User manual GARMIN G900X COCKPIT KIT PLANES - PILOT'S GUIDE

G900X TM Integrated Flight Deck Pilot's Guide Copyright © 2007 Garmin Ltd. or its subsidiaries. All rights reserved. This manual reflects the operation of System Software version 0718.00 or later. Some differences in operation may be observed when comparing the information in this manual to earlier or later software versions. Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Tel: 913/397.8200 Fax: 913/397.8282 Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A. Tel: 503/391.3411 Fax: 503/364.2138 Garmin (Europe) Ltd., Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K Tel: 44/0870.8501241 Fax: 44/0870.8501251 Garmin Corporation, No. 68, Jangshu 2nd Road, Shijr, Taipei County, Taiwan Tel: 886/02.2642.9199 Fax: 886/02.2642.9099 Website Address: www.garmin.com Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express written permission of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed for personal use, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited. Garmin® is a registered trademark of Garmin Ltd. or its subsidiaries, and G900XTM, FliteChartsTM, and SafeTaxiTM are trademarks of Garmin Ltd. or its subsidiaries. These trademarks may not be used without the express permission of Garmin. NavData® is a registered trademark of Jeppesen, Inc.; Avidyne® and TCAD® are registered trademarks of Avidyne Corporation; S-TEC® is a registered trademark of S-TEC; CO Guardian is a trademark of CO Guardian, Inc.; and XM® is a registered trademark of XM Satellite Radio, Inc. November 2007 Printed in the U.S.A Garmin G900X Pilot's Guide 190-00726-00 Rev. B LIMITED WARRANTY LIMITED WARRANTY This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase. Within this period, Garmin will, at its sole option, repair or replace any components that fail in normal use. Such repairs or replacement will be made at no charge to the customer for parts and labor, provided that the customer shall be responsible for any transportation cost. This warranty does not cover failures due to abuse, misuse, accident, or unauthorized alterations or repairs. THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY, INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, STATUTORY OR OTHERWISE. THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS, WHICH MAY VARY FROM STATE TO STATE. IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE, OR INABILITY TO USE THIS PRODUCT OR FROM DEFECTS IN THE PRODUCT. Some states do not allow the exclusion of incidental or consequential damages, so the above limitations may not apply to you. Garmin retains the exclusive right to repair or replace the unit or software, or to offer a full refund of the purchase price, at its sole discretion. SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY. Products sold through online auctions are not eligible for rebates or other secial offers from Garmin. Online auction confirmations are not accepted for warranty verification. To obtain warranty service, an original copy of the sales receipt from the original retailer is required. Garmin will not replace missing components from any package purchased through an online auction. To obtain warranty service, contact your local Garmin Authorized Service Center. For assistance in locating a Service Center, visit the Garmin website at www.garmin.com or contact Garmin Customer Service at one of the numbers listed below: Garmin International, Inc., 1200 East 151st Street, Olathe, Kansas 66062, U.S.A. Toll free: 800/800.1020 Tel: 913/397.8200 Garmin AT, Inc., 2345 Turner Road SE, Salem, OR 97302, U.S.A. Toll free: 800/525.6726 Tel: 503/391.3411 Fax: 913/397.8282 Fax: 503/364.2138 Garmin (Europe) Ltd., Liberty House, Bulls Copse Road, Hounsdown Business Park, Southampton, SO40 9RB, U.K Toll free (within U.K.): 0808 238 0000 Tel: 44/0870.8501241 Fax: 44/0870.8501251 Refer to the G900X Installation Manual for warranty registration instructions. Note: Record product serial numbers on reverse side and retain for your records. 190-00726-00 Rev. B Garmin G900X Pilot's Guide i LIMITED WARRANTY List all Garmin products and serial numbers and retain this document for your records. Product Serial Number ii Garmin G900X Pilot's Guide 190-00726-00 Rev. B WARNINGS, CAUTIONS, AND NOTES WARNING: Navigation and terrain separation must NOT be predicated upon the use of the terrain function. The G900X Terrain Proximity feature is NOT intended to be used as a primary reference for terrain avoidance and does not relieve the pilot from the responsibility of being aware of surroundings during flight. The Terrain Proximity feature is only to be used as an aid for terrain avoidance and is not certified for use in applications requiring a certified terrain awareness system. Terrain data is obtained from third party sources. Garmin is not able to independently verify the accuracy of the terrain data. WARNING: The displayed minimum safe altitudes (MSAs) are only advisory in nature and should not be relied upon as the sole source of obstacle and terrain avoidance information. Always refer to current aeronautical charts for appropriate minimum clearance altitudes. WARNING: The altitude calculated by G900X GPS receivers is geometric height above Mean Sea Level and could vary significantly from the altitude displayed by pressure altimeters, such as the GDC 74A Air Data Computer, or other altimeters in aircraft. GPS altitude should never be used for vertical navigation. Always use pressure altitude displayed by the G900X PFD or other pressure altimeters in aircraft. WARNING: Do not use outdated database information. Databases used in the G900X system must be updated regularly in order to ensure that the information remains current. Pilots using any outdated database do so entirely at their own risk. WARNING: Do not use basemap (land and water data) information for primary navigation. Basemap data is intended only to supplement other approved navigation data sources and should be considered as an aid to enhance situational awareness. WARNING: Traffic information shown on the G900X Multi Function Display is provided as an aid in visually acquiring traffic. Pilots must maneuver the aircraft based only upon ATC guidance or positive visual acquisition of conflicting traffic. WARNING: Use of the Stormscope is not intended for hazardous weather penetration (thunderstorm penetration). Stormscope information, as displayed on the G900X MFD, is to be used only for weather avoidance, not penetration. WARNING: GDL 69 Weather should not be used for hazardous weather penetration. Weather information provided by the GDL 69 is approved only for weather avoidance, not penetration. WARNING: NEXRAD weather data is to be used for long-range planning purposes only. Due to inherent delays in data transmission and the relative age of the data, NEXRAD weather data should not be used for short-range weather avoidance. 