Installation manual

ManualsBrandsCanon ManualsDigital CameraCDI-E151-010

190-00356-02 October 2008 Rev. F

400W SERIES

INSTALLATION MANUAL

GPS 400W, GNC

420W/420AW, and GNS

430W/430AW

GNC and GNS are trademarks of Garmin Ltd. or its subsidiaries and may not be

used without the express permission of Garmin.

Garmin International, Inc.

Summary of content (232 pages)

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400W SERIES INSTALLATION MANUAL GPS 400W, GNC TM 420W/420AW, and GNS TM 430W/430AW GNC and GNS are trademarks of Garmin Ltd. or its subsidiaries and may not be used without the express permission of Garmin. Garmin International, Inc. 190-00356-02 October 2008 Rev.
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400W Series Installation Manual 190-00356-02 Rev.
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© Copyright 2006-2008 Garmin Ltd. or its subsidiaries All Rights Reserved Except as expressly provided herein, no part of this manual may be reproduced, copied, transmitted, disseminated, downloaded or stored in any storage medium, for any purpose without the express prior written consent of Garmin.
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Revision F Page Number(s) Section Number i 1-14 3-12 TOC 1.6.2 3.13.1 5-3 5.3.1 5-4 5-27 5-27 5-37 5-42/43 6-3 6-4 8-1 B-1 G-1 G-3 G-4 G-7 G-7 H-1 H-14 H-20 H-29 H-33 H-40 H-56 H-57 5.3.1 5.4.7 5.4.8 5.5.6.13 Checkout Log 6.1 6.2 8.4 B.2 G.2 G.3 G.6 G.13 G.14 H.1 App. H App. H App. H App. H App. H App. H App. H Description of Change Added warning about disposing of lithium batteries. Removed TAWS from deviation #4 of TSO-C146a Added caption “Table 3-7, Autopilot Coupling Limitations”.
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This manual reflects the operation of main software version 3.10. Some differences in operation may be observed when comparing the information in this manual to other software versions.
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TABLE OF CONTENTS PARAGRAPH 1. 1.1 1.2 1.3 1.4 1.5 1.6 1.7 1.8 1.9 2. 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.8 2.9 3. 3.1 3.2 3.3 3.4 3.5 3.6 3.7 3.8 3.9 3.10 3.11 3.12 3.13 4. 4.1 4.2 4.3 4.4 4.5 3H 4H 5H 6H 7H 8H 9H 10H 1H 12H 13H 14H 15H 16H 17H 18H 19H 20H 21H 2H 23H 24H 25H 26H 27H 28H 29H 30H 31H 32H 3H 34H 35H 36H 37H 38H 39H 40H 41H 42H Page ii Rev. F PAGE GENERAL DESCRIPTION ............................................................................................
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4.6 Serial Data................................................................................................................................... 4-12 4.7 COM/VOR/ILS Audio (GNC 420W and GNS 430W only) ...................................................... 4-16 4.8 VOR/ILS Indicator (GNS 430W Only) ...................................................................................... 4-18 4.9 RMI/OBI............................................................................................................
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E.3 Icarus Altitude Sentence .............................................................................................................. E-1 E.4 Shadin Fuel Flow Sentence.......................................................................................................... E-2 E.5 ARNAV / EI Fuel Flow Sentence................................................................................................ E-2 E.6 Shadin Fuel/Air Data Computer Sentence ...................................................
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LIST OF FIGURES Figure 2-1. GPS Antenna Installation Considerations .............................................................................. 2-5 Figure 2-2. Source Selection Annunciation Field of View ....................................................................... 2-9 Figure 2-3. GPS Navigation Annunciation Field of View...................................................................... 2-10 Figure 3-1. Coaxial Cable Installation .............................................................
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Figure H-12. Figure H-13. Figure H-14. Figure H-15. Figure H-16. Figure H-17. Figure H-18. Figure H-19. Figure H-20. Figure H-21. Figure H-22. Figure H-23. Figure H-24. Figure H-25. Figure H-26. Figure H-27. Figure H-28. Figure H-29. Figure H-30. Figure H-31. Figure H-32. Figure H-33. Figure H-34. Figure H-35. Figure H-36. Figure H-37. ARINC 429 Sandel EHSI Interconnect (One 400W Series Unit, One Sandel SN3308) . H-21 ARINC 429 Sandel EHSI Interconnect (Two GNS 430W, One Sandel SN3308)...........
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400W SERIES HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification (Mod) Levels for the GPS 400W, GNC 420W and GNS 430W. Mod Levels are listed with the associated service bulletin number, service bulletin date, and the purpose of the modification. The table is current at the time of publication of this manual (see date on front cover) and is subject to change without notice.
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1. GENERAL DESCRIPTION 0B 1.1 Introduction 8B This manual describes the physical, mechanical, and electrical characteristics, as well as instructions and other conditions and limitations for installation and approval of the 400W Series panel-mounted units. The 400W Series includes the GPS 400W, GNC 420W, GNC 420AW, GNS 430W, and GNS 430AW panel-mounted units. Refer to Section 7, Limitations for additional information and other considerations.
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1.2 Scope 9B The installation instructions and other data contained within this manual are FAA approved under 400W/500W Series AML STC SA01933LA, which is applicable for implementation within airplanes that are type certificated only under Civil Air Regulation 3 (CAR 3) or 14 Code of Federal Regulations (CFR) Part 23.
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CAUTION The GPS 400W Series product lens is coated with a special anti-reflective coating which is very sensitive to skin oils, waxes and abrasive cleaners. CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI-REFLECTIVE COATING. It is very important to clean the lens using a clean, lint-free cloth and an eyeglass lens cleaner that is specified as safe for anti-reflective coatings. CAUTION The use of ground-based cellular telephones while aircraft are airborne is prohibited by FCC rules.
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1.4.2 General Specifications 69B Operating Temperature Range -20°C to +55°C. For more details see Environmental Qualification Form on the Dealers Only page on www.garmin.com. See Appendix A for part numbers.
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1.4.3 GPS Specifications 70B Number Of Channels Frequency Sensitivity (Acquisition, No Interference) Sensitivity (Drop Lock) Dynamic Range Lat/Lon Position Accuracy Velocity TTFF (Time To First Fix) Reacquisition Position Update Interval 1 PPS (Pulse Per Second) Datum SATCOM Compatibility 15 (12 GPS and 3 GPS/WAAS/SBAS) 1575.42 MHz L1, C/A code -134.5 dBm GPS -135.5 dBm WAAS -144 dBm > 20 dB <1.25 meter RMS horizontal, <2 meter vertical, with WAAS 1000 knots maximum (above 60,000 ft) 1:45 min.
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1.4.4 COM Transceiver Specifications (GNC 420W and GNS 430W Only) ** 71B Audio Output Audio Response Audio Distortion AGC Characteristics Sensitivity Squelch Selectivity Spurious Response Modulation Frequency Band Transmitting Power Transmitter Duty Cycle Modulation Capability Carrier Noise Level Frequency Stability Demodulated Audio Distortion Sidetone Demodulated Audio Response 100 mW minimum into a 500 Ω load. Less than 6 dB of variation between 350 and 2500 Hz.
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1.4.5 VOR Specifications (GNS 430W Only) 72B Receiver Audio Sensitivity Course Deviation Sensitivity Flag AGC Characteristics Spurious Response VOR OBS Bearing Accuracy Audio Output Audio Response Audio Distortion 1.4.6 At -103.5 dBm (S+N)/N shall not be less than 6 dB. -103.5 dBm or less for 60% of standard deflection. The VOR Course Deviation Flag must be flagged: a) in the absence of an RF signal. b) in the absence of the 9960 Hz modulation.
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1.4.7 Glideslope Specifications (GNS 430W Only) 74B Sensitivity Centering Accuracy Selectivity Standard deflection Flag Page 1-8 Rev. F -87 dBm or less for 60% of standard deflection. 0 ± .0091 ddm or 0 ± 7.8 mV The course deviation shall be 0 ddm ± .0091ddm when using the Glideslope Centering Test Signal as the RF frequency is varied ±17 kHz from the assigned channel. At frequencies displaced by ±132 kHz or greater, the input signal is at least 60 dB down.
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1.4.8 GPS Antenna Requirements 75B Antenna performance is critical to the GPS/WAAS operation. The antennas listed in Table 1-2 and Table 1-3 are approved for installation with the 400W Series units with specified limitations. Refer to the following sections and tables for selection of the GPS/WAAS antenna. 320H 321H 1.4.8.
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1.4.8.2 Antennas With IFR GPS Operational Limitations 207B The list of TSO-C144 antennas shown in Table 1-3 allow the 400W Series models to meet TSO-C146a requirements with the operational limitations specified in the Limitations Section 7.1.1 of this manual. Table 1-3.
