GTS 8XX. AML STC Installation Manual. Part 1. Overview and Limitations

GTS 8XX AML STC Installation Manual Part 1 Overview and Limitations 190-00993-00 November 2009 Rev. 2

2009 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin. Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto, provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited. Garmin, GDU 620, and Garmin SVT are trademarks of Garmin Ltd. or its subsidiaries. FliteCharts and SafeTaxi are also registered trademarks of Garmin Ltd. or its subsidiaries. These trademarks may not be used without the express permission of Garmin. NavData is a registered trademark of Jeppesen, Inc.; ChartView is a trademark of Jeppesen, Inc.; SkyWatch is a registered trademark of L-3 Communications; and XM is a registered trademark of XM Satellite Radio, Inc. 1984 2007, MATLAB is a registered trademark of The MathWorks, Inc. At Garmin, we value your opinion. For comments about this guide, please e-mail: Techpubs.Salem@garmin.com. Garmin International, Inc. 1200 E. 151 st Street Olathe, KS 66062 USA Telephone: 913-397-8200 Aviation Dealer Technical Support Line (Toll Free): 888.606.5482 http://www.garmin.com Garmin (Europe) Ltd. Liberty House Bull Copse Road Hounsdown Business Park Southampton, SO40 9RB, UK Telephone: +44 (0) 870 850 1243 Garmin AT, Inc. 2345 Turner Rd., SE Salem, OR 97302 USA Telephone: 503.581.8101 RECORD OF REVISIONS Revision Revision Date Description 1 11/5/09 Initial Release 2 11/30/09 Updated to clarify installation requirements and incorporate feedback from Garmin Engineering. GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page A Rev. 2 190-00993-00

Revision 2 Page Number(s) Section Number Description of Change 1-1 1.2 Added definition of active-low discrete signals. 1-2 1.4 Added STC number. 1-3 1.5 Clarified ADS-B interrogation information. 1-4 1.5.1 Added note that HSDB is not yet implemented. 1-6 1.6.2 Added note to make entry for receive-only equipment in the checkout log. 2-2 2.4.1 Added white and black low profile directional antennas. 2-4 2.5.1 Clarified GTS 800 and GTS 820/850 minimum configurations. 2-6, 2-7 2.5.4 Updated Figure 2-1 and Figure 2-2. 2-8 2.5.4 Clarified Antenna location requirements. 2-11 2.5.7 Added reference to GTS-IM3. 3-1 3.3 Removed Pressure vessel limitations 3-1 3.4 Removed antenna provisions for pressurized aircraft. A-1 A.2 Clarified Lightning Zoning requirements. A-2 A.3 Revised Figure A-4. A-2 A.3 Added Figure A-5. DOCUMENT PAGINATION Section Pagination Table of Contents i through ii Section 1 1-1 through 1-2 Section 2 2-1 through 2-10 Section 3 3-1 through 3-2 Appendix A A-1 through A-2 Page B GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

TABLE OF CONTENTS SECTION PAGE 1 GENERAL DESCRIPTION...1-1 1.1 Introduction...1-1 1.2 Terminology...1-1 1.3 Installation Manual Format...1-1 1.4 Scope...1-2 1.4.1 Approved Aircraft with Systems not Covered by the STC...1-2 1.4.2 Part 23 Aircraft Not Identified on AML...1-2 1.4.3 Other Aircraft Not Covered by AML...1-2 1.4.4 Required Documentation for All Installations...1-2 1.5 System Overview...1-3 1.5.1 Equipment Descriptions...1-4 1.5.2 Interface Summary...1-5 1.6 GTS 8XX Installation...1-6 1.6.1 Installation Overview...1-6 1.6.2 Antenna Installation Configurations...1-6 1.6.3 Sensitivity Level...1-7 1.6.4 Air/Ground Determination...1-7 1.6.5 Audio Suppression...1-7 1.7 Technical Specifications...1-9 1.7.1 Environmental Qualification Forms...1-9 1.7.2 Physical Characteristics...1-9 1.7.3 Power Requirements...1-9 1.8 Equipment Approvals...1-10 1.9 System Documentation...1-10 1.10 STC Permission...1-10 2 INSTALLATION OVERVIEW...2-1 2.1 Introduction...2-1 2.2 Pre-Installation Information...2-1 2.3 Available Equipment...2-1 2.4 Installation Materials...2-2 2.4.1 Accessories Available from Garmin...2-2 2.4.2 Materials Required but Not Supplied...2-3 2.4.3 Special Tools Required...2-3 2.5 Installation Considerations...2-4 2.5.1 Minimum System Configuration...2-4 2.5.1.1 GTS 800 Installations...2-4 2.5.1.2 GTS 820/850 Installations...2-4 2.5.2 Placards and Labels...2-4 2.5.3 Considerations on Pressurized Aircraft...2-4 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page i Rev. 2 190-00993-00

