400 SERIES INSTALLATION MANUAL GPS 400, GNC TM 420 (A), and GNS TM 430 (A) GNC and GNS are trademarks of Garmin Ltd. or its subsidiaries and may not be used without the express permission of Garmin. (GNS 430 Shown) £ Garmin International, Inc. 1200 E.
© Copyright 1998 - 2002 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.
This manual is written for software version 3.00, and is not suitable for earlier software versions. Information in this document is subject to change without notice. Visit the Garmin web site (www.garmin.com) for current updates and supplemental information concerning the operation of this and other Garmin products.
TABLE OF CONTENTS 1. GENERAL DESCRIPTION 1.1 INTRODUCTION .........................................................................................................................................1-1 1.2 EQUIPMENT DESCRIPTION......................................................................................................................1-1 1.3 TECHNICAL SPECIFICATIONS.................................................................................................................1-2 1.
LIST OF FIGURES FIGURE 2-1. GPS ANTENNA AND UNIT INSTALLATION CONSIDERATIONS .............................................2-2 FIGURE 3-1. FIGURE 3-2. FIGURE 3-3. FIGURE 3-4. FIGURE 3-5. FIGURE 3-6. FIGURE 3-7. FIGURE 3-8. FIGURE 3-9. COAXIAL CABLE INSTALLATION ................................................................................................3-5 GA 56 ANTENNA INSTALLATION DRAWING .............................................................................3-9 GNS 430 MOUNTING RACK DIMENSIONS .
LIST OF FIGURES - CONTINUED FIGURE 5-1. MAIN ARINC 429 CONFIG PAGE ....................................................................................................5-1 FIGURE 5-2. MAIN RS232 CONFIG PAGE ............................................................................................................5-3 FIGURE 5-3. MAIN INPUTS 1 PAGE ......................................................................................................................5-4 FIGURE 5-4. MAIN INPUTS 2 PAGE .........
400 SERIES HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification (Mod) Levels for the GPS 400, GNC 420 and GNS 430. 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.
This page intentionally left blank Page vi Page Rev L 400 SERIES INSTALLATION MANUAL P/N 190-00140-02
1. GENERAL DESCRIPTION 1.1 INTRODUCTION This manual describes the physical, mechanical, and electrical characteristics and the installation requirements for the 400 Series (GPS 400, GNC 420, and GNS 430) Panel-mounted units. After installation of the 400 Series system, FAA Form 337 must be completed by an appropriately certificated agency to return the aircraft to service. 1.2 EQUIPMENT DESCRIPTION The 400 Series units are mark width (6.25” wide) units, and 2.66” high.
1.3 TECHNICAL SPECIFICATIONS The conditions and tests required for TSO approval of the 400 Series are minimum performance standards. It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards. The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the administrator.
1.3.
1.3.
1.3.5 VOR Specifications (GNS 430 Only) Regulatory Compliance Receiver Audio Sensitivity Course Deviation Sensitivity Flag AGC Characteristics Spurious Response VOR OBS Bearing Accuracy Audio Output Audio Response Audio Distortion TSO C40c, JTSO-2C40c, RTCA DO-196, EuroCAE ED-22B 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.
1.3.6 LOC Specifications (GNS 430 Only) Regulatory Compliance Receiver Audio Sensitivity Course Deviation Sensitivity Flag AGC Characteristics Selectivity Spurious Response Centering Accuracy Audio Output Audio Response Audio Distortion 1.3.7 TSO C36e, JTSO-C36e, RTCA DO-195 CLASS A, EuroCAE ED-46B 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 LOC Course Deviation Flag must be flagged: a) in the absence of an RF signal.
1.4 LICENSE REQUIREMENTS The following guidance is provided to help ensure the proper licensing of the GNC 420/GNS 430 COM: 1. The Telecommunications Act of 1996 effective February 8, 1996 provides the FCC discretion to eliminate radio station license requirements for aircraft. At present, an individual license to operate the 400 Series aboard a private aircraft is not needed in many circumstances. Please see FCC Fact Sheet PR5000 or contact the FCC at 1-800-322-1117 for more information. 2.
