LYNX MultiLink Surveillance System NGT-1000 Part Number 9021000-10000 NGT-2000 and NGT-2500 Part Number 9022500-10000 This manual contains installation instructions and recommended flightline maintenance information for the NGT-1000 and NGT-2000/-2500 MultiLink Surveillance System. Installation guidelines for external equipment necessary for installation are included. This information is supplemented and kept current by revisions, service letters and service bulletins. 0040-17011-01 (Revision G)
Foreword This manual provides information intended for use by persons who, in accordance with current regulatory requirements, are qualified to install this equipment. Installation requirements may vary, depending on the particularities of each aircraft, and this manual is intended as a guideline for that purpose. This manual assumes familiarity with the setup and operation of the aircraft systems that interface with the NGT-1000 or NGT-2000/-2500. If further information is required, please contact: L-3 Avionics Systems Attn: Field Service Engineering 5353 52 nd Street, S.E. Grand Rapids, MI USA 49512-9704 Telephone: (800) 453-0288 or (616) 949-6600 Fax: (616) 977-6898 Email: fieldservice.avionics@l-3com.com Web: http:///www.l-3avionics.com This manual is distributed with permission by: L-3 Avionics Systems 5353 52 nd Street, S.E. Grand Rapids, MI USA 49512-9704 Telephone: (800) 453-0288 or (616) 949-6600 Fax: (616) 977-6898 Email: avionics.techpubs@l-3com.com We welcome your comments concerning this manual. Although every effort has been made to keep it free of errors, some may occur. When reporting a specific problem, please describe it briefly and include the manual part number, the paragraph/figure/table number, and the page number. Send your comments to the address or email above: Disclaimer This contains information that is considered relevant only at the time of distribution with the Avionics Systems product for which it is shipped. Information in this manual is subject to change without notice. WARNING INFORMATION SUBJECT TO EXPORT CONTROL LAWS This technical data is controlled under the Export Administration Regulations (EAR) and may not be exported without proper authorization by the U.S. Department of Commerce. Copyright 2014, 2015 ACSS Refer to the following for additional copyright information https://www.l-3avionics.com/open-source.aspx https://www.l-3avionics.com/customer-support/flight-data-info/open-source-software-report.aspx Trademarks Lynx is a registered trademark of L-3 Avionics Systems Patent Pending Page A 0040-17011-01 Revision G
About This Manual SECTION 1 GENERAL INFORMATION This section provides the following information: unit configurations, unit functionality, items required but not supplied with the unit, equipment specifications, installation approval/limitations and TSO approvals. SECTION 2 - INSTALLATION This section contains instructions to locate, assemble and install the NGT-1000/-2000/-2500 as well as information for unpacking equipment, and inspection procedure for in-shipment damage. SECTION 3 INSTALLATION CHECKOUT This section contains instructions for post installation setup, post installation and return to service checkout. SECTION 4 MAINTENANCE This section contains general flightline maintenance procedures. It includes periodic maintenance, troubleshooting and instructions for the return of defective components. APPENDIX A SIGNAL AND CABLE CHARACTERISTICS This appendix defines the electrical characteristics of all input and output signals. APPENDIX B ENVIRONMENTAL QUALIFICATION FORM This appendix provides the environmental qualification test data. APPENDIX C CONFIGURATION AND CHECKOUT LOG This appendix provides a log sheet that may be used to record configuration options and aircraft information. Descriptions for Warnings, Cautions and Notes are described below and are used through the manual to highlight importuned information. WARNING Used to give notice to or call one's attention to beforehand especially of danger (such as a warning to a Flight Crew person or a warning to a mechanic before performing a dangerous task). CAUTION Statement that expresses the need for heightened awareness to conditions that can cause damage to equipment. NOTE Used to point out a procedure, event or practice that it is desirable to highlight. 0040-17011-01 Page i Revision G
References Service Literature None Description Publication Description 0040-17010-01 Pilot's Guide for the NGT-2000/-2500 0040-17012-01 Pilot's Guide for the NGT-1000 0040-17250-01 Pilots guide for the CP-2500 Control Panel 0040-17251-01 for the CP-2500 Control Panel To get an up-to-date listing of all Avionics Systems technical publications and service literature go to www.l-3avionics.com and click on the Customer Support tab and select Technical Publications. Contact Avionics Systems Customer Service [1-800-453-0288] to determine availability of technical publications and directives. Service literature and publications can be obtained by either downloading from the L-3 Technical Publications website (may require secure site access) or by receiving a copy via email. Send an email request to avionics.techpubs@l-3com.com. Page ii 0040-17011-01 Revision G
List of Effective Pages Dates of original and changed pages are: Revision A... October 22, 2014 Revision B... December 12, 2014 Revision C... December 17, 2014 Revision D... January 06, 2015 Revision E... February 20, 2015 Revision F... April 24, 2015 Revision G... Total number of pages in this publication consists of the following: Title page A Page i thru xii 1-1 thru 1-30 2-1 thru 2-16 3-1 thru 3-28 4-1 thru 4-22 A-1 thru A-18 B-1 thru B-2 C-1 thru C-2 REVISION G HIGHLIGHTS Revision G is a republication. This republication completely replaces the existing book. Discard all previous revisions of this manual. Change Page: Pg. 1-15: Update Table 1-8 by correcting boot loader part number for NGT-2000/-2500 release 1.2. Revision F Summary of Changes: Incorporate release 1.2 for NGT-2000/-2500. Add PIM-9000 and install kit. Corrections and updates to verbiage and procedures. 0040-17011-01 Page iii Revision G
Paragraph NGT-1000/-2000/-2500 Table of Contents Page Foreword... A About This Manual... i References... ii List of Effective Pages... iii Table of Contents... iv List of Illustrations... vii List of Tables... viii Abbreviations, Acronyms, and Symbols... ix Section 1 General Information 1.1 Introduction... 1-1 1.2 Functional Description... 1-3 1.2.1 NGT-1000... 1-3 1.2.2 NGT-2000/-2500... 1-4 1.2.3 GPS Functional Overview... 1-4 1.2.4 Multiple Source Inputs Operation... 1-4 1.2.5 Discrete Inputs and Outputs... 1-5 1.2.6 Transponder Interface... 1-5 1.2.7 ADS-B System Overview... 1-6 1.2.8 FIS-B Functional Overview... 1-6 1.2.9 Enhanced Visual Acquisition Functional Overview... 1-6 1.3 Equipment Descriptions... 1-7 1.3.1 System Unlock Code... 1-10 1.3.2 Detachable Configuration Module (DCM)... 1-10 1.4 Specifications... 1-11 1.5 TSO Information... 1-13 1.5.1 Non-TSO Functions... 1-14 1.5.2 Incomplete-TSO Application... 1-14 1.5.3 Failure Classification... 1-14 1.6 Modifications... 1-15 1.7 Software Revisions... 1-15 1.8 Interfaces... 1-15 1.9 Equipment Required Not Supplied... 1-16 1.9.1 Antenna Cables... 1-19 1.10 Equipment Interfaces... 1-20 1.10.1 GPS Antenna... 1-20 1.10.2 L-Band (UAT) Antenna... 1-21 1.10.3 Traffic Displays... 1-21 1.10.4 Weather Display... 1-22 1.10.5 Control Panel... 1-22 1.10.6 WIFI Serial Adapter... 1-23 1.11 Applications (APPS)... 1-23 1.12 Software Updates... 1-24 1.12.1 Website Download... 1-24 1.12.2 Compact Disc... 1-24 1.12.3 Installation Procedure for Lynx MSS USB Driver... 1-25 1.13 Installation Approval and Limitations... 1-29 Page iv 0040-17011-01 Revision G
Paragraph Table of Contents (cont.) Page Section 2 Installation 2.1 Introduction... 2-1 2.2 Unpacking and Inspecting... 2-1 2.2.1 Transport and Storage Considerations... 2-1 2.3 Installation Procedures... 2-2 2.3.1 Location... 2-2 2.3.2 Antenna Installation Guidelines... 2-13 2.3.3 NGT-1000/-2000/-2500 Installation... 2-16 2.3.4 CP-2500 Installation Guidelines... 2-16 Section 3 Installation Checkout 3.1 Introduction... 3-1 3.2 Basic Operation... 3-1 3.2.1 CP-2500 Control Panel... 3-2 3.3 Maintenance PC... 3-4 3.4 Configure WiFi Serial Adapter... 3-6 3.5 Verify Software Revision... 3-7 3.6 Select Configuration Options... 3-8 3.6.1 Aircraft Options... 3-8 3.6.2 Altitude Options... 3-12 3.6.3 Config Settings 1... 3-13 3.6.4 Config Settings 3... 3-14 3.6.5 RS-422/RS-232 Options... 3-15 3.6.6 Backup... 3-15 3.6.7 Clear Fault Log... 3-16 3.7 Upgrade Model... 3-17 3.8 Installation Checkout... 3-18 3.8.1 UAT GPS Status... 3-20 3.8.2 UAT GPS Functional Status... 3-21 3.8.3 Indicator Lamp Check... 3-23 3.8.4 Discrete Switch Checks... 3-23 3.8.5 Control Panel Check... 3-23 3.8.6 Display Check... 3-23 3.8.7 PED Check... 3-24 3.8.8 GPS Operation Check... 3-24 3.8.9 ADS-B Out Check... 3-25 3.8.10 ADS-B In Check... 3-25 3.8.11 FIS-B Uplink Check... 3-26 3.8.12 Altitude Check... 3-26 3.8.13 Electromagnetic Interference (E.M.I.) Check... 3-27 3.8.14 Flight Test... 3-28 3.8.15 Installation Checkout Complete... 3-28 0040-17011-01 Page v Revision G
Paragraph Table of Contents (cont.) Page Section 4 Maintenance 4.1 Introduction... 4-1 4.2 Continued Airworthiness... 4-1 4.2.1 Periodic Maintenance... 4-1 4.3 Fault Isolation... 4-2 4.4 Using the Maintenance PC... 4-8 4.4.1 Load Software... 4-8 4.4.2 View or Retrieve Data... 4-9 4.4.3 Configuration Restore... 4-13 4.4.4 Service... 4-16 4.5 Return to Service... 4-17 4.5.1 NGT-1000... 4-17 4.5.2 NGT-2000/-2500... 4-18 4.5.3 Detachable Configuration Module... 4-20 4.5.4 L-Band (UAT) Antenna... 4-20 4.5.5 GPS Antenna... 4-20 4.6 Disposition of Failed Items... 4-21 Appendix A Signal Name & Cable Characteristics A.1 Introduction...A-1 A.2 Input and Output Interfaces...A-1 A.2.1 Input Power...A-1 A.2.2 I 2 C Serial Bus (Detachable Configuration Module)...A-1 A.2.3 RF Suppression Bus...A-1 A.2.4 Gillham Input (Altitude Input)...A-1 A.2.5 ARINC 429 Output...A-2 A.2.6 Discrete Input...A-3 A.2.7 Discrete Output...A-3 A.2.8 RS-422 Interface...A-4 A.2.9 RS-232 Interface...A-4 A.3 Pin Definition Summary...A-5 A.4 Connector [J2]...A-6 Appendix B Environmental Qualification Form B.1 Introduction...B-1 B.2 Environmental Qualification Form...B-1 Appendix C Configuration and Checkout Log Checkout Log... C-1 Page vi 0040-17011-01 Revision G
List of Illustrations Figure Page 1-1: System Interface Overview... 1-3 1-2: NGT-1000 Block Diagram... 1-8 1-3: NGT-2000 Block Diagram... 1-9 1-4: NGT-2500 Block Diagram... 1-9 2-1: Outline Dimensions for NGT-1000 and NGT-2000/-2500... 2-3 2-2: NGT-1000 Interconnect Diagram... 2-6 2-3: NGT-2000/-2500 Interconnect Diagram... 2-8 2-4: Mating Connector (P2) and Pin Assignments... 2-10 2-5: Mating Connector (P2) Assembly... 2-11 2-6: Outline Dimensions for the DCM... 2-12 2-7: Example of Antenna Mounting Locations... 2-13 3-1: CP-2500 Normal Mode... 3-3 3-2: Lynx Maintenance Appliance Tool Main Page... 3-5 3-3: Lynx MAT Example of Main Screens... 3-5 3-4: Lynx MAT WiFi Serial Adapter... 3-6 3-5: Lynx MAT Example of Check Versions... 3-7 3-6: Lynx MAT Aircraft Options... 3-8 3-7: Example of FAA Registry Website... 3-9 3-8: Lynx MAT Altitude Options... 3-12 3-9: Lynx MAT-Config Settings 1... 3-13 3-10: Lynx MAT - Config Settings 3... 3-14 3-11: Lynx MAT - RS-422/RS-232 Options... 3-15 3-12: Lynx MAT - Configuration Backup... 3-16 3-13: Lynx MAT Fault Log... 3-16 3-14: Lynx MAT Upgrade Model... 3-17 3-15: Lynx MAT Ground Test... 3-19 3-16: Lynx MAT UAT GPS Status... 3-20 3-17: Lynx MAT UAT GPS Status... 3-21 3-18: Lynx MAT Live Data-GPS... 3-24 4-1 Example of Software Loading... 4-8 4-2 Upload Complete... 4-9 4-3 Lynx MAT- Information... 4-9 4-4 Lynx MAT- Version... 4-10 4-5: Lynx MAT Restore Configuration... 4-13 4-6: Lynx MAT Restore Configuration... 4-14 4-7: Lynx MAT Service... 4-16 0040-17011-01 Page vii Revision G
List of Tables Table Page 1-1: MultiLink Surveillance System Components... 1-1 1-2: General Description... 1-2 1-3: NGT-1000/-2000/-2500 Built-In Interfaces... 1-8 1-4: Specifications for the NGT-1000/-2000/-2500... 1-11 1-5: Specifications for Detachable Configuration Module... 1-12 1-6: NGT-1000/-2000/-2500 Applicable TSO & Deviations... 1-13 1-7: Hardware Modifications... 1-15 1-8: Software Revisions... 1-15 1-9: Equipment List... 1-16 1-10: Coaxial Cable Specifications... 1-19 1-11: GPS Antennas... 1-20 1-12: L-Band (UAT) Antennas... 1-21 1-13: Traffic Displays... 1-21 1-14: FIS-B WX Displays... 1-22 1-15: Control Panels... 1-22 1-16: RS-232 to WiFi Serial Adapter... 1-23 1-17: APPS for PED... 1-23 1-18: CD Part Numbers and Contents... 1-24 2-1: Maximum UAT Antenna to Transponder Antenna Separation... 2-15 3-1: UAT GPS Functional Status... 3-22 4-1: Troubleshooting... 4-3 4-2: List of Fault Log Messages... 4-11 A-1: Connector (P2) Pin Assignments... A-5 C-1: Log Sheet for Configuration and Checkout (Sheet 1 of 2)... C-1 Page viii 0040-17011-01 Revision G
Abbreviations, Acronyms, and Symbols ITEM DEFINITION Degrees C Degrees Celsius F Degrees Fahrenheit 1090ES AC ACSS ADS-B ADS-R AHRS AIRB APP ARINC ASA ASSAP ATC ATCRBS ATM AWG BIT Cal CCW CDTI CFR CONUS CW db dbm dc DCM DL DME DO- 1090 megahertz extended squitter Advisory Circular Aviation Communication and Surveillance Systems Automatic Dependent Surveillance-Broadcast Automatic Dependent Surveillance - Rebroadcast Attitude & Heading Reference System Basic Airborne Situation Awareness Application Aeronautical Radio, Incorporated Aircraft Surveillance Applications Airborne Surveillance and Separation Assurance Processing Air Traffic Control Air Traffic Control Radar Beacon System Air Traffic Management American Wire Gauge Built In Test Calibration Counter Clock Wise Cockpit Display of Traffic Information Code of Federal Regulations Continental United States Clock Wise Decibel Decibels referenced to one Milli-watt Direct Current Detachable Configuration Module Data Loading Distance Measuring Equipment RTCA Document Number Prefix (i.e., DO-160) 0040-17011-01 Page ix Revision G
Abbreviations, Acronyms, and Symbols ITEM DTIF EMI ETX EVAcq FAA FAR FCC FIS-B FPGA FSS Ft FW g GPS H/W hpa Hz ICAO i.e. IAW ID in Hg Kg khz Kts DEFINITION Display Traffic Information File Electro-Magnetic Interference End of Transmission Enhanced Visual Acquisition Application Federal Aviation Administration Federal Aviation Regulations Federal Communications Commission Flight Information Services - Broadcast Field Programmable Gate-Array Flight Service Station feet Firmware Gravitational Acceleration Global Positioning System Hardware Hectopascal Hertz International Civil Aviation Organization That is In Accordance With Identification Inches of Mercury Kilogram Kilohertz Knots L-3 AS L-3 Communications Avionics Systems LLC LRU Lynx MAT m Max MHz Limited Liability Company Line Replaceable Unit Maintenance Application Tool Meter Maximum Megahertz Page x 0040-17011-01 Revision G
Abbreviations, Acronyms, and Symbols ITEM DEFINITION mm MPC MSS N/A NACp NAS NC NEXRAD NGT NIC NiMH No. NOTAM NVM Orig P/N PBIT PED PFD PPM RAIM RF RTCA RTS S/N S/W SBAS SPI STB STC STIF SUA Millimeter Maintenance Personal Computer MultiLink Surveillance System Not Applicable Navigation Accuracy Category for position National Airspace System Not Connected Next Generation Radar Reflectivity Not an abbreviation Navigation Integrity Category Nickel Metal Hydride Number Notice to Airmen Non-Volatile Memory Original Part Number Periodic Built-In Test Personal Electronic Device (i.e. Tablet or Smartphone) Primary Flight Display Parts Per Million Receiver Autonomous Integrity Monitoring Radio Frequency RTCA, Inc. Request to Send Serial Number Software Satellite Based Augmentation systems Special Position Identification Standby Supplemental Type Certification Standard TCAS Intruder File Special Use Airspace 0040-17011-01 Page xi Revision G
Abbreviations, Acronyms, and Symbols ITEM DEFINITION SURF TAF TAS TCAS TFR TIS-B TSAA TSO UAT USB UTC Vdc VHF VOR W WAAS WiFi WOW Wx Basic Surface application Terminal Area Forecasts Traffic Advisory System Traffic Alert and Collision Avoidance System Temporary Flight Restrictions Traffic Information Service Broadcast Traffic and Situational Awareness Alerts Technical Standard Order Universal Access Transceiver Universal Serial Bus Coordinated Universal Time Volts Direct Current Very High Frequency VHF Omni-directional Watts Wide Area Augmentation System Wireless Fidelity Weight On Wheels Weather Page xii 0040-17011-01 Revision G
Section 1 General Information 1.1 INTRODUCTION This section includes descriptions, specifications, TSO information, and installation approval and limitations for the NGT-1000, NGT-2000, and NGT-2500 MultiLink Surveillance System (MSS). The MultiLink Surveillance System (also referred to as the Lynx MSS UAT Device) includes a NGT-1000, NGT-2000, or NGT-2500 device and a Detachable Configuration Module. The system requires additional 3 rd party components. A list of system components is provided in Table 1-1. Refer to Table 1-2 for a general description of the NGT-1000/-2000/-2500. See Figure 1-1 for an overview of the unit s system interface. Included at the end of this section is a list of compatible equipment and equipment required but not supplied with the system. Table 1-1: MultiLink Surveillance System Components COMPONENT MODELS H/W PART NO. S/W PART NO. (2) NGT-1000 9021000-10000 9021105-005 Lynx MSS UAT Device NGT-2000 9022500-10000 9021105-006 NGT-2500 (1) Detachable Configuration Module DCM 9230-17003-01 - - GPS Antenna See Table 1-11 - - - - L-Band Antenna See Table 1-12 - - - - Control Panel See Table 1-15 - - - - Traffic Display (NGT-2500 Only) See Table 1-13 - - - - Weather Display (NGT-2500 Only) See Table 1-14 - - - - Notes: (1) The NGT-2500 configuration requires an unlock code that is set up during installation. See paragraph 1.3.1. (2) Details on software releases are located in Table 1-8. 0040-17011-01 General Information Page 1-1 Revision G
Table 1-2: General Description MODEL DESCRIPTION INTERFACES/FUNCTIONS NGT-1000 NGT-2000 NGT-2500 Supports GPS, ADS-B OUT Supports GPS, ADS-B IN/OUT, and WiFi. Supports GPS, ADS-B IN/OUT, WiFi, and interfaces with traffic (RS-232 and ARINC 429 only) and weather (RS- 232 and RS-422 only) displays. Maintenance Port Altitude data input (pressure altitude) Squawk code interception/comparator Detachable Configuration Module GPS Antenna UAT L-Band Antenna Remote IDENT switch RS-232 Control Panel Interface Status indicator outputs Operate/Standby switch Maintenance Port Altitude data input (pressure altitude) Squawk code interception/comparator Detachable Configuration Module GPS Antenna UAT L-Band Antenna Remote IDENT switch RS-232 output to which an external WiFi adapter can be connected RS-232 Control Panel Interface Status indicator outputs Coverage indicator output Operate/Standby switch Maintenance Port Altitude data input (pressure altitude) Squawk code interception/comparator Detachable Configuration Module GPS Antenna UAT L-Band Antenna Remote IDENT switch RS-232 output to which an external WiFi adapter can be connected RS-232 Control Panel Interface Status indicator outputs Coverage indicator output Operate/Standby switch ARINC 429 output to drive a Traffic Display terminal. (STIF) (DTIF is a future option) RS-422 output for standard RS-422 displays. (weather only, traffic is a future option) Page 1-2 General Information 0040-17011-01 Revision G
Figure 1-1: System Interface Overview 1.2 FUNCTIONAL DESCRIPTION 1.2.1 NGT-1000 The NGT-1000 contains an integrated GPS receiver and UAT transceiver providing output functionality of the Automatic Dependent Surveillance Broadcast (ADS-B). The integrated GPS receiver provides own aircraft information (position, velocity, track (or ground track), etc.) for ADS-B Out messages. The GPS is not intended as a position source to a navigation management unit that outputs deviation commands keyed to a desired flight path. The ADS-B datalink transmits using the 978 MHz Universal Access Transceiver (UAT). The ADS-B out function improves situational awareness and flight safety by providing aircraft position, velocity, and heading/track information that is automatically transmitted to other aircraft and ground stations providing immediate surveillance of air-to-air traffic. The unit uses a DCM that is installed in the wiring bundle of the mating connector to store configuration data. The following paragraphs provide an overview of each of these functions. The unit is equipped with IDENT capability that activates the Special Position Identification (SPI) pulse for 18 seconds. When permitted, the transmission of own ship identification can be inhibited using the Anonymous Mode function provided by the CP-2500 control panel. This may only be accomplished when VFR Mode is active. 0040-17011-01 General Information Page 1-3 Revision G
