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Garmin GNS 430 GPS Receiver User Manual

1. 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 THE GNS 530 MUST BE CONFIGURED TO OUTPUT SLIP CODE DME TUNING DATA FOR PROPER OPERATION IN THIS CONFIGURATION 3 THE GNS 530 MUST BE CONFIGURED TO OUTPUT BCD DME TUNING DATA FOR PROPER OPERATION IN THIS CONFIGURATION 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY 61 KN 65 P5006 2 P611 P651 14 4 14 20 E 15 21 2 16 33 1 17 57 gt 9 32 39 8 33 40 7 34 42 6 35 43 10 56 22 12 22 P5006 3 14 20 21 33 37 39 40 42 43 22 Tuned MO M1 M2 M3 KO K1 K2 K3 K50 DME COMMON uned M8 M4 M2 M1 K800 K400 K200 K100 K50 DME COMMON Figure 4 25 Parallel BCD Slip Code DME Tuning Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 69 Page 4 70 blank Rev G 5 POST INSTALLATION CONFIGURATION amp CHECKOUT PROCEDURE 5 1 CONFIGURATION MODE OPERATIONS With power applied to the aviation rack and the 500 Series unit turned off press and hold the ENT key and turn the unit on Release the ENT key when the display activates After the Data Base and Instrument Panel Self test 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 To change data on the displayed Configuratio
2. GARMIN GARMIN GARMIN GARMIN S Tec Bendix King3endix King Century Bendix King Col Collins Sperry Sperry GI 102 GI 102A 106 GI 106A ST 180 KI 206 525A NSD360A KPI 552 8 331A 6P 31A 9C RD 550A RD 650 NSD1000 KPI 553 A B P P1 P1 P1 P1 P2061 P1 P2 CD13 P101 P1 1 2 P1 P2 Pi P2 11 11 11 11 27 N 17 1 29 4 F 4 gt 12 12 12 12 43 J B 18 H 28 3 E 3 A gt 9 9 9 9 26 E 2 33 J 26 1 A 1 Lu 10 10 42 5 T 34 K 27 2 B 2 7 7 7 7 37 N K 31 51 8 8 8 8 38 F r 32 G 32 E 37 P 39 oe 38 5 36 13 13 44 K E 27 JJ 33 5 5 s Uo 14 14 28 M B 28 HH 34 6 D 6 15 15 36 d J 30 FF 35 U gt 16 16 35 J 29 GG 36 x 7 u 38 w 8 DO 1 1 1 1 22 x 15 w 1 1 DD 6 j 2 2 2 2 24 7 16 N V 3 3 FF 8 m 5 3 5 3 3 25 L v 24 7 4 4 9 J 5 5 5 5 39 P Y 25 A 5 5 AA 10 4 4 4 4 40 T 26 Y 6 6 BB 11 9 6 6 6 6 41 w 25 x 7 7 cc 12 E x gt N C 17 SEE NOIE 2 N C 18 NOTES Nav d ation cator LEFT RIGHT TO FROM NAV FLAG NAV FLAG NAV SUPERFLAG NAV SUPERFLAG LO UP DOWN GLIDESLOPE FLAG GLIDESLOPE FLAG GLIDESLOPE SUPERFLAG GLIDESLOPE SUPERFLAG LO OBS A H OBS C OBS D COS HI OBS E COS LO OBS F SIN Hi OBS G SIN LO GPS ANNUNCIATOR VLOC
3. 5 Equipment tested to Category A to Categories M amp os Category X notte Salt Spray Equipment identified as Category X no test required Lightning Induced Transient Susc 22 0 Equipment tested to Category ZZZZ per DO 160D See report 005 00096 72 for details Lightning Direct Effects Equipment identified as Category X no test required 500 SERIES INSTALLATION MANUAL Page A 3 P N 190 00181 02 Rev Voltage Spike Equipment tested to Category A Sand and Dust Equipment identified as Category X no test required Magnetic Effect Equipment tested is Class Z A 3 Environmental Qualification Form GPS 500 NOMENCLATURE GPS 500 Airborne GPS System TYPE MODEL PART NO 010 00176 which includes 011 00562 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 151 Street Olathe Kansas 66062 NOTE The following information provides examples only It is not intended to be a comprehensive listing of all test conditions Low Temperate High Temperature 24453 x Hm Fawpmmtsel CHen A Vibration Equipment tested without shock mounts to Categories B M amp N Lightning Induced Transient Susc 22 0 Equipment tested to Category ZZZZ per DO 160D See report 005 00096 72 for details