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1.5 License Requirements 12B The Telecommunications Act of 1996, effective February 8, 1996, provides the FCC discretion to eliminate radio station license requirements for aircraft and ships. The GNC 420W, GNC 420AW, GNS 430W and GNS 430AW installations must comply with current transmitter licensing requirements. In the US, to find out the specific details on whether a particular installation is exempt from licensing, please visit the FCC web site http://wireless.fcc.gov/aviation.
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1.6 Regulatory Compliance TSO Authorization and Advisory Circular Reference 1.6.1 13B 76B The conditions and tests required for TSO approval of this article are minimum performance standards. It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. TSO articles must have separate approval for installation in an aircraft.
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System Function Operating System GPS Navigation Information VOR Information LOC/Glideslope Information VHF Communication Display of altitude, heading, course, speed, and track Display of other information - moving map, terrain, flight plan overlay & flight mode, TAS/TIS traffic information, XM Weather data, data from passive lightning detection equipment, checklist & timer Terrain DO-178B Level B B C C C C D D NOTE Unauthorized changes or modifications to any 400W Series product may void the compliance to
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1.6.2 TSO Deviations 7B TSO TSO-C34e TSO-C36e TSO-C37d TSO-C38d TSO-C40c TSO-C113 TSO-C146a Page 1-14 Rev. F Deviation 1. Garmin was granted a deviation from TSO-C34e to use RTCA/DO-178B minimum software level C instead of RTCA/DO-178A level 2 to demonstrate compliance for the verification and validation of the computer software. 2.
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TSO C146a cont’d Deviation 7. Garmin was granted a deviation from TSO-C146a from RTCA/DO-229C paragraphs 2.1.1.10, 2.1.1.7, 2.1.1.8.1, 2.1.1.8.2, 2.1.1.9, 2.1.2.1, 2.1.3.1, 2.1.4.1.4, 2.1.4.1.5 and 2.1.5.1 in the form of an operational limitation to achieve an equivalent level of safety. The operational limitation is based on: a. The ability to use antennas that may not meet the minimum gain performance requirements of DO-228. b.
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1.6.4 ETSO Deviations 79B The GNS 400W Series meets the requirements of the listed ETSOs with the following deviations. ETSO Deviation ETSO-2C34f Garmin was granted a deviation from ETSO-2C34f to use RTCA/DO-160C instead of RTCA/DO-160D. ETSO-2C36f Garmin was granted a deviation from ETSO-2C36f to use RTCA/DO-160C instead of RTCA/DO-160D. ETSO-2C37e Garmin was granted a deviation from ETSO-2C37e to use RTCA/DO-160C instead of RTCA/DO-160D.
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1.7 Database Options and Updates 14B Aviation Database 1.7.1 81B The aviation database resides on a database card that is inserted in the left card slot on the unit front panel. The database is generated on periodic cycles from current Jeppesen data and converted to the format used by the 400W Series unit products.
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1.9 Limited Warranty 16B This Garmin product is warranted to be free from defects in materials or workmanship for two years from the date of purchase. For WAAS upgrade of this product, the warranty is separate and described in the service record or statement. Products bought through online auctions are not eligible for rebates or other special offers from Garmin. Online auction confirmations are not acceptable for warranty verification.
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2. INSTALLATION OVERVIEW 1B Introduction 2.1 17B Always follow acceptable avionics installation practices per AC 43.13-1B, AC 43.13-2A, or later FAA approved revisions of these documents. The GPS/WAAS installation instructions have been prepared to meet the guidance material contained in AC 20-138A “Airworthiness Approval of Global Navigation Satellite System (GNSS) Equipment”.
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2.2.3 IFR VOR/LOC/GS Installation 85B The minimum GNS 430W installation requires the following items for an IFR VOR/LOC/GS Installation: • GNS 430W (installed in the aircraft manufacturer approved location) • GPS antenna, VOR/LOC antenna, glideslope antenna, and COM antenna. • An External CDI/HSI indicator must be installed in the pilot’s primary field-of-view (or in the aircraft manufacturer approved mounting location).
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3. ARINC 429 from GTX 33/330 4. RS-232 FADC 2.3.3 Multiple Heading Sources 8B The 400W Series can accept heading data from an ARINC 429 INS/IRU, ARINC 429 EFIS, GAD 42, EHSI, GTX 33/330 transponder, ARINC 429 traffic advisory system, RS-232 FADC, and RS-232 WX-500 Stormscope®.
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2. The GPS antenna should be mounted in a location to minimize the effects of airframe shadowing during typical maneuvers. Typically mounting farther away from the tail section reduces signal blockage seen by the GPS antenna. 3a. The GPS antenna should be mounted no closer than two feet from any VHF COM antenna or any other antenna which may emit harmonic interference at the L1 frequency of 1575.42 MHz.
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Figure 2-1. GPS Antenna Installation Considerations 400W Series Installation Manual 190-00356-02 Page 2-5 Rev.
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2.4.3 VOR/LOC Antenna Location 91B The GNS 430W VOR/LOC antenna should be well removed from all projections, engines and propellers. It should have a clear line of sight if possible. The antenna must be mounted along the centerline of the aircraft, minimizing the lateral offset. 2.4.4 Glideslope Antenna Location 92B The GNS 430W Glideslope antenna should be well removed from all projections, engines and propellers. It should have a clear line of sight if possible. 2.4.
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2.5 Mounting Considerations 21B The 400W Series unit is designed to mount in the avionics stack in the aircraft instrument panel within view and reach of the pilot. The primary unit location should minimize pilot head movement when transitioning between looking outside of the cockpit and viewing/operating the 400W Series unit. The location should be such that the 400W Series unit is not blocked by the glare shield on top, or by the throttles, control yoke, etc. on the bottom.
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1. Determine the pilot’s primary view centerline, utilizing the following criteria: a) For aircraft with a basic “T” instrument configuration with the attitude indicator in the upper center location, the center of this instrument should be used as the primary view centerline.
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Figure 2-2. Source Selection Annunciation Field of View GPS Navigation Annunciation 2.5.1.2 209B Use the steps below to determine whether or not the integrated GPS navigation annunciation displayed on the 400W Series unit to be installed is within the acceptable field-of-view (see Figure 2-3): 37H 1. Determine the pilot’s primary view centerline, as defined in Step 1 of Section 2.5.1.1. 38H 39H 2.
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NOTE The entire annunciator unit must be within the acceptable field-of-view. The external GPS Navigation annunciator unit must contain, at a minimum, the following annunciations: • INTEG, INTG or LOI • TERM • APR • MSG • WPT Figure 2-3. GPS Navigation Annunciation Field of View Page 2-10 Rev.
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2.6 Cabling and Wiring Considerations 2B Wiring should be installed in accordance with AC 43.13-1B Chapter 11. For dual 400W Series unit installations, care should be taken to ensure separation between wires of redundant systems to reduce the possibility of loss of navigation due to a single event.
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2.9 Installation Approval Considerations 25B In most cases, AML STC SA01933LA only covers the interfaces in Appendix G. However, as described in the following sections, specific interfaces not listed in Appendix G can be approved under AML STC SA01933LA. 345H 346H 2.9.1 Autopilot Interface Approval 97B The 400W Series units have been approved to interface with a number of autopilots. Autopilots that will be coupled to GPS vertical guidance for GPS approaches must be specifically listed in Appendix G.
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2.9.3 Audio Panel Interface Approval 9B The 400W Series units have been approved to interface with a number of audio panels. However, audio panels not listed in Appendix G can still be approved under 400W/500W Series AML STC SA01933LA if all of the following conditions are met: 352H • The installation of the audio panel was previously FAA-approved; • The VHF COM audio and VHF NAV audio (if applicable) must be verified as described in sections 5.5.4 and 5.5.5.
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3. INSTALLATION PROCEDURES 2B 3.1 Unit and Accessories 26B The 400W Series units are available under the following part numbers: Table 3-1.
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3.2 Optional Accessories 27B GPS Antenna Options 3.2.1 10B For details regarding antenna selection, refer to Section 1.4.8. Once the antenna type is decided upon, refer to the information below for detailed parts information for antennas available directly from Garmin. Contact manufacturer directly for information on other antennas. Installation information for the antennas can be found in the appropriate installation manual listed in Section 3.5.
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3.2.2 GPS Antenna Doubler 10B If installing the antenna onto existing provisions a doubler may not be required. If installing the antenna using AML STC SA01695SE as the basis for approval, one of the following antenna doublers may be used: • Antenna doubler P/N 115-00846-00, for the GA 36 and GA 37 antennas. This doubler contains nut plates (qty. 4) for the antenna mounting screws. • Antenna doubler P/N 115-00846-10, for the GA 35 antenna. This doubler does not contain nut plates.
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3.6 Installation Materials Required but Not Provided 31B Optional Accessories Not Supplied (GNC 420W and GNS 430W Only) 3.6.1 103B The following installation accessories are required but not provided: ITEM COM Antenna VOR/LOC Antenna Glideslope Antenna Headphones Microphone REQUIREMENTS Shall meet TSO C37( ) and C38( ). Broad band, 50 Ω, vertically polarized with coaxial cable (GNC 420W and GNS 430W Only) Shall meet TSO C40( ) and C36( ).