The FDE function is built into the GPS 400/GNC 420/GNS 430 and does not require pilot interaction. In contrast, the FDE Prediction Program does require pilot interaction and must be used prior to oceanic/remote area flights to predict FDE availability. The 400 Series Trainer software (Garmin Part Number 190-00176-00) includes an FDE Prediction Program to meet the requirements for GPS as a primary means of navigation for oceanic/remote operations per N8110.60.
2. INSTALLATION 2.1 INTRODUCTION Careful planning and consideration of the suggestions in this section are required to achieve the desired performance and reliability from the 400 Series unit. Any deviations from the installation instructions prescribed in this document shall be accomplished in accordance with the requirements set forth in FAA AC 43.13-2A, and 14 CFR Part 43 Maintenance, Preventive Maintenance, Rebuilding, and Alteration. 2.
2.2.6 ANTENNA LIMITATIONS Garmin’s GA 56 Antennas are recommended for installations where the airspeed of the aircraft is subsonic. In such installations, GA 56—Mod 1 or later—must be used. See the COM, VOR/LOC, and Glideslope antenna specifications for their limitations. 2.2.7 VHF COM INTERFERENCE OF GPS On many panel-mounted installations, VHF COM transceivers can radiate strong harmonics from the transceiver and its antenna. The 400 Series COM does not interfere with its own GPS section.
2.2.8 COM, VOR/LOC, and Glideslope Antenna Installation Instructions Install the COM, VOR/LOC, and Glideslope antennas according to the manufacturer’s recommendations. Avoid running other wires and coaxial cables near the VOR/LOC antenna cable. 2.3 RACK CONSIDERATIONS Plan a location which gives the pilot complete and comfortable access to the entire keypad and which is plainly visible from the pilot’s perspective.
Qualified GPS Antenna This antenna must be one of those listed in the accessories list, or meet the following requirements: 1. DO-160C Environmental Conditions The antenna shall meet the environmental conditions listed below and shall conform to the test requirements of RTCA DO-160C. Environmental Condition Temperature (operating) (ground survival) Altitude Temperature Variation Humidity Vibration Waterproofness Fluids Lightning Icing Category F2 F2 F2 A C CLMY S F 2A C 2.
3. INSTALLATION PROCEDURE 3.1 UNIT AND ACCESSORIES The 400 Series units are available under the following part numbers: 3.1.
3.1.
The following installation accessories are available: 1. GPS Antenna Options: • GA 56 Antenna Kit, without cable (Mod 1 or later, Garmin P/N 010-10040-01). This kit contains the following items: ITEM GA 56 ANTENNA SUB-ASSEMBLY BACKING PLATE NUT, SELF-LOCKING, #8-32 ANTENNA GASKET • QTY 1 1 4 1 GA 56 Flange Mount Antenna Kit (Mod 1 or later, Garmin P/N 010-10040-02). This kit contains the following items: ITEM FLANGE MOUNT GA 56 ANTENNA SUB-ASSEMBLY NUT PLATE SCREW, #10-32 x 5/8” ANTENNA GASKET 2.
3.2 DATA BASE OPTIONS ITEM DATA CARD, WORLD WIDE DATA CARD, AMERICAS DATA CARD, INTERNATIONAL 3.3 MISCELLANEOUS OPTIONS ITEM CONNECTOR, BNC, MALE, CLAMP LOW-LOSS AVIATION ANTENNA EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR, 15 FT. LOW-LOSS AVIATION ANTENNA EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR, 30 FT. GPS 1.57542 GHz NOTCH FILTER 3.
3.6 CABLE INSTALLATION 1. Route the coaxial cable to the rack location keeping in mind the recommendations of Section 2. Secure the cable in accordance with good aviation practice. 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. Figure 3-1. Coaxial Cable Installation 3.
Table 3-2.
