Garmin STC for Bell 206/407 Rotorcraft Flight Manual Supplement
Contents
1. Visually acquire the terrain and avoid Use vigilance as the HSVT Terrain will not provide terrain or obstacle alerts Visually acquire the obstacle and avoid Use alternate source for weather data GPS data on the selected system 1s no longer valid The Moving Map and associated data are not updating The configured traffic system has determined that nearby traffic may be a threat to the aircraft The configured traffic system is not able to detect traffic and or provide the pilot with any traffic awareness The configured traffic system may have failed HSVT Terrain has determined that nearby terrain may pose a collision hazard HSVT Terrain has failed HSVT Terrain has determined that a nearby obstacle may pose a collision hazard The datalink for weather has failed NO DATA Data is not available for display Table 3 2 Caution Annunciations Yellow 190 01150 62 Rev A FAA APPROVED DATE February 25 2011 Page 13 of 28 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street Olathe KS 66062 USA Annunciation Various Alert Messages may appear under the MFD ALERTS soft key 190 01150 62 Rev A MANUAL SUPPLEMENT STC SR02295LA GARMIN G500H Bell 206A Pilot Action View and understand all advisory messages Typically they indicate communication issues within the G500H System Refer to the G500H Cockpit Reference for appropriate pil2. HSVT Terrain modes normal reduced protection RP and inhibit can be selected via softkey on the Terrain page on the G500H MFD Altitude Alerter The Altitude Bug Setting will flash when approaching within 1000 feet of the selected altitude and an audio tone 1s played when approaching or deviating within 200 feet of the selected altitude MULTI FUNCTION DISPLAY The primary function of the MFD is to display supplemental data including mapping terrain video charts and flight plan information MFD Knobs amp MFD Soft Keys The MFD controls are adjacent to and beneath the MFD display The rotary knobs are used to scroll through various pages page groups of the MFD Pressing the knob will activate a cursor and allow for the user to enter data and manipulate settings Soft keys at the bottom of the display allow for the rapid selection of pre defined functions to be performed on each page The soft keys operate by pressing releasing More detailed configuration is typically available by pressing the MENU button located on the right side of the display Pressing and holding down the CLR key for 2 seconds will display the main map page on the MFD Details of the functions available on the MFD are explained in the Garmin G500H Cockpit Reference Guide 190 01150 62 Rev A Page 21 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMEN
3. OAT displays Some derived functions such as true airspeed and wind calculations will also be lost Utilize standby instruments and visual references 3 2 5 Navigation If navigation information on the PFD MFD HSI Bearing Pointers 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 Utilize the data directly from the navigation equipment as required If GPS position information from the GPS WAAS navigator is not valid 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 LOI on the HSI The LOI annunciation will be colored yellow and the HSI needle will flag Press the CDI or 1 2 soft key to select an alternate navigation source 190 01150 62 Rev A Page 10 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A 3 2 6 Display Dimming When operating at high Outside Air Temperatures typically in excess of 20 C the GDU 620 display may automatically dim to reduce equipment temperatures but will still be visible The display will return to full brightness when operating temperatures are reduced Utilize the standby instruments and visual references for aircraft cont
4. 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 The HSVT function may be turned on or off as desired To access the HSVT 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 The synthetic vision display of terrain uses several data sources GPS terrain database attitude information etc in order to accurately display terrain 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 190 01150 62 Rev A Page 20 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A HSVT Terrain When the G500H has SVT enabled aural and visual terrain and obstacle alerting will be provided by the HSVT Terrain function of the G500H system
