Garmin 430
Contents
1. EFIS Horizon Series Installation Manual Caution Preliminary Due to software development occurring at this time this manual may contain inaccuracies and omissions Manual Version Preliminary Date 10 18 04 Grand Rapids Technologies Inc REVISION HISTORY sssiscscsssesarsasscsacenssidsbiesccusdesudisanconsesisssavcdasienceuddesnsedebacsuisssesctansases 2 IN PRODUC LE estote tet Tp 2 WIRING CONSIDERA TIONS ice seek eces bets cep r tYo epe FRE Enea rh GIN te a QUb HR FEE aee P oe ten er tE RERO RE 3 POWER CONNECTIONS aciosuekensn5eevadxe sopa esske readsouvutuc snb eut na ko s ee Ux pe Hina ie ee b Einen sean 0i 3 GROUND CONNECTIONS ii beeosep cien ie Vkpckka bn Pana vanos esee Ska Ur peeE ie bea Senor ond pa CHER REUS 4 OTHER WIRING CONSIDERATIONS eee esee seen setae tasto sten s essen sense tasto aeos 4 DISPLAY UNIT INSTALLATION sccsstksreaethonelo hene edo curb Ca Ehud e oto eIa Sla pep kon p IRR uhren 5 DISPLAY UNIT CHECKOUT PROCEDURE eene eene tnn stant tn atta sna 5 AHRS TNS TALIA TION wisscsessedestineedesovinedestunestcassenselasouubedeotsspudosevsesscnsdopuiassusbecasbupvodeseues 5 AHRS AIR DATA COMPUTER AND MAGNETOMETER CHECKOUT PROCEDURE siidisscocsessasscscsesssecatsasecsdschasedapsee seucdesesecavaassesiasoucedabsensoustesssesssuacsenssssenctensoutes 5 ALTITUDE ENCODER WIRING ssesessesseseeseseeseesorseeceesoeseecosoesececesorseecesoesereosoeserserseeee 6 WARNING LIGHT OUTPUT2. esesseseesseseeecseeseseosseseesorseecesoeseecesereosoesoesorsereesoesereosseeereee 6 CEOCK POWER qoe 6 AHRS TO DISPLAY UNIT WIRING eesessesseseseossesecscrseecesceseeeossesecsorseecesorsereeseesoreeseeeee 6 AHRS TO MAGNETOMETER WIRING e eeeee esee eene esatta stato setas etos tensa sone 7 INTER DISPLAY UNIT COMMUNICATION eeeeee eese en senno n tnnt tn setas tata senso 7 AUDIO OUTPUT Vetere 7 LOCALIZER GLIDESLOPE WIRING sisscssssscossssdissssessbonivecssesssnssussvsscuscseasedecsasendessons 7 NAVIGATION RECEIVER WIRING essesessesseseesesseseesosseecesoeseecesoesereosoescesorseeceseeeesoeseee 7 ARINC 429 ADAPTER WIRING essesseseesessesecsosseseesceseecesceeoseesecsorseecesoesereesoesersorsesceseese 8 GARMIN 430 WIRING 5 5 2 6 5 PE Ser I Zessuipuasovssnschensnidensubesdesbeppenssoudescsdessguascso s 9 GNX327 GNX330 TRANSPONDER sessssssisessecnsscossssssunseandecssnsssencbessetoossesiocnbosnesesncessous 14 GARMIN GPS 155XL GNC 30UX Ea cccssnnss es aisseeciscansapnasenascnsonadephengtaentsonacsiotanesuesbanen 16 SL30 SL40 WUBIN Gor 19 Revision History 2 4 04 Corrected error CNX80 showed pin P1 22 incorrectly as a serial input Changed this to P1 21 10 15 04 Added new equipment interfaces Introduction This document provides detailed descriptions of the wiring to the EFIS Horizon I Display Units and AHRS Air Data Computer AHRS The Cable Description document AHRS Installation diagram
3. although new d sub pins would need to be installed If the wires are not cut inspect the d sub connector pins to verify they have not been damaged Insert the indicated wire color into the appropriate d sub connector housing hole according to the cable description diagram It desired the crimp type d sub connector can be replaced with a solder type connector AHRS Air Data Computer and Magnetometer Checkout Procedure 1 Apply power to a display unit to which the AHRS is connected and the AHRS 2 Select the Set Menu from the softkeys and select the AHRS Maintenance page Verify AHRS communications status is valid and AHRS status is valid 4 Scroll down this screen to the Magnetic Heading field This is the raw magnetic heading sensed by the magnetometer 5 To verify the magnetic heading is reasonable the following conditions must be met a The roll and pitch attitude data must be accurate The magnetometer must be in the same attitude as the AHRS c The magnetometer must have been electrically connected to the AHRS when the AHRS was turned on d The magnetic heading should be accurate within 30 degrees for any direction in which the airplane is pointed This can be verified by observing the Magnetic Heading data while position the airplane in different directions If this accuracy is not achieved it is likely due to mis wiring of the magnetometer connector or magnetic disturbances in the vicinity of the magne
