Garmin STC for Bell 206/407 Rotorcraft Flight Manual Supplement
Contents
1. VIS Vertical Speed WAAS Wide Area Augmentation System 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 24 of 24 FAA APPROVED2. Coverage of the obstacle database includes the United States and Europe This database is updated on a 56 day cycle 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 6 of 24 FAA APPROVED 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 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 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 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
3. GPS WAAS Navigator Various models and or VOR Localizer GS GTN 6XX 7XX GNS 400W 500W series or GNS 480 required Traffic Various Models optional No 2 GPS WAAS Navigator and or VOR Localizer GS GTN 6XX 7XX GNS 400W 500W series GNS 480 or SL30 optional Weather Data Link GDL 69 optional XM Entertainment GDL 69 69A optional Iridium Datalink Standby Standby Magnetic GSR ES Altimeter Airspeed Compass optional required Radar Altimeter optional Figure 6 System Block Diagram RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 23 of 24 DEFINITIONS The following terminology is used within this 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 HDG Heading HSI Horizontal Situation Indicator ILS Instrument Landing System LDA Localizer Directional Aid LOC Localizer LOC BC Localizer Backcourse Multi Function Display PFD Primary Flight Display SD Secure Digital SDF Simplified Directional Facility SVT Synthetic Vision Technology TAS Traffic Awareness System TIS Traffic Information Service VFR Visual Flight Rules Visual Meteorological Conditions
4. MFD screen but more detailed information is available on the AUX pages Internal database validation prevents incorrect data from being displayed 190 01150 12 Rev B Garmin G500H as installed in Bell 206A Page 20 of 24 FAA APPROVED 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 RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 21 of 24 SYSTEM DESCRIPTION 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 Pitot Static System The pitot static system supplies pitot static pressure to the GDC 74H standby altimeter and standby airspeed indicator 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 22 of 24 FAA APPROVED System Block Diagram G500H Avionics System Magnetometer Equipment Installed per this STC GMU 44 I I GDU 620 PFD MFD AHRS GRS 77H Air Data Computer GDC 74H p Temperature Probe GTP 59 Audio Panel No 1
5. 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 near the poles but this will not affect the GPS track RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 7 of 24 2 6 AHRS Operation The GRS 77 AHRS used in the G500H uses GPS data air data and magnetometer inputs to improve availability The GRS 77 will operate in reversionary modes that do not require these inputs 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 2 7 Maximum Airspeed The airspeed markings on the G500H PFD match those on the standby indicator regardless of operating altitude 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 2 8 Navigation Angle The GDU 620 Navigation Angle can be set to either 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 the GNS navigators 2 Course Pointer Auto Slewing The G500H HSI will auto slew i e automatically rotate the GPS course pointer to the desired course defined by each GPS leg The system will al
6. 2 45 Equipment Requirements Table 1 3 below lists the minimum fully functional G500H System Elements required for VFR flight operations Equipment Number VFR installed Primary Multi Flight Display 1 0 Attitude Heading Unit AHRS 1 0 Air data computer ADC 1 0 Magnetometer GMU 1 0 Standby Altimeter 1 1 Standby Airspeed 1 1 Magnetic Compass 1 1 GIN 6XX GTN TXX GNS 400W 1 0 500W or 480 series navigator Table 1 3 G500H Equipment Requirements 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 10 of 24 FAA APPROVED Section 3 OPERATING PROCEDURES Refer to the Garmin G500H PFD MFD System Cockpit Reference Guide P N 190 01150 03 or G500H Pilot s Guide P N 190 01150 02 for detailed operating procedures This includes all Primary Flight Display and Multi Function Display information Although intuitive and user friendly the G500H PFD MFD System requires a reasonable degree of familiarity to avoid becoming too engrossed at the expense of situational awareness Pilots should take full advantage of training tools to enhance familiarity with the G500H system 31 NORMAL PROCEDURES 3 1 1 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 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 funct
7. 4 FAA APPROVED 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 that are within the depicted synthetic terrain field of view e Flight Path Marker FPM an indication of the current lateral and vertical path of the aircraft The FPM is displayed when synthetic terrain is selected for display and ground speed is more than 30 knots 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 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 out the windshield in front of the pilot Terrain features outside the field of view are not shown on the display Th
