 1 4 SYNTHETIC VISION TECHNOLOGY 5 2 13 1 5 AUTOPILOT 0 0 02001000001000000000000 000 14 1 6 AUDIO PANEL 15 17 TRAFFIC DISPLAY Recto detach a eo eS 15 1 8 WEATHER DATA 15 1 9 VIDEO DISPLAY otee ee ke saiia 15 1 10 RADAR 15 1 11 HIGH SPEED DATA BUS INTERFACE cccsessscecececeesscseceeececeenenteaeees 16 1 12 SINGLE G500 G600 OPERATIONAL BLOCK 17 1 13 DUAL G500 G600 OPERATIONAL BLOCK DIAGRAM 18 12145 DEFINITION S absense 19 SECTION 2 LIMITATIONS wsisssssssscsssscssessessssoosecsssassessssenscsesscesnasssonsesansose 20 2 1 COCKPIT REFERENCE amp PILOT S 20 2 2 SYSTEM SOFTWARE REQUIREMENTS 20 2 3 MOVING 20 2 4 DATABASE CARDS 5 el eR RR 20 2 5 AHRS OPERATIONAL 2 20 2 6 MAGNETIC VARIATION OPERATIONAL 2 20 2 7 NAVIGATION 20 2 8 AHRS NORMAL OPER
5. Section 4 NORMAL PROCEDURES Refer to the Garmin G500 G600 PFD MFD System Cockpit Reference Guide P N 190 00601 03 or G500 G600 Pilot s Guide P N 190 00601 02 for normal operating procedures This includes all Primary Flight Display and Multi Function Display information Although intuitive and user friendly the G500 G600 System requires reasonable degree of familiarity to avoid becoming too engrossed at the expense of basic instrument flying in IMC and basic see and avoid procedures in VMC Pilot workload will be higher for pilots with limited familiarity in using the unit in an IFR environment particularly without the autopilot engaged Garmin provides training material with the Cockpit Reference Guide and the detailed Pilot s Guide Pilots should take full advantage of these training tools to enhance system familiarization 41 PFD Knob amp PFD Soft Keys The basic PFD controls are on the side and bottom of the PFD next to and beneath the PFD display The rotary knob performs the function annunciated on the display just to the upper left of the HSI HDG CRS ALT V S or BARO If no function is annunciated then the knob is providing a HDG function Assigning the function of the knob is done by pressing releasing one of the dedicated function buttons to the left of the display The knob defaults back to HDG if it is not rotated for a period of 10 seconds The Garmin G500 G600 PFD MFD System Cockpit Reference Guide describes each f
6. 12 Single G500 G600 Operational Block Diagram Adapter optional GAD 43 43e Equipment Installed per this STC Aircraft Systems Magnetometer GMU 44 Electric required optional No 1 VOR Localizer GS optional No 2 VOR Localizer GS optional 2 GPS SBAS Navigator Autopilot Flight Director optional ADF DME optional Compass required Standby Attitude PFD MFD Display 620 optional Air Data Computer GDC 74 Temperature Probe GTP 59 Audio Panel No 1 GPS SBAS Navigator optional Existing Equipment already p aircraft Traffic optional Datalinks optional Weather Radar optional Radar Altimeter optional Stormscope optional Video Source optional Standby Attitude may be replaced with electric attitude indicator with integral dedicated backup battery Audio panel connection to GDU 620 is recommended for tones and aural alerts generated by the GDU 620 This MUST be connected if TAWS and or SVT is enabled Installation of the Mid Continent electric standby attitude indicator is approved by this STC AFMS GARMIN G500 G600 SYSTEM FAA APPROVED 190 00601 01 Rev K Page 17 of 51 1 13 Dual G500 G600 Operational Block Diagram OLS 14 Aq
7. 2 15 TAWS Function GDU 620 Units with internal TAWS Only the G600 system optionally contains Class B TAWS a TSO C151b certified function The G600 terrain configuration is indicated on the dedicated terrain page of the MAP group TAWS B will be displayed as the page title if this function is configured Pilots are authorized to deviate from their current ATC clearance to the extent necessary to comply with TAWS warnings Navigation shall not be predicated upon the use of TAWS To avoid unwanted alerts TAWS shall be inhibited when landing at an airport that is not included in the airport database 2 16 Datalinked Weather Display XM GFDS FIS B weather This limitation applies to datalinked weather products from SiriusXM via a GDL 69 69A FIS B via a Garmin ADS B receiver and Connext via a GSR 56 Do not use data link weather information for maneuvering in near or around areas of hazardous weather Information provided by data link weather products may not accurately depict current weather conditions Do not use the indicated data link weather product age to determine the age of the weather information shown by the data link weather product Due to time delays inherent in gathering and processing weather data for data link transmission the weather information shown by the data link weather product may be significantly older than the indicated weather product age Do not rely solely upon data link services to provide Temporary Flig
8. Garmin Adapter GAD 43 43e Electric Standby Attitude Indicator Except L 3 Trilogy and Mid Continent SAM installations In dual installations the pilot side equipment is suffixed with the number 1 and the copilot side equipment is suffixed with the number 2 For example PFD 1 and PFD 2 Equipment that receives power from two different circuit breakers will be suffixed with the letters A and B For example PFD 1A and PFD 1B or PFD 2A and PFD 2B 13 Navigation Sources The G500 G600 requires at least one Garmin GPS SBAS navigation unit to ensure the integrity of the Attitude and Heading Reference System The AHRS will still operate in a reversionary mode if the GPS fails and the attitude display on the PFD will still be presented see Paragraph 2 8 The G500 G600 HSI be selected to display course deviation information from up to four independent sources two GPS and two VHF NAV In addition the HSI can display two simultaneous bearing pointers sourced from GPS VHF NAV or ADF DME distances can be displayed adjacent to the HSI AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 12 of 51 14 Synthetic Vision Technology SVT SVT uses an internal terrain database and GPS location to present the pilot with a synthetic view of the terrain in front of the aircraft The purpose of the SVT system is to assist the pilot in maintaining situational awareness with regard to the terrain and traffic surroundin
9. STBY text is steadily illuminated Verify that the red gyro warning flag is not displayed Seek visual meteorological conditions VMC or land as soon as practical operation of standby attitude indicator is limited by battery life If the amber STBY text is steadily illuminated automatic operation 1 2 Verify that the red gyro warning flag is not displayed Seek visual meteorological conditions VMC or land as soon as practical operation of standby attitude indicator is limited by battery life WARNING Do not press the STBY PWR when the amber STBY text is steadily illuminated This will turn off the backup battery and the red gyro warning flag will be displayed If the STBY PWR button is inadvertently pressed and the red gyro warning flag is displayed press the STBY PWR button again to return to battery power operation red gyro warning flag should not be displayed AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 29 of 51 3 1 7 TAWS WARNING Red annunciator on PFD and aural PULL UP 1 Disconnect Autopilot 2 Initiate maximum power climb at best angle of climb airspeed Vx After warning ceases 3 Climb and maintain safe altitude 4 Advise ATC of altitude deviation if appropriate NOTE Only vertical maneuvers are recommended unless either operating in visual meteorological conditions VMC or the flight crew determines based on all available information that turn
10. aircraft O GAD 43 provides attitude to the autopilot GAD 43 provides yaw rate to the yaw damper GAD 43 provides baro correction to the altitude preselector GDU 620 provides attitude air data to autopilot 4 6 1 Attitude and Rate Based Autopilots Attitude based autopilots may be driven by the standby gyro a remote mounted gyro the GDU 620 or the GAD 43 adapter If the GDU 620 or GAD 43 is providing attitude to the autopilot it will be indicated in section 4 6 above Otherwise if the attitude based autopilot is receiving attitude from the standby a remote gyro the autopilot attitude input is independent of the attitude displayed on the PFD Rate based autopilots are driven by a turn coordinator gyro which may be mounted in the instrument panel or remotely mounted The autopilot rate input is independent of the G500 G600 system The pilot must understand the autopilot system inputs to detect faults and capabilities with inoperative equipment Refer to the autopilot flight manual for operational information AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 39 of 51 4 6 2 Course NAV Selection coupling to the autopilot When operating the autopilot in NAV mode the deviation information from the installed navigation sources i e GPS1 GPS2 NAV1 2 is switched via the G500 G600 PFD display Whatever is displayed on the HSI is the NAV source the autopilot is following Most autopilots