4. and Magnetometer Installation diagram make up the set of installation documents Wiring Considerations The cable assembly supplied with the EFIS includes wires pre installed in the connectors that are certain to be used Other connections to the EFIS which may or may not be used are not installed in the d sub connectors Colored tefzel wires with d sub connector contacts pre installed are included for these connections The cable description diagram includes recommended wire colors for each connection to the EFIS components When routing the wiring the following guidelines should be considered e Good practices for physical installation of the wiring should be followed such as grommets where wires pass through sheet metal considering for chaffing and interference with moving mechanisms etc e Cable lengths should include enough extra length to allow for servicing the equipment For example the cables which plug into the display unit should be long enough to allow them to be connected to display unit with the display unit not installed in the instrument panel e In general routing of the wiring is not critical as the EFIS is designed to be tolerant of the electrical noise and other emissions typically found in aircraft Some consideration should be given to avoid routing wires near antennas or other locations that could impart high levels of electromagnetic signals on the wiring e The checkout procedures should be completed to
5. 429 interface full VOR functionality is provided on the EFIS and selected course is transmitted to the 430 from the EFIS when the OBS selection on the 430 is in GPS Data to EFIS The Garmin 430 must be configured for AVIATION output on one its serial output channels This output is connected to a serial input of the display unit s serial input 5 is recommend and the input configured as AVIATION input at 9600 baud EFIS to GPS Data Configure the display unit for Fuel Air Data on one of its serial outputs and connect this serial output to one of the 4 serial inputs to the Garmin 430 Configure the Garmin 430 for Shadin FADC on this input This will allow fuel and air data to be supplied to the GPS allowing the RAIM integrity monitoring and other functions to operate in the GPS Alternatively the gray code altitude output can be connected from the EFIS to the GPS although no fuel or other data will be provided to the GPS which would enhance its functionality VOR Data To display VOR data on the EFIS the optional ARINC 429 interface is required The ARINC input on the interface is connected to the VOR ILS ARINC 429 output from the GPS connector P4006 pins 23 and 24 If this interface is used it may be possible to delete connections listed with an in the Other Connections section Display Unit Connector A Connections Mating Connector 25 pin Female D sub Instrument has 25 pin male D sub EFIS
6. Function Garmin 430 Notes Display Connector Pin Unit Pin A 5 Serial Out 4 RS232 Out Spare Any of the This is the recommended serial RS 232 serial output to be configured as inputs Fuel Air Data output to the GNS 430 A 6 Localizer Deviation Left Input P4001 21 A 7 Localizer Deviation Right Input P4001 22 A 8 Glideslope Deviation Down P4001 28 A 9 Glideslope Deviation Up P4001 27 A 10 Localizer Valid Input P4001 24 A 11 Localizer Valid Input P4001 23 A 12 Glideslope Valid Input P4001 30 A 13 Glideslope Valid Input P4001 29 A 22 Serial Input 5 RS232 GPS Data Any one of In NMEAO0183 or Aviation the RS 232 Format serial outputs Display Unit Connector B Connections Mating Connector 25 pin Male D sub Instrument has 25 pin Female D sub Pin Function Garmin 430 Notes Connector pin B 21 Analog Input 1 Reserved for future P4006 29 Pull Up Required growth ILS Tuned Input B 20 Analog Input 2 GPS Deviations P4001 2 Pull Up Required Active true when low B 19 Analog Input 3 VOR ILS P4001 1 Pull Up Required Deviations Active true when low B 18 Analog Input 4 OBS Select this P4001 7 Pull Up Required connection may not be required These connections may not be required if the ARINC 429 interface is used and connected to the VOR ILS ARINC 429 Output from the GPS Thes
