AIRPLANE FLIGHT MANUAL SUPPLEMENT or
Contents
1. In order to capture the vertical glidepath for LPV or LNAV VNAV instrument approaches the autopilot must be in an analog mode APR mode selected on the autopilot The autopilot will not track the vertical glidepath in GPS Roll Steering mode Not all autopilot systems are approved for GPS vertical coupling therefore consult the AFMS for the GPS WAAS system and the Autopilot installed 2 14 Terrain Display The G500 terrain and obstacle information appears on the MFD display as red and yellow tiles or towers and is depicted for advisory only Aircraft maneuvers and navigation must not be predicated upon the use of the terrain display Terrain unit alerts are advisory only and are not equivalent to warnings provided by TAWS 2 15 TAWS Annunciations on the PFD from a Garmin navigator The G500 can display TAWS Terrain Awareness and Warning System annunciations on the PFD if the G500 is interfaced to a Garmin navigator with integrated TAWS The required TAWS annunciations appear in the upper right of the PFD These annunciations include PULL UP red TERRAIN yellow TERR N A white TERR 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 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 System are only2. 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 190 01102 01 Rev 4 Page 17 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 2 19 Kinds of Operations Unless placarded as limited to VFR only operations G500 equipment installed in an appropriately 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 System Elements required for IFR flight operations Equipment Number VFR IFR installed Primary Multi Flight Display 1 or 2 la 1 GNS 400W 500W Series or GNS 480 1 or 2 1 Attitude Heading Unit AHRS 1 or2 1 Air data computer ADC lor2 la 1 Magnetometer GMU lor2 1 Standby Attitude Indicator 1 1 Standby Airspeed Indicator 1 lb 1 Standby Altimeter 1 lb 1 Magnetic Compass 1 1 1 For VFR operations under 14 CFR Part 91 the aircraft must have one source of altit
3. 25 4 5 Autopilot Operations with the G500 System 26 Section 5 PERFORMANCE 29 Section 6 WEIGHT AND BALANCE 29 Section 7 SYSTEM DESCRIPTIONS 29 190 01102 01 Rev 4 Page 4 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM Section 1 GENERAL 1 1 Garmin G500 Primary Flight Multi Function Display System The G500 PFD MFD 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 and Attitude and Heading Reference System AHRS The G500 interfaces with other installed systems in the aircraft including Garmin GNS series GPS WAAS navigators Garmin SL30 VHF navigators Garmin GDL 69 data link radios and various audio panels traffic systems and ADF navigators The primary function of the PFD is to provide attitude heading air data and navigation information from GNS units to the pilot The primary function of the MFD is to provide mapping terrain and flight plan information 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
4. and may be referenced if the PFD data is in question A second G500 system installed on the co pilot s side does not require additional standby instruments 1 2 System Power Sources The G500 system depends on electrical power to maintain proper operation The Garmin Display Unit GDU Attitude and Heading Reference System AHRS and Air Data Computer ADC should be 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 operable during engine start The major components of the G500 are circuit breaker protected with reset able type breaker available to the pilot These breakers are located at the main or essential bus circuit breaker panel and labeled as follows 1 PFD Garmin Display Unit PFD MFD GDU 620 2 AHRS Attitude and Heading Reference System GRS 77 3 ADC Air Data Computer GDC 74A 4 GAD Garmin Adapter GAD 43 optional Note In dual installations the pilot side equipment is suffixed with a 1 and the copilot side equipment is suffixed with a 2 Example PFD 2 190 01102 01 Rev 4 Page 5 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA
5. discharged 2 11 Course Pointer Auto Slewing The G500 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 activated in the GPS WAAS navigator The VHF NAV green course pointer will only auto slew if the approach is active in the navigator the 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 The system is not capable of automatically setting the inbound VHF NAV course pointer if an approach is not active in the GNS Navigation System The pilot should always double check the inbound course pointer prior to initiating any transition on any VHF NAV approach Auto slewing the VHF NAV course pointer to the correct selected course is a database dependent function 2 12 Synthetic Vision Technology The use of the synthetic vision display elements alone for aircraft control without reference to the G500 primary flight instruments or the aircraft standby instruments is prohibited The use of the synthetic vision display alone for navigation or obstacle terrain or traffic avoidance is prohibited 2 13 Autopilot Interface The G500 is not capable of controlling autopilot mode selection or