2.5.4 TAS/TCAS Antenna Location...2-5 2.5.5 GTS 8XX Location Considerations...2-9 2.5.6 GPA 65 Location Considerations...2-11 2.5.7 Cable and Wiring Considerations...2-11 2.5.8 Cooling Requirements...2-11 3 LIMITATIONS...3-1 3.1 Operation...3-1 3.2 STC Installations...3-1 3.3 Equipment Interfaced to the GTS 8XX...3-1 3.4 Major Alterations...3-1 3.5 Instructions for Continued Airworthiness...3-1 3.6 Rotorcraft Installation...3-1 APPENDIX A LIGHTNING ZONING...A-1 A.1 Purpose...A-1 A.2 Summary...A-1 A.3 Lightning Zoning Diagrams...A-1 Figure 1-1. Installation Manual Documentation Format...1-1 Figure 1-2. System Overview...1-3 Figure 1-3. GTS 8XX Antenna Installation Configurations...1-6 Figure 2-1. Antenna Acceptable Mounting Location High Wing Aircraft...2-6 Figure 2-2. Antenna Acceptable Mounting Location Low Wing Aircraft...2-7 Figure 2-3. GTS 8XX Vertical Installation Rack (Garmin P/N 115-00781-00)...2-9 Figure 2-4. GTS 8XX Horizontal Installation Rack (Garmin P/N 115-00784-00)...2-10 Figure 2-5. Suggested Mounting Locations for the GTS 8XX Remote Rack...2-10 Figure A-1. Zoning Legend...A-1 Figure A-2. Zoning for a Nose Mounted Prop...A-1 Figure A-3. Zoning for a Twin Prop or Twin Jet Engine...A-1 Figure A-4 : Zoning for a Forward-Mounted and a Reverse-Mounted Prop...A-2 Figure A-5: Zoning for a Top-Mounted Reverse Prop...A-2 Table 1-1. Equipment Summary...1-4 Table 1-2. GTS 8XX Equipment Environmental Qualification Forms...1-9 Table 1-3. GTS 8XX LRU Physical Specifications...1-9 Table 1-4. Garmin GTS 8XX Reference Documentation...1-10 Table 1-5. Other Reference Documentation...1-10 Table 1-6. Garmin Product Reference Documentation...1-10 Table 2-1. GTS 8XX System Equipment Part Numbers...2-1 Table 2-2. GTS 8XX Installation Rack Part Numbers...2-2 Table 2-3. GTS 8XX Connector Kit Part Numbers...2-2 Table 2-4. GTS 8XX Antenna Part Numbers...2-2 Table 2-5. GTS 8XX Configuration Module Part Numbers...2-3 Page ii GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

1 General Description 1.1 Introduction This manual provides an overview of the installation of the GTS 8XX/GPA 65 Traffic Advisory System (TAS) and Traffic Collision Avoidance System (TCAS I). This manual describes the physical, mechanical and electrical characteristics, as well as instructions and other conditions and limitations for installation and approval for all components of the GTS 8XX system. It is intended for use by persons certified by the Federal Aviation Administration (FAA) to install avionics. 1.2 Terminology Except where specifically noted, references made to the GTS 8XX applies equally to the GTS 800, GTS 820, and GTS 850. Except where specifically noted, references made to the 400/500 series applies equally to the GNS 430/530/430W/530W, GPS 400/500/400W/500W, and GNC 420/420W. An asterisk (*) following a signal name denotes that the signal is an Active-Low, requiring a ground to activate. If there is no asterisk, the signal is an Active-High. 1.3 Installation Manual Format This installation manual is only a part of the full documentation required for installation of the GTS 8XX. The installation is broken into 4 separate sections with a separate manual for each part of the installation. This manual provides an overview of the installation and limitations. For other aspects of the installation, see the pertinent installation manual. Be sure to read each of the separate manuals before beginning the installation. See Table 1-4 for a list of each manual and the part numbers associated with it. Part numbers are also contained in Figure 1-1. Figure 1-1. Installation Manual Documentation Format Part 1: Overview and Limitations describes the pre-installation information necessary to plan for installing the GTS 8XX system into an aircraft. For brevity, will be referred to as GTS-IM1. Part 2: Mechanical Installation describes location considerations and instructions pertaining to the mechanical installation of the GTS 8XX and related hardware. Referred to as GTS-IM2. Part 3: Electrical Installation describes cabling and wiring requirements, electrical harness build-up and installation, as well as electrical interconnect information. Referred to as GTS-IM3. GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 1-1 Rev. 2 190-00993-00

Part 4: Configuration and Checkout describes software loading and configuration and system checks required prior to operation of the GTS 8XX. Referred to as GTS-IM4. 1.4 Scope This installation manual applies to the modification of an aircraft to support the installation of the GTS 8XX system. Interfacing to additional equipment is also covered by this manual; however, the installation of such peripheral equipment (GPS, MFD, etc.) is not covered. Those systems require other installation data and approval. The data contained within this manual is FAA approved under the GTS 8XX AML STC SA02016SE-D, which is applicable for implementation within airplanes that are type certificated under the Civil Air Regulation 3 and 4a (CAR 3, CAR 4a) or Title 14 Code of Federal Regulations (CFR) Part 23 or other regulations as defined on the Approved Model List (AML). The STC data was developed to support installation in Part 23 aircraft, but only those identified on the STC AML are approved under this STC. 1.4.1 Approved Aircraft with Systems not Covered by the STC Aircraft identified on the Approved Model List have been determined to meet a minimum required configuration for applicability of the STC. However, since some of these aircraft may have been modified over the years or may have been manufactured with systems which are not identified or approved in this manual for integration with the GTS 8XX, it may be difficult to use the data herein to completely substantiate the installation in compliance with the STC. It is the installer s responsibility to make the final determination of applicability for each aircraft. Use this manual to assess each installation prior to modifying any Type Certificated aircraft to ensure the applicability of the GTS 8XX AML STC. It is possible/permissible for installers and other appropriately certificated persons to seek approval for installation and operational use of the GTS 8XX with systems not identified in this manual. It is the responsibility of such persons to validate any compatibility and document any limitations of such interfaces and to provide that data to the FAA for approval by means of a TC, STC, or Field Approval prior to returning the aircraft to service. 1.4.2 Part 23 Aircraft Not Identified on AML Part 23 aircraft which are not identified on the GTS 8XX AML STC may be valid candidates for the GTS 8XX AML STC. Installers should contact Garmin Tech Support with detailed drawings of the aircraft s proposed installation. Engineering analysis may allow for the inclusion of these aircraft in a future revision of the FAA Approved Model List. 1.4.3 Other Aircraft Not Covered by AML Transport Category Aircraft (Part 25), and Rotorcraft (Part 27/29) are not part of the GTS 8XX AML STC. These aircraft may be valid candidates for installation of this system. Installers may contact Garmin for possible additional information that may support an installation of this type. Data provided in this manual may be used in support of an alteration and obtaining other FAA approval. 1.4.4 Required Documentation for All Installations Regardless of applicability of the AML STC or alternative field approval application for installation and operational approval, prior to completing the installation and before returning the aircraft to service, the installer or other appropriately certificated person is required to complete and submit an FAA Form 337; Major Repair and Alteration Airframe, Powerplant, Propeller, or Appliance to the appropriate FAA Flight Standards District Office describing the work accomplished. The FAA Form 337 must detail the equipment and systems to which the respective GTS 8XX system is interfaced and reflect appropriately approved or acceptable data for which any follow-on FAA Field Approval is being sought. See AC 43.9-1E for instructions for completing the FAA Form 337. In addition, the GTS 8XX Configuration and Checkout Log must be completed and attached with the Instructions for Continued Airworthiness such that any aircraft with the modifications detailed in this manual may be properly maintained. Page 1-2 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