7. are allow for future growth Other Wiring Considerations Depending on the other equipment installed in the airplane switches may be necessary or desirable for the following functions e Aswitch to allow the autopilot to be controlled by the EFIS or directly from the GPS The benefit of this switch is to allow the GPS to control the autopilot in the even the display unit which normally commands the autopilot is not functioning e Aswitch may be necessary to manually select the localizer glideslope deviation indicators to be displayed While most nav radios include a ILS Tuned signal that the EFIS can use to activate the localizer glideslope deviation displays there may not be similar output from GPS Nav receivers which can drive these indicators with either ILS data or GPS data when GPS data is being output Display Unit Installation Mount the display unit s in the desired location in the instrument panel The main consideration in choosing a location is simply the ability to view display unit Since the display is fully sunlight readable no consideration for shielding the display unit from sunlight is required The use of nutplates behind the instrument panel greatly simplifies the task of installing and removing the 4 screws used to retain the display unit in the panel 6 socket cap stainless steel screws are recommended Display Unit Checkout Procedure 1 Apply Power to the display unit The LCD may flicker and within 10 sec
8. has 25 pin male D sub EFIS Function GPS 155XL GNC Notes Display 300XL Unit Pin Connector Pin A 5 Serial Out 4 RS232 Out Spare J101 17 Fuel Air Data This is the recommended serial Input output to be configured as Fuel Air Data output to the GPS A 22 Serial Input 5 RS232 GPS Data J101 24 Main GPS output In Aviation Format Display Unit Connector B Connections Mating Connector 25 pin Male D sub Instrument has 25 pin Female D sub Pin Function GPS 155XL GNC Notes 300XL Connector Pin B 18 Hold Sequence J102 13 Connects also to Garmin MD41 Switch Annunciator panel pin 9 Display Unit ARINC 429 Adapter Optional Mating Connector male D sub Adapter has 9 pin female D sub ARINC 429 Function GPS 155XL GNC Adapter Pin 300XL Connector Pin Notes C 1 or C 3 GPS Output J101 16 ARINC 429 A GPS Output C 2 or C 4 GPS Output J101 15 ARINC 429 B GPS Output C 5 EFIS Output J101 32 ARINC 429 A EFIS Output May also connect to other devices such as an autopilot or GNS430 C 9 EFIS Output J101 33 ARINC 429 B EFIS Output May also connect to other devices such as an autopilot or GNS430 C 1 C 2 or C 3 C4 must be use as pairs SL30 SL40 Wiring Display of Navigation Data from the SL30 The EFIS provides an HSI and others functions that display and use the VOR bearing data to
9. least 1 5 amps per display unit and 0 5 amps for the AHRS with a maximum rating of 5 amps The AHRS and display units monitor all of there power inputs and alarms are available to annunciate the loss of any power source that was provided and is expected to be working according to the General Setup menu The majority of the current flow into the display unit and AHRS will occur on the bus with the highest voltage It is desirable to have the display units and AHRS off during the engine start if all of the buses which power them are used for supplying power to the engine starter This maximizes the current available for the starter and may extend the life of the CCFL backlight in the display unit Ground Connections The cable assembly provided includes 20 or 22 gauge wire for the ground return of the display units This will result in a voltage drop of about 0 015 V foot which is acceptable for wire lengths up to 10 feet If any of the analog inputs 1 8 are used for monitoring which requires a high degree of precision it is recommended that the ground wire be less then 3 feet long or that a large gauge wire such as 18 gauge or larger be spliced onto the supplied ground wire which has been shortened to 1 foot orless The localizer and glideslope inputs are not affected by any voltage losses in the ground wire No uses for the analog inputs are specified at this time that require a high degree of precision Thus these recommendations
10. L30 to be connected to multiple display units Only one serial data output to the SL30 SL40 may be provided If the display unit which provides this tuning data to the SL30 SL40 was not operational the SL30 SL40 would be tuned by its front panel controls Display Unit Connector A Connections Mating Connector 25 pin Female D sub Instrument has 25 pin male D sub EFIS Function SL30 SL40 Notes Display Unit Pin A 2 Serial Output 1 Only 1 display unit may provide this connection A 20 Serial Input 1 This output from the SL30 may be connected to multiple display units Serial input 1 is the recommended port for this data although any port on the display unit may be used Configuring the Display Unit Using the general setup menu set the display unit to which the above connections are made to 9600 baud For the serial data output select SL30 SL40 Output For the serial input select SL30 SL40 Input Are any setups required for the SL30 SL40 Does the SL40 require 2 way communication ARINC 429 EFIS Output Message The following labels are transmitted on the EFIS ARINC 429 Output Label Data 100 Selected Heading 320 Magnetic Heading Roll Angle Command Roll Angle Pitch Angle Command Pitch Angle