11. also use the course datum to determine the best intercept angles when operating in NAV mode 4 6 3 Heading Bug coupling capability to the autopilot When operating the autopilot in HDG mode the difference between the HDG bug location on the HSI and the actual aircraft heading creates an error signal which the autopilot will minimize by turning in the direction of the bug If the bug is turned more than 180 degrees the autopilot may turn the airplane in the opposite direction of the desired turn 4 6 4 GPSS emulated via HDG mode For autopilots that do not support digital GPSS signals GPSS functionality may be emulated by operating the autopilot in HDG mode and selecting GPSS on the PFD Depending on the installation GPSS mode may be toggled via an external switch located near the autopilot control panel or by pressing and holding the HDG button on the PFD If an external switch is installed it will be either a toggle or push button switch as depicted below AP HDG DATUM AP HDG DATUM push button HDG toggle switch If the installation uses the HDG button on the PFD the PFD Knob Mode Indicator is expanded to label the button function HOLD HDG FOR GPSS HOLD HDG FOR HDG BUG GPSS OFF When GPSS is selected on the PFD the heading bug on the HSI changes to a hollow outline and a crossed out heading bug appears in the PFD Knob Mode Indicator indicating that the autopilot is not coupled to the h
12. radars The G500 G600 system can display data from StormScope lightning detection systems 19 Video Display The G500 G600 can display images from up to 2 video inputs Video images are displayed on the MFD The G500 G600 does not provide a means to control the video source however the digital images from the video source can be adjusted using the G500 G600 1 10 Radar Altimeter The G500 G600 supports the display of radar altitude on the PFD from certain radar altimeters AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 15 of 51 1 11 High Speed Data Bus Interface Some Garmin equipment connected to the G500 G600 system utilizes the High Speed Data Bus HSDB interface HSDB is similar to an Ethernet bus and provides a high speed interface between Garmin avionics Like Ethernet data between two units may be passed through intermediate hub units Interfaced equipment that uses HSDB includes the GTN 6XX 7XX navigators GDL 69 datalink receiver GDL 88 ADS B transceiver GWX 68 70 weather radar and GTS 8 traffic systems The HSDB interfaces are installed to so that maximum data path redundancy is achieved However depending on the number of HSDB units installed failure of one HSDB unit may result in loss of data on the G500 G600 from downstream HSDB units Any loss of data will be annunciated on the G500 G600 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 16 of 51 1
13. target relative to your ownship symbol The direction the traffic target is pointed may vary greatly from the motion vector and a target may be getting closer to your aircraft independent of the direction the target is pointed A green relative motion vector pointed towards your ownship indicates that the traffic target is converging on your aircraft Traffic targets displayed on the dedicated traffic page may be selected using the knobs in order to obtain additional information about a traffic target 78 Flight Plan The Flight Plan shown on the GDU 620 is the same as that provided by the GPS navigation source selected on the PFD When waypoints are removed from the Flight Plan on the GPS navigator or when the entire flight plan is deleted it may take as long as 20 seconds for the change to be reflected on the G500 600 Flight Plan page and map 7 9 GWX 70 Weather Radar The GWX 70 Weather Radar uses Doppler technology to provide advanced features to the flight crew such as turbulence detection and ground clutter suppression The turbulence detection function can only detect turbulence between 2 5nm and 40nm ahead of the aircraft The display of turbulence is only provided when the radar range is set to 160nm or less NOTE Turbulence detection does not detect all turbulence especially that which is occurring in clear air The display of turbulence indicates the possibility of Severe or greater turbulence as defined in the Aeronautical I
14. the vertical speed PFD knob mode indicator when vertical speed is being reduced automatically Manually changing the selected vertical speed while AUTO is displayed will cancel automatic vertical speed reduction 4 6 7 2 Bendix King Autopilots To select and maintain a vertical speed 1 Press and hold the VS button on the PFD to synch the VS to current vertical speed and engage vertical speed mode 2 Select the desired vertical speed with the PFD vertical speed bug NOTE When VS mode is engaged the VS bug will be synced to the aircraft s current vertical speed and the selected VS with flash momentarily VS is displayed in green text in the upper right corner of the PFD to indicate that VS mode is engaged While VS mode is engaged the vertical speed bug may be changed by e Adjust the vertical speed bug with the PFD knob or Press and hold the vertical trim rocker switch on the autopilot in the desired direction or e Press the CWS button on the control wheel to synchronize the vertical speed bug to the current vertical speed AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 43 of 51 4 6 8 Flight Director Display If autopilot flight director commands are interfaced to the G500 G600 they will be presented as a single cue flight director on the PFD Control of the flight director is accomplished via the autopilot flight director controller there are no pilot controls or adjustments for the flight directo
15. valid Air Data The G500 G600 monitors these integrity systems automatically and will alert the pilot when the AHRS is not receiving GPS or Air Data Note In dual GPS installations only one GPS needs to be available to the AHRS for IFR flight 2 9 Airspeed Limitations and Indicator Markings The original type design approved airspeed limitations remain in effect The airspeed limitations stated in the AFM POH standby airspeed indicator and or airspeed limitation placards must be observed The G500 G600 airspeed tape displays red white striping to indicate the maximum allowable airspeed This maximum allowable airspeed display is configured to indicate the appropriate maximum allowable airspeed for the airplane including variations for altitude or Mach number The G500 G600 airspeed tape displays a red low speed awareness band at the lower range of the airspeed tape This low speed awareness band is configured to a fixed value It does not indicate an actual or calculated stall speed and does not adjust with variations in aircraft weight or other factors All other G600 airspeed tape indications are configured to indicate the original type design limitations The G500 G600 airspeed tape does not adjust these additional markings including Vno landing gear or flap speed limitations for variations with aircraft weight altitude or other factors 2 10 Aerobatic Maneuvers Do not conduct aerobatic maneuvers if uninter
16. 00 000 27 3 2 ABNORMAL 31 3 3 WARNINGS CAUTIONS AND 5 5 34 SECTION 4 NORMAL PROCEDURES 37 4 1 PFD KNOB amp PFD SOFT 8 00000 37 4 2 KNOBS amp MED SOFT 6 00000 0 00 000 37 4 3 ALTITUDE SYNCHRONIZATION 38 44 ELECTRIC STANDBY ATTITUDE GYRO MID CONTINENT 4200 AND 4300 5 38 4 5 SYNTHETIC VISION 38 4 6 AUTOPILOT OPERATIONS WITH THE G500 G600 SYSTEM 39 47 SALW ae 45 4 8 RADAR ALTIMETER 45 SECTION 5 4 1 4 211 41 4 0 66 64 6660 1 0 000 46 SECTION 6 WEIGHT AND 4 0 46 SECTION 7 SYSTEM DESCRIPTIONG cssssscssssssccssssccscssseccsssssccessnees 47 7 1 5 E 47 7 2 ELECTRIC STANDBY ATTITUDE 2 48 7 3 AUTOPILOT INTERFACE 5 48 7 4 TAWS FUNCTION GDU 620 UNITS WITH INTERNAL 5
17. 500 G600 navigation source selection described herein Changing the navigation sources displayed on the HSI by pressing the CDI button or the 1 2 button may result in some autopilots disconnecting or entering a wings level mode AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K Page 48 of 51 74 TAWS Function GDU 620 Units with internal TAWS In Dual G600 installations TAWS audio is only provided by the Pilot side GDU If the Pilot side GDU TAWS becomes inoperative the Co Pilot side GDU TAWS visual annunciations may still function but the aural TAWS alerts will not be heard 7 5 TAWS Annunciations on the PFD from a Garmin navigator The G500 G600 will display TAWS Terrain Awareness and Warning System annunciations on the PFD if the G500 G600 is interfaced to a Garmin navigator with integrated TAWS on GPS 1 The required TAWS annunciations appear in the upper right of the PFD These annunciations include PULL UP red TERRAIN yellow TER N A yellow TER INHB white These annunciations are not relative to the terrain displayed on the MFD or the yellow red terrain shading of the Synthetic Vision displayed on the PFD of the G500 G600 system Refer to the Garmin navigator Airplane Flight Manual Supplement for proper pilot action and information on these alerts TAWS alerts on the PFD of the G500 G600 System are only displayed from the GPS TAWS navigator interfaced as GPS 1 and are displayed regardless of the system 1 2 setting w