5. by a removal of the sky ground presentation a red X over the attitude indicator and a yellow ATTITUDE FAIL shown on the PFD A heading failure will also be indicated Utilize visual references for aircraft control GPS Track Utilize for heading if available 190 01150 62 Rev A Page 9 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A 3 2 3 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 GPS Track Utilize for heading if available 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 course pointer will indicate straight up and operate much like traditional CDI with the Omni Bearing Selector being adjusted by the PFD knob set to CRS Utilize standby compass 3 2 4 Air Data Computer ADC Failure Complete loss of the Air Data Computer is indicated by a red X over the airspeed altimeter vertical speed TAS and
6. document ADC Air Data Computer AHRS Attitude amp Heading Reference System BARO Barometric Pressure BRG Bearing CDI Course Deviation Indicator CRS Course FPM Flight Path Marker GDU Garmin Display Unit GPS Global Positioning System GSR Garmin Iridium Transceiver HDG Heading HSI Horizontal Situation Indicator HSVT Helicopter Synthetic Vision Technology ILS Instrument Landing System LDA Localizer Directional Aid LOC Localizer LOC BC Localizer Backcourse MFD Multi Function Display PFD Primary Flight Display RP Reduced Protection Mode SD Secure Digital SDF Sunplified Directional Facility TAS Traffic Awareness System TIS Traffic Information Service 190 01150 62 Rev A FAA APPROVED DATE February 25 2011 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT STC SR02295LA GARMIN G500H Bell 206A Page 27 of 28 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SRO2295LA GARMIN G500H Bell 206A VFR Visual Flight Rules VMC Visual Meteorological Conditions V S Vertical Speed WAAS Wide Area Augmentation System 190 01150 62 Rev A Page 28 of 28 FAA APPROVED DATE February 25 2011
7. the display just to the upper left of the HSI HDG CRS ALT V S or BARO If no function is annunciated the knob is providing a HDG function Assigning the function of the knob is done by pressing releasing one of the dedicated function buttons adjacent to the PFD The knob defaults back to HDG if it is not rotated for a period of 10 seconds The Garmin G500H PFD MFD System Cockpit Reference Guide describes each function and its operation 190 01150 62 Rev A Page 17 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SRO2295LA GARMIN G500H Bell 206A 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 BRG1 and BRG2 button which may be overlaid in the HSI presentation on the PFD The soft keys operate by press and release The ATT SYNC soft key synchronizes the miniature aircraft symbol to the horizon line at the time it is pressed Pressing the soft key again will return the miniature aircraft symbol to its zero reference When ATT SYNC is active small marks will appear at the outboard edges of the attitude display that show the zero pitch reference The units and markings on the PFD are not user configurable They match the units as specified in the aircraft s FAA approved Rotorcraft Fligh
8. Era va Cav E V da E do E da Dus 8 a BEPOEE LARE OEP ins es va ae d e OT Pe 5 SECTION 3 EMERGENCY AND MALFUNCTION PROCEDURES 9 3 1 EMERGENCY PROCEDURES cccsecoccsccctocestecstescsseecsecusseensuceseneuecasns 9 3 2 MALFUNCTION INDICATIONS AND PROCEDURES cccsceeeeceseceeccetcececnceececeereaeceees 9 GARMIN G500H FLIGHT DISPLAY SYSTENML vett rater mta 16 SAO O EIANEPOMCER SODBISS sec iste ae c Reale nee Ras I7 PRIMARY EIGER ESP GAY eee sivit bct nA RN EIS FEET Reo dide 17 BME TEEN DISPLAY 55cescc xc teer tV Eve NTRS 21 NAVIGATION SOURE B ui RSV UE Ree E BE RR REPE RD UR 22 AUDIO PANE uec eG RR Ee 22 190 01150 62 Rev A Page 3 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A INTERFACED SOHEHSISESUMm creep irivee tat cca trees M JE Aare tee each tact m 23 SYSTEM BLOCK DIAGRAM m B M e e 26 DERT EE e T 27 190 01150 62 Rev A Page 4 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A Section 1 LIMITATIONS 1 1 Types of Operation Rotorcraft equipped with the G500H Avi
9. GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT GARMIN G500H As installed in Bell 206A Registration Number Serial Number This document serves as the Rotorcraft Flight Manual Supplement when the rotorcraft is equipped in accordance with Supplemental Type Certificate SRO2295LA for the installation and operation of the Garmin G500H avionics display system in Canadian registered rotorcraft This document must be carried in the rotorcraft 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 placards markings or an approved Rotorcraft 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 approved Rotorcraft Flight Manual FAA APPROVED Manager Fligh ranch ANM 160L Federal Aviati n Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate DATE Zoll GARMIN Ltd or its Subsidiaries c o Garmin nternational ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A LOG OF REVISIONS OF REVISIONS Page uz ision mum ae xx FAA pg Number 2 25 11 Complete Supplement m Mgr F
10. J id 190 01150 62 Rev A Page 16 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A The standby instruments airspeed altimeter and magnetic compass are completely independent from the PFD and will continue to operate in the event the PFD is inoperative These standby instruments should be included in the pilot s normal instrument scan and must be utilized if the PFD data is in question System Power Sources The G500H system depends on electrical power to function The Garmin Display Unit GDU Attitude and Heading Reference System AHRS and Air Data Computer ADC are connected to the aircraft main bus The major components of the G500H are circuit breaker protected with reset able type circuit breakers available to the pilot These breakers are located on the overhead circuit breaker panel and are labeled as follows Unit Controlled Attitude and Heading Reference System GRS 77H ADC Air Data Computer GDC 74H PRIMARY FLIGHT DISPLAY The function of the PFD is to provide attitude heading air data and navigation information from GNS units to the pilot PFD Garmin Display Unit PFD MFD GDU 620 PFD Knob amp PFD Soft Keys The basic PFD controls are adjacent to and beneath the PFD display The rotary knob performs the function annunciated on
11. T Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A NAVIGATION SOURCES The G500H requires at least one Garmin GPS WAAS navigation unit to be installed to ensure the integrity of the Attitude and Heading Reference System The AHRS will still operate in reversionary mode if all GPS sources fail and the PFD attitude display will still be presented The HSI on the G500H can display course deviation information from up to four sources GPS 1 GPS 2 VLOC 1 or VLOC 2 In addition the HSI can display two simultaneous bearing pointers sourced from GPS 1 GPS 2 VLOC 1 or VLOC 2 AUDIO PANEL The G500H Avionics Display System is interfaced with the audio panel installed in the rotorcraft to provide aural altering generated by the G500 INTERFACED EQUIPMENT The G500H Flight Display System is approved to interface with other avionics systems including a TIS Traffic TAS Traffic GDL 69 XM Data link Video GSR 56 Iridium Data link E GNS 400W or 500W Series Navigator Traffic Display and Control Optional The G500H Avionics Display System can display traffic from various sources including TIS data from the Garmin GTX Series Mode S Transponders or TAS data from various active traffic awareness systems The information from these systems 1s displayed on and controlled through the MFD XM Data link Optional The G500H Avionics Display System can display weather data from a Garmin GDL69 or GDL69A XM satellite receiver Graphical and textu
12. al ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A Section 2 NORMAL PROCEDURES 2 1 Preflight Databases Verify current MFD system startup page 2 1 Before Takeoff MFD Press Enter key Data fields on the PFD Verify valid and normal System Messages Considered 190 01150 62 Rev A Page 8 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A Section 3 EMERGENCY AND MALFUNCTION PROCEDURES These procedures supersede those presented as markings or placards or documented in the aircraft s FAA approved Rotorcraft Flight Manual as a result of the installation of the G500H system All other emergency procedures remain in effect 3 1 Emergency Procedures 3 1 1 Electrical Power Failure In the event of a total loss of electrical power the G500H system will cease to operate Utilize standby instruments and visual references for aircraft control 3 2 Malfunction Indications and Procedures 3 2 1 Primary Flight Display Malfunction Primary flight information Heading Altitude or Airspeed on the PFD not available or invalid Utilize standby instruments and visual references for aircraft control 3 2 2 AHRS Failure A failure of the Attitude and Heading Reference System AHRS is indicated