3.8 400 SERIES UNIT INSERTION AND REMOVAL The 400 Series unit is installed in the rack by sliding it straight in until it stops, about 1 inch short of the final position. A 3/32“ hex drive tool is then inserted into the access hole at the bottom of the unit face. Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit is firmly seated in the rack.
This page intentionally left blank.
3.10 GA 56 Antenna Installation Drawing 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-2.
3.11 Mounting Rack Dimensions 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-3.
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-4.
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-5.
3.12 Mounting Rack Installation 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-6.
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-7.
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-8.
3.13 Recommended Panel Cutout Dimensions 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 3-9.
4. SYSTEM INTERCONNECTS 4.1 PIN FUNCTION LIST 4.1.
Connector P4001, continued Pin 37 38 39 40 41 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 ALTITUDE ALARM AUDIO HI (Not implemented at time of publication) ALTITUDE ALARM AUDIO LO (Not implemented at time of publication) LIGHTING BUS HI LIGHTING BUS LO GPS RS 232 OUT 3 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
4.1.
4.1.
4.2 POWER, LIGHTING, AND ANTENNAS 4.2.1 Power, Lighting, and Antennas Function The section covers the Power Input requirements, Lighting Bus input, and Antenna connections. 4.2.2 Power, Lighting, and Antennas Electrical Characteristics 4.2.2.
4.2.3 Power, Lighting, and Antennas Configuration Refer to section 5.2.6 for lighting configuration. 4.2.4 Power, Lighting, and Antennas Calibration and Checkout Refer to section 3.9 for the COM antenna checkout. 4.2.5 Power, Lighting, and Antennas Interconnect Refer to Figure 4-5 on page 4-29 for the power, lighting, and antennas interconnect. 4.3 ALTIMETER 4.3.1 Altimeter Function Altitude input is required for GPS RAIM calculations, and is useful for advisory vertical navigation (VNAV) calculations.
4.4 MAIN INDICATOR 4.4.1 Main Indicator Function 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 430 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.
4.4.2.4 Superflags 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. 4.4.2.
4.5 ANNUNCIATORS/SWITCHES 4.5.1 Annunciators/Switches Function NOTE Initial certification of the 400 Series units was accomplished without use of any remote switches or annunciators, since the same switching and annunciation is available on the front panel of the 400 Series unit. However, if the 400 Series unit is not installed in the pilot’s normal field of view, some or all of the remote switches and annunciators may be required by your certification agency.
4.5.1.12 ILS/GPS APPROACH Output Sinks 500 mA when GPS navigation is selected and GPS approach is active or when VLOC navigation is selected and an ILS channel has been selected. This output may be connected to the ILS Engage input of an autopilot or flight director to provide higher autopilot gain while the 400 Series unit is operating in the ILS or GPS Approach modes of operation. 4.5.1.13 DEMO MODE SELECT This discrete input may be used to select Demo Mode on the 400 Series unit.
4.6 SERIAL DATA 4.6.1 Serial Data Function 4.6.1.1 RS-232 The 400 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.
Label # 251 251G 252 260G 261G 275G 300G 303 304G 305G 306G 307G 310 311 312 313 314 315 316 320 321 326G 330 331 332 333 334 335 340 351G 352G 371G 377 Parameter Name Distance to Go Distance to Go Time to Go Date (BCD) GPS Discrete Word 1 LRN Status Word Station Declination, Type, and Class Message Length/Type/Number Message Characters 1-3 Message Characters 4-6 NAV/Waypoint/Airport Latitude NAV/Waypoint/Airport Longitude Present Position Latitude Present Position Longitude Ground Speed Track Angle (True)
4.6.2 Serial Data Electrical Characteristics 4.6.2.1 RS-232 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. 4.6.2.
4.7 COM/VOR/ILS AUDIO (GNC 420 AND GNS 430 ONLY) 4.7.1 COM/VOR/ILS Audio Function and Emergency Mode 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.
4.7.2.3 COM AUDIO, VOR/ILS AUDIO 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. 4.7.2.
4.8 VOR/ILS INDICATOR (GNS 430 ONLY) 4.8.1 VOR/ILS Indicator Function NOTE Because the GNS 430 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).