1.2.2 NGT-2000/-2500 The NGT-2000/-2500 contains an integrated GPS receiver and UAT transceiver providing input and output functionality of the Automatic Dependent Surveillance Broadcast (ADS-B). Depending on the model/configuration, the unit has ARINC 429, RS-422 (Wx out only), and RS-232 data ports used to interface with traffic (RS-232 and ARINC 429 only), weather (RS-232 and RS-422 only) displays. The unit uses a DCM that is installed in the wiring bundle of the mating connector to store configuration data. The following paragraphs provide an overview of each of these functions. The integrated GPS receiver provides own aircraft information (position, velocity, track (or ground track), etc.) for ADS-B Out messages and traffic display. The GPS is not intended as a position source to a navigation management unit that outputs deviation commands keyed to a desired flight path. The ADS-B datalink receives and transmits using the 978 MHz Universal Access Transceiver (UAT). The ADS-B out function improves situational awareness and flight safety by providing aircraft position, velocity, and heading/track information (DTIF displays only) that is automatically transmitted to other aircraft and ground stations providing immediate surveillance of air-to-air traffic. The ADS-B In function provides own aircraft with Enhanced Visual Acquisition (EVAcq) traffic information and Flight Information Service Broadcast (FIS-B). The NGT-2000/-2500 Interfaces with RS-232 compatible transponders for the input of the Mode A squawk Code and mode of operation from the aircraft s existing Air Traffic Control Radar Beacon System (ATCRBS) transponder or through a dedicated MODE A control panel interface. The unit is equipped with IDENT capability that activates the Special Position Identification (SPI) pulse for 18 seconds. When permitted, the transmission of own ship identification can be inhibited using the Anonymous Mode function provided by the CP-2500 control panel. This may only be accomplished when VFR Mode is active. 1.2.3 GPS Functional Overview The GPS function utilizes signals from Global Positioning System (GPS) satellite constellation and Satellite-Based Augmentation Systems (SBAS) such as the USA Wide Area Augmentation System (WAAS), European EGNOS, Indian GAGAN and the Japanese MSAS. Currently it supports WAAS and WAAS compatible SBAS systems. This internal GPS function provides position, velocity, time and integrity (NIC, NAC etc) information to the ADS-B functions and is ADS-B rule compliant with the position source requirements of AC20-165A. 1.2.4 Multiple Source Inputs Operation The NGT-1000/-2000/-2500 have multiple altitude source connections available. There is an option, through the detachable configuration module (DCM), for connecting RS-232 serial altitude source or Grey code altitude source, however only one source can be connected at a time. The pressure altitude source is a required input and must be the same source used for the mode "C" transponder if so equipped. Page 1-4 General Information 0040-17011-01 Revision G
1.2.5 Discrete Inputs and Outputs The NGT-1000/-2000/-2500 have discrete inputs and outputs that can be used in place of some functions that are not available to equipment that is compatible with the NGT-1000/-2000/-2500. See Figure 1-1. The discrete input is typically active (ON) when the input is grounded. The WOW input discrete is optional. The input signals the On Ground status to the NGT-1000/- 2000/-2500 via a gear switch, squat switch, airspeed monitor, or a collective switch. The IDENT switch is optional. It is required only if command to activate the SPI and transmit an IDENT pulse is not available with other equipment. It is recommended when using the CP-2500 to allow IDENT entry to both the transponder and the UAT device with one button push. An IDENT pulse highlights the aircraft s symbol on the ATC s radar screen and is identified on the control panel when active. The Standby/Operate Switch is required if a CP-2500 is not a part of the installation. It is used to interrupt ADS-B out transmission (standby position). Setting this discrete to Standby inhibits UAT transmissions and turns the ADS-B Out Fail lamp ON. Note - This discrete input is disabled when using a CP-2500. ADS-B Out Fail Lamp is required if a CP-2500 is not a part of the installation and is recommended when the CP-2500 is part of the installation. The lamp provides the following indications: 1. If the Fail lamp is flashing at a fast rate (2 flashes per second), then a Mode A code mismatch is detected between the XPDR Out and the UAT-Out. 2. If the Fail lamp is flashing at a slow rate (1 flash per 2 seconds), then the unit is unable to transmit GPS position data because the aircraft position information is invalid (GPS is acquiring satellites). Note - The lamp stops flashing and remains illuminated (ON) after 2 minutes if GPS satellites are not acquired. 3. If the Fail lamp turns ON and does not flash, then the unit is unable to transmit due to a detected failure. Note - This can also be caused by the CP-2500 or the Operate/Standby switch set to "Standby. The No ADS-B Coverage lamp is required by the NGT-2000/-2500 if the CP-2500 is not installed. The lamp is used to indicate that the unit is not receiving an ADS-B ground station signal. 1.2.6 Transponder Interface If the aircraft is equipped with a non-compatible transponder, then the aircraft needs a CP-2500 Control Panel installed. When used with the CP-2500, the NGT-1000/-2000/-2500 can wirelessly intercept the Mode A squawk Code from the aircraft s existing ATCRBS transponder and conduct a cross check between the transponder broadcast value and the setting of the NGT-1000/-2000/-2500 Mode A control panel setting to ensure the consistency in selected Mode A squawk code selections. If the code entered from the control panel does not match the Mode A response from the transponder, then a Mode A mismatch failure message is displayed on the control panel and the last known mode A Code is used in the UAT Message transmissions. Pilot action is required to assure that the codes set into the transponder and the CP-2500 always match. If the aircraft is not equipped with a transponder, then the CP-2500 control panel is required to provide squawk code data and operation mode control (i.e. Standby, On, ALT modes). Compatible transponders are listed in Table 1-15 in paragraph 1.10.5. 0040-17011-01 General Information Page 1-5 Revision G
1.2.7 ADS-B System Overview The Automatic Dependent Surveillance-Broadcast (ADS-B) improves situational awareness and flight safety by providing real time traffic information. The ADS-B Out function used by the NGT-1000/-2000/-2500 is used to periodically broadcast (without interrogation) information on a 978 MHz UAT link about the aircraft that includes aircraft identification, position, altitude, velocity and other aircraft status information. The ADS-B In function used by the NGT-2000/-2500 is used to receive ground station supported TIS-B and ADS-R traffic, and direct communication with nearby like equipped aircraft (UAT) using ADS-B Out. The traffic display shows the relative position of ADS-B or standard traffic using text, shapes, and colors. ADS-B also provides similar information on ADS-B equipped ground vehicles. The effective surveillance range is 60 nmi and is capable of maintaining report messages for a minimum of 120 UAT ADS-B participants simultaneously. To reduce display clutter, only a set number of other aircraft of the highest priority are displayed at a time. 1.2.8 FIS-B Functional Overview The Flight Information Services - Broadcast (FIS-B) function used by the NGT-2000/-2500 provides pilots with a cockpit display of certain aviation weather and aeronautical information for awareness of own aircraft location with respect to reported weather, including hazardous meteorological conditions (CONUS NEXRAD /AIRMETS/ SIGMETS/ NOTAMS/ METARS, etc) and SUA status and TAF (FIS-B products). NOTE CONUS and Regional NEXRAD may not always contain complete data. The data is refreshed every 15 minutes and it is likely to be updated in a future cycle. FIS-B is advisory information only and is intended to enhance pilot decision-making during strategic flight planning. FIS-B augments traditional sources of this information such as ATC and Flight Service Station (FSS). FIS-B information is provided over the ADS-B Services network on the 978 MHz UAT link when in ground station coverage. 1.2.9 Enhanced Visual Acquisition Functional Overview The Enhanced Visual Acquisition (EVAcq) function used by the NGT-2000/-2500 provides flight crews with a display of nearby traffic relative to own aircraft (Cockpit Display of Traffic Information Traffic Display) to assist with visually acquiring traffic out the window and provide traffic situational awareness beyond visual range. Each displayed traffic symbol conveys aircraft position, vertical trend and altitude information (if available). Traffic on the display (i.e. STIF/CDTI displays or some PED applications) can be selected by the flight crew to obtain additional traffic information such as flight identification and ground speed. The EVAcq function can display traffic on either an integrated traffic display (STIF or DTIF) or an external traffic display (i.e. PED). The maximum number of other aircraft sent to the display is dependent on the interface detailed below: ARINC 429 STIF: 28 In-air aircraft RS-422: 30 In-air and 30 On-Ground aircraft (future option) RS-232: 30 In-air and 30 On-Ground aircraft Data received via a UAT link (Ground stations- when in a coverage area) is the ADS-R Rebroadcast and TIS-B Traffic Information Service Broadcast (traffic information used by EVAcq). ADS-B (UAT) traffic can also be received directly from another UAT equipped aircraft. TIS-B traffic and ADS-R traffic can only be received when in the coverage area of an ADS-B ground station. Page 1-6 General Information 0040-17011-01 Revision G
1.3 EQUIPMENT DESCRIPTIONS The NGT-1000/-2000/-2500 are equipped with a main 62 pin sub-d connector (J2) and RF connectors (UAT and GPS). A USB port (J1) is available to establish communication between the unit and a maintenance computer for installation and maintenance activities. Table 1-3 describes the available builtin interfaces. The NGT-1000 is capable of ADS-B out only. Figure 1-2 shows the NGT-1000 system interface. The NGT-2000/-2500 is capable of the following functionality; ADS-B out, ADS-B in: UAT, ADS-R, TIS-B (traffic), FIS-B weather, TFRs, and NOTAMS. Figure 1-3 shows the NGT-2000 system interface. Figure 1-4 shows the NGT-2500 system interface. The NGT-2000/-2500 provides an RS-232 output that can be used to display UAT ADS-B traffic as well as FIS-B weather information when an external WiFi Serial Adapter is connected to transmit the received weather data to a commercial PED (i.e. Personal Electronic Device) like a PED. The NGT-2500 outputs ARINC 429 to interface with an onboard cockpit display of traffic information display (STIF or DTIF) for the display of own ship (DTIF only) and traffic information. The NGT-2500 can interface with a RS-422 data bus output that may be interfaced to a display to provide weather or traffic (future option) information. The ADS-B Out function is used to broadcast (without interrogation) periodic information about the aircraft that includes aircraft identification, position, altitude, velocity and other aircraft status information. The UAT ADS-B In function supports the reception of ADS-B on a 978 MHz UAT link. The ADS-B In data contains information about proximate UAT aircraft such as aircraft position, velocity, direction, etc. and also receives FIS-B, ADS-R and TIS-B data from ground stations (when within ground station coverage areas). The FIS-B function provides pilots and flight crews with a cockpit display of certain aviation weather and aeronautical information for awareness of own aircraft location with respect to reported weather, including hazardous meteorological conditions and NAS status indicators. FIS-B is advisory information only and is intended to enhance pilot decision-making during strategic flight planning. FIS-B augments traditional sources of this information such as ATC, Flight Service Station (FSS), and Aircraft Operational Communications Center. FIS-B information is provided over the ADS-B Services network on the 978 MHz UAT link when within ground station coverage areas. Refer to Appendix A for detailed information on the interface options. The traffic and weather (RS-232) display interfaces are available to the NGT-2000. The traffic (RS-232 and ARINC 429 only) and weather (RS-232 and RS-422 only) display interfaces are available to the NGT-2500. An unlock code is required to activate the NGT-2500 from the NGT-2000/-2500 platform. See paragraph 1.3.1. 0040-17011-01 General Information Page 1-7 Revision G
Table 1-3: NGT-1000/-2000/-2500 Built-In Interfaces Interface (no.) Model Functionality ARINC 429 Output (1) NGT-2500 Transmit to a display(stif or DTIF) RS-232 Input / Output (2) NGT-1000/-2000/-2500 NGT-2000/-2500 Control panel port Wi-Fi accessory port RS-232 Input (1) NGT-1000/-2000/-2500 Altitude Encoder port RS-422 Input / Output (1) Discrete Inputs (14) Discrete Output (4) NGT-2500 NGT-1000/-2000/-2500 NGT-1000/-2000/-2500 NGT-2000/-2500 Communicate with an external display port. Traffic is a future option. Receive Gillham Altitude Encoder, IDENT Command, In Air / On Ground status, Standby / Operate Transmit ADS-B Out Fail RF Suppression Output No ADS-B Coverage. I2C Port (1) NGT-1000/-2000/-2500 DCM GPS Antenna Port L-Band Antenna Port NGT-1000/-2000/-2500 NGT-1000/-2000/-2500 Connect to a top mount antenna providing GPS data to support ADS-B functionality Connects to the bottom mount antenna. Provides UAT 978 MHz input and output to support ADS-B functionality. Figure 1-2: NGT-1000 Block Diagram Page 1-8 General Information 0040-17011-01 Revision G
Figure 1-3: NGT-2000 Block Diagram Figure 1-4: NGT-2500 Block Diagram 0040-17011-01 General Information Page 1-9 Revision G
1.3.1 System Unlock Code An unlock code is required if installing the NGT-2500 model option. The unlock code is a 10 digit code that is used during installation and requires the Lynx MAT to configure the unit. Contact L-3 Avionics Systems Customer Service to obtain the code. 1.3.2 Detachable Configuration Module (DCM) The DCM part number 9230-17003-01 is part of the NGT-1000/-2000/-2500 system and is used for the storage of configuration data. The DCM is permanently installed with the wire harness and interfaces to the unit via a 4 wire interface from the DCM. The configuration settings are stored in the unit s non-volatile memory and are entered via commands sent over the maintenance interface to configure such items as: I/O port allocation (e.g. which external equipment is tied to RS-232 and ARINC 429 Tx lines, etc.). Aircraft Configuration Data (specific aircraft ID information, unique ICAO address, make, model, registration, etc). Mode A Control Panel (RS-232) Optional equipment installation settings. Page 1-10 General Information 0040-17011-01 Revision G
1.4 SPECIFICATIONS Table 1-4: Specifications for the NGT-1000/-2000/-2500 PART NUMBER: CERTIFICATION: (NGT-1000) CERTIFICATION: (NGT-2000/-2500) ADVISORY CIRCULARS: (NGT-1000) ADVISORY CIRCULARS: (NGT-2000/-2500) COMPLIANCE: RTCA COMPLIANCE: FCC: SIZE: WEIGHT: CHASSIS GROUND: POWER REQUIREMENTS: ELECTRICAL CONNECTORS: 9021000-10000 (NGT-1000) 9022500-10000 (NGT-2000/-2500) Details on software revisions are provided in Table 1-8. TSO-C145c, C154c. For more information on TSO information, refer to paragraph 1.5. Listed are current certifications at time of publication, contact Field Service Engineering for latest certification information. TSO-C145c, C154c, C157a, C195a. For more information on TSO information, refer to paragraph 1.5. Listed are current certifications at time of publication, contact Field Service Engineering for latest certification information. AC 20-165A (ADS-B Out), AC 20-138D (GPS) AC 20-165A (ADS-B Out), AC 20-172A (ADS-B In), AC 20-138D (GPS), AC 20-149A (FIS-B) The NGT-1000/-2000/-2500 have been shown to comply with TSO- C154c and AC 20-165A and are eligible for use as an ADS-B Out Transmitter meeting the UAT requirements of 14 CFR 91.225 (b) and 91.227 when installed in accordance with L-3 s installation instructions. Environmental Category: DO-160G (See Environmental Qualification Form in Appendix B.) Software Category: DO-178B, Level C Hardware Category: DO-254 Level C Other: DO-229D, DO-282B, FAR 91.227 (NGT-2000/-2500 only) DO-317A, DO-267A FCC Identifier 2ACTZMSS25 Height 2.8 inch [71 mm] Width 4.5 inch [114 mm] Length 5.7 inch [145 mm] 2.0 lb Max [0.91Kg] Bonding impedance between aircraft ground and the NGT-1000/- 2000/-2500 chassis must be less than 2.5 milliohms. Main Power 14 Vdc/28 Vdc, 8.9 watts nominal, Maximum 11.5 watts with all external interfaces enabled. J1 is a Mini-B USB connection (5 pin) Maintenance Port J2 [62 pin] Mates with P/N M24308/2-14 (TE connectivity) or L- 3AS P/N 9001640-002 with backshell P/N 3050-17000-01 (See installation kit P/N 9060-17250-01) TNC Connectors (2) (GPS & UAT) 0040-17011-01 General Information Page 1-11 Revision G
Table 1-4: Specifications for the NGT-1000/-2000/-2500 UAT: OPERATING TEMPERATURE: STORAGE TEMPERATURE: MAXIMUM ALTITUDE: SCHEDULED MAINTENANCE: SERVICE LIFE: REPAIRABILITY: Frequency 978 MHZ Receiver Sensitivity Traffic Messages: Exceeds 90% MSR @ -93 dbm() Weather Messages: Exceeds 90 % MSR @ -91 dbm() Transmit power- 40 W Nominal Equipment Class A1S ( Single bottom UAT Antenna) -45 to +70 C (-49 to +158 F) -55 to +85 C (-67 to +185 F) 25,000 ft (5486 meters) NOTE: The unit is tested at 25,000 ft (5486 meters), however the UAT device is restricted to 18,000 ft for transmit (per FAR 91.225). None The unit has unlimited service life. Repairs performed at the FAA certificated Repair Station. Table 1-5: Specifications for Detachable Configuration Module PART NUMBER: 9230-17003-01 CERTIFICATION: RTCA COMPLIANCE: WEIGHT: SIZE: POWER REQUIREMENTS: INTERFACE (S): OPERATING TEMPERATURE: STORAGE TEMPERATURE: MAXIMUM ALTITUDE: SCHEDULED MAINTENACE: SERVICE LIFE: REPAIRABILITY: TSO-C145c, C154c, C157a, C195a. For more information on TSO information, refer to paragraph 1.5. Listed are current certifications at time of publication, contact Field Service Engineering for latest certification information. The DCM is tested as part of the NGT-1000/-2000/-2500 Negligible Length: 6 inches (includes wires and pins) 3.3 Vdc (regulated via J2 connector) Serial interface -40 to +70 C (-40 to +158 F) -55 to +85 C (-67 to +185 F) 55,000 ft (installation environment) None. Unlimited. Replacement only. Page 1-12 General Information 0040-17011-01 Revision G
1.5 TSO INFORMATION NOTE Unless otherwise specified Release 1 refers to Release 1.0, Release 1.1 and any subsequent minor changes to Release 1.0. The NGT-1000/-2000/-2500 Release 1 and DCM Release 1 meet the requirements of the following TSO s. Table 1-6: NGT-1000/-2000/-2500 Applicable TSO & Deviations TYPE DESIGNATION / HW PART NO / SW PART NO DESCRIPTION APPLICABLE TSO & DEVIATIONS CLASS, COMMENTS NGT-2500 1.0 9022500-10000 9021105-001 NGT-2500 1.1 9022500-10000 9021105-003 NGT-2500 1.2 9022500-10000 9021105-006 NGT-1000 1.0 9021000-10000 9021105-005 NGT-2000 contains an internal WAAS GPS and UAT-978. Supports ADS-B In/Out, and WiFi. NGT-2500 contains an internal WAAS GPS and UAT-978. Supports ADS-B In/Out, WiFi, and interfaces with traffic (RS-232 and ARINC 429 only) and weather (RS-232 and RS-422 only) displays. NGT-2000 contains an internal WAAS GPS and UAT-978. Supports ADS-B In/Out, and WiFi. NGT-2500 contains an internal WAAS GPS and UAT-978. Supports ADS-B In/Out, WiFi, and interfaces with traffic (RS-232 and ARINC 429 only) and weather (RS-232 and RS-422 only) displays. NGT-2000 contains an internal WAAS GPS and UAT-978. Supports ADS-B In/Out, and WiFi. NGT-2500 contains an internal WAAS GPS and UAT-978. Supports ADS-B In/Out, WiFi, and interfaces with traffic (RS-232 and ARINC 429 only) and weather (RS-232 and RS-422 only) displays. Contains an internal WAAS GPS and UAT- 978. Supports ADS-B OUT. TSO-C145c Deviation Note 1, 2, 3 TSO-C154c Deviation Note 3, 4 TSO-C157a Deviation Note 2, 3 TSO-C195a Deviation Note 2, 3 TSO-C145c Deviation Note 1, 2, 3 TSO-C154c Deviation Note 3, 4 TSO-C157a Deviation Note 2, 3 TSO-C195a Deviation Note 2, 3 TSO-C145c Deviation Note 1, 2, 3 TSO-C154c Deviation Note 3, 4 TSO-C157a Deviation Note 2, 3 TSO-C195a Deviation Note 2, 3 TSO-C145c Deviation Note 1, 2, 3 TSO-C154c Deviation Note 3, 4 Class Beta 1 (GPS SBAS Output) Class A1S (UAT In/Out) Class 2 Incomplete (FIS-B Display) Class C1 (ASSAP and ARINC 735 based traffic display Support) Class Beta 1 (GPS SBAS Output) Class A1S (UAT In/Out) Class 2 Incomplete (FIS-B Display) Class C1 (ASSAP and ARINC 735 based traffic display Support) Class Beta 1 (GPS SBAS Output) Class A1S (UAT In/Out) Class 2 Incomplete (FIS-B Display) Class C1 (ASSAP and ARINC 735 based traffic display Support) Class Beta 1 (GPS SBAS Output) Class B1S (UAT Out only) Note: The DCM part number is 9230-17003-01 and has not changed with any of the releases. 0040-17011-01 General Information Page 1-13 Revision G