4. Figure 5 9 CDI LAT VERT MAIN CDI OBS CONFIG Page Verify That Max left up The CDI is pegged to the left up Full left up The CDI is deflected full scale to the left up The CDI is centered Full right down The CDI is deflected full scale to the right down Max right down The CDI is pegged to the right down NAV FLAG LAT VERT Verify That Hidden The LAT VERT flag is hidden The LAT VERT flag is in view TO FROM Verify That FROM 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 500 Series unit s MAIN OBS inputs The SELECTED COURSE field should indicate near to 150 and a Calibrate to 150 field appears Selecting this field calibrates the 500 Series unit to match the input source Verify OBS operation by checking that the course displayed on the 500 Series unit is within 2 of the selected course Do this at 30 intervals around the OBS card NOTE If it is desired to ignore a selected course input either analog resolver or ARINC 429 for GPS operation in OBS mode press MENU on the MAIN CDI OBS CONFIG page and select Ignore SEL CRS or GPS When OBS mode is selected the selected course is entered on the controls of the 500 Series unit If ignoring the selected course input such that the VOR valid flag is dependent only on a valid VOR signal with lateral deviation calculated by another dis
5. LESS OTHERWISE NOTE RCO 89078917 WITH THIS Bendix King Collins S Tec Narco Narco ARC KN 62A DME 40 ICR 451 DME 890 DME 891 4 6 NOTE 2 NOTE 2 NOTE 2 NOTE 3 NOTE 3 NOTE 3 2621 P1 P1 P3501 P301 P2 12 28 28 2 51 11 5 12 10 9 52 29 4 30 9 8 45 30 5 11 8 12 39 31 7 11 32 B 28 24 C 9 23 4 19 33 D 27 22 6 27 34 E 8 21 H 12 35 gt 5 44 6 H 52 7 C 6 16 1 35 25 e 52 gt 51 E d N C D N C M D RALLEL 2x5 WITH THIS MH MH MH MH MH 00 00 00 00 00 50 K 10M COMMON HZ A 10 M 2X 5 CODE SELECT SLIP CODE SELECT BCD CODE SELECT Figure 4 24 Parallel 2 OF 5 DME Tuning Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 67 Page 4 68 blank RevG 4 11 24 Parallel BCD Slip Code DME Tuning Interconnect PARALLEL DME 8MHZ SER DME CHAN REQ PAR DME 4MHZ SER DME RNAV MODE PAR DME 2MHZ PARALLEL DME 1MHZ PARALLEL DME 800KHZ PARALLEL DME 400KHZ PARALLEL DME 200KHZ PARALLEL DME 100KHZ PARALLEL DME SOKHZ DME COMMON PARALLEL DME 8MHZ SER DME CHAN REQ PAR DME 4MHZ SER DME RNAV MODE PAR DME 2MHZ PARALLEL DME 1MHZ PARALLEL DME 800KHZ PARALLEL DME 400KHZ PARALLEL 200 PARALLEL DME 100KHZ PARALLEL DME SOKHZ DME COMMON NOTES Bendix King Bendix King