11. d ARINC 429 Adapter wiring for the GNX330 Mating Connector 9 pin male D sub Adapter has 9 pin female D sub ARINC 429 Function GNX330 Notes Adapter Pin P3271 Pin Number C 1 or C 3 Traffic Display 30 ARINC 429 A Traffic Data C 2 or C 4 Traffic Display 28 ARINC 429 B Traffic Data C 1 C 2 or C 3 C4 must be use as pairs Configuring the Display Unit tbd Configuring the GNX327 Refer to the GNX327 installation manual and configure serial input 1 for the fuel air data format and serial input 2 for GPS format Configuring the GNX330 Refer to the GNX330 330D installation manual and configure serial input 1 for GPS format and serial input 2 for tbd format GNX330 Traffic tbd Garmin GPS 155XL GNC 300XL The following guidelines are provided for reference purposes only It provides the suggested methods for connecting this GPS to the EFIS display unit to allow optimal performance of both units The interface between this GPS and the EFIS allows for e GPS position groundspeed and ground track to be provided to the EFIS e GPS flight plan data to the EFIS including approaches although curved paths such as DME arcs procedure turns holding patterns are not displayed at this time e Display of GPS lateral cross track or CDI deviation data e Ability to set course in to a GPS waypoint e For EFIS installations that
12. e RS 232 serial output channel used to receive this data from the EFIS The CNX80 can receive this data on any of 3 inputs giving the installer a choice dependent on other devices connected to the CNX80 These choices are listed in the table below This CNX80 input is connected to a serial output from any display unit s which receives AHRS and EIS engine data if installed Serial output 5 of the EFIS display unit is recommended with its pin number is listed in the table below The display unit serial input must be configured as Fuel Air Data S Format output at 9600 baud Alternative EFIS to GPS Data Connections Alternatively RS232 altitude encoder data can be transmitted to the GPS instead of the FADC output While less data is provided to the GPS with this method resulting in less functionality in the GPS this does allow the possibility of using 1 less serial output from the display unit Although not conforming to the RS 232 specification it is usually acceptable to connect this output to both the GPS and a transponder Garmin recommends RS232 RxD8 be used for this purpose VOR Data VOR data from the GPS cannot be displayed on the EFIS An OBS selection into the GPS cannot be provided by the EFIS According to page 2 3 of the CNX 80 installation manual full VOR functionality is available without an external CDI although this seemed to conflict with the pilots manual While you can perform the equivalent navigation function o
13. e signals may also be connected to a conventional nav head without the need for any special considerations such as isolation diodes or the like Pull Up required indicates a pull up resistor is required If this input is also connected to another system such as a nav head the pull up resistor is not required as long as this other system is installed If this signal is not shared with other systems a 10k ohm resistor connected with one lead to aircraft 12V power and the other lead tee d into this connection is required ARINC 429 Connections to the GNS430 The following connections to the GNS430 allow the EFIS to provide VOR navigation information The data transmitted to the EFIS also includes ILS data making it unnecessary to connect the analog localizer and glideslope deviation and validity signals ARINC 429 Function GNS430 Pin Notes Adapter Pin C 1 or C 3 VOR ILS Input J4006 24 ARINC 429 A VOR ILS Output C 2 or C 4 VOR ILS Input J4006 23 ARINC 429 B VOR ILS Output C 5 EFIS Output J4001 48 ARINC 429 A EFIS Output May also connect to other devices such as an autopilot C 9 EFIS Output J4001 49 ARINC 429 B EFIS Output May also connect to other devices such as an autopilot C 1 C 2 must be used as a pair or C 3 C 4 must be used as a pair f this input to the G430 is used the other ARINC 429 input may be used Garmin CNX 80 Wiring T