190-00726-00 Rev. B Garmin G900X Pilot's Guide iii WARNINGS, CAUTIONS, AND NOTES WARNING: The Garmin G900X has a very high degree of functional integrity. However, the pilot must recognize that providing monitoring and/or self-test capability for all conceivable system failures is not practical. Although unlikely, it may be possible for erroneous operation to occur without a fault indication shown by the G900X. It is thus the responsibility of the pilot to detect such an occurrence by means of cross-checking with all redundant or correlated information available in the cockpit. WARNING: For safety reasons, G900X operational procedures must be learned on the ground. WARNING: The United States government operates the Global Positioning System and is solely responsible for its accuracy and maintenance. The GPS system is subject to changes which could affect the accuracy and performance of all GPS equipment. Portions of the Garmin G900X utilize GPS as a precision electronic NAVigation AID (NAVAID). Therefore, as with all NAVAIDs, information presented by the G900X can be misused or misinterpreted and, therefore, become unsafe. WARNING: To reduce the risk of unsafe operation, carefully review and understand all aspects of the G900X Pilot's Guide documentation and the Pilot's Operating Handbook (POH) for the aircraft. Thoroughly practice basic operation prior to actual use. During flight operations, carefully compare indications from the G900X to all available navigation sources, including the information from other NAVAIDs, visual sightings, charts, etc. For safety purposes, always resolve any discrepancies before continuing navigation. WARNING: The illustrations in this guide are only examples. Never use the G900X to attempt to penetrate a thunderstorm. Both the FAA Advisory Circular, Subject: Thunderstorms, and the Aeronautical Information Manual (AIM) recommend avoiding "by at least 20 miles any thunderstorm identified as severe or giving an intense radar echo." WARNING: Lamp(s) inside this product may contain mercury (HG) and must be recycled or disposed of according to local, state, or federal laws. For more information, refer to our website at www.garmin.com/ aboutGarmin/environment/disposal.jsp. WARNING: Because of anomalies in the earth's magnetic field, operating the G900X within the following areas could result in loss of reliable attitude and heading indications. North of 70° North latitude and south of 70° South latitude. An area north of 65° North latitude between longitude 75º West and 120º West. An area south of 55° South latitude between longitude 120º East and 165º East. CAUTION: The GDU 1040 PFD(s) and GDU 1040 MFD displays use a lens coated with a special anti-reflective coating that is very sensitive to skin oils, waxes, and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective coatings. iv Garmin G900X Pilot's Guide 190-00726-00 Rev. B WARNINGS, CAUTIONS, AND NOTES CAUTION: The Garmin G900X does not contain any user-serviceable parts. Repairs should only be made by an authorized Garmin service center. Unauthorized repairs or modifications could void both the warranty and the pilot's authority to operate this device under FAA/FCC regulations. NOTE: When using Stormscope, there are several atmospheric phenomena in addition to nearby thunderstorms that can cause isolated discharge points in the strike display mode. However, clusters of two or more discharge points in the strike display mode do indicate thunderstorm activity if these points reappear after the screen has been cleared. NOTE: All visual depictions contained within this document, including screen images of the G900X panel and displays, are subject to change and may not reflect the most current G900X system. Depictions of equipment may differ slightly from the actual equipment. NOTE: This device complies with part 15 of the FCC Rules. Operation is subject to the following two conditions: (1) this device may not cause harmful interference, and (2) this device must accept any interference received, including interference that may cause undesired operation. NOTE: Interference from GPS repeaters operating inside nearby hangars can cause an intermittent loss of attitude and heading displays while the aircraft is on the ground. Moving the aircraft more than 100 yards away from the source of the interference should alleviate the condition. NOTE: Use of polarized eyewear may cause the flight displays to appear dim or blank. NOTE: This product, its packaging, and its components contain chemicals known to the State of California to cause cancer, birth defects, or reproductive harm. This notice is being provided in accordance with California's Proposition 65. If you have any questions or would like additional information, please refer to our web site at www.garmin.com/prop65. 190-00726-00 Rev. B Garmin G900X Pilot's Guide v REVISION INFORMATION Record of Revisions Part Number 190-00726-00 190-00726-00 Revision A B Date 04/04/07 11/6/07 Page Range i ­ I-6 Initial release i ­ I-6 Description Update to GDU 8.10, add three display no-EIS configuration. vi Garmin G900X Pilot's Guide 190-00726-00 Rev. B TABLE OF CONTENTS SECTION 1 SYSTEM OVERVIEW Line Replaceable Units ........................................1-2 Secure Digital (SD) Cards ....................................1-9 System Power-up ................................................1-10 System Operation...............................................1-11 Display Operation ....................................................1-11 G900X System Annunciations ...................................1-13 System Status..........................................................1-13 AHRS Operation ......................................................1-16 GPS Receiver Operation ...........................................1-17 G900X Controls ..................................................1-22 PFD/MFD Controls ...................................................1-22 MFD/PFD Control Unit (Optional) ..............................1-24 Softkey Function ......................................................1-27 Accessing G900X Functionality ........................1-33 Menus ....................................................................1-33 Data Entry ..............................................................1-33 Page Groups ...........................................................1-35 System Settings .......................................................1-39 System Utilities........................................................1-47 Electronic Checklists (Optional) .................................1-50 Display Backlighting ..........................................1-52 Low Altitude Annunciation .......................................2-28 