Deviation Notes: Deviation 1: TSO-C145c TSO requires use of DO-160E for environmental qualification testing; DO-160G was used instead. Deviation 2: TSO-C145c, C154c, TSO-C157a, TSO-C195a Per the guidance in FAA Order 8150.1c, the UAT devices are marked with the primary TSO along with a reference to the for the other TSO information (other applicable TSO s, deviations, etc.). Deviation 3: TSO-C145c, TSO-C154c, TSO-C157a, TSO-C195a The NGT-1000/-2000/-2500 utilizes a Maintenance Computer (i.e., a special tool ) as its primary support tool required for installation and debug effort. All installations will require that the Maintenance Computer be used to verify the software part number that is stored electronically in the unit thereby ensuring the part has been installed in compliance to the type design data. All software updates will also require that the Maintenance Computer be used to verify the software part number that is stored electronically in the unit thereby ensuring the part is in compliance to the type design data. Deviation 4: TSO-C154c The RF radiated emissions to exceed the Category L requirement for the RF radiated emission limit in the following frequency bands: 1956 MHz ± 2.25 MHz (2nd Transmitter harmonic) Exceeds Cat L by as much as 30 db 2934 MHz ± 1 MHz (3rd Transmitter harmonic) Exceeds Cat L by as much as 14 db 3912 MHz ± 1 MHz (4th Transmitter harmonic) Exceeds Cat L by as much as 15 db 4890 MHZ ± 1 MHz (5th Transmitter harmonic) Exceeds Cat L by as much as 8 db 5868 MHZ ± 1 MHz (6th Transmitter harmonic) Exceeds Cat L by as much as 3 db Meets DO-282B spectrum reply bounds. There is limited average radiated power in the deviation magnitudes due to the very low duty cycle. There are no defined aeronautical safety related operations utilizing these frequencies. For this deviation, the NGT-1000/-2000/-2500 will direct the installer to specifically verify noninterference with other avionic systems for these frequencies (See Installation Checkout section). 1.5.1 Non-TSO Functions The NGT-1000/-2000/-2500 Release 1 and DCM Release 1 do not have any Non-TSO functions. 1.5.2 Incomplete-TSO Application FIS-B Equipment Class The NGT-2000/-2500 is compliant to Class 2 of TSO-C157a, except that it does not contain a display. 1.5.3 Failure Classification The below summarizes the potential hazards associated with the NGT-1000/-2000/-2500 and the associated failure condition severity classifications per AC 23.1309-1E. 1. GPS Failure condition: Incorrect GPS position and integrity information displayed to the flight crew or annunciated loss of GPS Position and Integrity information. Hazard Classification: Major TSO-145C, section 3.b; AC 20-172A, section 2-7.d 2. ADS-B Out Failure condition: Incorrect ADS-B Message Output. Significant reduction in safety margins. Hazard Classification: Major AC 20-165A, Appendix 1, section 6; TSO-C154c, section 3.b Page 1-14 General Information 0040-17011-01 Revision G
1.6 MODIFICATIONS Modifications (MODS) are identified by an entry on the I.D tag on individual units. A list of modifications to the NGT-1000/-2000/-2500 is identified below: Table 1-7: Hardware Modifications MOD # EFFECTIVITY / COMPLIANCE DESCRIPTION None 1.7 SOFTWARE REVISIONS Software part number and revision is viewed using the maintenance computer via the Lynx Maintenance Application Tool (Lynx MAT). A list of current software revisions is identified in Table 1-8. The listed Lynx MAT listed is current at the time of publication; contact L 3 Field Service for latest information. Table 1-8: Software Revisions Description Release Part Number Compatible Lynx MAT Composite Software NGT-1000 1.0 9021105-005 8010-17002-0104 Composite Software NGT-2000/-2500 1.0 9021105-001 8010-17002-0104 Composite Software NGT-2000/-2500 1.1 9021105-003 8010-17002-0104 Composite Software NGT-2000/-2500 1.2 9021105-006 8010-17002-0104 Description Release Part Number Boot Loader NGT-1000 1.0 9021110-004 Boot Loader NGT-2000/-2500 1.0 9021110-002 Boot Loader NGT-2000/-2500 1.1 9021110-002 Boot Loader NGT-2000/-2500 1.2 9021110-002 1.8 INTERFACES The electrical characteristics of all input and output signals are detailed in Appendix A. 0040-17011-01 General Information Page 1-15 Revision G
1.9 EQUIPMENT REQUIRED NOT SUPPLIED Use Table 1-9 to identify equipment required for installation, calibration, and testing. NOTE Equivalent tools, equipment and hardware may be used. Table 1-9: Equipment List ITEM Cables and Wiring: DESCRIPTION The installer supplies all system wires and cables. Mating Connector (P2) Wires are 22 AWG as noted on interconnect wiring diagram in section 2. Use M22759 or equivalent wire and use M27500 or equivalent for twisted shielded Tefzel wire for installation. WiFi Serial Adapter Connector 9-Pin Sub-D Connector, P/N M24308/2-1 or equivalent. Use M27500 or equivalent for twisted shielded wire for installation as noted on interconnect wiring diagram. Antenna Cables L-Band and GPS Antenna Require M17/128-RG400 or equivalent coaxial cable. For the L-Band antenna the attenuation must not exceed 1.5 db per cable (including the connectors). For the GPS antenna the attenuation should not exceed 10 db per cable (including the connectors). Refer to Table 1-10. NOTE RG type coaxial cable insertion loss can vary significantly between manufacturers. Refer to the cable manufacturer's specification sheet for actual attenuation (insertion loss) for the cable being used. Circuit Breaker: Consumables: Installer is responsible for determining appropriate circuit breakers needed to protect aircraft wiring. Manufacturer recommends the following: 2.0 amp circuit breaker for the installations with 14VDC input. 1.0 amp circuit breaker for the installations with 28VDC input. (Note: For installations with a CP-2500 Control Panel the same circuit breakers may be used for both the CP-2500 and the NGT-1000/-2000/-2500) Antenna Sealant For pressurized aircraft, use a sealant that meets the requirements of SAE AMS-S-8802 such as Flamemaster CS3204 class B. For non-pressurized aircraft, use a non-corrosive sealant that meets the physical requirements of MIL-A-46146 such as General Electric RTV162. Surface Preparation Alodine No. 1001 required for installation of the antenna. Page 1-16 General Information 0040-17011-01 Revision G
Table 1-9: Equipment List Hardware: ITEM Installation Kits: DESCRIPTION The following items are commercially available and is the responsibility of the installer: Cockpit Switches Switches are optional and are dependent on the installation. (1) IDENT Input (momentary switch) (2) Standby / Operate Input (locking SPDT switch). Placards are recommended. Ring Terminals (For Grounding). Solder Sleeves. Cable tie/tie wrap. Ground Braid (RAY-101-20.0/AA59569R36TXXXX or equivalent). Coaxial connectors. Fusion tape. No. 6 Mounting Screws, washers and nuts (mounting hardware). Status Indicator Lamps. Lamps are optional and are dependent on the installation. See the general information section for details. (1) Blue colored No ADS-B Coverage lamp. (2) Amber colored ADS-B Out Fail lamp Placards are recommended. Installation Kit P/N 9060-17250-01 for the NGT-1000/-2000/-2500 is a customer option and is ordered separately. o Hood-Sub Shell Size 4 Alum. with rotating Jackscrews P/N 3050-17000-01 o Connector D Sub Receptacle Hi Density 62 Positions Crimps P/N 9001640-002 Installation Kit P/N 9060-17001-01 for the PIM-9000 Lynx PED Interface Module is a customer option and is ordered separately. The kit includes the following components: o Connector D-Sub 9 Pin Female - P/N 614A0022 o Backshell 9 POS w/ Slide Lock - P/N 3050-10081-01 Installation Tools: Twisted Shield Wire Stripper Tool: TSK-7000 (P/N 12-02031) Manufacturer: EDMO Distributors. Crimp Tool: P/N: M22520/2-01. For mating connector (P2) Positioner: P/N: M22520/2-08. Insertion/Extraction tool M81969/14-01. Heating tool and reflector: PR-25 or PR-25D and HL1802E-ADAPT. (Tyco Electronics) for solder sleeves. System Components: The following system components must be purchased separately and do not come with the NGT-1000/-2000/-2500: DCM, GPS antenna, L-Band antenna, control panel, WiFi serial adaptor, and any display. A list of compatible components is found in paragraph 1.10. 0040-17011-01 General Information Page 1-17 Revision G
Table 1-9: Equipment List ITEM DESCRIPTION Software: Software can be obtained over the internet or via CD. Refer to paragraph 1.12 for details. Lynx Maintenance Application Tool (Lynx MAT) Tool used for diagnostics, set up configuration options, and software downloading. The tool is only available to an Avionics Systems Authorized Installer. Refer to paragraph 1.12 for details on how to obtain a copy or Contact Avionics Systems Field Service for more information. P/N 8010-17002-0104 LynxMSS USB Drivers P/N 8010-17004-0001 (for Windows 7) P/N 8010-17006-0001 (for Windows XP) This driver is required for communication between the MPC and the NGT- 1000/-2000/-2500 via the USB interface. Procedures to install the LynxMSS USB Driver are found in paragraph 1.12.3. Test Equipment: Air Data Test Set Required to test altitude inputs. Maintenance Computer (MPC) The MPC is a laptop computer used to operate the Lynx Maintenance Application Tool for system setup, post installation checkout and troubleshooting. The computer should be using Windows XP or 7 as the operating system, 1.3 GHz processor or greater and 512 MB or more of RAM. Other configurations may operate normally, but they have not been tested. The computer must also have an USB connection and the installation of the correct Lynx MSS USB driver (versions for Windows XP or 7). Mini-B USB Cable Required to interface the MPC to the NGT-1000/-2000/-2500. (male mini-usb type B to male USB type A cable) DB9 F/F Standard Null Modem Cable Required to configure WiFi Serial Adapter. Flightline Tester IFR-6000 Ramp Test Set (with upgrade package Option #3 (1090) & #5 (UAT), Manufacturer: AEROFLEX. Milliohm Meter Required to check installation bonding to aircraft structure. Page 1-18 General Information 0040-17011-01 Revision G
1.9.1 Antenna Cables Table 1-10 lists examples of the recommended antenna cable vendors and the type of cable to be used for specific lengths of cable. Any cable meeting specifications is acceptable for the installation. Table 1-10: Coaxial Cable Specifications INSERTION LOSS (DB/100FT) [1] CARLISLE IT TYPE [2] MIL-C-17 TYPE [3] RG TYPE 18.5 N/A M17/128-RG400 RG-400 11.1 N/A M17/112-RG304 RG-304 9.2 N/A M17/127-RG393 RG-393 15.2 3C142B N/A N/A 9.2 311601 N/A N/A 7.5 311501 N/A N/A 5.8 311201 N/A N/A 3.8 310801 N/A N/A [1] RG type coaxial cable insertion loss can vary significantly between manufacturers. The insertion loss for RG type cables shown in this column is considered 'worst case'. Refer to the cable manufacturer's specification sheet for actual attenuation (insertion loss) for the cable being used. [2] Supplier information (for reference only): Carlisle IT 5300 W. Franklin Drive Franklin, WI 53132 Tel: 800-327-9473 414-421-5300 Fax: 414-421-5301 www.carlisle.com Alternate cable suppliers: Pic Wire (www.picwire.com) and EMTEQ (www.emteq.com) [3] Supplier information: See current issue of Qualified Products List QPL-17. 0040-17011-01 General Information Page 1-19 Revision G
1.10 EQUIPMENT INTERFACES The equipment listed here is compatible with the NGT-1000/-2000/-2500 where applicable. Equipment interfaces not listed in this section can still be found to be compatible for installation, but must meet the requirements for the NGT-1000/-2000/-2500. When interfacing to compatible equipment there may be set-up steps for the equipment that need to be done before it can communicate with the NGT-1000/- 2000/-2500. NOTE Listed software versions are the versions that were tested by the manufacturer. 1.10.1 GPS Antenna The antenna performance is critical to operation of GPS in the unit. The antennas listed in Table 1-11 meet the requirements of TSO-C190. The unit may be installed on aircraft with existing antenna if that antenna complies with TSO-C144a and has been tested for compatibility. All listed GPS antennas have a TNC connector. MANUFACTURER AeroAntenna AeroAntenna AeroAntenna AeroAntenna AeroAntenna AeroAntenna AeroAntenna Comant Comant Table 1-11: GPS Antennas PART NUMBER AT575-326W-TNCF-000-RG-30-NM AT575-343W-TNCF-000-RG-33-NM AT575-493W-TNCF-000-RG-29.5-NM AT575-516W-TNCF-000-RG-29-NM AT575-93 AT575-43F AT135-3 CI-2580-200 CI-2728-410 Comant CI 428-200 Comant CI 429-200 Comant CI 429-410 Sensor Systems Sensor Systems Sensor Systems Sensor Systems S67-1575-135 S67-1575-137 S67-1575-145 S67-1575-160 Page 1-20 General Information 0040-17011-01 Revision G
1.10.2 L-Band (UAT) Antenna The L-Band antenna listed in Table 1-12 meet the requirements of TSO-C66b (or more recent) and TSO- C74c (or more recent). The unit may be installed on aircraft with existing antenna if that antenna complies with TSO-C66b and TSO-C74c and has been tested for compatibility. Antennas not listed may still be used. Contact L-3 Communications for further information regarding compatibility. Table 1-12: L-Band (UAT) Antennas MANUFACTURER PART NUMBER CONNECTOR TYPE Comant CI-105 BNC Comant CI-105-11 TNC Comant CI-105-16 BNC RAMI AV-74 BNC RAMI AV-22 BNC Sensor Systems S65-5366-895L TNC 1.10.3 Traffic Displays Traffic information is output to a compatible traffic display from the NGT-2000/-2500 using an ARINC 735B interface format. Possible traffic output format selections include Standard TCAS Intruder File (STIF or TIF) and Display Traffic Information File (DTIF). The NGT-2000/-2500 allows installed configuration selection of STIF, DTIF, or both formats of output data via the ARINC 429 bus to the traffic display. Displays not listed below can still be found to be compatible for installation, but must meet the specifications required by the NGT-2000/-2500. Table 1-13: Traffic Displays MANUFACTURER MODEL SW VERSION Garmin GNS 430/530 (Standard traffic only) 5.0 GPS SW / Version 5.10 Garmin G 500 (Standard traffic only) GDU-620 Version 6.11 FPGA and I/O Version 2.1 Garmin GTN 650 (Standard traffic only) 4.0 GPS / SW Version 5.0 Garmin GMX 200 (Standard traffic only) (2) 2.13 SW / 011-01465- HW Garmin MX-20 (Standard traffic only) (2) 139-0282-0575v5.7 SW / 430-0270-9xx HW Notes: (1) Some Garmin displays may display OPERATE during the transition from self test to normal operation. (2) For Installations using the GMX 200/MX-20: Traffic may be displayed on the GMX 200/MX-20 using the ARINC 429 interface (GMX 200/MX-20 requires optional 429 card) The RS-422 Traffic interface is a future option. 0040-17011-01 General Information Page 1-21 Revision G
1.10.4 Weather Display Weather information is output to a compatible weather display from the NGT-2000/-2500 via RS-422. Table 1-14: FIS-B WX Displays MANUFACTURER MODEL SW VERSION Garmin GMX 200 (1) 2.13 Notes: (1) Traffic must be disabled if using the GMX 200 as a weather display. 1.10.5 Control Panel Control panels are used to display messages and transmit commands to the NGT-1000/-2000/-2500. Installation without a control panel can alternately use cockpit switches and annunciator lamps. The CP-2500 is specifically designed for operation with the NGT-1000/-2000/-2500. The CP-2500 and other control panels with similar capabilities are listed below. Table 1-15: Control Panels MANUFACTURER MODEL SW VERSION L-3 Aviation Products CP-2500 (9080-17250-01) FW Rev 09 and HW Rev 01 Garmin GTX 327 2.10 Garmin GTX 330 4.40 The NGT-1000/-2000/-2500 can receive mode control and the squawk code directly from these GTX 327/330 transponders. The NGT-1000/-2000/-2500 control panel TX line (pin 25) should not be connected to the GTX 327 or GTX 330. (Note Pin 25 is required if connecting the CP-2500.) The GTX 327/330 (RS-232 output) must be configured to remote before it will communicate with the NGT-1000/-2000/-2500. Page 1-22 General Information 0040-17011-01 Revision G
1.10.6 WIFI Serial Adapter The WiFi Serial Adapter is used with the NGT-2000/-2500 only. It provides a WiFi connection from the Lynx MSS UAT Device and the Lynx MAT and a PED. Table 1-16: RS-232 to WiFi Serial Adapter DESCRIPTION WiFly Serial Adapter (1) Lynx PED Interface Module (2) MODEL - PART NUMBER /MANUFACTURER RN370M / Roving Networks P/N 9080-10024-01 / L-3 Avionics Systems PIM-9000 / P/N 9230-17005-01 / L-3 Avionics Systems Notes: (1) The WiFly Serial Adapter is powered by two AAA batteries (Nickel Metal Hydride, not Lithium or Alkaline) and 5VDC (only) on pin 9 of the DB9 connector. Rechargeable NiMH batteries are trickle charged when used with an external 5VDC (only) power source. The unit operates for up to 8 hours while connected over WiFi on a fully charged set of batteries. (2) The voltage input for the PIM-9000 is rated from 4.5VDC to 32VDC. Input power is rated at 0.75W max. The Lynx PED Interface Module PIM-9000 is preconfigured by the manufacturer. An Installation Kit is available P/N 9060-17001-01. Refer to paragraph 1.9 for details. 1.11 APPLICATIONS (APPS) Apps are used with the PED (e.g. tablet or smartphone). Table 1-17: APPS for PED MANUFACTURER Sky Radar Radenna LLC Hilton Software LLC MODEL Sky Radar Wing X PRO NOTE Other apps may also operate, but have not been tested. 0040-17011-01 General Information Page 1-23 Revision G
1.12 SOFTWARE UPDATES Software for the unit and the Lynx MAT can be obtained by either downloading from the L-3 Technical Publications website or by receiving a compact disc by contacting L-3 Avionics Systems at (616) 285-6457. 1.12.1 Website Download If you have access to the Technical Publications website go to https://www.avionicstechpubs.com and do a basic search on the unit model or part number. If you do not have access go to https://www.l- 3avionics.com/customer-support/technical-publications/ download the Secure Site Access Request complete the form and return it to avionics.techpubs@l-3com.com. Files are downloaded to a temp folder on the user s computer as a.zip file. 1.12.2 Compact Disc Compact Disks (CD) available for the Lynx NGT-1000/-2000/-2500 are listed in Table 1-18. The Lynx MAT is installed on the Maintenance PC and is used to transfer application software to the Lynx NGT-1000/-2000/-2500. Table 1-18: CD Part Numbers and Contents PART NUMBER CONTENTS 9230-17007-0002 Lynx Maintenance Application Tool (Lynx MAT), P/N 8010-17002-0104 Tool used for diagnostics, set up configuration options, and software downloading. LynxMSS USB Drivers (versions for Windows 7 & Windows XP) P/N 8010-17004-0001 (for Windows 7) P/N 8010-17006-0001 (for Windows XP) Page 1-24 General Information 0040-17011-01 Revision G
1.12.3 Installation Procedure for Lynx MSS USB Driver Typically the MPC device manager pops up when the NGT-1000/-2000/-2500 is connected to the MPC. Follow the device manager instructions to install the driver. The procedure here is typical, but may differ per settings on the computer being used. The following procedures assume the following: The NGT-1000/-2000/-2500 and MPC have power applied. The driver has been downloaded from the internet or is available via CD. The NGT-1000/-2000/-2500 is connected to the MPC via USB cable. 1.12.3.1 Windows XP Installation 1. After the NGT-1000/-2000/-2500 and MPC are connected a Found New Hardware Wizard window should pop up on the MPC. 2. A new hardware wizard dialog is then shown on the MPC. 3. Select Install from a list or specific location (Advanced) and Press the Next button. See Below. 4. Press the Have Disk button. 0040-17011-01 General Information Page 1-25 Revision G
5. Press the Browse button and navigate to the location of the LynxMSS Driver file. See Below. 6. Select the LynxMSS Driver file and press the Open button. 7. Press the OK button. A screen with Lynx MSS as the Model is shown. See Below. 8. Press the Next button. The driver installation process begins. See Below. 9. When the installation completes a completed dialog is shown. Press the Finish button. Page 1-26 General Information 0040-17011-01 Revision G
1.12.3.2 Windows 7 Installation NGT-1000/-2000/-2500 1. After the NGT-1000/-2000/-2500 and MPC are connected, an Installing device driver software is shown on the tray. 2. If the Driver Software Installation fails a dialog window is shown. Close out of that window. 3. Open the Devices and Printers from the Start menu. An unspecified device with the label NGT should be available. See below. 4. Double click on the unspecified device icon. 5. In the NGT Properties window select the Hardware tab. See below. 6. Select the Properties button. 0040-17011-01 General Information Page 1-27 Revision G
7. Select the Change Settings button. See below. 8. Select the Update Driver button. 9. Select the Browse my computer for driver software. 10. Browse to the Windows 7 USB Driver folder and select Open. See below. 11. Select Next. The driver installation process begins. 12. When the installation completes a completed dialog is shown. Press the Close button. Page 1-28 General Information 0040-17011-01 Revision G