14. er calibration and to enter altimeter corrections Each AHRS includes 4 serial output drivers for convenient connections to 4 display units AHRS to Magnetometer Wiring All magnetometer connections are made directly to its AHRS This wiring includes the power connections necessary for the magnetometer to operate Each AHRS and magnetometer pair is calibrated together for optimal accuracy and thus this paring should be maintained for installations which include more than one ARHS Inter Display Unit Communication Display units communicate between themselves so that most entries made during flight can be made from any display unit and will be applied to all This communication is accomplished by connecting the serial output to serial input such that all display units are in this loop Audio Output An audio output is provided Future growth is planned to allow this output to provide a warning tone or possibly other type of audio output This output may be connected to a spare input on the aircraft s intercom system Volume level will be controlled by menu settings within the display unit Localizer Glideslope Wiring The localizer glideslope deviation indicators provided on the EFIS can be driven from any ILS receiver or combination nav GPS receivers such as the Garmin 430 530 CNX80 etc Specific wiring recommendations are provided for these systems below These inputs require practically no power from the nav receiver s output
15. erface are also described This requires the use of the optional ARINC 429 interface Display Unit Connector A Connections to the Garmin GNX327 Mating Connector 25 pin Female D sub Instrument has 25 pin male D sub EFIS Function GNX327 Notes Display Pin Number Unit Pin A 1 Serial Output 6 19 Provides Altitude Encoding Data to Transponder This output may also be wired to a GNS430 530 or other devices that require this data Tbd GPS Data Output 2 Optional Connection Allows Transponder to provide flight time and automatic switching to and from standby mode This connection is made to the EFIS if no external GPS is used Display Unit Connector A Connections to the Garmin GNX330 Mating Connector 25 pin Female D sub Instrument has 25 pin male D sub EFIS Function GNX330 Notes Display P3271 Pin Unit Pin Number A 1 Serial Output 6 24 Provides Altitude Encoding Data to Transponder This output may also be wired to a GNS430 530 or other devices that require this data B tbd Enable Disable TIS 46 TIS Select This connection is made to pin 46 of a GNS430 530 series unit if installed If no GNS430 530 is installed make the connection to the display unit Tbd GPS Data Output 22 Optional Connection Allows Transponder to provide flight time and automatic switching to and from standby mode This connection is made to the EFIS if no external GPS is use
16. esistor is not required as long as this other system is installed If this signal is not shared with other systems a 10k ohm resistor connected with one lead to aircraft 12V power and the other lead tee d into this connection is required ARINC 429 Adapter Wiring The ARINC 429 adapter provides 2 serial inputs and 1 serial output that conform to the ARINC 429 serial communication standard The inputs may be configured for various uses according to the other equipment installed in the airplane as described below Each input may be configured for any of the possible functions The ARINC429 output is used by the EFIS to generate data usable by a variety of equipment such as autopilots and gps receivers The ARINC 429 output is can be connected to as many ARINC 429 receivers as desired Garmin 430 Wiring The following guidelines are provided for reference purposes only It provides the suggested methods for connecting this GPS to the EFIS display unit to allow optimal performance of both units The interface between this GPS and the EFIS allows for GPS position groundspeed and ground track to be provided to the EFIS GPS flight plan data to the EFIS Display of Localizer Glideslope data on the EFIS Display of GPS CDI data to in the same format as localizer data Transmission of air and fuel data to the GPS to allow RAIM integrity monitoring and other functions within the GPS related to fuel management etc e With the optional ARINC