4.8.2.4 Flag 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.
4.9 RMI/OBI 4.9.1 RMI/OBI Function The MAIN OBI output provides bearing information from the active waypoint for Bendix/King Serial OBI devices based upon the 400 Series unit’s GPS navigation. For the GNS 430, the MAIN OBI output may be configured so that it sends VOR/ILS bearing information when VLOC is selected by the GNS 430 CDI key. The VOR OBI output provides bearing information from the active waypoint for Bendix/King Serial OBI devices based upon the GNS 430 VOR receiver.
4.10 DME TUNING (GNS 430 ONLY) 4.10.1 DME Tuning Function The GNS 430 can channel a DME based on the tuned VLOC frequency. The GNS 430 outputs 2 of 5, BCD or Slip parallel DME and King Serial DME channeling format. When DME COMMON is held low, the GNS 430 actively tunes the DME. 4.10.2 DME Tuning Electrical Characteristics 4.10.2.
4.10.3 DME Tuning Configuration Refer to section 5.2.12 for the DME tuning configuration. 4.10.4 DME Tuning Calibration and Checkout None. 4.10.5 DME Tuning Interconnect Refer to Figure 4-23 on page 4-65 for the King Serial Panel DME tuning interconnect. Refer to Figure 424 on page 4-67 for the King Serial Remote DME tuning interconnect. Refer to Figure 4-25 on page 4-69 for the parallel 2 of 5 DME tuning interconnect. Refer to Figure 4-26 on page 4-71 for the parallel BCD/Slip Code DME tuning interconnect.
4.11 400 SERIES INTERCONNECTS 4.11.1 400 Series System Interface Diagram 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-1.
4.11.2 400 Series Typical Installations 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-2.
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-3.
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-4.
4.11.3 Power, Lighting, and Antennas Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-5.
4.11.4 Altimeter Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-6.
4.11.5 Main Indicator Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-7.
4.11.6 KI 209A Main Indicator Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-8.
4.11.7 KI 208A Main Indicator Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-9.
4.11.8 Annunciators/Switches Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-10.
4.11.9 RS-232 Serial Data Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-11.
4.11.10 ARINC 429 EFIS Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-12.
4.11.11 ARINC 429 Sandel EHSI Interconnect (1 400 Series Unit, 1 Sandel SN3308) 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-13.
4.11.12 ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 1 Sandel SN3308) 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-14.
4.11.13 ARINC 429 Sandel EHSI Interconnect (2 GNS 430, 2 Sandel SN3308) 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-15.
4.11.14 ARINC 429 Air Data/IRU/AHRS Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-16.
4.11.15 ARINC 429 Flight Control Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-17.
4.11.16 Traffic Advisory System Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-18.
4.11.17 Weather and Terrain Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-19.
4.11.
4.11.19 VOR/ILS Indicator Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-21.
4.11.20 RMI/OBI Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-22.
4.11.21 King Serial Panel DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-23.
4.11.22 King Serial Remote DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-24.
4.11.23 Parallel 2 OF 5 DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-25.
4.11.24 Parallel BCD/Slip Code DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Figure 4-26.
5. POST INSTALLATION CONFIGURATION & CHECKOUT PROCEDURE 5.1 CONFIGURATION MODE OPERATIONS With power applied to the aviation rack and the 400 Series unit turned off, press and hold the ENT key and turn the unit on. Release the ENT key when the display activates, the unit is now in the configuration mode. After the data base pages, the first page displayed is the MAIN ARINC 429 CONFIG page. While in Configuration Mode, pages can be selected by ensuring the cursor is off and rotating the small right knob.
DATA IN 1, DATA IN 2 Selection Description No unit connected to this ARINC 429 input Altitude, temperature, and speed information from the following Airdata systems: B & D 2600, 2601, 2800, 90004-003, Bendix/King KAD 280/480, Shadin ADC 2000 Heading, altitude, temperature, and speed information from an Airdata/AHRS Airdata/AHRS system.