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3.7 Special Tools Required 32B 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. Table 3-3.
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3.8 Cable Installation 3B 1. Route the coaxial cable to the rack location keeping in mind the recommendations of Section 2.6. Secure the cable in accordance with good aviation practice. 362H 2. Trim the coaxial cable to the desired length and install the BNC connector (330-00087-00) per the cabling instructions on Figure 3-1. If the connector is provided by the installer, follow the connector manufacturer’s instructions for cable preparation. 36H Figure 3-1.
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Table 3-4. Pin Contact Part Numbers 78-pin conn (P4001) 44-pin conn (P4006) Connector Type Wire Gauge High Density Pin Contact 22-24 AWG Garmin P/N 25-pin Connector (P4002) Shield Ground Connector Standard Density Socket Contact .
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3.9 Equipment Mounting 34B Rack Installation 3.9.1 105B Use the dimensions shown in Figure F-1 to prepare the mounting holes for the 400W Series unit. You may also use the 400W Series unit mounting rack itself as a template for drilling the mounting holes. 365H 1. The back plate of the rack may optionally be removed for ease of mounting in the aircraft panel. To do so, remove the two #4-40 screws, tilt the back plate away from the tray, and then slide the back plate to the side. 2.
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3.10 Antenna Installation and Connection 35B 3.10.1 GPS Antenna 108B This section provides information on the antenna cable installation. For mounting of the GPS Antenna refer to the Garmin GA Antenna AML STC SA01695SE. Refer to 2.4.1 herein for installation location considerations. 369H NOTE The internal 400W Series COM does not interfere with its own GPS receiver.
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3.10.2 COM Antenna 109B The 400W Series unit requires a standard 50Ω vertically polarized antenna. Follow the antenna manufacturer’s installation instructions for mounting the antenna. 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 2.4.2 for installation location considerations. 374H The antenna coax cable should be made of RG-142B, RG-400 or a comparable quality 50Ω coax.
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3.12 Electrical Load Analysis 37B An electrical load analysis should be completed on each aircraft prior to installation in accordance with AC 43.13-1B, Chapter 11. Use the following values for computation: Table 3-6. 400W Series Power Input Input Connector Mode GPS 400W Main power P4001 GNC 420W Main power COM power 14 VDC 28 VDC Typical Max Typical Max -- 760mA 1.4A 410mA 700mA P4001 P4002 -RX TX 1.12A 4mA 3.25A 2.5A 15mA 6.0A 560mA 8mA 1.6A 1.2A 15mA 3.
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3.13 AFMS Completion – Based on Autopilot Type 38B 3.13.1 Autopilot Listed in 400W/500W Series AML STC 1B For all autopilots listed in Section G.4, the appropriate limitations for that autopilot are identified in Table 3-7 and described in the paragraphs following the table. Table 3-7. Autopilot Coupling Limitations 37H 378H Section 4.
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AFMS Section 4.3 Autopilot Coupling Limitations This section of the AFMS contains four possible limitations: [1] This installation prompts the pilot and requires the pilot to enable the A/P outputs just prior to engaging the autopilot in APR mode. [2] This installation supports a seamless transition from digital (GPSS) to analog guidance for the autopilot.
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For all autopilots that are not listed in the 400W/500W Series AML STC, select the appropriate limitation as follows: Limitation [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 5.3.3. in the appropriate installation manual). NOTE The 400W/500W Series GPS SELECT discrete output is connected to the GPS Select input (or equivalent) on the autopilot.
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4. SYSTEM INTERCONNECTS 3B 4.1 4.1.
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Pin 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 Pin Name GPS RS-232 IN 3 MAIN OBI CLOCK MAIN OBI DATA MAIN OBI SYNC GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B GPS ARINC 429 IN 2 A GPS ARINC 429 IN 2 B RESERVED RESERVED GPS RS-232 OUT 4 GPS RS-232 IN 4 GPS RS-232 OUT 1 GPS RS-232 IN 1 GPS RS-232 OUT 2 GPS RS-232 IN 2 ALTITUDE COMMON (GROUND) ALTITUDE C4 ALTITUDE C2 ALTITUDE C1 ALTITUDE B4 ALTITUDE B2 AL
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4.1.
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4.1.3 P4006 NAV Connector (GNS 430W Only) 15B (View looking at rear of unit) 15 14 30 13 29 44 Pin 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 Page 4-4 Rev.
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4.2 Power, Lighting, and Antennas 40B This section covers the power input requirements, lighting bus input, and antenna connections. See Figure H-5 for interconnect information. 380H 4.2.
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4.3 Altitude Gray Code 41B Altitude input is useful for advisory vertical navigation (VNAV) calculations. Pin Name ALTITUDE D4 ALTITUDE A1 ALTITUDE A2 ALTITUDE A4 ALTITUDE B1 ALTITUDE B2 ALTITUDE B4 ALTITUDE C1 ALTITUDE C2 ALTITUDE C4 ALTITUDE COMMON Connector P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 Pin 70 69 68 67 66 65 64 63 62 61 60 I/O In In In In In In In In In In In These inputs are considered active if either the voltage to ground is <1.
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4.4 Main Indicator 42B Main Indicator Function 4.4.1 19B The Main Indicator displays both lateral and vertical deviation from selected course, To/From indications, lateral and vertical flags and superflags. The “CDI” key on the bezel of the GNS 430W takes the place of remote “NAV/GPS” switches, and is used to toggle between display of GPS and VOR/ILS navigation display on a remote indicator. The Navigation source is annunciated on the display above the ‘CDI’ key.
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4.4.2.4 Superflags 213B Pin Name MAIN LATERAL SUPERFLAG MAIN VERTICAL SUPERFLAG Connector P4001 P4001 Pin 17 18 I/O Out Out The output supplies not less than 500 mA on a 28 volt system and 250 mA on a 14 volt system with the output voltage not less than (AIRCRAFT POWER –1.5 VDC) when the flag is to be OUT OF VIEW. The output voltage with respect to ground is less than 0.25 VDC when the flag is to be IN VIEW. OBS 4.4.2.
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4.5 Annunciators/Switches 43B Annunciators/Switches Function 4.5.1 124B NOTE Installations in conformance with the requirements specified in this installation manual may not require the use of any external annunciators, since all annunciations are provided on the 400W Series front panel. Refer to Section 2.5.1 to determine whether or not external annunciators are required. 391H 4.5.1.1 Message Annunciate When a new status message is available, the Message Annunciator flashes.
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4.5.1.9 APPROACH ANNUNCIATE When performing approach navigation, the approach annunciator illuminates when approach is active. 23B 4.5.1.10 INTEGRITY ANNUNCIATE The integrity annunciator illuminates when the GPS receiver detects a position error, or is unable to calculate the integrity of the position. 24B 4.5.1.11 ILS/GPS APPROACH Output The ILS/GPS Approach Output sinks 500 mA when: 25B • GPS navigation is selected and either a GPS approach mode is active or 0.
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4.5.2 Annunciators/Switches Electrical Characteristics 125B 4.5.2.1 Annunciators 231B Pin Name VLOC ANNUNCIATE GPS ANNUNCIATE WAYPOINT ANNUNCIATE TERMINAL ANNUNCIATE APPROACH ANNUNCIATE MESSAGE ANNUNCIATE OBS ANNUNCIATE AUTO ANNUNCIATE INTEGRITY ANNUNCIATE GPS SELECT [1] ILS/GPS APPROACH Connector P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 Pin 1 2 3 4 5 6 7 8 9 13 14 I/O Out Out Out Out Out Out Out Out Out Out Out [1] The Operation of the GPS SELECT can be configured.
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4.6 Serial Data 4B Serial Data Function 4.6.1 129B 4.6.1.1 RS-232 234B The 400W Series unit is capable of interfacing with other aviation instruments by transmitting RS-232 Type 1 (often known as ARNAV format) and Type 2 (often known as Northstar format) data on the GPS RS-232 OUT 1 port.
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4.6.1.2 ARINC 429 The data output on the GPS ARINC 429 OUT port depends on the configuration (see Section 5.3.1). Below is a list of the configurations and the labels output for each one: 235B 398H 1. 2. 3. 4. 5. 6. 7. ARINC 429 GAMA 429 GAMA 429 Graphics GAMA 429 Graphics w/Int GAMA 429 Pro Line 21 GAMA 429 Sextant GAMA 429 Bendix King (Main software version 3.