18. 9 sapon olpny 6S 19 L 6S 19 2 072 909 geq 2 11 589 SYHV ve NWO 029 Ae dsiq 101002 9 Ae dsiq GAW Gsd pd Jayndwog 22599 SUYHV OLS 514 sed 5 5 545 yeng NWO sa depy 190 00601 01 AFMS GARMIN G500 G600 SYSTEM FAA APPROVED Page 18 of 51 1 14 Definitions The following terminology is used within this document ADC Data Computer ADF Automatic Direction Finder ADS B Automatic Dependent Surveillance Broadcast AHRS Attitude amp Heading Reference System AUX Auxiliary BARO Barometric Pressure BRG Bearing CDI Course Deviation Indicator CRS Course DME Distance Measuring Equipment FD Flight Director FPM Flight Path Marker GDU Garmin Display Unit GPS Global Positioning System GPSS GPS Poll Steering HDG Heading HSI Horizontal Situation Indicator IFR Instrument Flight Rules IMC Instrument Meteorological Conditions LOI Loss of Integrity MFD Multi F
19. ARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 2 of 51 LOG REVISIONS Pag FAA Approval Added GAD 43 to section 1 2 Seyed Joussef Hashemi Ri Rev Page 8 12 16 8 Added section 1 4 Manager Flight Test Branch Added GAD 43 to diagram ANM 160L Added GAD 43 to diagram FAA Los Angeles ACO Added section 1 10 Transport Airplane Directorate Changed GDU s w to 3 01 AHRS s w to 2 12 GNS 400W 500W Date July hy 2009 software to 3 20 and added GAD 43 to section 2 2 7 11 12 13 Updated names of charting services in section 2 3 Expanded AHRS operational area in section 2 4 Added section 2 5 16 Added section 2 6 17 Added section 2 10 Added section 2 13 Updated section 2 14 to account for SVT Added section 2 17 Updated section 2 18 to account for VFR only installations Updated section 3 3 1 to account for Added check attitude and AHRS Updated section 3 6 to account for G600 internal TAWS 21 22 25 26 Updated section 4 1 for new PFD knob mode annunciation Added note pertinent to dual G600 installations in section 4 1 Added section 4 4 Added check boxes for FD with SVT and GAD 43 to section 4 5 Updated section 4 5 7 to explain FD behavior with SVT enabled 27 28 30 Added section 4 5 8 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 3 of 51 LOG OF REVISIONS FAA Appro
20. ATING 21 2 9 AIRSPEED LIMITATIONS AND INDICATOR MARKINGS 21 2 10 6 21 2 11 COURSE POINTER AUTO 6 7 21 2 12 SYNTHETIC VISION 22 2 13 AUTOPILOT INTERFACE cccccccecssssssececececsessaececccecsensaececececsesenseaeees 22 2 14 TERRAIN PROXIMITY FUNCTION 2 22 2 15 FUNCTION GDU 620 UNITS WITH INTERNAL TAWS 23 2 16 DATALINKED WEATHER DISPLAY XM GFDS FIS B WEATHER 23 2217 23 2 18 ACTIVE WEATHER 24 2 19 5 5 DISPLAY 0200 2 000 60 100000000 24 2 20 KINDS OF OPERATIONS 25 2 21 275 325 ALTITUDE 5 25 2522 RATINGS sos ck 25 223 ELECTRONIC STANDBY INSTRUMENT POWER csessccecececeesenteeeees 26 2 24 ELECTRONIC FLIGHT BAG EFB 8 2 26 2 25 SURFACE OPERATIONS 26 2 26 E 26 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 9 of 51 SECTION 3 EMERGENCY 5 4 4 27 3 1 EMERGENCY PROCEDURES 4
21. FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for the GARMIN 6500 6600 PRIMARY FLIGHT AND MULTIFUNCTION DISPLAY SYSTEM as installed in Make and Model Airplane Registration Number Serial Number This document serves as an Airplane Flight Manual Supplement or as a Supplemental Airplane Flight Manual when the aircraft is equipped in accordance with Supplemental Type Certificate SA02153LA D for the installation and operation of the Garmin G500 G600 System This document must be carried in the airplane at all times The information contained herein supplements or supersedes the information made available to the operator by the aircraft manufacturer in the form of clearly stated placards or markings or in the form of an FAA approved Airplane Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic placards or markings or the basic FAA approved Airplane Flight Manual FAA APPROVED BY 7 00 Michael Warren ODA STC Unit Administrator GARMIN International Inc ODA 240087 CE DATE J PR 20 9 AFMS GARMIN 6500 6600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page of 51 LOG OF REVISIONS FAA Approval Complete Supplement Seyed Joussef Hashemi Manager Flight Test Branch ANM 160L FAA Los Angeles ACO Transport Airplane Directorate Date July 15 2008 AFMS G
22. STEM FAA APPROVED 190 00601 01 Rev K Page 34 of 51 3 3 2 Caution annunciations Yellow Annunciation Pilot Action Cause CHECK Fly the aircraft The GDU 620 attitude monitors have ATTITUDE manually and detected an AHRS malfunction or the crosscheck GDU 620 inability to actively monitor the AHRS Autopilot will attitude indication output automatically with standby attitude disconnect indicator and other sources of attitude Note 2 2 5 information re heading optional GAD 43 altitude etc adapter MISCOMP Cross check the Difference detected between displayed flag displayed flagged information attitude airspeed or altitude dual on PFD against other sources installations only attitude to identify erroneous airspeed or information altitude indicators AHRS ALIGN Limit aircraft attitude Attitude and Heading Reference Keep Wings to 10 bank and 5 System is aligning AHRS may not Level pitch as AHRS align with excessive pitch bank angles Aligns OK to taxi NO GPS If the system is GPS data on the selected system is no POSITION configured with dual longer valid The Moving Map and GPS press the 1 2 associated data are not updating button TRAFFIC Visually acquire the The interfaced traffic system has traffic to see and determined that nearby traffic may be avoid a threat to the aircraft No Traffic Use vigilance as t
23. ational area Operations are prohibited north of 72 N and south of 70 S latitudes In addition IFR operations are prohibited in the following four regions 1 North of 65 North latitude between longitude 75 W and 120 W 2 North of 70 North latitude between longitude 70 W and 128 W 3 North of 70 North latitude between longitude 85 E and 114 E 4 South of 55 South latitude between longitude 120 E and 165 E Loss of G500 G600 heading and attitude may occur near the poles but this will not affect the GPS track or standby attitude indicator 2 6 Magnetic Variation Operational Area IFR operations are prohibited in areas where the magnetic variation is greater than 99 9 degrees East or West 27 Navigation Angle The GDU 620 Navigation Angle which defines whether the GDU 620 headings are referenced to True or Magnetic North can be set to either True or Magnetic on the AUX page The Navigation Angle set in the GDU 620 shall be set by the pilot to match that which is set on all GPS SBAS navigators interfaced to the unit AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 20 of 51 28 AHRS Normal Operating Mode The Attitude and Heading Reference System integrity monitoring function requires GPS and Air Data to be provided to the AHRS Note Attitude will remain valid if one of these systems becomes inoperative Flight in IMC is not authorized unless the AHRS is receiving valid GPS and
24. bility the Test controls are provided on the AUX System Setup age Refer to the Radar Altimeter user documentation for information about values displayed during Test Note for KRA 405 Radar Altimeters the displayed Test value will be between 25 and 50ft AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 45 of 51 Section 5 PERFORMANCE No change Section 6 WEIGHT AND BALANCE See current weight and balance data AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 46 of 51 Section 7 SYSTEM DESCRIPTIONS Garmin also provides a detailed G500 G600 Pilot s Guide P N 190 00601 02 This reference material is not required to be on board the aircraft but does contain a more in depth description of all the functions and capabilities of the G500 G600 71 Databases The G500 G600 utilizes several databases Database titles display in yellow if expired or in question Note the G500 G600 receives the calendar date from the GPS but only after acquiring a position fix Database cycle information is displayed at power up on the MFD screen but more detailed information is available on the AUX pages Internal database validation prevents incorrect data from being displayed The upper Secure Digital SD data card slot should be vacant as it is used for software maintenance and aviation database updates only The lower data card slot should contain a data card with the system s terrain obstacle infor