1.13 INSTALLATION APPROVAL AND LIMITATIONS 1. The conditions and tests required for TSO approvals of this article are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine the suitability of the installation. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the Administrator. 2. The NGT-1000/-2000/-2500 GPS receiver must use antenna meeting the requirements specified in para. 1.10.1 3. The NGT-1000/-2000/-2500 transceiver must use antenna meeting the requirements specified in para. 1.10.2. 4. The NGT-1000/-2000/-2500 is not approved for installations with SATCOM-equipped airplanes. 5. The NGT-1000/-2000/-2500 does not support the use of a frequency diplexer (per TSO-154c) and as such the UAT antenna cannot be diplexed with any L band antenna. 6. It is the installer s responsibility to ensure the ADS-B Out system is compliant with AC 20-165A, 14 CFR 91.225 (b) and 91.227 when installed in accordance with L-3 s installation instructions. 7. For NGT-2000/-2500, if aircraft ground speed is less than 7 knots, then traffic data is not shown on display. 0040-17011-01 General Information Page 1-29 Revision G
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Section 2 Installation 2.1 INTRODUCTION This section provides installation information for the NGT-1000 and NGT-2000/-2500 MultiLink Surveillance System (Lynx MSS UAT Device). Installation must be made by qualified personnel, in conformance with applicable government regulations. The information furnished is for convenience only. Tolerances (unless otherwise indicated): ANGLES ARE ± 0.5 0.00 TWO PLACE DECIMALS ARE ± 0.02 0.000 THREE PLACE DECIMALS ARE ± 0.010 2.2 UNPACKING AND INSPECTING Carefully unpack the unit and note any damage to shipping containers or equipment. Visually inspect each component for evidence of damage. Compare the equipment received with that noted on the packing list. Report immediately any missing items or evidence of damage to the carrier making the delivery. To justify a claim, retain the original shipping container and all packing materials. Every effort should be made to retain the original shipping containers for storage. If the original containers are not available, a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement. 2.2.1 Transport and Storage Considerations Transport of the NGT-1000/-2000/-2500 should be done in accordance with standard procedures, i.e. hand carried or transported in the original container. The container limits the shock to the unit at a maximum of 20g s when dropped from a distance of 36 inches (0.91 meters). Storage of avionics equipment must be consistent with industry standards for avionics equipment and performs satisfactorily after periods of storage up to 24 months. The ambient temperature of the storage area should not fall below -55 C (-65 F) or rise above +85 C (+185 F). 0040-17011-01 Installation Page 2-1 Revision G
2.3 INSTALLATION PROCEDURES 1. The installer must take the following into consideration prior to installation. The installer must obtain installation approval (i.e. Supplemental Type Certification or form 337 if the installer has prior approved data). Follow the acceptable avionics installation practices in FAA Advisory Circulars AC 43.13-1B and AC 43.13-2B or later revision of these documents. Installers are responsible for obtaining installation hardware (i.e. screws, supporting plates, etc). Installation kits are available for purchase. Refer to the Equipment Required Not Supplied Paragraph in the general information section. It is recommended that the aircraft battery be disconnected before performing installation procedure. GPS and L-band antenna cables should be clearly labeled to prevent inadvertently installing on the wrong connector. After installation, refer to the Installation Checkout section for calibration, power-up and ground testing procedures. 2. Electrical equipment chassis, shield/ground terminations, antennas, supporting brackets, and racks must be electrically bonded to the aircraft's main structure (metallic aircraft) or instrument panel (composite aircraft). Compliance of the electrical bonding should be verified by inspection using a calibrated milliohm meter. An equivalent OEM procedure may also be substituted. The electrical bond should achieve direct current (DC) resistance less than or equal to 2.5 milliohms to structure local to where the equipment is mounted for metallic aircraft or tube and fabric aircraft. The electrical bond should achieve direct current (DC) resistance less than or equal to 5.0 milliohms to the instrument panel for composite aircraft. The antenna ground plane must be electrically bonded to the antenna baseplate. Do not remove paint on outer skin of aircraft under the footprint of the antenna baseplate unless necessary to meet bonding requirements. Refer to antenna manufacturer's installation instructions. 2.3.1 Location The NGT-1000/-2000/-2500 provides flight information. When locating the unit in the aircraft take the following into consideration. 1. The unit should be accessible for inspection, maintenance, removal, free from excessive vibration or heat and located in a clean and dry area. 2. The wiring cable should not run adjacent to heaters, engine exhaust, or heat sources. 3. Ensure the space requirements for the unit is acceptable at the location area being considered. Refer to Figure 2-1 for dimensional requirements. The installer is advised to consider the space requirements (2-3 inches) needed for the connector backshell and the cable bend radius. 4. Unit to be mounted firmly to the airframe using # 6 pan head machine screws. 5. The chassis of the unit must be properly bonded to the Ground. The chassis of the unit itself is conductive and acts as a ground. Page 2-2 Installation 0040-17011-01 Revision G
Figure 2-1: Outline Dimensions for NGT-1000 and NGT-2000/-2500 0040-17011-01 Installation Page 2-3 Revision G
2.3.1.1 Electrical Connections NGT-1000/-2000/-2500 1. The installer must take the following into consideration before installation. Use of any wire or cable not meeting specification voids all warranties. The installer is responsible for supplying wires, cables and connectors. Wire-marking identification is at the discretion of the installer. GPS and L-band antenna cables should be clearly marked as both connections use TNC connectors. All wiring must be in accordance with industry-accepted methods, techniques, and practices. Refer to Appendix A for signal name and cable characteristics prior to wiring installation. This section is also helpful in determining the need for indicator lamps and switches. The length and routing of the external cables must be carefully studied and planned before attempting installation of the equipment. The wiring harness should not run adjacent to heaters, engine exhaust, and heat sources or be located near fuel lines, high electrical capacity lines, flight control cables, and protected areas of the aircraft or be exposed to wire chafing. Avoid sharp bends while routing the cables. Cable runs should be as short as practical. Grounded pigtails must not exceed 3 inches in length. Terminate shields in the backshell of the mating connector (at P1). All wires are 22 AWG. Use M22759 or equivalent wire and Tefzel Wire M27500 or equivalent for twisted shielded wired for installation. Installer is responsible for determining appropriate circuit breakers needed to protect aircraft wiring. Refer to the electrical connections paragraph for other connection options. Manufacturer recommends the following: o 2.0 amp circuit breaker for the installations with 14VDC input. o 1.0 amp circuit breaker for the installations with 28VDC input. o For installations with a CP-2500 Control Panel the same circuit breakers may be used for both the CP-2500 and the NGT-1000 or NGT-2000/-2500. 2. Refer to the following Interconnect Wiring Diagrams: Figure 2-2 for NGT-1000 Figure 2-3 for NGT-2000/-2500 3. The P2 mating connector is a TE Connectivity P/N M24308/2-14 or an L-3 P/N 9001640-002 with Backshell P/N 3050-17000-01 (Also See Install Kit P/N 9060-17250-01) or equivalent. Refer to Figure 2-4 for pin locations and assignments. Refer to General Information Section-Equipment and Materials required for Installation for connector installation tools. 4. Figure 2-5 shows manufacturing requirements for the P2 Mating Connector. Installation guidelines for the Detachable Configuration Module are provided in paragraph 5. The GPS and L-band (UAT) connections (TNC Amphenol P/N 31-5660) require a male TNC mating connector. Page 2-4 Installation 0040-17011-01 Revision G
6. When installing the status lamps in the cockpit a blue colored lamp is required for the No ADS-B Coverage indicator (NGT-2000/-2500 only) and an amber colored lamp is required for the ADS-B Out Fail indicator. Lamp power should be connected to dimming bus or day/night switch. Label lamps as No ADS-B Coverage and ADS-B Fail as applicable. 7. The WiFi interface requires configuration prior to installation if using the Roving Networks RN370M (L-3 P/N 9080-10024-01) WiFi Serial Adapter (Dongle). Refer to the Installation Checkout section for details. Note The PIM-9000 WiFi Serial Adapter is preconfigured by the manufacturer. The PIM-9000 WiFi Serial Adapter may be connected to the NGT-2000/-2500 circuit breaker through a 1/4 amp in line fuse. 8. Indicator lamps and switch installation guidelines: The ADS-B Out Fail (Disc 1 Out) is required if a CP-2500 is not installed and is recommended when the CP-2500 is installed. The No ADS-B Coverage (Disc 4 Out) status lamp is not required if a CP-2500 is installed. The Standby / Operate switch (Disc 4 In) is required when the CP-2500 is not installed. If the CP-2500 is installed the discrete is disabled (internally) and not connected. The In Air / On Ground input (WOW Disc 3 In) is optional and may be connected to either a squat switch, Airspeed monitor, or a collective switch. If a CP-2500 is installed, it is recommended that a remote IDENT switch be used that ties the NGT-1000/2000/2500 and transponder IDENT function together (if applicable). 9. It is recommended that the installer perform the following wiring checks during installation: Check all wiring point-to-point for continuity before connecting components. Ensure voltages are not applied to signal wires. Inspect cables for correct connection. 10. Use the following information for interfacing compatible equipment. Additional information may be found in the General Information section under Equipment Interfaces. The GTX 327/330 must be configured to remote before it will communicate with the NGT- 1000/-2000/-2500. The NGT-1000/-2000/-2500 control panel TX line (pin 25) does not need to be connected to the GTX 327/330. (Note - Pin 25 is required if connecting the CP-2500.) 0040-17011-01 Installation Page 2-5 Revision G
Figure 2-2: NGT-1000 Interconnect Diagram (Sheet 1 of 2) Page 2-6 Installation 0040-17011-01 Revision G
Figure 2-2: NGT-1000 Interconnect Diagram (Sheet 2 of 2) 0040-17011-01 Installation Page 2-7 Revision G
Figure 2-3: NGT-2000/-2500 Interconnect Diagram (Sheet 1 of 2) Page 2-8 Installation 0040-17011-01 Revision G
Figure 2-3: NGT-2000/-2500 Interconnect Diagram (Sheet 2 of 2) 0040-17011-01 Installation Page 2-9 Revision G
Figure 2-4: Mating Connector (P2) and Pin Assignments Page 2-10 Installation 0040-17011-01 Revision G
Figure 2-5: Mating Connector (P2) Assembly 0040-17011-01 Installation Page 2-11 Revision G
2.3.1.2 Installation Guidelines for the DCM Use the following information when locating and installing the DCM in the aircraft. 1. Use the following information when locating and installing the DCM in the aircraft. Refer to Figure 2-5 for DCM mounting location. 2. The DCM is connected to the P2 mating connector during wire installation. Refer to electrical connections paragraph 2.3.1.1 for wiring details. Refer to Figure 2-6 for the outline dimensions of the DCM. Refer to Figure 2-3 for interface connections to the P2 mating connector. Figure 2-6: Outline Dimensions for the DCM Page 2-12 Installation 0040-17011-01 Revision G
2.3.2 Antenna Installation Guidelines This information provides general installation guidance to ensure the installed antennas meet the requirements for the NGT-1000/-2000/-2500. Installation approval for the GPS and L-band antennas is not provided by the instructions provided in this manual. GPS and L-band antenna cables should be clearly marked as both connections use TNC connectors. Cable requirements are located in paragraph 2.3.1.1. Cable vendors and approved antenna manufactures are located in the General Information section. An example of antenna placement is shown in Figure 2-7. Refer to the aircraft manufacturer's data and the antenna manufacturer's installation instructions to mount the antenna. The installer may use other FAA approved data to gain a separate antenna installation approval. Figure 2-7: Example of Antenna Mounting Locations 2.3.2.1 GPS Antenna The GPS antenna performance is critical to the performance of the NGT-1000/-2000/-2500. The antenna must meet the minimum performance requirements for the NGT-1000/-2000/-2500. The antennas listed in the General Information section meet these requirements. The antenna performance is critical to operation of GPS in the unit. The antennas listed in this manual meet the requirements of TSO-C190. The unit may be installed on aircraft with existing antenna if that antenna complies with TSO-C144a and has been tested for compatibility. The performance of the unit is affected by the gain, noise figure, impedance, and frequency selectivity characteristics of the antenna. The unit should be used only with the recommended antenna and cable. Use of other antennas or cables may not meet all the performance characteristics required by TSO-C190 or if applicable TSO-C144a. The cable including connectors, loss should not exceed 10dB. 0040-17011-01 Installation Page 2-13 Revision G
2.3.2.1.1 GPS Antenna Location The following guidance provides information to aid the installer in determining the best location is selected for the installation of the GPS Antenna. The installation guidelines presented here meet the intent of AC 20-138D Chapter 13, Section 13-1. NOTE Not all the listed installation guidelines may be possible on all aircraft. The guidelines are listed in order of importance. The chances of optimal signal strength are decreased if the guidelines are not followed. 1. The antenna must be located on the top of the aircraft and should be mounted in a location to minimize the effects of airframe shadowing during typical maneuvers. Typically mounting farther away from the tail section reduces signal blockage seen by the antenna. 2. Mount the antenna as close to level as possible with respect to the normal cruise flight attitude of the aircraft. If the normal flight attitude is not known, substitute with the waterline, which is typically referenced as level while performing a weight and balance check. A shim may be used to level the antenna. 3. The antenna should be mounted no closer than 3 feet from any VHF COMM antenna or any other antenna, which may emit harmonic interference at the L1 frequency of 1575.42 MHz. An aircraft EMI check can verify the degradation of GPS in the presence of interference signals. If an EMI check reveals unacceptable interference, either insert a GPS notch filter in line with the offending VHF COMM or select a different GPS Antenna location. 4. To maintain a constant gain pattern and limit degradation by the windscreen, avoid mounting the antenna closer than 3 inches from the windscreen. 5. It is permissible to temporarily locate the GPS Antenna with a coaxial cable connected to the NGT- 1000/-2000/-2500 and check the GPS performance as described in the installation checkout section. Permanently mount the antenna once a suitable location has been verified. 6. Once the antenna mounting position has been established, route the coaxial cable from the antenna to the NGT-1000/-2000/-2500. Proper selection of coaxial cable and assembly of connectors is critical to GPS signal performance. 7. For installations on rotorcraft, ensure that the rotor blades do not interfere with the GPS received signal. This problem has been experienced in some rotorcraft and varies with rotation rate. 2.3.2.1.2 GPS Antenna Installation Refer to the aircraft manufacturer's data and the antenna manufacturer's installation instructions to mount the antenna. The installer may use other FAA approved data to gain a separate antenna installation approval. 1. Electrical Bonding Requirements: The GPS/WAAS antenna requires a minimum ground plane radius of 7.5 inches around the perimeter of the antenna. For metal aircraft, the surrounding metal skin on which the antenna is mounted supplies the ground plane. For non-metal aircraft, the ground plane can be composed of heavy duty aluminum foil tape, such as 3M P/N 438 or other adhesive backed dead soft aluminum foil minimum 0.012 inches thick. It should be noted that if the antenna is struck by lightning, the foil by itself may not be sufficient to dissipate lightning currents. Additional protection may be needed depending on the construction of the structure to which the antenna is mounted. The electrical bonding requirements stated in paragraph 2.3 step 2 must be met. To prepare an aluminum surface for proper bonding, refer to SAE ARP1870A. 2. Connection to the antenna should be made in accordance with the system interconnect diagram Figure 2-3. Page 2-14 Installation 0040-17011-01 Revision G
2.3.2.2 L-Band (UAT/978) Antenna The UAT/978 antenna must meet the minimum performance requirements for the NGT-1000/-2000/-2500. Only the antennas listed in the General Information section have been tested. Antennas meeting the minimum performance specifications needed by the NGT-1000/-2000/-2500 may already be installed in the aircraft and may be available for use. Use the antenna location information below to verify an existing antenna location is acceptable for use. Installation approval for the UAT Antenna is not provided through this Manual. 2.3.2.2.1 L-Band (UAT/978) Antenna Location The UAT/978 antenna installation should be installed in accordance with AC 43.13-2B Chapter 3. The following guidance provides information to aid the installer in determining that the best location is selected for the installation of the L-band Antenna. The UAT/978 antenna must be mounted vertically on the bottom of the aircraft fuselage. The antenna shall be located to minimize obstruction to fields in the horizontal plane. The total attenuation including connectors shall not exceed 1.5 db. Based on this, the length of the cable can be decided assuming RG-400 cable. RG type coaxial cable insertion loss can vary significantly between manufacturers. Refer to the cable manufacturer's specification sheet for actual attenuation (insertion loss) for the cable being used. The UAT/978 antenna should be located away from major protrusions, such as engine(s), propeller(s), and antenna masts. It should be as far as practical from landing gear doors, access doors, or other openings that could affect its radiation pattern. The UAT/978 antenna must be mounted no closer than 20 inches from any FADEC (Full Authority Digital Engine Control). The UAT/978 antenna must be mounted no closer than 7 feet to any DME antenna. The UAT/978 antenna must be mounted no closer than 36 inches to any TAS/TCAS/Transponder/ Com antenna. Refer to Table 2-1 for maximum transponder distances. Table 2-1: Maximum UAT Antenna to Transponder Antenna Separation UAT ANTENNA CABLE ASSEMBLY CABLE LOSS (1) Up to 1.0 db MAXIMUM ANTENNA SPACING (2) 137 inches 1.0 db < Cable Loss < 1.5 db 129 inches Note (1) Cable assembly cable loss includes loss of the coaxial cable with connectors. Note (2) Measured from center of UAT/978 Antenna to the center of transponder antenna. When the NGT-1000/-2000/-2500 is configured to communicate with the aircraft transponder using the self-interrogation feature (CP-2500 installed), the following antenna guidelines must also be followed: a. Deleted. b. The bottom UAT/978 Antenna must be mounted no further from the transponder antenna than specified in Table 2-1. 0040-17011-01 Installation Page 2-15 Revision G