Minimum Descent Altitude/Decision Height Alerting ...2-28 1.1 1.2 1.3 1.4 2.4 Abnormal Operations ........................................2-30 Abnormal GPS Conditions ........................................2-30 Unusual Attitudes ....................................................2-31 3.1 3.2 SECTION 3 ENGINE INDICATION SYSTEM EIS Display.............................................................3-3 Engine Page ..........................................................3-8 Electrical .................................................................3-13 Temperatures ..........................................................3-14 CO Alert Reset (Optional) .........................................3-14 Fuel Calculations .....................................................3-15 Leaning Assist Mode ..........................................3-17 Turbocharged ..........................................................3-17 Normally-aspirated ..................................................3-18 EIS Display in Reversionary Mode....................3-19 Lean Display ...........................................................3-21 System Display ........................................................3-26 SECTION 4 AUDIO PANEL AND CNS Overview ...............................................................4-1 PFD Controls and Frequency Display ............................4-2 Audio Panel Controls .................................................4-4 MFD/PFD Control Unit (Optional) ................................4-6 COM Operation .....................................................4-8 COM Transceiver Selection and Activation ....................4-8 COM Transceiver Manual Tuning .................................4-9 Quick-Tuning and Activating 121.500 MHz.................4-11 Auto-Tuning the COM Frequency...............................4-12 Frequency Spacing ...................................................4-16 Automatic Squelch...................................................4-17 Volume ...................................................................4-17 NAV Operation ....................................................4-18 NAV Radio Selection and Activation ..........................4-18 NAV Receiver Manual Tuning ....................................4-19 Auto-Tuning a NAV Frequency from the MFD .............4-21 Auto-Tuning NAV Frequencies on Approach Activation 4-25 Marker Beacon Receiver ...........................................4-26 GTX 33 Mode S Transponder(s).........................4-27 Transponder Controls ...............................................4-27 Transponder Mode Selection .....................................4-28 1.5 3.3 1.6 3.4 4.1 1.7 SECTION 2 FLIGHT INSTRUMENTS 2.1 Flight Instruments ................................................2-4 Airspeed Indicator .....................................................2-4 Attitude Indicator ......................................................2-6 Altimeter ..................................................................2-7 Vertical Speed Indicator (VSI) ......................................2-8 Vertical Deviation ......................................................2-9 Horizontal Situation Indicator (HSI) ...........................2-10 Course Deviation Indicator (CDI) ...............................2-15 2.2 Supplemental Flight Data .................................2-22 Outside Air Temperature ...........................................2-22 Wind Data ..............................................................2-23 Vertical Navigation (VNV) Indications ........................2-24 2.3 PFD Annunciations and Alerting Functions .....2-25 System Alerting .......................................................2-25 Marker Beacon Annunciations ..................................2-26 Traffic Annunciation .................................................2-26 TAWS Annunciations (Optional) ................................2-27 Altitude Alerting ......................................................2-27 4.2 4.3 4.4 190-00726-00 Rev. B Garmin G900X Pilot's Guide vii TABLE OF CONTENTS Entering a Transponder Code ....................................4-31 IDENT Function .......................................................4-32 Flight ID Reporting ..................................................4-33 4.5 Additional Audio Panel Functions ....................4-34 Power-Up ................................................................4-34 Mono/Stereo Headsets .............................................4-34 Speaker ..................................................................4-34 Intercom .................................................................4-35 Passenger Address (PA) System .................................4-37 Clearance Recorder and Player..................................4-37 Entertainment Inputs ...............................................4-38 4.6 Audio Panel Preflight Procedure ......................4-39 4.7 Abnormal Operation ..........................................4-40 Stuck Microphone....................................................4-40 COM Tuning Failure..................................................4-40 Audio Panel Fail-Safe Operation ................................4-40 PFD Failure, Dual System ..........................................4-41 PFD Failure, Single System (Reversionary Mode) ........4-42 5.1 5.2 SECTION 5 FLIGHT MANAGEMENT Introduction ..........................................................5-1 Navigation Status Box................................................5-3 Using Map Displays ..............................................5-4 Map Orientation ........................................................5-4 Map Range ...............................................................5-6 Map Panning.............................................................5-9 Measuring Bearing and Distance ...............................5-14 Topography .............................................................5-15 Map Symbols ..........................................................5-18 Airways ..................................................................5-24 Track Vector ............................................................5-26 Wind Vector ............................................................5-27 Nav Range Ring ......................................................5-28 Fuel Range Ring ......................................................5-29 No-EIS Option .........................................................5-30 Waypoints............................................................5-36 Airports ..................................................................5-37 Intersections ...........................................................5-43 NDBs ......................................................................5-45 