25. ction 3 2 1 1 Use Standby Attitude Indicator 2 Seek VFR conditions or land as soon as practical AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 27 of 51 3 1 3 Data Computer ADC Failure Air Data Computer failure is indicated by a red X and yellow text over the airspeed altimeter vertical speed TAS and OAT displays Some derived functions such as true airspeed and wind calculations will also be lost If valid GPS data is available the PFD will automatically revert to display GPS calculated altitude relative to mean sea level This GPS altitude is displayed above the altitude tape 1 Use Standby Airspeed Indicator and Altimeter 2 Seek VFR conditions or land as soon as practical If ADC 1 has failed and PFD 1 AIR DATA switch is installed 3 PFD 1 AIR DATA switch Select ADC 2 NOTE ALT NO COMP and IAS NO COMP alerts will be present 3 1 4 Loss of Electrical Power In the event of a total loss of electrical power the G500 G600 system will cease to operate and the pilot must utilize the standby instruments to fly the aircraft 3 1 5 Loss of Electrical Power to 3 inch Electric Standby Attitude Indicator flashing amber STBY PWR light MidContinent 4300 Series When a 3 inch electric standby attitude indicator is installed loss of primary electrical power to the attitude indicator is annunciated by a flashing amber light on the indicator The attitude indicator is operating on backup battery po
26. d Altitude Bug Coupling When installed appropriately certain autopilots may be coupled to the PFD selected altitude bug for altitude preselect and capture Except as described in this section refer to the autopilot AFMS and or Pilot s Guide for autopilot system operation 4 6 6 1 S Tec Autopilots To preselect and capture a selected altitude 1 Select the desired altitude with the PFD selected altitude bug 2 Press hold VS then press ALT on the autopilot programmer computer to arm altitude hold mode AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 41 of 51 4 6 6 2 Collins Autopilots To preselect and capture a selected altitude 1 Select the desired altitude with the PFD selected altitude bug 2 Select ALT SEL mode on the autopilot flight control panel CAUTION Changing the selected altitude bug while ALT SEL mode is selected may result in autopilot mode changes Verify the autopilot mode after changing the selected altitude 4 6 6 3 Bendix King Autopilots To preselect and capture a selected altitude 1 Select the desired altitude with the PFD selected altitude bug 2 Press and hold the ALT button on the PFD to arm or disarm the selected altitude NOTE When the selected altitude is armed for capture ALT is displayed in white text in the upper right corner of the PFD When altitude capture mode is active ALTC is displayed in green text in the upper right corner of the PFD When a KA 315 an
27. dered inoperative if the red annunciator is displayed during the test 4 5 Synthetic Vision Technology The SVT system may be turned on or off as desired To access the synthetic vision system softkey menu press the PFD softkey on the GDU 620 followed by the SYN VIS softkey Synthetic vision terrain horizon headings and airport signs can be toggled on and off from this menu Press the BACK softkey to return to the root PFD menu AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 38 of 51 4 6 Autopilot Operations with G500 G600 System The G500 G600 System offers various integration capabilities dependent mainly upon the type of autopilot installed in a particular aircraft The G500 G600 installation in this aircraft provides the following autopilot integration capabilities appropriate boxes will be checked O This installation does not interface with the autopilot basic wing leveling autopilot or no autopilot is installed in the aircraft Course NAV Selection coupling to the autopilot Heading Bug coupling capability to the autopilot Roll Steering emulated via heading mode Roll Steering capable autopilot Altitude Pre Selector integrated with the autopilot Vertical speed bug integrated with the autopilot Flight Director display driven from external autopilot FD computer Flight Director is not available with Synthetic Vision enabled A GAD 43 Adapter is installed in this
28. eading bug The bug is still controllable and may still be used by the pilot for reference AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 40 of 51 When GPSS is selected on the PFD GPSS is annunciated in the lower left portion of the PFD The GPSS mode annunciation depends on the location of the NAV STATUS information as shown below GPSS GPSS gt 5 NAV STATUS STYLE 1 NAV STATUS STYLE 2 NOTE GPSS mode is selectable from PFD 2 but GPSS is not annunciated on PFD 2 The GPSS commands to the autopilot are based on the GPS source displayed on PFD 1 When GPSS is selected on the PFD GPSS turn commands are converted into a heading error signal to the autopilot When the autopilot is operated in HDG mode the autopilot will fly the turn commands from the GPS navigator selected on PFD 1 If the GPSS data is invalid for example if there is no active GPS leg or the selected HSI source on PFD 1 is not GPS the annunciated GPSS text will be yellow and a zero turn command will be sent to the autopilot 4 6 5 Roll Steering capable autopilots If the autopilot is already designed to receive Roll Steering information the data is transmitted via a digital communications bus from the G500 G600 to the autopilot The G500 G600 receives this data from the GPS In dual GPS installations the G500 G600 sends Roll Steering information for the GPS which is currently selected for use via the PFD 1 2 button 4 6 6 Selecte
29. ed ESI 1000 limitation in section Section 2 25 Added MFD Video limitation in Section Section 3 1 Section 3 2 Added MISCOMP and NO AP DATA Section 4 1 procedure as new section 4 4 section 4 6 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 7 of 51 LOG OF REVISIONS Page FAA Approval Re issue complete supplement Re steal ie GARMIN International Inc Section 2 11 Updated Bendix King Altitude Preselect Date December 12 2013 functionality in Section 4 6 6 3 Moved sections 2 4 DB Card and 2 11 Elec Stby to section 7 Added TAWS Annun from Garmin Navigator to section 2 17 to include all electronic indicators in Section 2 24 ODA STG nt in Section 1 1 ODA STC Unit Administrator sections Procedures to section 1 1 separate sections 1 7 and 1 8 sections 2 19 and 7 6 Revised Standby Battery preflight check See Page 1 section 3 2 7 Added TER TAWS NO DATA and Revised sections 1 5 2 10 2 14 2 18 and 3 17 for EASA Added Cessna autopilots to section 4 6 6 4 Added detail to GAD 43 AC Ref to section 4 6 9 Included select systems descriptions in section 7 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 8 of 51 TABLE OF CONTENTS SECTION 1 GENERAL sisisssscsisnssescecssscevssssessscoottecsbansscssscasdsesscesensssesdesentcnses 11 1 1 G500 G600 PRIMARY FLIGHT MULTI FUNCTION DISPLAY SYSTEM 11 1 2 SYSTEM POWER SOURCES
30. er NO GPS POSITION text on the MFD moving map Loss of waypoint bearing or distance information Select alternate GPS source if available by pressing 1 2 softkey on PFD If alternate GPS source is not available 2 Select alternate navigation source using CDI 1 2 or BRG softkeys on PFD or refer directly to external navigation data 3 2 3 Navigation Data Failure VOR LOC GS ADF Navigation data failure may be indicated by any or all of following Loss of course deviation information on HSI Loss of glideslope glidepath information on PFD Loss of bearing pointer on HSI Select alternate navigation source using CDI 1 2 or BRG softkeys on PFD or refer directly to external navigation data 3 2 4 Synthetic Vision SVT Failure Several data sources are required to display SVT on the PFD GPS terrain database attitude information etc If any of these required data sources become unreliable or unavailable SVT will automatically be removed and the PFD will revert to the standard display of blue sky over brown ground If there is a discrepancy between the SVT display and the actual terrain around the aircraft SVT should be turned off manually To turn off SVT 1 Press the PFD softkey on the PFD 2 Press the SYN VIS softkey to turn off SVT AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 32 of 51 3 2 5 Electrical Load Shedding The following equi
31. f autopilot interfaces in section 4 6 1 Corrected altitude alerter description in section 4 6 6 Added Caution and Note regarding GAD 43 AP TEST function in section 4 6 8 g N 25 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 5 of 51 LOG OF REVISIONS FAA Approval All Changed references to GNS navigators Robert Grove to GPS SBAS navigators ODA STC Unit Administrator 10 Inserted new section 1 10 for HSDB GARMIN International Inc ODA 240087 CE interface description Inserted new section 2 3 for moving map Date April 01 2011 limitations GPS SBAS vertical coupling section 4 6 Added GDU 620 as an autopilot attitude source to section 4 6 1 Clarified dual autopilot interface in section 4 6 9 20 21 Moved rate of turn failure description from section 3 3 1 to section 3 3 2 25 Added checkbox for disabled altitude alerter in section 4 4 ODA STC Unit Administrator AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 6 of 51 LOG OF REVISIONS FAA Approval All Re issue complete supplement Michael Warren ODA STC Unit Administrator Revised information on system power GARMIN International Inc section 1 6 Updated block diagrams in sections 1 12 and 1 13 in section 2 2 Section 2 3 descriptions in section 2 4 in section 2 13 Added limitation for KFC 275 325 Added Type Ratings limitation in section 2 22 Add
