GTN 6XX/7XX AML STC Installation Manual 190-01007-A3 December 2012 Revision 4
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CURRENT REVISION DESCRIPTION Section Description Page D Added definitions of warnings, cautions, and notes. 1.1 Added STC information for GMA 35. 1.3 Rewrote section. 1.3.4 Added new section about required documentation for all installations. 1.5.1 Added new section and subsections about GTN/GTX installation overview. 1.6.1 Added new section about environmental qualification forms. 1.6.2 Added new section about power requirements. 1.6.3 Added new section about system documentation. 1.8.
Section Description 5.5.1.2 Added tables about RS-232 input and output selections. 5.5.1.4.3 Added new section about GDL 88. 5.5.1.4.5 Added new section about GWX. 5.5.1.4.6 Added new section about GSR 56. 5.5.1.8 Added information about the traffic page concerning the installation of a GDL 88. 5.5.1.9 Added information concerning upgrading from software version 2.00 to 3.00. 5.5.1.12 Added new section about ARINC 453/708 configuration page. 5.5.2.4 Added new section about Digital Radar.
DOCUMENT PAGINATION Section Table of Contents Pagination i - xiv Chapter 1 1-1 through 1-20 Chapter 2 2-1 through 2-38 Chapter 3 3-1 through 3-50 Chapter 4 4-1 through 4-8 Chapter 5 5-1 through 5-116 Chapter 6 6-1 through 6-2 Chapter 7 7-1 through 7-2 Chapter 8 8-1 through 8-2 Appendix A A-1 through A-16 Appendix B B-1 through B-8 Appendix C C-1 through C-12 Appendix D D-1 through D-2 Appendix E E-1 through E-90 Appendix F F-1 through F-10 Appendix G G-1 through G-8 Appendix
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TABLE OF CONTENTS 1 GENERAL DESCRIPTION ............................................................................................... 1-1 1.1 INTRODUCTION ............................................................................................................................. 1-1 1.2 TERMINOLOGY .............................................................................................................................. 1-1 1.3 SCOPE....................................................................
2.4.5 2.4.6 2.4.7 2.4.8 2.4.9 2.4.10 2.4.11 2.4.12 2.4.13 2.4.14 2.4.15 2.4.16 3 Electrical Bonding ................................................................................................................ 2-23 Placards and Labels .............................................................................................................. 2-25 Power Distribution ...............................................................................................................
4.1.1 P1001 Connector .................................................................................................................... 4-1 4.1.2 P1002 Connector .................................................................................................................... 4-2 4.1.3 P1003 GTN COM Connector (GTN 635/650/750 Only) ....................................................... 4-3 4.1.4 P1004 GTN NAV Connector (GTN 650/750 Only) ..............................................................
5.7.11 EMI/RFI Check .................................................................................................................. 5-106 5.8 FLIGHT CHECKS ........................................................................................................................ 5-107 5.8.1 GPS Flight Check ............................................................................................................... 5-107 5.8.2 VHF COM Flight Check (GTN 635/650/750) .......................................
C.6 C.7 C.8 C.9 C.10 C.11 C.12 C.13 C.14 C.15 C.16 C.17 C.18 C.19 EHSI ............................................................................................................................................ C-6 IRU/AHRS................................................................................................................................... C-7 TRANSPONDER .............................................................................................................................
LIST OF FIGURES Figure 1-1. GTN System Interface Overview ............................................................................................ 1-6 Figure 1-2. GMA 35 System Interface Overview ...................................................................................... 1-7 Figure 1-3. Interface between One GTN and One GTX ............................................................................ 1-8 Figure 1-4. Interface between One GTN and Two GTXs........................................
Figure 3-17. Example Electrical Load Tabulation ................................................................................... 3-43 Figure 3-18. Blank Emergency Power Operation Calculation Form ....................................................... 3-44 Figure 3-19. Example of Completed Emergency Power Operation Calculation ..................................... 3-45 Figure 5-1. Configuration Mode ..........................................................................................................
Figure 5-39. Connected Radios Configuration page ................................................................................ 5-65 Figure 5-40. GDL 88 Faults Page ............................................................................................................ 5-66 Figure 5-41. GDL 88 Aircraft Configuration Page .................................................................................. 5-67 Figure 5-42. GDL 88 Antenna Configuration Page ................................................
Figure E-7. External Navigation Source Selection Annunciator Interconnect ....................................... E-15 Figure E-8. GTN 6XX/7XX – CDI Interconnect .................................................................................... E-19 Figure E-9. GTN 6XX/7XX – Bendix King KI 209A Interconnect ....................................................... E-22 Figure E-10. GTN 6XX/7XX – Bendix King KI 208A Interconnect ..................................................... E-23 Figure E-11.
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LIST OF TABLES Table 1-3. Pre-Installation Checklist ....................................................................................................... 1-12 Table 1-4. GTN 6XX/7XX and GMA 35 Environmental Qualification Forms ...................................... 1-13 Table 1-5. GTN and GMA 35 Current Specifications ............................................................................. 1-13 Table 1-6. Garmin GTN 6XX/7XX Reference Documentation ....................................................
Table 5-3. ARINC 429 DATA OUT Selections ...................................................................................... 5-12 Table 5-4. SDI Selections ........................................................................................................................ 5-13 Table 5-5. RS-232 Channel Input Selections ........................................................................................... 5-14 Table 5-6. RS-232 Channel Output Selections ...........................................
Table 5-44. AHRS Labels ........................................................................................................................ 5-50 Table 5-45. Air Data Computer (ADC) Labels........................................................................................ 5-51 Table 5-46. EFIS Display System (EFIS/ADC) Labels ........................................................................... 5-51 Table 5-47. GPS/FMS Navigation System (GPS) Labels.............................................
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1 1.1 GENERAL DESCRIPTION Introduction This manual is written for software version 2.00 or later. The software version and information in this document are subject to change without notice. Visit the Dealer Resource Center on Garmin’s website (www.garmin.com) for current updates and supplemental information concerning the operation of this and other Garmin products.
1.3 Scope This installation manual applies to the modification of an aircraft under AML STC SA02019SE-D to install the equipment described in Table 1-1. Interfaces between the equipment listed in the second column and the GTN and/or GMA 35 are covered by STC SA02019SE-D. Table 1-1.
1.3.1 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.
1.4 GTN/GMA 35 System Overview The GTN WAAS navigators are a family of aviation panel mounted retro-fit products that are intended to supersede the Garmin 400/500 WAAS series GPS, GPS/COM, and GPS/NAV/COM retro-fit products. The GTN 6XX product family consists of the GTN 625 GPS/SBAS navigator, the GTN 635 GPS/SBAS/COM navigator, and the GTN 650 GPS/SBAS/NAV/COM navigator. The GTN 7XX product family consists of the GTN 725 GPS/SBAS navigator, and the GTN 750 GPS/SBAS/NAV/COM navigator.
1.4.1.2 GTN 6XX Series Description The GTN 6XX WAAS navigators are a family of panel-mounted products that supersede the 400W series GPS/NAV/COM navigators. The GTN 6XX series units include the GTN 625, GTN 635, and GTN 650. They are 6.25 inches wide and 2.65 inches tall. The GTN 6XX features a 600 by 266 pixel color LCD touchscreen.
1.4.3 GTN Interface Summary The GTN utilizes ARINC 429, RS-232, discrete inputs/outputs, and Garmin High Speed Data Bus (HSDB) interfaces to communicate with other LRUs and Systems on the aircraft. A summary of the GTN interfaces are shown in Figure 1-1. For more detail, refer to Appendix E.
1.4.4 GMA 35 Interface Summary A summary of the GMA 35 interfaces is shown in Figure 1-2. GTN 7XX Control Head Marker Beacon Antenna RS-232 COM 1 Transceiver COM 2 Transceiver Cockpit Speaker COM 3 Transceiver NAV 1 Radio Garmin GMA 35 Audio Panel NAV 2 Radio Pilot/Copilot Headsets (x 2) Passenger Headset (x 4) DME Radio Unswitched, Unmuted Audio Input (x 4) ADF Radio Music Input (x 2) Telephone Audio Marker Beacon Annunciators Figure 1-2.
1.5 GTN/GMA 35 Installation Overview Always follow acceptable avionics installation practices per AC 43.13-1B, AC 43.13-2B, or later FAA approved revisions of these documents. The GPS/SBAS installation instructions have been prepared to meet the guidance material contained in AC 20-138A, “Airworthiness Approval of Global Navigation Satellite System (GNSS) Equipment”.
If there are two GTX units, they must both be connected to the GTN as shown in Figure 1-4. In this case, the GTN can control both GTX #1 and GTX #2. GTX 3X/3XX #1 RS232 GTN 6XX/7XX RS232 GTX 3X/3XX #2 Figure 1-4. Interface between One GTN and Two GTXs Similarly, to connect one GTX to dual GTNs, each of the GTNs needs to have an RS-232 connection to the single GTX as shown in Figure 1-5. In this case, both GTN #1 and GTN #2 can control the transponder.
If there are two GTXs connected to dual GTNs, GTN #1 should be connected to GTX #1 and GTN #2 should be connected to GTX #2 as shown in Figure 1-6. In this configuration, each of the GTN units is capable of controlling either GTX through the HSDB interface. GTN 6XX/7XX #1 RS232 GTX 3X/3XX #1 HSDB GTN 6XX/7XX #2 RS232 GTX 3X/3XX #2 Figure 1-6.
1.5.1.2 Installation without GTN Control of GTX Transponder The GTX 327, 328, and 330 can be connected to the GTN without allowing the GTN to control the transponder functions. GTN and GTX configuration settings can be found in Section C.8 and Figure E-12, respectively. If the GTN is not set to control the GTX 327, the interface to the GTX 327 is not required. However, the GTN can send GPS groundspeed to the transponder.
1.5.2 Pre-Installation Checklist Before beginning a GTN/GMA 35 installation, it is important to ensure the aircraft meets the prerequisites for the installation of the GTN system under this STC. The following checklist is provided to help the installer determine the necessary requirements that must be met before beginning installation of the GTN in a specific aircraft. Ensure each of the items outlined are completed as necessary before beginning the modification.
1.6 Technical Specifications For GTN 6XX technical specifications, see GTN 625/635/650 TSO Installation Manual, P/N 190-01004-02. For GTN 7XX technical specifications, see GTN 725/750 TSO Installation Manual, P/N 190-01007-02. 1.6.1 Environmental Qualification Forms The latest revision of the Environmental Qualification Forms for the GTN 6XX and 7XX as well as the GMA 35 are available directly from Garmin under the part numbers listed in Table 1-4. Table 1-4.
[2] The specified current draw does not include the superflags. If connected, their current draw must be added to the specified current. The superflags will supply up to 320 mA each regardless of the GTN’s input voltage. 1.6.3 System Documentation Table 1-6.
Table 1-9.
1.7 GPS/WAAS Antenna Requirements Antenna Performance is critical to GPS/SBAS operation. Table 1-10 lists antennas that meet Garmin’s minimum performance specifications. The GTN must be installed with one of these antennas to achieve acceptable performance. The installation of these antennas must be previously FAA-approved (i.e. field approval) or installation must be completed via Garmin GPS/WAAS antenna AML STC SA02018SE-D.
1.8 GTN Databases The GTN utilizes various databases. With the exception of the Navigation, Basemap, SafeTaxi, and Obstacle databases which reside internal to the GTN, all databases are stored in a single SD memory card that is inserted into the vertical slot on the left side of the GTN. The following describes each database and how the databases are updated. See Table 1-11 for a summary of the database location and update rate.
1.8.2 Navigation Database The Jeppesen navigation database provides the GTN with the required information for displaying flight plan information. The GTN utilizes a database stored on an SD memory data card for easy updating and replacement. The navigation database may be updated by inserting an updated navigation database update card into the vertical SD card slot on the left side of the GTN. The actual database is downloaded into the unit, so the card can be removed after the update.
1.8.5 SafeTaxi® Database SafeTaxi diagrams provide detailed taxiway, runway, and ramp information at more than 900 airports in the United States. The data conversion process is performed using software that is developed and maintained under Garmin configuration management according to RTCA/DO-200A, Level 2, Standards for Processing Aeronautical Data. The SafeTaxi database is stored internally in the GTN for normal operation.
1.9 Fault Detection and Exclusion (FDE) The GTN, when installed as defined in this manual, complies with the requirements for GPS primary means of navigation in oceanic and remote airspace when used in conjunction with the provided FDE prediction program. The GTN includes internal Fault Detection and Exclusion (FDE) software which is active for all flight phases including oceanic and remote operations, en route and terminal, and precision and non-precision approaches.
2 INSTALLATION OVERVIEW 2.1 Introduction This chapter is an overview of the steps required for the installation of the GTN 6XX and 7XX navigators. 2.2 Available Equipment The GTN and GMA 35 are available under the part numbers listed in Table 2-1. The GPS/WAAS antennas are available under the part numbers listed in Table 1-10. Table 2-1.
2.3 2.3.1 Installation Materials Accessories Available from Garmin Table 2-4 through Table 2-11 list the items provided in the GTN and GMA 35 installation kits. Table 2-4.
Table 2-7. GTN Installation Kit P/N 010-00819-50 Accessories Used With GTN 725 (Black) Item Part Number Connector Kit, GTN 725 011-02326-00 Database Card, GTN 6XX/7XX 010-00900-00 SMP, Mounting Rack, GTN 7XX 115-01294-00 Backplate Sub-Assembly, GTN 725 011-02246-00 Configuration Module Kit 011-00979-03 Product Info Kit, GTN 7XX K00-00488-00 Cleaning Kit, GTN 6XX/7XX 010-11527-00 Table 2-8.
Table 2-10. GTN Installation Kit P/N 010-00890-50 Accessories Used With GTN 750 (Gray) Item Part Number Connector Kit, GTN 750 011-02326-02 Database Card, GTN 6XX/7XX 010-00900-00 SMP, Mounting Rack, GTN 7XX 115-01294-00 Backplate Sub-Assembly, GTN 750 011-02246-02 Configuration Module Kit 011-00979-03 Product Info Kit, GTN 7XX K00-00488-00 Cleaning Kit, GTN 6XX/7XX 010-11527-00 Table 2-11.
2.3.2 Materials Required but not Supplied 2.3.2.1 Accessories Required but not Supplied The following installation accessories are required for the installation but not supplied by Garmin. Table 2-13. Accessories Required but Not Supplied Item Requirements COM Antenna (GTN 635/650/750 only) Shall meet TSO-C37( ) and C38( ) or TSO-C169( ). 50 Ω, vertically polarized with coaxial cable NAV Antenna (GTN 650/750 only) Shall meet TSO-C40( ) and C36( ). 50 Ω, horizontally polarized with coaxial cable.
2.3.2.3 • • • Materials Required but Not Supplied for Optional GMA 35 Installations Mounting Screws for the GMA 35 (6 minimum – MS24693 Screw, Machine, Flat Countersunk Head 100°, Cross Recessed with .1380-32 UNC-2A Thread, corrosion resistant steel) Marker Beacon Antenna approved to TSO-C35( ) Stereo headphone jacks (up to 6), microphone jacks (up to 6), 3.5mm stereo jacks (up to 2), and insulating washers for all. 2.3.2.
2.3.2.6 Manufacturer Information NOTE Manufacturer information is provided for convenience only. It was current at the time of initial publication and may change at any time. Aluminum Foil Tape: 3M 3M Corporate Headquarter 3M Center St. Paul, MN 55144-1000 Phone: 1-888-364-3577 www.3m.com Fuse: Littelfuse World Headquarters 8755 West Higgins Road Suite 500 Chicago, IL 60631 USA Phone: (773) 628-1000 Fax: (847) 391.0894 www.littelfuse.
2.3.2.7 Materials Required for Some GTN 650/750 NAV Antenna Installations Some aircraft may require the use of a splitter or diplexer for connection of the VOR/LOC and G/S antennas, or combination VOR/LOC/GS antennas. Refer to Figure E-18 to determine if a splitter or diplexer is required for the installation. • • 2.3.3 Garmin Part Number 013-00112-00 (Mini-Circuits ZFSC-2-1B+BNC.) Comant Diplexer VOR/GS, Model CI-507.
5. Click Setup. The window shown in Figure 2-2 will appear to guide you through the software loader card creation process. Figure 2-2. System and Software Version 6. Click Next to get to the window shown in Figure 2-3. Figure 2-3. GTN Software Loader Card Formatting CAUTION 190-01007-A3 Rev.
In order to create a GTN Software Loader Card, the drive that you select will be completely erased. 7. Ensure that the correct drive is selected. Click Next to create the card. Click Next to acknowledge any warnings that appear. The progress window shown in Figure 2-4 will appear when the card is being created. Figure 2-4. Update Progress Window 8. After the card has been created, the window shown in Figure 2-5 will appear. Click Finish to complete the update process. Figure 2-5. Update Completion 9.
2.3.4 Special Tools Required Some of the connectors use crimp contacts. The table below identifies crimp tools required to ensure consistent, reliable crimp contact connections for the rear D-sub connectors. A milliohm meter with an accuracy of ± 0.1 mΩ (or better) is required to measure the electrical bonding between the GTN and GMA 35 system components and aircraft ground. Table 2-14.
2.4 Installation Considerations 2.4.1 Minimum System Configuration The following section describes the minimum configuration required for IFR and VFR installations of the GTN. 2.4.1.1 VFR GPS Installation The minimum GTN unit installation requires the following items for a VFR Installation: • • • • • GTN 6XX/7XX unit (installed in the aircraft manufacturer approved location for 6.25 inch wide avionics equipment). GPS/WAAS antenna required for GPS navigation functions.
2.4.1.3 IFR Installation of a GTN 650/750 For an IFR installation of a GTN 650 or GTN 750, the criteria in Section 2.4.1.1 must be met in addition to the following: • If the GTN is installed for GPS primary navigation, then the GTN must be interfaced to a navigation indicator installed in the pilot’s primary field-of-view (or in the aircraft manufacturer approved mounting location). The indicator must have a vertical deviation indicator (GS) in order to perform approaches with vertical guidance.
2.4.2.1 Multiple Uncorrected Pressure Altitude Sources The GTN unit can accept uncorrected pressure altitude from multiple ARINC 429 and RS-232 sources. If multiple sources of altitude data are supplied to the GTN, only valid data from the highest priority source is used. If the highest priority source becomes unavailable, data is taken from the next-highest priority source. The priorities of the altitude sources are as follows from highest to lowest: 1. 2. 3. 4. 5. 6. 7. 8.
2.4.2.3 Multiple Heading Sources NOTE Heading is not required by the GTN; however, to take full advantage of the GTN unit capabilities, an optional heading source is recommended to allow the map to be oriented to heading up, to provide autopilot roll steering on ARINC 424 heading legs, to display TAS traffic and WX-500 Stormscope data on the moving map, and to calculate winds if airspeed is also available. The GTN unit can accept heading data from multiple ARINC 429, RS-232, and Synchro sources.
2.4.2.5 Multiple True Airspeed Sources NOTE True Airspeed is not required for the GTN; however, the GTN uses true airspeed to calculate winds aloft if heading is also available. The GTN unit can accept true airspeed data from multiple ARINC 429 and RS-232 sources. If multiple sources of true airspeed data are supplied to the GTN, only valid data from the highest priority source is used. If the highest priority source becomes unavailable, data is taken from the next-highest priority source.
2.4.2.8 Multiple Total Air Temperature Sources The GTN unit can accept total air temperature data from multiple ARINC 429 and RS-232 sources. If multiple sources of total air temperature data are supplied to the GTN, only valid data from the highest priority source is used. If the highest priority source becomes unavailable, data is taken from the nexthighest priority source. The priorities of the total air temperature sources are as follows from highest to lowest: 1. 2. 3. 4. 5.
ANTENNA MASKED BY VERTICAL FIN, TTAIL OR DORSAL FIN. ANTENNA NOT MOUNTED LEVEL WITH RESPECT TO THE NORMAL FLIGHT ATTITUDE DISTANCE BETWEEN COM AND GPS/WAAS ANTENNAS SHOULD BE GREATER THAN 2 FT. SEE ITEM 2.5.1 IN THIS SECTION FOR GPS/WAAS ANTENNA LOCATION. GOOD BETTER GREATER THAN 3" AFT OF WINDSCREEN NORMAL FLIGHT ATTITUDE SIDE VIEW ANTENNA MUST BE ON TOP OF AIRCRAFT CENTERLINE GPS 1 COMM GPS 2 TOP VIEW GPS/WAAS ANTENNA OFFSET FROM CENTERLINE WITH TYPICAL DUAL GPS INSTALLATION Figure 2-6.
2.4.4.1 GPS Antenna Location The GPS antenna is a key element in the overall system performance and integrity for a GPS/SBAS system. The mounting location, geometry, and surroundings of the antenna can affect the system performance and/or availability. The following guidance provides information to aid the installer in ensuring that the most optimum location is selected for the installation of the GPS antenna.
6. A 12-inch center-to-center spacing between GPS antennas is needed to achieve the best possible low-elevation antenna gain by minimizing pattern degradation due to shadowing and near-field interaction. When practical, 12-inch center-to-center spacing between GPS antennas must be used. If 12-inch spacing is not practical, the maximum center-to-center spacing possible must be used, but never less than 9-inch center-to-center spacing.
2.4.4.4 Ground Plane Ensure that the GPS/NAV/COM antennas are electrically bonded to the aircraft. Follow the aircraft manufacturers’ instructions for the NAV and COM antenna installations, or obtain other FAA approval. The GPS/WAAS antenna requires a minimum ground plane radius of 7.5 inches around the perimeter of the antenna. Refer to Figure 2-7. For metal aircraft, the surrounding metal skin on which the antenna is mounted supplies the ground plane.