VORs ......................................................................5-47 User Waypoints .......................................................5-49 Airspaces .............................................................5-54 5.5 Direct-to-Navigation .........................................5-59 5.6 Flight Planning....................................................5-65 Flight Plan Creation .................................................5-66 Adding Waypoints To An Existing Flight Plan ..............5-69 Adding Airways to a Flight Plan ................................5-71 Adding Procedures To A Stored Flight Plan .................5-74 Flight Plan Storage ..................................................5-80 Flight Plan Editing ...................................................5-83 Along Track Offsets ..................................................5-86 Parallel Track ...........................................................5-88 Activating a Flight Plan Leg ......................................5-91 Inverting a Flight Plan ..............................................5-92 Flight Plan Views .....................................................5-93 Closest Point of FPL .................................................5-95 5.7 Vertical Navigation ............................................5-96 Altitude Constraints .................................................5-98 5.8 Procedures ........................................................5-102 Departures ............................................................5-102 Arrivals ................................................................5-105 Approaches ..........................................................5-107 5.9 Trip Planning .....................................................5-113 Trip Planning .........................................................5-113 5.10 RAIM Prediction ...............................................5-117 5.11 Navigating a Flight Plan ..................................5-121 5.12 Abnormal Operation ........................................5-148 6.1 SECTION 6 HAZARD AVOIDANCE XM Satellite Weather (Opt) .................................6-1 Activating Services.....................................................6-2 Using XM Satellite Weather Products...........................6-3 Airborne Color Weather Radar (Opt) ...............6-25 System Description ..................................................6-25 Principles of Pulsed Airborne Weather Radar ..............6-25 Safe Operating Distance ...........................................6-30 Basic Antenna Tilt Setup ...........................................6-30 Weather Mapping and Interpretation ........................6-32 Ground Mapping and Interpretation ..........................6-45 Terrain Proximity ................................................6-46 Displaying Terrain Proximity Data ..............................6-47 Terrain Proximity Page..............................................6-49 Terrain Awareness & Warning System (Opt) ...6-51 Displaying TAWS Data ..............................................6-52 6.2 5.3 6.3 5.4 6.4 viii Garmin G900X Pilot's Guide 190-00726-00 Rev. B TABLE OF CONTENTS TAWS Page .............................................................6-54 TAWS Alerts ............................................................6-56 System Status..........................................................6-62 6.5 Traffic Information Service (TIS) .......................6-63 Displaying TRAFFIC Data ..........................................6-64 Traffic Map Page......................................................6-66 TIS Alerts ................................................................6-67 System Status..........................................................6-68 6.6 TAS600 Traffic Advisory System (Opt) ..............6-71 TAS Symbology........................................................6-71 Operation ...............................................................6-72 Altitude Display .......................................................6-74 Traffic Map Page Display Range ................................6-74 TAS Alerts ...............................................................6-76 System Status..........................................................6-77 SECTION 7 AUTOMATIC FLIGHT CONTROL SYSTEM 8.1 8.2 SECTION 8 ADDITIONAL FEATURES SafeTaxi .................................................................8-1 SafeTaxi Cycle Number and Revision ...........................8-4 ChartView..............................................................8-7 ChartView Softkeys ....................................................8-7 Terminal Procedures Charts ........................................8-8 Chart Options..........................................................8-18 Day/Night View .......................................................8-24 ChartView Cycle Number and Expiration Date ............8-26 FliteCharts ...........................................................8-30 FliteCharts Softkeys .................................................8-30 Terminal Procedures Charts ......................................8-31 Chart Options..........................................................8-39 Day/Night View .......................................................8-43 FliteCharts Cycle Number and Expiration Date............8-45 XM Radio Entertainment (Optional) ................8-49 Activating XM Satellite Radio Services .......................8-49 Using XM Radio ......................................................8-51 Scheduler.............................................................8-55 Abnormal Operation ..........................................8-57 APPENDICES Annunciations and Alerts ..............................................A-1 Comparator Annunciations (3 Display Only) .................A-5 Reversionary Sensor Annunciations (3 Display Only) .....A-6 G900X System Message Advisories .............................A-9 SD Card Use and Databases..........................................B-1 Glossary...........................................................................C-1 Frequently Asked Questions .........................................D-1 General TIS Information ................................................ F-1 Map Symbols ................................................................. G-1 INDEX 8.3 8.4 8.5 8.6 190-00726-00 Rev. B Garmin G900X Pilot's Guide ix TABLE OF CONTENTS BLANK PAGE x Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW SECTION 1 SYSTEM OVERVIEW The G900X Integrated Flight Deck System presents flight instrumentation, position, navigation, communication, and identification information to the pilot using flat-panel color displays. The system is distributed across the following Line Replaceable Units (LRUs): · GDU 1040 Primary Flight Display(s) (PFD) · GDU 1040 Multi Function Display (MFD) · GMA 1347 Audio Panel with Integrated Marker Beacon Receiver · GIA 63W Integrated Avionics Units (IAU) · GDC 74A Air Data Computer (ADC) Figure 1-1 shows interactions between the LRUs. Additional/optional equipment are shown in Figure 1-2. The G900X is capable of interfacing with the following optional equipment: · GCU 476 MFD/PFD Control Unit · GDL 69A Data Link Receiver · GWX 68 Weather Radar · CO Guardian Aero 353R/452R Remote Carbon Monoxide Detector · Avidyne TAS600-series Traffic Advisory System · Artex ELT 406-N Emergency Locator Transmitter · S-TEC 55X Autopilot · TruTrak Sorcerer/DFC Series autopilots · TruTrak Digiflight II-Series autopilots · TruTrak Digitrak/Pictorial Pilot autopilots · TruTrak ADI · Trio Avionics EZ Pilot Autopilot · GEA 71 Engine/Airframe Unit · GTX 33 Mode S Transponder · GRS 77 Attitude and Heading Reference System (AHRS) · GMU 44 Magnetometer 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-1 SYSTEM OVERVIEW 1.1 LINE REPLACEABLE UNITS · GDU 1040 (2 or 3) ­ In a two display configuration, the left-hand GDU is configured as a Primary Flight Display (PFD) and the right-hand GDU as a Multi Function Display (MFD). In a three display configuration, the outside GDUs are configured as Primary Flight Displays (PFDs) and the inside GDU as a Multi Function Display (MFD).All feature 10.4-inch LCD screens with 1024 x 768 resolution. The displays communicate with each other through a High-Speed Data Bus (HSDB) Ethernet connection. Each display is also paired with an Ethernet connection to an IAU. · GMA 1347 ­ The Audio Panel integrates navigation/communication radio (NAV/COM) digital audio, intercom, and marker beacon controls, and is installed between the displays. This unit also provides manual control of display reversionary mode (red DISPLAY BACKUP Button; see Section 1.5, System Operation) and communicates with both IAUs using an RS-232 digital interface. · GIA 63W (2) ­ The Integrated Avionics Units (IAU) function as the main communication hubs, linking all LRUs with the on-side display. Each IAU contains a GPS WAAS receiver, VHF COM/NAV/GS receivers, and system integration microprocessors, and is paired with the on-side display via HSDB connection. The IAUs are not paired together and do not communicate with each other directly. 1-2 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW · GDC 74A (1 or 2) ­ The Air Data Computer (ADC) processes data from the pitot/static system and outside air temperature (OAT) sensor. The ADC provides pressure altitude, airspeed, vertical speed, and OAT information to the G900X System, and it communicates with the primary IAU, displays, and AHRS using an ARINC 429 digital interface. · GEA 71 ­ The Engine Airframe Unit receives and processes signals from the engine and airframe sensors. This unit communicates with both IAUs using an RS-485 digital interface. · GTX 33 (1 or 2) ­ The solid-state Transponder provides Modes A, C, and S capability and communicates with both IAUs through an RS-232 digital interface. · GRS 77 (1 or 2) ­ The Attitude and Heading Reference System (AHRS) provides aircraft attitude and heading information via ARINC 429 to both PFDs and the primary IAU. The AHRS contains advanced sensors (including accelerometers and rate sensors) and interfaces with the Magnetometer to obtain magnetic field information, with the ADC to obtain air data, and with both IAUs to obtain GPS information. AHRS operation is discussed in Section 1.4, System Operation. 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-3 SYSTEM OVERVIEW · GMU 44 (1 or 2) ­ The Magnetometer measures local magnetic field and sends data to the AHRS for processing to determine aircraft magnetic heading. This unit receives power directly from the AHRS and communicates with it via an RS-485 digital interface. · GCU 476 ­ The Control Unit (optional with 2 display configuration) provides MFD/PFD and radio tuning control through an RS-232 digital interface · GDL 69A ­ The optional Data Link Satellite Radio Receiver provides real-time weather information to the G900X MFD and PFD Inset Map, as well as digital audio entertainment. The Data Link Receiver communicates with the MFD via a HSDB connection. A subscription to XM Satellite Radio Service is required to enable the GDL 69A capability. · GWX 68 (1) ­ (optional) Provides airborne weather and ground mapped radar data to the MFD, through the GDL 69A, via HSDB connection. 1-4 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW Primary Flight Display GDU 1040 GMA 1347 Audio Panel Multi Function Display GDU 1040 Reversionary Control Reversionary Control GDC 74A Air Data Computer No. 1 GIA 63W Integrated Avionics Unit System Inegration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope GPS Output OAT Airspeed Altitude Vertical Speed No. 2 GIA 63W Integrated Avionics Unit System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope GPS Output GRS 77 AHRS Attitude Rate of Turn Slip/Skid GMU 44 Magnetometer Heading GTX 33 Transponder GEA 71 Engine/Airframe Unit Figure 1-1 Basic G900X Two Display System Block Diagram 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-5 SYSTEM OVERVIEW GDU 1040 PFD #1 Audio Panel GMA 1347 GDU 1040 MFD GDU 1040 PFD #2 MFD/PFD Control Unit GCU 476 Integrated Avionics Unit GIA 63W #1 Integrated Avionics Unit GIA 63W #2 GDC 74A #1 System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope Air Data Computer GDC 74A #2 Air Data Computer OAT Airspeed Altitude Vertical Speed System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope OAT Airspeed Altitude Vertical Speed GRS 77 #1 AHRS GPS Output GRS 77 #2 AHRS Attitude Rate of Turn Slip/Skid GPS Output Attitude Rate of Turn Slip/Skid Magnetometer Heading GMU 44 #1 Magnetometer Heading GMU 44 #2 GTX 33 #1 Transponder GTX 33 #2 Transponder Engine/ Airframe Unit GEA 71 Figure 1-2 Basic G900X Three Display System Block Diagram 1-6 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW MFD/PFD Control Unit (optional) GCU 476 No. 1 GIA 63W Integrated Avionics Unit System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope No. 2 GIA 63W Integrated Avionics Unit System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope Real-time Weather and Digital Audio Entertainment (optional, subscription-based service) Data Link GDL 69A Emergency Locator Transmitter (optional) ELT Avidyne TAS600-series Provides Traffic Information (optional) CO Guardian Carbon Monoxide Detection (optional) STEC/ TruTrak/ Trio Autopilot (optional) Figure 1-3 G900X Two Display With Optional/Additional Equipment NOTE: For information on non-Garmin optional/additional equipment shown in Figure 1-3 and Figure 1-4, consult the applicable optional interface user's guide. This document assumes that the reader is already familiar with the operation of this additional equipment. 