32. for RADAR stabilization The GAD 43 has the ability to disconnect the autopilot if an error in the GAD 43 output or GRS 77 is detected This disconnect mechanism must be tested prior to each flight in the following manner 1 Upon startup an AP TEST soft key will be available on the PFD side of the display 2 Engage the AP while on the ground 3 Press the AP TEST soft key and verify that the autopilot disconnects CAUTION Do not use the autopilot if the AP TEST key fails to disengage the autopilot normally NOTE Pressing and holding the AP TEST key for longer than 1 second will prevent the test from running and the AP TEST key will remain displayed Do not engage the autopilot if advisory AC Reference Lost or Reference Timeout Fault is present 4 6 10 Dual G500 G600 Autopilot Interface If the installation has dual G500 G600 systems installed control of navigation course heading or altitude data affecting the autopilot from the co pilot side can only be made if the systems are synchronized with each other Refer to the Garmin G500 G600 Cockpit Reference Guide for additional information 47 TAWS At system startup verify that the TAWS SYSTEM TEST audio message is loud and compelling Adjust headset volumes as necessary 48 Radar Altimeter If the installation of the G500 G600 is interfaced to radar altimeter the radar altitude can be displayed on the PFD If the installed radar altimeter includes self test capa
33. g the aircraft A typical SVT display is shown below SVT provides additional features on the G500 G600 primary flight display PFD which display the following information e Synthetic Terrain an artificial database derived three dimensional view of the terrain ahead of the aircraft within a field of view of approximately 25 degrees left and 25 degrees right of the aircraft heading e Obstacles obstacles such as towers including buildings over 200 AGL that are within the depicted synthetic terrain field of view Powerlines are not depicted in synthetic vision AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 13 of 51 e Flight Path Marker FPM an indication of the current lateral and vertical path of the aircraft The FPM is always displayed when synthetic terrain is selected for display Traffic a display on the PFD indicating the position of other aircraft detected by a traffic system interfaced to the G500 G600 system e Horizon Line a white line indicating the true horizon is always displayed on the SVT display e Horizon Heading a pilot selectable display of heading marks displayed just above the horizon line on the PFD e Airport Signs pilot selectable signposts displayed on the synthetic terrain display indicating the position of nearby airports that are in the G500 G600 database e Runway Highlight a highlighted presentation of the location and orientation of the runway s at t
34. he The configured traffic system is not Data traffic sensor is not able to detect traffic and or provide able to detect traffic the pilot with any traffic awareness NO AP DATA Verify autopilot Autopilot mode of operation is not mode of operation available using alternate means TER N A Use vigilance terrain Database errors or lack of required TER FAIL depiction is no GPS position longer provided AFMS GARMIN G500 G600 SYSTEM FAA APPROVED 190 00601 01 Rev K Page 35 of 51 TAWS N A Use vigilance terrain Database errors or lack of required TAWS FAIL depiction and TAWS alerting is no longer provided NO DATA Displayed on Loss of connection or failure of dedicated display interfaced sensor pages Indicates that data from the interfaced sensor is not available 3 3 3 Advisories White Annunciation Pilot Action Various Alert Messages may appear under the MED View and understand all advisory messages Typically they indicate communication issues within the G500 G600 System Refer to the G500 G600 Cockpit Reference for appropriate pilot or service action ALERTS soft key A C Reference The A C reference signal used for attitude provided to the Lost or autopilot has been lost Disconnect the autopilot and do not Reference re engage Timeout Fault AFMS GARMIN G500 G600 SYSTEM FAA APPROVED 190 00601 01 Rev K Page 36 of 51
35. he destination airport The synthetic terrain depiction displays an area approximating the view from the pilot s eye position when looking directly ahead out the windshield in front of the pilot Terrain features outside this field of view are not shown on the display The synthetic terrain display is intended to aid the pilot awareness of the terrain and obstacles in front of the airplane It may not provide either the accuracy or fidelity or both on which to solely base decisions and plan maneuvers to avoid terrain or obstacles The synthetic vision elements are not intended to be used for primary aircraft control in place of the primary flight instruments 15 Autopilot Interface The G500 G600 may optionally be interfaced to an autopilot The G500 G600 typically provides course and heading datum to the autopilot based on the data selected for display on the HSI For aircraft equipped with multiple GPS NAV systems the G500 G600 acts as a selection hub for the autopilot s NAV mode and the G500 G600 may also provide GPS Steering GPSS data Some autopilots may have Flight Director capabilities which can be displayed on the G500 G600 Attitude Indicator as a Single Cue Flight Director Optionally the autopilot can capture the pre selected altitude or couple to the selected vertical speed if these capabilities are supported by the autopilot equipment installed Refer to the autopilot operator s manual or autopilot Airplane Flight Manual Su
36. he display for hazardous weather thunderstorm penetration is prohibited StormScope lightning data on the display is intended only as an aid to enhance situational awareness of hazardous weather not penetration It is the flight crew s responsibility to avoid hazardous weather using official weather data sources AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 24 of 51 2 20 Kinds of Operations Unless placarded as limited to VFR only operations G500 G600 equipment installed in a certified aircraft is approved for Day and Night VFR and IFR operations in accordance with 14 Code of Federal Regulations Part 91 Part 121 and Part 135 when appropriately maintained The table below lists the minimum fully functional G500 G600 System Equipment required for IFR flight operations Equipment Number VFR IFR installed Primary Multi Flight Display 1 or 2 1 1 Garmin GPS SBAS Navigator 1 or2 1 Attitude Heading Unit AHRS 10 2 1 Air data computer ADC 1 or2 1 Magnetometer 1 2 1 Standby Attitude Indicator 1 1 Standby Airspeed Indicator 1 1b 1 Standby Altimeter 1 1b 1 Magnetic Compass 1 1 1 For VFR operations under 14 CFR Part 91 the aircraft shall have one source of altitude and airspeed information This may be from either the PFD or the standby instruments i e all 1 items or all 1b items from the table above
37. hich drives all other PFD and MFD data used by the G500 G600 7 6 StormScope When optionally interfaced to a StormScope weather detection system the G500 G600 may be used to display the StormScope information Weather information supplied by the StormScope will be displayed on the StormScope page of the G500 G600 system and may be overlaid on the map page For detailed information about the capabilities and limitations of the StormScope system refer to the documentation provided with that system AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K Page 49 of 51 77 ADS B Traffic System Interface The G500 G600 system can be interfaced to sources of ADS B traffic The nose of the ownship symbol both the G500 G600 main map page and dedicated traffic page serves as the actual location of your aircraft The center of the traffic target icon serves as the reported location for the target aircraft Motion vectors for traffic may be displayed in either absolute or relative motion The location of the traffic targets relative to the ownship are the same regardless of the selected motion vector Absolute motion vectors are colored white and depict the reported track of the traffic target referenced to the ground An absolute motion vector pointed towards your ownship symbol does not necessarily mean the traffic target is getting closer to your aircraft Relative motion vectors are colored green and depict the motion of the traffic