17. f flying on a selected radial to from a VOR the CNX80 uses GPS for this guidance If you want to see actual VOR data you will need a separate nav head Rumor has it this may be corrected with the addition of VOR bearing data via a serial output in the future GPS Vertical and Lateral Deviation and Localizer Glideslope Per Rev E of the CNX Installation manual vertical and lateral gps deviations and localizer and glideslope deviations are not provided in a digital format at this time These deviations are provided via the localizer and glideslope deviation and valid signals shown below This requires that the analog connections for these signals be made between the CNX80 and as many display units as desired Display Unit Connector A Connections Mating Connector 25 pin Female D sub Instrument has 25 pin male D sub EFIS Function CNX80 Notes Display Connector Pin Unit Pin A 5 Serial Out 4 RS232 Out Spare P1 4 Use any 1 of This is the recommended serial P1 21 these output to be configured as P5 1 Fuel Air Data output to the GNS 430 A 6 Localizer Deviation Left Input P7 14 A 7 Localizer Deviation Right Input P7 13 A 8 Glideslope Deviation Down P7 31 A 9 Glideslope Deviation Up P7 30 A 10 Localizer Valid Input P7 29 A 11 Localizer Valid Input P7 10 A 12 Glideslope Valid Input P7 32 A 13 Glideslope Valid Input P7 28 A 22 Serial In
18. he following guidelines are provided for reference purposes only It provides the suggested methods for connecting this GPS to the EFIS display unit to allow optimal performance of both units At the time of this writing lateral and vertical deviation data is only available via analog interfaces as described below The interface between this GPS and the EFIS allows for GPS position groundspeed and ground track to be provided to the EFIS GPS flight plan data to the EFIS Display of Localizer Glideslope data on the EFIS Display of GPS lateral and vertical deviation data displayed in the same format as ILS data e Transmission of air and fuel data to the GPS to allow RAIM integrity monitoring sequencing of altitude dependent type waypoints and other functions within the GPS related to fuel management etc GPS Data to EFIS The CNX80 must be configured for MAPCOM output on the RS 232 serial output channel used to send data to the EFIS The CNX80 can transmit this data on any of 3 outputs giving the installer a choice dependent on other devices connected to the CNX80 These choices are listed in the table below This CNX80 output is connected to any serial input of the display unit s serial input 5 of the EFIS is recommend with its pin number is listed in the table below and the display unit serial input configured as AVIATION input at 9600 baud EFIS to GPS Data The CNX80 must be configured for FADC input on th
19. include the ARINC 429 interface selected course and magnetic heading data is sent to the GPS and CDI scaling can be read from the GPS e Transmission of air and fuel data to the GPS to allow RAIM integrity monitoring sequencing of altitude dependent type waypoints and other functions within the GPS related to fuel management etc GPS Data to EFIS The GPS RS 232 serial output channel 1 is used to send data to the EFIS This data is provided in the Aviation format The GPS 155XL GNC 300XL must be configured to set up serial output 1 as Aviation format This output is connected to any serial input of the display unit s serial input 5 of the EFIS is recommended with its pin number is listed in the table below and the display unit serial input configured as Aviation Mapcom input at 9600 baud EFIS to GPS Data The GPS must be configured for shadin fuel input on the RS 232 serial input channel 1 This input is connected to a serial output from any display unit s which receives AHRS and EIS engine data if installed Serial output 4 of the EFIS display unit is recommended with its pin number is listed in the table below The display unit serial input must be configured as Fuel Air Data S Format output at 9600 baud Alternative EFIS to GPS Data Connections Alternatively RS232 serial altitude encoder data that is transmitted to the transponder can also be wired to the GPS instead of the fuel aid data output This ma
20. onds the display should show the first page 2 If multiple power buses connect to the display unit turn off the display unit and apply power from each bus individually AHRS Installation Follow the instructions provided on the AHRS Mounting diagram Similarly temporarily install the magnetometer in the location you have chosen for it according to the Magnetometer Mounting diagram No periodic maintenance is required for these devices although it is desirable to mount them in locations that allow access to them if necessary Be sure to mount the AHRS and magnetometer with the connector toward the rear of the airplane A standard level can be used to orient these two devices such that are both level in roll and equal in pitch These devices must also be oriented to point in out the nose of the airplane This can be accomplished by adjusting the orientation of these devices so they are parallel to a fuselage centerline In cases where the magnetometer is mounted in the wing it may be possible to orient the magnetometer parallel to a wing rib if these ribs are oriented in the wing such that they are parallel to the fuselage centerline This is quite practical in airplanes such as Van s RV s Typically the cable supplied for the EFIS will not have a d sub connector installed on magnetometer cable end This makes it easier to route this cable through the airplane After the cable has been routed the wires can be cut to length if desired