2.3.2.3 L-Band (UAT/978) Antenna Installation Refer to the aircraft manufacturer's data and the antenna manufacturer's installation instructions to mount the antenna(s). The installer may use other FAA approved data to gain a separate antenna installation approval. Electrical Bonding Requirements: Each L-Band antenna requires a minimum ground plane radius of 12 inches of contiguous metal (no access panels, etc.) around the perimeter of the antenna. For metal aircraft, the surrounding metal skin on which the antenna is mounted supplies the ground plane. For non-metal aircraft, the ground plane can be composed of heavy duty aluminum foil tape, such as 3M P/N 438 or other adhesive backed dead soft aluminum foil minimum 0.012 inches thick. It should be noted that if the antenna is struck by lightning, the foil by itself may not be sufficient to dissipate lightning currents. Additional protection may be needed depending on the construction of the structure to which the antenna is mounted. The electrical bonding requirements stated in paragraph 2.3 step 2 must be met. Connection to the antenna should be made in accordance with the system interconnect diagram Figure 2-3. GPS and L-band antenna cables should be clearly marked as both connections use TNC connectors. Refer to Table 2-1 for Antenna Cables for UAT Antenna cable loss and minimum antenna spacing requirements. Refer to General Information Section - lists some suitable cable types. Suitable 50 ohm, doubleshielded coaxial cable assembly that meets airworthiness requirements and the acceptable attenuation requirements (including connectors) may be used. When computing cable loss refer to cable/connector manufacture data. Refer to paragraph 2.3 step 2 for antenna electrical bonding requirements. 2.3.3 NGT-1000/-2000/-2500 Installation Perform the following to the extent necessary to install the NGT-1000/-2000/-2500: 1. Place the unit in the location selected in paragraph 2.3.1. 2. Use four customer supplied fasteners to mount the unit to the aircraft. 3. Connect P2 mating connector to connector J2 of the unit. 4. Connect GPS and L-Band antenna to unit at appropriately marked TNC connections. 2.3.4 CP-2500 Installation Guidelines Use the following guidelines if the CP-2500 Control Panel is used with the NGT-1000/-2000/-2500. The ADS-B Fail (amber) lamp installation is optional. The No ADS-B Coverage (blue) lamp is optional when installing a CP-2500. The Standby / Operate switch is not required and the discrete input for this switch is disabled when the CP-2500 is installed. It is recommended that an IDENT switch be used that ties the CP-2500 and transponder (if applicable) IDENT function together. If a single switch is not used for both, then when instructed by the ATC the IDENT must be selected for both the transponder and the NGT-1000/-2000/-2500 when using the CP-2500. Page 2-16 Installation 0040-17011-01 Revision G
Section 3 Installation Checkout 3.1 INTRODUCTION This section contains instructions to check out the installation of the Lynx MSS UAT Device (NGT- 1000/-2000/-2500) and DCM. Refer to the fault isolation information provided in the maintenance manual for help in correcting installation issues found during checkout. Refer to the General Information section- Equipment Required Not Supplied for details on equipment used in this section. The installation of the NGT-1000 requires a compatible control panel. Note that compatible control panel may not operate exactly as stated in this checkout. Refer to the operating instructions for the controller for details. The installation of the NGT-2000/-2500 requires a compatible control panel/display. Note that compatible control panel/display may not operate exactly as stated in this checkout. Refer to the operating instructions for the controller/display for details. NOTE These procedures assume that the mounting, wiring, power, and antenna requirements have been checked out according to the instructions given in the installation section. CAUTION Operating the unit with the GPS antenna connected and the UAT antenna NOT connected may damage the unit. 3.2 BASIC OPERATION The NGT-1000/-2000/-2500s are remote mount devices that require compatible control panels or cockpit switches and lamps or both (depending on the needs of the control panel) to initiate commands and display messages. The CP-2500 Control Panel provides all the necessary command and annunciation functions. Refer to paragraph 3.2.1 for operating instructions. Additional operating instructions for the CP-2500 are provided in the Pilot Guide for the CP-2500, NGT-1000, and NGT-2000/-2500 and Installation Manual for the CP-2500. The NGT-2000/-2500 can be interfaced to a compatible Personal Electronic Device (PED, e.g. Tablet or Smartphone) that can be used to view traffic and weather. The NGT-2500 can also be interfaced to compatible cockpit displays that can be used to view traffic, weather, and messages. The operation of other 3 rd party equipment (i.e. transponder, display) is not provided in this manual. Refer to the operations manual for the 3 rd party equipment for command instructions. There is no power on/off switch for the NGT-1000/-2000/-2500. Depending on the aircraft, use either the battery switches or avionics master switch to apply power. Normal operation begins within 10 seconds of applying power. During start up the unit checks for valid configuration data and initializes self tests. 0040-17011-01 Installation Checkout Page 3-1 Revision G
If the CP-2500 is not installed then whatever is installed (i.e. compatible control panel, transponder, and cockpit switches/lamps) must be able to support the following functions: o Enter Mode A Squawk Code o Set Operation Mode or Standby / Operate (switch), ON, ALT, and Ident o VFR Code Select o IDENT (or a IDENT switch) o Display Transponder Code Mismatch Message (or ADS-B Out Fail lamp) o Display Fault Messages (or minimum ADS-B Out Fail lamp and No ADS-B Coverage lamp) If installed, the ADS-B Out Fail lamp (amber) has the following functions. o Flashes at a slow rate (1 flash per 2 seconds) while the GPS is initializing. Check by cycling power to the unit. Flashing will last only 2 minutes before the lamp stays ON (this indicates the unit is unable to transmit GPS position due to aircraft position information being invalid.) o Flashes at a fast rate (2 flashes per second) if a code mismatch is detected. Check by entering the different Mode A code from the one being transmitted by the transponder. Note - Occurs with CP-2500 installations only. o The lamp is ON when the ADS-B has failed or if the Standby / Operate switch is set to Standby or CP-2500 (if installed) is set to standby. If installed the No ADS-B Coverage lamp (blue) indicates if a ground station signal is being detected. The lamp is OFF when a signal is detected and ON when a ground station signal is not detected. If installed the IDENT and Standby / Operate switches provide the following functions: o Pressing the remote IDENT switch activates the IDENT message to be sent by the unit via ADS- B Out. An IDENT pulse highlights the aircraft s symbol on the ATC s radar screen and is identified on the control panel when active. o The Standby / Operate switch is used to stop ADS-B Out transmission for standby operation. Setting this switch to Standby turns the ADS-B Out Fail lamp ON. This switch should always be in the "operate" mode unless otherwise directed by ATC. 3.2.1 CP-2500 Control Panel The CP-2500 is specifically designed for operation with the NGT-1000/-2000/-2500. The operational information provided in this section is limited. Refer to the CP-2500 Pilot s Guide or for details. 1. Press the small knob button to apply power to the control panel. To remove power to the unit press and hold the small knob button until the message Power Down is shown on the display. 2. After power is applied, if the self test passes, the CP-2500 briefly displays OK. That is followed by the scrolling of the firmware and hardware levels of the CP-2500 (approximately 15 seconds). The CP-2500 then reverts to normal operation. 3. A GPS INIT message is shown on the CP-2500 display, indicating that the NGT-1000/-2000/-2500 GPS is initializing. After 2 minutes the CP-2500 displays ADS-B SYSTEM FAIL if the GPS position was not acquired. If the CP-2500 displays ADS-B SYSTEM FAIL in less than 2 minutes then a different problem has been detected. Cycle power to the NGT-1000/-2000/-2500. If the problem continues refer to the troubleshooting section for possible corrective actions. 4. The display of the CP-2500 shows the operational mode on the left side of the display and the squawk code on the right side of the display as shown in Figure 3-1. Page 3-2 Installation Checkout 0040-17011-01 Revision G
Figure 3-1: CP-2500 Normal Mode 5. In normal operation the user can change the operational mode, set the squawk code, view the current pressure altitude, and optionally set a flight ID or activate anonymous mode. (The anonymous mode and flight ID functions are optional and are part of the configuration options set during installation of the NGT-1000/-2000/-2500.) Select these items by rotating the large knob. Messages being received from the NGT-1000/-2000/-2500 have priority over normal display operation and is seen scrolling across the display. Rotating the large knob scrolls through unseen messages and the normal display operation (showing operational mode and squawk code). The display begins showing the high priority message again after 10 seconds of no activity. The priority of the messages is discussed in the CP-2500 product manuals. NOTE If any Menu function is selected, no message is displayed until the menu or maintenance mode is exited by pressing the "M" button. The operational mode is changed by rotating the small knob and can be set to Altitude, On, or Standby. The Altitude (ALT) mode should always be selected unless Air Traffic Control (ATC) requests a change or if there is a known problem with the control panel or NGT-1000/-2000/- 2500. Note If the CP-2500 operational mode is set to Standby the ADS-B Out Fail lamp (if installed) is ON and the ADS-B Out Fail message is displayed on the CP-2500 screen. Change the squawk code by rotating the large knob to select squawk and press the small knob. Observe that the left most digit blinks. Rotate the small knob to change the number, rotate the large knob to select the next digit. Repeat until all digits are changed. Press the small knob or allow the screen to time out to commit the change. NOTE The four digit squawk code may be missing from the ALT and ON screen of the CP-2500 (code appears OK in STB mode), if the Lynx MSS has failed or if the GPS signal is missing for greater than 2 minutes. View the pressure altitude by rotating the large knob until the Altitude is shown. Press the small knob to view. Press the small knob again to return to normal operation. If configured rotate the large knob to select flight ID. Press the small knob to select the first digit. Rotate the small knob to change the digit (CCW) or character (CW). Rotate the large knob clockwise to move the cursor to the next digit. Press the small knob to commit. Deactivate the Flight ID by rotating the large knob CW to move the cursor off the right side of the display. Continue rotating unit only dashes fill the display. Press the small knob to commit. 0040-17011-01 Installation Checkout Page 3-3 Revision G
The CP-2500 has three buttons identified as I (Ident), V (VFR), and M (Menu). Pressing the I button activates the IDENT message to be sent by the ADS-B unit for 18 sec. IDENT is momentarily displayed while this message is being sent. The use of this button is directed by Air Traffic Control (ATC). Pressing the V button sets the squawk code to a programmed VFR code that is set in the menu. Pressing the button again returns the code to the previous squawk code. Pressing the M button gains access to the menu, as well as the hardware and firmware status. Rotating the large knob allows the pilot to change modes, while the small knob can set the VFR mode. The Menu button also allows access to the Maintenance Mode, where the pilot can conduct a self test. Press the M button to exit to normal operation. o Self Test operation: a. Press the Menu (M) button. b. Turn the small knob to select "Self Test". The display shows "Disabled". c. Press the small knob to change display to "Enable". d. Press small knob again to activate self test. The display shows "Self Test Started". e. Observe that the System Failure Annunciator begins to flash. f. Observe that 3 targets are shown on a PED or traffic display (NGT-2500 only). If installed the ADS-B Out Fail lamp and No ADS-B Coverage lamp (located on instrument panel) will flash for a couple of seconds. 3.3 MAINTENANCE PC The procedures for installation checkout require the use of a Maintenance PC (MPC), Lynx Maintenance Appliance Tool (Lynx MAT), LynxMSS USB Driver, and a USB cable. The MPC may only be connected and used while the aircraft is on ground. An example of the main page of the Lynx MAT is shown in Figure 3-2. NOTES 1. The revision of the Lynx MAT can be found in the Help/About menu item at the top of the screen. Refer to software revisions in the General information section for additional revision information. 2. The screen information for Lynx MAT is very similar between the NGT-1000, NGT-2000, and NGT-2500. Differences in appearance are either noted or will be shown in the following procedures. A compatible Lynx MAT revision must be used to successfully communicate with an NGT-1000/-2000/- 2500. Refer to the Software Revisions information in the General information section for details. Persons performing the checkout should monitor the Lynx MAT status bar. The bottom left corner of the screen provides information on connection type, communication status, and Operation Mode. The communication status is either Connected green indicator or Not Connected red indicator. The Operation Mode shows the current status of the unit. There are four modes OP, MAINT, UAT, and ATE. The OP (Operation) mode is the normal unit operation. The other modes can only be entered if the unit is communicating On Ground status. The Air/Ground state is determined through a Weight-On-Wheels (WOW) input or GPS Groundspeed. Messages are also shown on the right side of the status bar providing guidance to the user. NOTE When the unit is in MAINT mode, it is normal for the unit to display FAIL mode. Depending on the installation, this is either with the ADS-B Out Fail lamp illuminated, or if a CP-2500 is used the message ADS-B SYSTEM FAIL. This indicates that the unit is not currently transmitting. Page 3-4 Installation Checkout 0040-17011-01 Revision G
Figure 3-2: Lynx Maintenance Appliance Tool Main Page 1. Do the following to connect and establish communication between the MPC and the NGT-1000/- 2000/-2500 via the USB connection. a. Apply power to the NGT-1000/-2000/-2500 and MPC. b. The Lynx MAT is active on the MPC. c. Connect USB cable between MPC and the NGT-1000/-2000/-2500. d. From the Lynx MAT menu select Connect Appliance USB. e. Communication is established when the Lynx MAT left view panel changes from gray to tan and the message Connected green indicator is shown in the lower status bar. See Figure 3-3. If Not Connected red indicator is shown, then check the USB cable for proper connection. If a Response timeout for write request message is seen on the status bar, then the unit is not responding to requests. Cycle power to the NGT-1000/-2000/-2500. Note - This symptom can also be caused by having the wrong USB driver is installed. See the general information section for details. Maintenance mode (MAINT) can be entered within the first 2 minutes from power-on irrespective of Air/Ground state. After 2 minutes, maintenance mode can only be entered if the Air/Ground state is On-Ground. The Air/Ground state is determined through a Weight- On-Wheels (WOW) input (if installed) or GPS Groundspeed. The unit will need to be cycled again before maintenance mode can be entered by the Lynx MAT. When the unit is in maintenance mode the ADS-B Out Fail lamp is ON. NGT-2500 Figure 3-3: Lynx MAT Example of Main Screens NGT-1000 0040-17011-01 Installation Checkout Page 3-5 Revision G
3.4 CONFIGURE WIFI SERIAL ADAPTER NOTE The Lynx PED Interface Module PIM-9000 is preconfigured by the manufacturer. This procedure is for NGT-2000/-2500 only using the Roving Networks RN370M (L-3 P/N 9080-10024- 01) WiFi Serial Adapter. This procedure requires a Maintenance PC (MPC), Lynx Maintenance Appliance Tool (Lynx MAT), and a standard Null Modem cable (DB9 F/F). These procedures assume the following: The Lynx MAT is active on the MPC. 1. Connect WiFi Serial Adapter to the MPC via the Com Port that the dongle is connected to using a standard Null Modem cable. 2. From the Lynx MAT menu select Tools Configure WiFi Dongle. See Figure 3-4. Figure 3-4: Lynx MAT WiFi Serial Adapter 3. Verify the following: Dip switches 1-4 are in the off position (i.e. towards the connector side of the dongle). Com Port: Typically COM1. Dongle type is set to WiFly 4.x SSID is set to WiFly-GSX-nn. Where nn is variable per dongle. 4. Click Configure to begin. A message is shown to indicate configuration complete or if configuration could not be completed. 5. If the configuration could not be completed, then check the following: Cable connection Com port connection Check batteries for the WiFi Serial Adapter 6. After the configuration is complete remove the serial cable and cycle power to the dongle. 7. Connect the WiFi Serial Adapter to the aircraft wiring harness connecting to the NGT-2000/-2500. 8. Verify that the SSID name can be seen with a WI-FI personal electronic device. Note - The SSID will show the default SSID being used, which is typically Wifly-Serial-nn, where nn is variable per dongle. Page 3-6 Installation Checkout 0040-17011-01 Revision G
3.5 VERIFY SOFTWARE REVISION The Maintenance PC (MPC) and Lynx Maintenance Appliance Tool (Lynx MAT) are used to interface with the NGT-1000/-2000/-2500 to load software / firmware, view factory / version data, and retrieve fault logs. These procedures assume the following: Power is being supplied to the aircraft and the MSS Appliance. The MPC is interfaced to the unit using the USB interface. The Lynx MAT is active on the MPC. (Note If Maint Mode is not accessible, then it is likely that 2 minutes have passed since power was cycled with no GPS lock. Cycle power again.) 1. From the Lynx MAT select Info Versions. See Figure 3-5 for an example of this screen. 2. Use the versions screen to verify that the composite software and boot software are correct for this installation. Details on software part numbers and versions are available in the General Information section under paragraph heading Software Versions. If a software part number and version is found to be incorrect, update using the procedures located in the maintenance section of this manual. Figure 3-5: Lynx MAT Example of Check Versions 0040-17011-01 Installation Checkout Page 3-7 Revision G
3.6 SELECT CONFIGURATION OPTIONS This procedure is used to configure the NGT-1000/-2000/-2500s and must be completed prior to performing the Installation Checkout for first time installations. The Log Sheet provided in Appendix C should be filled out prior to this procedure and maintained with the aircraft s permanent records. If a configuration file has already been created using the Lynx MAT Backup function, then it may be used to load the data options. The configuration restore procedure is located in the maintenance section of this manual. An unlock code is required to enable the model NGT-2500. Contact L-3 Avionics Systems Customer Service to obtain the code. If the Lynx MAT is not connected or is disconnected the left side panel color changes to a light gray and the Not Connected message is displayed at the bottom of the tool screen. Re-connect by doing the following - from the Lynx MAT panel select Connect Appliance USB. This is required each time the unit power is cycled. Place the curser over option titles to view tool tips (not always available). A DCM read monitor that checks the interface of the unit and DCM is located at the top of the each configuration page. A Warning message is shown when the user first attempts an operation that requires confirmation from the user stating Changes should be done by trained service personnel. The user will need to press the confirm button to acknowledge this warning. No configuration changes take effect until they are entered, applied, and power is cycled to the unit. Pressing Apply from any setup/configuration/modify screen applies all changes from all screens. These procedures assume the following: Power is being supplied to the NGT-1000/-2000/-2500 and system components (i.e. antenna, display, and controllers). The Lynx MAT is active on the MPC. The MPC is connected to the unit via the USB interface The MPC and unit are communicating. 3.6.1 Aircraft Options 1. From the Lynx MAT select Setup Configuration Modify Aircraft. See Figure 3-6. Figure 3-6: Lynx MAT Aircraft Options Page 3-8 Installation Checkout 0040-17011-01 Revision G