1.5 System Overview The GTS 8XX system is designed to use active interrogations (active interrogations applicable to GTS 820 and GTS 850 only) of Mode S and Mode C transponders to provide Traffic Advisories (TA) to the pilot. Passive surveillance is available only when installed with a 1090 MHz ADS-B transmit class of equipment, or other complementary ADS-B link transmit class of equipment (such as UAT). Traffic is displayed on an external MFD via ARINC 429 and/or Ethernet High Speed Data Bus (HSDB not yet implemented). An overview of the GTS 8XX system is shown in Figure 1-2. Further detail on each of the system components is provided in the following sections. 1030 MHz RX 1090 MHz TX Mode A/C Interrogations Mode S Interrogations Broadcast Messages Optional Top Antenna Mode A/C/S Replies Mode S Squitter 1090 MHz TX Bottom Antenna 1030 MHz RX 1030 MHz TX Mode C Interrogations Broadcast Messages (GTS 820 / GTS 850) Mode S Interrogations (GTS 820 / GTS 850) Mode C Replies Mode S Replies Mode S Squitters Top Directional Antenna 1090 MHz RX GPA 65 PA/LNA (GTS 820 / GTS 850) Suppression Bus 1090 MHz RX 1030 MHz TX Optional Bottom Antenna 1030 MHz RX 1090 MHz TX Mode A/C Interrogations Mode S Interrogations Broadcast Messages Optional Top Antenna Mode A/C/S Replies Mode S Squitter 1090 MHz TX 1030 MHz RX Bottom Antenna Mode S Transponder Mode S Transponder (second transponder optional) Baro Altitude (required) Transponder Serializer OR GPS PPS Airborne Status Magnetic Heading (optional for active surveillance) AHRS Analog GPS PVT (required for ADS-B surveillance) GPS/UAT Audio Alerts Unswitched Audio OR OR Audio Output GTS 8XX TAS / TCAS I Gear Status Audio Inhibit Aural Traffic Alert Visual Traffic Alert System Status OR Radio Altitude (optional for active surveillance) ARINC Analog LRU Data Operate/ Standby Self Test ABV/BLW/ NRM Display #1 Status OR Display #2 Status Data Source Options ARINC 429 Generic Control/ Display Unit Optional Second Display Unit Discrete I/O Suppression RS-232 Color Display Knobs/Buttons Color Display RS-422 Analog I/O w/ discrete flag Figure 1-2. System Overview GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 1-3 Rev. 2 190-00993-00

1.5.1 Equipment Descriptions The GTS 8XX is a microprocessor-based Line Replaceable Unit (LRU) that uses active interrogations of Mode S (GTS 820 and GTS 850 only) and Mode C transponders to provide Traffic Advisories to the pilot. The GTS 820 and GTS 850 include a GPA 65 power amplifier/low-noise amplifier (PA/LNA) module, which allows for up to 40 nm of active surveillance range as well as Mode S interrogation capability. When installed with a 1090 MHz ADS-B transmit class of equipment (e.g. GTX 330 ES with Extended Squitter, GDL 90, etc.) the GTS 8XX will utilize passive surveillance. Traffic is displayed on an external MFD via ARINC 429 and/or Ethernet HSDB High Speed Data Bus (HSDB traffic display not yet implemented). An aural alert is also provided to inform the crew of a traffic advisory (TA). A topmounted directional antenna is used to derive bearing of the intruder aircraft, which is displayed with relative altitude to own aircraft. Top antenna transmitted interrogations are directional, reducing the number of transponders that receive the interrogation thus reducing potential garble on the 1090 MHz band. Optional bottom antenna transmitted interrogations are omni-directional, using a monopole antenna (recommended for fixed gear installations) or a directional antenna (recommended for retractable gear installations). A bottom directional antenna installation gives the benefit of intruder bearing visibility for targets that are shaded from the top directional antenna. Traffic Advisory System (TAS) Traffic Collision Avoidance System (TCAS I) 1090 ES ADS-B Receiver GPA 65 PA/LNA Transmit Power (Watts) GTS 800 011-01356-00 X X 40 GTS 820 011-01446-00 X X X 250 GTS 850 011-01553-00 X X X 250 Table 1-1. Equipment Summary Page 1-4 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

1.5.2 Interface Summary The GTS 8XX is designed as an open architecture system that uses typical ARINC 429, RS-232, and Ethernet communications interfaces. See Figure 1-2 for more information. The following list is a summary of the interfaces provided for the GTS 8XX units. 4 RS-232 Inputs/Outputs 1 RS-422 Input/Output 2 PA/LNA RS-422 Data Inputs/Outputs 6 ARINC 429 Inputs/Outputs Configuration Module (for storing aircraft configuration data) Aircraft Power Input 1 Analog Radar Altimeter Input 26 VAC Heading Reference Input Synchro Magnetic Heading Input 1 Alert Audio Output 16 Active Low Discrete Inputs 2 Active High Discrete Inputs 4 Annunciator Outputs 1 External Suppression Input/Output GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 1-5 Rev. 2 190-00993-00