2.4.4.5 Interference of GPS On some installations, VHF COM transceivers, Emergency Locator Transmitter (ELT) antennas, and Direction Finder (DF) receiver antennas can re-radiate harmonics that can potentially interfere with the GPS antenna. The GTN unit COM does not interfere with its own GPS section. However, placement of the GPS antenna relative to a COM transceiver and COM antenna (including the GTN 635/650/750 COM antenna), ELT antenna, and DF receiver antenna is important.
the antenna’s susceptibility to RF radiation from components inside the aircraft. 2.4.5 Electrical Bonding Electrical equipment chassis, shield/ground terminations, antennas, supporting brackets, and racks must be electrically bonded to the aircraft’s main structure (metallic or tube/fabric aircraft) or instrument panel (composite aircraft). Refer to SAE ARP 1870 Section 5 when surface preparation is required to achieve electrical bond.
Figure 2-8. Electrical Bonding Preparation – Nut Plate (LOCKING WASHER SHOULD BE USED) Figure 2-9. Electrical Bonding Preparation – Bolt/Nut Joint ELECTRICAL BOND PREP – TERMINAL LUG. (LOCKING WASHER SHOULD BE USED) Figure 2-10. Electrical Bonding Preparation – Terminal Lug GTN 6XX/7XX AML STC Installation Manual Page 2-24 190-01007-A3 Rev.
2.4.6 Placards and Labels All placards and labels must be readable in all cockpit lighting conditions. Ambient flood lighting is acceptable. Placards added as part of the GTN and GMA 35 installation must be displayed in a conspicuous place and must not be easily erased, disfigured, or obscured. Text height must be a minimum of 0.10 inch, and the text must contrast with the placard surroundings such that it is easily readable.
2.4.7.3 Power Distribution – Dual GTNs, Aircraft Less than 6000 Pounds When two GTNs are installed in aircraft with a maximum certified gross takeoff weight of less than 6000 pounds, connect GTN #1 to the avionics bus. The NAV/GPS and COM circuit breakers (reference Figure E-4) for GTN #1 must be connected to the same avionics bus. If a second avionics bus is available, connect GTN #2 to the second avionics bus; otherwise connect GTN #2 to the same avionics bus as GTN #1.
2.4.7.5 Power Distribution – Dual GTNs, Aircraft Greater than 6000 Pounds When dual GTNs are installed in aircraft with a maximum certified gross takeoff weight of 6000 pounds or greater, each GTN must be installed on a separate avionics bus. If two avionics busses are not available in the aircraft, install GTN #1 on the main bus and GTN #2 on the avionics bus. Both options are shown in Figure 2-14. Preferably, GTN# 1 should not be connected to the bus that supplies power to the GTN #2 avionics bus.
2.4.9 External Annunciators Installations completed in accordance with the requirements specified in this manual may not require the use of any external annunciators, since all annunciations are provided on the GTN unit’s front panel. Refer to Section 2.4.10.1.1 to determine whether or not external annunciators are required. If external GPS annunciators are required as part of the GTN installation, the preferred annunciator is the Mid-Continent MD 41-151X, as shown in Figure E-7.
If the GNS 400W/500W is installed concurrently with a GTN 6XX/7XX, there are special mounting guidelines. The GTN crossfills flight plan and user waypoint data to the GNS. Since the data flows from the GTN to the GNS, it is recommended that the GTN be mounted in the #1 position relative to the GNS in a GTN/GNS installation. In a typical radio stack, this would be above the GNS. This recommendation is only applicable if the GTN-GNS crossfill function is utilized in the installation. 2.4.10.1.
o The top edge of the GTN unit is no lower than the bottom edge of the primary flight instruments or the unit is line abreast with the affected CDI. 4. If the GTN unit is mounted to the left of the primary instruments, the internal display of annunciation within the GTN unit is considered to be within the acceptable field-of-view if the following criteria are met: o The right edge of the GTN unit is within 10.0 ± 0.
2.4.10.1.3 GPS Navigation Annunciation Use the steps below to determine whether or not the integrated GPS navigation annunciation displayed on the GTN unit to be installed is within the acceptable field of-view as depicted in Figure 2-16. 1. Determine the pilot’s primary view centerline, as defined in Step 1 of Section 2.4.10.1.2. 2. Measure the horizontal distance from the primary view centerline to the left or right edge of the GTN unit, as appropriate. 3.
UPPER LIMIT PILOT’S INSTRUMENT “T” Glareshield ACCEPTABLE FIELD-OF-VIEW AREA GTN 7XX SHOWN 2 3 LOWER LIMIT 12.2 16.8 14.4 16.8 Instrument “T” Centerline 1 NOTES: 1 FOR AIRCRAFT WITHOUT THE BASIC INSTRUMENT “T” CONFIGURATION, THE CENTER OF THE PILOT’S YOKE OR CONTROL STICK IN THE NEUTRAL POSITION SHOULD BE USED TO DETERMINE THE CENTERLINE.
2.4.10.1.4 TAWS Annunciation (units with TAWS only) Use the steps below to determine whether or not the integrated TAWS annunciations displayed on the GTN unit to be installed is within the acceptable field of view as depicted in Figure 2-17. 1. Determine the pilot’s primary view centerline, as defined in Step 1 of Section 2.4.10.1.2. 2. Measure the horizontal distance from the primary view centerline to the left or right edge of the GTN unit, as appropriate. 3.
UPPER LIMIT PILOT’S INSTRUMENT “T” Glareshield ACCEPTABLE FIELD-OF-VIEW AREA GTN 750 SHOWN 2 3 LOWER LIMIT 11.5 16.8 15.4 16.8 Instrument “T” Centerline 1 NOTES: 1 FOR AIRCRAFT WITHOUT THE BASIC INSTRUMENT “T” CONFIGURATION, THE CENTER OF THE PILOT’S YOKE OR CONTROL STICK IN THE NEUTRAL POSITION SHOULD BE USED TO DETERMINE THE CENTERLINE.
2.4.11 Cable and Wiring Considerations Wiring should be installed in accordance with AC 43.13-1B Chapter 11, sections 8 through 13. The following issues should be addressed: • • • • • • • • It should not be possible for the cable harness to be exposed to wire chafing; It should not be possible for a cable harness to be exposed to wire chafing in a manner that both GPS units fail simultaneously; The cable harness should not be located near flight control cables, high capacity electrical lines (e.g.
2.4.11.4 Shield Termination Consideration Shield termination at non-Garmin equipment end must be as short as possible and not to exceed 3.0” taking into consideration any non-Garmin equipment’s installation requirements. When there are no requirements given by the non-Garmin equipment installation manual, then the shields may be connected to the metal connector backshell when the backshell is grounded to airframe chassis ground.
2.4.12 Audio Electrical Noise Because the audio panel is a point in the aircraft where signals from many pieces of equipment are brought together, take care to minimize effects from coupled interference and ground loops. Coupled interference can creep into audio system interconnecting cables when they are routed near large AC electric fields, AC voltage sources and pulse equipment (strobes, spark plugs, magnetos, EL displays, CRTs, etc).
2.4.14 GMA 35 Wiring Considerations for Failsafe Operation The GMA 35 includes a failsafe circuit that connects the pilot’s headset and microphone directly to COM1 in the event that power is interrupted or RS-232 communication with the GTN is lost. When the GMA 35 is installed with a GTN 750 and a second COM radio, the GTN 750 COM must be connected to the COM 2 pins (J3501-13,-14,-15) on the GMA 35. The other radio should be connected to the COM 1 pins.
3 INSTALLATION PROCEDURE 3.1 Optional Accessories 3.1.1 GPS/WAAS Antenna Options For information regarding antenna selection, refer to Section 1.10. Once the antenna type is decided upon, refer to the information below for detailed parts information for antennas available from Garmin. Contact the antenna manufacturer directly for non-Garmin antennas. 3.1.1.1 GA 35 Antenna The GA 35 antenna, Garmin P/N 013-00235-XX, contains one of the items listed in Table 3-1. Table 3-1.
3.1.1.3 GA 37 Antenna The GA 37 antenna, Garmin P/N 013-00245-XX, contains the one of the items listed in Table 3-3. Table 3-3. GA 37 Antenna Item Part Number Qty 013-00245-00 (White) GA 37 GPS/WAAS + XM Antenna [1] 013-00245-01 (Black) 1 013-00245-02 (Olive Green) [1] Antenna includes 8-32 UNC-2A x 1.00” Stainless Steel mounting screws (qty 4) and O-ring (qty 1). An antenna doubler may also be required. Refer to Section 3.1.2 for additional information.
3.3 3.3.1 Antenna Installation and Connections GPS/WAAS Antenna This section provides information on the antenna cable installation. Refer to Section 2.4.4.1 for antenna installation location considerations. NOTE The internal GTN unit COM does not interfere with its own GPS receiver. However, placement of the GTN unit antenna relative to other COM transceivers and antennas (including the GTN unit COM antenna) is critical.
If a VHF COM transmitter causes problems with the GPS on the selected frequencies as listed in the postinstallation checkout, the problem may be due to the ELT. This can be verified by disconnecting the ELT antenna coaxial at the ELT unit. If the ELT is found to cause the problem, then contact the ELT manufacturer or replace the ELT. 3.3.1.
NOTES: 1 THE OVERBRAID MUST BE INSERTED INTO THE GROUNDING LUG BY COMBING OUT AND TWISTING THE WIRE STRANDS AND BEFORE TERMINATING THEM IN A TERMINAL LUG. 2 WHEN INSTALLING OVERBRAID AT CONNECTOR END OF PIGTAIL, THE OVERBRAID IS PUSHED DOWN UNTIL IT TOUCHES THE TOP SURFACE OF THE CONNECTOR. CONTINUE PUSHING BRAID DOWN BY SPREADING IT OUT ALONG THE TOP SURFACE OF THE CONNECTOR. APPLY THE FIRST TIE WRAP AROUND THE BRAID AND ANTENNA CABLE WHERE IT ENTERS THE CONNECTOR.
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3.3.2 COM Antenna Cable Considerations The GTN requires a standard 50Ω vertically polarized antenna. Follow the antenna manufacturer’s installation instructions for mounting the antenna, and gain other FAA approval. For optimum performance the antenna should be mounted on a metal surface or a ground plane with a minimum area of 18 x 18 inches. Refer to Section 2.4.4.2 for installation location considerations. The antenna coaxial cable must be made of RG-142B, RG-400 or a comparable quality 50Ω coaxial.
3.3.3 NAV Antenna The NAV antenna is a standard 50Ω horizontally polarized NAV/VOR/Localizer/Glideslope antenna. The NAV antenna receives VOR frequencies between 108.00 and 117.95 MHz and localizer frequencies between 108 and 112 MHz and glideslope information between 328.6 and 335.4 MHz Follow the antenna manufacturer’s installation instructions for mounting antennas, and gain other FAA approval. It is recommended that the installer use RG-142B, RG-400 or equivalent 50Ω coaxial for the NAV antenna(s).
3.3.3.2 NAV Antenna Cable Diplexer Installation The Comant CI-507 diplexer is required to be installed with the NAV antenna coaxial cable wiring in certain configurations, and it must be installed in accordance with the guidance below. Connecting the diplexer is installation-dependent. Wire the diplexer as shown in the applicable diagram in Figure E-18.
3.4 GTN/GMA 35 Location and Mounting 3.4.1 GTN Rack Installation Use the dimensions shown in Figure A-4 (GTN 6XX) or Figure A-6 (GTN 7XX) to prepare the mounting holes for the GTN 6XX or GTN 7XX unit. The GTN 6XX or GTN 7XX unit mounting rack itself may also be used as a template for drilling the mounting holes. 1. The backplate of the rack may optionally be removed for ease of mounting in the aircraft panel.
3.4.3 GMA 35 Rack Installation Use the six 6-32 screws that accompany the GMA 35 installation kit to install the GMA 35 mounting rack to a GTN 7XX mounting rack. The screws are installed from the bottom side of the GTN 7XX mounting rack using through-holes to access the mounting locations on the GMA 35 mounting rack. Refer to Figure A-2 and Figure A-8. 3.4.4 GMA 35 Unit Insertion and Removal The GMA 35 is installed into the rack by sliding it straight in until it stops.
Table 3-6. Sample Aircraft Weight and Balance Calculation Previous Aircraft Weight and Balance Calculated: 06/29/12 Useful Load (lb) 1093.3 Empty Weight (lb) 2306.70 Description of Items removed from aircraft Weight (lb) C.G. (in) 138.83 Arm (in) Moment (lb-in) 320233.96 Moment (lb-in) SL15 Audio Panel 1.00 55.00 55.00 GMX200 4.60 55.00 253.00 CNX80/GNS480 Color GPS/NAV/COM 6.10 55.00 335.50 SL30 NAV/COM 2.30 55.00 126.50 Total Removed: 14.
3.6 Electrical Installation Procedure 3.6.1 Special Tools Required A crimp tool meeting MIL specification M22520/2-01 and a positioner/locator are required to ensure consistent, reliable crimp contact connections for the rear D-sub connectors. Refer to Table 2-14 for a list of recommended crimp tools. A milliohm meter is required to check GTN and optional GMA 35 installation bonding to aircraft structure or instrument panel. 3.6.
CAUTION Check wiring connections for errors before inserting the unit into the tray. Incorrect wiring could cause component damage. Table 3-7. Socket Contact Part Numbers [1] P1001-P1005 Wire Gauge (including P1001 configuration module) [2] 22-28 AWG Garmin 336-00021-00 Military M39029/58-360 [3] AMP 204370-2 [3] Positronic MC8522D [3] ITT Cannon 030-2042-000 [3] [1] Recommended crimp tools are listed in Table 2-14.
3.6.3 Backshell Assembly and D-Subminiature Connectors The GTN connector kits (P/N 011-02325-00 [GTN 625], P/N 011-02325-01 [GTN 635], P/N 011-02325-02 [GTN 650], P/N 011-02326-00 [GTN 725], and P/N 011-02326-01 [GTN 750]) include Garmin backshell assemblies and Garmin ground adapter assemblies. Backshell connectors give the installer the ability to terminate shield grounds at the backshell housing using the shield block ground kit.
Table 3-9. GMA 35 Backshell Assembly Figure 3-2 thru Figure 3-5 Ref [1] [2] [3] [4] [5] [6] [7] Description Garmin P/N Notes 1 Backshell 125-00083-00 [2] 2 Shield block 117-00147-00 [3] 3 Screw, 4-40x.250, FLHP 100, SS/P 211-63234-08 [3] 6 Screw, 4-40x.437, FLHP100, SS/P, Nylon 211-60234-11 [2] 7 Strain Relief 115-00499-02 [2] 8 Cover 115-00500-02 [2] 9 Screw, 4-40x.
3.6.3.1 Shield Block Assembly Procedure The parts for the connector and backshell assemblies for the GTN installation are listed in Table 3-8. The parts for the connector and backshell assemblies for the GMA 35 installation are listed in Table 3-9. Backshell connectors give the installer the ability to terminate shield grounds at the backshell housing using the Shield Block ground kit. Table 3-8 and Table 3-9 list Garmin part numbers for the GTN and GMA 35 D-sub connectors and the backshell assemblies.
PREFERRED METHOD ALTERNATE METHOD 1 SHIELD DRAIN COMPONENTS AS SHORT AS PRACTICAL (3" MAX COMBINED) 13 12 13 2.5 INCHES MAX 0.31 INCHES MAX 0.17 INCHES ALTERNATE METHOD 2 (DAISY CHAIN) Figure 3-3. Shielded Cable Preparation GTN 6XX/7XX AML STC Installation Manual Page 3-18 190-01007-A3 Rev.
OF ACT GE NT ED CO ET CK A/R 14 . AX M .5" 2 SO D IEL ING NN GI H FS O BE 12 A/R 10 11 A/R A/R 19 15 A/R 18 A/R . AX D M E " .31 POS LD X E HIE S 13 A/R 17 A/R 16 A/R Figure 3-4. Shield Termination on Backshell Assembly (Preferred Method) 190-01007-A3 Rev.
The screws (16) used to ground the shields to the shield block must not penetrate too far past the shield block when installed. If the screws are too long, they could potentially damage the wires going into the backshell. Note that a maximum of three ring terminals per screw is allowed for grounding shields to the shield block. A maximum of two shield drains may be inserted into each ring terminal, meaning that one shield block grounding screw (16) may accommodate grounding of up to six shield drains.
Prepare all of the shielded cables as shown in Figure 3-3. Refer to Figure 3-5 for details of the shield termination to the connector backshell. Skip to step 5 below for wires with no shielding. 1. At the end of the shielded cable (11), strip back a 2.5” maximum length of the jacket to expose the braid. Remove this exposed braid. Carefully score the jacket 1/4” to 5/16” from the end and remove the jacket to leave the braid exposed.
Complete the following steps to assemble the backshell onto the connector: 1. Attach the Shield Block (2) to the backshell (1) by inserting the flathead screws (3) through the holes on the Shield Block and threading into the tapped holes on the backshell (1) (See Figure 3-2). 2. Wrap the cable bundle with Silicone Fusion Tape (19 or a similar version) at the point where the backshell strain relief and cast housing will contact the cable bundle. 3.
3.6.3.2 Configuration Module Installation (P1001 only) GTN P1001 connector assemblies serve as the housing for a configuration module. This sections lists configuration module assemblies for new and existing GTN installations. Table 3-10. Configuration Module Wire Color Reference Chart Color Function P1001 Contact Red Vcc 65 Black Ground 64 Yellow Data 62 White Clock 63 NOTE The pin contacts supplied with the GTN configuration module are specifically made to accommodate 28 AWG wire.
Figure 3-6. Backshell Assembly (Potted Configuration Module) GTN 6XX/7XX AML STC Installation Manual Page 3-24 190-01007-A3 Rev.
3.6.3.2.2 Configuration Module Assembly with Spacer (existing installations) NOTE Configuration module assembly P/N 011-00979-00 may not be available for new GTN installations. For new GTN installations, refer to Section 3.6.3.2.1. Table 3-12.
Figure 3-7. Backshell Assembly (Configuration Module with Spacer) GTN 6XX/7XX AML STC Installation Manual Page 3-26 190-01007-A3 Rev.
3.6.4 GTN Fan Installation CAUTION To avoid damage to the GTN, take precautions to prevent Electro-Static Discharge (ESD) when handling the GTN, connectors, fan, and associated wiring. ESD damage can be prevented by touching an object that is of the same electrical potential as the GTN before handling the GTN itself. Table 3-13 lists part numbers for the Fan Kit which is used with P1001 only. Table 3-13.
1 2 3 Do not use 3 tapped holes on shield block above the fan. There is insufficient clearance between the fan casing and terminal lugs. Wrap fan wires with fusion tape separately from the main harness to prevent the fan wires from being dislodged or damaged if there is movement between the main harness and the fan harness. Ensure the fan wires do not exceed a length of 8 inches. Figure 3-8. Fan Wiring Installation GTN 6XX/7XX AML STC Installation Manual Page 3-28 190-01007-A3 Rev.
3.6.5 TVS, Fuse and Resistor Installation (nonmetallic aircraft only) This section applies to IFR, nonmetallic aircraft only. VFR, non-metal aircraft do not require the use of TVSs or fuses. Certain nonmetallic aircraft will require TVSs at the main and NAV power inputs of the GTN. Refer to Appendix G to determine which aircraft require them. Refer to Section 2.3.2.4 for TVS component part numbers. 3.6.5.1 TVS/Fuse Installation NOTE Only TVS1/F1 are installed as described below.
Figure 3-9. TVS/Fuse Installation (TVS1/F1) 3.6.5.1.1 TVS2 Assembly (Nonmetallic Aircraft Only) Certain nonmetallic aircraft will require a TVS assembly at the power bus that supplies power to the GTN (refer to Appendix G to determine which aircraft require them). Refer to Section 2.3.2.4 for component part numbers. Refer to Figure E-4 for interconnect drawings that show the TVS installed. SOCKET CONTACT CRIMP & SOLDER 0.5" Max Figure 3-10.
3.6.5.1.2 TVS2 Fabrication 1. Cut the TVS leads to 0.75+0.00/-0.10 inches on both sides. 2. Crimp and solder each of the four TVS banded side (cathode) leads to their connector specific sockets (refer to Figure 3-10), and insert into the 4-pin connector with sockets. 3. Install heat shrink around the four TVSs – this will help to hold them in place during the following steps. 3.6.5.1.3 TVS2 Assembly Build Refer to Figure 3-11 while completing the following steps. 1.
3.6.6 Coaxial Cable Termination Follow the steps below for installation of coaxial cables: 1. Route the coaxial cable to the radio rack location, keeping in mind the recommendations above. Secure the cable in accordance with AC 43.13-1B Chapter 11, Section 11. If overbraid is required on the GPS antenna coaxial cable, refer to Figure 3-1. 2. Trim the coaxial cable to the desired length and install the TNC or BNC connectors per the cabling instructions in Figure 3-12 below.
3.6.7 Marker Beacon Antenna Cable Termination This section provides guidance for terminating the coaxial cable into the D-Sub connector. See Appendix F for pin assignments. RG-400 coaxial cable is recommended for the marker beacon antenna. Since RG-400 is too thick to fit through the backshell strain relief, RG-179 or RG-188 may be used instead. Route the cable to the D-Sub as described in Section 2.4.11.
3.6.8 Instrument Panel Bonding Procedure If the instrument panel is electrically isolated from the aircraft structure, additional bonding may also be required for the installation. A copper bonding strap with cross sectional area greater than 0.016 sq inches (approx 20816 circular mils) is required. A 7/16-inch or wider QQ-B-575B (24120 circular mils) overbraid meets this requirement. The strap length should be as short as possible and must not exceed six inches in length.