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Label # 330 331 332 333 334 335 340 351G 352G 371G 377 Parameter Name Conic Arc Inbound Course Conic Arc Radius Conic Arc Course Change Angle Airport Runway Azimuth Airport Runway Length in Feet Left/Right Hand Holding Pattern Azimuth Left/Right Hand Procedure Turn Azimuth Distance To Destination (Via Flight Plan) Estimated Time To Destination (Via Flight Plan) Specific Equipment ID Equipment Hex ID Code 1 2 3 ● ● ● ● ● ● ● ● ● ● ● ● ● ● ● ● 4 ● ● ● ● ● ● ● ● ● ● ● 5 6 7 ● ● ● ● ● ● ● ● ● ● ● ● [1]
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4.6.2 Serial Data Electrical Characteristics 4.6.2.1 130B RS-232 236B Pin Name GPS RS-232 OUT 1 GPS RS-232 IN 1 GPS RS-232 OUT 2 GPS RS-232 IN 2 GPS RS-232 OUT 3 GPS RS-232 IN 3 GPS RS-232 OUT 4 GPS RS-232 IN 4 Connector P4001 P4001 P4001 P4001 P4001 P4001 P4001 P4001 Pin 56 57 58 59 41 42 54 55 I/O Out In Out In Out In Out In The RS-232 outputs conform to EIA Standard RS-232C with an output voltage swing of at least ± 5 V when driving a standard RS-232 load. ARINC 429 4.6.2.
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4.7 COM/VOR/ILS Audio (GNC 420W and GNS 430W only) 45B COM/VOR/ILS Audio Function 4.7.1 134B Activation of COM MIC KEY enables COM MIC AUDIO and causes the transceiver to transmit. 500Ω COM AUDIO and 500Ω VOR/ILS AUDIO are 100 mW audio outputs that are intended to drive a headset or an audio panel. Momentarily depressing the COM REMOTE TRANSFER button toggles the active and standby COM frequencies. Momentarily depressing the VLOC REMOTE TRANSFER button toggles the active and standby VLOC frequencies.
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4.7.2.3 COM AUDIO, VOR/ILS AUDIO 240B Pin Name 500Ω COM AUDIO HI 500Ω COM AUDIO LO 500Ω VOR/ILS AUDIO HI 500Ω VOR/ILS AUDIO LO Connector P4002 P4002 P4006 P4006 Pin 7 19 16 17 I/O Out Out Out Out 500Ω COM AUDIO and 500Ω VOR/ILS AUDIO each supply 100 mW into a 500 Ω load. These are balanced outputs and the LO output must be connected. 500Ω COM AUDIO is the summation of the COM receiver audio, COM sidetone audio, and INTERCOM MIC audio. DISCRETE INPUTS 4.7.2.
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4.8 VOR/ILS Indicator (GNS 430W Only) 46B VOR/ILS Indicator Function 4.8.1 139B NOTE Because the GNS 430W includes a “CDI” button that performs switching between GPS and VOR/ILS on a remote indicator, it is seldom necessary to use these outputs to drive an indicator. It is only necessary when it is desired for a separate indicator to display VOR/ILS deviation full-time (regardless of the “CDI” button status).
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4.8.2.4 Flag 245B Pin Name VOR/LOC +FLAG VOR/LOC -FLAG (VOR/LOC COMMON) GLIDESLOPE +FLAG GLIDESLOPE +DOWN/-FLAG (GLIDESLOPE COMMON) Connector P4006 P4006 P4006 P4006 Pin 3 4 30 31 I/O Out Out Out Out The Flag output is capable of driving up to three 1000 Ω meter loads. When valid information is present (Flag OUT OF VIEW) the Flag output is 375 ±80 mVDC. When invalid information is present (Flag IN VIEW) the Flag output is 0 ±25 mVDC. 4.8.2.
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4.9 RMI/OBI 47B RMI/OBI Function 4.9.1 14B The MAIN OBI output provides bearing information from the active waypoint for Bendix/King Serial OBI devices based upon the 400W Series unit’s GPS navigation. For the GNS 430W, the MAIN OBI output may be configured so that it sends VOR/ILS bearing information when VLOC is selected by the GNS 430W CDI key. The VOR OBI output provides bearing information from the currently tuned VOR station for Bendix/King Serial OBI devices based upon the GNS 430W VOR receiver.
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4.10 DME Tuning (GNS 430W Only) 48B 4.10.1 DME Tuning Function 149B The GNS 430W can channel a DME based on the tuned VLOC frequency. The GNS 430W outputs 2 of 5, BCD or Slip parallel DME and King Serial DME channeling format. When DME COMMON is held low, the GNS 430W actively tunes the DME. 4.10.2 DME Tuning Electrical Characteristics 150B 4.10.2.
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4.10.3 DME Tuning Configuration 15B Refer to Section 5.3.14 for the DME tuning configuration. 413H 4.10.4 DME Tuning Calibration and Checkout 152B None. 4.10.5 DME Tuning Interconnect References 153B Refer to Appendix H for interconnect information. 41H NOTE For the GNS 430W to tune a Narco DME 890 or IDME 891 or an ARC (Cessna) RTA-476A using parallel 2 of 5, unique wiring and configuration are required. Refer to 5.3.14 and Figure H-24. 415H Page 4-22 Rev.
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5. POST INSTALLATION CONFIGURATION & CHECKOUT PROCEDURES 4B Once the 400W Series unit has been installed, configure the unit for the particular installation and then complete the checkout procedures herein to verify proper operation. The steps that are not applicable to a particular installation may be skipped. A checkout log is included in Table 5-1 at the end of this section and is to be filled out during the checkout procedures.
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5.3.1 MAIN ARINC 429 CONFIG Page 154B Select the MAIN ARINC 429 CONFIG Page (see Figure 5-1). This page configures the GPS ARINC 429 output port, and the two GPS ARINC 429 input ports. The two input ports can each be configured independently for the desired function(s). 418H Figure 5-1. MAIN ARINC 429 CONFIG Page SPEED Selection Description Low Standard low-speed ARINC 429 (nominally 12.
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DATA IN 1, DATA IN 2 Selection Off Airdata Airdata/AHRS EFIS EFIS/Airdata Flight Control Garmin GAD 42 Garmin GDU [1] Garmin GTX 330 Honeywell EFIS INS/IRU RADAR Graphics Sandel EHSI Traffic Advisory Description No unit connected to this ARINC 429 input Altitude, temperature, and speed information from the following Air Data systems: B & D 2600, 2601, 2800, 90004-003 Bendix/King KAD 280/480, Shadin ADC 2000 Heading, altitude, temperature, and speed information from an Air Data/AHRS system.
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DATA OUT Selection [2] Off ARINC 429 GAMA 429 Description No unit(s) connected to ARINC 429 output Standard ARINC 429 output data (non-GAMA). ARINC 429 data as defined by the General Aviation Manufacturers’ Association (GAMA) General Aviation Subset, 2nd Edition.
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VNAV Selection Disable Labels Enable Labels 5.3.2 Description ARINC 429 labels associated with GPS-based vertical guidance (labels 117G and 327G) are not transmitted in the output data stream. ARINC 429 labels associated with GPS-based vertical guidance (labels 117G and 327G) are transmitted in the output data stream. ARINC 429 vertical guidance labels are used by the following systems: Sandel SN3500 Other systems may also use these labels.
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CHANNEL INPUTS Selection Off Arnav/ei-fuel Crossfill GDL 69 Icarus-alt Ryan TCAD Shadin-adc Shadin-alt Shadin-fadc Shadin-fuel WX-500 Page 5-6 Rev. F Description No unit(s) connected to input of this channel.
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CHANNEL OUTPUTS Selection Off Aviation Description No unit(s) connected to output of this channel Serial position, altitude, velocity, and navigation data to the following units: Argus 3000, 5000, or 7000 Moving Map Electronics International FP-5L Fuel Flow Computer (non-TSO’d) Garmin MX20 (V5.
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5.3.3 MAIN SYSTEM CONFIG 156B Select the MAIN SYSTEM CONFIG Page (see Figure 5-3). This page allows you to configure the Fuel, Terrain, and Discretes options. 42H Figure 5-3. MAIN SYSTEM CONFIG Page Fuel Select Fuel in the CONFIGURE field to select the FUEL TYPE (AV Gas, Jet A, or Jet B) Selection Description AV gas The aircraft is using Aviation gas (5.8 lbs./gal.) Jet A The aircraft is using Jet A or Jet A-1 fuel (6.7 lbs./gal.) Jet B The aircraft is using Jet B (JP-4) fuel (6.5 lbs./gal.
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Discretes Select Discretes in the CONFIGURE field to configure the operation of specific discrete outputs. Figure 5-5. MAIN SYSTEM CONFIG Page GPS Select Selection Auto Prompt Description When in GPS mode, the GPS Select discrete is unasserted (open) whenever a GPS approach mode is active – no associated messages appear and no pilot action is required. The pilot is also allowed to select automatic or manual GPS to ILS CDI transitions on the AUX CDI/ALARMS page.
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5.3.4 MAIN INPUTS 1 Page 157B Select the MAIN INPUTS 1 Page (see Figure 5-6). This page (along with the MAIN INPUTS 2 Page) allows you to monitor the data on ARINC 429, RS-232 and other electrical inputs. This is used for verifying electrical interfaces during installation and troubleshooting. Information that is not being received by the 400W Series unit is dashed out. 425H Figure 5-6. MAIN INPUTS 1 Page Field OAT SAT TAT IAS TAS WSPD HDG WDIR B ALT D ALT P ALT 5.3.
