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Garmin AS_350B2/B3 Rotorcraft Flight Manual Supplement
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1. Placards EE EE OE 16 SECTION 3 EMERGENCY PROCEDURES neeese 17 RFMS Eurocopter AS350B2 B3 G500H System FAA APPROVED 190 00792 13 Rev 1 Page 3 of 25 3 1 Loss of Electrical POWET ee ese ee ee ee ee ee ee ee 17 3 2 Malfunction Indications and Procedure iss ss 17 SECTION 4 NORMAL PROCEDURES ee see see se ee se ee ee ee sees see 22 41 PED Knob amp PFD Soft Keys ese eee 22 42 MED Knobs amp MFD Soft Keys 22 4 3 Helicopter Synthetic Vision Technology HSVT 23 AA HSVT Terrain sesse see gese EVER Gee Deed SEE REEDE De Se GEUR EE 23 AS Alatude Alerter issie SR Ee Ee SR Ee FREE EA Res Se Ee Ee 23 SECTION 5 PERFORMANCE soseer Shigutsauvbines DE Gee R 24 SECTION 6 WEIGHT AND BALANCE 1 see se ee see se ee se ee see 25 TABLE OF FIGURES Figure 1 1 GDU 620 PFD MFD DisplayS esse sesse see see ee ee see see ee 5 Figure 1 2 Typical HSVT Display iese esse esse esse se se see ee ee ee ee ee 7 Figure 1 3 G500H Flight Display System Block Diagram 11 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 4 of 25 FAA APPROVED SECTION 1 GENERAL 1 1 System Description 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 and Attitude and Heading Reference Systems GRS 77H AHRS The G500H interfaces with a Garmin GNS 400W 500W or 480 s
2. 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 Equipment Requirements Table 2 3 lists the minimum fully functional G500H System Elements required for VFR flight operations RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 15 of 25 Table 2 3 Equipment Requirements Equipment a VFR Primary Multi Flight Display 1 0 Attitude Heading Unit AHRS 1 0 Air Data Computer ADC 1 0 Magnetometer 1 0 Standby Altimeter 1 1 Standby Airspeed 1 1 Magnetic Compass 1 1 GNS 400W 500W or 480 series navigator 1 0 2 15 Placards If NAV 2 system is not compatible with GSOOH NAV 2 must be labeled NAV 2 NOT DISPLAYED ON THE G500H unless otherwise displayed on a separate unit 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 16 of 25 FAA APPROV
3. 3 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 18 of 25 FAA APPROVED 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 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 RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 19 of 25 Table 3 1 Warning Annunciations Red Annunciation Pilot Action Cause Display system is not receiving ATTITUDE Use visual attitude reference information from the AHRS accompanied by the FAIL references removal of sky ground presentation and a red X over the attitude area Display system is not receiving AIRSPEED FAIL Use Standby airspeed input from the air data Airspeed computer accompanied by a red X through the airspeed display Display system is not receiving ALTITUDE Use Standby altitude input from the air data FAIL Altitude computer accompanied by a red X through the altimeter display Display system is not receiving vertical spe
4. ED SECTION 3 EMERGENCY PROCEDURES 3 1 Loss of Electrical Power In th e 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 3 2 Malfunction Indications and 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 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 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 Set course datum using CRS selection of the PFD knob The Attitude Heading and Reference System AHRS requires at least one GPS or air data input to function properly In the unlikely event that GPS data and air data is not received by the AHRS the system will not provide Attitude Heading Altitude or Airspeed information however if the PFD is receiving valid GPS information the reversionary data on the PFD provid
5. Garmin International Inc 1200 E 151st Street Olathe Kansas 66062 USA FAA APPROVED ROTORGRAFT FLIGHT MANUAL SUPPLEMENT for Eurocopter Model AS 350 B2 B3 with Garmin GS00H System Registration Number Serial Number This supplement shall be attached to the Eurocopter AS 350 B2 B3 Rotorcraft Flight Manual when the Garmin G500H Flight Display System has been installed in ascordance with STC No SRO9575RC The Information contained herein supplements or supersedes the basic Rotorcraft Flight Manwal only in those areas listed herein For limitations procedures and perfovmance information not contained in this document consult the basic Rotorcraft Flight Manual FAA Approved By Michael wa en ODA STC Unit Administrator CLARMIN International Inc ODA 240087 CE Date May Ed ZOTY RFMS Eurocopter A 350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 1 of 25 LOG OF REVISIONS EE eel NEE N Revision Date Number Description FAA Approved Number 05 05 2014 Complete Supplement See page 1 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 2 of 25 FAA APPROVED TABLE OF CONTENTS SECTION 1 GENERAL joe ie sesse SE ESE cases stesdstssstetenees 1 1 System Description esse ses see see ee ee 1 2 System Power Sources see see ee ee 1 3 Navigation Sources eee see ee ee 1 4 Helicopter Synthetic Vision Technology Optional 6 1 5 Audio Panel ii ese GEE Arise EES EE