3.6.8.1 Attaching Bonding Strap to Tubular Structure A tab may be welded to the tubular structure, or a conductive clamp may be used with the following limitations. Complete the installation using the following procedures along with the guidance in AC 43.13-2B, Acceptable Methods, Techniques, and Practices - Aircraft Alterations, AC 43.13-1B, Acceptable Methods, Techniques, and Practices – Aircraft Inspection and Repair, and aircraft make/model specific structural repair documentation, as indicated.
3.7 Electrical Load Analysis A complete electrical load analysis (ELA) must be completed on each aircraft prior to installation to verify that the aircraft electrical system is capable of supporting the GTN and optional GMA 35.
3.7.2 Aircraft without Existing Electrical Load Analysis Prior to undertaking a complete electrical load analysis, the net change to the electrical load resulting from the GTN installation should be determined (refer to Figure 3-14 for a sample calculation). The results of this analysis will determine how to proceed further. Items removed from aircraft: Electrical Load (A) [1] GNS 530W (Main Connector) GNS 530W (Com Connector) 1.4 A 0.015 A GNS 530W (NAV Connector) PMA 7000M Subtotal: 0.5 A 2.5 A 4.
3.7.3 Performing an Electrical Load Analysis by Measurement NOTE According to FAR 23.1351(a)(2)(ii), performing an ELA using electrical measurements is not acceptable for commuter category airplanes. If the installation of the GTN/GMA 35 increases the overall load, an electrical load analysis must be performed. Due to the age of much of the equipment, adequate information regarding the current draw of this equipment may not exist.
CAUTION To avoid damage to equipment, ensure that the ammeter is capable of handling the anticipated load. 5. Insert/attach the calibrated ammeter in the line from the external power source to the master relay circuit as shown in Figure 3-15 (this will eliminate errors due to the charging current drawn by the battery). EXTERNAL POWER ALTNTR ELECTRICAL BUS + BATTERY - MASTER RELAY Ammeter placement – either location acceptable (does not include battery charging current) Figure 3-15.
CAUTION The pitot heat should only be switched on long enough to take the current measurement and then switched off. The pitot probe may get hot so care should be exercised to avoid burns or damaging the unit. 11. Using the tabulation completed above, switch on all continuous electrical loads used in the normal takeoff/landing phase and record ammeter current reading. Measurements must be taken with the landing lights ON and OFF (measurements (b1) and (b2) in Figure 3-16). 12.
Date: ______________ Electrical Load Measurement Tail No.:______________ Normal Operation Circuit/ System Circuit Breaker No.
Date: ______________ Electrical Load Measurement (cont’d)Tail No.:____________ Normal Operation Circuit/ System MEASURED VALUE Circuit Breaker No.
Date: 1/6/2010 Circuit/ System Alternator Field Annunciator Panel Vacuum Warning Stall Warning Gear Warning Gear Actuator Cluster Gage Ignition PFD Turn Coordinator Gear Relay ADC Panel Lights Glareshield Lights AHRS Flap Actuator Com 1 GPS/NAV 1 Com 2 GPS/NAV 2 Autopilot Audio Panel Radio Blower ADF Transponder GDL 69 TCAD JPI Engine Monitor Bose Headsets Altitude Encoder Strobe Light Nav Lights Recognition Lights Landing Light Pitot Heat Elevator Trim Boost Pump Electrical Load Measurement Circuit Brea
Date: ______________ Tail No.:______________ Power Sources Item Number Installed Voltage (DC Volts) Manufacturer Model Number Alternator Battery Battery Capacity: x 0.75 (derating factor) = ________ Ah x 60 min = ________ A-min [i] Current drawn during Normal Cruise (amps): ________ (c) enter current calculated in step 13. above Cruise consumption during recognition: (c) A x 5 min = ________ A-min [ii] Emergency Landing Current (amps): _________ (e) enter current measured in step 15.
Date: 1/6/2012 Tail No.: N5272K Power Sources Item Number Installed Voltage (DC Volts) Manufacturer Model Number Alternator 1 13.75 Prestolite AL 12-P70 Battery 1 12 Gill G-35 Battery Capacity: 35 x 0.75 (derating factor) = 26.25 Ah x 60 min = 1575 A-min [i] Current drawn during Cruise (amps): 43.5 (c) enter current calculated in step 13. above Cruise consumption during recognition: (c) 43.5 A x 5 min = ___217.5__ A-min [ii] Emergency Landing Current (amps): ____48.
3.8 3.8.1 AFMS Completion System Capabilities Section 1.2 of the AFMS contains a list of system capabilities of the installed GTN system and associated navigation interface. This section contains six options in the Airplane Flight Manual Supplement for Garmin GTN 6XX/7XX GPS/SBAS Navigation System (P/N 190-01007-A2) and three options ([1], [2], and [5]) in the VFR GPS Limited Airplane Flight Manual Supplement for Garmin GTN 6XX/7XX GPS/SBAS Navigation System (P/N 190-01007-A5).
3.8.2 Autopilot Listed in GTN 6XX/7XX AML STC For all autopilots listed in Section C.4, the appropriate limitations for that autopilot are identified in Table 3-15 and described in the paragraphs following the table. Table 3-15. Autopilot Coupling Limitations Honeywell (Bendix/King) Century Sperry AFMS Section 4.
AFMS Section 2.11 Autopilot Coupling Limitations This section of the AFMS contains one possible limitation: [a] Lateral coupling only for GPS approaches. Coupling to the vertical path for GPS approaches is not authorized. For all autopilots covered by the GTN 6XX/7XX AML STC, no limitations apply in this section and none should be checked on the AFMS. This section is not included in the VFR GPS Limited Airplane Flight Manual Supplement for Garmin GTN 6XX/7XX GPS/SBAS Navigation System (P/N 190-01007-A5).
For all autopilots that are not listed in the GTN 6XX/7XX AML STC, select the appropriate check box as follows: Box [1] is checked for any installation that meets all of the following criteria: • The GPS SELECT discrete is set to ‘Prompt’ on the Main System Config Page (refer to Section 5.5.1.9). NOTE The 6XX/7XX GPS SELECT discrete output is connected to the GPS Select input (or equivalent) on the autopilot. This input is used by the autopilot to determine if the navigation source is GPS or VLOC.
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4 CONNECTOR PINOUT INFORMATION 4.1 GTN 6XX/7XX 4.1.
4.1.
4.1.
4.1.
4.1.
4.2 GMA 35 4.2.
4.2.
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5 SYSTEM CONFIGURATION AND CHECKOUT 5.1 System Configuration Overview This section contains instructions for configuring the GTN for each installation as well as checks to ensure the system is properly installed and functioning correctly. The steps that are not applicable to a particular installation may be skipped. A checkout log that is included in Table 5-66 at the end of this section should be filled out during the checkout procedures.
5.2 Mounting, Wiring, and Power Checks Verify that all cables are properly secured and shields are connected to the shield block of the connectors. Check the movement of the flight and engine controls to verify there is no interference between the cabling and control systems. Ensure that all wiring is installed in accordance with Section 2.4.11. Prior to powering up the GTN, the wiring harness must be checked for proper connections to the aircraft systems and other avionics equipment.
5.4 Software Loading NOTE Prior to installing a version of the GTN main board software that is older than the currently installed version, all RS-232 and ARINC 429 ports should be set to Off. NOTE Screenshots in this section are provided for reference only. For actual GTN software versions, refer to the GTN 6XX/7XX AML STC Equipment List, 005-00533-C1. The GTN comes pre-loaded with software.
5.4.1 GTN Software Loading 1. Remove power from the GTN by opening the circuit breaker. 2. Insert the correct GTN Software Loader Card into the SD card slot. See Section 2.3.3 for instructions on how to create a loader card. 3. Restore power to the GTN by closing the circuit breaker. 4. The Configuration Mode home page, shown in Figure 5-1,should now be displayed. Touch Updates to display the software updates that are available. 5.
5.4.2 GMA 35 Software Loading Before attempting to load software to the GMA 35, the GTN RS-232 port to which the GMA 35 is connected must be configured for ‘GMA Format 1’. See Section 5.5.1.2 for more information. 1. Remove power from the GTN by opening the circuit breaker 2. Insert the correct GMA 35 Loader Card into the GTN 7XX SD card slot. See Section 2.3.3 for instructions on how to create a loader card. 3.
5.4.4 GWX 68/70 Software Loading This STC does not cover the installation of the GWX 68/70 or its software. To install software on the GWX 68/70, use the GWX Install Tool. Refer to the GWX 68 Installation Manual, P/N 190-00286-01 or the GWX 70 Installation Manual, P/N 190-00829-01. 5.4.5 GDL 88 Software Loading Although the GTN is a portal to install software for the GDL 88, this STC does not cover the installation of the GDL 88 or its software. Refer to the GDL 88 Installation Manual, P/N 190-01310-00. 1.
5.5 Configuration Mode Operations NOTE A Garmin transponder (GTN 32/327/328/33/330) controlled by the GTN will reboot into the same mode as the controlling GTN; i.e., if the GTN boots into configuration mode, the transponder will also boot into configuration mode. Before configuring the GTN, ensure that no Configuration Module service messages are displayed in the message queue. This would indicate that the configuration module is improperly wired or damaged.
5.5.1 GTN Setup Page The following sections describe pages that are accessed from the main GTN Setup page, as shown in Figure 5-4 A and B. To access the GTN Setup page, touch the GTN Setup key from the Configuration Mode home page as shown in Figure 5-1. The UPDATE CONFIG MODULE key stores the current installation-specific configuration information in the configuration module. Updating the configuration module is done automatically, so this key will not normally need to be touched. B. GTN 7XX A.
5.5.1.1 ARINC 429 Configuration Page To access the ARINC 429 Configuration page, shown in Figure 5-6, first access the GTN Setup page from the Configuration Home page, shown in Figure 5-4 above, by touching GTN Setup key. Then touch the ARINC 429 key. This page allows configuration of the ARINC 429 input ports and the ARINC 429 output ports. Select the correct speed for each port depending upon the installed interfaced equipment by touching the speed key and toggling the high or low selection.
Table 5-2. ARINC 429 DATA IN Selections Selection GNS Equivalent Description Off Off No unit(s) connected to this ARINC 429 input Notes Altitude, temperature, and speed information from the following Air Data systems: Airdata Airdata Airdata/AHRS Airdata/AHRS Heading, altitude, temperature, and speed information from Air Data/AHRS systems. This interface is not used in this STC Data Concentrator Garmin GTX 330 This is a Garmin data concentration format.
Selection GNS Equivalent Traffic Format 3 Traffic Advisory Traffic Format 4 Traffic Advisory Traffic Format 5 Traffic Advisory Traffic information from the following traffic systems: Traffic Format 6 Traffic Advisory Traffic information from the following traffic systems: [1] [2] [3] [4] [5] Description Notes Traffic information from the following traffic systems: • Skywatch HP SKY899 [5] Traffic information from the following traffic systems: • • • • Bendix/King KTA 870/970 Bendix/King K
NOTE Refer to GTN 625/635/650 TSO Installation Manual, P/N 190-01004-02 and GTN 725/750 TSO Installation Manual, P/N 190-01007-02 for information about ARINC 429 labels. Table 5-3. ARINC 429 DATA OUT Selections Selection GNS Equivalent Description Off Off No unit(s) connected to ARINC 429 output ARINC 429 ARINC 429 Standard ARINC 429 output data (non-GAMA).
NOTE Only one ARINC 429 output port can be configured to a GAMA Format output at one time. If more than one interfaced system requires a GAMA Format output, splice the GAMA 429 output wires from the GTN into each system requiring GAMA Format information. Table 5-4. SDI Selections 5.5.1.2 Selection Description Common RX: Accepts all ARINC 429 inputs TX: Generates all ARINC 429 outputs with SDI = 0. LNAV 1 Number 1 (Pilot) long-range navigator RX: Accepts 429 inputs with SDI = 0 or 1.
NOTE Refer to Appendix C for approved third party equipment interfaces to the GTN. If the equipment and interface selections described below are not listed in Appendix C, other FAA approval is required for that interface. Table 5-5. RS-232 Channel Input Selections Selection GNS Equivalent Description Off Off No unit(s) connected to input of this channel.
GNS Equivalent Description Notes N/A Select this format for the GTX 32/327 transponder #2. Provides status data, and flight ID. Choosing this input setting will automatically configure the corresponding channel output to the same setting. [4] N/A Select this format for the GTX 33/33ES/328/330/330ES transponder #1. Provides status data, ICAO address, and Flight ID. Choosing this input setting will automatically configure the corresponding channel output to the same setting.
Selection GNS Equivalent Description Notes Panel GTX w/TIS #2 N/A Select this format for the GTX 330/330ES transponder #2. This provides TIS data from the panel mount GTX 330/330ES transponder without controlling the transponder via the GTN. [4] Panel GTX w/TIS+ #2 N/A Select this format for the GTX 330ES transponder #2 with GTX software version 7.01 or later for AC 20-165 compliance.
Table 5-6. RS-232 Channel Output Selections Selection GNS Equivalent Description Off Off No unit(s) connected to output of this channel. ADS-B Serial communication of GPS data to Garmin panel mount mode S transponders. Note: This format is not required when using any other GTX output format. [1] ADS-B [1] [7] N/A Serial communication of GPS data to Garmin panel mount mode S transponders with GTX software version 7.01 or later for AC 20-165 compliance.
Selection GNS Equivalent Description Notes N/A Control of GTX 33ES/330ES #1 transponder functions, pressure altitude data, groundspeed data, and TIS traffic. For use with GTX software version 7.01 or later for AC 20-165 compliance. [1] [7] GTX w/TIS+ #1 GTX w/TIS #2 N/A Control of GTX 33/33ES/330/330ES #2 transponder functions, pressure altitude data, groundspeed data, and TIS traffic.
5.5.1.3 HSDB Ethernet Configuration Page The HSDB Ethernet configuration page can be accessed from the GTN Setup page. To configure each Ethernet port, touch the key next to the port to configure it as Connected or Not Connected. See Figure 5-7. If a Garmin LRU is connected to a specific Ethernet port, then configure the port as Connected. If no LRU is connected to the port, configure it as Not Connected. Figure 5-7. HSDB Ethernet Port Configuration Page 190-01007-A3 Rev.
5.5.1.4 Interfaced Equipment Configuration Page To access the Interfaced Equipment configuration page, touch the Interfaced Equipment key from the GTN Setup page, as shown in Figure 5-8 . This page configures which LRUs are installed and interfaced to the GTN. From the available list of LRUs, select either Present or Not Present. The Transponder Interfaced Equipment configuration should be prepopulated when the RS-232 data format is selected for each RS-232 channel. 5.5.1.4.
5.5.1.4.6 GSR 56 Select either Present or Not Present. In installations with multiple GTNs, this selection must be the same on all GTNs. 5.5.1.5 Main Indicator (Analog) Configuration Page Select the Main Indicator (Analog) Configuration Page, shown in Figure 5-9, from the GTN Setup page. This page allows you to calibrate the OBS resolver, configure the CDI key, selected course for GPS and VLOC, as well as the V-Flag state. Configurable fields are described below.
Table 5-8. VLOC Selected Course Selection Description Allowed (Default) Select if it is desired to allow a selected course input from the analog resolver or ARINC 429 for VLOC operation in OBS mode. Ignored Select if it is desired to ignore a selected course input such that the VOR valid flag is dependent only on a valid VOR signal, with lateral deviation calculated by another display device. Table 5-9.
5.5.1.6 Lighting Configuration Page From the GTN Setup page shown in Figure 5-4 above, select the GTN Lighting Configuration page, shown in Figure 5-10 page allows you to set display parameters that affect the display backlight and key lighting brightness. Fields listed in Table 5-10 are adjusted separately for both the Display and Key lighting features. The display source can only be configured to track the photocell or lighting bus 1. The display source cannot be configured to track lighting bus 2.
Minimum Level This sets the minimum brightness of the keys or display. Touch the ‘Minimum Level’ key corresponding to either the Keys or the Display to adjust the minimum brightness. The minimum brightness level can be adjusted in a range from 0.05% to 100.00% when tracking the lighting bus, and from 0.14% to 100.00% when tracking the photocell, with 100.00% being the maximum brightness level. The default minimum display brightness level when tracking the lighting bus is 0.05%.
Lighting Bus Source To configure the lighting bus source voltage, touch the Lighting Bus 1 or Lighting Bus 2 key. Select 14V DC, 28V DC, 5V DC, or 5V AC, depending on the lighting bus voltage source. 5.5.1.7 Audio Configuration Page The Audio Configuration page allows the adjustment of Alert audio volume. See Figure 5-12. Adjust Alert volume by touching the + or - signs to decrease or increase the volume accordingly.
5.5.1.9 Main System Configuration Page Select ‘Main System’ from the GTN Setup page. This page displays miscellaneous configuration options as described below. Air/Ground Threshold The air/ground threshold is the groundspeed at which the GTN transitions from a ground state to an airborne state, and vice versa. To adjust the air/ground threshold, touch the key to the right and enter a value. This field has a range of 0 to 99 knots and is set to 30 knots as a default value.
Figure 5-15. Measurement of GPS Antenna Vertical Offset Table 5-12 . Fuel Type Selection Description AV gas (Default) The aircraft burns Aviation gas (5.8 lbs./gal.) Jet A The aircraft burns Jet A or Jet A-1 fuel (6.7 lbs./gal.) Jet B The aircraft burns Jet B (JP-4) fuel (6.5 lbs./gal.) Table 5-13. Synchro Heading Input (GTN 7XX Only) Selection Description Connected A Synchro heading source is connected to the GTN 7XX.
Heading Source Input (software version 3.00 or later) When upgrading from GTN software version 2.00 to 3.00, this setting defaults to ‘Connected’. If a nuisance heading lost message appears a few minutes after power up and no heading source is present, configure this setting to 'Not Connected'. Table 5-15. Heading Source Input Selection Description Connected (Default) A heading source is connected to the GTN. Not Connected A heading source is not connected to the GTN.
5.5.1.10 COM Configuration Page (GTN 635/650/750 Only) Select the COM Configuration page, shown in Figure 5-16, from the main GTN Setup page, shown in Figure 5-4 above. These values are set at the factory and rarely require calibration. To enable or disable the COM radio, touch the key to toggle between Enabled and Disabled. The COM radio defaults to the enabled state. COM RF Squelch This setting configures the RF squelch threshold for the COM radio. This field may be set to any value between 0% and 100%.
5.5.1.11 VOR/LOC/GS Configuration Page (GTN 650/750 Only) Select the VOR/LOC/GS key from the GTN Setup page by touching the key on the display shown in Figure 5-4 above. This page allows you to verify the CDI outputs from the VOR/LOC/GS receiver as well as the OBS resolver input to the VOR receiver. It also allows you to select the format for the DME tuning data. NAV Radio To enable or disable the NAV radio, touch the key to toggle between Enabled and Disabled. The NAV radio defaults to the enabled state.
DME Channel Mode This configuration setting allows you to set the format for DME tuning data output. Table 5-21. DME Channel Mode Selection Description King serial King Serial DME tuning data Parallel 2x5 2 of 5 parallel DME tuning. Parallel BCD Shifted BCD (Binary Coded Decimal) parallel DME tuning Parallel slip Slip-code parallel DME tuning 2 of 5 parallel DME tuning, compatible with the following DME units: Narco 890/891 • Narco DME 890 • Narco DME 891 5.5.1.
5.5.2 GTN Options Configuration Page Access the GTN Options configuration page, shown in Figure 5-18, by touching the GTN Options key on the Configuration Mode page. This page allows optional purchased features to be enabled. All optional features are activated using the GTN Options Configuration Page. NOTE The feature unlock card should be provided to the customer after the GTN installation. 5.5.2.
5.5.2.1.1 TAWS Audio Configuration (Only if TAWS is Enabled) From the TAWS page in the GTN Options page group, touch the Configure TAWS Audio key. This page, shown in Figure 5-20, allows configuration of TAWS Audio. For each audio alert, select the desired audio text, as described in the following tables. 5.5.2.1.1.1 Figure 5-20. TAWS Audio Configuration Page Caution Fields Table 5-22.
Table 5-26. ROC-CAUTION Field Selection Description Caution, Obstacle (2x) Sets the Forward Looking Terrain Clearance (FLTA) Reduced Required Obstacle Clearance (ROC) cautionary alert to the specified text. (Default) Obstacle Ahead (2x) Sets the Forward Looking Terrain Clearance (FLTA) Reduced Required Obstacle Clearance (ROC) cautionary alert to the specified text. Table 5-27.
Table 5-31. ITI-WARNING Field Selection Description Terrain Ahead, Pull-Up (2x) Sets the Forward Looking Terrain Clearance (FLTA) Imminent Terrain Impact (ITI) warning alert to the specified text. (Default) Terrain (2x); Pull-Up (2x) Sets the Forward Looking Terrain Clearance (FLTA) Imminent Terrain Impact (ITI) warning alert to the specified text. Table 5-32.
5.5.2.1.2 Airport Criteria Configuration For installations of the GTN with TAWS enabled, the GTN provides aural and visual terrain alerts. The alerting algorithm adapts the terrain alerting criteria based on nearby airports. The GTN must be configured to specify the minimum criteria that an airport must meet to be considered as a nearby airport for the purpose of TAWS/Terrain alerting. For installations with TAWS enabled, obtain the information listed in Table 5-35. Figure 5-21.