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5.3.6 INSTRUMENT PANEL SELF-TEST Page 159B Select the INSTRUMENT PANEL SELF-TEST Page (see Figure 5-8). This page allows verification that the 400W Series unit is communicating properly with other instruments. Compare on-screen indications with the information depicted on connected instruments, such as the CDI, HSI, RMI and/or external annunciators. It also displays fuel capacity, amount on-board, and flow. 427H Figure 5-8. INSTRUMENT PANEL SELF-TEST Page 5.3.
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SLOPE Sets the sensitivity of the display brightness in proportion to changes in the input level. The higher the number, the brighter the display is for a given increase in the input level. This field has a range of 0 (zero) to 99, and is set to 50 at the factory. OFFSET Adjusts the lighting level up or down for any given input level. This field has a range of 0 (zero) to 99, and is set to 50 at the factory. This may also be used to match lighting curves with other equipment in the panel. Figure 5-10.
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5.3.9 MAIN DISCRETE INPUTS Page 162B Select the MAIN DISCRETE INPUTS Page (see Figure 5-12) if the encoding altimeter input is used. Verify that the DECODED ALTITUDE field indicates the correct altitude. 431H GRAY CODE If the encoding altimeter input is used, verify that the DECODED ALTITUDE field indicates the correct altitude. Figure 5-12. MAIN DISCRETE INPUTS Page EXTERNAL SWITCH STATE This allows you to verify the operation of any external switches that are present in the installation.
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5.3.11 MAIN CDI/OBS CONFIG Page 164B Select the MAIN CDI/OBS CONFIG Page (see Figure 5-14). This page allows you to verify the MAIN CDI outputs, both lateral (LAT) and vertical (VERT), and verify and calibrate the MAIN OBS input. Using the controls on the 400W Series unit front panel, make the selections below and verify the interfaces as appropriate: 43H Figure 5-14.
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CDI (GNS 430W Only) Selection GPS VLOC Description The GNS 430W CDI button is in the GPS state, and the GPS ANNUNCIATE output is active. This annunciator output may be required to be active for some installations. The GNS 430W CDI button is in the VLOC state, and the VLOC ANNUNCIATE output is active. NOTE If it is desired to disable the GNS 430W CDI key, press MENU on the MAIN CDI/OBS CONFIG page and select “Ignore CDI Key?”.
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5.3.12 COM SETUP Page (GNC 420W and GNS 430W Only) 165B Select the COM SETUP Page (see Figure 5-15). These values are set at the factory and seldom require calibration. FREQ Selects a VHF communication frequency. For purposes of setting the squelch and sidetone levels, only the frequencies 118.000, 127.000, and 136.975 MHz can be used. SPACING 43H Figure 5-15. COM SETUP Page Selection Description 25.0 kHz Selects traditional 25 kilohertz spacing (760 channel). 8.33 kHz Selects 8.
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5.3.13 VOR DISCRETE INPUTS Page (GNS 430W Only) 16B Select the VOR DISCRETE INPUTS Page (see Figure 5-16). This page allows you to verify the operation of an external VLOC transfer switch that may be present in the installation. 435H Figure 5-16. VOR DISCRETE INPUTS Page Selection REMOTE XFR Verify That: The box is filled in while a remote VLOC transfer switch is pressed. 5.3.14 VOR/LOC/GS CDI Page (GNS 430W Only) 167B Select the VOR/LOC/GS CDI Page (see Figure 5-17).
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TO-FR (LAT) Selection FROM Hide TO Verify That: The FROM flag is in view. The TO/FROM flag is hidden. The TO flag is in view. SELECTED COURSE Select 150° on the CDI/HSI that is connected to the 400W Series VOR/LOC/GS OBS inputs. The SELECTED COURSE field should indicate near to 150° and a Calibrate to 150°? field appears. Selecting this field calibrates the 400W Series to match the input source.
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5.3.15 VOR/LOC/GS ARINC 429 CONFIG Page (GNS 430W Only) 168B Select the VOR/LOC/GS ARINC 429 CONFIG Page (see Figure 5-18). This page configures the VOR/ILS ARINC 429 output and input ports. 437H Figure 5-18. VOR/LOC/GS ARINC 429 CONFIG Page SPEED Selection Low High Description Standard low-speed ARINC 429 (nominally 12.
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5.3.16 GPS Vertical Offset 169B The GPS Vertical Offset setup function is used to enter the height above ground of the GPS antenna. Prior to proceeding, measure the GPS antenna vertical offset (to the nearest foot) as shown in Figure 5-19. 438H Figure 5-19. Measurement of GPS Vertical Offset Use the large and small knobs to enter the offset value and press ENT to save. Figure 5-20. GPS Vertical Offset Page Page 5-20 Rev.
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5.3.17 STORMSCOPE CONFIG Page 170B NOTE The Stormscope pages are only available if one of the RS-232 inputs is configured for the WX-500. Select the STORMSCOPE CONFIG Page (see Figure 5-21). This page shows the L3 Communications WX500 Stormscope configuration as reported by the WX500 through RS-232 data. 439H Verify that the STATUS field indicates “Ok”, and that the other displayed parameters are correct. Verify that all the boxes in the lower portion of the page are green.
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5.3.20 TRAFFIC Page 173B NOTE The following pages are only available if one of the RS-232 inputs is configured for the Ryan TCAD or one of the ARINC 429 inputs is configured for Traffic Advisory. Select the TRAFFIC Page (see Figure 5-24). This page shows the L3 Communications SkyWatch or Ryan TCAD modes of operation and current traffic situation. 42H For L3 Communications SkyWatch, this page shows: 1. The altitude mode—below (BLW), normal (NORM), above (ABV), or unrestricted (UNR) 2.
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5.3.21 RYAN TCAD CONFIG Page 174B Select the RYAN TCAD CONFIG Page (see Figure 5-26). This page shows the TCAD’s current shield settings for the selected mode, approach mode status, volume, mute status, mute duration, voice alert selection, and system status. 45H Verify that the TCAD system status is GREEN. Also, verify that shield settings and volume, mute duration, and voice alert selection can be modified. Verify that changes in mute (if a mute switch is installed) are shown.
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5.3.24 DATA LINK DIAGNOSTICS Page 17B The 8-character test word returned from the GDL 69 is displayed on the DATA LINK DIAGNOSTICS page for each of the following parameters: Figure 5-29. Data Link Diagnostics Display QOS TERR SAT1 SAT2 TUNER Page 5-24 Rev.
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5.4 Ground Checks (Configuration Mode) 52B Main Indicator (Analog Only) 5.4.1 178B NOTE If the GNS 400W Series unit is interfaced to an electronic HSI and the main indicator analog output is not used, this check is not required. If the GNS 400W Series unit is interfaced to an analog indicator on the main CDI/OBS, perform the following steps: 1. Go to the MAIN CDI / OBS CONFIG page. 2. Verify correct operation of the lateral deviation, flag and TO/FROM flag using the corresponding selections. 3.
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5.4.4 ADC, Altitude Encoder, Fuel Sensor and Fuel/Air Data Computer 18B NOTE This check does not apply to parallel connections to an altitude encoder. If the gray code interface to an altitude encoder is used, the check in Section 5.4.5 must be completed. 47H The GNS 400W Series unit can receive altitude or fuel/air data from an external source. This check verifies that the GNS 400W Series unit is receiving data from these units.
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5.4.6 AHRS/IRU Interface Check 183B The GNS 400W Series unit can receive heading data from an external source. This check verifies that the GNS 400W Series unit is receiving data from these units. Ensure that the GNS 400W Series unit is turned on and in configuration mode. If the following steps do not perform correctly, check the electrical connections and configuration setup. 1. Go to the Main Inputs 1 page.
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5.5 Ground Checks (Normal Mode) 53B Turn the 400W Series unit off and bring the unit back up in normal mode for the following checks. 5.5.1 Display of Self-Test Data 186B Following normal power-up, the Data Base Pages are displayed followed by the Instrument Panel SelfTest Page. Pressing the ENT key once then displays the Instrument Panel Self-Test page (see Figure 5-8). During this time, the electrical outputs are activated and set to the values listed below.
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5.5.2 Signal Acquisition Check 187B NOTE All other avionics should be turned off at the start of this test. Turn on the GNS 400W Series unit. Upon acknowledgement of the Instrument Panel Self-Test Page, the Satellite Status Page is displayed. If the unit is unable to acquire satellites, relocate the aircraft away from obstructions which might be shading GPS reception. If the situation does not improve, check the GPS antenna installation.
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Once the Signal Acquisition Test has been completed successfully, perform the following steps: 1. View the Satellite Status Page and verify that at least 7 satellites have been acquired on the 400W Series unit. 2. Verify that the GPS “INTEG” flag is out of view. 3. Select 121.150 MHz on the COM transceiver to be tested. 4. Transmit for a period of 35 seconds. 5. Verify that the GPS “INTEG” flag does not come into view. 6.