2. Enter the information specific to the installation for the intended certification. Review the information below before entering the data. Call Sign. This is the Flight ID / tail number (Aircraft Registration Number i.e. N12345) and is assigned unique to each aircraft for voice communications purposes. In the U.S., this typically begins with N and is 6-7 digit. This information must be entered before any DCM changes can be saved. The Call Sign can have a maximum of 8 alphanumeric and blank characters. The Call sign may not be started with or contain a blank and in the U.S. may not contain the letters I or O. ICAO Address (Octal). (Mode S Identifier). This 24-Bit (8-digit octal) unique address is assigned to an aircraft during the registration process. The code can be obtained from either the aircraft registration certificate or the N number inquiry page http://registry.faa.gov/aircraftinquiry/. (See Figure 3-7 for an example location indicated with arrow). All eight (base 8 or octal) digits of the ICAO address must be entered before upgrading the unit to a NGT-2500. Leading zeros are not automatically added. If the ICAO address is changed after the model upgrade code is entered, than the unit will be downgraded to a NGT-2000 and a new upgrade code will need to be obtained. Figure 3-7: Example of FAA Registry Website VFR Code (Octal). Permits the use of different VFR codes for different regions / altitudes in the world. (i.e. 1200 for USA). 0040-17011-01 Installation Checkout Page 3-9 Revision G
Aircraft Emitter Category. This information provides an indication of the aircrafts size and performance capabilities. Emitter categories are defined below: EMITTER CATEGORY Unknown Light Small Large High Vortex Large Heavy High Performance Rotorcraft Glider/Sailplane Lighter than Air Parachutist Ultra Light UAV Space Surface - Emergency Surface - Service Point Obstacle Cluster Obstacle Line Obstacle DESCRIPTION No aircraft type information. If no emitter category fits the installation, seek guidance from the FAA. Light (ICAO) < 15,500 lbs. This includes very light aircraft (light sport aircraft) that do not meet the requirements of 14 CFR 103.1. Small 15,500 to 75,000 lbs. Large 75,000 to 300,000 lbs. High Vortex Large - 75,000 to 300,000 lbs. that has been determined to generate a high wake vortex. (e.g. B757). Heavy (ICAO) - > 300,000 lbs Highly Maneuverable > 5G acceleration and > TAS high speed. Any rotorcraft regardless of weight. Any Glider/Sailplane regardless of weight. Any lighter than air (airship or balloon) regardless of weight. Sky diver A vehicle that meets the requirements of 14 CFR 103.1. Light sport aircraft should not use the ultra light emitter category unless they meet 14 CFR 103.1. Any unmanned aerial vehicle or unmanned aircraft system regardless of weight. Trans-atmospheric vehicle Emergency vehicle Service vehicle Includes tethered balloons Cluster Obstacle Line Obstacle Aircraft Length (feet). This parameter sets the aircraft dimension that will be transmitted to ATC and other aircraft. Aircraft Width (feet). This parameter sets the aircraft dimension that will be transmitted to ATC and other aircraft. Air/Ground Indication: This setting is based on the interconnect wiring for Pin 53 (Discrete Input 3 WOW). The Aircraft ground indication can be wired for electrically Open or Ground. Determine the correct setting by referring to the interconnect wiring diagram for the aircraft to. If Pin 53 (WOW input) is not part of the installation then select Not Available. Note: Selecting Ground on Ground or Open on Ground forces the Aircraft Min Ground Speed Threshold When In Air and Altitude Change For Ground To Air to be zero. Aircraft Max Ground Speed Threshold When On Ground is editable. The Ground Speed Threshold for True Track Validity is always set to 7. Aircraft Min Ground Speed Threshold When In Air (knots). This sets the minimum ground speed of the aircraft, used in determination of air - ground status while the aircraft is in - air. This may be set only when the Air/Ground Indication is set for Not Available. o For an aircraft with an air/ground discrete, this value is automatically hard coded to 0, therefore only using the discrete. o For an aircraft without an air/ground discrete, the ground speed threshold is set below which the aircraft status changes to on-ground. For non-rotorcraft, set a value of 50 % below Vs0 to be certain the on-ground setting occurs conservatively. The value is set up as the minimum speed of the aircraft in knots while in air. This value is not available for Rotorcraft because rotorcraft will not be set to on-ground after having been in-air within a given power cycle. Page 3-10 Installation Checkout 0040-17011-01 Revision G
Aircraft Max Ground Speed Threshold When On Ground (knots). This sets the max ground speed of the aircraft, used in determination of air - ground status while the aircraft is on - Ground. This threshold must be manually set. This sets the maximum ground speed threshold at which the air/ground switch is declared as stuck on ground and at which the aircraft status is overwritten to in-air. o For a non-rotorcraft with an air/ground discrete set the threshold to the value of half the takeoff speed (Vr -50%). o For a non-rotorcraft without an air/ground discrete, set the threshold to VS0 to be conservative. o For a Rotorcraft (either with or without an air/ground discrete) set the threshold to a stationary GPS ground speed error level to ensure stationary readings are not mistakenly placing aircraft in air around 3 knots. Ground Speed Threshold for True Track Validity (knots). This is to provide an indication of the groundspeed threshold for the ownship track angle to be considered valid. This is always set to 7 and is not editable. Altitude change for ground to air (feet). This provides the minimum elevation above the ground reference for the air/ground status to be considered as In - Air. This may be set only when the Air/Ground Indication is set for Not Available. GPS Antenna Offset Lateral (feet). The GPS Antenna Offset lateral indicates the lateral distance between the longitudinal center line of the aircraft and the GPS Antenna. GPS Antenna Offset Longitudinal (feet). The GPS antenna offset longitudinal indicates the longitudinal distance between the nose of the aircraft and the GPS antenna. GPS Antenna Direction (with respect to lateral axis). Sets the direction of the GPS antenna lateral offset (left or right of the longitudinal centerline). Audio Volume. (NGT-2000/-2500 only) Use for Installation adjustment of audio output volume (Future). 3. Click on Apply after all information is entered. This information is saved to the DCM. 0040-17011-01 Installation Checkout Page 3-11 Revision G
3.6.2 Altitude Options 1. From the Lynx MAT select Setup Configuration Modify Altitude. See Figure 3-8. Figure 3-8: Lynx MAT Altitude Options 2. Enter the information specific to the installation for the intended certification. Review the information below before entering the data. Baro Altitude Source. Indicates if the Baro Altitude source is RS-232 or 11-bit discrete Gillham code. Selecting RS-232 sets the NIC Baro to Altitude is non-gillham or crosschecked. Selecting Gillham Code sets the NIC Baro to No altitude integrity and gray s out (N/A) the RS-232 Altitude Protocol and Pressure Altitude Baud Rate Override. NIC BARO. Sets the NIC (navigation integrity category) baro to be used in ADS-B Messages. This selection is determined by the Baro Altitude Source. RS-232 Altitude Protocol. Sets the protocol for the serial altitude encoder installed. Selecting one of these options automatically sets (but can still be overridden) the Pressure Altitude Baud Rate Override. Pressure Altitude Baud Rate Override. Used to override the automatic selection of baud rate when one of the 7 protocols is selected. Altitude Resolution. Used in setting of NGT output encoding for compatibility with external systems. Set to 100 foot if using Gilham code encoder; otherwise set to 1 foot. 3. Click on Apply after all information is entered. This information is saved to the DCM. Page 3-12 Installation Checkout 0040-17011-01 Revision G
3.6.3 Config Settings 1 1. From the Lynx MAT select Setup Configuration Modify Config Settings 1. See Figure 3-9. NGT-2500 Figure 3-9: Lynx MAT-Config Settings 1 NGT-1000 2. Enter the information specific to the installation for the intended certification. Review the information below before entering the data. CSID Logic. Call-Sign Identification (CSID) logic configuration setting shall be enabled or disabled in the DCM. When the CSID logic is enabled, the UAT transmits call sign and Flight Plan ID alternately in the ADS-B messages. When CSID is set to disabled, only call sign is transmitted. This option is automatically set to Enabled and cannot be changed (grayed out). TSAA. (Future Option). ARINC Format. (NGT-2000/-2500 only) Used in creation of ARINC messages to be transmitted to Traffic Display. This option is typically set to STIF due to the limited use of CDTI displays. The STIF (Standard Traffic Information File) format is traffic data without directional data. Other aircraft are shown as diamonds. The DTIF (Directional Traffic Information File) format is traffic data with directional data. Other aircraft are shown as arrowheads. Note: This option is selectable for NGT-2000 and NGT-2500, but only functions with the NGT-2500. Note: DTIF output is provisional and is not supported with this version of the NGT-1000/- 2000/-2500 SW. When using the ARINC 429 output, set to STIF. Note: For NGT-1000 the ARINC format value is not used so it is always set to STIF. ADS-B WiFi Enable. (NGT-1000 only) Set to Disabled for normal NGT-1000 operation. (For NGT-2000/2500 operation it is always set to enabled.) 3. Click on Apply after all information is entered. This information is saved to the DCM. 0040-17011-01 Installation Checkout Page 3-13 Revision G
3.6.4 Config Settings 3 1. From the Lynx MAT select Setup Configuration Modify Config Settings 3. See Figure 3-10. Figure 3-10: Lynx MAT - Config Settings 3 2. Enter the information specific to the installation for the intended certification. Review the information below before entering the data. Control Panel Type. Used to indicate if or which control panel used is: [SL70/GSL 71 (RS-232) not yet available, do not select], GTX 327 or GTX 330 (RS-232), or CP-2500 Control Panel. Selecting CP-2500 grays out the RS-232 Control Panel Baud Rate Override. RS-232 Control Panel Baud Rate Override. (1200, 9600). This field is inhibited when the control panel type is not a RS-232 type. Anonymous Mode. Indicates if the aircraft has the ability to use Anonymous Mode or not. This function may only be used by the CP-2500 Control Panel. Pilot Entry of Flight ID. Disabled - typical configuration or Enabled. This function may only be used by the CP-2500 Control Panel. Set to Enabled to allow the option of pilot entry of a flight ID number in place of the "N" number, if the flight ID is being used in place of the "N" number. 3. Click on Apply after all information is entered. This information is saved to the DCM. Page 3-14 Installation Checkout 0040-17011-01 Revision G
3.6.5 RS-422/RS-232 Options 1. This page is not available for the NGT-1000. Installations for the NGT-1000 can ignore this procedure. 2. From the Lynx MAT select Setup Configuration Modify RS-422/RS-232 Options. See Figure 3-11. Figure 3-11: Lynx MAT - RS-422/RS-232 Options 3. Enter the information specific to the installation for the intended certification. Review the information below before entering the data. Display Interface. (NGT-2500 only) Set this to GMX200 (Traffic Alert) to output traffic over RS-232, RS-422, or Wi-Fi otherwise set to none. Note - Must be set to GMX-200 (Traffic) to receive information over RS-232 WiFi Baud Rate. (NGT-2500 only) Sets the baud rate of the RS-422 output. Typically this is set to 38400. This must be manually set. (future option) WiFi Baud Rate. (NGT-2000/-2500 only) Sets the baud rate to be used for the Wi-Fi (RS-232) communication. 115200 is the default rate for WiFi Serial Adapter RN370M (or L-3 P/N 9080-10024-01) 4. Click on Apply after all information is entered. This information is saved to the DCM. 3.6.6 Backup 1. From the Lynx MAT select Setup Configuration Backup. When this screen is entered the MPC attempts to create a backup copy of the MPC, if it is not already loaded. 2. Click Save to copy the configuration information to a file on the MPC. See Figure 3-12. If operation worked... status bar indicates: "Save of DCM succeeded" If the DCM data is not loaded after the Save button is pressed a message is shown on the screen to indicate this. Instructions are given on how to attempt to get the data loaded. If MAINT mode cannot be entered, then cycle power to the unit and try again. After saving these settings, the file acquired can then be used to restore an aircraft s configuration settings later. The restore command instructions are found in section 4.4.3 of this document. 0040-17011-01 Installation Checkout Page 3-15 Revision G
Figure 3-12: Lynx MAT - Configuration Backup 3.6.7 Clear Fault Log Instructions to save these logs (if needed) are provided in the maintenance section. 1. Clear the fault log from the Lynx MAT by selecting Info Fault Log See Figure 3-13. 2. Select Clear button. 3. Answer Yes to confirmation dialogs. 4. Cycle power to the unit. 5. The calibration and configuration setup is complete. Figure 3-13: Lynx MAT Fault Log Page 3-16 Installation Checkout 0040-17011-01 Revision G
3.7 UPGRADE MODEL Use this procedure to upgrade the NGT-2000 to a NGT-2500. The selection is only available when NGT-2000-LRU is at the top of the item list. It is required that the ICAO Address be set up in the configuration options before the upgrade procedure is performed. The unlock code is set to only one ICAO Address and no other address will work. (Note - If needed, remove the NGT-2500 upgrade by attempting to modify the ICAO Address. When prompted that a change to the ICAO Address results in downgrading the unit, select Yes.) 1. From the Lynx MAT select Update Upgrade Model. 2. Press the Upgrade button. See Figure 3-14. (Note If the message Cannot upgrade with unsaved data is shown on the Lynx MAT, then either apply the DCM changes or re-connect.) 3. Enter the unlock code and press OK. (Note - characters are case sensitive.) 4. The message Model number change succeeded. Unit will reset. is shown. 5. Confirm the change after reconnecting and observe that the model listed on the Lynx MAT is identified as NGT-2500. Figure 3-14: Lynx MAT Upgrade Model 0040-17011-01 Installation Checkout Page 3-17 Revision G
3.8 INSTALLATION CHECKOUT This procedure validates the installation and configuration setup of the NGT-1000/-2000/-2500 and secondary equipment. Installers are advised to read through the entire procedure before performing the checkout. Take the following into consideration prior to installation. NOTE The compatible display/control panel/ped may not operate exactly as stated in this checkout. Refer to the operating instructions for the controller/display/ped for details. Perform the installation checkout procedure with aircraft on ground. Perform only those checks that are applicable to the installation. To conserve aircraft battery power, it is recommended that the aircraft be connected to an external aircraft power source during installation and checkout. An IFR-6000 (or equivalent) Ramp Test Set with UAT capabilities is required. These checks assume familiarity with the set up and operation of the ramp test set. All test equipment shall be calibrated in accordance with the manufacturer's recommendations. The CP-2500 Control Panel is specifically designed to interface with the NGT-1000/-2000/-2500 and may be used during the checkout to verify the operation of the NGT-1000/-2000/-2500. Depending on the installation - when power is applied to the unit the following indication is observed while the GPS is initializing (acquiring a signal). o The CP-2500 shows a GPS INIT message. o The ADS-B Out Fail indicator lamp flashes at a slow rate. o (NGT-2000/-2500 only) Compatible equipment may have its own kind of message or indication. It is normal for STIF displays to indicate "DATA-FAIL" until GPS signal is acquired. (NGT-2000/-2500 only) It is normal for the No ADS-B Coverage lamp to be ON during checkout if there is not an ADS-B ground station or signal within range. Note: The lamp will not extinguish even when simulating signals with the IFR-6000. Some tests require the unit be set to Ground Test Mode. This is accomplished from the Lynx MAT by selecting Service Ground Test Overrides and setting the ground speed to greater than 7kts (which sets the unit to Operate mode) and setting the track to match the present aircraft true heading (which points the traffic on the traffic screen in the correct orientation). Press the Enable button to enter ground test mode and disable to return to normal operation mode. See Figure 3-15. Note The Ground Test Override selection is removed when the unit and MPC are connected via WiFi. NOTES 1. When entering heading information into the IFR-6000 UUT HDG entry field make sure to enter either the same simulated heading as was entered into the Lynx MAT own direction field or the actual aircraft heading (true heading) as appropriate. 2. Determine true heading by adding the East Variation to the aircraft current magnetic heading or subtracting the West Variation to the aircraft current magnetic heading (e.g. airport KGRR has a 04W variation so with a magnetic heading of 290 the true heading would be 286). Go to AirNav.com and type in the airport location to find the variation for that area. Page 3-18 Installation Checkout 0040-17011-01 Revision G
The End Session selection is used to set the NGT-1000/-2000/-2500 into operational mode. Press the End Session button. If successful a dialog window is shown with the following message Unit in Operational Mode. The Lynx MAT disconnects from the unit. The screen becomes blank. If changing to operational mode is not successful the Lynx MAT remains connected and a dialog window is shown with the following message Request for operational mode timed out. These procedures assume the following: o Power is being supplied to the NGT-1000/-2000/-2500 and system components (i.e. antenna, display, and controllers). o The Lynx MAT is active on the MPC. o The MPC is connected to the unit via the USB interface o The MPC and unit are communicating. (Green connected indicator on the MAT.) Figure 3-15: Lynx MAT Ground Test 0040-17011-01 Installation Checkout Page 3-19 Revision G
3.8.1 UAT GPS Status The power ON self-test (PBIT) and continuous self-test (CBIT) checks the operation and the major hardware components in the unit. Verify this by viewing the Status information provided by the Lynx MAT as follows: 1. From the Lynx MAT select Service UAT GPS Status. See Figure 3-16. Figure 3-16: Lynx MAT UAT GPS Status 2. Review the Bite Status and verify that no failures, indicated by a 0 in the right column. A BITE Status of 1 for BIT Value 0 indicates that the Self Test has not completed and is in progress. 3. If a failure is observed the problem must be resolved before continuing with the checkout. If the BITE Status for BIT Values 1, 2, 3, 5, 7, 9, 10, 11, 12, 14, 15, 16, 17, 18, 21, 22, 23, 25, 26, 27, 30, or 31 are 1 (failed) then cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal of the unit. If the BITE Status for BIT Value 29 (GPS Antenna is short) is 1 (failed) then cycle power to the unit. If the fault persists refer to the troubleshooting information in the maintenance section to resolve. Page 3-20 Installation Checkout 0040-17011-01 Revision G
3.8.2 UAT GPS Functional Status The power ON self-test (PBIT) and continuous self-test (CBIT) checks for the proper operation of input/output signals. Verify this by viewing the functional status of the UAT GPS provided by the Lynx MAT as follows: 1. From the Lynx MAT select Service UAT GPS Functional Status. See Figure 3-17. 2. Review the Status and verify that no failures, indicated by a 1 in the right column, are present. 3. If a failure is observed the problem must be resolved before continuing with the checkout. Use Table 3-1 and the troubleshooting help in the maintenance section to resolve the issue. Figure 3-17: Lynx MAT UAT GPS Status 0040-17011-01 Installation Checkout Page 3-21 Revision G
Table 3-1: UAT GPS Functional Status DESCRIPTION ADS-B Message Transmission Lesser than lower threshold ADS-B Message Transmission higher than lower threshold Invalid ICAO Address Broadcast schedule violation Mode A Code Mismatch GPS position unavailability Air/Ground Discrete Failure Control Panel Failure ACTION 1. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal of any equipment. 1. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal of any equipment. 1. Change DCM setting (ICAO address should be other than 00000 or FFFFFF in hex). See paragraph 3.6.1 (aircraft options) for details. 1. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal of any equipment. 1. The code on the CP-2500 control panel and the transponder are different. This code must be the same to remove mismatch error. 2. Check the troubleshooting procedures in the maintenance section. If the fault persists, contact L 3 Field Service before removal of any equipment. 1. This indicates that the GPS cannot acquire a position. GPS attempts to acquire for 2 minutes, and then a FAIL indication is shown (fail lamp, etc). 2. Check the troubleshooting procedures in the maintenance section. 1. Check that the Air/Ground Pin is wired correctly and that it is not damaged. 2. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal of any equipment. 1. Verify that Control panel is ON. 2. Check control panel connections. If using a GTX327/330, verify that RS-232 output of the transponder is set to REMOTE. 3. Verify that the DCM is configured for the correct control panel type. See section 3.6.4 (Config settings 3). 4. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal of any equipment. Page 3-22 Installation Checkout 0040-17011-01 Revision G