5.5.2.2 Charts (GTN 7XX Only) The GTN 7XX can display Jeppesen charts using the optional ChartView feature, which must be activated. To configure which Charts to display, touch either None, FliteCharts, or ChartView. If ChartView is selected, it must be enabled as described below. NOTE The ChartView Enablement Card can only be used on one GTN (for dual GTN installations a separate ChartView Enablement Card must be used on each GTN). 1. Turn the GTN off by pulling the circuit breaker. 2.
5.5.2.3 COM Transmit Power When the optional 16W COM power is configured, the GTN COM will transmit with 16 watts rather than the standard 10 watts. 16W COM transmit power should be enabled for aircraft certified to fly above FL180. This section describes how to enable the 16W COM transmit power. NOTE The 16W COM Enablement must only be used in 28V installations. NOTE The 16W COM Enablement Card can only be used on one GTN (for dual GTN installations a separate Enablement Card must be used on each GTN).
5.5.2.4 Digital Radar (GTN 7XX Only) This section describes how to enable the Digital Radar feature, which allows approved ARINC 708 Weather Radars to be interfaced with the GTN 7XX. NOTE The Digital Radar Enablement Card can only be used on one GTN (for dual GTN installations a separate Digital Radar Enablement Card must be used on each GTN). 1. Turn the GTN off by pulling the circuit breaker. 2.
5.5.2.6 Flight Simulator The Flight Simulator enablement is used to support GTN use in flight simulators. Selection of this setting is not approved under this STC. 5.5.3 GTN Diagnostics Page The GTN Diagnostics page, shown in Figure 5-25, is accessed from the Configuration Mode Home page and is a useful tool for diagnosing issues and troubleshooting problems that arise during installation. Ground checks are also performed using the tools in this page.
5.5.3.6 Main Indicator (Analog) The Main Indicator diagnostics page allows the CDI connected to the main board (P1001) to be ground checked and allows the interface to be verified. For the Main Indicator checkout procedure, see Section 5.6.1. 5.5.3.7 Analog Inputs The analog inputs diagnostics page displays the bus voltage setting for Lighting Bus 1 and Lighting Bus 2 as well is the input voltage setting for each bus.
5.5.4 External Systems Configuration The following section contains procedures for configuring remote-mount units that are connected to the GTN. To configure external systems using the GTN, touch the External Systems key from the main configuration Home page. 5.5.4.1 GDL 69/69A Configuration If installed, the GDL 69/69A must be configured to match the installation. Follow the steps below. 1. Go to the GDL 69/69A configuration page.
5.5.4.2 Stormscope Configuration NOTE The Stormscope pages are only available if the WX-500 is connected to the RS-232 channel that is configured for the WX-500. Select the Stormscope configuration page from the External Systems page, shown in Figure 5-26. The L-3 Communications WX-500 Stormscope configuration is reported by the WX-500 through RS-232 data. To display the Stormscope configuration information, touch the Configure key.
5.5.4.3 Stormscope Test Page To access the Stormscope Test page, shown in Figure 5-29, select the Stormscope Test key from the Stormscope page, shown in Figure 5-27 above. This page shows current strike activity, WX-500 status, and the heading supplied by the WX-500. The WX-500 mode may be changed to Cell, Strike, Noise, Strike Test, Self Test, and Demo. The strikes can be cleared from the display by touching the Clear Strikes key. The view can be changed by touching either the 360˚ key or the Arc key.
5.5.4.5.1 Ryan TCAD For Ryan TCAD, the Traffic Test page displays the following data: • • • Current shield mode Altitude filter-Normal, Above, Below, and Unrestricted Barometric pressure By touching Menu, the traffic menu can be displayed. Under Traffic Audio, the mute duration (9900B only) and traffic audio volume can be set and the TCAD can be toggled between voice and tone alerts. Under Shield Setup, the shield settings can be configured for the various shield types.
5.5.4.6 GAD 42 Configuration The GAD 42 can be configured by the GTN if an ARINC 429 input is connected to the GAD 42. To configure the GAD 42, select the External Systems page group and then touch the GAD 42 key. The GAD 42 configuration page allows remote configuration of the GAD 42 Interface Adapter Unit. For details on how to configure the unit, see Chapter 5 of the GAD 42 Installation Manual, P/N 190-00159-00. Figure 5-31. GAD 42 Configuration Page 5.5.4.
5.5.4.7.1 Transponder Inputs and Outputs Access the transponder inputs and outputs page, shown in Figure 5-33 by touching the Inputs and Outputs key from the Remote XPDR configuration page. The transponder RS-232 channel inputs can be configured by the GTN. RS-232 channel 1 input for the transponder can only be set to Remote, and is the default for channel 1 input. RS-232 channel 1 is used for control and remote configuring of the transponder. 5.5.4.7.1.
Table 5-38. RS-232 Channel 2 Inputs Selection Description OFF DEFAULT. The altitude code input is not from an RS-232 source. Airdata Format 1 RS-232 serial air data information from Shadin ADC 200, 200+, 2000 plus altitude data. This input is the same as ‘ADC W/ALT’ in the GTX 330. Airdata Format 2 RS-232 serial air data information from Shadin ADC 200, 200+, 2000. This input is the same as ‘ADC no ALT’ in the GTX 330. Altitude Format 1 RS-232 serial altitude from an Icarus Instruments 3000.
Baud Rate Selection Select the baud rate for each RS-232 channel. Table 5-40. RS-232 Baud Rate Selections Selection Description 9600 Sets the baud rate to 9600 Bd. 19200 Sets the baud rate to 19200 Bd. 28800 Sets the baud rate to 28800 Bd. 38400 Sets the baud rate to 38400 Bd. 57600 Sets the baud rate to 57600 Bd. Parity Selections Select the parity for RS-232 channel 2. Table 5-41. RS-232 Parity Selections Selection Description Even Parity Sets the Parity to Even.
ARINC 429 Input Selections Select the correct Data In and Data Out settings for each port. The data selections are described below. Table 5-43. ARINC 429 Input Selections Channel Selection Description All OFF No unit connected to this ARINC 429 input GPS Selected waypoint information and GPS groundspeed recognition.
Table 5-45. Air Data Computer (ADC) Labels Label Data 203 [1] Pressure Altitude (feet) 204 Barometric Corrected Altitude (feet) 205 Mach Number 206 Indicated Air Speed (knots) 210 True Air Speed (knots) 211 Total Air Temperature (degrees) 212 Vertical Speed (feet/min) 213 Static Air Temperature (degrees) [1] If ADC W/ALT or EFIS/ADC W/ ALT format selected. Table 5-46.
Table 5-47. GPS/FMS Navigation System (GPS) Labels Label Data 102 Selected Altitude (feet) 310 GPS Latitude (degrees) 311 GPS Longitude (degrees) 312 Groundspeed (knots) 313 Track Angle (degrees) Table 5-48. Garmin Display Labels Label Data 310 GPS Latitude (degrees) 311 GPS Longitude (degrees) 261 GPS Discretes 312 GPS Groundspeed (knots) 313 GPS Track Angle (degrees) 314 True Heading (degrees) 320 Magnetic Heading (degrees) Table 5-49.
ARINC 429 Output Selections ARINC 429 Channel 1 defaults to Off. ARINC 429 channel 2 defaults to Garmin w/ TIS. The GTX 33 can be configured to include GPS, Airdata, AHRS, EFIS/Airdata, and ADLP ARINC 429 input, functioning as an ARINC 429 data concentrator. Each output port can be configured independently for the desired function. Both ARINC 429 outputs send high speed ARINC 429 data. SELECTION DESCRIPTION • DATA SOURCE: OFF, ADLP, GARMIN, GARMIN TAS, or GARMIN W/TIS. CHANNEL 1 (DATA) • DEFAULTS to OFF.
The following data are sent out in packets approximately every 0.5 seconds at high speed (100 kHz), in the specified sequence. Table 5-52.
5.5.4.7.2 Transponder Installation Settings Page VFR Key Code Input a VFR transponder code by touching the key and typing the selected code into the keypad. This field has a range of 0000-7777. NOTE Exercise care when making routine code changes. Enter only valid VFR codes. Avoid using code 7500 and codes in the 7600-7777 range, as these codes trigger special indicators in automated facilities. Figure 5-34.
Air/Ground Logic Select the source for the air/ground logic. Table 5-54. Air/Ground Logic Selection Description Auto Airborne Off This is not a valid setting. Squat Switch The transponder is connected to a squat switch to determine airborne state. GPS Data The transponder is using GPS data to determine the airborne state. Only select this setting if a GTX input port is configured to GPS.
Flight ID Type (GTX 33 Only) Select the flight ID type. For operation requiring the flight crew to enter an aircraft identification designator, select the page identified as PILOT ENTRY. When this choice is selected and the crew enters the Flight ID correctly, the flight number call sign for radio contact with ATC is the same flight identification that the GTX 33 Mode S transponder replies to ATC radar interrogations. Table 5-57.
Surveillance Integrity Level (GTX 33 Only) This field sets the correct GPS Integrity for the interfaced GPS receiver. Set to 1E-3, 1E-5, or 1E-7. When interfaced to the GTN, the GPS Integrity must be set to 1E-5. NOTE The GPS INTEGRITY configuration field indicates the integrity of the GPS sensor that is connected to the transponder. It is measured in errors per flight hour, 1E-3 being the worst and 1E-7 being the best rating. This data is used in ADS-B transmissions.
5.5.4.8 5.5.4.8.1 GMA 35 Audio Panel Configuration (GTN 7XX Only) Audio Terminology The following terms will be used throughout the audio panel configuration sections and are defined here. ALERT - Unswitched inputs. These inputs are typically warnings, and there is no way for the user to deselect the audio. COPILOT - The second crewmember is considered the COPILOT. The copilot is typically the front right-seat for airplanes. CREW - Refers to aircraft occupants who can transmit on radios. i.e.
5.5.4.8.2 GMA 35 Audio Panel Settings NOTE When configuring volumes and squelches, keys can be touched and held to scroll quickly through values. To configure the audio panel, go to the External Systems page and touch the Audio Panel key to display the audio panel configuration page shown in Figure 5-36. On the main audio panel configuration page, there are two keys labeled Configure and Connected Radios.
5.5.4.8.2.1 Configuration Settings Mute PASS to CREW intercom during alerts This option mutes the passenger ICS audio to the crew during system alerts. Select True to mute passenger audio during alerts or select False to allow passenger audio to be audible to the crew during alerts. False is the default selection. Mute PASS to CREW intercom during selected audio This option mutes the passenger ICS audio to the crew during selected audio.
Audio Processor generates COM3 internal side tone Selecting True causes the audio panel to provide COM3 side tone. Selecting False allows the COM3 radio to generate its own side tone. False is the default selection. COM 1 is connected as COM 2 Select True if COM 1 is connected as COM 2, select false if COM 1 is connected as COM 1. False is the default selection. This setting allows the GTN 7XX to be connected to the COM 2 port, but appear to the pilot as COM 1. Refer to Section 2.4.
Alert 1 thru 4 input audio volume These settings allow the unswitched alert input audio to the GMA 35 to be adjusted. This setting is configurable from -96 to +96. The default is 0. Failsafe warn input audio volume This setting allows the failsafe warn audio input to the GMA 35 to be adjusted. This setting is configurable from -96 to +96. The default is 0. Marker volume This adjusts the marker beacon volume output to the crew headsets. This setting is configurable from -96 to +96. The default is 0.
5.5.4.8.2.4 Squelch Threshold Configuration Settings COM 1-3 Squelch Threshold These settings adjust the signal strength required to break squelch for each input. These are configurable from -96 dB to 0 dB. A value of 0 dB will require high signal levels to break squelch. Decreasing the value to -96 dB will allow squelch to be broken with low signal levels. The default value is -48 dB.
5.5.4.8.2.5 Other GMA 35 Configuration Settings Marker Beacon high sense threshold The marker high sensitivity threshold configures the marker beacon signal strength that is required to activate the marker beacon signal in marker high sense mode. This is adjustable from -31 to +31. A value of -31 will cause the marker beacon signal to activate at lower signal strength; therefore the beacon signal will remain active for a longer period of time while on approach.
For RCVR 3, RCVR 4, and RCVR 5, the type of radio must also be configured. For each connected RCVR source, select the type of radio. Selection Description ADF 1 An Automatic Direction Finder (ADF) is connected to the RCVR input. ADF 2 A second Automatic Direction Finder (ADF) is connected to the RCVR input. DME 1 Distance Measuring Equipment (DME) is connected to the RCVR input. DME 2 A second Distance Measuring Equipment (DME) is connected to the RCVR input.
5.5.4.9.1 Aircraft Configuration Page The aircraft page allows configuration of aircraft information and settings as shown in Figure 5-42. To access this page, touch External Systems → GDL 88 → Configuration → Aircraft. Figure 5-41. GDL 88 Aircraft Configuration Page 5.5.4.9.1.1 ICAO Address Enter the aircraft assigned ICAO address code, eight octal digits.
5.5.4.9.1.4 Aircraft Category This setting selects the aircraft emitter category for which the GDL 88 is installed. Select Light for aircraft with maximum gross weight less than 15,500. 5.5.4.9.1.5 Aircraft Length Enter the length of the aircraft. This field has a range of 1 to 300 feet. 5.5.4.9.1.6 Aircraft Width Enter the width (wingspan) of the aircraft. This field has a range of 1 to 300 feet. 5.5.4.9.1.
5.5.4.9.1.13 Air/Ground Discrete The GDL 88 AIR/GROUND discrete input is active-low, and can be configured to interpret whether the aircraft is airborne or on the ground based upon whether the input is grounded or open. If the GDL 88 AIR/GROUND discrete is not connected, then select Not Installed (default configuration). If the GDL 88 AIR/GROUND discrete connected, and the aircraft air/ground state is On-Ground when the input is grounded, the select Active for Ground.
5.5.4.9.2 Antenna Configuration Page The antenna page allows configuration of antenna settings as shown in Figure 5-42. To access this page, touch External Systems → GDL 88 → Configuration → Antenna. Figure 5-42. GDL 88 Antenna Configuration Page 5.5.4.9.2.1 UAT/1090 Antenna These settings control whether the GDL 88 antenna self tests are performed. If the Top UAT/1090 Antenna (GDL 88D models only) is of the DC grounded type, select Enabled, otherwise select Disabled.
5.5.4.9.2.3 External GPS/SBAS Source Antenna These settings indicate the horizontal placement of the external GPS source(s) GPS/WAAS antenna(s). External GPS #1 is the GPS source connected to GDL 88 Time Mark 1 If external GPS #1 is connected to the GDL 88, enter the external source’s GPS/WAAS antenna longitudinal offset distance rounded to the nearest foot from the nose of the aircraft, and the lateral offset as measured in feet (left or right, looking forward) from the centerline of the aircraft.
5.5.4.9.4 ARINC 429 Configuration Page This page allows configuration of the ARINC 429 input and output ports as shown in Figure 5-44. To access this page, touch External Systems → GDL 88 → Configuration → Ports and then select A429 at the top of the page. Refer to the GDL 88 Part 23 AML STC Installation Manual for approved third-party equipment interfaces to the GDL 88.
Table 5-59. ARINC 429 RECEIVE Selections Selection Description Off No unit connected to the ARINC 429 input. Same as Disabled in the GDL 88 Install Tool. Airdata #1 Select this format for the Air Data system, or the Air Data system #1 in a dual Air Data system installation. Provides altitude, airspeed, and altitude rate information. Airdata #2 Select this format for the Air Data system #2 in a dual Air Data system installation. Provides altitude, airspeed, and altitude rate information.
5.5.4.9.5 RS-232 Configuration Page This page allows configuration of the RS-232 input ports and the RS-232 output ports as shown in Figure 5-45. To access this page, touch External Systems → GDL 88 → Configuration → Ports and then select RS232 at the top of the page. Figure 5-45. GDL 88 RS-232 Port Configuration Refer to the GDL 88 Part 23 AML STC Installation Manual for approved third-party equipment interfaces to the GDL 88.
Table 5-62. RS-232 INPUT Selections Selection Description Disabled No unit connected to this RS-232 input. Airdata Format 1 Provides altitude, airspeed, and altitude rate information. Altitude Format 1 Provides altitude information. Altitude Format 2 Provides altitude information. Altitude Format 3 Provides altitude information. GNS 1 Provides GPS data and FIS-B requests. Same as GNS Series #1 in the GDL 88 Install Tool. GNS 2 Provides GPS data and FIS-B requests.
5.5.4.9.6 Ethernet Configuration Page This page configures which LRUs are installed on the GDL 88 Ethernet (HSDB) network. To access this page, touch External Systems → GDL 88 → Configuration → Ports and then select HSDB (Ethernet) at the top of the page. From the available list of LRUs, select either Enabled or Disabled as shown in Figure 5-46. Figure 5-46.
NOTE This setting should only be set to Enabled if the GTS 8XX is interfaced to the GDL 88 via Ethernet (HSDB) instead of ARINC 429 for traffic correlation. If the GTX 8XX is interfaced to the GDL 88 using ARINC 429, select Disabled. 5.5.4.9.7 GDL 88 Diagnostics The GDL 88 Diagnostics page is a useful tool for diagnosing issues and troubleshooting problems that arise during installation.
5.5.4.9.7.8 RS-232 Inputs The RS-232 Inputs diagnostics page allows the display of serial data that is being received and is useful for determining if the GDL 88 is receiving data on each connected port. To access this page, touch External Systems → GDL 88 → Diagnostics → RS232 Inputs. Select the desired port by touching the Port key and selecting the RS-232 channel from the list. The data log can be paused by toggling the Pause key. Clear the data log by touching Clear Log. 5.5.4.9.7.
Return Bins This setting specifies the number of range bins used to encode the data for one radar spoke. The default for this value is 600. 5.5.4.11.2 Roll Trim Configuration in Normal Mode Figure 5-47. Roll Trim Configuration in Normal Mode Use the following procedure to configure weather radar roll trim while flying (in normal mode). 1. Start the GTN in Normal Mode. 2. Touch Radar on the Weather page to bring up the radar display. 3.
5.5.4.11.3 ARINC 708 Weather Radar Configuration NOTE If a GWX weather radar is already configured, the key to configure an ARINC 708 weather radar will be disabled because the radar types are mutually exclusive. NOTE The Digital Radar option must be enabled before ARINC 708 weather radar can be configured, Refer to Section 5.5.2.4. As part of the wiring installation the GTN 7XX will be connected to the weather radar as display #1 or #2, and the GTN 7XX must be configured accordingly.
5.5.4.11.3.1 Honeywell (Bendix/King) 2XXX Series Radars This section describes Post-Installation System Configuration and Calibration of the Bendix/King RDR2000 and RDR-2100 Radar Systems using the GTN 7XX. The CM 2000 Configuration Module for the WXR must be configured using the Honeywell (Bendix/King) KPA 900 Configuration Module Programmer Kit (P/N 050-03311-0000) in conjunction with a personal computer. Refer to the configuration module programmer operator’s guide for detailed setup instructions.
Stabilization Calibration Perform the WXR stabilization calibration as follows: 1. Ensure that the radar is in calibration mode. 2. Note the Roll Trim value for re-entry following the stabilization calibration procedure. Adjust the Roll Trim field to 0.000. 3. Beginning with the step C in Section 2.3.6.3 of the RDS 81 Installation Manual (Honeywell P/N 006-00954-0001) or the RDS 82 Installation Manual (Honeywell P/N 006-00955-0006), perform the stabilization alignment in the aircraft. 4.
5.6 Ground Checks (Configuration Mode) The following checks are done in Configuration Mode. For instructions on entering Configuration Mode, see Section 5.5. 5.6.1 Main Indicator Check (Analog Only) NOTE If the GTN is interfaced to an electronic HSI/EFIS and the main indicator analog output is not used, this check is not required. If the GTN is interfaced to an analog indicator on the main CDI/OBS (P1001), perform the following steps: 1. Go to the GTN Diagnostics page. See Section 5.5.3. 2.
5.6.3 Discrete Inputs Checkout If the GTN is connected to any external switches, perform the following steps: 1. Go to the GTN Diagnostics page. 2. Go to the Discrete Inputs page, shown in Figure 5-48.. 3. For each external switch that is connected, exercise the switch source and check the ‘ACTIVE’ or ‘INACTIVE’ indication on the screen correlating to the appropriate input, and ensure it is displayed correctly. 4.
5.6.5 HSDB Wiring Checkout If HSDB wiring has been installed for other Garmin LRUs that interface via HSDB, follow the procedure below to ensure it has been installed and configured correctly. 1. Access the GTN Diagnostics page from the main Configuration Mode home page. 2. Touch the HSDB (Ethernet) key. The HSDB Diagnostics page, shown in Figure 5-50., will be displayed. 3. Ensure any LRUs connected via HSDB are powered on and properly configured. 4.
5.6.7 TAWS Audio Check (For Units with TAWS Only) NOTE The audio panel must also be powered on for the TAWS audio check The TAWS audio volume has an initial default of 80% of the maximum value. The TAWS volume needs to be set to ensure that aural alerts are audible under all anticipated noise environmental conditions. 1. Touch the Audio configuration page from the Main GTN Setup page. 2. Under ‘Alert Volume’, increase or decrease the volume by touching the + or - keys. 3.
5.6.9 Lighting Bus Interface Check The display and key backlighting on the GTN can track an external lighting/dimmer bus input and use it to vary the display and key backlight levels accordingly. This check verifies that the interface is connected correctly. CAUTION When 14 VDC or 28 VDC lighting buses are connected to the GTN, connection of the aircraft lighting bus to the incorrect input pins can cause damage to the GTN.