13. al weather information is displayed on and controlled through the MFD If the G500H is 190 01150 62 Rev A Page 22 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SRO2295LA GARMIN G500H Bell 206A interfaced to a Garmin GDL 69A XM satellite receiver then control of audio entertainment can be performed through the MFD Video Input Optional The G500H Avionics Display System can display images from up to 2 video inputs Video images are displayed on the MFD The G500H does not provide a means to control the video source however the digital images from the video source can be adjusted using the G500H Iridium Data link Optional The G500H Avionics Display System can automatically report the rotorcraft position when interfaced with a Garmin GSR 56 Iridium Data link Position reports are controlled through the MFD DATABASES The G500H utilizes several databases Database titles display in yellow if expired or in question Note the G500H 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 is typically vacant as it is used for
14. bruary 25 2011 Display system 1s not receiving attitude reference information from the AHRS accompanied by the removal of sky ground presentation and a red X over the attitude area Display system is not receiving airspeed input from the air data computer accompanied by a red X through the airspeed display Display system is not receiving altitude input from the air data computer accompanied by a red X through the altimeter display Display system is not receiving vertical speed input from the air data computer accompanied by a red X through the vertical speed display Display system is not receiving valid heading input from the AHRS accompanied by a red X through the digital heading display Attitude and Heading Reference system is aligning Keep attitude level using outside references AHRS will not align if bank angle remains over 10 degrees Page 12 of 28 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A NO GPS POSITION TRAFFIC NO TRAFFIC DATA TREC FAIL TERRAIN TER FAIL OBSTACLE WEATHER DATALINK FAILED If the system Is configured with dual GPS press the 1 2 button Visually acquire the traffic to see and avoid Use vigilance as the traffic sensor 1s not detecting traffic Use vigilance as the traffic sensor may not be able to detect traffic
15. e 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 190 01150 62 Rev A Page 24 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A PITOT STATIC SYSTEM The pitot static system supplies pitot static pressure to the GDC 74H standby altimeter and standby airspeed indicator 190 01150 62 Rev A Page 25 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A SYSTEM BLOCK DIAGRAM G500H Avionics System Magnetometer Equipment Installed per this STC GMU 44 ee es h GRS 77H ae E GDU 620 i PFD MFD Air Data Computer GDC 74H rT Temperature Probe GTP 59 ph TE No 1 GPS WAAS Navigator and or VOR Localizer GS GNS 400WIS00W seres or GNS 480 Iridium Datalink R56 optional 190 01150 62 Rev A Page 26 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA DEFINITIONS The following terminology is used within this
16. lected for display and ground speed is more than 30 knots Horizon Line a white line indicating the true horizon is always displayed on the SVT display The position of the terrain relative to the horizon line depends on aircraft altitude Horizon Heading a pilot selectable display of heading marks displayed just above the horizon line on the PFD 190 01150 62 Rev A Page 19 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A e Airport Signs pilot selectable signposts displayed on the synthetic terrain display indicating the position of nearby airports that are in the G500H database e Runway Highlight a highlighted presentation of the location and orientation of the runway s at the destination airport e Traffic Optional a display on the PFD indicating the position of other aircraft detected by a traffic system interfaced to the G500H system The synthetic terrain depiction displays an area approximating the view from the pilot s eye position when looking directly ahead of the pilot Terrain features outside the 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 aircraft It may not provide either the accuracy or fidelity or both on which to solely