8. ED 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 press and release 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 will display the main map page on the MED Details of the functions available on the MFD are explained in the Garmin G500H Cockpit Reference Guide defined in Paragraph 1 1 3 1 3 Helicopter Synthetic Vision Technology HSVT 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 3 1 4 HSVT Terrain When the G500H has SVT enabled aural and visual terrain and obstacle alerting will be provided by the Terrain HSVT function of the G500H system Terrain HSVT modes normal RP and inhibit can be selected via softkey on the Terrain page on the G500H MFD 3 1 5 Altitude Alerter The Altitude Bug Setting will flash when approaching within 1000 feet of the selected altitude
9. FD 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 RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 13 of 24 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 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 2 7 Synthetic Vision 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 aircr
10. Garmin International Inc 1200 E 151 Street Olathe Kansas 66062 USA FAA APPROVED ROTORCRAFT FLIGHT MANUAL SUPPLEMENT Garmin G500H as installed in Bell 206A Registration Number Serial Number This supplement shall be attached to the Bell 206A Rotorcraft Flight Manual when the Garmin G500H Flight Display System has been installed in accordance with STC SR02295LA information contained herein supplements or supersedes the basic Rotorcraft Flight Manual only in those areas listed herein For limitations procedures and performance information not contained in this document consult the basic FAA approved Rotorcraft Flight Manual FAA Approved By Hide ale Michael Warren ODA STC Unit Administrator GARMIN International Inc ODA 240087 CE pate 79 20 4 RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 1 of 24 5 2010 November 14 2014 ll 5 LOG OF REVISIONS ONE reper ere Revision Date No Description FAA Approved Number A Origina 1 B Complete Supplement Jousef Mgr Fit Test Br ANM 160L Federal Aviation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate Date May 5 2010 Table 1 1 GDU software was 4 00 GRS 77H software was 3 50 GDC 74H software was 3 06 Table 1 2 Added GTN 6XX and 7XX along with note 1 14 Added Ra
11. ISPLAY ccceesessscecececeessseeececeesenssaeeeeeeeees 9 2 13 TRAFFIC DISPLAY neret ti aces sense 9 2 14 RADAR ALTIMETER DISPLAY emen nennen nennen 9 2 15 EQUIPMENT REQUIREMENTS cessere nennen nennen 10 SECTION 3 OPERATING PROCEDURES e eere seen ee ette seen nessuno 11 3 1 NORMAL PROCEDURES seen 11 3 1 1 PFD Knob amp PFD Soft Keys eene 11 3 1 2 MFD Knobs amp Soft Keys esee 12 3 1 3 Helicopter Synthetic Vision Technology HSVT 12 3 1 4 HSVI 12 3 1 5 Altitude Alerter oss aee a e onm 12 3 2 EMERGENCY PROCEDURES cernere 12 3 2 1 Loss of Electrical Power eene 12 3 2 2 Primary Flight Display esee 12 3 2 3 erret ee eh UH 13 3 2 4 Heading see eto n deed 13 3 2 5 Air Data Computer ADC Failure esee 13 3 2 6 AUTE 13 3 2 7 Synthetic VISION ss dS ERU EI 14 3 2 8 Display Dimming esee etr eere ER de tens 14 3 2 9 Warnings Cautions and Advisory Annunciations 14 SECTION 4 PERFORMANCE DATA sccssscssssscssscsssscssscsssessssssssesessces 16 GENERAL INFORMATION scccsscsssscsssscsssscsssssssscsssesssscssssssssssssnsssssssees 17 GARMIN G500H FLIGHT DISPLAY SYSTEM cccsesssecececeesesssaeceeecenenssaeeeeees 17
12. R ONLY operations in accordance with 14 Code of Federal Regulations Part 91 and Part 135 2 2 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 2 3 System Software Requirements The G500H must utilize the following approved software versions Component Identification Software Version npe or later FAA approved GRS 77H 3 52 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 Component Identification Software Version or later FAA approved GNS 400W Series GPS WAAS NAV 3 30 GNS 500W Series GPS WAAS NAV 3 30 GNS 480 CNX80 GPS WAAS NAV 2 2 GTN 6XX Series GPS WAAS NAV 4 00 GTN 7XX Series GPS WAAS NAV 4 00 Table 1 2 GNS Navigator Required Software Versions 2 4 Databases 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 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
13. SYSTEM POWERS OURGES e bett voee eie te cutee teed 17 NAVIGATION SOURCES csssessscccecccsessnseaececccscsensnaececececsessaaececeesesessnaeaeeececs 18 HELICOPTER SYNTHETIC VISION TECHNOLOGY OPTIONAL 18 P AUBONUDE 19 INTERFACED nennen esse inert nennen nna 19 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 4 of 24 FAA APPROVED Traffic Display and Control esee 20 XM Data link Optional cte eR e ea pte dee ertet 20 Video Input Optional cesses eterne nennen rennes 20 Iridium Data link Optional eee 20 Radar Altimeter Optional eese eerte 20 GTN 6XX or 7XX Series Navigator eseeeseeeeeeeeeeee mene 20 GNS 400W 500W Series Navigator eee 20 DATABASE CARDS e iren pre e DERE RERO reet RE Reese 20 SYSTEM DESCRIPTION 5 trt reet rr SPERA 22 Pitot St tic S ystem zs ase Rees ee Rete ess UNUM 22 SYSTEM BLOCK nennen rennen eerte nee tenete 23 DEPFINITIONS eae hhesHecepc reme eB RB 24 RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 5 of 24 Section 2 OPERATING LIMITATIONS 21 Types of Operation Rotorcraft equipped with the G500H Avionics Display System are limited to VF