5.6.10 Air/Fuel Data Interface Check The GTN can receive fuel and altitude data from an external source. This check verifies that the GTN is receiving data from these sources. Ensure that the GTN is powered on and in configuration mode. If the following steps do not perform correctly, check the electrical connections (Appendix E) and configuration setup (Section 5.5.1.2) for the interfaced data source. 1. Go to the GTN Diagnostics page from the Configuration Mode Home page. 2.
5.7 Ground Checks (Normal Mode) For the following checks, cycle power on the GTN and power it up in normal mode. 5.7.1 Display of Self Test Data Following normal power-up, the Database pages are displayed, followed by the Instrument Panel SelfTest page. Touching Continue displays the Instrument Panel Self-Test page. During this time, the electrical outputs are activated and set to the values listed below. Touch ‘Continue’ to acknowledge the Instrument Panel Self-Test page.
5.7.2 Signal Acquisition Check NOTE All other avionics should be turned off at the start of this test, with the GTN powered on. Ensure the GTN is able to acquire sufficient satellites to compute a GPS position. From the Home page, touch the System key and then touch the GPS Status key. Under ‘GPS Solution’, ensure that a ‘3D Fix’ or ‘3D Diff Fix’ is obtained. If the unit is unable to acquire satellites, move the aircraft away from obstructions which might be shading GPS reception.
5.7.3 VHF COM Interference Check NOTE Interference checks must be completed on all IFR installations. Certain non-aviation radios, including marine transceivers, can interfere with civil aviation navigation and surveillance equipment including the Garmin GTN. When installing GTN equipment, it is the responsibility of the installer to ensure that the GTN modification is compatible with all previous aircraft modifications.
5.7.4 VHF NAV Checkout (GTN 650/750 Only) Touch the CDI key to select VLOC mode, which is indicated by a green ‘VLOC’ annunciation on the bottom center of the display. Check the VOR reception with ground equipment, operating VOT or VOR, and verify audio and Morse code ID functions (if possible). Tune a Localizer frequency and verify the CDI needle and NAV flag, and VDI needle and GS flag operation. 5.7.4.1 1. 2. 3. 4. 5. 6. 7.
5.7.6.2 Failsafe Operation Check 1. Power the GMA 35 off by pulling the GMA 35 circuit breaker. 2. Check the failsafe operation by exercising the COM1 microphone, microphone key and audio over the pilot’s headphones. NOTE Use of a true mono headset is required for this test to ensure proper wiring even if a stereo jack is provided in the installation. Wiring left channel (tip contact) and right channel (ring contact) backwards will cause failsafe mode not to function with mono headsets.
Depending on configuration settings, other transceivers may be muted during transmit. Also, the audio panel may mute the speaker during PTT. 4. Move the headset to the copilot’s headset jacks and verify that any one of the installed transceivers (testing each is not necessary) receives and transmits copilot mic properly as above. 5.7.6.4 NAV Audio Check Ensure the GMA 35 and each installed NAV receiver is powered on. 1. 2. 3. 4. 5. Tune the NAV receiver to a local VOR station.
5.7.6.7 Intercom System (ICS) Check NOTE If a monaural headset is plugged into any stereo phone jack position, no damage will occur to the GMA 35. In the case of plugging a monaural headset into any passenger position, any stereo listener will lose one channel when another passenger plugs in a monaural headset. 1. Place the audio panel into ALL ICS mode (refer to the GTN Pilot’s guide) so that all ICS positions hear all others. 2.
5.7.7 TAWS System Check (For Units with TAWS Only) While on the ground, turn on the GTN following normal power-up procedures. Also turn on the audio panel. NOTE A 3D GPS position fix is required to conduct this check. 1. 2. 3. 4. Select the Terrain page from the normal mode Home page. Touch the MENU key. Touch the Test TAWS key. Wait until the TAWS self-test completes (10-15 seconds) to hear the TAWS system status aural message.
5. Verify that the radar begins sweeping and the test pattern is shown. WARNING Aircraft should be outdoors and personnel should not be in front of the weather radar when it is radiating (i.e., when Weather or Ground mode is selected on the GTN). 6. If stabilization is supplied to the radar, turn the radar to Weather mode and turn stabilization on in the weather menu. Verify that STAB On is displayed in the upper right corner or the radar display.
5.7.8.2 GSR 56 Iridium® Check NOTE When testing the GSR 56, the aircraft must be located outside and have an unobstructed view of the sky. NOTE For additional information on using the GSR 56 features refer to the GTN 725/750 Pilot’s Guide, P/N 190-01007-03, or the GTN 625/635/650 Pilot’s Guide, P/N 190-01004-03. NOTE To use the position reporting feature of the GSR 56, a short burst data (SBD) Iridium account is required. To use the phone feature of the GSR 56, an Iridium voice account is required.
5.7.8.3 Honeywell (Bendix/King) EFS 40/50 Interface Check If a Honeywell EFS40/50 has been connected to the GTN, the interface should be verified as described in this section. 1. Cycle power to the first GTN and acknowledge the prompts until it gets to the Instrument Panel Self-Test page (see Section 5.7.1) 2. Ensure that GPS1 data is displayed by pressing the 1-2 key on the EFS40/50 control panel. 3.
5.7.8.4.2 Two GTNs/One SN3308 1. Remove power from GTN #2. 2. Cycle power to GTN #1 and acknowledge the prompts until it gets to the Instrument Panel SelfTest page (see Section 5.7.1). 3. Select GPS1 as the navigation source by pressing the NAV key on the SN3308. Verify that GPS1 is displayed on the SN3308. 4. Ensure that the SN3308 is receiving valid heading. NOTE The Vertical Deviation Indication will not be displayed unless the SN3308 is receiving valid heading. 5.
• 5. 6. 7. 8. 9. 10. 11. 12. 13. Vertical Deviation: Half-scale up deviation, flag pulled • Active Waypoint: GARMN On GTN #1 verify that an OBS value is displayed (and not dashed out). Acknowledge the self test on GTN #1 by touching the ‘Continue’ key. Select VLOC on GTN #1 and verify that the SN3308 displays NAV 1 or NAV 2 (depending on which navigation source the GTN is). Using a VOR test set verify that the CDI deviation on the SN3308 is displayed correctly.
5.7.8.7 EHSI Deviation Scaling for HSI/CDI Driven by GTN via ARINC 429 Data If the GTN has a serial connection to an EFIS display, proper scaling of the EFIS CDI and VDI must be verified. 1. Cycle power to the GTN and acknowledge the prompts until it gets to the Instrument Panel SelfTest page (see Section 5.7.1). 2. With the Instrument Panel Self-Test page displayed on the GTN, look on the EHSI/EFIS and verify that the lateral deviation is half-scale left and not flagged. 3.
5.7.8.10 GMX 200/MX20 Interface Check If a Garmin GMX 200 or MX20 has been connected to the GTN, the interface should be verified as described in this section. 1. Ensure that the GTN has a 3-D position fix. 2. Create and activate a flight plan on the GTN by touching the Direct-To key and entering a waypoint. 3. Verify that the RTE and POS data flags are not displayed on the GMX 200/MX20. 4. Verify that the flight plan is displayed on the GMX 200/MX20 using the flight plan (FPL) function. 5.7.8.
5.7.8.11.2 SiriusXM® Satellite Radio Audio Checkout Procedure The following steps only need to be completed for GDL 69A installations. 1. Go to the Music page from the Home page. NOTE If the SiriusXM Satellite Radio audio subscription has not been activated, audio is available only on Channel 1. If the audio subscription has been activated, audio should be available on multiple channels. 2. Ensure the GDL 69A audio is not muted. 3. Verify that audio can be heard over the headsets.
5.7.8.14 TIS (Garmin GTX 33/330) Interface Test If a Garmin GTX 33/330 sensor has been connected to the GTN, the traffic interface should be verified as described in this section. 1. Select the Traffic Map on the GTN. 2. Verify that TIS FAIL is not displayed in the upper left corner under Traffic Status, and that NO DATA (yellow) is not displayed over the ownship symbol. 3.
5.7.9 GDL 88 Interface Check When testing the GDL 88, the aircraft must be located outside and have an unobstructed view of the sky. If the GDL 88 is installed and connected to the GTN, check the operation as follows: 1. Start all GTNs in Configuration Mode. See Section 5.5. 2. Go to the GDL 88 page in the External Systems page group. 3. Touch Diagnostics and then GPS/SBAS Data. 4. Verify that the GDL 88 is receiving valid position source data. 5.
5.8 Flight Checks All GTN functions that cannot be adequately tested on the ground will require a flight check. Even if all functions can be verified on the ground, a flight check is required as final installation verification. Verify system operation as described in the following sections.
5.8.5 Autopilot Flight Check 1. Enter and activate a flight plan on the GTN. For the GTN 650/750, ensure that GPS is selected on the CDI. Engage the autopilot in the GPSS mode, if available. Verify that the autopilot flies the course. 2. Disengage the autopilot and fly off course. Re-engage the autopilot (in GPSS mode) and verify that it correctly intercepts the course and continues to fly it. 3. Turn off the autopilot GPSS but leave the autopilot engaged in NAV mode.
Table 5-65. Marker Beacon Annunciator Light Duration Groundspeed (Knots) Light Time (seconds) 2000 ft 3000 ft 90 13 20 110 11 16 130 9 14 150 8 12 If the marker beacon annunciator lights do not remain illuminated for the required time, adjust the marker beacon low sensitivity threshold as described in Section 5.5.4.8.2.5, and then repeat steps 1 and 2. 5.9 Database Check Check the navigation database to ensure it is current.
5.10 Documentation Checks 5.10.1 Airplane Flight Manual Supplement Ensure that the Airplane Flight Manual Supplement (AFMS) is completed and inserted in the Airplane Flight Manual (AFM) or Pilot’s Operating Handbook (POH). See Section 3.8 for information about completing the AFMS. 1. Fill in the required airplane information in the AFMS. 2. Fill in the appropriate checkbox in the Limitations Section of the AFMS corresponding to the autopilot coupling limitations.
Table 5-66. GTN Post-Installation Checkout Log Sheet 1 of 4 GTN Post-Installation Checkout Log Aircraft Model: Unit P/N: Unit Model: GPS Antenna P/N: INSTALLATION INFORMATION: Date: ____ /____ /____ By: ________________ Aircraft Serial #: Mod Level: Serial #: GPS Ant Model: CONNECTOR ENGAGEMENT (See Section 5.3) CONNECTOR ENGAGEMENT CHECK Connector engagement checked EXTERNAL BONDING REQUIREMENT (See Section 2.4.5) Metal/Tube and Fabric: Composite: Resistance less than or equal to 2.
Table 5-66.
Table 5-66.
Table 5-66. GTN Post-Installation Checkout Log Sheet 4 of 4 COMMENTS: GTN 6XX/7XX AML STC Installation Manual Page 5-114 190-01007-A3 Rev.
6 TROUBLESHOOTING Refer to System Maintenance Manual, GTN 6XX/7XX Part 23 AML STC, P/N 190-01007-A1, for troubleshooting information. 190-01007-A3 Rev.
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7 LIMITATIONS Limitations for specific aircraft models can be found in Appendix H. 7.1 7.1.1 Operational Limitations Operations There are no Part 23 aircraft type limitations. All functions of the GTN unit meet the appropriate primary or secondary design assurance qualifications for airplane Class I, Class II, Class III, and Class IV in accordance with AC 23.1309-1E Figure 2.
7.2.5 Rotorcraft Installation The installation and operational approval for use of a GTN and GMA 35 in rotorcraft is not authorized by the GTN AML STC SA02019SE-D; however, instructions and data provided in this manual may be applicable to the alteration. Installation of GTN and GMA 35 equipment in rotorcraft requires separate approval from the cognizant aviation authority. The GTN unit TAWS functionality is not approved for use in rotorcraft. 7.2.
8 PERIODIC MAINTENANCE For periodic maintenance refer to the GTN STC Maintenance Manual, P/N 190-01007-A1. 190-01007-A3 Rev.
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Appendix A Outline and Installation Drawings Figure A-1. GMA 35 Dimensions and Center of Gravity Figure A-2. GMA 35 Mounting Rack Assembly Overview Figure A-3. GTN 6XX Dimensions and Center of Gravity Figure A-4. GTN 650 Mounting Rack Assembly Figure A-5. GTN 7XX Dimensions and Center of Gravity Figure A-6. GTN 750 Mounting Rack Assembly Figure A-7. GTN 750 with GMA 35 Installation Dimensions and Center of Gravity Figure A-8. GTN 750 with GMA 35 Mounting Rack Assembly Figure A-9.
5.997 3.630 6.247 7.732 1.475 .880 1.162 1.516 1.012 .200 2 X 4.500 2 X 2.250 2 X .800 3 X 5.360 6.290 3.120 NOTES: 1. CG MEASURED WITH UNIT, RACK, BACKPLATE, AND CONNECTORS WEIGHT MODEL UNIT UNIT, RACK, BACKPLATE & CONNECTOR KIT GMA 35 1.4 lb [ .64 kg] 2.2 lb [1.00 kg] Figure A-1. GMA 35 Dimensions and Center of Gravity GTN 6XX/7XX AML STC Installation Manual Page A-2 190-01007-A3 Rev.
211-60234-08 SCREW, 4-40 X .250 1 5 115-01464-00 GMA 35 MOUNTING RACK 5 2 3 211-63234-11 SCREW, 4-40 X .437 125-00040-00 1 GMA 35 BACKPLATE 2 011-00950-02 BACKSHELL (2X) 011-01169-00 GROUND ADAPTER (4X) 330-00185-44 CONNECTOR (2X) 336-00021-00 PINS (A/R) 1 PART OF 011-02300-00 BACKPLATE KIT 2 PART OF 011-02302-00 CONNECTOR KIT 3 PART OF 010-00831-01 INSTALLATION KIT 4 SEE TABLE FOR KIT REFERENCE INFORMATION 5 TORQUE 4.5 – 5.
.894 [22.71] 6.250 [158.75] BEZEL 6.300 [160.02] RACK "A" 1.830 [46.48] "B" 10.410 [264.41] TO COAXES GTN 650 SHOWN 11.270 [286.26] TO D-SUB STRAIN RELIEFS .125 [3.18] .331 [8.41] TO .025 DIMPLES Ø.213 [Ø5.41] [Ø5.41] 100° CSK INSIDE RACK (5 PER SIDE) .985 [25.02] 2.640 [67.06] BEZEL 1.970 [50.04] .985 [25.02] .437 [11.10] 8.000 [203.20] 2.665 [67.69] TO .025" DIMPLES .364 [9.25] TO .025" DIMPLES NOTES: 1. DIMENSIONS: INCH [mm]. 2. CG MEASURED WITH UNIT, RACK BACKPLATE, AND CONNECTORS.
211-60234-08 SCREW, 4-40 x .250 (4X) 1 330-00053-01 BNC CONNECTOR 1 212-00022-00 SHOULDER WASHER 2 1 115-01293-00 GTN 6XX MOUNTING RACK 253-00421-00 CHASSIS GASKET 1 1 211-60234-23 SCREW, 4-40 X 1.375 (4X) 330-00053-01 BNC CONNECTOR 1 1 4 125-00220-10 GTN 6XX BACKPLATE 1 1 371-00013-01 FAN 117-00392-00 FAN SPACER (4X) 2 011-02325-0X CONNECTOR KIT NOTES: 1 PART OF 011-02245-00 (GTN 625, BLACK), 011-02245-01 (GTN 635, BLACK), AND 011-02245-02 (GTN 650, BLACK AND GRAY) KITS.
.892 [22.65] 6.300 [160.02] RACK 6.250 [158.75] BEZEL "A" 1.820 [46.23] "B" 10.410 [264.41] TO COAXES 11.264 [286.11] TO D-SUB STRAIN RELIEFS 1.000 [25.40] GTN 750 SHOWN .125 [3.17] 2.385 [60.57] Ø.213 [Ø5.41] 100° CSK INSIDE RACK (5 PER SIDE) 6.010 [152.65] TO .025" DIMPLES 6.000 [152.40] BEZEL 3.811 [96.80] 2.220 [56.39] 1.970 [50.04] "C" 8.000 [203.20] .349 [8.86] TO .025" DIMPLES NOTES: 1. DIMENSIONS: INCH [mm]. 2. CG MEASURED WITH UNIT, RACK, BACKPLATE, AND CONNECTORS. Figure A-5.
211-60234-08 SCREW, 4-40 x .250 (4X) 1 330-00053-02 BNC CONNECTOR 1 212-00022-00 SHOULDER WASHER 2 115-01294-00 GTN 7XX MOUNTING RACK 330-00053-02 BNC CONNECTOR 1 1 253-00421-00 CHASSIS GASKET 1 125-00221-10 GTN 7XX BACKPLATE 1 1 371-00014-01 FAN 117-00392-00 FAN SPACER (4X) 1 4 211-60234-23 SCREW, 4-40 X 1.375 011-02326-0X CONNECTOR KIT 2 1 1 PART OF 011-02246-00 (GTN 725, BLACK) AND 011-02246-02 (GTN 750, BLACK AND GRAY) KITS. SEE TABLE FOR KIT CONTENT DIFFERENCES.
3.225 4.560 9.132 1.400 7.647 7.397 5.169 4.665 2.433 NOTES: 1. CG MEASURED WITH UNIT, RACK, BACKPLATE, AND CONNECTORS Figure A-7. GTN 750 with GMA 35 Installation Dimensions and Center of Gravity GTN 6XX/7XX AML STC Installation Manual Page A-8 190-01007-A3 Rev.
1 115-01294-00 GTN 7XX INSTALL RACK 011-02645-00 GMA 35 INSTALL RACK 211-62237-09 SCREW, 6-32 X .312 (6X) 1 PART OF 011-00819-50 (GTN 725, BLACK), 011-00820-50 (GTN 750, BLACK), AND 011-00890-50 (GTN 750, GRAY) KITS 2 PART OF 011-02645-00 (GMA 35) KIT 3 TORQUE 8.5 – 9.5 IN-LBS 2 2 3 Figure A-8. GTN 750 with GMA 35 Mounting Rack Assembly GTN 6XX/7XX AML STC Installation Manual Page A-9 190-01007-A3 Rev.
OPTION 1: STACK CUTOUT (RACK INSTALLED FROM FRONT OF AIRCRAFT PANEL) GTN 6XX GTN 7XX 6.32 OPTION 2: RADIO CUTOUT (RACK INSTALLED FROM FRONT OF AIRCRAFT PANEL) 6.07 GTN 7XX 2.69 GTN 6XX 6.32 6.32 OPTION 3: RADIO CUTOUT (RACK INSTALLED FROM BACK OF AIRCRAFT PANEL ONLY) MAXIMUM AIRCRAFT PANEL THICKNESS IS .125 INCH. 6.00 GTN 7XX 2.62 6.25 GTN 6XX 6.25 NOTES, ALL OPTIONS: 1. DIMENSIONS ARE IN INCHES 2.
GTN 7XX Mounting Rack GTN 6XX Mounting Rack During installation of the mounting racks, ensure edge of the tab (bottom flange of the rack) is flush with the face of the instrument panel Tabs Figure A-10. GTN 6XX/7XX Mounting Rack Tab Alignment Detail GTN 6XX/7XX AML STC Installation Manual Page A-11 190-01007-A3 Rev.
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VIEW LOOKING AT REAR OF GMA 35 Figure A-11. GMA 35 Connector Layout Detail GTN 6XX/7XX AML STC Installation Manual Page A-13 190-01007-A3 Rev.
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Figure A-12. GTN 6XX Connector Layout Detail—Rear View Figure A-13. GTN 7XX Connector Layout Detail—Rear View 190-01007-A3 Rev.
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Appendix B B.1 Installation Guidance and Sample Installations Requirements for GTN 6XX/7XX Installations The GTN 6XX/7XX Navigators are designed to be installed in the mounting rack attached to the back of the instrument panel. In many cases, the existing “brackets” or “rails” fastened to the face of an instrument panel can provide adequate means to attach the GTN 6XX/7XX mounting racks and may be re-used requiring no modifications to the instrument panel.
GTN 6XX / 7XX Instrument Panel Installation Decision Tree Start: Installation of the GTN 6XX, GTN 7XX, or GTN 7XX with GMA 35 in the instrument panel Does the instrument panel already contain an avionics stack? Yes No Is there an STC or other approval method to install an avionics stack in the aircraft? No Yes Will the GTN 6XX or GTN 7XX fit in the existing instrument panel / mounting rail configuration? Return to Start See Appendix B.
B.2 General Requirements for GTN 6XX/7XX Installations Figure B-2 illustrates the avionics rack mounting rails and forward rack support required in all GTN 6XX/7XX installations. In order to satisfy the structural requirements for the GTN 6XX/7XX the following conditions must be met: 1. If existing structure is to be used for mounting the GTN 6XX/7XX, it must meet the following requirements: a. Sheet aluminum instrument panel structure must be at least 0.062” thick b.
Use existing avionics mounting rails for the attachment to instrument panel. Existing mounting rails must be electrically grounded to the instrument panel. The rail surface that touches the GTN 6XX or GTN 7XX racks need to be cleaned and prepped for electrical bond. See Section 2.4.4.4 for electrical bonding guidance. Ensure support of forward end of installation by securing mounting brackets together using a plate (shown), bracket, links, or similar method.
B.3 Avionics Stack Cutout Some instrument panels may require minor modification to increase width or height of the avionics stack cutout to accommodate installation of the GTN 6XX, GTN 7XX, or both. In order to satisfy the structural requirements for the installation of the GTN 6XX/7XX the following conditions must be met: 1. A cutout cannot be made into aircraft primary structure. 2. Cutout area must not affect any subpanel structure. 3. Some stationary instrument panels are considered primary structure.