6. equipped only with a placard for determining maximum airspeed based on altitude that placard remains as the means to determine maximum airspeed 2 9 Aerobatic Maneuvers Conducting aerobatic maneuvers may cause the attitude information displayed on the G500 to be incorrect or temporarily removed from the display 2 10 Standby Attitude Gyro A standby attitude indicator is required for IFR operations The Standby Attitude Gyro may operate via the aircraft vacuum system or 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 190 01102 01 Rev 4 Page 14 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM Complete charging is required to bring the battery up to full capacity if it has been unused for more than four months or partially
7. for STC SA02015SE D GARMIN G500 SYSTEM 1 3 Navigation Sources The G500 requires at least one Garmin GPS WAAS 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 PFD attitude display will still be presented see Paragraph 2 7 The G500 HSI can 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 1 4 Synthetic Vision Technology 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 surrounding the aircraft A typical SVT display is shown below DIS DTK 190 01102 01 Rev 4 Page 6 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM SVT provides additional features on the G500 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
8. icon In the event that the pitch command provided by the autopilot flight director is greater than the distance allowed by the G500 the command bars will be displayed at the maximum distance allowed by the G500 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 limits the command bar shown as 4 5 degrees pitch up which is the maximum deviation that can be displayed The G500 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 190 01102 01 Rev 4 Page 28 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 4 5 8 GAD 43 Operation The GAD 43 Adapter provides attitude heading and barometric correction information from the G500 System to the autopilot The GAD 43 can also be configured to provide synchro heading output to other systems and its atti
9. 01 Rev 4 Page 12 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 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 Coverage of the airport terrain database is worldwide The obstacle database contains data for obstacles such as towers that pose a potential hazard to aircraft Obstacles 200 feet and higher are included in the obstacle database It is very important to note that not all obstacles are necessarily charted and therefore may not be contained in the obstacle database Coverage of the obstacle database includes the United States and Europe This database is updated on a 56 day cycle The Garmin SafeTaxi database contains detailed airport diagrams for selected airports These diagrams aid in following ground control instructions by accurately displaying the aircraft position on the map in relation to taxiways ramps runways terminals and services This database is updated on a 56 day cycle The Garmin FliteCharts database contains procedure charts for the coverage area purchased This database is updated on a 28 day cycle If not updated within 180 days of the expiration date FliteCharts will no longer
10. E D GARMIN G500 SYSTEM 5 If GPS position information from the 400VV 500VV 480 is not valid due to an inability to track GPS the own ship icon on the MFD is removed and NO GPS POSITION text is overlaid on the MFD moving map The system will annunciate a loss of integrity LOT on the HSI The LOI annunciation will be colored yellow and the HSI needle will flag The pilot should select an alternate navigation source via CDI key or 1 2 key Pressing the CDI soft key will change the HSI navigation source If GPS navigation is subsequently restored the MFD moving map will display the own ship icon and the HSI navigation source may be selected to GPS at that time the LOT annunciation will be removed 3 3 Abnormal Indications 3 3 1 Heading Failure A magnetometer failure is indicated by a HDG with a red X over it just to the left of the heading display If the GDU 620 is still receiving valid GPS ground track from the GNS navigator the heading will be replaced with GPS ground track in magenta The aircraft can be flown by reference to GPS ground track instead of heading In this case the autopilot will continue to fly in HDG mode but the course being sent to the autopilot will be based on ground track instead of magnetic heading A complete Heading Failure magnetometer and GPS ground track failure is indicated by the digital heading presentation being replaced with a red X and the compass rose digits being removed The cour
11. GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM FAA APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for THE GARMIN G500 PRIMARY FLIGHT AND MULTIFUCTION 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 SA02015SE D for the installation and operation of the Garmin G500 PFD MFD 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 Cited rove Robert Grove ODA STC Unit Administrator GARMIN International Inc ODA 240087 CE 190 01102 01 Rev 4 Page 1 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o Garm
12. Heading Reference System AUX Auxiliary BARO Barometric Pressure BRG Bearing CDI Course Deviation Indicator CRS Course FD Flight Director FPM Flight Path Marker GDU Garmin Display Unit GPS Global Positioning System GPSS GPS Roll Steering HDG Heading HSI Horizontal Situation Indicator IFR Instrument Flight Rules IMC Instrument Meteorological Conditions LOI Loss of Integrity MFD Multi Function Display PFD Primary Flight Display 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 VMC Visual Meteorological Conditions V S Vertical Speed WAAS Wide Area Augmentation System 190 01 102 01 Rev 4 Page 11 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM Section 2 LIMITATIONS 2 1 Cockpit Reference amp Pilot s Guide The Garmin G500 Cockpit Reference Guide P N 190 01102 03 Revision A or later appropriate revision must be immediately available to the flight crew Garmin also provides a detailed G500 Pilot s Guide P N 190 01102 02 This reference material is not required to be on board the aircraft but do
13. LEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 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 available by pressing the MENU button which is on the right side of the display Pressing and holding down the CLR key is a good way to get back to the main map page on the MFD 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 MFD are explained in the Garmin G500 Cockpit Reference Guide 4 3 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 Cockpit Reference Guide for a complete description and the usage of synchronization in dual installations 4 4 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 t
14. M Say ae ee i eee ee xx 2U0 A0 69 69 100 jusWUleya us XM NX f uondo si poyy snouEA peL l uondo si poyy snounen dav x 2U0Nd0 0615 10 087 SND MOES MOE SND 89 21 2001 2 ON xxx 2UONdO st poyy snoLeA joued olpny xx leuondo 0615 10 087 SND MOES MOEY SND S M Z IESOT HOA ON euondo HVOVH 134IM p nb ogy SND 40 S H S 009 101E51AEN SYYM Sd9 Z ON p snb q SND 40 s H S MO00S MO0r JoyeBINeN SVVAVSd ON cib 69 dl leqoig aunyesodwia OG d ynd lo2 geq sly 0811 SUD SYHV Ae dsiq G4W dad 101000 ev avd ieuondo saydepy aR AN L 6S 41 qold 1 029 nd 029 NAD Ae dsiq AAW Q4d 1014 L VbZ OGD u yndwop eyeq y Vik 22 SH 1 9 Dual G500 Operationa vv NWO Jayowojoubeyy SHHV Hi vy NWS OLS Slu s d p llelsul yuewdinby Jejowojeubeyy Page 10 of 29 190 01102 01 Rev 4 AUG 24 2010 FAA APPROVED DATE GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 1 10 Definitions The following terminology is used within this document ADC Air Data Computer ADF Automatic Direction Finder AHRS Attitude amp
15. PLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM Section 4 NORMAL PROCEDURES Refer to the Garmin G500 PFD MFD System Cockpit Reference Guide P N 190 01102 03 or G500 Pilot s Guide P N 190 01102 02 presented in Paragraph 2 1 of this document for normal operating procedures This includes all Primary Flight Display and Multi Function Display information Although intuitive and user friendly the G500 PFD MFD System requires a 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 excellent 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 4 1 PFD Knob amp PFD Soft Keys The basic PFD controls are on the left side of the unit 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 t
16. alink weather via the Garmin GDL69 and GDL69A receivers If an optional XM datalink receiver is installed the pilot will be able to access graphical and text weather products on the MFD and control the audio entertainment data from the MFD while listening via an appropriately installed audio panel 190 01102 01 Rev 4 Page 8 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for STC SA02015SE D GARMIN G500 SYSTEM 1 8 Single G500 Operational Block Diagram Equipment Installed per this STC Magnetometer GMU 44 1 AHRS GRS 77 1 Air Data Computer GDC 74A 1 PFD MED Display GDU 620 Temperature Probe GTP 59 1 No 1 GPS WAAS Navigator 400W 500W Series or GNS 480 required No 2 GPS WAAS Navigator 400W 500W Series or GNS 480 optional No 1 VOR Localizer GS GNS 430W 530W GNS 480 or SL30 optional No 2 VOR Localizer GS GNS 430W 530W GNS 480 or SL30 optional Audio Panel Various Models optional ADF Various Models optional Standby ADI Standby Altimeter required Ma te ee 190 01102 01 Rev 4 FAA APPROVED DATE AUG 24 2010 Adapter optional GAD 43 Autopilot Flight Director Various Models optional Traffic Various Models optional XM WX Enterta
