Garmin STC for Bell 206/407 Rotorcraft Flight Manual Supplement
Contents
1. 190 01150 68 Rev A FAA APPROVED DATE February 25 2011 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT STC SRO2295LA GARMIN G500H Bell 206L 4 Various models Audio Panel Page 26 of 28 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 document ROTORCRAFT FLIGHT MANUAL SUPPLEMENT STC SR02295LA GARMIN G500H Bell 206L 4 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 simplified Directional Facility TAS Traffic Awareness System TIS Traffic Information Service 190 01150 68 Rev A FAA APPROVED DATE February 25 2011 Page 27 of 28 GARMIN Ltd or its Subsidiaries c o Garmin International 1200 E 151 Street Olathe KS 66062 USA VFR Visual Flight Rules VMC Visual Meteorological Conditions V S Vertical Speed WAAS Wide Area Augmentation System 190 01152. 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 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 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 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 190 01150 68 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 SR02295LA GARMIN G500H Bell 206L 4 BRGI 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 aircr
3. 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 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 68 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 SRO2295LA GARMIN G500H Bell 206L 4 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 temper
4. navigator Table 1 3 G500H Equipment Requirements 190 01 150 68 Rev A Page 7 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 206L 4 Section 2 NORMAL PROCEDURES 2 Preflight Databases Verify current MFD system startup page 2 2 Before Takeoff MED Press Enter key Data fields on the PFD Verify valid and normal System Messages Considered 190 01150 68 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 206L 4 Section 3 EMERGENCY 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 Primary Flight Display Malfunction Primary flight information Heading Altitude or Airspeed on the PFD not availa
5. advisory messages Typically may appear under the they indicate communication issues within the G500H MFD ALERTS soft System Refer to the G500H Cockpit Reference for key appropriate pilot or service action Table 3 3 Advisories White 190 01150 68 Rev A Page 14 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 Section 4 PERFORMANCE No change Section 5 WEIGHT AND BALANCE Reference most current aircraft weight and balance 190 01150 68 Rev A FAA APPROVED DATE February 25 2011 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT STC SR02295LA GARMIN G500H Bell 206L 4 Page 15 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 206L 4 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 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 vid
6. database includes the United States and Europe Detailed 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 i 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
7. is prohibited 1 10 Terrain and Obstacle Display Terrain and obstacle information is depicted for advisory purposes only and is not to be used for aircraft maneuvers or navigation 190 01150 68 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 206L 4 1 11 Traffic Display 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 softkevs 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 on Ses Primary Multi Function Display Attitude Heading Ref System AHRS Air Data Computer eee Mapememrgewmuy 8 h 8 ee Smg Anes 4 yq v p w uw AME 3 3 23 we 1 159 19 GNS 400W 500W or 480 series iani l
8. 0 68 Rev A FAA APPROVED DATE February 25 201 ROTORCRAFT FLIGHT MANUAL SUPPLEMENT STC SR02295LA GARMIN G500H Bell 206L 4 Page 28 of 28
9. ALFUNCTION PROCEDDAURES 7 9 3 1 EMERGENCY PROCEDURES peno V pc RP FU Va ac c Fr Fa e PR ac 9 3 2 MALFUNCTION INDICATIONS AND PROCEDURES eene 9 SECTION S WEIGHT AND BALANCE asssoeanzsasesnzuxenAtoau skeunkX bu repo ranks e 190 01150 68 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 206L 4 GENERAL INFORMA FTO uissasisncz nzhz Eam RuEEEMk EO REESE E uL Rnbak aa 16 GARMIN G300H FLIGHT DISPLAY SYSTEM aererint rettet tttm hme 16 void OSC HL S qvos PNIS D ere 17 PRIMARY FELEIGIEI USP LAY sese rera icri aen eene moneri RE ek boire ccena WE METEIFLINCIUN DISPLAY uico tepseackoxcoekt ecu trente denn e UHR ERER e hor S ELE Miel LR Es E P IBIBIGE 12 Ae INTERFACED EQUIPMIENT 5 7 diri dria tiani disini cb i diss ca DATABASE m aa SYSTEM BLOCK DIAGRAM cecccoscca anaes TAE 26 DEPINITIONS ees S URTEGVIWOCL STEEL E A EI Ee VE E DUM E DELE VUE 27 190 01150 68 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 GARMI
10. 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 206L 4 Registration Number __ Serial Number This document serves as the Rotorcraft Flight Manual Supplement when the rotorcraft is equipped in accordance with Supplemental Type Certificate SR02295LA 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 Flight Test Branch ANM 160L Federal Aviation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate 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 206L 4 CMM OF REVISIONS a FAA Approved Number 2 25 11 Complete Supplement Original Mer FIt Test Br ANM 160L Federal Av
11. N G500H Bell 206L 4 Section 1 LIMITATIONS 1 1 Types of Operation Rotorcraft equipped with the G500H Avionics 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 3 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 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 GPS WAAS NAV 3 30 GNS 480 CNX80 GPS WAAS NAV Table 1 2 GNS Navigator Required Software Versions 190 01150 68 Rev A Page 5 of 28 FAA APPROVED DATE February 25 201 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 206L 4 1 4 Databases Coverage of the terrain database is between North 75 latitude and South 60 latitude in all longitudes Coverage of the obstacle
12. OVED 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 206L 4 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 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 is 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 dow