3*D MINIMUM Ø 0.144 ±0.005 2*D MINIMUM USE EXISTING RAIL THICKNESS Figure B-3. Avionics Rack Mounting Rail Considerations GTN 6XX/7XX AML STC Installation Manual Page B-6 190-01007-A3 Rev.
B.5 Fabrication of Instrument Panel Given the age of the aircraft and the number and type of past avionics rack modifications, it may not be possible to reuse the existing instrument panel. For example, removal and replacement of the mounting rails may create a scenario where the rivet holes in the instrument panel have been enlarged too much to repair. Under certain conditions, it may be possible to fabricate an identical instrument panel to allow installation of the GTN 6XX/7XX.
B.6 Example Instrument Panel Layouts with GTN 6XX/7XX Navigator Installations Figure B-4, Figure B-5, and Figure B-6 show various configurations utilizing the GTN 6XX and/or the GTN 7XX with other avionics. Figure B-4. GTN 6XX and GTN 7XX Example Installation GTX330 S-TEC HDG FIFTY FIVE X NAV APR REV ALT VS Figure B-5. GTN 6XX Example Installation Figure B-6. GTN 7XX Example Installation GTN 6XX/7XX AML STC Installation Manual Page B-8 190-01007-A3 Rev.
Appendix C GTN Equipment Compatibility and Configuration The following equipment listed in this appendix is compatible with the GTN system when configured as described herein. For detailed configuration information refer to Section 5. C.
C.2 Air Data Computer Air data computers not listed below can still be approved under this GTN AML STC if all of the following conditions are met: The air data computer provides the following labels: 203 – Pressure Altitude 204 – Barometric-Corrected Altitude 210 – True Airspeed • The interface check for the altitude encoder described in Section 5.6.10 must be successfully completed. • The installation of the air data computer was previously FAA-approved. • The air data computer is TSO approved.
C.3 Altitude Serializer or Fuel/Air Data Altitude serializers/encoders not listed below can still be approved under this GTN AML STC if all of the following conditions are met: • The altitude serializer/encoder is TSO approved; • The installation of the altitude serializer/encoder was previously FAA-approved; • The interface check for the altitude serializer/encoder described in Section 5.6.10 must be successfully completed.
C.4 Autopilot Autopilots that will be coupled to GPS vertical guidance for GPS approaches must be specifically listed in the table below, unless the interface to the autopilot is installed in accordance with the G500 (STC #SA02015SE-D) or G600 (STC #SA02153LA-D) AML STC.
Table C-4. Compatible Autopilot Models Mfr. Model Honeywell (Bendix/King) Century Data Format Notes KAP 100/140/150, KFC 150/200/250/ 300 Analog Deviation, Discrete If an EFIS is installed, the GTN is connected to the EFIS using ARINC 429 and the EFIS interfaces to the autopilot. The GTN is not connected directly to the autopilot.
C.
C.7 IRU/AHRS Other IRU/AHRS sources can provide heading to the GTN via the following ARINC 429 labels: • 314-True Heading • 320-Magnetic Heading IRU/AHRS not listed below can still be approved under the GTN AML STC if all of the following conditions are met: • The IRU/AHRS provides ARINC 429 labels 314 and/or 320; • The installation of the IRU/AHRS was previously FAA-approved; • The checkout procedure described in Section 5.6.
C.8 Transponder Manufacturer Model Data Format Notes/Configuration GTX 32 GTX Mode C #1 or #2 GTX 327 GTN Control of GTX 327: GTX Mode C #1 or #2 No GTN Control of GTX 327: Aviation Output 1(output) to send GPS groundspeed. Altitude Format 1 (input, optional) to receive pressure altitude GTX 328 Garmin Configuration GTX 33/33D GTX software version 2.
C.10 Weather, Traffic, and Terrain Manufacturer Garmin Honeywell (Bendix/King) Avidyne (Ryan) Model Data Format GDL 69/69A Garmin HSDB GTX 330/33/330D/33D (with or without ES) RS-232 Refer to Section C.8.
C.12 CDI/HSI Source Selection Annunciators An external CDI/HSI Source Selection Annunciation or external GPS annunciations may be required for some installations – see Section 2.4.10.1 for additional information describing when external annunciation is required.
C.13 TAWS Annunciator Panels An external TAWS annunciator may be required for some installations. See Section 2.4.10.1 for additional information describing when a TAWS annunciator is required. The following indicators are suitable for external annunciation. Manufacturer Part Number Type Notes Garmin 013-00079-XX Indicator/switch 5VDC, 14VDC, and 28VDC indicators.
C.17 Weather Radar Manufacturer Garmin Data Format Model GWX 68 Garmin HSDB GWX 70 Bendix/King HSDB RDS 81 (RS 811A), RDS 82 (RS 181A), RDR 2000 (ART 2000) RDR 2100 (ART 2100) ARINC 429, ARINC 708, Discrete Configuration Notes/Configuration HSDB Configured for Return Bins: 600. Within the radome, HSDB cabling to the weather radar transceiver must be protected with overbraid. Refer to Section 5.5.1.4. GWX 68 software version 2.12 or later. HSDB Configured for Return Bins: 600.
Appendix D GMA 35 Equipment Compatibility The following equipment listed in this appendix is compatible with the GMA 35 Audio Panel when configured as described herein. For detailed configuration information refer to Section 5.5.4.8. D.
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Appendix E GTN Interconnect Diagrams Figure E-1. GTN System Interface Diagram Figure E-2. GTN 650/750 Typical Installation Interconnect Figure E-3. GTN 625/725 Typical Installation Interconnect Figure E-4. GTN Power Lighting Configuration Interconnect Figure E-5. GTN 6XX/7XX – PFD/MFD Interconnect Figure E-6. GTN 6XX/7XX – ARINC 429 EFIS Interconnect Figure E-7. External Navigation Source Selection Annunciator Interconnect Figure E-8. GTN 6XX/7XX – CDI Interconnect Figure E-9.
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GTN 6XX/7XX CONNECTOR P1001 AIRCRAFT POWER & GROUND AIRCRAFT LIGHTING BUS EXTERNAL INSTRUMENTATION POWER & GROUND LAT DEVIATION & FLAGS MAIN CDI/HSI (GPS/VOR/ILS) TO/FROM LIGHTING BUS TIME MARK OUT VERT DEVIATION & FLAGS SUPERFLAGS STORMSCOPE MAIN OBS RS-232 IN RS-232 OUT ARINC 429 IN FUEL/AIR DATA OR SERIALIZER SWITCHES/ ANNUNCIATORS SWITCHES ARINC 429 IN ARINC 429 OUT FLIGHT CONTROL SYSTEM TRAFFIC DISCRETES RS-232 IN ANNUNCIATORS ILS/GPS APPROACH RS-232 OUT EXTERNAL MAP DISPLAY RS-232
GTN 650/750 TYPICAL INSTALLATION—SEE DETAIL DRAWINGS FOR WIRING INFORMATION GTN 650/750 NAVIGATION INDICATOR P1001 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 4 49 68 CDI+ L CDI+ R s MAIN +TO OUT MAIN +FROM OUT 11 30 +TO FLAG +FROM FLAG s MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 NAV+ FLAG NAV- FLAG s MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT + UP + DOWN 12 31 s MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 G/S+ FLAG G/S- FLAG s MAIN OBS ROTOR H (GND) MAIN OBS ROTO
NOTES: 1. SEE DETAIL DRAWINGS FOR WIRE GAUGE INFO 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
GTN 625/725 TYPICAL INSTALLATION—SEE DETAIL DRAWINGS FOR WIRING INFORMATION GTN 625/725 NAVIGATION INDICATOR P1001 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 MAIN +TO OUT MAIN +FROM OUT 11 30 4 CDI+ L CDI+ R s +TO FLAG +FROM FLAG s MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 NAV+ FLAG NAV- FLAG s MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT 12 31 MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 + UP + DOWN s G/S+ FLAG G/S- FLAG s MAIN OBS ROTOR H (GND) MAIN OBS ROT
GTN 6XX/7XX 8 NAV/GPS P1001 AIRCRAFT POWER AIRCRAFT POWER 19 20 AIRCRAFT GND AIRCRAFT GND 77 78 CONFIG MODULE POWER CONFIG MODULE GND CONFIG MODULE DATA CONFIG MODULE CLOCK 65 64 62 63 LIGHTING BUS 1 HI LIGHTING BUS 1 LO LIGHTING BUS 2 HI LIGHTING BUS 2 LO 18 17 61 42 3 22 AWG (5A C/B) 20 AWG (7.5A C/B) 14 22 AWG (5A C/B, 28VDC) 20 AWG (7.
NON-METAL AIRCRAFT (VFR-ONLY INSTALLATIONS EXCLUDED) GTN 6XX/7XX 8 NAV/GPS P1001 6" (MAX) AIRCRAFT POWER AIRCRAFT POWER 19 20 20 AWG F1 3 s 5A (28 VDC) 7.
NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND VERIFY AIRCRAFT GROUND MEETS BONDING REQUIREMENTS IN SECTION 2.4.5. 3 ALL POWER LEADS AND GROUND LEADS ARE REQUIRED. 22 AWG WIRE CAN BE USED FOR THE SPLICE. USE APPROPRIATE HEAT-SHRINK TUBING TO PROVIDE SUFFICIENT INSULATION FROM SURROUNDING CONTACTS. 4 CONFIGURATION MODULE IS MOUNTED IN THE BACKSHELL OF THE P1001 CONNECTOR.
Figure E-5. GTN 6XX/7XX – PFD/MFD Interconnect Sheet 1 of 2 GTN 6XX/7XX AML STC Installation Manual Page E-10 190-01007-A3 Rev.
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
Figure E-6. GTN 6XX/7XX – ARINC 429 EFIS Interconnect Sheet 1 of 3 GTN 6XX/7XX AML STC Installation Manual Page E-12 190-01007-A3 Rev.
Figure E-6. GTN 6XX/7XX – ARINC 429 EFIS Interconnect Sheet 2 of 3 GTN 6XX/7XX AML STC Installation Manual Page E-13 190-01007-A3 Rev.
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
EXTERNAL NAVIGATION SOURCE SELECTION ANNUNCIATORS STACO INDICATOR CONNECTION GTN 6XX/7XX P1001 VLOC ANNUNCIATE* P1 52 N/C GPS ANNUNCIATE* 15 VLOC (W) 6 P1 2 3 9 6 11 12 5 (WHITE) VLOC (GREEN) GPS 4 LAMP VOLTAGE FROM 13 DIMMER CIRCUIT GPS (G) NAV/GPS INDICATOR VIVISUN INDICATOR CONNECTION GTN 6XX/7XX VLOC ANNUNCIATE* P1001 P1 52 C VLOC (W) 7 P1 D 15 VLOC (GREEN) GPS 4 B LAMP VOLTAGE FROM DIMMER CIRCUIT 13 G GPS ANNUNCIATE* (WHITE) A GPS (G) NAV/GPS INDICATOR VIVISUN
MID-CONTINENT PREFERRED SOURCE SELECTION ANNUNCIATOR MD41-151X GPS ACU GTN 6XX/7XX 14 15 VLOC ANNUNCIATE* GPS ANNUNCIATE* WAYPOINT ANNUNCIATE* TERMINAL ANNUNCIATE* APPROACH ANNUNCIATE* MESSAGE ANNUNCIATE* OBS ANNUNCIATE* LOI ANNUNCIATE* OBS/SUSP MODE SELECT* CDI SOURCE SELECT* 157X J1 P1001 52 15 33 34 55 54 14 53 16 39 2 1 8 3 9 10 11 20 12 4 VLOC ANNC GPS ANNC WPT ANNC TERM ANNC APR ANNC MSG ANNC OBS INPUT LOI ANNC OBS/SUSP MODE SELECT CDI SOURCE SELECT 24 SUSP ANNC P1002 SUSPEND ANNUNCIATE* 3
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. IF A CDI/HSI SOURCE SELECTION ANNUNCIATOR IS REQUIRED, INDICATORS ON THIS PAGE ARE SUITABLE TO MEET THE ANNUNCIATION REQUIREMENT. 4. LEGENDS ARE HIDDEN (BLACK) WHEN NOT ILLUMINATED. 5. THE PREFERRED ANNUNCIATION IS VLOC/GPS ALTHOUGH NAV/GPS IS ACCEPTABLE. 6. STACO SWITCH INDICATOR P/N 992561-1241762200 (14V SYSTEMS) AND P/N 992561-1241862200 (28V SYSTEMS) SHOWN. 7.
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NAVIGATION INDICATOR MID-CONTINENT MD200306/307 MD200302/303 MD222402 MD222406 GI 102 GI 102A GI 106 GI 106A KI 206 P1001 P1 P1 P1 P1 P1 P1 P2061 P1 P2 KPI 552 KPI 552B KPI 553 KPI 553A KPI 553B P101 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 11 12 11 12 22 23 22 23 11 12 11 12 n j V b - i h CDI+ L CDI+ R MAIN +TO OUT MAIN +FROM OUT 11 30 9 10 9 10 16 17 16 17 9 10 9 10 e S Z T - j k +TO FLAG +FROM FLAG MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50
NAVIGATION INDICATOR S-TEC GTN 6XX/7XX 6 CENTURY ROCKWELL COLLINS SPERRY PN-101 IND 351D P1001 P2 P1 P2 P1 P2 P1 P2 P1 P1 P2 P1 P1 NSD 1000 NSD 360A CD132 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 27 43 - F E - F E - 4 3 29 28 - 4 3 j i 11 12 17 18 CDI+ L CDI+ R MAIN +TO OUT MAIN +FROM OUT 11 30 26 42 - A B - A B - 1 2 26 27 - 1 2 n p 9 10 33 34 +TO FLAG +FROM FLAG MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 37 38 - - - - - -
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
NAVIGATION INDICATOR BENDIX/KING KI 209A GTN 6XX/7XX P209A1 P1001 8 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 MAIN +TO OUT MAIN +FROM OUT 11 30 MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT 12 31 MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 s s s s s 20 21 LNAV LATERAL DEV +LEFT IN LNAV LATERAL DEV +RIGHT IN 43 42 LNAV +TO IN LNAV +FROM IN 48 3 LNAV LATERAL +FLAG IN LNAV LATERAL -FLAG IN 27 26 LNAV VERTICAL +UP
NAVIGATION INDICATOR BENDIX/KING KI 208A GTN 6XX/7XX P208A1 P1001 MAIN LATERAL +LEFT OUT 49 MAIN LATERAL +RIGHT OUT 68 8 MAIN +TO OUT MAIN +FROM OUT 11 30 MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 s s s 20 21 LNAV LATERAL DEV +LEFT IN LNAV LATERAL DEV +RIGHT IN 43 42 LNAV +TO IN LNAV +FROM IN 48 3 LNAV LATERAL +FLAG IN LNAV LATERAL -FLAG IN ILS/GPS APPROACH 56 9 LNAV FCS LOC ENGAGE IN MAIN OBS ROTOR H (GND) MAIN OBS ROTOR C 1 2 50 2 OBS RETURN LNAV OBS EXCITATION IN MAIN
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NAVIGATION INDICATOR GTN 650/750 GARMIN GI 102/A GI 106/A P1 P1 P1004 VOR/LOC +LEFT VOR/LOC +RIGHT 5 6 KI 202 P2021 KI 203 P2031 KI 204 P2041 BENDIX/KING KI 206 KI 208 P2061 P2081 KI 209 P2091 KI 208A P208A1 KI 209A P209A1 11 12 11 12 n j - - n j - - - - +LEFT +RIGHT 9 10 9 10 e S - - e S - - - - +TO +FROM 7 8 7 8 N F - - N F - - - - NAV +FLAG NAV -FLAG - - - Y Y - 2 2 6 6 VOR/LOC COMPOSITE - - - K K - 4 4 10 10 ILS ENERGIZE - 13 14 - - k
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SINGLE GTN/SINGLE GTX WITH OR WITHOUT TIS GTN 6XX/7XX #1 P1001 4 7 GTX 32 GTX 327 P3271 P3281 GTX 33/33D GTX 330/330D P3301 GTX 328 GARMIN GTX TRANSPONDER RS-232 IN 1 27 20 23 23 RS232 TxD1 8 19 22 22 RS232 RxD1 25 51 51 SIGNAL GROUND RS-232 OUT 1 RS-232 GND 1 46 s SINGLE GTN/DUAL GTXs WITH OR WITHOUT TIS GTN 6XX/7XX #1 P1001 7 RS-232 IN 1 27 4 RS-232 OUT 1 8 RS-232 GND 1 46 GTX 32 GTX 327 P3271 GARMIN GTX TRANSPONDER #1 P3281 GTX 33/33D GTX 330/330D P3301 20 23 23 RS232
DUAL GTNs/SINGLE GTX WITH OR WITHOUT TIS GTN 6XX/7XX #1 P1001 7 RS-232 IN 1 27 4 RS-232 OUT 1 8 GTX 32 GTX 327 P3271 GTX 328 P3281 GTX 33/33D GTX 330/330D P3301 20 23 23 RS232 TxD1 22 22 RS232 RxD1 8 19 RS-232 GND 1 46 GARMIN GTX TRANSPONDER 25 6 51 51 SIGNAL GROUND 24 8 25 25 RS232 TxD2 24 24 RS232 RxD2 58 58 SIGNAL GROUND s GTN 6XX/7XX #2 P1001 7 RS-232 IN 1 27 4 RS-232 OUT 1 8 2 RS-232 GND 1 46 25 s 6 DUAL GTNs/DUAL GTXs WITHOUT TIS GTN 6XX/7XX #1 P1001 7
DUAL GTNs/DUAL GTXs WITH TIS GTN 6XX/7XX #1 P1001 GTX 33/33D GTX 330/330D P3301 7 RS-232 IN 1 27 4 RS-232 OUT 1 8 RS-232 GND 1 46 s GARMIN GTX TRANSPONDER #1 23 RS232 TxD1 22 RS232 RxD1 51 SIGNAL GROUND 25 RS232 TxD2 24 RS232 RxD2 58 SIGNAL GROUND 7 RS-232 IN 2 26 4 RS-232 OUT 2 7 RS-232 GND 2 45 s GTN 6XX/7XX #2 P1001 7 RS-232 IN 1 27 4 RS-232 OUT 1 8 RS-232 GND 1 46 s GTX 33/33D GTX 330/330D P3301 GARMIN GTX TRANSPONDER #2 23 RS232 TxD1 22 RS232 RxD1 51 SIGNAL GROUND
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
CONNECTIONS TO ARINC 429 TRAFFIC SOURCE 11 6 GTN 6XX/7XX P1001 4 ARINC 429 IN 1A ARINC 429 IN 1B 48 67 HONEYWELL L3 COMM 8 RYAN TRAFFIC ADVISORY SYSTEM KTA 970 KMH 980 J10 9900BX P1 KTA 870 KMH 880 J10 34 33 42 43 54 55 54 55 8 9 A ARINC 429 OUT B 85 19 2 2 - TAS TEST IN TRC 497 TRC 899 P1 P1 s TRAFFIC TEST* 75 (OPTIONAL) 8 7 TRAFFIC STANDBY* 76 82 21 23 23 - STANDBY / OPERATE TAWS AUDIO ACTIVE OUT* 35 32 34 22 22 - TA INHIBIT* (TAWS UNITS ONLY) CONNECTIO
CONNECTION TO RS-232 TRAFFIC SOURCE RYAN 9900B/BX TCAD PROCESSOR GTN 6XX/7XX P1 P1001 13 RS-232 IN 1 27 17 RS-232 OUT 2 8 19 RS-232 IN 2 18 RS-232 GND 2 16 SWITCH RS-232 OUT 1 RS-232 GND 1 46 s 12 DUAL GTN CONNECTION TO RS-232 TRAFFIC SOURCE RYAN 9900B/BX TCAD PROCESSOR GTN 6XX/7XX #1 P1 P1001 RS-232 IN 1 27 13 RS-232 OUT 1 8 RS-232 GND 1 46 17 RS-232 OUT 2 19 RS-232 IN 2 18 RS-232 GND 2 20 RS-232 OUT 3 22 RS-232 IN 3 21 RS-232 GND 3 16 SWITCH s GTN 6XX/7XX #2 P1001 RS-
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT THE GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT CHASSIS WITH AS SHORT A CONDUCTOR AS PRACTICAL. 4. ONLY ONE TRAFFIC SOURCE MAY BE CONNECTED TO THE GTN. IN DUAL GTN INSTALLATIONS, THE TRAFFIC SOURCE SHOULD BE CONNECTED TO EACH GTN ON WHICH TRAFFIC IS TO BE DISPLAYED. 5.