17. lt Test Br ANM 160L Federal Aviation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate Date I 26 261 190 01150 62 Rev A Page 2 of 28 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A Table of Contents SECTION 1 LIMITATIONS ocanscacensescexsensnareceasapensesersserresvsceves EPIO e 1 1 TYFES FOPERA TON o iuto RR N ON EN XR EE RR RA ve UU Rl ER e os 5 1 2 COCKPIT REFERENCE t FILOT 5S GUIDES scant S ener aa 5 1 3 SYSTEM SOFTWARE KEQUIREMENTS ities GRO ees 5 1 4 I ES Tog cc PRENNE AA A ai nil Oo aLaA TT 6 1 5 AFHES OPERATIONAL BIS A esercrkten k HERE UMOR PRI ER ER IPRNT EFE EU UIN PEU TEE ATEEK 6 1 6 AHRS OPERATII aeoea EEEE E E EASA E AEAEE E E AAE 6 L3 MAXKUM AIRS PEET n ecsnimeisiuti mda EIE t MR UM RR EE T ERE 6 1 8 TRATEN ROUTIETS ee CE GRE ee re S RUDI RESUME ERN PAR 6 1 9 HELICOPTER SYNTHETIC VISION TECHNOLOGY HSV T seen 6 1 10 TERRAIN AND OBSTACLE DISPLAY U PEN 6 LEL TRAPIC DHSBLA Yu seeseciscetatencit aiti eot sso ccu ex p med eek te St QD EO e OR EN RC erba T 112 EQUIPMENT REQUIREMENTS 245i rdc Exod Fa a vv Ye Cups mii SEL TION 2 NURMBAL FROCEDLE BIEN srocennensocsnenssmnensnnersenesanersvgonnsneynsenegransanseransnyiens B 2 1 PEBEEIQHUT uc t E ee cM E e s Ci Ede Lice Du
18. onics Display System are limited to VFR ONLY 1 3 Cockpit Reference amp Pilot s Guides Garmin G500H Cockpit Reference Guide P N 190 01150 03 Revision A or later appropriate revision must be immediately available to the flight crew 1 35 System Software Requirements The G500H must utilize the following approved software versions for this Flight Manual Supplement to be valid Component Identification Software Version or later approved GDC 74H Air Data Computer GMO Table 1 1 G500H Software Versions In addition to the main components of the G500H at least one Garmin GPS WAAS navigator must be interfaced to the G500H Any GPS WAAS systems connected to the G500H must utilize the following applicable software versions for this Flight Manual Supplement to be valid Component Identification Software Version or later approved GNS 400W Series GPS WAAS NAV GNS 500W Series GPS WAAS NAV GNS 480 CNX80 GPS WAAS NAV i Table 1 2 GNS Navigator Required Software Versions 190 01150 62 Rev A Page 5 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A 1 4 Databases Coverage of the terrain database is between North 75 latitude and South 60 latitude in all longitudes Coverage of the obstacle database includes the United States and Europe De
19. ot or service action Table 3 3 Advisories White Page 14 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A Section 4 PERFORMANCE No change 190 01150 62 Rev A Page 15 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A GENERAL INFORMATION Garmin G500H Flight Display System The G500H Flight Display System consists of a Primary Flight Display PFD and Multi Function Display MFD housed in a single Garmin Display Unit GDU 620 an Air Data Computer GDC 74H ADC an Attitude and Heading Reference Systems GRS 77H AHRS The G500H interfaces with a Garmin GNS 400W 500W or 480 series GPS W AAS navigator and an audio panel Optionally the G500H may interface with other systems installed in the rotorcraft including a Garmin GT X330 transponder TAS traffic system GDL 69 A satellite data link video sources and GSR 56 Iridium data link Reference Garmin G500H PFD MFD System Cockpit Reference Guide P N 190 01150 03 for basic operational aspects of the system For a complete detailed explanation of all the G500H s capabilities see the G500H Pilot s Guide P N 190 01150 02 GARMIN I
20. rol 3 2 7 Warnings Cautions and Advisory Annunciations The following tables show the color and significance of the warning caution and advisory messages which may appear on the G500H displays NOTE The G500H Cockpit Reference Guide and the G500H Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories A red X through any display field Utilize alternate indicates that display field 1s not equipment receiving data or the data is corrupted HSVT Terrain has determined that nearby terrain poses a collision hazard HSVT Terrain has determined that a nearby obstacle poses a collision hazard Red E Visually acquire the terrain and avoid TERRAIN Visually acquire the OBSTACLE obstacle and avoid Table 3 1 Warning Annunciations Red 190 01150 62 Rev A Page 11 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SRO2295LA GARMIN G500H Bell 206A Pilot Actio ATTITUDE FAIL AIRSPEED FAIL ALTITUDE FAIL VERT SPD FAIL AHRS ALIGN Keep Wings Level 190 01150 62 Rev A Use visual references Use Standby Airspeed Use Standby Altimeter Cross check instruments Use Standby Magnetic Compass or GPS track information Limit rotorcraft bank to less than 10 degrees as AHRS Aligns FAA APPROVED DATE Fe
