Garmin G500 Manual
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1-5190-01102-02 Rev. DGarmin G500 Pilot’s Guide ForewordSec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.1.5 GMU 44 The GMU 44 magnetometer senses the earth’s magnetic field. Data is sent to the GRS 77 AHRS for processing to determine aircraft magnetic heading. This unit receives power directly from the GRS 77 and communicates with the GRS 77 using a RS-485 digital interface. Figure 1-6 GMU 44 Magnetometer 1.1.6 GTX 330/330D (Optional) Figure 1-7 GTX 330/330D Mode S Transponder The GTX 330/330D is a solid-state transponder that provides Modes A, C, and S functions. The transponder provides traffic information to the display through an ARINC 429 digital interface. NOTE: GTX 33/33D can also be used to display traffic information on the GDU 620. 1.1.7 GTP 59 The GTP 59 temperature probe provides Outside Air Temperature (OAT) data to the GDC 74A. Figure 1-8 GTP 59 Temperature Probe 1.1.8 GSR 56 The GSR 56 is an Iridium® satellite transceiver that supports voice telephone calls, aircraft position reporting, and world wide weather products.
1-6Garmin G500 Pilot’s Guide190-01102-02 Rev. D Foreword Sec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.1.9 GDL 69/69A (Optional) The GDL 69/69A is an XM Satellite Radio Data Link Receiver that receives broadcast weather data. The GDL 69A is the same as the GDL 69 with the addition of an XM Satellite Radio audio entertainment receiver. Weather data and control of audio channel and volume is displayed on the MFD, via a High- Speed Data Bus (HSDB) Ethernet connection. The GDL 69A is also interfaced to an audio panel for distribution of the audio signal. A subscription to the XM Satellite Radio service is required to enable the GDL 69/69A capability. Figure 1-9 GDL 69/69A XM Satellite Radio Data Link Receiver 1.1.10 GAD 43 (Optional) The GAD 43 is an adapter that converts AHRS digital pitch, roll, heading and yaw rate data into analog signals used by autopilot systems. The GAD 43 is installed remotely between the AHRS and an existing autopilot. The analog signals from the GAD 43 mimic those of spinning-mass gyros that provide attitude data to the autopilot and allow the gyro to be replaced by the AHRS and GAD 43 combination. Figure 1-10 GAD 43 AHRS Adapter
1-7190-01102-02 Rev. DGarmin G500 Pilot’s Guide ForewordSec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.1.11 Weather Radar The Garmin GWX system, or selected 3rd party radar, provides airborne weather and ground mapped radar data to the MFD. Figure 1-11 GWX 68 Weather Radar 1.1.12 Garmin Navigator Interface The G500 system requires connection to at least one external Garmin WAAS GPS navigator, such as the 400W/500W series or GNS 480. 1.1.13 Attitude Heading Reference System (AHRS) NOTE: Aggressive maneuvering while AHRS is not operating in normal mode may degrade AHRS accuracy. Attitude and heading information is displayed on the PFD when the AHRS receives appropriate combinations of information from the external sensor inputs. AHRS InputsAHRS Mode AHRS Outputs GPSMagnetometerAir DataAttitudeHeading Available Available —Normal Available Available Available Unavailable AvailableNo MagAvailable GPS Track Available Unavailable UnavailableNo Air/ No Mag Available GPS Track Unavailable AvailableAvailableNo GPSAvailable Available Unavailable AvailableUnavailable FailUnavailable Unavailable Unavailable Unavailable —FailUnavailable Unavailable Table 1-1 AHRS Operation
1-8Garmin G500 Pilot’s Guide190-01102-02 Rev. D Foreword Sec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index AHRS Normal Operation Heading Invalid AHRS No-GPS Mode Altitude/Heading Invalid Figure 1-12 AHRS Operation Loss of GPS, magnetometer , or air data inputs is communicated to the pilot by message advisory alerts (refer to Section 6 for specific AHRS alert information). Any failure of the internal AHRS inertial sensors results in loss of attitude and heading information (indicated by red “X” flags over the corresponding flight instruments). A maximum of two GPS inputs are provided to the AHRS. If GPS information from one of the inputs fails, the AHRS uses the remaining GPS input and an alert message is issued to inform the pilot. If both GPS inputs fail, the AHRS will continue to provide attitude and heading information to the PFD as long as magnetometer and airspeed data are available and valid. If the magnetometer input fails, the AHRS continues to output valid attitude information and GPS Track information is used; however, the heading display on the PFD is flagged as invalid with a red “X,” “TRK” in magenta is annunciated to the right of the Track value, and the Track value color is changed from white to magenta. NOTE: In this case the magnetic standby compass and GPS ground track can be used to keep the aircraft on the desired heading. Note that SVT is turned off in “track-based reversionary mode” and must be manually re-enabled when heading is restored. Also, map orientations change from HDG UP to TRACK UP and must be manually changed back after heading is restored. When heading fails the heading bug is not removed and the GDU continues driving the autopilot heading error output using track in place of heading.
1-9190-01102-02 Rev. DGarmin G500 Pilot’s Guide ForewordSec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index Track Mode Active SVT Is Turned Off When Heading FailsHeading Failed Figure 1-13 Track Mode shown as Active when Heading Info has failed Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information. Invalid or unavailable airspeed data in addition to complete GPS failure results in loss of all attitude and heading information. NOTE: Fastest AHRS alignment is achieved with the aircraft stationary and with all AHRS inputs valid (3-D GPS position, magnetometer, and air data). During initial power up on the ground, no GPS position and/or magnetic anomalies are common. If the aircraft is taxied prior to AHRS alignment, alignment may be delayed until after a valid 3-D GPS position is available. NOTE: During in-flight alignment of the AHRS, minimize aircraft maneuvering. The AHRS will align with shallow banking and pitch angles (less than 20 degrees of roll or 5 degrees of pitch). AHRS alignment may not be possible during more aggressive maneuvers.