1.6 GTS 8XX Installation 1.6.1 Installation Overview This section provides hardware equipment information for installing the GTS 8XX system, cabling for the antenna, and related hardware. Installation of the GTS 8XX should follow the aircraft TC or STC requirements. For interconnects with the GDU 620, MX20 MFD, GMX 200 MFD, 400W/500W series or the 400/500 series refer to GTS-IM3, Garmin Document # 190-00993-05. For installation information on the GDU 620 Display Systems, MX20 MFD, GMX 200 MFD, 400W/500W series or 400/500 series, refer to their product installation manuals. 1.6.2 Antenna Installation Configurations The GTS 8XX system can be installed with a top only or a top and bottom antenna. The bottom antenna can either be a monopole or directional antenna. A bottom directional antenna is recommended for retractable gear aircraft while a monopole antenna is recommended for fixed-gear aircraft. NOTE The GTS 8XX is a receive-only class of equipment. A statement must be included in the Configuration and Checkout Log stating the following: This installation is TSO-C166a Class A0/Type 1 Receiving Only. The Configuration and Checkout Log is contained in GTS-IM4 section 3. NOTE Termination resistors need to be connected to the bottom antenna ports in top-only antenna installations. The GPA 65 is only installed in conjunction with the GTS 820 or GTS 850 top antenna and is not used with a GTS 800 installation. Directional GTS 800 OR *All unused antenna ports need to be terminated with a resistive load Directional (Optional)* Monopole (Optional)* Directional GPA 65 GTS 820/850 OR *All unused antenna ports need to be terminated with a resistive load Directional (Optional)* Monopole (Optional)* Figure 1-3. GTS 8XX Antenna Installation Configurations Page 1-6 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

Note that if only the top antenna is installed, the GTS 8XX may experience antenna shading in certain flight attitudes. Antenna shading occurs when the aircraft structure is blocking the reply from an intruder aircraft. For maximum intruder aircraft detection and visibility, it is recommended that the GTS 8XX be installed with both a top and bottom antenna. The best system performance is typically achieved by installing directional antennas on the top and bottom of the aircraft fuselage in areas with the fewest obstructions. 1.6.3 Sensitivity Level The GTS 8XX issues Traffic Advisories according to the current sensitivity level (SL). The GTS 8XX has two sensitivity levels available, either sensitivity level A (SLA) or sensitivity level B (SLB). The logic for choosing the sensitivity level is based upon aircraft configuration. SLA is determined according to the following order: 1. Ownship is below 2000 ft AGL (if equipped with a radio altimeter) 2. Landing gear is extended (on retractable gear aircraft) 3. Groundspeed is below 120 kts (no radio altimeter installed in a fixed-gear aircraft) The GTS 8XX will remain in SLB at all other times. In the event a fixed-gear aircraft is not equipped with a radio altimeter and groundspeed (from GPS over ARINC 429) is not available, the GTS 8XX will remain in SLB at all times. NOTE If the GTS 8XX is interfaced to a radio altimeter or if the gear/wheel is configured as fixed, the system will ignore the GEAR DOWN AND LOCKED* (* indicates active low) discrete input. Refer to the wiring diagrams in GTS-IM3 (190-00993-05) for additional wiring considerations. 1.6.4 Air/Ground Determination The GTS will transition automatically from standby mode into operate mode if it senses that the aircraft has become airborne. There are multiple sources that the GTS 8XX can use for the air/ground determination: Fixed Gear Aircraft (no squat switch) with GPS Source If the GTS is receiving valid ARINC 429 position/velocity/time from a GPS source, then the valid ownship GPS ground speed transitions according to the following parameters: a) Airborne: transition from GPS ground speed less than 35 knots to 35 knots or greater b) On Ground: transition from GPS ground speed greater than 30 knots to 30 knots or less Retractable Gear Aircraft (squat switch installed) with GPS Source If a state transition (ground/open) has been detected on the AIR/GROUND* input, the GTS 8XX will convert the status to On Ground or Airborne according to the configured sense of the AIR/GROUND* input. See GTS-IM4 for configuration information. For wiring information, refer to GTS-IM3. If a state transition has not occurred on the AIR/GROUND* input, the GTS 8XX will convert GPS ground speed transitions according to the following parameters: a) Airborne: transition from GPS ground speed less than 35 knots to 35 knots or greater b) On Ground: transition from GPS ground speed greater than 30 knots to 30 knots or less 1.6.5 Audio Suppression To preclude nuisance audio alerts during landing, audio alerts are suppressed according to the following conditions: GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 1-7 Rev. 2 190-00993-00

1. A radio altimeter is installed and valid and is reading less than or equal to 400 ft altitude with 50 ft hysteresis. 2. The landing gear is extended and no radio altimeter is installed. Aural traffic alerts are not inhibited when the GTS 8XX is configured for fixed-gear aircraft and when no radio altimeter is installed. Page 1-8 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

1.7 Technical Specifications 1.7.1 Environmental Qualification Forms The latest revision of the Environmental Qualification Forms for each GTS 8XX LRU is available directly from Garmin under the part numbers listed in Table 1-2. Table 1-2. GTS 8XX Equipment Environmental Qualification Forms Document Garmin Part Number GTS 8XX Environmental Qualification Form 005-00323-02 GPA 65 PA/LNA Environmental Qualification Form 005-00323-22 GA 58 Environmental Qualification Form 005-00323-23 To obtain a copy of these forms, see the Dealer/OEM portion of the Garmin web site (www.garmin.com). 1.7.2 Physical Characteristics All width, height, and depth measurements are taken with unit rack (if applicable) and connectors. Table 1-3. GTS 8XX LRU Physical Specifications Characteristics GTS 8XX Width w/out rack GTS 8XX Height w/out rack GTS 8XX Depth w/connector Kit GPA 65 Width GPA 65 Height GPA 65 Depth Not Including Connector and Cable GPA 65 Depth w/connector and Cable Fully Extended GA 58 Width GA 58 Height GA 58 Depth GTS 8XX Unit Weight w/out Connector Kit GTS 8XX Unit Weight with Connector Kit and Vertical Rack GTS 8XX Unit Weight with Connector Kit and Horizontal Rack GPA 65 PA/LNA Unit Weight with Pigtail Connector Kit* GA 58 Antenna Unit Weight w/screws and O-ring *Used with the GTS 820 and 850. 1.7.3 Power Requirements Specifications 2.66 inches (6.74cm) 6.25 inches (15.88 cm) 14.78 inches (37.54 cm) 4.25 inches (10.80 cm) 1.00 inches (2.54 cm) 7.96 inches (20.22 cm) 16.83 inches (42.75 cm) 5.63inches (14.30 cm) 2.97 inches (7.54 cm) 4.03 inches (10.23 cm) 8.9 lbs (4.03 kg) 10.5 lbs (4.76 kg) 11.3 lbs (5.12 kg) 1.9 lbs (0.86 kg) 0.82 lbs (0.37 kg) Characteristics GTS 8XX Power Requirements GTS 800 Power Consumption GTS 820/850 Power Consumption GTS 8XX Boot-up Current Draw Specifications 14/28 Vdc. See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages. 1.1 +/- 0.2 A typical 1.5 A max operating @ 28 VDC 2.2 +/- 0.2 A typical 2.6 A max operating @ 14 VDC 1.3 +/- 0.2 A typical 1.6 A max operating @ 28 VDC 2.7 +/- 0.3 A typical 3.2 A max operating @ 14 VDC 4.0 A @ 28 VDC for 70 ms 5.6 A @ 14 VDC for 100 ms GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 1-9 Rev. 2 190-00993-00