6. able 1 1 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 1 3 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 IF NAV 2 source is compatible with G500H In addition the HSI can display two simultaneous bearing pointers sourced from GPS 1 GPS 2 VLOC 1 VLOC 2 1 4 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 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 6 of 25 FAA APPROVED purpose of the HSVT 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 in Figure 1 2 Figure 1 2 Typical HSVT Display HSVT provides additional features on the G500H primary flight display PFD which include the following information e Synthetic Terrain an artificial database derived thre
7. ach 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 The unaided use of the synthetic vision display for aircraft control navigation or obstacle terrain traffic avoidance without reference to G500H primary flight instruments and or the aircraft standby instruments is prohibited 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 14 of 25 FAA APPROVED 2 11 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 The information is depicted for advisory purposes only and is not to be used for aircraft maneuvers or navigation Terrain HSVT alerts are not equivalent to warnings provided by HTAWS 2 12 Datalinked Weather Display XM weather data is provided by an optional GDL 69 or GSR 56 interface The weather information display on the MFD of the G500 is limited to supplemental use only and may not be used in lieu of an official weather data source 2 13 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
8. 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 applicable software versions found in table 2 2 Table 2 2 GNS Navigator Required Software Version 190 00792 13 Rev 1 Page 12 of 25 Software Version Component Identification 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 RFMS Eurocopter AS350B2 B3 G500H System FAA APPROVED 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 Coverage of the obstacle database includes the United States and Europe This database is updated on a 56 day cycle The Garmin SafeTaxi database contains detailed airport diagrams for selected airports These diagrams aid in following 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 FliteChar
9. agnetometer 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 9 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 also auto slew the VHF NAV course pointer when the CDI transitions to a LOC setting if an ILS LOC LOC BC LDA or SDF approach is activated in the GPS WAAS navigator The VHF NAV green course pointer will only auto slew if the approach is active in the navigator the LOC frequency is loaded in the active NAV frequency and then the HSI source is changed to the corresponding VHF NAV for the approach Back Course approaches will auto slew to the reciprocal course The system is not capable of automatically setting the inbound VHF NAV course pointer if an appro
10. doe Eb SE 8 1 6 Interfaced Equipment sees see se ee ee ee ee Se ee 8 1 7 Traffic Display and Control Optional 0 00 9 1 8 XM Data link Optional iese esse se ee ee ee ee RR ee 9 1 9 Video Input Optional sees see se ee ee ee ee Ge ee 9 1 10 Iridium Data link Optional 0 0 ee se es ee GR ee 9 1 11 Radar Altimeter Optional iese ese ee se ee ee GR ee 9 1 2 Database Cards is EE vtec ee a Eg Se 10 1 13 System Description ses se se ee ee ee ee ee ee 10 1 14 Pitot Static SYSTEM see eee ee ee ee ee ee ee 10 SECTION 2 LIMITATIONS e esse sees se ese ee ee Ge ee ee ee ee be ee 12 2 1 Types of Operation 0 eee se ee ee ee ee se ee ee 12 2 2 Cockpit Reference amp Pilots Guides se see 12 2 3 System Software Requirements iese sesse ee ee ee 12 24 vi SE EE ER EE aE 13 2 5 AHRS Operational Area esse see see see se ee ee ee ee 13 2 0 AHRS Operat oii ee 1 Ri bation ia were RE Se eg Se 13 2 7 Maximum Airspeed ees ee ee ee ee ee ee ee ge 14 2 8 Navigation Angle eee ee ee ee ee ee se ee ee 14 2 9 Course Pointer Auto Slewing sesse see see see se ee ee 14 2 10 Helicopter Synthetic Vision Technology HSVT 14 2 11 Terrain and Obstacle Display 0 0 0 see se ee ee ee see 15 2 12 Datalinked Weather Display sees see se ee ee ee se 15 2 13 Traffic Display siese EES EER EES ER GR ERGE ERG ER Ee ee NEGE Bee EDE ESE 15 2 14 Equipment Requirements ses see see se ee ee ee 15 219