38. ht Restriction or Notice to Airmen information Not all TFRs NOTAMS may be depicted on the G500 G600 217 Traffic Display Traffic may be displayed on the G500 G600 System when connected to an approved optional TCAS TAS TIS or ADS B traffic device These systems are capable of providing traffic monitoring and alerting to the pilot Traffic shown on the display may or may not result in traffic alerts The display of traffic is an aid to visual acquisition and shall not be utilized for aircraft maneuvering AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 23 of 51 2 18 Active Weather RADAR RADAR is broadcasting energy while in Weather or Ground mapping modes If the G500 G600 system is configured to control an airborne weather radar unit observe all safety precautions including Do not operate in the vicinity of refueling operations e Do not operate while personnel in the vicinity approximately 20 feet of the radar sweep area WARNING If a radar system is installed it generates microwave radiation and improper use or exposure may cause serious bodily injury DO NOT OPERATE THE RADAR EQUIPMENT UNTIL YOU HAVE READ AND CAREFULLY FOLLOWED THE SAFETY PRECAUTIONS AND INSTRUCTIONS in the USER MANUAL 2 19 StormScope Display StormScope lightning information displayed by the G500 G600 is limited to supplemental use only The use of the StormScope lightning data on t
39. ing in addition to the vertical escape maneuver is the safest course of action or both AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 30 of 51 3 2 Abnormal Procedures 3 21 Heading Failure Heading failure is indicated by replacement of the digital heading display with amber HDG text and a red X If valid GPS ground track is available it will automatically be displayed in place of heading The HSI heading bug and course pointer will continue to function normally using GPS ground track as a reference instead of magnetic heading If GPS track is not available pm Use standby compass for heading reference 2 Verify selected course using CRS button and PFD knob CAUTION No directional references will be displayed on HSI The heading bug will be removed and the course pointer will remain fixed at the top of the HSI regardless of aircraft heading Course deviation indications will behave similar to a traditional CDI VOR deviations will be relative the selected course with a TO FROM indication Localizer deviations will not be affected by the selected course and reverse sensing will occur when tracking inbound on a localizer back course AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 31 of 51 3 2 2 GPS Data Failure GPS data failure may be indicated by any or all of following Loss of GPS course deviation information on HSI Amber LOI text on the HSI Amb
40. lable by pressing the MENU button which is on the right side of the display Pressing and holding down the CLR key is a shortcut to get back to the main map page on the MED This can be used as a quick way back or when the pilot has selected a submenu within the system The functions available under the MED are explained in the Garmin G500 G600 Cockpit Reference Guide 43 Altitude Synchronization The pilot must synchronize the PFD BARO setting and the Standby Altimeter Kollsman window with the local altimeter setting as appropriate In dual installations if synchronization between the units is enabled setting either PFD will adjust both PFDs but the standby must still be set by the pilot Reference the Garmin G500 G600 Cockpit Reference Guide for a complete description and the usage of synchronization in dual installations 44 Electric Standby Attitude Gyro Mid Continent 4200 and 4300 Series When an electric standby attitude gyro is installed test the backup battery before takeoff 1 Apply power to electric standby attitude gyro and allow the gyro to reach operating speed approximately 5 minutes 2 Verify that the red gyro flag is not in view 3 Press and hold the STBY PWR button until the amber annunciator begins to flash 4 Verify that the green annunciator is displayed continuously and the red annunciator is not displayed for the duration of the test approximately 1 minute CAUTION The standby attitude gyro must be consi
41. mation and optional data including Safe Taxi FliteCharts and ChartView electronic charts The terrain databases are updated periodically and have no expiration date Coverage of the terrain database is between North 75 latitude and South 60 latitude in all longitudes The obstacle database contains data for obstacles and wires that pose a potential hazard to aircraft Obstacles 200 feet and higher are included in the obstacle database Wires which have been identified as a hazard to fixed wing aircraft are included in the database It is very important to note that not all obstacles or wires are necessarily charted and therefore may not be contained in the obstacle database Coverage of the obstacle database includes the United States and Europe Wire coverage is limited to the United States This database is updated on a 56 day cycle The Garmin SafeTaxi database contains airport diagrams for selected airports This database is updated on a 56 day cycle The Garmin FliteCharts or Jeppesen ChartView electronic charts database contains procedure charts for the coverage area purchased An own ship position icon will be displayed on these charts when the aircraft icon on the chart page is not X d This database is updated on a 28 day cycle If not updated within 180 days of the expiration date FliteCharts or ChartView will no longer function AFMS GARMIN G600 SYSTEM 190 00601 01 Rev K Page 47 of 51 The airport directory database c
42. nformation Manual AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K Page 50 of 51 7 10 Depiction of Obstacles and Wires 7 10 1 Dedicated Terrain Page The dedicated Terrain page will always depict point obstacles at zoom scales of 10 nm or less and depict wire obstacles at zoom scales of 5 nm or less The obstacle or wire overlay icon shown below will be shown near the bottom of the display when the obstacle or wire depiction is active based on the zoom scale NOTE The Obstacle or Wire Overlay Icon is displayed when wires or obstacles will be available on the Terrain Page based on the zoom scale Only obstacles and wires within 2 000 ft vertically of the aircraft will be drawn on the Terrain Page Obstacle Overlay Icon Left Wire Overlay Icon Right 7 10 2 Map Page The Map page may be configured to depict point obstacles and wire obstacles at various zoom scales by the pilot by using the Map page menu The obstacle or wire overlay icon shown below will be shown near the bottom of the display when the obstacle or wire overlay is active based on the current zoom scale and setting selected by the pilot The settings chosen by the pilot on the Map page menu including obstacle and wire display ranges are saved over a power cycle NOTE The Obstacle or Wire Overlay Icon is displayed when wires or obstacles will be available on the Map Page based on map setup and the zoom scale Only obstacles and wires within 2 000 ft ver
43. nunciator panel is installed the ALT ARM annunciator on this panel will not be operative NOTE KFC 200 250 autopilots will inhibit glideslope GS mode if altitude capture ALTC mode is engaged during glideslope intercept CAUTION Changing the selected altitude bug while ALTC mode is active will result in cancellation of ALTC mode Verify the autopilot mode after changing the selected altitude 4 6 6 4 Cessna Autopilots To preselect and capture a selected altitude 1 Select the desired altitude with the PFD selected altitude bug 2 Press and hold the ALT button on the PFD to arm or disarm the selected altitude NOTE When the selected altitude is armed for capture ARMED is displayed in white text next to the selected altitude AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 42 of 51 4 6 7 Vertical Speed Bug Coupling Certain autopilots may be coupled to the PFD vertical speed bug for maintaining a selected vertical speed Except as described in this section refer to the autopilot AFMS and or Pilot s Guide for autopilot system operation 4 6 7 1 S Tec Autopilots To select and maintain a vertical speed 1 Select the desired vertical speed with the PFD vertical speed bug 2 Press VS on the autopilot programmer computer to engage vertical speed mode NOTE The selected vertical speed will automatically be reduced towards zero when approaching the selected altitude bug AUTO will appear in