17. displayed from GNS system and are displayed regardless of the system 1 2 setting which drives all other PFD and MFD data used by the G500 2 16 Datalinked Weather Display XM weather data is provided by an optional GDL 69 interface The weather information display on the MFD of the G500 is limited to supplemental use only and may not be used in lieu of an official weather data source 2 17 Traffic Display Traffic may be displayed on the G500 System vvhen connected to an approved optional TCAS TAS or TIS traffic device These systems are capable of providing traffic monitoring and alerting to the pilot Traffic shovvn on the display may or may not have traffic alerting available The display of traffic is an aid to visual acquisition and may not be utilized for aircraft maneuvering 190 01102 01 Rev 4 Page 16 of 29 FAA APPROVED DATE AUG 24 2010 AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for STC SA02015SE D GARMIN G500 SYSTEM GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA 2 18 Active Weather RADAR RADAR is broadcasting energy while in Weather or Ground mapping modes If the G500 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 are in the vicinity approximately 20 feet of the radar sweep area
18. displaying the autopilot selected mode except for GPS Steering mode when emulating Roll Steering via the autopilot heading mode see Paragraph 4 5 Refer to the autopilot operators manual or Airplane Flight Manual Supplement for proper operation of the installed autopilot system The G500 acts as a navigation source switching hub to an interfaced autopilot when multiple navigation sources are available The autopilot will follow navigation deviations from the selected course which is displayed on the G500 HSI Some autopilots may have navigation source selection integral to their system this feature is overridden by the G500 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 190 01102 01 Rev 4 Page 15 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM The G500 altitude alerter may be used as an altitude pre selector for some autopilot installations The autopilot will not couple to the pre selected altitude if not properly configured or supported by the installation Refer to the autopilot operators manual or Airplane Flight Manual Supplement for the proper operation of that system
19. er True or Magnetic on the AUX page The Navigation Angle defines whether the GDU 620 headings are referenced to True or Magnetic North The Navigation Angle set in the GDU 620 must match that which is set on all GNS navigators interfaced to the unit 2 7 AHRS Normal Operating Mode The Attitude and Heading Reference System integrity monitoring features require the availability of GPS and Air Data Although the attitude will remain valid if one of these systems becomes inoperative IFR flight is not authorized unless both integrity systems are fully operational The G500 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 for IFR use 2 8 Maximum Airspeed Primary means of determining maximum airspeed in this aircraft are described belovv O The airspeed markings on the G500 PFD match those on the standby indicator regardless of operating altitude Vne as displayed on the G500 PFD may be used as the means to determine maximum airspeed O This aircraft was originally equipped with an airspeed indicator that also displayed an altitude variable airspeed limitation such as Mmo or a variable Vmo Vne The standby airspeed indicator is the controlling display for the maximum airspeed Do not use Vne as displayed on the G500 PFD unless Mmo is greater than Vmo Vne at the current altitude O This aircraft was originally
20. es contain a more in depth description of all the functions and capabilities of the G500 2 2 System Software Requirements The G500 must utilize the following or later FAA approved software versions Component Identification GDU 620 PFD MFD GRS 77 AHRS GDC 74 Air Data Computer GMU 44 GAD 43 Adapter 2 00 optional In addition to the main components of the G500 at least one Garmin GPS WAAS navigator must be interfaced to the G500 Any GPS WAAS systems connected to the G500 must utilize the following applicable software versions Component Identification Software Version or later GNS 400W Series GPS VVAAS NAV GNS 500W Series GPS VVAAS NAV GNS 480 CNX80 GPS WAAS NAV 2 3 Database Cards The G500 utilizes several databases Database titles display in yellovv if expired or in question Note the G500 receives the calendar date from the GPS but only after acquiring a position fix Database eycle information is displayed at povver up on the MFD sereen 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 is typically vacant as it is used for software maintenance and navigational database updates The lower data card slot should contain a data card with the system s terrain obstacle information and optional data including Safe Taxi FliteCharts and ChartView electronic charts 190 01102