21. provided by the SL30 Nav Com radio Localizer and glideslope deviation data is also displayed on the EFIS from this radio This data is transmitted to the EFIS display unit via an RS 232 output from the nav radio While the RS 232 connection is the preferred method for communicating this data to the EFIS the SL30 s analog outputs for glideslope and localizer may also be connected to the EFIS If both the RS 232 serial data connection and analog connections are made the EFIS will use the RS 232 data Radio Tuning and Loading of Pre Sets in the SL30 SL40 The EFIS has the ability to load the SL30 and SL40 with frequency pre sets to allow convenient selection of these frequencies from the front panel controls of the radio For the SL30 the EFIS can also tune the navigation radio This data is transmitted to the radio via an RS 232 output from the EFIS display unit Multi Display Unit Considerations Although the data from the SL30 is communicated to other display units via the inter display unit serial data connections allowing this data to appear on all display units it is preferable to connect the serial data output from the SL30 to at least 2 display units Connecting the serial output from the SL30 to multiple display units allows its data to be displayed in the event one display unit is not functional The serial ports within the display unit provide minimal loading of the serial data signals allowing the one serial data output from the S
22. put 5 RS232 GPS Data P1 5 RS232 TxD1 Use any 1 of In NMEAO0183 or Aviation P1 22 RS232 TxD2 these Format P5 21 RS232 TxD5 Display Unit Connector B Connections Mating Connector 25 pin Male D sub Instrument has 25 pin Female D sub Pin Function CNX80 Notes Connector pin B 21 Analog Input 1 ILS Tuned P5 68 Pull Up Required Precision Approach Input B 20 Analog Input 2 GPS Deviations P7 17 Pull Up Required Active B 19 Analog Input 3 VOR ILS P7 18 Pull Up Required Deviations Active Pull Up required indicates a pull up resistor is required If this input is also connected to another system such as a nav head the pull up resistor is not required as long as this other system is installed If this signal is not shared with other systems a 10k ohm resistor connected with one lead to aircraft 12V power and the other lead tee d into this connection is required GNX327 GNX330 Transponder The EFIS can provide altitude encoding data to these transponders The data must be provided via a serial data output as the gray code input to these transponders is not compatible with the gray code output provided by the EFIS If the optional ARINC 429 interface is used it is preferable to use its output to provide altitude data to the GNX330 transponder Traffic data will be available on the EFIS from the GNX330 in the near future As such the connections for this int
23. s allowing the nav receiver to be wired to as many display units as desired Nav heads may also be wired to these connections For redundancy purposes it is desirable to connect these signals to all display units Navigation Receiver Wiring When stand alone nav receivers are connected to the EFIS the localizer and glideslope deviation and flag connections are made to the EFIS localizer glideslope deviation and flag inputs If the nav receiver includes an ILS Tuned output indicating an ILS frequency is selected on the nav radio connect this to the display unit s analog 1 input as shown in the following tables Display Unit Connector A Connections Mating Connector 25 pin Female D sub Instrument has 25 pin male D sub EFIS Function Notes Display Unit Pin A 6 Localizer Deviation Left Input A 7 Localizer Deviation Right Input A 8 Glideslope Deviation Down A 9 Glideslope Deviation Up A 10 Localizer Valid Input A 11 Localizer Valid Input A 12 Glideslope Valid Input A 13 Glideslope Valid Input Display Unit Connector B Connections Mating Connector 25 pin Male D sub Instrument has 25 pin Female D sub Pin Function Notes B 21 Analog Input 1 ILS Tuned Input Pull Up Required Pull Up required indicates a pull up resistor is required If this input is also connected to another system such as a nav head the pull up r