1-10Garmin G500 Pilot’s Guide190-01102-02 Rev. D Foreword Sec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.1.14 Secure Digital Cards The G500 System uses Secure Digital (SD) cards to load and store various types of data. For basic flight operations, SD cards are required for Terrain, Obstacle, FliteChart, SafeTaxi, and ChartView database storage as well as Jeppesen aviation and ChartView database updates. The Aviation Database update card is generally inserted in the upper SD card slot for database updates and then removed. Other database cards are normally located in the lower SD card slot. ChartView is an optional feature that requires enablement by a Garmin dealer. NOTE: Ensure the GDU 620 is powered off before inserting or removing an SD card. NOTE: Refer to Appendix A for instructions on updating the aviation database. Inserting an SD Card 1) Insert the SD card in the SD card slot (the front of the card should be flush with the face of the display bezel). 2) To eject the card, gently press on the SD card to release the spring latch.
1-11190-01102-02 Rev. DGarmin G500 Pilot’s Guide ForewordSec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.2 System Power Up NOTE: See the Aircraft Flight Manual (AFM) for specific procedures concerning avionics power application and emergency power supply operation. NOTE: Refer to Section 6 for system-specific annunciations and alerts. The G500 System is integrated with the aircraft electrical system and receives power directly from electrical busses. The GDU 620 and supporting sub-systems include both power-on and continuous built-in test features that exercise the processor, memory, external inputs, and outputs to ensure safe operation. During system initialization, test annunciations are displayed. All system annunciations should disappear typically within the first 30 seconds after power- up. Upon power-up, bezel key backlights also become momentarily illuminated on the GDU 620 display bezel. On the PFD, the AHRS begins to initialize and “AHRS ALIGN: Keep Wings Level” is displayed. The AHRS should display valid attitude and heading fields typically within the first minute after power-up. The AHRS can align itself both while taxiing and during level flight. NOTE: Fastest AHRS alignment is achieved with the aircraft stationary and with all AHRS inputs valid (3-D GPS position, magnetometer, and air data). During initial power up on the ground, no GPS position and/or magnetic anomalies are common. If the aircraft is taxied prior to AHRS alignment, alignment may be delayed until after a valid 3-D GPS position is available. NOTE: During in-flight alignment of the AHRS, minimize aircraft maneuvering. The AHRS will align with shallow banking and pitch angles (less than 20 degrees of roll or 5 degrees of pitch). AHRS alignment may not be possible during more aggressive maneuvers.
1-12Garmin G500 Pilot’s Guide190-01102-02 Rev. D Foreword Sec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index When the MFD powers up, the splash screen displays the following information: • Software version and part number • Copyright • Land database name and version • Obstacle database name and version • Terrain database name and version • Aviation database name, version, and effective dates • Airport Directory expiration dateCurrent database information includes valid operating dates, cycle number , and database type. When this information has been reviewed for currency (to ensure that no databases have expired), the pilot is prompted to continue. Databases are displayed in white if they are determined to be current. Databases are displayed in yellow if they have expired, are not yet effective, or if the current date/time is not yet available from the GPS. Figure 1-14 System Startup Pages
1-13190-01102-02 Rev. DGarmin G500 Pilot’s Guide ForewordSec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.3 international Geomagnetic reference Field The IGRF (International Geomagnetic Reference Field) model is contained in the GRS 77 and is only updated once every five years. The IGRF model is part of the Navigation Database. At system power-up, the IGRF models in the GRS 77 and in the Navigation Database are compared, and if the IGRF model in the GRS 77 is out of date, the user is prompted to update the IGRF model in the GRS 77. The following prompt will appear after the G500 splash screen is acknowledged on the MFD. GRS MV DB UPDATE AVAILABLE. UPDATE FROM yyyy TO yyyy (e.g. 2005 to 2010) Pressing the ENT key (or right-most soft key) acknowledges this information and displays the Navigation Map Page. When the interfaced GPS unit has acquired a sufficient number of satellites to determine a position, the aircraft’s current position is shown on the Navigation Map Page.
1-14Garmin G500 Pilot’s Guide190-01102-02 Rev. D Foreword Sec 1 System Sec 2 PFD Sec 3 MFD Sec 4 Hazard Avoidance Sec 5 Additional Features Sec 6 Annun. & Alerts Sec 7 Symbols Sec 8 Glossary Appendix A Appendix B Index 1.4 System Operation NOTE: Refer to Section 6 for detailed descriptions of all alerts and annunciations. 1.4.1 Pilot Controls The GDU 620 controls have been designed to simplify operation of the system and minimize workload and the time required to access functionality. Controls are located on the PFD and MFD bezels and are comprised of a PFD knob, MFD dual concentric knobs, bezel keys, and soft keys. 1.4.1.1 PFD Knob Turning the PFD knob adjusts the values for the mode selected by the PFD bezel keys, such as, Heading (HDG), Course (CRS), Altitude (ALT), Vertical Speed (V/S), and Barometric Setting (BARO). The values are shown in a window to the left of the HSI. Pressing the PFD knob reverts to the default value of the selected mode. Heading Mode Course Mode Altitude Mode Vertical Speed Mode Barometer Mode Figure 1-15 Selection Modes Adjusted with the PFD Knob NOTE: After 10 seconds of inactivity in another mode, the PFD knob selected mode will revert to Heading mode. 1. Press the desired PFD mode selection key (HDG, CRS, A LT, V/S, or BARO). A window will be displayed near the upper right corner of the HSI showing the current value for that mode. 2. Turn the PFD knob to select the desired value.