1.8 Equipment Approvals Refer to GTS 8XX/GPA 65 Installation manual (190-00587-00) Section 1.5 for TSO/ETSO compliance information. 1.9 System Documentation Table 1-4. Garmin GTS 8XX Reference Documentation Document Reference Garmin P/N GTS 8XX AML STC Installation Manual Part 1 Overview and Limitations GTS-IM1 190-00993-00 GTS 8XX AML STC Installation Manual Part 2 Mechanical Installation GTS-IM2 190-00993-04 GTS 8XX AML STC Installation Manual Part 3 Electrical Installation GTS-IM3 190-00993-05 GTS 8XX AML STC Installation Manual Part 4 Checkout and Maintenance GTS-IM4 190-00993-03 GTS 8XX/GPA 65 Installation Manual -- 190-00587-00 Table 1-5. Other Reference Documentation Document Part Number Jackscrew Backshell Installation Instructions 190-00313-11 FAA Advisory Circular, Acceptable Methods, Techniques, and Practices Aircraft Inspection and Repair FAA Advisory Circular, Acceptable Methods, Techniques, and Practices Aircraft Alterations Aerospace Systems Electrical Bonding and Grounding for Electromagnetic Compatibility and Safety Table 1-6. Garmin Product Reference Documentation FAA AC 43.13-1B FAA AC 43.13-2B SAE ARP1870 Document Garmin Part Number GDU 620 Installation Manual 190-00601-04 400W Series Installation Manual 190-00356-02 500W Series Installation Manual 190-00357-02 GNS 480 (CNX80) Color GPS/NAV/COM Installation Manual 560-0982-01 GMA 1347 Installation Manual 190-00303-20 GMX 200 Installation Manual 190-00607-04 GTX 330 Installation Manual 190-00207-02 1.10 STC Permission Consistent with Order 8110.4C and AC 21-40, a permission letter to use this STC data is available for download on the Dealers Only portion of the Garmin website at www.garmin.com. Page 1-10 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

This page intentionally left blank GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 1-11 Rev. 2 190-00993-00

2 INSTALLATION OVERVIEW 2.1 Introduction The following section contains an overview of the steps required for the installation of the GTS 8XX/GPA 65 and related hardware. This section includes requirements for selection of proper locations in the aircraft, as well as requirements for supporting structure, mechanical alignment and electrical wiring. Any restrictions on nearby equipment and requirements are also specified herein. 2.2 Pre-Installation Information Always follow acceptable avionics installation practices in FAA Advisory Circulars (AC) 43.13-1B, 43.13-2B, or later FAA approved revisions of these documents. A successful installation should start with careful planning, including determination of mounting location for the GTS 8XX, cable routing, and other required modifications. Once the mounting location has been determined, prepare the mounting tray for installation. It may be easier to complete the wiring harness and attach the connectors to the tray upon installation. NOTE After choosing a mounting location, complete a Weight and Balance computation as described in GTS-IM2 Section 2 before beginning the installation. The GTS 8XX can have a significant affect on the weight and balance of small aircraft if an aft location is chosen. Evaluate the affects of the chosen location to determine whether it is within acceptable limits. Follow the installation procedures in each of the GTS 8XX installation manuals as it is presented for a successful installation. Read each manual before beginning the procedure. Prior to installation, consider the structural integrity of the GTS 8XX system installation as defined in AC 43.13-2B, Chapter 1. Perform the post installation checkout as described in GTS-IM4 before closing the work area in case problems occur. Refer to GTS-IM2 for additional mounting details. Complete an electrical load analysis as described in GTS-IM3 Section 2 on the aircraft prior to starting modification to ensure the aircraft has the ability to carry the additional load of the GTS 8XX equipment. 2.3 Available Equipment The GTS 8XX and GPA 65 are available under the following part numbers: Table 2-1. GTS 8XX System Equipment Part Numbers Model Unit P/N Garmin P/N Voltage (VDC) GTS 800 011-01356-00 010-00519-00 14/28 GTS 820 011-01446-00 010-00562-00 14/28 GTS 850 011-01553-00 010-00563-00 14/28 GPA 65 011-01347-00 010-10721-00 -- GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 2-1 Rev. 2 190-00993-00