21. 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 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 e Traffic a display on the PFD indicating the position of other aircraft detected by a traffic system interfaced to the G500 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 database e Runway Highlight a highlighted presentation of the location and orientation of the runway s at the 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 fideli
22. function The Jeppesen ChartView electronic charts database contains procedure charts for the coverage area purchased An own ship position icon will be displayed on these charts This database is updated on a 14 day cycle If not updated within 70 days of the expiration date ChartView will no longer function 2 4 AHRS Operational Area The AHRS used in the G500 is limited in its operational area IFR 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 the G500 heading and attitude may occur near the poles but this will not affect the GPS track or standby attitude indicator 2 5 Magnetic Variation Operational Area IFR operations are prohibited in areas where the magnetic variation is greater than 99 9 degrees East or West 190 01102 01 Rev 4 Page 13 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 2 6 Navigation Angle The GDU 620 Navigation Angle can be set to eith
23. he 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 PFD MFD System Cockpit Reference describes each function 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 BRGI and 2 button which are may be overlaid in the HSI presentation on the PFD The soft keys operate by press and release Note In Dual G500 installations the CDI key located on the GNS units is not operational Consult the Garmin G500 PFD MFD System Cockpit Reference 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 and standby instruments Display and control of the airspeed references are made via the AUX page of the MFD consult the Garmin G500 Cockpit Reference Guide for description and operation of these references 4 2 MFD Knobs 6 MFD Soft Keys The MFD controls are on the right side of the unit next to and beneath the MFD display The rotary knobs scroll through various page groups and pages of the MED and manipulate data and settings by pressing the knob to activate a cursor 190 01102 01 Rev 4 Page 24 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPP
24. his menu Press the BACK softkey to return to the root PFD menu 190 01102 01 Rev 4 Page 25 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 4 5 Autopilot Operations with the G500 System The G500 PFD MFD System offers various integration capabilities dependent mainly upon the type of autopilot installed in a particular aircraft The autopilot installed in this aircraft provides the following capabilities 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 Flight Director display driven from external autopilot or FD computer O Flight Director is not available with Synthetic Vision enabled LI A GAD 43 Adapter is installed in this aircraft 4 5 1 Attitude and Rate Based Autopilots If the autopilot is an attitude based system it is operating by inputs from the standby attitude gyro or a remote gyro not the G500 AHRS which is presenting attitude data to the pilot in the PFD If the autopilot is rate based
25. ical Power In the event of a total loss of electrical power the G500 system will cease to operate and the pilot must utilize the standby instruments to fly the aircraft For installations utilizing the battery powered electric attitude gyro the amber standby power light will start flashing Press the STBY PWR button to operate the gyro via its emergency battery If the red warning flag is in view the gyro is inoperative and must not be used 190 01102 01 Rev 4 Page 21 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA 3 5 Warnings Cautions and Advisories AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for STC SA02015SE D GARMIN G500 SYSTEM The following tables show the color and significance of the warning caution and advisory messages which may appear on the G500 displays NOTE The G500 Cockpit Reference Guide and the G500 Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories Warning annunciations Red Annunciation Pilot Action Cause ATTITUDE FAIL Use Standby Display system is not receiving Attitude attitude reference information from the AHRS accompanied by the removal of sky ground presentation and a red X over the attitude area AIRSPEED FAIL Use Standby Display system is not receiving Airspeed airspeed inpu