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5.5.4 VHF NAV Checkout (GNS 430W) 189B Press the CDI key to select VLOC mode (indicated by a white VLOC in the lower left corner 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. 5.5.5 VHF COM Checkout (GNC 420W/GNS 430W) 190B 5.5.5.
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5.5.6.2.1 One 400W Series Unit / One SN3308 26B 1. Cycle power to the GNS 400W Series unit and acknowledge the prompts until it gets to the self test page (see Section 5.5.1). 452H 2. Ensure that the SN3308 is receiving valid heading. NOTE The Vertical Deviation Indication will not be displayed unless the SN3308 is receiving valid heading. 3. While the GNS 400W Series unit is displaying the self test page, verify that the SN3308 is displaying the following data from the GPS source.
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5.5.6.2.2 Two 400W Series Units/One SN3308 267B The checkout for two 400W Series units also applies to one 400W Series unit and one 500W Series unit. 1. Remove power from the second (no. 2) 400W Series unit. 2. Cycle power to the first GNS 400W Series unit and acknowledge the prompts until it gets to the self test page (see Section 5.5.1). 453H 3. Select GPS1 as the navigation source by pressing the NAV key on the SN3308. 4. Ensure that the SN3308 is receiving valid heading.
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5.5.6.3 Sandel SN3500 Interface Check 25B IF a Sandel SN3500 EHSI has been connected to a 400W Series unit, the interface should be verified as follows: 1. Cycle power to the GNS 400W Series unit and acknowledge the prompts until it gets to the self test page (see Section 5.5.1). 45H 2. Ensure that the SN3500 is receiving valid heading. NOTE The Vertical Deviation Indication will not be displayed unless the SN3500 is receiving valid heading. 3.
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5.5.6.5 ARINC 429 Traffic System Interface Check 257B If an L3 Communications SKY497/SKY899 SkyWatch® sensor or a Honeywell (Bendix/King) KTA 810 TAS/KMH 820 IHAS has been connected to the GNS 400W Series unit, the traffic interface should be verified as described in this section. 1. Go to the Traffic page on the GNS 400W Series unit (in the NAV page group). 2. Verify that NO DATA is not displayed in yellow on the center of the traffic page. 3.
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NOTE The following sections only verify the correct interface of GDL 69/69A to the GNS 400W Series unit. It does not activate the GDL 69 XM data link radio. Complete instructions for activating the XM data link radio can be found in document 190-00355-04. XM Satellite Radio Weather Checkout Procedure 5.5.6.9.1 268B 1. With the 400W Series unit running in the normal mode, go to the XM Information page (in the AUX page group). 2. Verify that the DATA ID field has a valid ID and does not contain “---“.
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5.5.6.11.1 Main OBI Output 270B If the Main OBI output from the GNS 400W Series unit is connected to an RMI navigation indicator verify the interface as follows: 1. Apply power to the equipment and wait for the GNS 400W Series unit to acquire a position. 2. In the GNS 400W Series unit, set a course to a destination waypoint and ensure GPS is selected for display on the CDI. 3. If installed, set the RMI select switch to the GPS position. 4.
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5.6 Flight Checks 54B All system functions that cannot be adequately tested on the ground will require a flight test. Even if all functions can be verified on the ground, a flight test is recommended as final installation verification. Verify system operation as described in the following sections.
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5.6.4 ILS Flight Check (GNS 430W) 196B 1. Tune an ILS at the local airport. 2. Verify the audio ident and audio quality and verify that no objectionable electrical interference such as magneto noise is present. 3. Verify the Morse code decoder IDs the station (95% probability). 4. Fly the approach. 5. Verify NAV flag, GS flag, and CDI and VDI are operational. 5.6.5 Autopilot Flight Check 197B 1. Enter and activate a flight plan on the 400W Series unit.
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5.8 Airplane Flight Manual Supplement Checks 56B Ensure that the Airplane Flight Manual Supplement (AFMS) is completed and inserted in the Airplane Flight Manual (AFM) or Pilot’s Operating Handbook (POH). 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 type of GPS antenna that was installed. 3.
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Table 5-1. GNS 400W Series Post-Installation Checkout Log GNS 400W Series Post-Installation Checkout Log Date: ____ /____ /____ By: ________________ INSTALLATION INFORMATION: Aircraft Model ___________________________ Aircraft Serial # ______________ Unit P/N ________________________________ Mod Level __________________ Unit Model ______________________________ Serial # _____________________ GPS Antenna P/N _________________________ GPS Ant Model EXTERNAL ANNUNCIATION REQUIREMENT (See Section 2.
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CONFIGURATION ITEMS (CONT’D): VOR/LOC/GS CDI (GNS 430W only) DME Channel Mode: ___________________ VOR/LOC/GS ARINC 429 Configuration (GNS 430W only) RX Speed: High Low TX Speed: High Low SDI: GDL Configuration Attenuation: ______________ Model: GDL 69A GDL 69 [ N/A] Common VOR/ILS 1 VOR/ILS 2 DME Mode: Directed freq 1 Directed freq 2 After completing configuration and prior to checkout, restart unit for changes to take effect SYSTEM CHECKOUT Ground Checks (Configuration Mode) MA
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GROUND CHECKS (NORMAL MODE) SIGNAL ACQUISITION CHECK Position checked Signal reception checked Interference from other avionics checked VHF COM INTERFERENCE VHF COM interference checked VHF NAV CHECKOUT (GNS 430W ONLY) VOR reception checked Localizer reception checked Deviation needle and flag checked VHF COM CHECKOUT (420W and 430W) Receiver / Transmitter operation checked Antenna checked VSWR __________ INTERFACE CHECKS [ N/A] Honeywell EFS 40/50 [ N/A] Sandel SN3308 [ N/A] San
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6. TROUBLESHOOTING 5B This section provides information to assist troubleshooting if problems occur after completing the installation. Devices connected to the 400W Series unit can be useful for determining whether the 400W Series unit is functioning properly or if there are problems with the installation. 6.1 Troubleshooting Procedure 57B Table 6-1. Troubleshooting Guide Problem Possible Cause Solution The 400W Series unit does not power on.
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Table 6-1. Troubleshooting Guide Problem Possible Cause OBS Resolver won’t • Incompatible resolver or calibrate. improper connection. OBS indication on 400W Series unit does not agree with OBS setting. 400W Series unit is not receiving heading from compass system (ARINC 429 heading input used) Autopilot is not getting GPSS/Roll Steering data from the 400W Series unit (ARINC 429 Roll Steering used) • • 400W Series unit resolver input • not calibrated correctly. • Resolver has not been calibrated.
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Table 6-1. Troubleshooting Guide Problem RS-232 device is not communicating with the 400W Series unit. Possible Cause Solution • 400W Series unit RS-232 port not configured correctly. • Check RS-232 port setting for port that device is connected to. • Improper setup on the remote device. • Verify the configuration of the other device. • Device not compatible, or improper connection. • • Multiple TX lines connected together.
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6.2 Alert Text Troubleshooting Procedure 58B Table 6-2 is a list of alerts that are relevant to installers. There are additional messages in the 400W/500W Pilot’s Guide. If a message is displayed that is not in Table 6-2 or the Pilot’s Guide, please contact Garmin technical support. 46H 465H Table 6-2.
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Alert Text COM push-to-talk key stuck (430W only) Possible Cause • The external push-to-talk (PTT) switch is stuck in the enabled (or “pressed”) state. • Wiring is incorrect. Solution • Try pressing the PTT switch again to cycle its operation. COM remote transfer key is stuck (430W only) • The remote COM transfer switch is stuck in the enabled (or “pressed”) state. • Try pressing the switch again to cycle its operation. • Verify the wiring is correct.
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Alert Text G/S is not responding (430W only) • G/S needs service (430W only) • GAD configuration required • GAD needs service • GDL 69 is not responding • Possible Cause Internal system-to-system communication between the main processor and the glideslope receiver has failed. Operational status of the glideslope receiver is unknown. The unit has detected a failure in its glideslope receiver. The glideslope receiver may still be usable.
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Alert Text Loss of integrity — cross-check NAV Possible Cause • Improper antenna installation or coax routing • Antenna shaded from satellites • RF interference at 1575.42 MHz from VHF COM. Low Battery - Unit Needs Service • Time data may have been lost due to a memory battery failure. MAIN processor requires service • The 400W-series unit has detected a failure in the main system processor.
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Alert Text OBS not available RAIM position warning Searching the sky Stored data was lost TERRAIN configuration has changed Possible Cause • No destination waypoint has been selected. • The GPS receiver cannot currently determine its position. • Although sufficient GPS satellite coverage may exist, Receiver Autonomous Integrity Monitoring (RAIM) has determined the information from one or more GPS satellites may be in error. • The 400W Series unit is searching the sky for GPS satellites.
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Alert Text Possible Cause VLOC needs service (430W only) • The unit has detected a failure in its VLOC receiver. The VLOC receiver may still be usable. VLOC remote transfer key is • The remote VLOC transfer stuck (430W only) switch is stuck in the enabled (or “pressed”) state. Solution • Contact Garmin technical support. • Try pressing the switch again to cycle its operation. • Contact Garmin technical support. • Try pressing the VLOC flip-flop key again to cycle its operation.