2.4 Installation Materials 2.4.1 Accessories Available from Garmin Table 2-2. GTS 8XX Installation Rack Part Numbers Installation Racks* Garmin P/N GTS 8XX Vertical Installation Rack 115-00781-00 GTS 8XX Horizontal Installation Rack 115-00784-00 * Either the vertical or horizontal rack is required, but not both. For a GTS 800 installation with a single GA 58 directional antenna, two QMA Connector Kits (4 pieces, either straight or right angle) are required. For a GTS 800 installation with dual GA 58 directional antennas, four QMA Connector Kits (4 pieces, either straight or right angle) kits are required. For a GTS 800 installation with a single GA 58 directional antenna and a monopole antenna, two QMA Connector Kits (4 pieces, either straight or right angle) and one QMA Connector Kit (1 piece, either straight or right angle) are required. The monopole antenna will require one BNC connector (either straight or right angle). For GTS 820 and 850 installations, add two QMA Connector Kits (4 pieces, either straight or right angle) for the GPA 65 connections. One QMA Termination Connector Kit (4 pieces) is required for single antenna installations. One QMA Termination Kit (3 pieces) is required for bottom monopole antenna installations. Table 2-3. GTS 8XX Connector Kit Part Numbers Connector Kits Garmin P/N QMA Right Angle Connector Kit (4 pieces) 011-01364-00 QMA Straight Connector Kit (4 pieces) 011-01364-01 QMA Right Angle Connector Kit (1 piece) 011-01364-02 QMA Straight Connector Kit (1 piece) 011-01364-03 QMA Termination Connector Kit (4 pieces) 011-01364-04 QMA Termination Connector Kit (3 pieces) 011-01364-05 GTS 8XX Connector Kit 011-01360-00 GPA 65 Circular Connector Kit 011-01365-00 USB-B Pigtail (non-g1000 installations only) 011-01782-00 Table 2-4. GTS 8XX Antenna Part Numbers Antennas Garmin P/N GA 58 Directional Antenna 010-10720-00* Garmin Monopole Antenna 010-10160-00 L-Band Monopole Antenna that meets TSO-C74c or TSO-C66b or later Sensor Systems low profile antenna (white) 013-00276-00** Sensor Systems low profile antenna (black) 013-00276-01** *010-10720-00 includes mounting screws and o-ring, unless specifically requested to exclude. **Or Sensor Systems Incorporated P/N S72-1735-24 that meets the requirements of Garmin P/N 013-00276-XX. NOTE The GA 58 is the only antenna covered under the GTS AML STC. Although the GTS AML STC does not include the Sensor Systems low profile antenna or any monopole antenna installations, this does not preclude the installer from obtaining other FAA installation approval e.g. STC, field approval, etc. Page 2-2 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

Table 2-5. GTS 8XX Configuration Module Part Numbers Configuration Module Garmin P/N Configuration Module (Non-G1000 installations only) 011-00979-20 2.4.2 Materials Required but Not Supplied The GTS 8XX equipment is intended for use with standard aviation accessories. The following items are required for each installation: Wire (MIL-W-22759/16 or equivalent) Shielded Wire (MIL-C-27500 or equivalent) Aircraft Grade Category 5 Ethernet Cable for HSDB installations (refer to the interconnect drawings in GTS-IM3 for applicable part numbers) Circuit Breakers Switches (dependent upon chosen installation, refer to GTS-IM3 Appendix C for part numbers) Miscellaneous Nuts, screws, washers, rivets (Standard installation hardware, including AN525-1032R8 screws, MS20426AD4-6 rivets, MS21059L3 rivet nut plates, MS21071-06 reduced rivet spacing nut plates) Tie wraps or lacing cord Ring Terminals (for grounding) Shield Terminators Silicon Fusion Tape USB-A to USB-B cable (for interface between the computer USB-A receptacle and the GTS 8XX USB-B receptacle) 2.4.3 Special Tools Required Refer to GTS-IM3 for a list of electrical installation tools required. A ramp tester, such as a TIC TR220 test set or equivalent is required for system performance and checkout. If a test set is unavailable a flight check may be performed. Refer to GTS-IM4 section 3 for more information. GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 2-3 Rev. 2 190-00993-00

2.5 Installation Considerations Fabrication of a wiring harness is required. Sound mechanical and electrical methods and practices are required for installation of the GTS 8XX/GPA 65. 2.5.1 Minimum System Configuration 2.5.1.1 GTS 800 Installations The minimum GTS 800 installation requires the following items: GTS 800 unit GA 58 Antenna Approved GPS source (refer to GTS-IM3 for approved sources) Approved Display (refer to GTS-IM3 for approved sources) Approved Altitude source (transponder, serial altitude encoder, etc. Refer to GTS-IM3 for approved sources) 2.5.1.2 GTS 820/850 Installations The minimum GTS 820/850 installation requires the following items: GTS 820/850 unit GA 58 Antenna GPA 65 PA/LNA Approved GPS source (refer to GTS-IM3 for approved sources) Approved Display (refer to GTS-IM3 for approved sources) Approved Altitude source (transponder, serial altitude encoder, etc. Refer to GTS-IM3 for approved sources) Approved Transponder (Optional for ADS-B operation. Refer to GTS-IM3 for approved sources) 2.5.2 Placards and Labels All placards and labels should be readable in all cockpit lighting conditions. Ambient flood lighting is acceptable. 2.5.3 Considerations on Pressurized Aircraft GTS 8XX system installation in pressurized aircraft is beyond the scope of the GTS 8XX STC. However, the data provided by this STC may be used to assist the installer in obtaining other approval options. Installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such installations incorporate alteration (penetration) of the cabin pressure vessel by connector holes and/or mounting arrangements. Use of existing bulkhead connectors previously approved by other means is permissible. For needed engineering support pertaining to the design and approval for pressurized aircraft installations, it is recommended that the installer proceed according to any of the following listed options: 1. Obtain an FAA field approval. 2. Obtain approved installation design data from the aircraft manufacturer. 3. Obtain an FAA approved Supplemental Type Certificate (STC) pertaining to and valid for the subject installation. Page 2-4 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

4. Contact the FAA Aircraft Certification Office in the appropriate Region and request identification of FAA Designated Engineering Representatives (DERs) who are authorized to prepare and approve the required installation engineering data. 5. Obtain FAA Advisory Circular AC-183C and select (and contact) a DER from the roster of individuals identified. 2.5.4 TAS/TCAS Antenna Location To achieve proper interrogation and surveillance volumes the following GTS 8XX antenna installation guidelines should be followed. See GTS-IM2 for additional mounting details. Acceptable mounting locations for high wing aircraft is shown in Figure 2-1. For low wing aircraft, see Figure 2-2. NOTE For bottom antenna installations, a monopole antenna is recommended for fixed-gear aircraft, while retractable gear aircraft may use either a monopole or directional antenna. The target bearing accuracy may be degraded for bottom directional antenna installations on aircraft with fixed gear. GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 2-5 Rev. 2 190-00993-00