6. MAIN UP MAIN GPS ARINC 429 IN 1 GPS ARINC 429 IN 1 B ARINC 429 OUT A INC 429 OUT B LS GPS APPROACH MAIN LE MAIN 810 MAIN LATERAL FLAG MAIN LATERAL FLAG P5006 24 25 NAV 1 2 RELAY SENSE 429 2 RX A 429 2 RX B WITCHING RELAY NG RELAY WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 SOME PINS OF THE SANDEL SN3308 ARE CONFIGURABLE REFER TO SANDEL DOCUMENTATION AND CONFIGURATION NAV SYSTEM 1 RELAXED N C ENERGIZED NAV SYSTEM 2 28 VDC Figure 4 13 OR PINOUT INFORMATION NAV AND VOR ILS OF THE 1 AND THE SDI OF THE 2 TO 2 FOR PROPER OPERATION IZER ENG ARINC 429 Sandel EHSI Interconnect 2 GNS 530 1 Sandel SN3308 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 45 Page 4 46 blank Rev 0 18100 061 N d NOLLV TIV LSNI SHISSS 005 D AY que Tq 87 93ed Lp p 9304 80 ENS Iepues OES SND 1 euuoojeju ISH3 ezr ONIHV anb GARMIN GNS 530 1 VOR ILS ARINC 429 OUT A VOR ILS ARINC 429 OUT B GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B GPS ARINC 429 OUT A GPS ARINC 429 OUT B ILS GPS APPROACH MAIN LEFT MAIN RIGHT MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAC GARMIN GNS 530 2 VOR ILS ARINC 429 OUT VOR ILS ARINC 429 OUT B GPS ARI
7. e e 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 e2e 2e00200000000800808808080 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 0 2 3 4 5 6 7 8 9 10 1 11 12 13 14 15 16 17 18 19 20 Pin PinName 6 MESSAGEANNUNCIATE Out 8 SPAREANNUNCIATE Out 9 INTEGRITYANNUNCIATE Ot 33 MANOBSSTATORD ln 35 MAINOBSSTATORF Applies only to GNS 530 part numbers 011 00550 30 GNS 530A 011 00835 10 and GPS 500 part number 011 00562 10 For applications requiring secondary or alternate power bus input MAIN LATERAL FLAG 2 5V COMMON 500 SERIES INSTALLATION MANUAL Page 4 1 P N 190 00181 02 Rev Connector P5001 continued Pin _ PinName O O O Oo 39 LIGHTINGBUSHI in 40 LIGHTINGBUSLO Z o 41 GPSRS2320UT3 o 48 GPSARINC429IN1A o Z 49 GPSARINC429INTB 50 GPSARINC429IN2A o hn 51 GPSARINC429IN2B U n 52 RESERVED 1 Soe 58 RESERVED O 55 GPSRS232INA nn 57 GPSRS232INT rr nn 59 GPSRS232IN2 n 60 ALTITUDECOMMON GROUND o o O Out 64 ALTITUDEBA j 65 ALTITUDEB2 y yon 66 67 ALTITUDEA4 in 68 ALTITUDEA y yon 69 ALTITUDEA 7
8. AIRCRAFT POWER 2 AIRCRAFT POWER 2 AIRCRAFT GROUND AIRCRAFT GROUND LIGHTING BUS HI LIGHTING BUS LO AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT GROUND AIRCRAFT GROUND AIRCRAFT POWER AIRCRAFT GROUND GPS ANTENNA COMM ANTENNA VOR LOC ANTENNA GLIDESLOPE ANTENNA NOTE 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED GNS 530 CIRCUIT BREAKER 530 2 IF THE AIRCRAFT HAS MULTIPLE AIRCRAFT POWER BUSES E CES CIRCUIT IT IS RECOMMENDED THAT ALL CNS 530 POWER INPUTS BE P5001 BREAKER 500 CONNECTED TO THE SAME POWER BUS THE FOLLOWING TABLE SHOWS WHAT GNS 530 FUNCTIONS 19 5A AIRCRAFT POWER SEE NOTES 2 AND 3 DEPEND ON WHICH POWER INPUTS 20 pu ALL CNS 530 FUNCTIONS 72 lt 5A AIRCRAFT POWER SEE NOTE 7 5001 DEPEND ON THIS POWER INPUT 15 P5002 COM TRANSMITTER 77 78 P5006 NAV SUPERFLAG GLIDESLOPE SUPERFLAG 39 lt LIGHTING BUS HI SEE NOTE 4 40 lt LIGHTING BUS LO 3 AIRCRAFT POWER INPUT TO THE MAIN BOARD P5001 AND THE GNS 530 VOR ILS BOARD P5006 MAY 11 35 n THE AIRCRAFT POWER INPUT ON THE COM BOARD P5002 IS P5002 COM DEPENDENT ON THE PART NUMBER OF THE UNIT 530 ONLY Y 18 AWG Q8 V AIRCRAFT POWER GNS 530 P N 011 00550 00 28 VOLTS DC 12 P SEE TABLES AND NOTES 2 3 AND 5 14 V GNS 530A P N 011 00835 00 4 CNS 53