DATA OUT Selection Description Off ARINC 429 GAMA 429 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.
CHANNEL INPUTS Selection Description Off Arnav/ei-fuel No unit(s) connected to input of this channel. Serial fuel flow information from the following units: ARNAV FC-10, FT-10 Electronics International FP-5L Serial transfer of flight plans and user waypoints between two 400 Series units. If Crossfill is selected for a channel output, then Crossfill is automatically selected for that channel’s input. Serial data input for in-flight access to weather and messaging.
5.2.3 MAIN INPUTS 1 Page Select the MAIN INPUTS 1 Page (see Figure 5-3). 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 400 Series unit is dashed out. Figure 5-3.
5.2.6 MAIN LIGHTING Page Select the MAIN LIGHTING Page (see Figure 5-6). This page allows you to set display parameters that affect the display backlight and key lighting brightness. The DISPLAY and KEY lighting characteristics are adjusted separately, each with the following fields: LIGHTING Shows the current level of display backlighting, based on the lighting input source (lighting bus voltage, or the ambient light if the source is PHOTO) and the settings on this configuration page.
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. PHOTO TRANS % - (Photocell Transition Percentage) When a lighting bus is used to control the lighting of the display (see Figure 5-7), this parameter sets the point on the lighting bus control below which the display brightness tracks the 400 Series unit’s photocell.
5.2.9 MAIN DISCRETE OUTPUTS Page Select the MAIN DISCRETE OUTPUTS Page (see Figure 5-11). This page allows you to verify the operation of any external annunciators and switches that are present in the installation. Figure 5-11. MAIN DISCRETE OUTPUTS Page DISCRETE TOGGLE Selection Verify That: APR GPS The APR annunciator is active and inactive as selected on this page. The GPS source select annunciator is active and inactive as selected on this page.
TO-FROM Selection Verify That: FROM Hidden TO 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 400 Series unit’s MAIN OBS inputs. The SELECTED COURSE field indicates near to 150° and a Calibrate to 150°? field appears. Selecting this field calibrates the 400 Series unit to match the input source.
5.2.11 COM SETUP Page (GNC 420 and GNS 430 Only) Select the COM SETUP Page (see Figure 5-13). 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. Figure 5-13. COM SETUP Page SPACING Selection Description 25.0 kHz 8.33 kHz Selects traditional 25 kilohertz spacing (760 channel). Selects 8.
5.2.12 VOR DISCRETE INPUTS Page (GNS 430 Only) Select the VOR DISCRETE INPUTS Page (see Figure 514). This page allows you to verify the operation of an external VLOC transfer switch that may be present in the installation. Figure 5-14. VOR DISCRETE INPUTS Page Selection Verify That: REMOTE XFR The box is filled in while a remote VLOC transfer switch is pressed. 5.2.13 VOR/LOC/GS CDI Page (GNS 430 Only) Select the VOR/LOC/GS CDI Page (see Figure 5-15).
SELECTED COURSE Select 150° on the CDI/HSI that is connected to the 400 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 400 Series to match the input source. Verify OBS operation by checking that the course displayed on the 400 Series is within 2° of the selected course. Do this at 30° intervals around the OBS card.
5.2.15 STORMSCOPE CONFIG Page (Only if 400 Series unit configured for BFG WX-500 Stormscope interface) Select the STORMSCOPE CONFIG Page (see Figure 517). This page shows the BF Goodrich WX-500 Stormscope configuration as reported by the WX-500 through RS-232 data. 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. Figure 5-17.
5.2.18 TRAFFIC Page (Only if 400 Series unit configured for BFG Skywatch or Ryan TCAD interfaces) Select the TRAFFIC Page (see Figure 5-20). This page shows the BFG Skywatch or Ryan TCAD modes of operation and current traffic situation. For BFG Skywatch, this page shows: 1. The altitude mode—below (BLW), normal (NORM), above (ABV), or unrestricted (UNR) 2. The operating mode—standby (STBY) or operating (OPER) Figure 5-20. TRAFFIC Page (Skywatch) 3. Current altitude (ALT) 4.