Acceptable Installation Area 18" 102.4" 102.4" Optimum Location Max aft location determined When top of antenna is level With crown of aircraft 8' Max Bottom Antenna Figure 2-1. Top Antenna Acceptable Mounting Location High Wing Aircraft Page 2-6 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

Acceptable Installation Area 18" 102.4" 102.4" Optimum Location Max aft location determined When top of antenna is level With crown of aircraft 8' Max Bottom Antenna Figure 2-2. Top Antenna Acceptable Mounting Location Low Wing Aircraft GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 2-7 Rev. 2 190-00993-00

The GTS 8XX requires a top-mounted directional antenna. An optional bottom mounted directional or L-band monopole antenna can be installed in conjunction with the top-mounted directional antenna. Antenna locations are critical to maintain the surveillance coverage across all azimuth and elevation angles. Locations must be chosen so the top mounted and bottom mounted antenna will represent same range and bearing to an intruder. The mounting location, geometry, and surroundings of the antenna can affect the system performance. The following guidance provides information to aid the installer in ensuring that the most optimum location is selected for the installation of the antenna. Because meeting all of these installations guidelines may not be possible on all aircraft, these guidelines are listed in order of importance to achieve optimum performance. The installer must use best judgment to balance the installation guidelines. Installations must be thoroughly tested as described in GTS-IM4 to verify that performance degradation as a result of antenna placement is not an issue for the TAS/TCAS system as well as other systems. Refer to GTS-IM3 for additional requirements concerning the maximum coaxial line loss allowed between the GTS 8XX, the GPA 65, and the antenna. 1. Antenna must be installed in a lightning-safe area on the metal skin of the fuselage. See Appendix A for examples of areas where the antenna may be installed. 2. The antenna cannot be mounted in any wet or dry fuel bays. The fasteners that attach the antenna or its doubler must not penetrate the fuel bay for protection of fuel systems from lightning attachment to the antenna. 3. Top antenna must be mounted as far forward on the fuselage as possible, while still maintaining the lightning zone limitations. The antenna should be mounted at the uppermost point on the crown of the fuselage to prevent antenna shading. 4. The TAS/TCAS antenna(s) should be mounted on the aircraft skin so that the horizontal base is horizontal to within +/-5 in longitudinal and lateral axes when the aircraft is in level flight. 5. The TAS/TCAS antenna(s) should be mounted on a flat section of the fuselage to reduce the gap formed between the base plate and the fuselage when normal mounting torque is applied. 6. All antennas should be mounted at least 20 inches away (measured from center to center) from the TAS/TCAS antenna(s). 7. Top and bottom antennas must be electrically grounded to the aircraft ground plane. 8. Ground plane considerations should include minimization of any discontinuities such as overlapped un-riveted airframe skins, cowlings, or hatches. All such discontinuities should be at least 18 inches from the nearest edge of the TAS/TCAS antenna. 9. For installations using a bottom mounted antenna, the top and bottom antennas should be located near the same vertical line through the aircraft such that they represent the same range and bearing to an intruder. The top and bottom antenna should not be separated horizontally by more than 8 ft. Refer to Figure 2-1 and Figure 2-2 for more information. 10. The top and bottom mounted TAS/TCAS Antenna should be as close as possible to the aircraft centerline. 11. If possible, no antenna should be mounted in front of the top or bottom TAS/TCAS antenna(s). Page 2-8 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

CAUTION Ensure that TCAS antenna placement will not cause an ingestion hazard to propellers, engine intakes, etc. located downstream of the antenna and that ice particles can not accumulate and break off into the engine intake or propeller. Locations upstream of the engine intake/propeller may not be used unless the aircraft manufacturer has approved these locations for antenna placement. CAUTION Ensure that the bottom TCAS antenna placement will not interfere with moisture drainage holes on the bottom of the aircraft. 2.5.5 GTS 8XX Location Considerations Determine a suitable location for the GTS 8XX unit. The unit can either be mounted vertically or horizontally using the racks shown in Figure 2-3 and Figure 2-4. Refer to GTS-IM2 Section 2 for additional mounting detail and outline and installation drawings. The GTS 8XX can be installed in any section of the aircraft s fuselage or the forward equipment bay for multi-engine aircraft. However it cannot be mounted in an area enclosed by a fiberglass radome or on any composite structure that forms part of the exterior of the aircraft. The tray can be installed in a variety of locations, such as the electronics bay or behind the rear baggage area. Refer to Figure 2-5. Be sure to evaluate the location chosen carefully before beginning the modification. Perform a Weight and Balance computation as described in GTS-IM3 Section 2 before beginning the installation. The GTS 8XX can have a significant affect on the weight and balance of small aircraft if an aft location is chosen. Evaluate the affects of the chosen location to determine whether it is within acceptable limits. The GTS 8XX must be mounted in a serviceable location in the aircraft (e.g. accessible through an access panel). Installation in an unpressurized area of a pressurized aircraft is acceptable. Avoid locating the GTS 8XX near high sources of heat. Figure 2-3. GTS 8XX Vertical Installation Rack (Garmin P/N 115-00781-00) GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 2-9 Rev. 2 190-00993-00

Figure 2-4. GTS 8XX Horizontal Installation Rack (Garmin P/N 115-00784-00) Figure 2-5. Suggested Mounting Locations for the GTS 8XX Remote Rack Page 2-10 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