44. ontains information on landing facilities such as operating hours services available and transportation lodging resources Airport directory information may be available from multiple sources and coverage areas This database is updated on a 56 day cycle 7 2 Electric Standby Attitude Gyro If an electric standby attitude gyro is installed the gyro operates from the aircraft electrical system with a dedicated emergency battery specific to the electric gyro The electric attitude gyro battery capacity may vary considerably depending on temperature charge status and battery life condition Low temperatures below 32 F will temporarily degrade battery capacity Internal chemistry will slowly degrade battery capacity over several years of operation even when correctly maintained A poorly maintained battery will suffer accelerated degradation Extended storage in a discharged state and over charging will permanently damage the battery Complete charging is required to bring the battery up to full capacity if it has been unused for more than four months or partially discharged 7 3 Autopilot Interface The G500 G600 acts as a navigation source switching hub to an interfaced autopilot when multiple navigation sources are available The autopilot will only couple to the heading navigation altitude and vertical speed selections on PFD 1 Some autopilots may have navigation source selection integral to their system this feature is overridden by the G
45. overall conduct of the flight The standby instruments altimeter airspeed attitude and magnetic compass are completely independent from the PFD and will continue to operate in the event the PFD is not usable These standby instruments should be included in the pilot s normal instrument scan and may be referenced if the PFD data is in question A second G500 G600 system installed on the co pilot s side does not require additional standby instruments AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 11 of 51 1 2 System Power Sources The G500 G600 system depends on electrical power to function The Garmin Display Unit GDU Attitude and Heading Reference System AHRS and Air Data Computer ADC are directly tied to the aircraft s main or essential bus and energized when the aircraft master switch is turned on Other systems like the navigation equipment weather datalink autopilot and Adapter GAD are typically located on the avionics bus and may not be functional when this bus is powered off The major components of the G500 G600 are circuit breaker protected with resettable type breakers available to the pilot These breakers are located at the main or essential bus circuit breaker panel and labeled as follows Circuit Breaker Equipment Label PFD Garmin Display Unit PFD MFD GDU 620 AHRS Attitude and Heading Reference System GRS 77 ADC Air Data Computer GDC 74A B GAD
46. pment is considered non essential If it becomes necessary to reduce electrical load for example during loss of generators or alternators power to these units may be removed in the order listed 1 2 circuit breaker s if installed PULL 2 AHRS 2 circuit breaker s if installed PULL 3 ADC 2 circuit breaker s if installed PULL 4 GAD circuit breaker s if installed PULL 3 2 6 TAWS Caution TAWS Cautions include an amber TERRAIN or OBSTACLE or annunciator on the PFD and one of the following aural messages Terrain Ahead or Caution Terrain Obstacle Ahead or Caution Obstacle Wire Ahead or Caution Wire Too Low Terrain Sink Rate Don t Sink Ifa TAWS Caution occurs take corrective action until the alert ceases Stop descending or initiate either a climb or a turn or both as necessary based on analysis of all available instruments and information 3 2 7 GAD 43 AC Reference Lost of Reference Timeout Fault If AC Reference Lost or Reference Timeout Fault message is present the reference signal used by the autopilot is unavailable and the autopilot may deviate from the intended path or may disconnect 1 Immediately disengage the autopilot and do not re engage AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 33 of 51 33 Warnings Cautions and Advisories The following tables show the color and significance of the
47. pplement for the proper operation of the autopilot system Not all autopilot systems are approved for coupling to vertical guidance on GPS based approaches therefore consult the AFMS for the GPS SBAS system and or autopilot system AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 14 of 51 16 Audio Panel The G500 G600 system may be interfaced to the aircraft audio panel to provide aural alerting generated by the G500 G600 required for TAWS B installations 17 Traffic Display The G500 G600 system can display traffic data from interfaced traffic systems Sources of traffic data include TIS A traffic via the Garmin GTX Series Mode S Transponders TAS TCAS traffic from various active traffic awareness systems and ADS B traffic from Garmin ADS B transceivers The information from these systems is displayed on and controlled using the MFD 1 8 Weather Data The G500 G600 system can display weather data from interfaced datalink systems Sources of weather data include the Garmin GDL69 and GDL69A Sirius XM receivers Garmin GSR 56 Iridium Transceiver and Garmin GDL 88 ADS B transceiver If one of these optional weather datalink receiver is installed the pilot will be able to access graphical and text weather products using the MFD The G500 G600 system can control various airborne weather radars and display their data Compatible weather radars include Garmin GWX weather radars as well as certain 3 weather
48. r on the G500 G600 The G500 G600 system limits the distance the flight director pitch commands may deviate from the aircraft attitude icon In the event that the pitch command provided by the autopilot flight director is greater than the distance allowed by the G500 G600 the command bars will be displayed at the maximum distance allowed by the G500 G600 As the aircraft pitch changes to satisfy the command bars the bars will continue to be displayed at the maximum distance from the aircraft attitude icon until the aircraft pitch deviation is within the command display limit In both examples below the flight director is commanding approximately 7 degrees pitch up With SVT turned off the 7 degree pitch up command is displayed with the command bar at 7 degrees pitch up With SVT turned on the G500 G600 limits the command bar shown as 4 5 degrees pitch up which is the maximum deviation that can be displayed The G500 G600 system will hold the command bars at the same distance from the aircraft icon until the aircraft pitch attitude is within 4 5 degrees of the command SVT Off AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 44 of 51 4 6 9 43 The GAD 43 Adapter may provide attitude heading and barometric correction information from the G500 G600 System to the autopilot The GAD 43 can also be configured to provide synchro heading output to other systems and its attitude output can be used
49. rupted attitude information is required on the PFD 211 Course Pointer Auto Slewing The G500 G600 HSI will auto slew i e automatically rotate the GPS course pointer to the desired course defined by each GPS leg The system will also auto slew the VHF NAV course pointer when the CDI transitions to a LOC setting if an ILS LOC LOC BC LDA or SDF approach is loaded in the GPS SBAS navigator The VHF NAV green course pointer will only auto slew if the approach is loaded in the navigator a LOC frequency is loaded in the active NAV frequency and then the HSI source is changed to the corresponding VHF NAV for the approach Back Course approaches will auto slew to the reciprocal course AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 21 of 51 The system is not capable of automatically setting the inbound VHF NAV course pointer if an approach is not loaded in the GPS SBAS Navigation System Auto slewing the VHF NAV course pointer to the correct selected course is a database dependent function The pilot shall confirm the inbound course pointer is set to the proper course prior to initiating any transition on any VHF NAV approach 2 12 Synthetic Vision Technology The use of the synthetic vision display elements alone for aircraft control without reference to the G500 G600 primary flight instruments or the aircraft standby instruments is prohibited The use of the synthetic vision display alone for navigation or obs
50. s SafeTaxi or Chartview functions shall not be used as the basis for ground maneuvering SafeTaxi and Chartview functions do not comply with the requirements of AC 20 159 and are not qualified to be used as an airport moving map display AMMD SafeTaxi and Chartview use is limited to airport surface orientation to improve flight crew situational awareness during ground operations 2 26 Video Display Video images displayed on the MFD are intended for use as an aid to situational awareness only Aircraft maneuvering based solely on the MED video display is prohibited AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 26 of 51 Section 3 EMERGENCY PROCEDURES 31 Emergency Procedures 311 PFD 1 Failure PFD 1 failure is indicated by the loss of displayed information on the PFD including blank frozen or unresponsive display 1 Use standby flight instruments for attitude airspeed altitude and heading reference 2 Refer directly to navigation source for navigation information such as GPS If autopilot is engaged 3 Verify autopilot mode and cross check against standby flight and navigation data 312 AHRS Failure Attitude and Heading Reference System AHRS failure is indicated by removal of the sky ground presentation a red X and a yellow ATTITUDE FAIL on the Rate of turn information heading trend vector will not be available A heading failure will also occur as described in Se