3.8.3 Indicator Lamp Check Verify the following indicator lamps are functioning properly (if installed) during the checkout. These lamps are required if the control panel installed on the aircraft does not provide the indications stated below. Note The CP-2500 is capable of displaying messages for both these indications. 1. ADS-B Out Fail This lamp does the following depending on the situation: Flashes at a slow rate (1 flash per 2 seconds) while the GPS is initializing. Check by cycling power to the unit. If no GPS signal is available, the flashing lasts only 2 minutes before the lamp stays ON. Normally GPS position is acquired within 2 minutes, and the lamp extinguishes. Flashes at a fast rate (2 flashes per second) if a code mismatch is detected. Check by entering the different Mode A Code from the one being transmitted by the transponder. The amber lamp is ON when the ADS-B has failed or if the Standby / Operate switch or CP- 2500 is set to Standby. 2. (NGT-2000/-2500 only) No ADS-B Coverage This blue lamp is ON if no ground station signal is detected. The lamp is OFF when a signal is detected by a ground station. 3.8.4 Discrete Switch Checks Verify the following external switches are functioning properly (if installed) during the checkout. The Ident and Standby / Operate switches are required if the control panel installed on the aircraft does not provide the functions stated below. Note The CP-2500 is capable of performing these functions. 1. Verify that the IDENT Input switch causes an IDENT annunciation on the IFR-6000 for approximately 18 +/- 10 seconds. Note Due to sampling interval of the IFR-6000, a precise reading is not obtainable on ground. 2. Set the Standby / Operate switch to Standby and verify that the ADS-B Out Fail lamp is ON, indicating a fail condition. Set the switch to Operate and verify that the ADS-B Out Fail lamp is OFF. 3. The On -Ground switch function is verified by viewing the On Ground status message on the IFR-6000 during other checkout procedures. 3.8.5 Control Panel Check The NGT-1000/-2000/-2500 requires a compatible control panel (RS-232) to operate. The instructions provided in this manual for a compatible control panel is limited. Refer to the manufacturers control panel manual for operation and checkout procedures. When interfacing to a compatible transponder there may be set up steps for the transponder that need to be done before it will communicate with the NGT-1000/-2000/-2500. As an example the GTX 327 is required to be configured for Remote to establish communication with the NGT-1000/-2000/- 2500. 3.8.6 Display Check The NGT-2500 may be interfaced to a compatible traffic display (ARINC 429) and weather display (RS-422). The instructions provided in this manual are generic. Refer to the manufacturers display manual for operation and checkout procedures. A functional check with the NGT-2500 is accomplished during the check of the ADS-B In, TIS-B, FIS-B and any other checks requiring the use of a Display. 0040-17011-01 Installation Checkout Page 3-23 Revision G
3.8.7 PED Check The NGT-2000/-2500 may be interfaced to a compatible PED (i.e. Tablet or Smartphone). The PED interface requires that a WiFi Serial Adapter be connected to the wiring harness and the WiFi configuration option be set up. The PED requires a compatible APP. The PED and NGT-2000/-2500 WiFi interface must be configured. Refer to paragraph 3.4. A functional check with the NGT-2000/-2500 is accomplished during the check of the ADS-B In, TIS-B, FIS-B and any other checks requiring the use of a PED. 3.8.8 GPS Operation Check This check requires that the GPS antenna to be open to a clear sky or a GPS Simulator or repeater to generate the necessary signal. 1. From the Lynx MAT select Service Live Data GPS. 2. Cycle power to the NGT-1000/-2000/-2500 and allow the GPS to acquire the position Acquisition of signal can take up to 2 minutes. 3. Observe that the GPS data is being received and signal strength is within 30 to 50 db. Note The Navigation State always shows RAIM even though the device is actually in WAAS mode. See Figure 3-18. If the GPS reception is a problem, check the following: The GPS signal may be blocked; move the aircraft to an open environment or input a GPS signal using test equipment. Check the GPS antenna or wiring for installation issues. Check that the L-Band and GPS antenna cables are not swapped. Check the fault log (Info Fault Log) for issues. Figure 3-18: Lynx MAT Live Data-GPS Page 3-24 Installation Checkout 0040-17011-01 Revision G
4. Verify that the ADS-B Out Fail Lamp (if installed) is flashing until the position is available and then remains OFF indicating that the GPS position is computed by the Unit. If a CP-2500 Control Panel is installed the GPS INIT and ADS-B SYSTEM FAIL messages are removed from its display. 5. Verify that the GPS position agrees with a known reference point. 6. Verify that the Day, Month, and Year data is correct. 7. Verify that the signal Strength (C/No) of 30-50dB is displayed in the GPS signal strength for all the GPS/SBAS satellites in view. 8. Turn ON other avionics and verify that the signal Strength (C/No) of 30-50 db is displayed in the GPS signal strength for the satellites do not degrade significantly and position remains steady. 9. Turn ON VHF Com radios. Verify that the signal Strength (C/No) of 30-50 db displayed in the GPS Receiver Information Packet for the satellites do not degrade significantly and position remains steady. 10. If the aircraft is TAS/TCAS equipped, turn on the TAS/TCAS system and verify that the signal Strength (C/No) of 30-50 db displayed in the GPS signal strength for the satellites do not degrade significantly and position remains steady. 11. Any GPS interference (significant degrade in signal strength) must be resolved prior to completing the installation. Use the troubleshooting procedures in the maintenance section for help. 3.8.9 ADS-B Out Check Before performing this check ensure that the GPS position is acquired, that the ADS-B Out Fail lamp (if installed) is OFF, and the display/ped is in ON. 1. From the ADS-B/GICB/UAT main screen on the IFR-6000, select UAT, then UAT MON. 2. Verify that the ADS-B Out test performed by the test set is successful. 3. Ensure correct AA (Aircraft Address) in HEX and OCTAL is displayed on the IFR-6000. This test should confirm the configuration settings made in Section 3.6.1 are correctly transmitted in the ADS-B Out messages. 3.8.10 ADS-B In Check This check is required for the NGT-2000/-2500 only. Before performing this check make sure that the GPS position is acquired, that the ADS-B Out Fail lamp (if installed) is OFF, and the display/ped is showing operate/standby mode. Standby is shown on traffic display (STIF) until the UAT is placed in the ground test Override mode with ground speed set to a value of 10 knots and then switches to "operate" mode. See paragraph 3.8 for details. Perform the ADS-B In check using an IFR-6000 (or equivalent) Ramp Test Set using the latest ADS- B update. The test set simulates ADS-B intruders by manually defining a position over the earth. Intruding flight parameters are programmed from the IFR-6000 screen. If the WiFi option is installed and a WiFi Serial Adapter is connected to the wiring harness. The PED requires a compatible APP be installed. The PED and NGT-2000/-2500 WiFi interface must be configured. Refer to paragraph 3.4. 1. From the ADS-B/GICB/UAT screen on the IFR-6000, select UAT, then GPS Status, and allow the unit to acquire a GPS position (GPS SYNC). 0040-17011-01 Installation Checkout Page 3-25 Revision G
2. Verify 978 MHz ADS-B In traffic information displayed on the unit with that being transmitted by the test set. a. From the ADS-B/GICB/UAT, select UAT, then UAT GEN, then ADS-B. Ensure targets are defined and UUT heading on the IFR-6000 is equal to aircraft true heading. Set RNG (nm) of at least one target to 15 Nm. Ensure UUT LAT and UUT LON on the IFR-6000 match aircraft s present position. Select Run Test. b. Observe that targets all targets are showing on the display (s). A difference of 100ft between the test set data and the displayed information is acceptable. Note: All traffic on STIF (ARINC 429) displays are non directional targets (open diamonds). If outer range target(s) do not display, possibly the incorrect Lynx MAT is being used. Refer to Section 1.12 (Software Updates) to update the Lynx MAT. 3. Verify 978 MHz TIS-B In traffic information display on the unit with that being transmitted by the test set. a. From the ADS-B/GICB/UAT screen on the IFR-6000, select UAT, then UAT GEN, then TIS-B. Ensure targets are defined and UUT heading on the IFR-6000 is equal to aircraft true heading. Ensure UUT LAT and UUT LON on the IFR-6000 match aircraft s present position. Ensure TIS-B SITE ID is set to 1 (or any number between 1 and 15). Select Run Test b. Observe that targets are showing on the display. A difference of 100ft between the test set data and the displayed information is acceptable. Note: All traffic on STIF (ARINC 429) displays are non directional targets (open diamonds). 3.8.11 FIS-B Uplink Check Before performing this check (NGT-2000/-2500 only) make sure that the GPS position is acquired, that the ADS-B Out Fail lamp (if installed) is OFF, and the display/ped is in ON operational mode. 1. Set the Ground Test Override using the Lynx MAT. See paragraph 3.8 for details. 2. Perform the FIS-B check using the IFR-6000 (or equivalent) Ramp Test Set. The test set simulates FIS-B ground base uplink (such as a METAR). 3. Verify that weather information (such as a METAR) is being displayed on the display/ PED. 3.8.12 Altitude Check 1. Verify the pressure altitude indicated on the primary flight instrument of the aircraft matches the pressure altitude output of the NGT-1000/-2000/-2500. Page 3-26 Installation Checkout 0040-17011-01 Revision G
3.8.13 Electromagnetic Interference (E.M.I.) Check Check the following applicable aircraft systems, as well as any other system or device that is not listed, for interference. Initial tests are to be conducted with the aircraft operating on external ground power. Disregard any system or device that does not apply. NOTE The Electromagnetic Interference Check is required only for initial system installations and not required if the NGT-1000/-2000/-2500 is removed or replaced. 1. Communications a. Cockpit Intercom Using the cockpit intercom, verify interference free communications between the crew while monitoring the effects of the NGT-1000/-2000/-2500. b. VHF Communications Set VHF communications radios to multiple frequencies and monitor effects of NGT-1000/- 2000/-2500 while transmitting and receiving. At a minimum, the frequencies listed below should be tested, in addition to locally available frequencies: Check the GPS signal status of the each satellite being received does not drop while transmitting each frequency for a period of 35 seconds. Degradation of individual received satellite signals below a point where navigation is no longer possible is not acceptable and will require that additional isolation measures be taken. For installations on rotorcraft, ensure that the rotor blades do not interfere with the received GPS signals. This problem has been experienced in some rotorcraft and varies with the rotation rate. Test the following frequencies for 25 khz COM channel spacing: 121.150 MHz 121.200 MHz 121.250 MHz 131.225 MHz 131.275 MHz 131.325 MHz 121.175 MHz 121.225 MHz 131.200 MHz 131.250 MHz 131.300 MHz 131.350 MHz In addition test the following frequencies for VHF radios with 8.33 khz channel spacing: 121.185 MHz 121.190 MHz 130.285 MHz 131.290 MHz 2. Navigation a. VOR / ILS Verify the operation of each VHF Nav receiver in both VOR and ILS modes (including glideslope) while monitoring the effects of the NGT-1000/-2000/-2500. b. DME Verify the operation of each DME while monitoring the effects of the NGT-1000/-2000/-2500. The same frequencies used for VOR and ILS testing may be used for this test. c. Marker Beacon Verify the operation of the Marker Beacon Receiver while monitoring the effects of the NGT- 1000/-2000/-2500. d. ADF Verify the operation of the ADF receiver while monitoring the effects of the NGT-1000/-2000/- 2500. Frequencies from each band should be tested when possible. Public broadcast stations are acceptable for conducting test. 0040-17011-01 Installation Checkout Page 3-27 Revision G
3. Flight Director / Autopilot Operate the flight director/autopilot system and verify it responds to commands from the flight guidance panel while monitoring the effects of the NGT-1000/-2000/-2500. 4. Compass System Verify each compass system is presenting correct information while monitoring the effects of the NGT-1000/-2000/-2500. 5. Attitude System Verify each attitude system is presenting correct information while monitoring the effects of the NGT-1000/-2000/-2500. 6. Safety Equipment a. TAWS (If Installed) Verify the function of the TAWS and Terrain Display while monitoring the effects of the NGT- 1000/-2000/-2500. b. Weather Monitoring System (If Installed) Verify the function of the weather monitoring system while monitoring the effects of the NGT- 1000/-2000/-2500. 3.8.14 Flight Test It is recommended that a flight test be conducted after installation to verify proper operation of the NGT- 1000 or NGT-2000/-2500 system per the AML STC. A flight test report can be obtained from the FAA by sending a request to 9-AWA-AFS-300-ADSB-AvionicsCheck@faa.gov, with aircraft registration number and date of flight. 3.8.15 Installation Checkout Complete This completes the Installation Checkout procedure. Page 3-28 Installation Checkout 0040-17011-01 Revision G
Section 4 Maintenance 4.1 INTRODUCTION This section contains general flightline maintenance and fault isolation procedures. Fault isolation is intended to aid in identifying and correcting invalidities or isolating failures to a defective assembly. 4.2 CONTINUED AIRWORTHINESS Regular maintenance of the NGT-1000/-2000/-2500 is not required except as included in this section and is to be maintained on a Condition Monitored basis. Condition monitoring is based upon the following: Visual observation by the user. All units have unlimited service life, where service life is defined as that point in time when repair is no longer economical. 4.2.1 Periodic Maintenance Perform the following at regular aircraft inspection intervals: Visually inspect for signs of corrosion. Visually inspect for condition of wiring, shield terminations for proper grounding, routing, and attachment/clamping. Check the security of the mounting hardware. It is recommended that an electrical bond check be performed between the unit and nearby exposed portion of the aircraft metallic structure and verify that the measured value is less than or equal to 2.5 milliohms. In the event of bonding check failure, remove the unit and clean it and its mounting holes at both the unit and the aircraft structure and reattach the unit. Re-verify the resistance between the unit and nearby exposed portion of aircraft metallic structure, and ensure it is less than or equal to 2.5 milliohms. 0040-170011-01 Maintenance Page 4-1 Revision G
4.3 FAULT ISOLATION Use the troubleshooting help provided in Table 4-1 for initial installations and debugging issues that may appear during operation. Use Table 4-1 to view observed failures or conditions and possible cause and corrective actions. The symptoms listed are for all the possible equipment installations. It is up to the user to identify their particular installation. Failures are typically observed via the indicator lamps (ADS-B Out Fail and No ADS-B Coverage) or through messages displayed on the control panel or display screens depending on the particular installation. A MPC connected to the USB port of the NGT-1000/-2000/-2500 is essential in troubleshooting. Refer to paragraph 4.4.4 and Table 4-2 for instructions on viewing fault logs and using the service functions of the Lynx MAT. The information provided here should be in conjunction with the information provided in Table 4-1. In addition, devices connected to the NGT-1000/2000/2500, such as a control panel or display can be useful for determining whether the NGT-1000/-2000/-2500 is functioning properly or if there are problems with the installation. NOTE The information listed in the Symptoms column encompass many of the possible issues that a technician may observe, but only some of the items may actually be seen depending on the model and the installation of optional equipment. If the CP-2500 is not installed, a locked standby/operate switch must also be installed. It should be noted that the ADS-B Out Fail Lamp is ON when the unit is in maintenance mode (via the Lynx MAT) or if the control panel or transmit switch is set to Standby. If the only corrective action left is to contact L-3 Field Service, then L-3 Field service personnel may request that a file be created using the MPC that would provide them with information on the unit (i.e. version, faults, and configuration). Create this file by going to the File menu of the Lynx MAT, selecting Save, and placing the file in a location that can be easily located for transfer to L-3 Field Service FieldService.Avionics@l-3com.com. Page 4-2 Maintenance 0040-170011-01 Revision G
Table 4-1: Troubleshooting SYMPTOMS No sign of power: Cannot communicate to the unit with the MAT tool. ADS-B Out Fail lamp and No ADS-B Coverage lamp (NGT- 2000/-2500 only) never illuminate at power ON. (NGT-2000/-2500 only) Traffic (STIF) displays indicate "DATA-FAIL" and no WI-FI information is available. CP-2500 (If installed) displays "ADS-B SYSTEM FAIL". Note: If one breaker is used for both devices, the CP-2500 may also be blank. At power on, ADS-B Out Fail lamp Flashes (slow rate) for 60-90 seconds and then remains ON. (NGT-2000/-2500 only) Traffic (STIF) displays indicate "DATA-FAIL" and WI-FI information is not available. CP-2500 displays "ADS-B SYSTEM FAIL". CAUSE / CORRECTIVE ACTIONS The NGT-1000/-2000/-2500 is not operating: 1. Verify the breaker is closed. Check and reset the circuit breaker. 2. Verify that the mating connector is secure. 3. Verify power and ground supplied to the unit. 4. If lamps do not illuminate, but you can connect to the unit with the MAT, then verify that the lamps have power from the aircraft dimming circuit. 5. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. The unit is operating, but has failed: If installation was previously operational: 1. Verify standby/operate switch is set to operate. If a CP-2500 is installed, verify mode set to "ALT". ( SBY mode on the CP-2500 indicates "FAIL" of the unit to indicate that it is not transmitting). 2. If a GTX-327 or 330 are being used as the control panel, verify that it is powered ON. 3. Connect to MAT and view fault logs and status screens to troubleshoot cause of the failure. 4. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. In new installation (Assuming wiring has been verified): 1. Verify DCM was configured properly, applied, and the power to the unit was cycled to apply those settings. 2. If a CP-2500 is installed, verify mode set to "ALT". ( SBY mode on the CP-2500 indicates "FAIL" of the unit to indicate that it is not transmitting). 3. If GTX-327 or 330 is installed, verify that the RS-232 output is set to "REMOTE". 4. Verify correct wiring to the standby/operate switch. The switch needs to be wired to ground (operate) for the unit to transmit, 5. Connect to MAT and view fault logs and status screens to troubleshoot cause of the failure. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. 0040-170011-01 Maintenance Page 4-3 Revision G