2.5.6 GPA 65 Location Considerations The GPA 65 can be mounted anywhere in the aircraft fuselage in any orientation. However, it cannot be mounted in an area enclosed by a fiberglass radome or on any composite structure that forms part of the exterior of the aircraft. Ensure the GPA 65 is located such that the power wires and antenna cable loss do not exceed the values listed in Section 2.4 of GTS-IM3. Note that due to the cable loss limitations outlined in GTS-IM3 section 2.4, the GPA 65 must be mounted in close proximity to the TAS/TCAS antenna. The GPA 65 should be mounted in a serviceable location in the aircraft (e.g. accessible through an access panel). Do not mount the GPA 65 near sources of high heat or moisture. Reference GTS-IM2 Section 2 for additional mounting detail. 2.5.7 Cable and Wiring Considerations In single antenna installations, the GTS 800 requires one set of coaxial cable assemblies; the GTS 820/850 requires two sets of coaxial cable assemblies. In a dual antenna installations using a directional GA 58 antenna (or other Garmin approved antenna) for both top and bottom, the GTS 800 requires two sets of coaxial cable assemblies; the GTS 820/850 requires three sets of coaxial cable assemblies. Each set consists of four coaxial cable assemblies. A bottom monopole antenna installation requires one coaxial cable length. Refer to section 2.3.4 of GTS-IM3 for more information. Wiring should be installed in accordance with AC 43.13-1B Chapter 11, sections 8 through 13. When wire separation cannot be achieved, the following issues should be addressed: The cable harness should not be located near flight control cables, high electrical capacity lines or fuel lines The cable harness should be located in a protected area of the aircraft Do not route cable near high-energy sources The cables used to connect the GPA 65 to the antenna must be assembled using the same type of coaxial cable in order to meet phase and attenuation matching requirements. In order for the system to operate in compliance with manufacturer specifications, the coaxial cable assemblies must not exceed the attenuation specifications list in GTS-IM3, Section 2. The contacts used to facilitate the use of #18 AWG wire for Aircraft Power and Aircraft Ground have expanded-diameter barrels that extend out from the back of the standard D-sub connector body to accommodate the larger diameter wire. Appropriate heat shrink tubing should be utilized to provide sufficient insulation from surrounding contacts. Ensure that routing of the wiring does not come in contact with sources of heat, RF or EMI interference. Check that there is ample space for the cabling and mating connectors. Avoid sharp bends in cabling and routing near aircraft control cables. A visual inspection shall be performed to verify that all coaxial cables are connected properly; before attempting to operate the equipment. NOTE All appliance to antenna cabling shall bundle top channels as a group and bottom channels as a group to prevent incorrect wiring between top and bottom channels. 2.5.8 Cooling Requirements The GTS 8XX and GPA 65 meet all TSO requirements without external cooling. A 5/8 diameter air fitting is provided on the rear of the GTS 8XX for the purpose of admitting cooling air if desired. If a form of forced air cooling is installed, make certain that rainwater cannot enter and be sprayed on the equipment. Avoid mounting the GTS 8XX near sources of high heat. Limiting thermal buildup by means of a fan or convective cooling is always a good practice and recommended to increase product life. GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 2-11 Rev. 2 190-00993-00

This page intentionally left blank Page 2-12 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

3 LIMITATIONS 3.1 Operation All functions of the GTS 8XX meet the design assurance qualifications for a secondary system for airplanes in Class I, Class II, Class III, and Class IV in accordance with AC 23.1309-1C, Figure 2. 3.2 STC Installations The physical mounting of the GTS 8XX and required antennas is covered within STC installation data. However, if it is necessary to relocate other equipment within the aircraft to make room for the GTS 8XX, the relocation of other equipment is beyond the scope of this STC. The installer should reference the aircraft manufacturer s data or other approved alteration methods. 3.3 Equipment Interfaced to the GTS 8XX Connections from the GTS 8XX to aircraft systems other than those interface connections installed by this STC are outside the scope of the GTS 8XX AML STC and may require further evaluation and/or certification approval. All equipment interfaced to the GTS 8XX must be previously or concurrently approved. 3.4 Major Alterations The installation of the GTS 8XX is a major alteration to the aircraft type design. Before returning the aircraft to service, installers are required to complete and submit an FAA Form 337; Major Repair and Alteration Airframe, Powerplant, Propeller, or Appliance to the appropriate FAA Flight Standards District Office describing the work accomplished. The FAA Form 337 must detail the equipment and systems to which the GTS 8XX is interfaced. 3.5 Instructions for Continued Airworthiness Before returning the aircraft to service, the GTS 8XX Configuration and Checkout Log must be completed and attached with the Instructions for Continued Airworthiness so that any aircraft with the modifications detailed in this manual may be properly maintained. 3.6 Rotorcraft Installation The installation and operational approval for use of the GTS 8XX in rotorcraft is not covered by this GTS AML STC; however, instructions and data provided in this manual may be used to perform the alteration and obtain other FAA approval. GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page 3-1 Rev. 2 190-00993-00

This page intentionally left blank Page 3-2 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2

Appendix A Lightning Zoning A.1 Purpose The GA 58 directional antenna is mounted externally on the aircraft and there are restrictions on where it can be mounted to ensure it is safe during a lightning strike to the aircraft. Lightning zoning diagrams are provided to give instructions on the correct placement of the GA 58, with respect to lightning considerations only. A.2 Summary The location of the antenna has been determined based on the different severity of strikes that occur on different areas of the aircraft and the qualification of the antenna to withstand direct effects of lightning. These diagrams depict safe locations for the antenna in the event of a lightning strike. They do not necessarily show the most optimum location for antenna performance. When choosing a mounting location, follow the recommendations in section 2.5.4 while staying within the lightning zones shown below. When determining the distance from the nose, use the physical distance instead of relying on drawings in which the reference point may be other than the tip of the nose. A.3 Lightning Zoning Diagrams Note that neither the wings nor the horizontal stabilizer have been zoned. The values d1 and d2 are defined as follows: d1 = 51 in (1.3m) d2 = 102.4 in (2.6m) Figure A-1. Zoning Legend Figure A-2. Zoning for a Nose Mounted Prop d 2 TOP (VIEW LOOKING DOWN) BOTTOM (VIEW LOOKING UP) Figure A-3. Zoning for a Twin Prop or Twin Jet Engine GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page A-1 Rev. 2 190-00993-00

Figure A-4 : Zoning for a Forward-Mounted and a Reverse-Mounted Prop d 2 d 1 TOP (VIEW LOOKING DOWN) BOTTOM (VIEW LOOKING UP) Figure A-5: Zoning for a Top-Mounted Reverse Prop Page A-2 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations 190-00993-00 Rev. 2