11. e 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 RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 7 of 25 e Obstacles obstacles such as towers including buildings 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 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 th
12. e 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 base decisions and plan maneuvers to avoid terrain or obstacles The synthetic vision elements are not intended to be used for primary aircraft control in place of the primary flight instruments 1 5 Audio Panel The G500H Flight Display System is interfaced with the audio panel installed in the rotorcraft to provide aural altering generated by the GSOOH 1 6 Interfaced Equipment The G500H Flight Display System is designed to interface with other avionics systems including TIS Traffic TAS Traffic GDL 69 XM Data link 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 8 of 25 FAA APPROVED Video GSR 56 Iridium Data link GNS 400W or 500W Series Navigator Radar Altimeter System 1 7 Traffic Display and Control Optional The G500H Flight 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 MFD 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 When TAS traffic is installed TIS
13. e 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 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 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 aircraft and terrain shown on the SVT display the display of synthetic vision should be manually turned off using the procedure in section 4 3 of this flight manual supplement 190 00792 1
14. ed VERT SPD FAIL Cross check input from the air data instruments computer accompanied by a red X through the vertical speed display Use Standby Display system is not receiving HDG Magnetic Compass valid heading from the AHRS or GPS track accompanied by a red X through information the digital heading display Reference the data A red X through any display field Red X source or alternate indicated that display field is not equipment receiving data or is corrupted Visually acauire the SVT Terrain has determined that a TERRAIN oe nearby terrain poses a collision terrain and avoid hazard EET N SVT Terrain has determined that a OBSTACLE y acquire nearby obstacle poses a collision obstacle and avoid Ed 190 00792 13 Rev 1 Page 20 of 25 RFMS Eurocopter AS350B2 B3 G500H System FAA APPROVED Table 3 2 Caution Annunciations Yellow Annunciation Pilot Action Cause Attitude and Heading Reference System is aligning Keep attitude level using outside references AHRS will not align if bank angle remains over 10 Limit rotorcraft bank to less than 10 degrees as AHRS Aligns AHRS Aligning Keep Wings Level degrees If the system is GPS data on the selected NO GPS configured with dual system is no longer valid The POSITION GPS press the 1 2 Moving Map and associated button data are not updating The configured traffic system has determined that nearby traffic may be a threat to the aircraft Visual
15. el No 1 GPS WAAS Navigator Various models and or VOR Localizer GS GNS 400W 500W series or GNS 480 askie Traffic Various Models optional No 2 GPS WAAS Navigator and or VOR Localizer GS GNS 400W 500W series Weather Data Link GNS 480 or SL30 GDL 69 optional optional XM Entertainment GDL 69 69A optional Iridium Datalink Standby Standby Magnetic GSR a Altimeter Airspeed Compass optional required Radar Altimeter Various Models optional Figure 1 3 G500H Flight Display System Block Diagram RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 11 of 25 SECTION 2 LIMITATIONS 2 1 Types of Operation Rotorcraft equipped with the G500H Flight Display System are limited to VFR ONLY operations in accordance with Title 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 found in table 2 1 Table 2 1 G500H Software Versions Software Version Component Identification or later FAA approved GDU 620 PFD MFD 5 00 GRS 77H AHRS 3 51 GDC 74H Air Data Computer 3 06 GMU 44 Magnetometer 2 05 In
16. eries 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 radar altimeter 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 Figure 1 1 GDU 620 PFD MFD Displays RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 5 of 25 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 1 2 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 push pull type circuit breakers available to the pilot These breakers are located in the pedestal 30 o circuit breaker panel and are labeled as shown in Table 1 1 T
17. es GPS Track and GPS Altitude data along with course information and deviations which are still valid and may be used to navigate 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 RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 17 of 25 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 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 Navigation If navigation information on the PFD MFD HSI RMI WPT bearing and distance information or Moving Map Data is not availabl