26. in International 1200 E 151 Street Olathe KS 66062 USA OF oo Ter Dae Ho 7577 07 30 09 10 30 09 07 29 10 08 17 10 Rerelease document 190 01102 01 Rev 4 FAA APPROVED DATE AUG 24 2010 Complete Supplement Remove requirement for standby ADI for VFR operations installations Add maximum airspeed limitation section Correct page numbering AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for STC SA02015SE D GARMIN G500 SYSTEM FAA Approved Dauid Cunsteong David Armstrong ODA STC Unit Administrator GARMIN International INC ODA 240087 CE Date OC 30 09 obari Drove Robert Grove ODA STC Unit Administrator GARMIN International INC ODA 240087 CE Date L2 0 09 Robart Prove Robert Grove ODA STC Unit Administrator GARMIN International INC ODA 240087 CE Date 02 30 Kal Irete Robert Grove ODA STC Unit Administrator GARMIN International INC ODA 240087 CE Date O 0 0 Page 2 of 29 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM Table of Contents SECTION PAGE Section 1 GENERAL 5 1 1 Garmin G500 Primary Flight Multi Function Display System 5 1 2 System Power Sources 5 1 3 Navigation Sources 6 1 4 Synthetic Vision Technology 6 1 5 Autopilo
27. inment GDL 69 69A optional Weather RADAR optional Existing Equipment already installed in the aircraft 5 ADI may be replaced with electric ADI with integral dedicated backup battery STBY ADI Not required to be installed or operational for VFR operations Audio panel connection to GDU 620 is recommended for tones and aural alerts generated by the GDU 620 Page 9 of 29 AIRPLANE FLIGHT MANUAL SUPPLEMENT or GARMIN Ltd or its Subsidiaries c o SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Garmin International 1200 E 151 Street Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 029 NAD v Aq spoye Jeune pue S UO 10 papusWWODaJ S 029 NAD 01 uoWOSUUOD Jaued OIPNY yx s JUaWdinbe ieuondo SY 0 1iG9 y UO jqejene aq IlIM q t dinb jeuondo y Aq suoyoun4 p nb jou SI SGD uloq ol Juatudinba ieuondo UOND UUOD JuaWdinby 010 suonesado HAA 40 fEUONE dO 10 p lle sul JON IAY AALS A neq dnyoeq payeopep e16 u YUM qy m l yum p oeld l Aew lav Aqpuels yee y ul pajjeysul juawdinb3 Sunsixz iagram I Block D e IEuondo sjapoy snoLEAN r 1 Joya 1461 1 Auo apis jojid uo amp
28. it uses a Turn Coordinator rate gyro which may be in the instrument panel or remotely mounted In either case independent systems are driving the autopilot and the PFD the pilot should understand the system to better detect possible faults which could occur Refer to the autopilot AFMS to review the system installed in the aircraft 4 5 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 NAV 2 is switched via the G500 PFD display Whatever is displayed on the HSI is the NAV source the autopilot is following Most autopilots also use the course datum to determine the best intercept angles when operating in NAV mode 4 5 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 then 180 degrees the autopilot may turn the airplane in the opposite direction of the desired turn 190 01102 01 Rev 4 Page 26 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 4 5 4 Roll Steering emula
29. n this instance the PFD will not provide Attitude Heading Altitude or Airspeed information however if the PFD is receiving valid GPS information the reversionary data on the PFD provides GPS Track and GPS Altitude data along with course information and deviations which are still valid and may be used to navigate 3 If navigation information on the PFD MFD HSI RMI WPT bearing and distance information or Moving Map Data is not available or appears invalid select an alternate data source via CDI key or 1 2 key or utilize the data directly from the navigation equipment as required 4 synthetic vision display of terrain uses several data sources to correctly display terrain GPS terrain database attitude information etc If any of these data sources become unreliable or unavailable the display of synthetic terrain will automatically revert to the non SVT PFD display of blue over brown Additionally if during the course of normal operations there is any discrepancy between actual terrain around the aircraft and terrain shown on the SVT display the display of synthetic vision should be manually turned off using the procedure in section 4 4 of this flight manual supplement 190 01102 01 Rev 4 Page 19 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015S
30. o the autopilot The G500 receives this data from the GPS In dual GPS installations the G500 sends Roll Steering information for the GPS which is currently selected for use via the PFD 1 2 button 4 5 6 Altitude Pre Selector integrated with the autopilot If the autopilot is compatible with the Altitude Alerter in the G500 system then the alerter may be used as an Altitude Pre Selector for the autopilot The G500 system does not control the rate or pitch of the climb it only communicates the approaching altitude to the autopilot computer The Altitude Bug Setting will flash when approaching within 1000 feet of the selected altitude and an audio tone is played when approaching or deviating within 200 feet of the selected altitude 190 01102 01 Rev 4 Page 27 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 4 5 7 Flight Director Display If autopilot flight director commands are interfaced to the G500 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 director on the G500 The G500 system limits the distance the flight director pitch commands may deviate from the aircraft attitude