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AUDIO PANEL INTERCONNECT AUDIO PANEL 9 GTN 6XX/7XX GARMIN 3 P1003 3 6 500 Ω COM AUDIO HI 7 500 Ω COM AUDIO LO 18 COM MIC 1 AUDIO IN HI COM MIC 1 KEY* MIC AUDIO IN LO SL 10 SERIES SL 15 SERIES GMA 340 GMA 347 BOTTOM J1 J3471 9/(10) GND LUG 9/(13) 10/(14) 7/(12) 8/(13) 9/(13) 10/(14) P/(H) R/(V) GND LUG 11/(15) 12/(30) 10/(14) 26/(32) 27/(33) 8/(13) 7 7 31 32 5 5 11 20 PS ENGINEERING PMA 6000 PMA 8000 PMA 7000 BOTTOM J1 (BOTTOM) BENDIX/KING KMA 24 KMA 26 KMA 28 P241 P261 J1 (BO
GMA 350/350H INTERCONNECT GMA 350/350H GTN 6XX/7XX 3 P1003 500 Ω COM AUDIO HI 7 500 Ω COM AUDIO LO 18 3 MIC AUDIO IN LO 6 COM MIC 1 AUDIO IN HI COM MIC 1 KEY* P3501 5 9/(13) 10/(14) COM 1/(COM 2) AUDIO HI COM 1/(COM 2) AUDIO LO 11/(15) 12/(30) COM 1/(COM 2) MIC AUDIO COM 1/(COM 2) MIC KEY 17/(19) 18/(20) NAV 1/(NAV 2) AUDIO HI NAV 1/(NAV 2) AUDIO LO 7 s 20 5 11 s P1004 3 500 Ω VOR/LOC AUDIO OUT HI 16 500 Ω VOR/LOC AUDIO OUT LO 17 s P1001 31 32 AUDIO OUT HI 4 AUDIO OUT LO 23 ALERT 1 AUDI
NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: 3 THE 500 OHM AUDIO OUTPUTS ARE BALANCED OUTPUTS, AND THE LO OUTPUTS MUST BE CONNECTED. IF THE AUDIO PANEL DOES NOT HAVE A LO INPUT, THE LO OUTPUT SHOULD BE CONNECTED TO A GROUND LUG AT THE AUDIO PANEL. 4 REFER TO MANUFACTURER’S DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY.
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SINGLE GTN CONNECTION TO WX-500 GTN 6XX/7XX L3 Communications WX-500 RS-232 OUT 4 RS-232 IN 4 RS-232 GND 3/4 5 P1001 P3 5 24 44 8 20 4 RS-232 RX RS-232 TX P2 s 5 RS-232 GROUND DUAL GTN CONNECTIONS TO WX-500 GTN 6XX/7XX #1 RS-232 OUT 4 RS-232 IN 4 RS-232 GND 3/4 5 L3 Communications WX-500 P1001 P3 5 24 44 8 20 s 4 RS-232 RX RS-232 TX P2 5 RS-232 GROUND GTN 6XX/7XX #2 7 P1001 RS-232 IN 4 RS-232 GND 3/4 5 24 44 s GTN CONNECTION TO KGP 560 GTN 6XX/7XX Bendix/King KGP 560 GA Enhanced G
NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: 3 AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4.
METAL AIRCRAFT ONLY SINGLE GTN INSTALLATIONS GTN 7XX ETHERNET OUT 2 ETHERNET IN 2 P1002 A B A B 7 4 17 18 15 16 GWX 70 P400 P3271 34 35 36 37 4 3 23 22 A B A B 44 15 56 8 RT ON/OFF POWER GROUND 17 1 16 31 24 43 61 60 CONFIG MODULE POWER CONFIG MODULE GROUND CONFIG MODULE DATA CONFIG MODULE CLOCK ETHERNET IN ETHERNET OUT s s 5 GARMIN WEATHER RADAR GWX 68 4 1 3 2 CONFIG MODULE RED BLK YEL WHT 6 DUAL GTN INSTALLATIONS GTN 6XX/7XX #1 ETHERNET OUT 2 ETHERNET IN 2 A B A B P1002 7 4
ARINC 708 WXR – SINGLE GTN INSTALLATIONS HONEYWELL (BENDIX/KING) GTN 7XX P1005 11 8 ARINC 453/708 IN 1 WEATHER RADAR R/T 11 RDS 81 RDS 82 RDR 2000 RDR 2100 RS 811A RS 181A ART 2000 ART 2100 15 P1001 P1001 P5001 P5001 8 9 8 9 42 43 42 43 19 (18) 20 (5) 19 (18) 20 (5) 2 (4) 3 (5) 2 (4) 3 (5) 24 (12) 24 (12) 31 (32) 31 (32) RT ON/OFF #1 (#2) - - 1 1 STRUT SWITCH IN 12 12 10 A 18 B 60 A ARINC 453 OUT B (WEATHER) s 14 ARINC 429 OUT 3 A 28 B 7 A ARINC 429 IN #1 (#2) B (CON
NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: 3 AT THE GTN, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0". CONNECT THE SHIELD GROUNDS AT THE GWX 68/70 TO ITS CONNECTOR BACKSHELL IN ACCORDANCE WITH THE GWX 68/70 INSTALLATION INSTRUCTIONS. 4 s SHIELD BLOCK GROUND AIRFRAME GROUND USE AIRCRAFT GRADE CATEGORY 5 ETHERNET CABLE.
7 GTN 6XX/7XX GDL 69/69A P1002 4 ETHERNET IN 3A ETHERNET IN 3B ETHERNET OUT 3A ETHERNET OUT 3B P691 5 23 24 25 26 s s GDL 69/69A CONFIGURATION MODULE BLK RED YEL WHT 25 24 23 22 ETHERNET OUT 1A ETHERNET OUT 1B ETHERNET IN 1A ETHERNET IN 1B 1 21 40 60 CM GROUND CM POWER OUT CM DATA CM CLOCK 6 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3.
SINGLE GTN INSTALLATION 1 VOR/LOC/GS Antenna GTN 6XX/7XX COM Antenna P1008 NAV GPS/WAAS Antenna 2 P1007 COM P1006 5 5 GPS/WAAS s DUAL GTN INSTALLATION 1 COM Antenna GTN 6XX/7XX #1 GPS/WAAS Antenna 2 P1007 COM P1006 5 5 VOR/LOC/GS Antenna GPS/WAAS s P1008 NAV 3 1 Splitter S 2 GTN 6XX/7XX #2 COM Antenna P1008 NAV GPS/WAAS Antenna 2 P1007 COM P1006 GPS/WAAS Figure E-18. GTN 6XX/7XX Antenna Interconnect Sheet 1 of 5 190-01007-A3 Rev.
G/S Antenna SINGLE GTN/DUAL NAV ANTENNA INSTALLATION 4 1 VOR/LOC Antenna 7 G/S ANT Diplexer VOR GTN 6XX/7XX COM Antenna P1008 NAV GPS/WAAS Antenna 2 P1007 COM P1006 5 5 GPS/WAAS s DUAL GTN/DUAL NAV ANTENNA INSTALLATION 1 COM Antenna GTN 6XX/7XX #1 GPS/WAAS Antenna 2 P1007 COM P1006 5 5 GPS/WAAS s G/S Antenna P1008 NAV VOR/LOC Antenna 3 4 7 1 G/S Splitter 2 GTN 6XX/7XX #2 S ANT Diplexer VOR COM Antenna P1008 NAV GPS/WAAS Antenna 2 P1007 COM P1006 5 5 GPS/WAAS s F
SINGLE GTN, OTHER RADIO (SEPARATE G/S AND VOR/LOC ANTENNA PORTS), AND SINGLE ANTENNA GTN 650/750 #1 VOR/LOC/GS Antenna P1008 NAV 3 1 Splitter VHF NAV RADIO WITH SEPARATE G/S AND VOR/LOC ANTENNA PORTS S 2 G/S G/S Diplexer ANT VOR VOR/LOC REFERENCE ONLY SINGLE GTN, OTHER RADIO (SEPARATE G/S AND VOR/LOC ANTENNA PORTS), AND DUAL ANTENNAS GTN 650/750 #1 4 3 7 VOR/LOC Antenna P1008 NAV G/S Antenna G/S ANT 1 Splitter Diplexer VOR S 2 3 VHF NAV RADIO WITH SEPARATE G/S AND VOR/LOC ANTENNA
SINGLE GTN, OTHER RADIO, AND SINGLE ANTENNA VOR/LOC/GS Antenna GTN 650/750 P1008 NAV 3 1 Splitter S 2 VHF NAV RADIO WITH COMBINED VOR/LOC/ GS ANTENNA PORTS NAV REFERENCE ONLY SINGLE GTN, OTHER RADIO, AND DUAL ANTENNAS GTN 650/750 G/S Antenna P1008 NAV VOR/LOC Antenna 3 4 7 1 G/S Splitter 2 S ANT Diplexer VOR VHF NAV RADIO WITH COMBINED VOR/LOC/ GS ANTENNA PORTS NAV REFERENCE ONLY Figure E-18.
NOTES: 1. REFER TO SECTION 3.3.1, 3.3.2, AND 3.3.3 FOR ANTENNA CABLE SPECIFICATIONS. 2. THE GPS ANTENNA COAXIAL CABLE MUST BE DOUBLE OR TRIPLE SHIELDED AND THE LOSS (INCLUDING CONNECTORS) MUST USUALLY BE GREATER THAN 1.5 dB AND LESS THAN 6.5 dB. REFER TO SECTION 3.3 FOR ADDITIONAL INFORMATION. 3. GARMIN P/N 013-00112-00 (MINI-CIRCUITS SPLITTER P/N ZFSC-2-1B+) MUST BE USED. 4. COMANT DIPLEXER P/N CI 507 MUST BE USED. 5.
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GTN 6XX/7XX P1001 TAWS NOT AVAILABLE ANNUNCIATE* TAWS WARNING ANNUNCIATE* TAWS CAUTION ANNUNCIATE* TAWS INHIBIT ANNUNCIATE* TAWS INHIBIT IN* 72 71 73 57 37 TAWS AUDIO ACTIVE OUT* 35 GARMIN 013-00079-XX J1 MID-CONTINENT MD41-10XX J1 10 11 5 19 20 21 22 23 24 25 10 11 5 19 20 21 22 23 24 25 TAWS ANNUNCIATOR PANEL 5 TERR N/A ANNC IN TERR PULL UP ANNC IN TERR CAUTION ANNC IN TAWS INHIBIT ANNC IN TAWS INHIBIT OUT AIRCRAFT GROUND AIRCRAFT GROUND AIRCRAFT GROUND AIRCRAFT GROUND AIRCRAFT GROUND 7 9 AUDI
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GTN 6XX/7XX CDI P1001 3 CDI SOURCE SELECT* 39 OBS/SUSP 4 OBS/SUSP MODE SELECT* 16 AIR/GROUND* 38 5 COM RMT XFR P1003 COM REMOTE TRANSFER* 27 6 COM CHAN UP COM REMOTE TUNE UP* 28 7 COM REMOTE TUNE DOWN* 29 COM CHAN DN NAV RMT XFR P1004 8 VLOC REMOTE TRANSFER 28 NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. THE CDI SOURCE SELECT INPUT MAY BE USED TO TOGGLE BETWEEN GPS AND VLOC COURSE DEVIATION SOURCES.
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6 ACK Technologies A-30 Shadin 8800T/9000T 9200T Icarus Instruments 3000 DB15 Trans-Cal IA-RS232-X SSD-120 DB9 DB15 P3 (DB9) J5 7 (14) SHELL 4 (9) 5 7 15 2 SHELL 1 (2) 5 9 - 1 2 - - - CONFIG JUMPER (RESOLUTION) 9 - 7 8 - - - CONFIG JUMPER (OUTPUT FORMAT) GTN 6XX/7XX P1001 10 RS-232 IN 2 26 RS-232 GND 2 45 4 s s ALTITUDE ENCODER 7 Sandia SAE5-35 RS-232 OUT HI RS-232 OUT LO s s TO GTN #2 (IF INSTALLED) 8 Shadin Shadin Shadin Shadin Shadin Shadin Electronics GARMIN ARNA
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
GTN 6XX/7XX GARMIN GAD 42 4 5 P421 P1001 7 ARINC 429 OUT 1A ARINC 429 OUT 1B 10 29 ARINC 429 IN 1A ARINC 429 IN 1B 48 67 s s 1 2 GPS ARINC 429 IN A GPS ARINC 429 IN B 13 14 ARINC 429 OUT A ARINC 429 OUT B 3 4 NAV ARINC 429 IN A NAV ARINC 429 IN B P1004 6 VOR/ILS ARINC 429 OUT A VOR/ILS ARINC 429 OUT B 24 23 s NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3.
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AIR DATA COMPUTER GTN 6XX/7XX P1001 ARINC 429 IN 1A ARINC 429 IN 1B 5 Shadin ADC 2000 Shadin ADC 2000 J2 (DB 15) J1 (MS CONN) 7 8 40 22 48 67 Bendix/King Bendix/King B&D KDC 481 90004-003 KDC 281 27 9 P2811 P4811 5 6 U i TRANSMITTER A TRANSMITTER B s IRU/AHRS GTN 6XX/7XX Collins AHC-85E ARINC 429 IN 1A ARINC 429 IN 1B 5 P1001 P1 48 67 16 14 IRU/AHRS TRANSMITTER A IRU/AHRS TRANSMITTER B s AIR DATA COMPUTER GTN 6XX/7XX Insight TAS 1000 P1001 4 RS-232 OUT 1 RS-232 IN 1 RS-232 GND
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TYPICAL CONNECTIONS TO RMI GTN 650/750 KI 229 P1004 P2291 VOR OBI CLOCK 25 VOR OBI DATA 27 VOR OBI SYNC 26 s s s BENDIX/KING KNI 582 KDA 692 Pointer #1 P6921 P5821 RADIO MAGNETIC INDICATOR KNI 582 Pointer #2 P5821 12 11 8 7 OBI CLOCK 19 L 17 16 OBI DATA 11 M 33 24 OBI SYNC NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3.
ARINC 429 EHSI DISPLAY Sandel SN3500 GTN 6XX/7XX 7 8 P2 P1004 VOR/ILS ARINC 429 OUT A 24 3/(35) VOR/ILS ARINC 429 OUT B 23 33/(21) s NAV 429 IN PORT A 1/(2) NAV 429 IN PORT B 1/(2) P1001 4 ARINC 429 IN 1A 48 30 ARINC 429 IN 1B 67 15 ARINC 429 OUT 1A 10 31/(2) GPS 429 IN PORT A 1/(2) ARINC 429 OUT 1B 29 17/(32) GPS 429 IN PORT B 1/(2) s 429 OUT A 429 OUT B s 6 LOCALIZER ENGAGE 56 ILS/GPS APPROACH Autopilot +LEFT MAIN LATERAL +LEFT OUT 49 MAIN LATERAL +RIGHT OUT 68 MAI
ARINC 429 EHSI DISPLAY # 1 Sandel SN3308 GTN 6XX/7XX 8 P1 P1004 P3 9 VOR/ILS ARINC 429 OUT A 24 26 429-3 RX-A VOR/ILS ARINC 429 OUT B 23 7 429-3 RX-B s P1001 4 ARINC 429 IN 1A 48 ARINC 429 IN 1B 67 s 11 429-1 TX-A 29 429-1 TX-B 429-1 RX-A ARINC 429 OUT 1A 10 10 ARINC 429 OUT 1B 29 28 MAIN +TO OUT 11 MAIN +FROM OUT 30 429-1 RX-B s 17 +TO (FLAG) 35 +FROM (FLAG) 27 ILS 1 ENERGIZE s 37 CDI+L 19 CDI+ R 18 NAV+ VALID (FLAG) 36 NAV– VALID (FLAG) 16 GSI+ UP 34
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
Sandel SN3308 ARINC 429 EHSI DISPLAY P1 P2 P3 7 9 VOR/ILS 1 (RELAXED) 6 GTN 6XX/7XX #1 N/C 33 NAV 1/2 RELAY SENSE P1004 VOR/ILS ARINC 429 OUT A 24 VOR/ILS ARINC 429 OUT B 23 s 11 9 429-2 RX-A 27 429-2 RX-B 5 VHF NAV 2 SWITCHING RELAY VOR/ILS 2 (ENERGIZED) 15 P1001 ARINC 429 IN 1A 48 ARINC 429 IN 1B 67 ARINC 429 OUT 1A 10 ARINC 429 OUT 1B 29 ILS/GPS APPROACH 56 MAIN +TO OUT MAIN +FROM OUT 11 30 MAIN LATERAL +LEFT OUT 49 MAIN LATERAL +RIGHT OUT 68 13 AIRCRAFT POWER 14
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
8 GTN 6XX/7XX #1 6 Sandel SN3308 VOR/ILS 1 (RELAXED) P2 N/C P1004 VOR/ILS ARINC 429 OUT A 24 VOR/ILS ARINC 429 OUT B 23 ARINC 429 EHSI DISPLAY #1 7 P3 NAV 1/2 RELAY SENSE 33 10 13 s s s 9 429-2 RX-A 27 429-2 RX-B 5 VHF NAV 2 SWITCHING RELAY 21 GPS 2 SWITCHING RELAY VOR/ILS 2 (ENERGIZED) s 14 12 A/C PWR P1001 ARINC 429 IN 1A 48 ARINC 429 IN 1B 67 ARINC 429 OUT 1A 10 ARINC 429 OUT 1B 29 ILS/GPS APPROACH MAIN LATERAL +LEFT OUT 13 s s s s s s 56 13 s s 11 429-1 TX-
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
KING SERIAL DME (PANEL-MOUNTED DME) DME TRANSCEIVER GTN 650/750 #1 BENDIX/KING P1004 5 7 KN62/62A P621/P62A1 KN64 P641 14 14 CLOCK BUS 13 13 DATA BUS L L RNAV/CHANNEL REQ C C DME COMMON SERIAL DME-CLOCK 18 s s s s 7 SERIAL DME-DATA 19 s s s s 7 SERIAL DME-RNAV/CH REQ 20 s s s s NAV 1 DME COMMON 41 NAV 2 GTN 650/750 #2 NAV SELECTION SW 6 P1004 5 SERIAL DME-CLOCK 18 s SERIAL DME-DATA 19 s SERIAL DME-RNAV/CH REQ 20 s DME COMMON 41 NOTES: 1.
KING SERIAL DME (REMOTE-MOUNTED) REMOTE DME GTN 650/750 #1 BENDIX/KING P1004 7 KN63 KDM 706 P631 P7061 7 SERIAL DME-CLOCK 18 s s s s s s s s s s s 7 s s s s 8 CLOCK BUS 6 9 DATA BUS D 24 DME REQUEST 7 SERIAL DME-RNAV/CH REQ 20 s F s SERIAL DME-DATA 19 s 7 NAV DME COMMON 41 DME INDICATOR BENDIX/KING GTN 650/750 #2 P1004 KDI 572 P5721 KDI 574 P5741 15 15 DME REQUEST s 11 11 DATA BUS s 12 12 CLOCK BUS s 17 17 RNAV REQUEST 48 48 NAV 1 COMMON 49 49 NAV 2
4 GTN 650/750 4 BENDIX/KING COLLINS DME 40 KN 62A P621 P1 P1004 5 5 COLLINS DME 42 P1 NARCO DME 890 P301 NARCO IDME 891 P301 4 6 DME PAR DME 1MHZ-A 45 12 28 28 2 31 1 MHZ-A PAR DME 1MHZ-B PAR DME 1MHZ-C 46 47 - - - 3 12 9 32 32 4 30 1 MHZ-B 1 MHZ-C PAR DME 1MHZ-D/SERIAL DME ON 33 56 8 11 43 35 43 35 5 - 11 - 1 MHZ-D 1 MHZ-E PAR DME 100KHZ-A/SERIAL DME HOLD PAR DME 100KHZ-B PAR DME 100KHZ-C PAR DME 100KHZ-D PAR DME 100KHZ-E PAR DME 50KHZ 37 39 40 42 54 7 4 6 H 11
TO MAIN CDI VERTICAL +DOWN VERTICAL +UP VERTICAL -FLAG VERTICAL +FLAG LATERAL +RIGHT LATERAL +LEFT LATERAL -FLAG LATERAL +FLAG AUTOPILOT GTN 6XX/7XX KAP 100 (KC 190) P1001 MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT s 50 69 s MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 11 s 8 s 8 s s 8 s KAP 140 (KC 140) KAP 150 KFC 150 (KC 19X) BENDIX/KING KFC 200 KFC 225 KFC 250 (KC 225) (KC 295) (KCP 299) P1 P2 P1 P2 KFC 275 KFC 325 (K
P1001 GTN 6XX/7XX LATERAL +FLAG LATERAL -FLAG LATERAL +LEFT LATERAL +RIGHT VERTICAL +FLAG VERTICAL -FLAG VERTICAL +UP VERTICAL +DOWN ILS/GPS APPROACH* TO MAIN CDI 4 AUTOPILOT BENDIX MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT 12 31 s s 11 s s s 4 ILS/GPS APPROACH* 8 M4C 5536E-2 J1 J2 M4D 5536F J1 J2 - - - - LAT DEV FLAG+
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT THE GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT GROUND WITH AS SHORT A CONDUCTOR AS PRACTICAL. 4. THE ILS/GPS APPROACH DISCRETE IS REQUIRED BY SOME CDIS/ HSIS THAT ARE USED WITH THE M4C/D AUTOPILOTS.