5.2.21 MONITORING THE DATA LINK The Data Link is monitored on the Data Link Page. There are four main page groups in the 400 Series software version 2.25 or higher: NAV, WPT, AUX, and NRST (see the 400 Series unit Pilot’s Guide for detailed information on the unit’s Page Groups). The Data Link Page (Figure 5-24) appears in the sequence of AUX Pages. To select the Data Link Page, rotate the large right knob until a page from the AUX group is displayed.
5.3 ADDITIONAL GROUND TESTS 5.3.1 Connector Engagement Test 1. 2. 3. 4. Turn on the 400 Series unit, and turn on the avionics master switch (if applicable). Place the 400 Series unit in the rack and engage the pawl mechanism. Turn the Allen screw of the locking pawl slowly clockwise until the 400 Series unit just comes on. A “T” handle makes the turns easy to count, but do not over-tighten.
5.3.4 Deviation & Flags Check 5.3.4.1 Analog Deviation & Flags The analog deviation (LEFT/RIGHT and UP/DOWN), TO/FROM, and FLAG (lateral and vertical) outputs to a CDI or HSI should be verified in flight with potential sources of electrical noise such as autopilot, flaps, gear, heater blowers, etc. operating. Lateral deviation and flags may be checked with either GPS or VOR/ILS, and vertical deviation and flags must be checked with Glideslope.
5.3.7 VHF COM Check (GNC 420 and GNS 430 Only) A flight test is recommended after the installation is complete to ensure satisfactory performance. To check the communications transceiver, maintain an appropriate altitude and contact a ground station facility at a range of at least 50 nautical miles. Contact a close ground station. Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical noise which would increase the squelch threshold.
Appendix A. CERTIFICATION DOCUMENTS A.1 Continued Airworthiness This section provides assistance to the installing agency in preparing Instructions for Continued Airworthiness (ICA) in response to Bulletin Number HBAW 98-18, “Checklist for Instructions for Continued Airworthiness for Major Alterations Approved Under the Field Approval Process”, effective 10/7/98.
6. Troubleshooting Information Refer to the 400 Series Maintenance Manual. 7. Removal and Replacement Information Refer to section 3.8 of this manual. If the unit is removed and reinstalled, a functional check of the equipment should be conducted in accordance with section 5.3 of this manual. 8. Diagrams Refer to sections 3 and 4 of this manual. 9. Special Inspection Requirements N/A 10. Application of Protective Treatments N/A 11.
A.2 Environmental Qualification Form—GNS 430 NOMENCLATURE: GNS 430 Airborne GPS/VOR/ILS/COM System TYPE/MODEL/PART NO.: TSO/JTSO COMPLIANCE: 010-00139-(), which includes 011-00280-00 TSO-C129a Class A (1) (GPS) TSO-C37d Class 4 & 6, JTSO-2C37e (COM TX, GNS 430) TSO-C37d Class 3 & 5, JTSO-2C37e (COM TX, GNS 430A) TSO-C38d Class C & E, JTSO-2C38e (COM RECEIVER) TSO-C40c, JTSO-2C40c (VOR RECEIVER) TSO-C36e, JTSO-C36e (LOCALIZER RECEIVER) TSO-C34e, JTSO-C34e (GLIDESLOPE RCVR.
A.3 Environmental Qualification Form—GNC 420 NOMENCLATURE: GNC 420 Airborne GPS/COM System TYPE/MODEL/PART NO.: TSO/JTSO COMPLIANCE: 010-00173-(), which includes 011-00506-00 TSO-C129a Class A (1) (GPS) TSO-C37d Class 4 & 6, JTSO-2C37e (COM TX, GNC 420) TSO-C37d Class 3 & 5, JTSO-2C37e (COM TX, GNC 420A) TSO-C38d Class C & E, JTSO-2C38e (COM RECEIVER) MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: 004-00044-00 MANUFACTURER: GARMIN International, Inc. ADDRESS: 1200 E.