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-7 SYSTEM OVERVIEW GDU 1040 PFD #1 Audio Panel GMA 1347 GDU 1040 MFD GDU 1040 PFD #2 Integrated Avionics Unit System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope GIA 63W #1 Integrated Avionics Unit System Integration Processors I/O Processors VHF COM VHF NAV/LOC GPS Glideslope GIA 63W #2 GDL 69A Data Link Real-time Weather and Digital Audio Entertainment (optional, subscription-based service) Emergency Locator Transmitter (optional) ELT Avidyne TAS600 Traffic Advisory System (optional) STEC/ TruTrak/ Trio Autopilot (optional) Weather Radar (optional) GWX 68 Figure 1-4 G900X Three Display With Optional/Additional Equipment 1-8 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW 1.2 SECURE DIGITAL (SD) CARDS NOTE: Ensure the G900X System is powered off before inserting an SD card. NOTE: Refer to Appendix B for instructions on updating the aviation database. The PFD and MFD data card slots use Secure Digital (SD) cards and are located on the upper right side of the display bezels. Each display bezel is equipped with two SD card slots. SD cards are used for aviation database and system software updates as well as terrain database storage. Installing 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. SD Card Slots Figure 1-3 Display Bezel SD Card Slots 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-9 SYSTEM OVERVIEW 1.3 SYSTEM POWER-UP NOTE: Refer to Appendix A for system-specific annunciations and alerts. The G900X System is integrated with the aircraft electrical system and receives power directly from electrical busses. The PFD(s), MFD, and supporting sub-systems include both power-on and continuous built-in test features that exercise the processor, RAM, ROM, external inputs, and outputs to provide safe operation. During system initialization, test annunciations are displayed, as shown in Figure 1-4. All system annunciations should disappear typically within the first minute of power-up. Upon power-up, key annunciator lights also become momentarily illuminated on the Audio Panel, the MFD/PFD Control Unit, and the display bezels. On the PFD(s), the AHRS begins to initialize and displays "AHRS ALIGN: Keep Wings Level". The AHRS should display valid attitude and heading fields typically within the first minute of power-up. The AHRS can align itself both while taxiing and during level flight. When the MFD powers up, the splash screen (Figure 1-5) displays the following information: · System version · Copyright · Land database name and version · Obstacle database name and version · Terrain database name and version · Aviation database name, version, and effective dates Current 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. Pressing the ENT Key (or right-most softkey) acknowledges this information, and the Navigation Map Page is displayed upon pressing the key a second time. When the system has acquired a sufficient number of satellites to determine a position, the aircraft's current position is shown on the Navigation Map Page. Figure 1-4 PFD Initialization Figure 1-5 Example MFD Power-up Splash Screen 1-10 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW 1.4 SYSTEM OPERATION NOTE: Refer to Appendix A for detailed descriptions of all annunciations and alerts. The G900X System alerts the pilot when backup paths are utilized by the LRUs. The kitplane builder should establish appropriate pilot actions in response to all G900X annunciations in the aircraft-specific Pilot's Operating Handbook (POH). The displays are connected together via a single Ethernet bus for high-speed communication. As shown in Figure 1-1, each IAU is connected to the on-side display. This section discusses normal and reversionary G900X display operation, AHRS modes, GPS receiver operation, and G900X System Annunciations. DISPLAY OPERATION NOTE: In normal operating mode, backlighting can only be adjusted from the PFD(s) (see Section 1.7). In reversionary mode, it can be adjusted from the remaining display(s). In normal operating mode, the PFD(s) presents graphical flight instrumentation (attitude, heading, airspeed, altitude, vertical speed), replacing the traditional flight instrument cluster (see the Flight Instruments Section for more information). The MFD normally displays a full-color moving map with navigation information (see the Flight Management Section), while the left portion of the MFD is dedicated to the Engine Indication System or to Navigation Information (EIS, see the EIS Section; Navigation Information, see the Flight Management Section). Both displays offer control for COM and NAV frequency selection. Figure 1-6 G900X Two Display System Normal Operation Figure 1-7 G900X Three Display System Normal Operation 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-11 SYSTEM OVERVIEW In the event of a display failure, the G900X System automatically switches to reversionary (backup) mode. In reversionary mode, all important flight information is presented on the remaining display(s) in the same format as in normal operating mode. · PFD1 failure ­ MFD enters reversionary mode; PFD2 remains in normal mode. · MFD failure ­ PFD1 and PFD2 enter reversionary mode. · PFD2 failure ­ PFD1 and the MFD remain in normal mode. If a display fails, the appropriate IAU-display Ethernet interface is cut off. Thus, the IAU can no longer communicate with the remaining display (refer to Figure 1-1), and the NAV and COM functions provided to the failed display by the IAU are flagged as invalid on the remaining display. The system reverts to backup paths for the AHRS, ADC, Engine/Airframe Unit, and Transponder, as required. The change to backup paths is completely automated for all LRUs and no pilot action is required. If the system fails to detect a display problem, reversionary mode may be manually activated by pressing the Audio Panel's red DISPLAY BACKUP Button. Pressing this button again deactivates reversionary mode. NAV1 and COM1 (provided by the failed PFD) Flagged Invalid DISPLAY BACKUP Button Manually Activates/ Deactivates Reversionary Mode on Both Displays Figure 1-8 G900X Two Display Reversionary Mode (Failed PFD) NAV1 and COM1 Flagged Invalid (provided by the failed PFD) DISPLAY BACKUP Button Manually Activates/Deactivates Reversionary Mode on All Displays Figure 1-9 G900X Three Display Reversionary Mode (Failed PFD1) 1-12 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW G900X SYSTEM ANNUNCIATIONS When an LRU or an LRU function fails, a large red `X' is typically displayed over the instrument experiencing failed data (Figure 1-10 displays all possible flags and responsible LRUs). Upon G900X power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should be operational within one minute of