Table 4-1: Troubleshooting SYMPTOMS ADS-B Out Fail lamp and No ADS-B Coverage lamp (NGT- 2000/-2500 only) are ON. If installed, CP-2500 indicates ADS-B SYSTEM FAIL. The ADS-B Out Fail lamp Flashes (slow rate) for 120 seconds and then remains ON. (NGT-2000/-2500 only) The No ADS-B Coverage lamp is illuminated. (NGT-2000/-2500 only) Traffic (STIF) displays indicate "DATA-FAIL" and WI-FI information is not available. NOTE: If the traffic (STIF) display is in Standby mode, then that is an indication that GPS signal was available at least once during this power cycle, but has been lost. CP-2500 displays "GPS-INIT" for 2 minutes, followed by "ADS-B SYSTEM FAIL". The No ADS-B Coverage lamp stays illuminated. Note: No ADS-B Coverage lamp remains illuminated even when testing with an IFR- 6000. Displays Normal operation. CP-2500 displays No ADS-B Coverage. CAUSE / CORRECTIVE ACTIONS 1. Verify standby/operate switch is set to operate. If a CP-2500 is installed, verify mode set to "ALT". ( SBY mode on the CP-2500 indicates "FAIL" of the unit to indicate that it is not transmitting). 2. Check the fault log and live signals with the MPC. Failure can also be caused by loss of control panel signal to the NGT-1000/-2000/-2500. NOTE: If CP-2500 is installed, verify it is turned on. If using a GTX-327/330, verify it is turned on. 3. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. GPS attempts to acquire for 2 minutes, and then a FAIL indication shown (fail lamp, etc). This indicates that the GPS cannot acquire a position: 1. Verify correct wiring of the GPS antenna. Verify that the GPS and L-band antenna cables are not swapped. 2. If inside a hangar, verify GPS repeater is operational and is within line of site of the aircraft GPS antenna. 3. If outside the hangar, verify the GPS antenna has a clear view of the sky. 4. Connect the MAT and verify fault logs and check for GPS reception status. Signal strengths should be between 30-50db to be usable. 5. Remove the GPS antenna connector from the unit, and verify that approx +12 VDC is available at the center pin of the GPS connector of the unit. 6. Remove power from other broadcasting equipment and wait 2 minutes for the GPS to acquire a signal. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. (NGT-2000/-2500 only) A ground station is not being detected by the unit. 1. Aircraft may not be within range of a local ground station. 2. If No ADS-B Coverage lamp continues to remain illuminated even when airborne within range of a ground station, check the lamp wiring for proper connection to the unit. 3. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. NOTE When crossing boundaries between ground station coverage areas, out of coverage indications are possible. Page 4-4 Maintenance 0040-170011-01 Revision G
Table 4-1: Troubleshooting SYMPTOMS The ADS-B Out Fail lamp flashes (fast rate). (NGT-2000/-2500 only) Displays Normal operation. CP-2500 displays CODE MISMATCH -CHECK TRANSPONDER". Note: This does not apply if using GTX-327/330 as a control panel, as there cannot be a mismatch. CAUSE / CORRECTIVE ACTIONS The unit cannot detect a mode "A" code being transmitted from the transponder. 1. Transponder is not powered or is in Standby (STB) mode. The transponder must be in ALT or ON mode to remove this message. 2. Transponder antenna and the L-band antenna (for UAT operation) are located too far apart so that the unit cannot detect the transmitted Mode A Code from the transponder. Refer to the installation section for the chart for maximum distance between antennas. 3. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. NOTE Occasional mismatch detections may occur due to interference conditions. However, flashing should not be continuous when matching Mode A code is present. The ADS-B Out Fail lamp flashes (fast rate). (NGT-2000/-2500 only) Displays Normal operation. CP-2500 displays CODE MISMATCH - PUSH TO ACCEPT XXXX. Note: This does not apply if using GTX-327/330 as the control panel; as there cannot be a mismatch. Lamps - Normal operation. Traffic (STIF) displays continues to show "DATA- FAIL" even though no ADS-B Out Fail lamp or message is indicated. CP-2500 - Normal operation. Lamps - Normal operation. Traffic symbols on the Traffic display are open diamonds and not directional traffic (arrowheads or triangles). CP-2500 - Normal operation. The unit is detecting a different code selected in the transponder from the code entered into the CP-2500. 1. Press the small knob on the CP-2500 to change it to the same squawk code as the selection set in the CP-2500. Or, alternately, change the squawk code in the transponder to match the code entered into the CP-2500. (NGT-2000/-2500 only) Display is not receiving 429 STIF data. Normal operation is that "DATA-FAIL" is displayed until GPS is acquired, and then the STIF display should indicate Standby mode. 1. Verify DCM and display are configured for STIF traffic and the correct speed. The unit emulates L-3 Avionics System SKY497 format. This is a high speed 429 bus. Consult display manufacturer's installation manual for proper set-up procedures. 2. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. (NGT-2000/-2500 only) This is normal for all STIF displays. Directional symbology can only be displayed on a DTIF display. 1. The traffic display does not support the DTIF format necessary to show directional data provided by ADS-B. 2. The directional information that is being received by the unit does not have directional data. The unit continues to transmit non-directional data to the traffic display. 0040-170011-01 Maintenance Page 4-5 Revision G
Table 4-1: Troubleshooting SYMPTOMS ADS-B Out Fail lamp is OFF, and no other fail indications are showing. The No ADS-B Coverage lamp is ON unless the aircraft is receiving an actual ground station. Use of the IFR-6000 does NOT extinguish the lamp. Traffic not appearing on the Traffic Displays and they indicate Standby mode. Also, no traffic showing on the WI-FI device while simulating ADS-B (UAT) traffic with a ramp tester such as the IFR-6000. CP-2500 - Normal operation. Baro Altitude (Pressure altitude) is not being transmitted as indicated by the IFR-6000 in Monitor mode. Geometric altitude is being transmitted from the unit, and all other information is available. ADS-B Out Fail lamp is OFF. (NGT-2000/-2500 only) Display/PED Altitude information is shown as dashes. The CP-2500 altitude page displays "INVLD PA". CAUSE / CORRECTIVE ACTIONS (NGT-2000/-2500 only) The Traffic (STIF) displays revert to standby whenever the GPS groundspeed is below 7 knots. This speed assures a valid aircraft track for orientation of traffic on the displays. 1. Run Self Test on unit using the CP-2500, if available (instructions are located in installation checkout section). If 3-track traffic image does not appear, an open wire or other connection problem exists. If traffic does appear, the below override setting should be observed. 2. Place the unit in ground test mode using the MAT tool. This screen gives the technician the option to simulate a groundspeed value of 10 knots and also the aircraft heading. NOTE: Once in Ground test mode with a ground speed of 10 knots, the STIF displays should automatically switch to Operate mode. 3. Certain software versions of the IFR-6000 may inhibit traffic if the vertical rate on the simulated target is set to "LEVEL". It is recommended to set the simulated targets to either climbing or descending targets. Note - This issue has been resolved on the IFR-6000 Version 03.09.00 and later. Either the unit is not receiving BARO-ALT (Pressure altitude), or the control panel is set to ON mode. 1. Verify that the GTX-327/330, or CP-2500 is set to ALT Mode. 2. Verify that the unit is receiving BARO-ALT (Pressure altitude). If a CP-2500 is being used it can be viewed by going to the Altitude page. The page should display the altitude for example as: 800PA (for 800 ft pressure altitude). In the case of missing altitude, it displays "INVLD PA". Pressure altitude is a required output for FAA compliance. In the event of the loss of Pressure altitude, the UAT device continues to operate by reverting to GPS altitude as a back-up. The GPS altitude can be viewed with the MAT device. NOTE Some altitude encoders can take 1-3 minutes to output data. Page 4-6 Maintenance 0040-170011-01 Revision G
Table 4-1: Troubleshooting SYMPTOMS Lamps - Normal operation. No traffic or weather information is being displayed on the PED over WI-FI. CP-2500 - Normal operation. Lamps - Normal operation. FIS-B weather (such as METARS, NEXRAD, CONUS Data) is not being seen on the weather displays. CP-2500 - Normal operation. Cannot connect to the unit with the MPC/MAT tool. Lamps - Normal operation. CP-2500 - Normal operation. (NGT-2000/-2500 only) Displays - Normal operation. The four digit squawk code is missing from the ALT and ON screen of the CP-2500. The ADS-B Out Fail lamp Flashes (slow rate) for 60-90 seconds and then remains ON. Note: Code appears OK in SBY mode. CAUSE / CORRECTIVE ACTIONS (NGT-2000/-2500 only) 1. Verify WI-FI module is receiving data from the unit. For example, on the RN-370M models, this is indicated from visually seeing the blue flashing light on the unit. If indicator light is not flashing, verify WI-FI is configured properly in the DCM settings. Also verify the device has power (batteries) and that the connections between the WI-FI module and the unit are correct. 2. If WI-FI module is indicating it is receiving data, verify that the PED Wi-Fi connection is configured to receive the correct device name. (I.E. "WI-FLY-100"). 3. Verify PED App is compatible with the unit. 4. Verify the configuration setting for the PED App being used. 5. Replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. (NGT-2000/-2500 only) Ground testing with the IFR-6000 can only simulate textural data such as METARS. 1. When used in flight, the aircraft must be within range of a ground station No OUT OF COVERAGE message (CP-2500) or No ADS-B Coverage lamp is OFF. NEXRAD information is only transmitted every 5 minutes, and CONUS information is only available from certain ground stations, and is only transmitted every 15 minutes. 1. The USB connection to the unit requires special drivers that must be installed on the MPC being used (see the general information section for details). If that has been successfully accomplished, replacement of the unit may be required. Contact L-3 Field Service before removal of the unit. 2. Verify that the MAT being used is compatible with the software in the unit being serviced. Contact L-3 Field service for more information. This is an indication that the Lynx MSS has failed and may also be seen if the aircraft is in the hanger with no GPS signal for > 2 minutes. 1) Move the aircraft into an area with access to a GPS signal. 2) Cycle power to the Lynx MSS. 3) Replacement of the Lynx MSS or system component may be required. Contact L-3 Field Service before removal of the unit. 0040-170011-01 Maintenance Page 4-7 Revision G
4.4 USING THE MAINTENANCE PC The Maintenance PC (MPC) and Lynx Maintenance Application Tool (Lynx MAT) are used to interface with the NGT-1000/-2000/-2500 to load software/firmware/, view factory / version data, retrieve fault logs, data recording, and simulating live data. NOTE The screen information for Lynx MAT is very similar between the NGT- 1000, NGT-2000, and NGT-2500. Differences in appearance are either noted or will be shown in the following procedures. These procedures assume the following: Power is being supplied to the NGT-1000/-2000/-2500 and system components (i.e. antenna, display, and controllers). The correct Lynx MAT software is being used to load software. See the General Information section (Software Versions) for software details. The software to be loaded is available on the MPC being used. The Lynx MAT is active on the MPC. The MPC is connected to the unit via the USB interface The MPC and unit are communicating. Additional instructions on using the MPC are given in the Installation Checkout section. 4.4.1 Load Software This procedure is used to update the system software used by the NGT-1000/2000/2500. 1. Ensure that the MPC and NGT-1000/-2000/-2500 are in Maint Mode by viewing the Lynx MAT status bar. If needed press the Request Maint Mode button on the bottom of the page to change the mode. 2. From the Lynx MAT select Update Load Software. See Figure 4-1. Note - Do not remove power to the unit or disconnect the MPC during this procedure. Figure 4-1 Example of Software Loading Page 4-8 Maintenance 0040-170011-01 Revision G
3. Press the Browse button to open a file window and select the composite binary file (i.e. UAT- MSS.bin or similar looking file). The MAT verifies the contents of the file to be loaded. This takes approximately 5 seconds. If the Lynx MAT fails to validate the composite binary file, then the "Status" field will contain the error (highlighted in red). 4. Press the Upload button to begin loading the software. A progress bar is shown for each SW load. 5. An upload completed message is shown when the procedure has finished. See Figure 4-2. After the OK button is pressed, the MPC is disconnected and the screen goes blank. When the procedures are complete cycling power to the NGT-1000/-2000/-2500 system is recommended. A failure message is shown if a problem loading the software is detected. Check that the file being loaded is correct and try the procedure again. If the problem persists cycle power to the unit. Figure 4-2 Upload Complete 6. Perform a functional check (see installation checkout) to verify unit is functioning correctly. Verify the software Load by going to the Select Info Versions page of the MAT, see Figure 4-1. Refer to the Fault Isolation section if errors are detected. 4.4.2 View or Retrieve Data Use the Lynx MAT to view versions and factory information and retrieve fault logs. See Figure 4-3. The versions data and fault log can be saved to a file for later viewing. Figure 4-3 Lynx MAT- Information 0040-170011-01 Maintenance Page 4-9 Revision G
4.4.2.1 Versions Use the version screen to view the current software versions being used by the unit. Buttons on the bottom of the page provide the user the options of Refresh, Save, and Load. Figure 4-4 Lynx MAT- Version 4.4.2.2 Fault Log The Fault Log screen can be used for troubleshooting. Each fault is entered on its own indexed row, with details for date, time, etc. Clicking on a row provides the user with additional information at the top of the page. This information includes a fault description. Buttons on the bottom of the page provide the user the options of Refresh, Clear, Filter, Save, Load, and Export to CSV. The fault data can be cleared at the option of the user. NOTE Typically the fault log should not be cleared unless instructed by L-3 Field Service personnel. A saved fault log can be viewed by the Lynx MAT when the unit is not connected by using the Load function. Page 4-10 Maintenance 0040-170011-01 Revision G
Table 4-2: List of Fault Log Messages BIT DESCRIPTION ACTIONS 0x0001 0x0002 0x0003 0x0004 0x0005 0x0007 0x0009 0x000A 0x000B 0x000C 0x000E 0x000F 0x0010 0x0011 0x0012 0x0014 0x0015 0x0016 0x0017 0x0019 UAT RF PLL Failure GPS RF PLL Failure CDTI Failure(ARINC port of the Appliance) GPS Antenna Open Power Amplifier Failure Software Integrity Failure Control Panel Input Failure(UART) UART for Altitude Failure Temperature Sensor Failure Power Supply Failure UAT Transmit Failure UAT Receive Failure DCM Read Failure Wi-Fi Failure UART or FIS-B Failure Over- temperature Shutdown FPGA Failure GPS Processor Failure UAT Processor Failure UAT Flash Failure Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Check if GPS antenna is properly connected, and is not swapped with the L band antenna. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. If yes, then reload the composite software and again check for the same fault. If the fault persists, send the unit to L-3 Customer support. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L 3 Field Service before removal. Clear fault log then cycle power to the unit and check if the fault persists. If yes, verify DCM wiring. Replacement of the DCM or unit may be required. Contact L-3 Field Service before removal of the DCM or unit. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Log the fault and allow the unit to cool down. If the fault continues to be seen contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. 0040-170011-01 Maintenance Page 4-11 Revision G
Table 4-2: List of Fault Log Messages BIT DESCRIPTION ACTIONS 0x0020 0x0021 0x0022 0x0023 0x0024 0x0025 0x0026 0x0027 0x001A 0x001B ADS-B Message Transmission lesser than lower threshold ADS-B Message Transmission higher than upper threshold Invalid ICAO Address Broadcast schedule violation Mode A Code Mismatch GPS Position Unavailability Air/Ground Discrete Failure Control Panel Failure EEPROM Failure Computed GPS oscillator rate exceeds 6.3 ppm Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Verify the proper DCM setting of the ICAO address. It should be other than 00000 or FFFFFF in hex. See installation checkout for details. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. 1. The code on the CP-2500 control panel and the transponder are different. This code must be the same to remove mismatch error. 2. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. NOTE Occasional mismatch detections may occur due to interference conditions. UAT-Out broadcasting continues with this fault present. Check Table 4-1. Check the Air/Ground Pin wiring and switching operation. This fault is only logged when the unit is in-air. 1. Verify that control panel is ON. 2. If GTX-327/300 is used, verify the RS-232 output is set to REMOTE. 3. Check control panel connections 4. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal of any equipment. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. 0x001D GPS Antenna Short Check Table 4-1. 0x001E Mode A RF Failure Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. 0x001F External RAM Failure Cycle power to the unit and check if the fault persists. Contact L-3 Field Service before removal. Page 4-12 Maintenance 0040-170011-01 Revision G
4.4.3 Configuration Restore NGT-1000/-2000/-2500 This procedure is used to automatically fill in the configuration options from a backup file. Perform the following procedure using a MPC and Lynx MAT. These procedures assume the following: The unit is in Maintenance Mode A DCM is connected (via the mating connector) The MPC is interfaced to the unit via USB. 4.4.3.1 NGT-1000 1. From the Lynx MAT select Setup Configuration Restore. See Figure 4-5. Figure 4-5: Lynx MAT Restore Configuration 2. Click on the Load button to load the configuration into the MAT. 3. After the file is successfully loaded into the Lynx MAT a dialog screen (see below) stating that the loaded data has not yet been applied to the unit. 0040-170011-01 Maintenance Page 4-13 Revision G
4. Click the Yes button to apply the DCM data to the unit. Click the "No" button to review the current configuration page options to make or verify changes. Click the "Apply" button at the bottom of the page to finish the update to the unit. (Note- clicking the apply button on any page saves all the configuration information from all pages.) Details for each option are provided in the Installation Checkout section. 5. Validate the configuration options by comparing the configuration data in the setup pages with the log sheet for configuration and checkout created during initial installation. 4.4.3.2 NGT-2000 1. From the Lynx MAT select Setup Configuration Restore. See Figure 4-6. Figure 4-6: Lynx MAT Restore Configuration 2. Click on the Load button to load the configuration into the MAT. 3. After the file is successfully loaded into the Lynx MAT a dialog screen (see below) stating that the loaded data has not yet been applied to the unit. Page 4-14 Maintenance 0040-170011-01 Revision G
4. Click the Yes button to apply the DCM data to the unit. Click the "No" button to review the current configuration page options to make or verify changes. Click the "Apply" button at the bottom of the page to finish the update to the unit. (Note- clicking the apply button on any page saves all the configuration information from all pages.) Details for each option are provided in the Installation Checkout section. 5. Validate the configuration options by comparing the configuration data in the setup pages with the log sheet for configuration and checkout created during initial installation. 4.4.3.3 NGT-2500 In order to restore DCM data to the NGT-2500 the unit must first be downgraded to a NGT-2000 where the data may be restored, then upgraded again to a NGT-2500. The unlock code for the unit is required for the upgrade portion of this procedure. The unlock code is based on only one ICAO Address This code cannot be re-used with a different ICAO address aircraft. 1. From the Lynx MAT select Setup Configuration Restore. See Figure 4-6 2. Click on the Load button to load the configuration into the MAT. 3. A dialog screen letting the user know that continuing with the restore results in the unit being downgraded to a NGT-2000 is shown. 4. Click on the Yes button to continue. (Click on the No button to abort). Another dialog screen is shown confirming the downgrade of the unit to a NGT-2000. Click Ok 5. Re-connect the Lynx MAT. From the Lynx MAT menu select Connect Appliance USB. 6. From the Lynx MAT select Setup Configuration Restore. 7. After the file is successfully loaded into the Lynx MAT a dialog screen (see below) stating that the loaded data has not yet been applied to the unit. 0040-170011-01 Maintenance Page 4-15 Revision G