31. se pointer will indicate straight up and operate much like a traditional CDI with the Omni Bearing Selector being adjusted by the PFD knob set to CRS Under this condition the pilot must use an alternate source of heading such as the standby compass If the installation includes an autopilot the pilot workload may be reduced by operating that system in NAV mode 3 3 2 AHRS Failure A failure of the Attitude and Heading Reference System AHRS is indicated by a removal of the sky ground presentation a red X and a yellow AHRS FAILURE shown on the PFD A heading failure will also occur as described above in 3 3 1 1 Use Standby Attitude Indicator and standby compass 2 Set course datum using CRS selection of the PFD knob 3 Seek VFR conditions or land as soon as practical 190 01102 01 Rev 4 Page 20 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 3 3 3 Air Data Computer ADC Failure Complete loss of the Air Data Computer 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 1 Use Standby Airspeed Indicator and Altimeter 2 Seek VFR conditions or land as soon as practical 3 4 Loss of Electr
32. t Interface 7 1 6 Audio Panel 8 1 7 Traffic and Weather Systems 8 1 8 Single G500 Operational Block Diagram 9 1 9 Dual G500 Operational Block Diagram 10 1 10 Definitions 11 Section 2 LIMITATIONS 12 2 1 Cockpit Reference amp Pilot s Guide 12 2 2 System Software Requirements 12 2 3 Database Cards 12 2 4 AHRS Operational Area 13 2 5 Magnetic Variation Operational Area 13 2 6 Navigation Angle 14 2 7 AHRS Normal Operating Mode 14 2 8 Maximum Airspeed 14 2 9 Aerobatic Maneuvers 14 2 10 Standby Attitude Gyro 14 2 11 Course Pointer Auto Slewing 15 2 12 Synthetic Vision Technology 15 2 13 Autopilot Interface 15 2 14 Terrain Display 16 2 15 TAWS Annunciations on the PFD from a Garmin navigator 16 2 16 Datalinked Weather Display 16 2 17 Traffic Display 16 2 18 Active Weather RADAR 17 2 19 Kinds of Operations 18 Section 3 EMERGENCY PROCEDURES 19 3 1 Emergency Procedures 19 3 2 Abnormal Procedures 19 3 3 Abnormal Indications 20 3 4 Loss of Electrical Power 21 3 5 Warnings Cautions and Advisories 22 Section 4 NORMAL PROCEDURES 24 4 1 PFD Knob amp PED Soft Keys 24 4 2 MED Knobs z MED Soft Keys 24 4 3 Altitude Synchronization 25 190 01102 01 Rev 4 Page 3 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 44 Synthetic Vision Technology
33. t from the air data computer accompanied by a red X through the airspeed display ALTITUDE FAIL Use Standby Display system is not receiving Altitude altitude input from the air data computer accompanied by a red X through the altimeter display VERT SPD FAIL Cross check Display system is not receiving instruments vertical speed input from the air data computer accompanied by a red X through the vertical speed display HDG Use Standby Display system is not receiving valid Magnetic heading input from the AHRS Compass or GPS accompanied by a red X through the track information digital heading display Red X Reference the data A red X through any display field 190 01102 01 Rev 4 source or alternate equipment FAA APPROVED DATE AUG 24 2010 indicates that display field is not receiving data or is corrupted Page 22 of 29 GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA AIRPLANE FLIGHT MANUAL SUPPLEMENT or SUPPLEMENTAL AIRPLANE FLIGHT MANUAL for STC SA02015SE D GARMIN G500 SYSTEM Caution annunciations Yellow Annunciation Pilot Action Cause Fly the aircraft The GDU 620 attitude monitors CHECK ATTITUDE have detected an AHRS Autopilot will automatically disconnect Note Only appears with the installation of an optional GAD 43 adapter manually and crosscheck GDU 620 attitude indication with standby attitude indicator and other so
34. ted via HDG mode If the autopilot does not have GPS Roll Steering capability the G500 may be able to emulate this functionality by operating the autopilot in HDG mode and selecting GPS Roll Steering mode via one of two types of external switches located near the autopilot control panel A toggle or push button switch as depicted below allows the pilot to select the heading datum source that the autopilot will use AP HDG AP HDG DATUM DATUM po HDG toggle switch push button Whenever GPSS is selected as the autopilot s heading datum source the mode is annunciated just left of the G500 HSI The icon is the heading bug with an X through it signifying that GPSS information is overriding the heading bug data GPS steering information is then sent via the heading error signal to the autopilot to make the aircraft turn onto course or fly arcs and holding patterns The G500 HDG bug is decoupled from the autopilot in this mode but the bug is still controllable and may still be used by the pilot for reference If the GPS Roll Steering data becomes invalid because the GPS system has flagged it or the selected HSI source is not GPS the text of the GPSS annunciator will be yellow and the data to the autopilot will command wings level flight 4 5 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 t