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7. LIMITATIONS 6B 7.1 Operations 60B There are no Part 23 aircraft type limitations. All functions of the 400W Series unit meet the appropriate design assurance qualifications for primary or secondary for airplane Class I, Class II, Class III, and Class IV in accordance with AC 23.1309-1C Figure 2. The TSO authorizations with the RTCA/DO178B software levels by function are listed in Table 1-4. 46H 7.1.
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7.1.2 Safety Assessment Considerations 20B This STC requires that the modified aircraft meet navigation and communication availability requirements at the aircraft level appropriate to the failure condition category, aircraft category and class. TSO-C146a defines loss of function of en route, terminal, non-precision approach, or precision approach navigation data as a major failure condition. AC 23.
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7.3 Rotorcraft Installation 62B The installation and operational approval for use of a 400W Series unit in rotorcraft is not covered by AML STC SA01933LA; however, instructions and data provided in this manual may be used to perform the alteration and obtain other FAA approval. The 400W Series unit TERRAIN functionality is not recommended for use in rotorcraft. 7.4 Aircraft Radio Station License 63B An aircraft radio station license is not required when operating in U.S.
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8. PERIODIC MAINTENANCE 7B 8.1 Equipment Calibration 64B No scheduled servicing tasks are required on the 400W Series unit. 8.2 VOR Checks 65B Refer to CFR 14 paragraph 91.171. Every 30 days verify the limits of the permissible indicated bearing error. 8.3 Cleaning 6B The front bezel, keypad, and display can be cleaned with a soft cotton cloth dampened with clean water. DO NOT use any chemical cleaning agents. Care should be taken to avoid scratching the surface of the display. 8.
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Appendix A ENVIRONMENTAL QUALIFICATION FORM 27B For RTCA/DO-160D Environmental Qualification Forms (EQFs) visit the Dealers Only page on http://www.garmin.com. The part numbers for each form are listed below. Table A-1. Environmental Qualification Form Part Numbers Unit GPS 400W GNC 420W GNC 420AW GNS 430W GNS 430AW 400W Series Installation Manual 190-00356-02 EQF Part Number 005-00221-08 005-00221-47 005-00221-48 005-00221-49 005-00221-50 Page A-1 Rev.
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Appendix B STC DATA 273B B.1 STC Information The 400W/500W Series STC SA01933LA with Approved Model List (AML) and Master Data List (P/N 005-C0221-00) information is available on the Garmin web site at www.garmin.com and can be downloaded from the Dealers Only page. B.2 Permission to use STC Consistent with Order 8110.4B and AC 21-40, a permission letter to use this STC data is available for download on the Dealers Only portion of the Garmin website at www.garmin.com. B.
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Appendix C RESERVED 274B 400W Series Installation Manual 190-00356-02 Page C-1 Rev.
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Appendix D 400W SERIES RS-232 AVIATION DATA FORMAT 275B D.1 Electrical Interface The output signals are compatible with RS-232C. Data is generated at 9600 baud with a word length of 8 bits, one stop bit, and no parity. D.
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Table D-1 describes the Type 1 output sentence item designator (id) and item data (dddd) fields. If data for these sentences is invalid or unavailable, dashes ("-") are used to fill in all non-blank character positions. Table D-1.
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D.
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Table D-2 describes the Type 2 output sentence item designator (id), sequence number (seq), waypoint identifier (wpt), waypoint latitude (lat), waypoint longitude (lon), and magnetic variation at waypoint (mvar) fields. Table D-2.
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Appendix E 400W SERIES RS-232 FUEL/AIR DATA INPUT FORMAT 276B E.1 Electrical Interface The input signals are compatible with RS-232C. Data input is at 9600 baud with a word length of 8 bits, one stop bit, and no parity. One message is received per second. E.
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E.4 Shadin Fuel Flow Sentence The Garmin 400W Series units are capable of receiving the following 55-byte message from the Shadin Fuel Flow Indicator: K0543.20100.00040.00060.00123.40045.40078.0123 Where: start-transmit character (0x02) K units designation (i.e., Gallons, Liters, Kilograms, B[pounds]) 0543.2 total fuel remaining (i.e., ASCII-coded decimal format: 0x30, 0x35, 0x34, 0x33, 0x2e, 0x32) space (0x20) 0100.
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E.
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SHADIN “G” FORMAT GA012 "GA" (ASCII characters); "012" represents indicated Air Speed (knots) GB345 "GB" (ASCII characters); "345" represents true Air Speed (knots) GC678 "GC" (ASCII characters); "678" represents Mach Speed (thousandths) GD<+/->9012 "GD" (ASCII characters); sign; "9012" represents pressure altitude (tens of feet) GE<+/->3456 "GE" (ASCII characters); sign; "3456" represents density altitude (tens of feet) GF<+/->78 "GF" (ASCII
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SHADIN “S” FORMAT SA012 "SA" (ASCII characters); "012" represents indicated Air Speed (knots) SB345 "SB" (ASCII characters); "345" represents true Air Speed (knots) SC678 "SC" (ASCII characters); "678" represents Mach Speed (thousandths) SD<+/->9012 "SD" (ASCII characters); sign; "9012" represents pressure altitude (tens of feet) SE<+/->3456 "SE" (ASCII characters); sign; "3456" represents density altitude (tens of feet) SF<+/->78 "SF" (ASCII
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Appendix F MECHANICAL DRAWINGS 27B F.1 Drawing List The following drawings are included in this section. Figure F-1. Figure F-2. Figure F-3. Figure F-4. Figure F-5. 472H 473H 47H 476H 475H 400W Series Mounting Rack Dimensions GNS 430W Mounting Rack Installation GNC 420W Mounting Rack Installation GPS 400W Mounting Rack Installation 400W Series Recommended Panel Cutout Dimensions 400W Series Installation Manual 190-00356-02 Page F-1 Rev.
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DIMENSIONS MODEL A B GPS 400W 2.85 [72.4] 4.6 [117] C 1.2 [30.5] GNC 420W 3.05 [77.5] 4.8 [122] 1.3 [33] GNS 430W 3.05 [77.5] 4.9 [124] 1.4 [35.6] Figure F-1. 400W Series Mounting Rack Dimensions 400W Series Installation Manual 190-00356-02 Page F-3 Rev.
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Figure F-2. GNS 430W Mounting Rack Installation Page F-4 Rev.
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Figure F-3. GNC 420W Mounting Rack Installation 400W Series Installation Manual 190-00356-02 Page F-5 Rev.
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Figure F-4. GPS 400W Mounting Rack Installation Page F-6 Rev.
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Figure F-5. 400W Series Recommended Panel Cutout Dimensions 400W Series Installation Manual 190-00356-02 Page F-7 Rev.
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Appendix G APPROVED EQUIPMENT 278B The following tables list equipment that can be interfaced with the Garmin 400W Series units. This is not a complete listing however; it only represents those units that are approved under 400W/500W Series AML STC SA01933LA, with any exceptions noted by the appropriate table. When installing equipment on the aircraft always refer to the manufacturers’ documentation for complete pinout and interconnect information. G.
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G.3 Altitude Serializer or Fuel/Air Data Altitude serializers/encoders not listed below can still be approved under 400W/500W Series AML STC SA01933LA 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 5.4.4 (serial interface) or 5.4.
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G.4 Autopilots Autopilots that will be coupled to GPS vertical guidance for GPS approaches must be specifically listed in the table below.
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G.5 Encoding Altimeter or Blind Encoder (Gray Code) Encoding altimeters or blind encoders not listed below can still be approved under 400W/500W Series AML STC SA01933LA if all of the following conditions are met: • The altitude encoding altimeter / encoder is TSO approved; • The installation of the altitude encoder was previously FAA-approved; • The interface check for the altitude encoder described in section 5.4.4 (serial interface) or 5.4.
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G.8 IRU/AHRS Manufacturer Honeywell (Bendix/King) Collins Honeywell (Bendix/King) Litef Litton G.
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G.11 DME Manufacturer ARC Honeywell (Bendix/King) Collins S-TEC Narco Model RTA-476A KN61 KN62/62A KN63/KDI 572/KDI 574 KN64 KN65 KDM 706/KDI 572/KDI 574 DME 40 DME 42 TCR-451 DME 890 IDME 891 Data Format Notes Parallel Slip Code Parallel 2x5 or King Serial King Serial King Serial Parallel Slip Code King Serial Parallel 2x5 Parallel 2x5 Parallel 2x5 Parallel 2x5 G.
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G.13 Multifunction Displays Manufacturer Model Data Format MX20 RS-232 GMX 200 RS-232 Garmin Avidyne EX500 P/N 700-00007-( ) EX5000 P/N 700-00004-( ) or P/N 700-00030-( ) ARINC 429 ARINC 429 Notes “Avtn no alt” format for MX20 version 5.5 and earlier. “Aviation” format for MX20 version 5.6 and later. (MX20 will not accept GPS altitude even though it is part of “Aviation” format). “MapMX” format for MX20 version 5.6 or later.