14. a red X through the altimeter display VERT SPD FAIL Cross check instruments Display system is not receiving vertical speed input from the air data computer accompanied by a red X through the vertical speed display HDG Use Standby Magnetic Compass or GPS track information Display system is not receiving valid heading input from the AHRS accompanied by a red X through the digital heading display Red X Reference the data source or alternate equipment A red X through any display field indicates that display field is not receiving data or is corrupted TERRAIN Visually acquire the terrain and avoid SVT Terrain has determined that nearby terrain poses a collision hazard OBSTACLE Visually acquire the obstacle and avoid SVT Terrain has determined that a nearby obstacle poses a collision hazard RFMS Garmin G500H as installed in Bell 206A FAA APPROVED Table 1 Warning Annunciations Red 190 01150 12 Rev B Page 15 of 24 Pilot Action Cause AHRS Aligning Limit rotorcraft bank to less than 10 degrees as Attitude and Heading Reference System is aligning Keep attitude level using Keep Wings Level AHRS Aligns outside references AHRS will not align if bank angle remains over 10 degrees If the system is GPS data on the selected system is no NO GPS 5 POSITION configured with dual longer va
15. aft and terrain shown on the SVT display the display of synthetic vision should be manually turned off using the procedure in section 2 1 3 of this flight manual supplement 3 2 8 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 The display will return to full brightness when operating temperatures are reduced 3 2 9 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 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 14 of 24 FAA APPROVED The 500 Cockpit Reference Guide and G500H Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories Annunciation Pilot Action Cause ATTITUDE FAIL AIRSPEED FAIL Use visual references Use Standby Airspeed Display system is 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 ALTITUDE FAIL Use Standby Altitude Display system is not receiving altitude input from the air data computer accompanied by
16. and an audio tone is played when approaching or deviating within 200 feet of the selected altitude 3 2 EMERGENCY 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 2 1 Loss of Electrical Power In the event of a total loss of electrical power the G500H system will cease to operate and the pilot must utilize the standby instruments and visual references to fly the aircraft Primary Flight Display 3 22 Primary Flight Display If primary flight information Heading Altitude or Airspeed on the PFD is not available or appears invalid utilize the standby instruments installed as required 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 12 of 24 FAA APPROVED 3 2 3 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 over the attitude indicator and a yellow AHRS FAILURE shown on the PFD A heading failure will also be indicated 1 Use visual references for aircraft control 2 Setcourse datum using CRS selection of the PFD knob The Attitude Heading and Reference System AHRS requires at least one GPS or data input to function properly In the unlikely event that GPS data and air data is not received by the AHRS the syst
17. dar Altimeter Display Table 1 3 Added GTN 6XX and GTN 7XX Added to Interfaced Equipment Radar Altimeter and GTN 6XX 7XX Series Navigator See page 1 Added Radar Altimeter 190 01150 12 Rev B Page 2 of 24 RFMS Garmin G500H as installed in Bell 206A FAA APPROVED LOG OF REVISIONS eee eee Revision Date No Description FAA Approved Number 23 Updated Figure 6 RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 3 of 24 Table of Contents SECTION 2 OPERATING LIMITATIONS 6 2 1 TYPES OF OPERATION enne enne etn nest nete nnne ene 6 2 2 COCKPIT REFERENCE amp PILOT S GUIDES eee 6 23 SYSTEM SOFTWARE REQUIREMENTS eese eene enne nnns 6 24 Ee eI NE APERIRE E P EXE Rabe VPE 6 2 5 AHRS OPERATIONAL AREA eere eene nennen nennen ene 7 2 6 irren Here YER erroe iter e e Ee 8 2 MAXIMUM AIRSPEED a rear nennen ena 8 2 8 NAVIGATION ANGLE tirer PEE aee ete e 8 2 9 COURSE POINTER AUTO SLEWING ccccsesseceeeceesesseeceeeceesenssaeeeeeeeees 8 2 10 HELICOPTER SYNTHETIC VISION TECHNOLOGY HSVT 8 2 11 TERRAIN AND OBSTACLE DISPLAY ccscsscscccceceesessececececeesenssaeeeeeeeenes 8 2 12 DATALINKED WEATHER D
18. e not equivalent to warnings provided by HTAWS 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 8 of 24 FAA APPROVED 2 12 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 213 Traffic Display Traffic may be displayed on the G500H System from TIS or TAS systems These systems are capable of providing traffic monitoring and alerting to the pilot Traffic shown on the display may or may not have traffic alerting available The display of traffic is an aid to visual acquisition and is 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 TAS 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 2 14 Radar Altimeter Display Precise Above Ground Level AGL altitude information may be displayed on the G500H System from supported radar altimeters RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 9 of 24