24. tometer 6 The magnetometer calibration may now be performed Refer to the user manual for these procedures ios Altitude Encoder Wiring Gray code outputs are provided for transponders that require this format for the data These outputs are provided on connector B The corresponding output such as Al A2 A4 etc from the display unit connects to the same input A1 A2 A4 etc of the transponder Warning Light Output A warning and caution output are provided on connector B to drive external warning and caution indicators These output provide a path to ground when active thus the indicator should be wired with one of its terminals to aircraft power and the other to this output The maximum current that can be controlled by this output is 0 2 amps Clock Power Clock power allows the internal time of day clock to maintain its time while the EFIS is turned off AHRS to Display Unit Wiring The cable description document describes the wiring that is pre installed between the AHRS and the display unit The only consideration of any consequence occurs in systems which include multiple AHRS Since a display unit can control only 1 AHRS only the display unit with a serial output to the AHRS can be used to command magnetometer calibration or be used to enter altimeter corrections into the associated AHRS The AHRS does not require any serial input to operate although serial input to the AHRS is required to active the magnetomet
25. verify the EFIS is not affected by radio transmissions on any frequency Power Connections The display units and AHRS each include 3 isolated power input connections This allows redundant power sources such as a main and secondary bus and the possibly of a third power source Since the AHRS only consumes about 0 1 amps and will operate down to 9V even 8 dry cells could be used as a source of emergency power This would allow many hours of operation from cells as small as AA The display units consume approximately 1 amp making even a small 3 Amp Hour gel cell a suitable emergency source The configuration of the power supplied to the display unit s is left to the installer Considerations such as the number of power buses the desire or not to supply one piece of equipment with power from redundant buses which in theory allows the possibility of one device affecting both buses the configuration of the electrical system with respect to backup equipment and so on may dictate the best configuration for a particular airplane No provision is included within the display units for a power switch If a power switch is desired for the EFIS the 12V power should be controlled with the switch not ground The display units and AHRS include internal thermally activated fuses This protects the equipment from internal electrical faults Power supplied to the EFIS must pass through a fuse or circuit breaker or fuse It should be sized to allow at
26. y limit the amount of data is provided to the GPS to accommodate the needs of the transponder resulting in less functionality in the GPS this does allow the possibility of using 1 less serial output from the display unit Although not conforming to the RS 232 specification it is usually acceptable to connect this output to both the GPS and a transponder ARINC 429 Connections At the time of this writing it is believed although not confirmed through testing that ARINC 429 connections to the GPS are not required The benefit of using the ARINC 429 interface is as follows e CDI scaling information is provided directly by the GPS Without this scaling information the EFIS attempts to duplicate the scaling based flight plan data e Selected Course Data is provided to the GPS from the EFIS This allows the CDI analog output of the GPS to operate correctly when waypoint sequencing is in the HOLD state e Magnetic Heading information is provided to the GPS The GPS must be configured with its ARINC 429 output as Collins PL2 EFS or King EFS 40 50 The display unit must be configured for LOW speed ARINC data Note that since both ARINC input channels must be configured for the same rate and since traffic data provided by the GNX330 is high speed it is not possible to connect this GPS and the GNX330 transponder into the same ARINC 429 interface Display Unit Connector A Connections Mating Connector 25 pin Female D sub Instrument
Download Pdf Manuals
Related Search