VERTICAL +UP VERTICAL +DOWN VERTICAL +FLAG VERTICAL -FLAG LATERAL +LEFT LATERAL +RIGHT LATERAL +FLAG LATERAL -FLAG TO MAIN CDI AUTOPILOT CENTURY GTN 6XX/7XX Century Century Century Century Century II I III IV 21 CD194 CD34 CD34 CD58 CD66 CD92 P1001 s MAIN LATERAL +FLAG OUT MAIN LATERAL -FLAG OUT 50 69 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 9 MAIN VERTICAL +FLAG OUT 51 MAIN VERTICAL -FLAG OUT 70 MAIN VERTICAL +UP OUT 12 MAIN VERTICAL +DOWN OUT 31 ILS/GPS APPROACH* 56 s s s s
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
To Main CDI VERTICAL +DOWN VERTICAL +UP VERTICAL -FLAG VERTICAL +FLAG LATERAL +RIGHT LATERAL +LEFT LATERAL -FLAG LATERAL +FLAG AUTOPILOT CESSNA 300B CA550A/ FD GTN 6XX/7XX s 50 69 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT 49 68 MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT 12 31 ILS/GPS APPROACH* 56 7 800B CA550A/ FD 300IFCS CA530FD 400IFCS CA530FD 800IFCS CA530FD J1/P5 J1/P5 J1/P5 J1/P4 J2/P5 J1/P4 J2/P5 J1/P4 J2/P5 P1001
TO MAIN CDI 6 49 68 MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT 12 31 MAIN LATERAL +FLAG OUT MAIN LATERAL –FLAG OUT 50 69 MAIN VERTICAL +FLAG OUT MAIN VERTICAL -FLAG OUT 51 70 VERTICAL SUPERFLAG LATERAL SUPERFLAG P1001 MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT VERTICAL -FLAG VERTICAL +FLAG LATERAL -FLAG LATERAL +FLAG VERTICAL +DOWN VERTICAL + UP LATERAL +RIGHT LATERAL +LEFT GTN 6XX/7XX APC 65/65B/ 65C/65E/65F/ 65H/65J J3 J1 s s s 5 s s FGC-65( ) FYD-65 J1 J3 J1 J3 - 54 53 -
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". CONNECT OTHER END OF THE SHIELD PER THE REMOTE EQUIPMENT INSTALLATION REQUIREMENTS. IF NO SHIELD TERMINATION REQUIREMENT EXISTS FOR THE REMOTE EQUIPMENT, TERMINATE SHIELDS AS SHORT AS POSSIBLE, NOT TO EXCEED 3.0". SEE SECTION 2.4.11.4. 4.
VERTICAL + UP VERTICAL + DOWN VERTICAL + FLAG VERTICAL - FLAG LATERAL + LEFT GTN 6XX/7XX LATERAL + RIGHT LATERAL + FLAG LATERAL - FLAG TO MAIN CDI P1001 s MAIN LATERAL +FLAG OUT 50 MAIN LATERAL –FLAG OUT 69 MAIN LATERAL +LEFT OUT 49 MAIN LATERAL +RIGHT OUT 68 15 MAIN VERTICAL +FLAG OUT 51 MAIN VERTICAL -FLAG OUT 70 s s 12 System 20 P1 System 30 P1 System 40 P1 - - - System 50 P1 - 9 10 9 10 14 13 - - - AUTOPILOT System 60-1 0109 System System 60 PSS 60-2 / 65 0110 0109 0110 13 14
S-TEC ST-901 GPSS CONVERTER CONNECTION GTN 6XX/7XX J3 P1001 11 ARINC 429 OUT 1A 10 ARINC 429 OUT 1B 29 S-TEC ST-901 GPSS CONVERTER A ARINC DATA IN B 8 9 S-TEC ST-901 GPSS CONVERTER CONNECTION 8 s P1001 11 S-TEC ST-901 GPSS CONVERTER 10 GTN 6XX/7XX ARINC 429 OUT 1A ARINC 429 OUT 1B GPSS (RELAXED) J3 8 9 10 29 9 A ARINC DATA IN B s VLOC ANNUNCIATE* 52 22 TO OTHER SYSTEM REQURING VLOC ANNUNCIATE SIGNAL GPS OVERRIDE 4 NO GPSS (ENERGIZED) 10 VLOC ANNUNCIATE* 52 13 AIRCRAFT POWER 14 CO
NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT THE GTN, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD LEADS MUST BE LESS THAN 3.0". CONNECT OTHER SHIELD GROUNDS TO AIRCRAFT GROUND WITH AS SHORT A CONDUCTOR AS PRACTICAL. 4. IF VLOC ANNUNCIATE SIGNAL IS USED ONLY BY AUTOPILOT, THIS MAY BE CONNNECTED DIRECTLY.
GTN 7XX BENDIX/KING HSI KI-525A P2 (BOT) P1005 7 SYNCHRO X 35 S HDG XMT X SYNCHRO Y 14 V HDG XMT Y SYNCHRO Z 56 T HDG XMT Z SYNCHRO VALID INPUT (ACTIVE LOW) 33 SYNCHRO VALID INPUT (ACTIVE HI) 54 SYNCRO REF HI 36 R HDG XMT H SYNCHRO REF LO 15 U HDG XMT C 5 s N/C 6 9 s s s A/C 26VAC 400 HZ HI A/C 26VAC 400 HZ LO NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3.
GTN 6XX/7XX #2 GTN 6XX/7XX #1 P1002 P1002 ETHERNET IN 1A ETHERNET IN 1B ETHERNET OUT 1A ETHERNET OUT 1B 5 6 7 8 9 s 8 9 6 7 ETHERNET OUT 1A ETHERNET OUT 1B ETHERNET IN 1A ETHERNET IN 1B 10 SYSTEM ID PROGRAM* s s 4 NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2. GROUND DESIGNATIONS: s SHIELD BLOCK GROUND AIRFRAME GROUND 3. AT GTN 6XX/7XX, CONNECT SHIELD GROUNDS TO THE CONNECTOR BACKSHELL -- THE SHIELD TERMINATION LEADS MUST BE LESS THAN 3.0". 4.
GARMIN GTN 6XX/7XX P561 P1002 GSR STATUS IN* 11 GSR REMOTE PWR* 12 GARMIN GSR 56 31 STATUS DISCRETE* OUT 16 IRIDIUM RMT PWR ON* 12 13 14 RS-232 OUT RS-232 IN SIGNAL GROUND 4 5 GSR 56 AUDIO IN HI GSR 56 AUDIO IN LO 1 2 GSR 56 AUDIO OUT HI GSR 56 AUDIO OUT LO P1001 RS-232 IN 4 5 RS-232 OUT 4 RS-232 GND 4 24 5 44 s s AUDIO PANEL TEL MIC AUDIO OUT HI TEL MIC AUDIO OUT LO 4 (OPTIONAL) TEL AUDIO IN HI TEL AUDIO IN LO s NOTES: 1. ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2.
DUAL GTN INTERCONNECT – SINGLE GDU GTN 6XX/7XX #1 VOR/ILS 429 OUT A VOR/ILS 429 OUT B P6202 P1004 24 23 7 24 s P1002 4 ETHERNET IN 2A ETHERNET IN 2B ETHERNET OUT 2A ETHERNET OUT 2B P6201 13 14 11 12 6 s TIME MARK OUT A TIME MARK OUT B 3 22 P6202 s ARINC 429 OUT 2A ARINC 429 OUT 2B ARINC 429 IN 2A ARINC 429 IN 2B 12 46 RS-232 IN 3 RS-232 GND 3 40 41 TIME MARK IN 1A TIME MARK IN 1B 6 23 ARINC 429 IN 3A ARINC 429 IN 3B 3 20 ARINC 429 OUT 1A ARINC 429 OUT 1B 13 47 RS-232 IN 4 RS-232 GND 4
NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: 3 IF ONLY ONE GTN 6XX/7XX IS INSTALLED, CONNECT AS SHOWN FOR GTN #1. 4 IF A TAWS-EQUIPPED GTN6XX/7XX UNIT IS INSTALLED, IT MUST BE CONNECTED AS GTN #1 – ONLY TAWS ANNUNCIATIONS FROM GTN #1 ARE DISPLAYED ON THE PFD. 5 REFER TO GDU 620 INSTALLATION MANUAL FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION. PIN-OUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY. 6 USE AIRCRAFT GRADE CATEGORY 5 ETHERNET CABLE.
SINGLE GTN AND GDL 88 3 GTN 6XX/7XX TIME MARK OUT A 3 TIME MARK OUT B 22 S P1001 22 TIME MARK 1A 3 TIME MARK 1B 37 AUDIO INHIBIT #1* S S TAWS AUDIO ACTIVE OUT* GDL 88/D TO EXISTING AIRCRAFT WIRING P881 35 (GTN 6XX/7XX TAWS UNITS ONLY) P1002 ETHERNET IN 3 A 23 B 24 ETHERNET OUT 3 A 25 B 26 4 6 S 53 A 54 B ETHERNET OUT 1 51 A 52 B ETHERNET IN 1 S Figure E-40. GTN 6XX/7XX – GDL 88/88D Interconnect Sheet 1 of 2 GTN 6XX/7XX AML STC Installation Manual Page E-88 190-01007-A3 Rev.
DUAL GTNS AND GDL 88 GTN 6XX/7XX #1 3 TIME MARK OUT A 3 TIME MARK OUT B 22 S P1001 TO EXISTING AIRCRAFT WIRING 35 22 TIME MARK 1A 3 TIME MARK 1B 37 AUDIO INHIBIT #1* S S TAWS AUDIO ACTIVE OUT* GDL 88/D P881 (GTN 6XX/7XX TAWS UNITS ONLY) P1002 ETHERNET IN 3 A 23 B 24 ETHERNET OUT 3 A 25 B 26 5 4 ETHERNET OUT 1 51 A 52 B ETHERNET IN 1 6 S S ETHERNET IN 4 53 A 54 B A 13 B 14 4 ETHERNET OUT 4 A B 4 5 S 5 GTN 6XX/7XX #2 6 P1002 ETHERNET IN 3 B 24 A 23 ETHERNET OUT 3
LATERAL SUPERFLAG VERTICAL SUPERFLAG GTN 6XX/7XX VERTICAL + UP VERTICAL + DOWN LATERAL + LEFT LATERAL + RIGHT TO MAIN CDI P1001 13 49 68 VERTICAL SUPERFLAG OUT 32 SPZ-200A/500 FZ-500 FD Computer J1A J1B 16 20 21 - LAT SUPERFLAG LAT DEV +LT LAT DEV +RT - 7 G/S SUPERFLAG - 16 17 GS DEV +UP GS DEV +DN 22 - s s LATERAL SUPERFLAG OUT MAIN LATERAL +LEFT OUT MAIN LATERAL +RIGHT OUT AUTOPILOT COMPUTER SPERRY s 4 s MAIN VERTICAL +UP OUT MAIN VERTICAL +DOWN OUT 12 31 s ILS/GPS APPROACH
Appendix F GMA 35 Interconnect Diagrams Figure F-1. GMA 35 – COM/NAV Interconnect ..................................................................................... F-2 Figure F-2. GMA 35 Power/RS-232/Marker Beacon Interconnect .......................................................... F-4 Figure F-3. GMA 35 – Headset Interconnect ........................................................................................... F-5 Figure F-4. GMA 35 – Other Audio Sources Interconnect.........................
GMA 35 Audio Panel COM 1 Transceiver* *See Next Page for COM Wiring To GMA 35 with GTN 750 COM SL 30/ GTN 635/ SL 40 650/750 5 P3501 COM 1 AUDIO IN HI COM 1 AUDIO LO 9 10 COM 1 MIC KEY OUT* COM 1 MIC AUDIO OUT HI 12 11 3 Garmin 400/500 Series P4002/ P5002 P1 P1003 14 13 7 18 7 19 500 Ω COM AUDIO HI 500 Ω COM AUDIO LO 7 4 8 20 11 5 18 4 6 COM MIC AUDIO LO COM MIC KEY COM MIC AUDIO HI s s COM 2 Transceiver* Garmin 5 COM 2 AUDIO IN HI COM 2 AUDIO LO 13 14 COM 2 MIC KEY OUT* COM 2 MIC AU
GTN 750 Installation with Second COM GMA 35 Audio Panel Garmin GTN 750 P1003 P3501 COM 2 AUDIO IN HI COM 2 AUDIO LO 13 14 COM 2 MIC KEY OUT* COM 2 MIC AUDIO OUT HI 30 15 3 COM 1 Transceiver (Connected as COM 2) 7 18 500 Ω COM AUDIO HI 500 Ω COM AUDIO LO 20 11 5 COM MIC AUDIO LO COM MIC KEY COM MIC AUDIO HI s s Garmin GNS 530W P5002 COM 1 AUDIO IN HI COM 1 AUDIO LO 9 10 COM 1 MIC KEY OUT* COM 1 MIC AUDIO OUT HI 12 11 COM 2 Transceiver (Connected as COM 1) 7 19 500 Ω COM AUDIO HI 500 Ω C
GMA 35 Audio Panel 7 P3502 AUDIO AIRCRAFT POWER AIRCRAFT POWER 8 9 20 AWG AIRCRAFT GROUND AIRCRAFT GROUND 10 11 20 AWG 14/28 VDC AIRCRAFT POWER 3A (14/28 VDC) AIRCRAFT GROUND GTN 725/750 3 RS-232 IN RS-232 OUT P1001 7 26 45 17 18 RS-232 OUT 2 RS-232 IN 2 RS-232 GND 2 8 s s Marker Beacon Antenna P3501 5 MARKER ANTENNA IN HI MARKER ANTENNA IN LO 1 2 MIDDLE MARKER SENSE OUT 39 4 INNER MARKER LAMP OUT MIDDLE MARKER LAMP OUT 36 38 6 OUTER MARKER LAMP OUT 37 9 AIRCRAFT GROUND NOTES
GMA 35 Audio Panel P3501 MIC JACK PILOT MIC KEY IN* PILOT MIC AUDIO IN HI PILOT MIC AUDIO IN LO 34 33 35 PILOT PTT s P3502 COPILOT MIC KEY IN* COPILOT MIC AUDIO IN HI COPILOT MIC AUDIO IN LO MIC JACK 33 32 34 COPILOT PTT s PASS 1 MIC AUDIO IN HI PASS 1 MIC AUDIO IN LO 35 36 PASS 1 MIC JACK s PASS 2 MIC AUDIO IN HI PASS 2 MIC AUDIO IN LO 37 38 PASS 2 MIC JACK s PASS 3 MIC AUDIO IN HI PASS 3 MIC AUDIO IN LO 39 40 PASS 3 MIC JACK s PASS 4 MIC AUDIO IN HI PASS 4 MIC AUDIO IN LO 41 42 PASS 4 MI
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GMA 35 Audio Panel L3 COMM P3501 ALERT 1 AUDIO IN HI ALERT 1 AUDIO IN LO 31 32 TEL AUDIO IN HI TEL AUDIO IN LO 25 26 TEL MIC OUT HI TEL MIC OUT LO 27 28 ALERT 4 (TEL RING) AUDIO IN HI 44 ALERT 2,3,4 AUDIO IN LO 43 3 4 KTA 870 KTA 970 TRC 497 TRC 899 KMH 880 KMH 980 P1 P1 J10 J10 92 90 s HONEYWELL 89 91 20 21 20 21 RYAN Traffic Advisory System GARMIN 9900B 9900BX P1 P1 3 4 3 4 GTX 330/ GTS 8XX GDL 88 33 P881 P8002 P3301 15 16 4 23 58 59 ALERT AUDIO OUT HI ALERT AUDIO OUT LO P
NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: 3 THE GMA 35 HAS 4 UNSWITCHED ALERT AUDIO INPUTS FOR ALERT AUDIO SOURCES SUCH AS TAWS OR TRAFFIC. 4 TO PREVENT COUPLED INTERFERENCE AND GROUND LOOPS FROM BEING INJECTED INTO THE AUDIO INPUTS, GROUND THE SHIELDS AT ONLY ONE END. EITHER END OF THE SHIELD MAY BE GROUNDED. 5 FOR REFERENCE ONLY. SEE THE G500 OR G600 STC INSTALLATION MANUAL FOR MORE DETAIL.
GMA 35 Audio Panel P3501 COM ACTIVE* OUT 24 4 P3502 MARKER HI SENS* IN 3 13 3 PASS ICS KEY* IN 14 PA MUTE* OUT 12 5 PA MODE SELECTED* OUT 19 6 3 COM CYCLE* IN 20 3 CLEARANCE RECORDER PLAYBACK* IN 22 NOTES: 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE SPECIFIED. 2 GROUND DESIGNATIONS: 3 THESE SWITCHES ARE SHOWN FOR REFERENCE ONLY. INSTALLATION OF THESE SWITCHES IS NOT COVERED BY THIS STC.
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Appendix G G.1 Lightning Protection Lightning Protection in Metal Aircraft G.1.1 HSDB Weather Radar Interface When interfacing the GTN 6XX/7XX to an HSDB weather radar (WXR), overbraid is required over any HSDB cabling in the radome area prior to entering the metal fuselage (or metallic wing). Any wiring for weather radar configuration modules does not require overbraid as part of this STC. This section describes how to install the overbraid for the WXR cabling.
CAUTION All overbraid ends must be secured outside the backshell by the strain relief bar. Failure to do so may allow overbraid ends to contact and short HSDB pins, resulting in weather radar malfunction or damage. 6. At the bulkhead end of the overbraid (or grounding provisions at the metallic wing entry area), comb out a maximum of two inches of braid, twist it, cut to length if necessary, and terminate it in a terminal lug. Refer to Figure G-1. 7. Secure the overbraid pigtail to a terminal stud. G.1.1.
OVERBRAID QQB575R30T0437 OR QQB575F36T0781 OVERBRAID INSTALLED OVER WEATHER RADAR CABLING THAT IS IN RADOME AREA, PRIOR TO ENTERING THE METAL FUSELAGE ELECTRICAL TIE-DOWN STRAP MS3367-{1, 2, or 7}-X OVERBRAID ENDS Ensure that the overbraid does not protrude more than ¼” past the strain relief bar into the backshell.
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BULKHEAD 1 2 2" MAXIMUM EXPOSED CABLE OVERBRAID WEATHER RADAR R/T MUST BE ELECTRICALLY BONDED TO BULKHEAD 1. 2. INSTALL 5/16" GROUNDING HARDWARE IN ACCORDANCE WITH AC 43.13-1B, SECTION 11-189. IF THERE IS AN EXISTING HOLE LOCATED IN AN APPROPRIATE AREA IT MAY BE UTILIZED FOR THE GROUNDING HARDWARE – OTHERWISE AN EXISTING FASTER (5/16" OR LARGER) MAY BE USED. IF THERE IS NO EXISTING HOLE OR SUITABLE FASTER USABLE FOR THIS PURPOSE THEN DRILL AND DE-BURR A 0.323"0.332" HOLE.
G.2 Lightning Protection for Nonmetallic Aircraft Table G-1 provides detailed information about the lightning protection components that are required for a particular aircraft model. Only nonmetallic models are listed. A ‘Y’ in the LRU column indicates that a TVS and fuse combination is required for that LRU; a ‘N’ indicates that the TVS and fuse combination is not required. The interconnect diagrams showing how the TVS and fuse are connected for a particular LRU are found in Appendix E.
Protection Required? Aircraft Make (TCDS Holder) [common name or previous make] Hawker Beechcraft (Hawker Beechcraft Corporation) [Beech Aircraft Company; Raytheon Aircraft Company] Hawker Beechcraft (Hawker Beechcraft Corporation) [Beech Aircraft Company; Raytheon Aircraft Company] Howard (Howard Aircraft Foundation) [Jobmaster Co] Liberty (Liberty Aerospace Incorporated) Maule (Maule Aerospace Technology, Inc.) Piper Aircraft, Inc. (Piper Aircraft, Inc.) [New Piper] Piper Aircraft, Inc.
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Appendix H Aircraft Model Specific Information Table H-1 provides additional limitations that are placed on some aircraft as a part of this STC. Table H-1. Aircraft Model Specific Information Aircraft Make (TCDS Holder) [common name or previous make] Aircraft Model Notes Air Tractor (Air Tractor, Inc.) AT-502, AT-502A, AT-502B, AT-802, AT-802A Must have optional radio box (P/N 60616-1) installed as a prerequisite for the installation of the GTN. [1] Diamond (Diamond Aircraft Industries, Inc.
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Appendix J Acceptable Hardware Screws, Non-Structural Size Type 6-32 8-32 - NASM35206 (MS35206) (AN515) Pan Head, Brass - NASM35214 (MS25214) (AN515B) Pan Head, Stainless - MS51957 (AN515C) Pan Head, Alloy Steel - NAS602 100 Deg Countersunk NASM24693 (MS24693) (AN507) - 100 Deg Countersunk, Alloy Steel NAS514P - Pan Head, Low Carbon Steel Note: Part numbers in parentheses are inactive or cancelled part numbers; these numbers may still be available and/or referenced on packaging mater
Washers, Stainless Steel Nominal Inside Diameter Size .016 Thick .032 Thick .063 Thick #6 NAS1149CN616R (AN960C-6L) NAS1149CN632R (AN960C-6) - #8 NAS1149CN816R (AN960C-8L) NAS1149CN832R (AN960C-8) - Note: Part numbers in parentheses are inactive or cancelled part numbers; these numbers may still be available and/or referenced on packaging material.
Nuts, Stainless Steel Size Type Nut, Self-locking Metal, Hex, Thin Nut, Self-locking Elastic, Hex, Thin Nut, Self-locking Metal, Hex Nut, Self-locking Elastic, Hex 6-32 NASM21043-06 NAS1291C06 (MS21043-06) NASM21083C06 (MS21083C06) (AN364C632A) NASM21046C06 MS20365C632C NAS1021C06 (MS21046C06) (AN363C632) MS20365C632A MS21044C06 (AN365C632A) 8-32 NASM21043-08 NAS1291C08 (MS21043-08) NASM21083C08 (MS21083C08) (AN364C832A) NASM21046C08 MS20365C832C NAS1021C08 (MS21046C08) (AN363C832) MS20365C832
Nutplates, Stainless Steel Size Type One Lug Fixed One Lug Floating Two Lug Fixed Two Lug Floating Corner Side-by-Side 6-32 MS21052 MS21054 MS21072 MS21062 MS21048 MS21050 MS21070 MS21060 MS21076 MS21056 MS21058 MS21074 MS21087 8-32 MS21052 MS21054 MS21072 MS21062 MS21048 MS21050 MS21070 MS21060 MS21076 MS21056 MS21058 MS21074 MS21087 GTN 6XX/7XX AML STC Installation Manual Page J-4 190-01007-A3 Rev.