13. UAL SUPPLEMENT Olathe KS 66062 USA STC SR02295LA GARMIN G500H Bell 206L 4 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 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 190 01150 68 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 206L 4 PITOT STATIC SYSTEM The pitot static system supplies pitot static pressure to the GDC 74H standby altimeter and standby airspeed indicator 190 01150 68 Rev A Page 25 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 SYSTEM BLOCK DIAGRAM G500H Avionics System Equipment Installed per this STC Magnetometer GMU 44 AHRS P GRS 77H Jl ir Data Computer i GDC 74H GDU 620 PFD MFD Not 1 GPSIWAAS Navigator VOR Localizer GS _ i No 2 GPSIWAAS qoum andor VOR Localizer GS GNSS 400 ies
14. aft 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 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 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 Labs LECCE GS TRK i 5 LLLI D LIN GREC GEI in Eu 190 01150 68 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 206L 4 HSVT provides additional features on the G500H primary flight display PFD which include the following information e Synthetic Terrain an artificial database derived three dimensional view of the terrain ahead of the a
15. atures 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 control 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 GSOOH displays NOTE The G300H Cockpit Reference Guide and the G500H Pilot s Guide contain detailed descriptions of the annunciator system and all warnings cautions and advisories Annunciation Pilot Action Cause A red X through any display field Utilize alternate indicates that display field is not equipment receiving data or the data is corrupted HSVT Terrain has determined that nearby terrain poses a collision Red X Visually acquire the terrain and avoid lusti TERRAIN HSVT Terrain has determined that a VISUM BOR ESAME nearby obstacle poses a collision VPSLTACLE obstacle and avoid hazard Table 3 1 Warning Annunciations Red 190 01150 68 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 SR02295LA GARMIN G500H Bell 206L 4 Pilot Actio ATTITUDE FAIL AIRSPEED FAIL ALTITUDE FAIL VERT SPD FAIL AHRS ALIGN Keep Wings Level 190 01150 68 Rev A Use visual refer
16. ble 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 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 68 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 206L 4 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 1s 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
17. ences 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 February 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 206L 4 NO GPS POSITION TRAFFIC NO TRAFFIC DATA TRFC FAIL TER FAIL OBSTACLE WEATHER DATALINK FAILED If the system 1s configured with dua
18. eo 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 ae TRA LP 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 190 01150 68 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 206L 4 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 Label Unit Controlled P FD Garmin Display Unit PFD MFD GDU 620 AHRS Attitude and Heading Reference System GRS 77H Air Data Computer GDC 74H
19. es 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 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 textual weather information is displayed on and controlled through the MFD If the G500H is 190 01150 68 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 SR02295LA GARMIN G500H Bell 206L 4 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 rece
20. iation Administration Los Angeles Aircraft Certification Office Transport Airplane Directorate Date CA 25 z o i 190 01150 68 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 206L 4 Table of Contents SECTION E LIMITATIONS ee oe AB AA AR Ae eB ae OR A eee Oe A eee E 5 1 1 TYPES OF PE A TIBI esxspesveseui CEREREM AEX UN FEAPER CHEN EMI AEXR aiv CODOVA UR ODD RED EA 5 1 2 COCKPIT REFERENCE amp PHOT S CIUIDES ueste rer merce er RE QU ER REY a Cc eana sA 1 3 SYSTEM SOFTWARE REQUIREMENTS uccide a eaa 5 1 4 EXT UH ores iB EIE DES 6 1 5 AHRS OPERATIONAL AREA eccna A E EENET 6 1 6 AHRS OPERATION convenant 6 1 7 DAS RT RSPERBEEu n ncc aa Eee edet eco de cta doc a ocu cv cuo tuve dI edes 6 1 8 DEAWVICEAT ICON ANGE ase RENE a mE CERA ro 6 1 9 HELICOPTER SYNTHETIC VISION TECHNOLOGY HSVT eeeeeee 6 1 10 TERRAIN AND OBSTACLE DISPLAY eene Serres a ae I E Sosa 6 1 11 TRAFFIC DISPLAY ee ML ae NER P EPEE RUN Maxis oleate 7 1 12 EQUIPMENT REQUIREMENTS RRRNMMM x 7 SECTION 2 NORMAL PROCEDURES SPSS SASSER ASEE GSE KREGER EECCA EES 8 2 1 cee pessoa a E AEE eiamnnenncecieneaean 8 4 7 BEFORE ECT E cios o DNE Rru 8 SECTION 3 EMERGENCY M
21. ircraft within a field of view of approximately 25 degrees left and 25 degrees right of the aircraft heading e Obstacles obstacles such as towers 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 The position of the terrain relative to the horizon line depends on aircraft altitude 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 of the pilot Terrain features outside the field of view are not shown on the display The synthetic terrain display 1s intended to aid the pilot awareness of the terrain and obs
22. ives 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 Ihe 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 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 68 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 MAN
23. l GPS press the 1 2 button Visually acquire the traffic to see and avoid Use vigilance as the traffic sensor is not detecting traffic Use vigilance as the traffic sensor may not be able to detect traffic 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 is no longer valid The Moving Map and associated data are not updating The configured traffic system has determined that nearby traffic may bea 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 68 Rev A Page 13 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 206L 4 Annunciation Pilot Action Various Alert Messages View and understand all
24. n 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 68 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 SUPPLEMENT Olathe KS 66062 USA STC SRO2295LA GARMIN G500H Bell 206L 4 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 1s 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 o GNS 400W or 500W Series Navigator Traffic Display and Control Optional The G500H Avionics Display System can display traffic from various sourc
25. tacles 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 190 01150 68 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 206L 4 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 68 Rev A Page 20 of 28 FAA APPR
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