19. e 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 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 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 TIS Traffic TAS Traffic GDL 69 XM Data link Video GSR 56 Iridium Data link Radar Altimeter RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 19 of 24 GTN 6XX or 7XX Series Navigator 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 is displayed on and controlled through the XM Data link Optional The G500H Avionics Display System can display weather data from a Garmin GDL69 or GDL69A XM satellite receiver Graphical and textual weather information is displayed on and con
20. em 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 32 4 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 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 a traditional CDI with the Omni Bearing Selector being adjusted by the PFD knob set to CRS Under this condition the pilot must use the standby compass 3 2 5 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 and Altimeter visual references and secondary cues 3 2 6 Navigation If navigation information on the P
21. ion 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 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 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 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 Flight 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 RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 11 of 24 3 1 2 MED Knobs amp Soft Keys The MFD controls are adjacent to and beneath the M
22. lid The Moving Map and GPS press the 1 2 button associated data are not updating Visually acquire the The configured traffic system has TRAFFIC ae aed determined that nearby traffic may be a traffic to see and avoid threat to the aircraft Use vigilance as the The configured traffic system is not able No Traffic Data traffic sensor is not able to detect traffic and or provide the to detect traffic pilot with any traffic awareness TERRAIN Visually acquire the SVT Terrain has determined that nearby terrain and avoid terrain may pose a collision hazard Visually acquire the SVT Terrain has determined that a OBSTACLE Nace nearby obstacle may pose a collision obstacle and avoid hazard Table 2 Caution Annunciations Yellow Annunciation Pilot Action Various Alert Messages may appear under the ALERTS soft key or service action View and understand all advisory messages Typically they indicate communication issues within the G500H System Refer to the G500H Cockpit Reference for appropriate pilot Table 3 Advisories White Section 4 PERFORMANCE DATA No change 190 01150 12 Rev B Page 16 of 24 RFMS Garmin G500H as installed in Bell 206A FAA APPROVED 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 Compu
23. s follows RFMS Garmin G500H as installed in Bell 206A 190 01150 12 Rev B FAA APPROVED Page 17 of 24 Label Unit Controlled PFD Garmin Display Unit PFD MFD GDU 620 AHRS Attitude and Heading Reference System GRS 77H ADC Air Data Computer GDC 74H 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 VLOC 2 Helicopter Synthetic Vision Technology 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 1708 Figure 5 Typical HSVT Display HSVT provides additional features on the G500H primary flight display PFD which include the following information 190 01150 12 Rev B RFMS Garmin G500H as installed in Bell 206A Page 18 of 2
24. so 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 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 10 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 traffic avoidance is prohibited 2 41 Terrain and Obstacle Display Terrain elevation information can be selected for display on the MFD as red orange yellow green and black tiles Obstacles are displayed in red yellow and gray towers obstacles The information is depicted for advisory purposes only and is not to be used for aircraft maneuvers or navigation Terrain HSVT alerts ar
25. ter GDC 74H ADC and Attitude and Heading Reference Systems GRS 77H AHRS The G500H interfaces with a Garmin GNS 400W 500W or 480 series GPS WAAS navigator and an audio panel Optionally the G500H may interface with other systems installed in the rotorcraft including a Garmin GTX330 transponder TAS traffic system GDL 69 A satellite data link video sources and GSR 56 Iridium data link 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 display supplemental data including mapping terrain video charts and flight plan information E 1 A i I Figure 4 GDU 620 Displays 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 GSOOH are circuit breaker protected with reset able type circuit breaker available to the pilot These breakers are located on the overhead circuit breaker panel and are labeled a
26. trolled through the If the G500H is 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 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 Radar Altimeter Optional The G500H system can display radar altitude information Radar altitude minimums alerting are controlled through the MFD GTN 6XX or 7XX Series Navigator The G500H requires an approved navigator such as a GTN 6XX or 7XX series navigator The G500H can display annunciations received from the GTNs GNS 400W or 500W Series Navigator The G500H requires an approved navigator such as a GNS 400W or 500W series navigator The G500H can display annunciations received from the GNSs Database Cards 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
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