18. g tools to enhance familiarity with the GSOOH system 4 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 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 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 BRG 1 and BRG 2 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 c
19. 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 MED 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 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 1 13 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 1 14 Pitot Static System The pitot static system supplies pitot static pressure to the GDC 74H standby altimeter and standby airspeed indicator 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 10 of 25 FAA APPROVED G500H Avionics System Magnetometer Equipment Installed per this STC GMU 44 TT AHRS GRS 77H I GDU 620 PFD MFD Air Data Computer GDC 74H m lt Temperature Probe GTP 59 j Audio Pan
20. ly acquire the TRAFFIC traffic to see and avoid The configured traffic system is not able to detect traffic and or provide the pilot with any traffic awareness Use vigilance as the No Traffic Data traffic sensor is not able to detect traffic Visually acquire the SVT Terrain has determined TERRAIN A that nearby terrain may pose a terrain and avoid EA collision hazard Visually acquire the SVT Terrain has determined OBSTACLE N na that a nearby obstacle may pose obstacle and avoid Sa a collision hazard Table 3 3 Advisories White Annunciation Pilot Action View and understand all advisory messages Typically that indicates Various Alert Messages may appear communication issues within the under the MFD ALERTS soft key G500H System Refer to the G500H Cockpit Reference for the appropriate pilot or service action RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 21 of 25 SECTION 4 NORMAL PROCEDURES Refer to the Garmin G500H PFD MFD System Cockpit Reference Guide P N 19001150 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 GSOOH 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 trainin
21. must be disabled 1 8 XM Data link Optional The G500H Flight 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 interfaced to a Garmin GDL 69A XM satellite receiver then control of audio entertainment can be performed through the MFD 1 9 Video Input Optional The G500H Flight 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 GSOOH 1 10 Iridium Data link Optional The G500H Flight 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 Datalink weather is also available via the Garmin GSR 56 Iridium Transceiver The control and display of Iridium satellite weather on the MFD is similar to XM weather 1 11 Radar Altimeter Optional The G500H supports the display of radar altitude on the PFD from supported radar altimeters Radar altitude minimums alerting can be controlled through the MFD RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 9 of 25 1 12 Database Cards The G500H utilizes several databases Database titles display in yellow if expired or
22. nd visual terrain and obstacle alerting will be provided by the Terrain HSVT function of the GSOOH system Terrain HSVT modes normal RP and inhibit can be selected via softkey on the Terrain page on the GSOOH MED 4 5 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 RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 23 of 25 SECTION 5 PERFORMANCE No Change from Basic Flight Manual 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 24 of 25 FAA APPROVED SECTION 6 WEIGHT AND BALANCE No Change from the Basic Flight Manual RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 25 of 25
23. ontrol 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 4 2 MFD Knobs amp MED Soft Keys The MED controls are adjacent to and beneath the MED 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 190 00792 13 Rev 1 RFMS Eurocopter AS350B2 B3 G500H System Page 22 of 25 FAA APPROVED 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 MFD Details of the functions available on the MFD are explained in the Garmin G500H Cockpit Reference Guide defined in Paragraph 1 1 4 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 4 4 HSVT Terrain When the G500H has SVT enabled aural a
24. ts 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 77H 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 near the poles but this will not affect the GPS track 2 6 AHRS Operation The GRS 77H AHRS uses GPS data air data and magnetometer inputs to improve availability The GRS 77H will operate in reversionary modes that do not require these inputs RFMS Eurocopter AS350B2 B3 G500H System 190 00792 13 Rev 1 FAA APPROVED Page 13 of 25 When operating in no magnetometer or no m
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