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190-00993-00 November 2009 Rev. 2

GTS 8XX

AML STC Installation Manual

Part 1

Overview and Limitations

GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page A

Rev. 2 190-00993-00

© 2009

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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.

Page B GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations

190-00993-00 Rev. 2

Revision 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.

2

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



Appendix A A-1 through A-2

GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page i

Rev. 2 190-00993-00

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

Page ii GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations

190-00993-00 Rev. 2

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

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

Rev. 2 190-00993-00

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.

Page 1-2 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations

190-00993-00 Rev. 2

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.


Rev. 2 190-00993-00

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.

Mode S Transponder

GTS 8XX

TAS / TCAS I

Top

Directional

AntennaOptional

Bottom

Antenna

Mode C Replies

Mode S Replies

Mode S Squitters

Mode C Interrogations

Broadcast Messages

(GTS 820 / GTS 850)

Mode S Interrogations

(GTS 820 / GTS 850)

1090 M

Hz R

X1090 M

Hz R

X

1030 M

Hz T

X1030 M

Hz T

X

Optional

Top

Antenna

Bottom

Antenna

Mode A/C/S

Replies

Mode S Squitter

Mode A/C

Interrogations


Broadcast Messages

1090 M

Hz T

X

1090 M

Hz T

X

1030 M

Hz R

X

1030 M

Hz R

X

Suppression Bus

Audio Inhibit

Aural Traffic Alert

Visual Traffic Alert

Baro Altitude (required)

ORTransponder

Serializer

Magnetic Heading (optional for active surveillance)

ORAHRS

Analog

Radio Altitude (optional for active surveillance)

GPS PVT (required for ADS-B surveillance)

ORGPS/UAT

Data Source

Options

Analog I/O w/ discrete flag

Discrete I/ORS-232

ARINC 429

LRU Data Opera

te/

Sta

ndby

Self T

est

GPS PPS

Generic Control/

Display Unit

Color Display

Knobs/Buttons

GPA 65 PA/LNA

(GTS 820 / GTS 850)

System Status

OR

Mode S Transponder(second transponder optional)

Optional

Top

Antenna

Bottom

Antenna

Mode A/C/S

Replies

Mode S Squitter

Mode A/C

Interrogations


Broadcast Messages

1090 M

Hz T

X

1090 M

Hz T

X

1030 M

Hz R

X

1030 M

Hz R

X

ARINC

Analog

AB

V/B

LW

/

NR

M

Dis

pla

y #

1

Sta

tus

Suppression

Optional Second

Display Unit

Color Display

Dis

pla

y #

2

Sta

tus

RS-422

Gear Status

Airborne Status

ORAudio AlertsUnswitched Audio

Audio

Output

Figure 1-2. System Overview


190-00993-00 Rev. 2

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 top-

mounted 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


Rev. 2 190-00993-00

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


190-00993-00 Rev. 2

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.

GTS 800

GPA 65

GTS 820/850

Directional

Directional

(Optional)*

Monopole

(Optional)**All unused antenna ports need

to be terminated with a resistive

load

Directional

Directional

(Optional)*

Monopole

(Optional)**All unused antenna ports need

to be terminated with a resistive

load

OR

OR

Figure 1-3. GTS 8XX Antenna Installation Configurations


Rev. 2 190-00993-00

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:


190-00993-00 Rev. 2

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.


Rev. 2 190-00993-00

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 Specifications

GTS 8XX Width w/out rack 2.66 inches (6.74cm)

GTS 8XX Height w/out rack 6.25 inches (15.88 cm)

GTS 8XX Depth w/Connector Kit 14.78 inches (37.54 cm)

GPA 65 Width 4.25 inches (10.80 cm)

GPA 65 Height 1.00 inches (2.54 cm)

GPA 65 Depth Not Including Connector and Cable 7.96 inches (20.22 cm)

GPA 65 Depth w/Connector and Cable Fully Extended 16.83 inches (42.75 cm)

GA 58 Width 5.63inches (14.30 cm)

GA 58 Height 2.97 inches (7.54 cm)

GA 58 Depth 4.03 inches (10.23 cm)

GTS 8XX Unit Weight w/out Connector Kit 8.9 lbs (4.03 kg)

GTS 8XX Unit Weight with Connector Kit and Vertical Rack 10.5 lbs (4.76 kg)

GTS 8XX Unit Weight with Connector Kit and Horizontal Rack 11.3 lbs (5.12 kg)

GPA 65 PA/LNA Unit Weight with Pigtail Connector Kit* 1.9 lbs (0.86 kg)

GA 58 Antenna Unit Weight w/screws and O-ring 0.82 lbs (0.37 kg)

*Used with the GTS 820 and 850.

1.7.3 Power Requirements

Characteristics Specifications

GTS 8XX Power Requirements 14/28 Vdc. See the Environmental Qualification Form for details on surge ratings and minimum/maximum operating voltages.

GTS 800 Power Consumption 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

GTS 820/850 Power Consumption 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

GTS 8XX Boot-up Current Draw 4.0 A @ 28 VDC for 70 ms

5.6 A @ 14 VDC for 100 ms


190-00993-00 Rev. 2

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 AC 43.13-1B

FAA Advisory Circular, Acceptable Methods, Techniques, and Practices – Aircraft Alterations

FAA AC 43.13-2B

Aerospace Systems Electrical Bonding and Grounding for Electromagnetic Compatibility and Safety

SAE ARP1870

Table 1-6. Garmin Product Reference Documentation

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.


Rev. 2 190-00993-00

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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 --


190-00993-00 Rev. 2

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.


Rev. 2 190-00993-00

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.


190-00993-00 Rev. 2

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.


Rev. 2 190-00993-00

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.


190-00993-00 Rev. 2

102.4"

18"

Acceptable

Installation

Area

102.4"

Optimum

Location

8' Max

Max aft location determined

When top of antenna is level

With crown of aircraft

Bottom

Antenna

Figure 2-1. Top Antenna Acceptable Mounting Location – High Wing Aircraft


Rev. 2 190-00993-00

102.4"

18"

Acceptable

Installation

Area

102.4"

Optimum

Location

8' Max

Max aft location determined

When top of antenna is level

With crown of aircraft

Bottom

Antenna

Figure 2-2. Top Antenna Acceptable Mounting Location – Low Wing Aircraft


190-00993-00 Rev. 2

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).


Rev. 2 190-00993-00

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)


190-00993-00 Rev. 2

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


Rev. 2 190-00993-00

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.


190-00993-00 Rev. 2



Rev. 2 190-00993-00

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.


190-00993-00 Rev. 2


GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations Page A-1

Rev. 2 190-00993-00

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

TOP (VIEW LOOKING DOWN)

BOTTOM (VIEW LOOKING UP)

d2

Figure A-3. Zoning for a Twin Prop or Twin Jet Engine

Page A-2 GTS 8XX AML STC Installation Manual - Part 1 - Overview and Limitations

190-00993-00 Rev. 2

Figure A-4 : Zoning for a Forward-Mounted and a Reverse-Mounted Prop

TOP (VIEW LOOKING DOWN)

BOTTOM (VIEW LOOKING UP)

d2d1

Figure A-5: Zoning for a Top-Mounted Reverse Prop

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