A.4 Environmental Qualification Form—GPS 400 NOMENCLATURE: GPS 400 Airborne GPS System TYPE/MODEL/PART NO.: 010-00171-(), which includes 011-00504-00 TSO/JTSO COMPLIANCE: TSO-C129a Class A (1) (GPS) MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: 004-00044-00 MANUFACTURER: GARMIN International, Inc. ADDRESS: 1200 E. 151st Street, Olathe, Kansas 66062 NOTE: The following information provides examples only.
A.5 Environmental Qualification Form—GA 56 NOMENCLATURE: GA 56, GPS Aviation Antenna TYPE/MODEL/PART NO.: 011-00134-00 (Stud Mount) 011-00147-00 (Flange Mount) TSO COMPLIANCE: C129 Class A (1) MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: 004-00015-00 MANUFACTURER: GARMIN International, Inc. ADDRESS: 1200 E. 151st Street, Olathe, Kansas 66062 NOTE: The following information provides examples only. It is not intended to be a comprehensive listing of all test conditions.
Appendix B. STC Permission Consistent with N8110.69 or Order 8110.4, Aviation Authority approved installers are hereby granted permission to use STC’s #SA00705WI (GNS 430), #SA00801WI (GNC 420), and #SA00800WI (GPS 400) data to modify aircraft.
Page B-2 Page Rev L 400 SERIES INSTALLATION MANUAL P/N 190-00140-02
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Page B-3 Page Rev L
Page B-4 Page Rev L 400 SERIES INSTALLATION MANUAL P/N 190-00140-02
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Page B-5 Page Rev L
Page B-6 Page Rev L 400 SERIES INSTALLATION MANUAL P/N 190-00140-02
400 SERIES INSTALLATION MANUAL P/N 190-00140-02 Page B-7 Page Rev L
Page B-8 Page Rev L 400 SERIES INSTALLATION MANUAL P/N 190-00140-02
Appendix C. 400 Series RS-232 Aviation Data Format C.1 ELECTRICAL INTERFACE The output signals shall be compatible with RS-232C. Data shall be generated at 9600 baud with a word length of 8 bits, one stop bit, and no parity. C.2 GENERAL OUTPUT FORMAT The 400 Series RS-232 data shall have the following general format: STX - ASCII start-of-text character (02 hex) C.
The following table 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.
C.
The following table 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.
Appendix D. 400 Series RS-232 Fuel/Air Data Input Format D.1 ELECTRICAL INTERFACE The input signals shall be compatible with RS-232C. Data shall be input at 9600 baud with a word length of 8 bits, one stop bit, and no parity. One message is received per second. D.
D.4 SHADIN FUEL FLOW SENTENCE The GARMIN 400 Series units shall be 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.
D.
This page intentionally left blank.
Appendix E. 400 Series LRU Interface Overview The following tables provide a quick overview of some of the equipment that can be interfaced with the GARMIN 400 Series units. This is not a complete listing however; it only represents those units listed in Section 4 of this manual. When installing equipment on the aircraft always refer to the manufacturers’ documentation for complete pinout and interconnect information E.1 GARMIN 420/430 LRU INTERFACE Function Audio Panel E.
Function EFIS Displays Bendix/King EFIS 40/50 SG 465 Function EHSI Sandel SN 3308 Function IRU/AHRS Function Nav Indicator Bendix/King KI 202A KI 203 KI 204 KI 206 KI 208/A KI 209/A KI 525A KPI 522/B KPI 553/A/B Function Weather, Traffic and Terrain Page E-2 Page Rev L Bendix/King KAU 461 Collins EFIS-84 DPU-84 Collins AHC 85E Garmin GI 102/A GI 106/A Bendix/King KTA 870 KMH 880 Honeywell Laseref HG 1075 AB HG 1095 AB Century NSD 360A NSD 1000 Litef LTR 81 Collins 331A-6P 331A-6G BF Goodri