power-up. If any instrument remains flagged, the G900X should be serviced by a Garmin-authorized repair facility. GIA 63W Integrated Avionics Units GIA 63W Integrated Avionics Units GDC 74A Air Data Computer GRS 77 AHRS OR GMU 44 Magnetometer GEA 71 Engine Airframe Unit OR GIA 63W Integrated Avionics Unit GIA 63W Integrated Avionics Units GDC 74A Air Data Computer GTX 33 Transponder OR GIA 63W Integrated Avionics Units Figure 1-10 G900X System Failure Annunciations SYSTEM STATUS The System Status Page displays the statuses, serial numbers, and software version numbers for all detected system LRUs. Active LRUs are indicated by green check marks; failed, by red `X's. Failed LRUs should be noted and a service center or Garmin-authorized dealer informed. Viewing LRU information: 1) Use the FMS Knob to select the AUX - System Status Page. 2) To place the cursor in the `LRU Info' Box, a) Select the LRU Softkey. Or: a) Press the MENU Key. b) With `Select LRU Window' highlighted, press the ENT Key. 3) Use the FMS Knob to scroll through the box to view LRU status information. 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-13 SYSTEM OVERVIEW Figure 1-11 Example System Status Page 1-14 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW Pertinent information on all system databases is also displayed on this page. Refer to the Appendices and Additional Features sections for more information about databases. Viewing database information: 1) Use the FMS Knob to select the AUX - System Status Page. 2) To place the cursor in the `Database' Box, a) Select the DBASE Softkey. Or: a) Press the MENU Key. b) Highlight `Select Dbase Window' and press the ENT Key. 3) Use the FMS Knob to scroll through the box to view database status information. The G900X uses aural tones to convey the priority of airframe-specific alerts. The alerting system's annunciation tone may be tested from the System Status Page. Refer to the Appendices for airframe-specific alerts. Testing the system annunciation tone: 1) Use the FMS Knob to select the AUX - System Status Page. 2) Select the ANN TEST Softkey. Or: a) Press the MENU Key. b) Highlight `Enable Annunciator Test Mode' and press the ENT Key. 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-15 SYSTEM OVERVIEW AHRS OPERATION NOTE: Aggressive maneuvering while AHRS is not operating normally may degrade AHRS accuracy. The Attitude and Heading Reference System (AHRS) performs attitude, heading, and vertical acceleration calculations for the G900X System, utilizing GPS, magnetometer, and air data in addition to information from its internal sensors. Attitude and heading information are updated on the PFD(s) while the AHRS receives appropriate combinations of information from the external sensor inputs. unavailable unavailable Airspeed Data available AHRS Normal Operation AHRS no- AHRS no-Mag/ Mag Mode no-Air Mode Heading Invalid AHRS no-GPS Mode available un av ail ab le Attitude/Heading Invalid Figure 1-12 AHRS Operation Loss of GPS, magnetometer, or air data inputs is communicated to the pilot by message advisory alerts. 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). 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 can continue to provide attitude and heading information to the PFD(s) as long as magnetometer and airspeed data are available and valid. If the magnetometer input fails, the AHRS continues to output valid attitude information; however, the heading output on the PFD(s) is flagged as invalid with a red `X'. Failure of the air data input has no effect on the AHRS output while AHRS is receiving valid GPS information. Invalid/unavailable airspeed data in addition to GPS failure results in loss of all attitude and heading information. 1-16 Garmin G900X Pilot's Guide unavailable Magnetometer available available unavailable GPS available 190-00726-00 Rev. B SYSTEM OVERVIEW GPS RECEIVER OPERATION Each Integrated Avionics Unit (IAU) contains a GPS receiver. Internal system checking is performed to ensure both GPS receivers are providing accurate data to the PFD(s). When both GPS receivers are providing accurate data, the GPS receiver producing the better solution is used by the system. Information collected by the specified receiver (GPS1 for the #1 IAU or GPS2 for the #2 IAU) may be viewed on the AUX - GPS Status Page. Viewing GPS receiver status information: 1) Use the large FMS Knob on the MFD to select the Auxiliary Page Group (see Section 1.6 for information on navigating MFD page groups). 2) Use the small FMS Knob to select GPS Status Page (third page in the AUX Page Group). 3) To change the selected GPS receiver: Select the desired GPS Softkey. Or: a) Press the MENU Key. b) Use the FMS Knob to highlight the receiver which is not selected and press the ENT Key. 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-17 SYSTEM OVERVIEW Satellite Constellation Diagram Satellite Signal Information GPS Receiver Status RAIM Availability Prediction Satellite Signal Strength Bars Figure 1-13 GPS Status Page GPS sensor annunciations are most often seen after system power-up when one GPS receiver has acquired satellites before the other or one of the GPS receivers has not yet acquired a WAAS signal. While the aircraft is on the ground, the WAAS signal may be blocked by obstructions causing one GPS receiver to have difficulty acquiring a good signal. Also, while airborne, turning the aircraft may result in one of the GPS receivers temporarily losing the WAAS signal. If no failure message exists, check the GPS Status Page and compare the information for GPS1 and GPS2. Discrepancies may indicate a problem. GPS RECEIVER STATUS The GPS solution type (ACQUIRING, 2D NAV, 2D DIFF NAV, 3D NAV, 3D DIFF NAV) for the active GPS receiver (GPS1 or GPS2) is shown in the upper right of the GPS Status Page. When the receiver is in the process of acquiring enough satellite signals for navigation, the receiver uses satellite orbital data (collected continuously from the satellites) and last known position to determine the satellites that should be in view. ACQUIRING is indicated as the solution until a sufficient number of satellites have been acquired for computing a solution. 1-18 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW When the receiver is in the process of acquiring a 3D navigational GPS solution, 3D NAV is indicated as the solution until the 3D differential fix has finished acquisition. Satellite-Based Augmentation System (SBAS) status should be indicated as INACTIVE at this point. When acquisition is complete, the solution status changes to 3D DIFF NAV and SBAS becomes active. In certain situations, such as when the aircraft is outside or on the fringe of the WAAS coverage area, it may be desirable to disable WAAS (although it is not recommended). When disabled, the SBAS field in the GPS Status box indicates DISABLED. Disabling WAAS: 1) Select the GPS Status Page. 2) Select the SBAS Softkey. The RAIM PREDICTION box is replaced by SBAS SELECTION. 