51. tacle terrain or traffic avoidance is prohibited 2 13 Autopilot Interface Flight director commands on PFD 2 are repeated from PFD 1 When utilizing the flight director display on PFD 2 the pilot shall ensure that the CDI source and BARO settings on PFD 2 match those on PFD 1 For installations where the GAD 43 provides attitude information to the autopilot the GAD 43 autopilot disconnect mechanism shall be tested and operational before each flight using the autopilot 214 Terrain Proximity Function The G500 G600 terrain configuration is indicated on the dedicated terrain page of the MAP group TERRAIN PROXIMITY will be displayed as the page title if this function is configured Terrain information appears on the map and terrain display pages as red and amber and is depicted for advisory use only Obstacle and wire information appears on the map and terrain display pages as red amber and white and is depicted for advisory use only Aircraft maneuvers and navigation must not be predicated upon the use of the terrain display Terrain obstacle and wire information is advisory only and is not equivalent to warnings provided by TAWS The terrain display is intended to serve as a situational awareness tool only By itself it may not provide either the accuracy or the fidelity on which to base decisions and plan maneuvers to avoid terrain or obstacles AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 22 of 51
52. tically of the aircraft will be drawn on the Map Page Obstacle Overlay Icon Left Wire Overlay Icon Right NOTE The Map page may be configured by the pilot to not show any obstacles or wires at any zoom scale AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K Page 51 of 51
53. unction Display PFD Primary Flight Display SBAS Space based Augmentation System SD Secure Digital SVT Synthetic Vision Technology TAS Traffic Awareness System TAWS Terrain Awareness and Warning System a TSO C151b function TCAS Traffic Collision and Avoidance System TIS Traffic Information Service VFR Visual Flight Rules Visual Meteorological Conditions V S Vertical Speed AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 19 of 51 Section 2 LIMITATIONS 21 Cockpit Reference amp Pilot s Guide The Garmin G500 G600 Cockpit Reference Guide P N 190 00601 03 Revision G or later appropriate revision must be immediately available to the flight crew 2 22 System Software Requirements The G500 G600 must utilize the following or later FAA approved software versions for this AFMS revision to be applicable Identification Software Version GDU 620 PFD MFD GRS 77 AHRS 23 Moving Map The moving map on the MFD is advisory in nature and is shall not be used for course guidance The moving map on the MFD must be cross checked for correctness against the PFD HSI published charts or other approved sources of navigation information 2 4 Database Cards Databases identified as intended for helicopter use shall not be used These databases are identified by the word HELI or HELICOPTER in their title 2 5 AHRS Operational Area The AHRS used the G500 G600 is limited in its oper
54. unction and its operation The soft keys at the bottom of the PFD display are used to configure the course data displayed in the HSI CDI button 1 2 button and select the optional bearing pointers BRG2 button which may be overlaid in the HSI presentation on the PFD The soft keys operate by press and release Note In Dual G500 G600 installations the CDI key located on the GNS units is not operational Consult the Garmin G500 G600 PFD MFD System Cockpit Reference Guide for a complete description The units and markings on the PFD are not user configurable They match the units as specified in the aircraft s FAA approved Airplane Flight Manual standby instruments Display and control of the airspeed references Vr Vx Vy and GLIDE are made via the AUX page of the MFD consult the Garmin G500 G600 Cockpit Reference Guide for description and operation of these references 42 Knobs amp Soft Keys The MFD controls are on the side and bottom of the MFD next to and beneath the MFD display The rotary knobs scroll through various page groups and pages of the MFD and manipulate data and settings by pressing the knob to activate a cursor AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 37 of 51 Soft keys at the bottom of the display allow for some quick functions to be performed on each page The soft keys operate by press and release More detailed configuration is typically avai
55. val Added section 2 8 Robert Grove ODA STC Unit Administrator GARMIN International Inc ODA 240087 CE Date September 15 2009 Remove requirement for standby ADI for Robert Grove VFR operations installations Add ODA STC Unit Administrator maximum airspeed limitation section GARMIN International Inc ODA 240087 CE Date November 17 2009 AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 4 of 51 LOG OF REVISIONS Page Changed GPS W AAS to GPS SBAS Robert Grove ODA STC Unit Administrator ODA 240087 CE Added new feature to sections 1 7 1 8 and 1 9 Date January 28 2011 10 11 Updated block diagrams for new features Updated section 2 2 for applicability to this AFMS revision Removed GPS navigator software table Updated section 2 3 with limitation on use of helicopter databases and SD card usage with GSR 56 datalink Added information on airport directory database Updated section 2 8 to reflect current airspeed tape behavior Updated sections 2 14 2 15 and 2 16 to better describe the various terrain awareness functions Updated section 2 17 for GFDS weather function Corrected description of AHRS failure Corrected description of heading failure Corrected description of ADC failure Corrected table entry for AHRS ALIGN Added new section 4 4 for altitude alerter configuration Added detail to section 4 6 regarding GAD 43 interface Corrected description o
56. warning caution and advisory messages which may appear on the G500 G600 displays NOTE The G500 G600 Cockpit Reference Guide and the G500 G600 Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories 3 3 1 Warning annunciations Red Annunciation Pilot Action Cause ATTITUDE Use Display system is not receiving attitude FAIL Standby reference information from the AHRS Attitude accompanied by the removal of sky ground presentation and a red X over the attitude area AIRSPEED Use Display system is not receiving airspeed input FAIL Standby from the air data computer accompanied by a Airspeed red X through the airspeed display ALTITUDE Use Display system is not receiving altitude input FAIL Standby from the air data computer accompanied by a Altitude red X through the altimeter display VERT SPD Cross check Display system is not receiving vertical speed FAIL instruments input from the air data computer accompanied by ared X through the vertical speed display HDG Use Display system is not receiving valid heading Standby input from the AHRS accompanied by a red X Magnetic through the digital heading display Compass or GPS track information Red X Reference A red X through any display field indicates that the data display field is not receiving data or is source or corrupted alternate equipment AFMS GARMIN G500 G600 SY
57. wer and pilot action is required for the gyro to continue operating Press STBY PWR button on the indicator one time Verify that the flashing amber light extinguishes Verify that the red gyro warning flag is not displayed Seek visual meteorological conditions VMC or land as soon as practical operation of standby attitude indicator is limited by battery life WARNING Do not press the STBY PWR button a second time after the flashing amber light extinguishes This will turn off the backup battery and the red gyro warning flag will be displayed If the STBY PWR button is inadvertently pressed and the red gyro warning flag is displayed press the STBY PWR button again to return to battery power operation red gyro warning flag should not be displayed AFMS GARMIN G500 G600 SYSTEM 190 00601 01 Rev K FAA APPROVED Page 28 of 51 3 1 6 Loss of Electrical Power to 2 inch Electric Standby Attitude Indicator flashing or steady amber STBY text MidContinent 4200 Series When a 2 inch electric standby attitude indicator is installed loss of primary electrical power to the attitude indicator is annunciated by amber STBY text on the Annunciation Control Unit The attitude indicator is operating on backup battery power and pilot action may be required for the gyro to continue operating If the amber STBY text is flashing manual operation 1 2 3 4 Press the STBY PWR button one time Verify that the amber

Garmin Part 23 AML STC Airplane Flight Manual Supplement

Contents

Download Pdf Manuals

Related Search

Related Contents