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Appendix H STC APPROVED INSTALLATION DIAGRAMS 279B H.1 Introduction The equipment interconnect diagrams defined in this appendix are approved per the 400W/500W Series unit AML STC SA01933LA. H.2 Drawing List The following drawings are included in this section: Figure H-1. 400W Series System Interface Diagram Figure H-2. GNS 430W Typical Installation Figure H-3. GNC 420W Typical Installation Figure H-4. GPS 400W Typical Installation Figure H-5. Power, Lighting, and Antenna Interconnect Figure H-6.
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Figure H-1. 400W Series System Interface Diagram 400W Series Installation Manual 190-00356-02 Page H-3 Rev.
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Figure H-2. GNS 430W Typical Installation Sheet 1 of 2 Page H-4 Rev.
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Figure H-2. GNS 430W Typical Installation Sheet 2 of 2 400W Series Installation Manual 190-00356-02 Page H-5 Rev.
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Figure H-3. GNC 420W Typical Installation Sheet 1 of 2 Page H-6 Rev.
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Figure H-3. GNC 420W Typical Installation Sheet 2 of 2 400W Series Installation Manual 190-00356-02 Page H-7 Rev.
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Figure H-4. GPS 400W Typical Installation Sheet 1 of 2 Page H-8 Rev.
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Figure H-4. GPS 400W Typical Installation Sheet 2 of 2 400W Series Installation Manual 190-00356-02 Page H-9 Rev.
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Figure H-5. Power, Lighting, and Antenna Interconnect Sheet 1 of 3 Page H-10 Rev.
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Figure H-5. Power, Lighting, and Antenna Interconnect Sheet 2 of 3 400W Series Installation Manual 190-00356-02 Page H-11 Rev.
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Figure H-5. Power, Lighting, and Antenna Interconnect Sheet 3 of 3 Page H-12 Rev.
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Figure H-6. Gray Code Altimeter Interconnect 400W Series Installation Manual 190-00356-02 Page H-13 Rev.
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Figure H-7. Main Indicator Interconnect Page H-14 Rev.
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Figure H-8. KI 209A Main Indicator Interconnect 400W Series Installation Manual 190-00356-02 Page H-15 Rev.
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Figure H-9. KI 208A Main Indicator Interconnect Page H-16 Rev.
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Figure H-10. RS-232 Serial Data Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-17 Rev.
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Figure H-10. RS-232 Serial Data Interconnect Sheet 2 of 2 Page H-18 Rev.
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Figure H-11. ARINC 429 EFIS Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-19 Rev.
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H-11. ARINC 429 EFIS Interconnect Sheet 2 of 2 Page H-20 Rev.
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Figure H-12. ARINC 429 Sandel EHSI Interconnect (One 400W Series Unit, One Sandel SN3308) Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-21 Rev.
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Figure H-12. ARINC 429 Sandel EHSI Interconnect (One 400W Series Unit, One Sandel SN3308) Sheet 2 of 2 Page H-22 Rev.
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Figure H-13. ARINC 429 Sandel EHSI Interconnect (Two GNS 430W, One Sandel SN3308) Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-23 Rev.
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Figure H-13. ARINC 429 Sandel EHSI Interconnect (Two GNS 430W, One Sandel SN3308) Sheet 2 of 2 Page H-24 Rev.
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THE TWO GNS 430W/TWO SN3308s CONFIGURATION IS CURRENTLY NOT SUPPORTED Figure H-14. ARINC 429 Sandel EHSI Interconnect (Two GNS 430W, Two Sandel SN3308) 400W Series Installation Manual 190-00356-02 Page H-25 Rev.
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Figure H-15. ARINC 429/RS-232 Air Data/IRU/AHRS Interconnect Sheet 1 of 2 Page H-26 Rev.
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Figure H-15. ARINC 429/RS-232 Air Data/IRU/AHRS Interconnect Sheet 2 of 2 400W Series Installation Manual 190-00356-02 Page H-27 Rev.
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Figure H-16. Traffic Advisory System Interconnect Sheet 1 of 2 Page H-28 Rev.
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Figure H-16. Traffic Advisory System Interconnect Sheet 2 of 2 400W Series Installation Manual 190-00356-02 Page H-29 Rev.
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Figure H-17. GTX 330 Interconnect Page H-30 Rev.
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Figure H-18. Weather and Terrain Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-31 Rev.
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Figure H-18. Weather and Terrain Interconnect Sheet 2 of 2 Page H-32 Rev.
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Figure H-19. Audio Panel Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-33 Rev.
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Figure H-19. Audio Panel Interconnect Sheet 2 of 2 Page H-34 Rev.
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Figure H-20. VOR/ILS Indicator Interconnect 400W Series Installation Manual 190-00356-02 Page H-35 Rev.
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Figure H-21. RMI/OBI Interconnect Page H-36 Rev.
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Figure H-22. King Serial Panel DME Tuning Interconnect 400W Series Installation Manual 190-00356-02 Page H-37 Rev.
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Figure H-23. King Serial Remote DME Tuning Interconnect Page H-38 Rev.
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Figure H-24. Parallel 2 of 5 DME Tuning Interconnect 400W Series Installation Manual 190-00356-02 Page H-39 Rev.
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Figure H-25. Bendix/King Analog Autopilot Interconnect Page H-40 Rev.
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` Figure H-26. Century Autopilot Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-41 Rev.
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{ } Figure H-26. Century Autopilot Interconnect Sheet 2 of 2 Page H-42 Rev.
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Figure H-27. S-TEC Autopilot Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-43 Rev.
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Figure H-27. S-TEC Autopilot Interconnect Sheet 2 of 2 Page H-44 Rev.
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Figure H-28. ARINC 429 Sandel EHSI Interconnect (One 400W, One Sandel SN3500) Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-45 Rev.
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Figure H-28. ARINC 429 Sandel EHSI Interconnect (One 400W, One Sandel SN3500) Sheet 2 of 2 Page H-46 Rev.
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EXTERNAL NAVIGATION SOURCE SELECTION ANNUNCIATORS STACO INDICATOR CONNECTION GARMIN 400W/420W/430W P4001 VLOC ANNUNCIATE P1 1 N/C GPS ANNUNCIATE 2 VLOC (W) 5 P1 2 3 9 6 11 12 (WHITE) VLOC (GREEN) GPS 3 4 LAMP VOLTAGE FROM DIMMER CIRCUIT GPS (G) NAV/GPS INDICATOR VIVISUN INDICATOR CONNECTION GARMIN 400W/420W/430W P4001 VLOC ANNUNCIATE 1 P1 VLOC (W) C 6 P1 2 D VLOC (GREEN) GPS 4 B LAMP VOLTAGE FROM DIMMER CIRCUIT G GPS ANNUNCIATE (WHITE) A GPS (G) NAV/GPS INDICATOR VIV
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EXTERNAL GPS ANNUNCIATIONS MID-CONTINENT ACU CONNECTION GARMIN 400W/420W/430W P4001 VLOC ANNUNCIATE 1 GPS ANNUNCIATE 2 WAYPOINT ANNUNCIATE 3 TERMINAL ANNUNCIATE 4 APPROACH ANNUNCIATE 5 MESSAGE ANNUNCIATE 6 OBS ANNUNCIATE 7 INTEGRITY ANNUNCIATE 9 OBS MODE SELECT 71 CDI SOURCE SELECT 73 8 MID-CONTINENT MD41-xxxx -1484W -1404A/1408A -1464A/1474A -1488W -1414A/1418A -1468A/1478A J1 J1 J1 7 8 2 4 6 3 1 - 8 3 9 10 24 20 12 - 2 1 8 3 9 10 24 20 12 4 MD41-14xx GPS ACU 1470 J1 2 1 8 3 9 10 24 20 12 - VLOC A
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Figure H-30. Parallel Slip Code DME Tuning Interconnect 400W Series Installation Manual 190-00356-02 Page H-49 Rev.
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Figure H-31. Cessna Autopilot Interconnect Page H-50 Rev.
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Figure H-32. Bendix Autopilot Interconnect 400W Series Installation Manual 190-00356-02 Page H-51 Rev.
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Figure H-33. Switches Interconnect Page H-52 Rev.
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Figure H-34. ARINC 429 Avidyne PFD/MFD Interconnect Sheet 1 of 2 400W Series Installation Manual 190-00356-02 Page H-53 Rev.
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Figure H-34. ARINC 429 Avidyne PFD/MFD Interconnect Sheet 2 of 2 Page H-54 Rev.
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- - - - - - - - - COLLINS Figure H-35. Collins Autopilot Interconnect 400W Series Installation Manual 190-00356-02 Page H-55 Rev.
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Figure H-36. Garmin GAD 42 Interconnect Page H-56 Rev.
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Figure H-37. Garmin G600 Interconnect 400W Series Installation Manual 190-00356-02 Page H-57 Rev.
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