3) Press the FMS Knob. `WAAS' is highlighted. 4) Press the ENT Key to uncheck the box. 5) Press the FMS Knob to remove the cursor. Figure 1-14 Enable/Disable WAAS RAIM PREDICTION Receiver Autonomous Integrity Monitoring (RAIM) is a GPS receiver function that performs a consistency check on all tracked satellites. RAIM ensures that the available satellite geometry allows the receiver to calculate a position within a specified RAIM protection limit (2.0 nautical miles for oceanic and enroute, 1.0 nm for terminal, and 0.3 nm for non-precision approaches). During oceanic, enroute, and terminal phases of flight, RAIM is available nearly 100% of the time. The RAIM prediction function also indicates whether RAIM is available at a specified date and time. RAIM computations predict satellite coverage within ±15 min of the specified arrival date and time. In most cases performing RAIM prediction is not necessary. However, in some cases, the selected approach may be outside the WAAS coverage area and it may be necessary to perform a RAIM prediction for the intended approach. Because of the tighter protection limit on approaches, there may be times when RAIM is not available. The G900X automatically monitors RAIM and warns with an alert message when it is not available. If RAIM is not predicted to be available for the final approach course, the approach does not become active, as indicated by the messages "Approach is not active". If RAIM is not available when crossing the FAF, the missed approach procedure must be flown. 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-19 SYSTEM OVERVIEW Predicting RAIM availability: 1) Select the GPS Status Page. 2) Select the RAIM Softkey. 3) Press the FMS Knob. The `WAYPOINT' field is highlighted. 4) Turn the small FMS Knob to display the Waypoint Information Window. 5) Enter the desired waypoint and press the ENT Key (refer to Section 1.6 for instructions on data entry). Or: a) To use the present position, press the MENU Key. b) With `Set WPT to Present Position' highlighted, press the ENT Key. c) Press the ENT Key to accept the waypoint entry. 6) Enter an arrival time and press the ENT Key. 7) Enter an arrival date and press the ENT Key. 8) With the cursor highlighting `COMPUTE RAIM?', press the ENT Key. Once RAIM availability is computed, one of the following is displayed: · `COMPUTE RAIM?'--RAIM has not been computed for the current waypoint, time, and date combination · `COMPUTING AVAILABILITY'--RAIM calculation in progress · `RAIM AVAILABLE'--RAIM is predicted to be available for the specified waypoint, time, and date · `RAIM NOT AVAILABLE'--RAIM is predicted to be unavailable for the specified waypoint, time, and date SATELLITE INFORMATION Satellites currently in view are shown at their respective positions on a satellite constellation diagram. This sky view is always oriented north-up, with the outer circle representing the horizon, the inner circle representing 45° above the horizon, and the center point showing the position directly overhead. Each satellite is represented by an oval containing the Pseudo-random noise (PRN) number (i.e., satellite identification number). Satellites whose signals are currently being used are represented by solid ovals. The GPS Status Page can be helpful in troubleshooting weak (or missing) signal levels due to poor satellite coverage or installation problems. As the GPS receiver locks onto satellites, a signal strength bar is displayed for each satellite in view, with the appropriate satellite PRN number (01-32 or 120-138 for WAAS) below each bar. The progress of satellite acquisition is indicated by signal bar appearance: · No signal strength bar--Receiver is looking for the indicated satellite. · Hollow signal strength bar--Receiver has found the satellite and is collecting data. Each satellite has a 30second data transmission that must be collected (signal strength bar is hollow) before the satellite may be used for navigation (signal strength bar becomes solid). · Solid signal strength bar--Receiver has collected the necessary data and the satellite signal can be used. · Checkered signal strength bar--Receiver has excluded the satellite (Fault Detection and Exclusion; FDE). · "D" indication on signal strength bar--Satellite is being used for differential computations. 1-20 Garmin G900X Pilot's Guide 190-00726-00 Rev. B SYSTEM OVERVIEW Using the current satellite signal information, they system calculates the aircraft's GPS position, time, altitude, ground speed, and track for the aircraft (displayed below the satellite signal accuracy measurements for reference). The following quantities denote the accuracy of the aircraft's GPS fix: · Estimated Position Uncertainty (EPU)--A statistical error indication; the radius of a circle centered on an estimated horizontal position in which actual position has 95% probability of lying · Horizontal Dilution of Precision (HDOP)--Measures satellite geometry quality (i.e., number of satellites received and where they are relative to each other) on a range from 0.0 to 9.9, with lower numbers denoting better accuracy · Horizontal and Vertical Figures of Merit (HFOM and VFOM)--Measures of horizontal and vertical position uncertainty; the current 95% confidence horizontal and vertical accuracy values reported by the GPS receiver 190-00726-00 Rev. B Garmin G900X Pilot's Guide 1-21 SYSTEM OVERVIEW 1.5 G900X CONTROLS The G900X controls have been designed to simplify operation of the system and minimize workload and the time required to access sophisticated functionality. Controls are located on the PFD and MFD bezels, MFD/PFD Control Unit, and Audio Panel. PFD and MFD controls and softkeys are discussed in this section. Audio Panel controls are described in the Audio Panel and CNS section; see the Audio Panel and CNS Section for more information about NAV/COM controls. PFD/MFD CONTROLS 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 18 17 Figure 1-15 PFD/MFD Controls 1 2 3 4 5 NAV VOL/ID Knob Turn to control NAV audio volume (shown in the NAV Frequency Box as a percentage) Press to toggle Morse code identifier audio ON/OFF Transfers the standby and active NAV frequencies NAV Frequency Transfer Key Turn to tune NAV receiver standby frequencies (large knob for MHz; small for kHz) NAV Knob Press to toggle light blue tuning box between NAV1 and NAV2 Turn to manually select a heading Heading Knob Press to display a digital heading momentarily to the left of the HSI and synchronize the Selected Heading to the and current heading Turn to change map range Joystick Press to activate Map Pointer for map panning Garmin G900X Pilot's Guide 190-00726-00 Rev. B 1-22 SYSTEM OVERVIEW 6