35. tude output can be used 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 G500 startup an AP TEST soft key will be available on the G500 PFD side of the G500 display 2 Engage the AP while on the ground 3 Press the AP TEST soft key and verify that the autopilot disconnects 4 5 9 Dual G500 Autopilot Interface If the installation has dual G500 PFD MFD systems installed the autopilot is physically connected to the pilot side system 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 Cockpit Reference Guide for additional information Section 5 PERFORMANCE No change Section 6 WEIGHT AND BALANCE See current weight and balance data Section 7 SYSTEM DESCRIPTIONS See Garmin G500 PFD MFD System Cockpit Reference Guide P N 190 01102 03 for basic operational aspects of the system For a complete detailed explanation of all the G500 s capabilities see the G500 Pilot s Guide P N 190 01102 02 190 01102 01 Rev 4 Page 29 of 29 FAA APPROVED DATE AUG 24 2010
36. ty 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 1 5 Autopilot Interface The G500 may be interfaced to an optional autopilot The G500 typically provides course and heading datum to the autopilot based on the data selected for display on the HSI For multiple GPS NAV systems the G500 acts as a selection hub for the autopilot s NAV mode and the G500 may also provide GPS Steering data Some autopilots may provide Flight Director capabilities which can be displayed on the G500 Attitude Indicator as a Single Cue Flight Director 190 01102 01 Rev 4 Page 7 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM 1 6 Audio Panel The G500 PFD MFD system should be interfaced into the aircraft audio panel to provide aural altering generated by the G500 1 7 Traffic and Weather Systems The G500 PFD MFD system supports TIS traffic via the Garmin GTX Series Mode S Transponders The system also supports TAS TCAS TIS traffic from various active traffic awareness systems The information from these systems is available and controllable on the MFD The G500 PFD MFD system supports XM dat
37. ude and airspeed information This may be from either the PFD or the standby instruments i e all 1a items or all 1b items from the table above For IFR flight a fully functional G500 system should not generate system alerts which indicate faults within the system or any interfaced equipment 190 01102 01 Rev 4 Page 18 of 29 FAA APPROVED DATE AUG 24 2010 GARMIN Ltd or its Subsidiaries c o AIRPLANE FLIGHT MANUAL SUPPLEMENT or Garmin International 1200 E 151 Street SUPPLEMENTAL AIRPLANE FLIGHT MANUAL Olathe KS 66062 USA for STC SA02015SE D GARMIN G500 SYSTEM Section 3 EMERGENCY PROCEDURES 3 1 Emergency Procedures No change 3 2 Abnormal Procedures These procedures supersede those presented as markings or placards or documented in the aircraft s FAA approved Airplane Flight Manual as a result of the installation of the 6500 PFD MFD system All other emergency procedures remain in effect 1 If primary flight information Attitude Heading Altitude or Airspeed on the PFD is not available or appears invalid utilize the standby instruments installed around and adjacent to the G500 as required 2 The Attitude Heading and Reference System AHRS requires at least one GPS or air data input to function properly In the unlikely event that GPS data and air data is not received by the AHRS the system will subsequently lose attitude and heading and the pilot will be required to use the standby instrumentation I
38. urces of attitude information airspeed heading altitude etc malfunction or the inability to actively monitor the AHRS output AHRS Aligning Limit aircraft Attitude and Heading Reference Keep Wings Level banking as AHRS System is aligning Keep wings Aligns OK to taxi level using standby attitude indicator AHRS will align even if you must bank but the alignment time may be slightly longer if maneuvering NO GPS POSITION If the system is GPS data on the selected system configured with dual is no longer valid The Moving GPS press the 1 2 Map and associated data are not button updating TRAFFIC Visually acquire the The configured traffic system traffic to see and has determined that nearby avoid traffic may be a threat to the aircraft No Traffic Data Use vigilance as the The configured traffic system is traffic sensor is not able to detect traffic not able to detect traffic and or provide the pilot with any traffic awareness Advisories White Annunciation Pilot Action Various Alert Messages may appear under the MED ALERTS soft key 190 01102 01 Rev 4 FAA APPROVED DATE AUG 24 2010 View and understand all advisory messages Typically they indicate communication issues within G500 System Refer to the G500 Cockpit Reference for appropriate pilot or service action Page 23 of 29 GARMIN Ltd or its Subsidiaries c o AIR
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