21. 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 The terrain databases are updated periodically and have no expiration date The obstacle database contains data for obstacles such as towers that pose a potential hazard to aircraft It is very important to note that not all obstacles are necessarily charted and therefore may not be contained in the obstacle database 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 air traffic 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 190 01150 62 Rev A Page 23 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SRO2295LA GARMIN G500H Bell 206A The Garmin FliteCharts database contains procedure charts for the coverage area purchased This database 1s updated on a 28 day cycle If not updated within 180 days of the expiration date FliteCharts will no longer function The Jeppesen ChartView electronic charts database contains procedur
22. t Manual and standby instruments Display and control of the airspeed references are made via the AUX page of the MFD consult the Garmin G500H Cockpit Reference Guide for description and operation of these references Helicopter Synthetic Vision Technology HSVT Optional HSVT uses an internal terrain database and GPS location to present the pilot with a synthetic view of the terrain and obstacles 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 HSVT display is shown below 190 01150 62 Rev A Page 18 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A ATT SYNC HSVT provides additional features on the G500H primary flight display PFD which include the following information 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 Obstacles obstacles such as towers 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 displayed when synthetic terrain is se
23. tailed database coverage areas can be found at www garmin com 1 5 AHRS Operational Area The GRS 77 AHRS used in the G500H is limited in its operational area AHRS Operation is not assured north of 72 N and south of 70 S latitudes In addition AHRS operation is not assured 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 G500H heading and attitude may occur in these regions 1 6 AHRS Operation When operating in no magnetometer or no magnetometer no air data modes rapid pitch or roll movements may result in temporary loss of attitude indication 1 7 Maximum Airspeed This rotorcraft was originally equipped only with a placard for determining maximum airspeed based on altitude that placard remains as the means to determine maximum airspeed 1 8 Navigation Angle The Navigation Angle set in the GDU 620 must match that which is set on the GNS navigators 1 e output in degrees MAGNETIC or TRUE 1 9 Helicopter Synthetic Vision Technology HSVT Helicopter Synthetic Vision Technology HSVT is for situational awareness ONLY The use of the synthetic vision display for aircraft control navigation or obstacle terrain or traffic avoidance is prohibited 1 10 Terrain and Obstacle Displa
24. y Terrain and obstacle information is depicted for advisory purposes only and is not to be used for aircraft maneuvers or navigation 190 01150 62 Rev A Page 6 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin International ROTORCRAFT FLIGHT 1200 E 151 Street MANUAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206A 1 11 Traffic Display The display of traffic 1s an aid to visual acquisition and 1s not to be utilized for aircraft maneuvering CAUTION some TAS traffic systems may not automatically transition to OPERATE mode upon becoming airborne or in the event of a power interruption while in the air may power on in STANDBY mode The pilot must be aware of the operating status of the T AS traffic system by referring to the traffic icon on the map pages or the status annunciator on the traffic page If the traffic system is in STANDBY mode use the traffic page softkeys to change to the OPERATE mode 1 12 Equipment Requirements Table 1 3 below lists the minimum fully functional G500H System Elements required for VFR flight operations Equipment Number installed I E Primary Multi Function Display Attitude Heading Ref System AHRS Air Data A ADC GNS 400W 500W or 480 series Lond navigator Table 1 3 G500H Equipment Requirements 190 01150 62 Rev A Page 7 of 28 FAA APPROVED DATE February 25 2011 GARMIN Ltd or its Subsidiaries c o Garmin Internation
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