9. LEFT RIGHT TO FROM NAV FLAG NAV FLAG UP DOWN GLIDESLOPE FLAG GLIDESLOPE FLAG 085 A H 9856 OBS D COS HI S E COS LO BS F SIN HI S G SIN LO GARMIN GTX 327 RS 232 OUT 1 ALTITUDE D4 ALTITUDE A1 ALTITUDE A2 ALTITUDE A4 ALTITUDE B1 ALTITUDE B2 ALTITUDE B4 ALTITUDE C1 ALTITUDE C2 ALTITUDE C4 AIRCRAFT POWER SEE NOTE 2 ANO TABLE K 16 17 NOTES 41 ALL WIRES 24 AWG OR LARGER UNLESS OTHFRWISF NOTED 2 AIRCRAFT POWER INPUT TO THE MAIN 30ARD 25001 AND THE GNS 530 VOR ILS BOARD P5006 MAY 3E 11 33 VDC THE AIRCRAFT POWFR INPUT ON THE COM BOARD P5002 IS DEPENDENT ON THE PART NUMBER OF THE UNIT GNS 530 P N 011 00550 00 28 VOLTS DC GNS 530 P N 011 00835 00 GNS 530 P N 011 00835 10 GNS 530A P N 011 00550 10 11 33 VOLTS DC S 550A P N 011 00550 30 11 12 10 timeter or Blind Encoder D4 2 A4 82 84 c2 C4 COMMON COM 1 AUDIO HI COM 1 AUDIO LO COM 1 MIC AUDIO COM 1 MIC KEY COM 1 MIC AUDIO LO NAV 1 AUDIO HI NAV 1 AUDIO LO SNOILVTIVLSNI IWOIdAL 531935 004 0 18100 061 N d NOLLV TIV LSNI SHISSS 005 Cf P5001 GPS 500 MAIN LEFT 2 A RIGHT 22 9 MAIN 25 MAIN FROM 26 MAIN LATERAL FLAG 23 MAIN LATERAL FLAG 24 MAIN 0 27 MAN DOWN 28 K SEE NOTE 2 MAIN
10. MESSAGE ANNUNCIATE 500 Out INTEGRITY ANNUNCIATE P501 9 Ou All outputs sink up to 500 mA when activated 4 5 2 2 Switch Inputs PinName Connector Pin OBS MODE SELECT CDI SOURCE SELECT P5001 DEMO MODE SELECT P5001 These inputs are considered active if either the voltage to ground is 1 9 V or the resistance to ground is 375 Q These inputs are considered inactive if the voltage to ground is 11 33 Vdc 4 5 2 3 TIME MARK OUT PinName Connector Pin TIME MARK OUT outputs a 1 ms 1 us wide pulse once every 1 0 s 2 ms TIME MARK OUT is a logic level output capable of sourcing 1 mA at up greater than 3 8 V and sinking 1 mA at less than 0 4 V 4 5 3 Annunciators Switches Configuration None 4 5 4 Annunciators Switches Calibration and Checkout Refer to section 5 2 7 for the annunciators switches checkout 4 5 5 Annunciators Switches Interconnect Refer to Figure 4 9 on page 4 37 for the annunciators switches interconnect Page 4 10 500 SERIES INSTALLATION MANUAL P N 190 00181 02 4 6 SERIAL DATA 4 6 1 Serial Data Function 4 6 1 1 RS 232 The 500 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 port The data consists of the following refer to Appendix C for a detailed data format descript
11. 500 DATA TO BE DISPLAYED ON THE PAGE THIS DRAWING IDENTIFIES SPECIFIC RS 232 PORTS CONFIGURATION OF 500 SERIES UNITS WITH MAIN SOFTWARE VERSION 2 04 OR EARLIER REQUIRES THESE SPECIFIC PORTS MAIN SOFTWARE VERSION 2 05 OR LATER DOES NOT HAVE THIS LIMITATION SUCH THAT ANY SERIAL FORMAT CAN BE SELECTED ON ANY OF THE FOUR RS 232 PORTS IF AN RS 232 OUTPUT PORT IS CONFIGURED FOR THE HONEYWELL EGPWS THE CORRESPONDING RS 232 INPUT OF THE SAME PORT MAY NOT BE USED REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY CONNECTION TO RS 232 PORT 2 OF THE 500 SERIES UNIT IS SHOWN IF PORT 2 IS ALREADY IN USE ANY OTHER AVAILABLE RS 232 PORT MAY BE USED AS WELL GPS RS 232 OUT 1 GPS RS 232 IN 2 GPS RS 232 OUT 2 P5001 55 58 SEE NOTES 3 AND 4 23 Pe T 7 Y OPTIONAL EXTERNAL CLEAR SWITCH 6 P2 5 6 P491 7 6 18 RS 232 RX RS 232 TX EXTERNAL CLEAR RS 232 GROUND GPS RXA GDL 49 Jata Link NOTE 6 RS 232 OUT 2 RS 232 IN 2 SHIELD GROUND Figure 4 18 Weather and Terrain Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 55 Page 4 56 blank Rev G 4 11 18 Audio Panel Interconnect GARMIN PS Bendix King Bendix Ki
12. CDI SOURCE CONTROL RCVR 1 2 K NOTE ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 5 ENERGIZED NAV SYSTEM 2 28 VDC gt SOME PINS OF THE SANDEL 5 5508 ARE CONFIGURABLE REFER TO SANDEL DOCUMENTATION AND CONFIGURATION SOFTWARE FOR PINOUT INFORMATION THE SDI CONFIGURATIONS INAV AND VOR ILS OF 1 500 530 MUST BE SET TO 1 AND THE SDI OF THE 2 UNIT MUST BE TO 2 FOR PROPER OPERATION REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY Autopilot LOCALIZER ENGAGE LEFT RIGHT LATERAL FLAG LATERAL FLAG UP DOWN ERTICAL FLAG ERTICAL FLAG 80 NS OES SND Z 1 euuooJe1uJ ISHI 62 ONIHV 4 11 14 ARINC 429 Air Data IRU AHRS Interconnect f KAIN iy Yat tar Aer Zim adin Shadin B amp D B amp D Bendix King Bendix K 200 2000 ADC 2000 2601 2800 KDC 281 KDC 481 P500 J2 DB 15 J1 MS CONN 2201 2811 4811 1A 48 7 40 6 14 11 27 5 RANSMITTER A 1B 49 4 8 22 15 28 9 6 TRANSMITTER B SEE NOTE 2 ins i Bendix King ARMIN KAU 461 AHC 85E g 7 z oF o o z P1 NSE B INSERT B J1B 5 5 v w IRU AHRS TRANSMITTER A IRU AHRS TRANSMITTER B 16 G7 G7 G7 NE
13. Power Lighting and Antennas Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 27 Page 4 28 blank Rev 4 11 4 Altimeter Interconnect S 51 1 UDE D4 1 A 24 UDE A1 2 3 2 ALTITUDE A2 3 C 5 UDE A4 67 4 4 U 3 66 5 N gt 31 65 9 9 B2 2 10 B4 11 11 C1 13 U 13 C2 61 12 V 12 4 60 6 R 6 Figure 4 5 Altimeter Interconnect 500 SERIES INSTALLATION MANUAL Page 4 29 Page 4 30 blank P N 190 00181 02 Rev 4 11 5 Main Indicator Interconnect MAIN LEFT MAIN RIGHT MAIN 10 MAIN FROM MAIN MAIN LATERAL FLAG LATERAL FLAG MAIN LATERAL SUPERFLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG MAIN VERTICAL SUPERFLAG MAIN OBS ROTOR H MAIN OBS ROTOR C MAIN OBS STATOR D MAIN OBS STATOR E MAIN OBS STATOR F MAIN OBS STATOR G GPS ANNUNCIATE VLOC ANNUNCIATE P5001 21 22 25 26 23 24 17 27 28 32 31 33 34 Na 2 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 5001 2 GPS ANNUNCIATE AND P5001 1 ANNUNCIATE DO NOT APPLY TO GPS 500 vLoc LOWER CASE PIN DESIGNATORS ARE SHOWN AS UNDERLINED UPPER CASE LETTERS REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY
14. and the other TSOs and the GARMIN document s which satisfy each requirement for the GNC 500 series be found in GNC 500 Traceability Matrix GPN 005 00096 62 Revision C A list of the technical data required by Notice 8110 60 and the GARMIN document s which satisfy each requirement for the GNC 500 series and the associated FDE Prediction Program is in the GNC 500 FDE Traceability Matrix GPN 005 00096 74 Revision A 500 SERIES INSTALLATION MANUAL Page B 5 P N 190 00181 02 Rev G The GNC 500 series will be manufactured at your Olathe Kansas facility under quality assurance procedures contained in GARMIN Quality Assurance Procedures Manual Revision dated 05 04 2000 or later FAA Approved revisions As GARMIN has previously received TSO C129a Class A1 TSO Authorization for the GNC 500 series products through the Wichita ACO and as GARMIN has met the additional requirements of Notice 8110 60 this letter serves as the Letter of Design Approval for Notice 8110 60 GPS as a Primary Means of Navigation for Oceanic Remot erations for the following GNC 500 series models and FDE Prediction Program GARMIN Part Number GPN Model Description GNS 530 GPS Receiver 10W VHF Comm VOR LOC Glide Slope System GNS 530A 010 00285 GPS Receiver 16W VHF Comm VOR LOC Glide Slope System FDEPRDCT 006 A0072 00 FDE Prediction Program Software Revision B As agreed upon in GNC 400 500 Plan for Software Aspects
15. left tenths gallons hour ZP ASCII characters 89012 represents fuel used left tenths gallons ZQ ASCII characters 345 represents error log reason indicator ZR ASCII characters 678 represents checksum lt STX gt start transmit character 0x02 CR lt LF gt lt gt carriage return character 0x0d line feed character 0x0a sign indicator 0x2b or Ox2d lt ETX gt end transmit character 0x03 Not available from Airdata Computer Note Checksum is calculated by adding each byte in the message including all characters from lt STX gt up to and including the error log reason indicator such that carries are discarded to give a one byte result The ASCII coded decimal representation of that byte is given ranging from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page D 3 RevG This page intentionally left blank Page D 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 Appendix E 500 Series LRU Interface Overview The following tables provide a quick overview of some of the equipment that can be interfaced with the Garmin 500 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 530 LRU I
16. removal and replacement should be in accordance with applicable provisions of AC43 13 1A and 43 13 2A Also refer to section 3 7 of this manual 12 Special Tools N A 13 This Section is for Commuter Category Aircraft Only A Electrical loads Refer to section 1 3 2 of this manual B Methods of balancing flight controls N A C Identification of primary and secondary structures N A D Special repair methods applicable to the airplane Antenna installation removal and replacement should be in accordance with applicable provisions of AC43 13 1B and 43 13 2A 14 Overhaul Period No additional overhaul time limitations 15 Airworthiness Limitation Section Refer to the 500 Series unit Sample Flight Manual Supplement 16 Revision To revise this ICA a letter must be submitted to the local FSDO with a copy of the revised FAA Form 337 and revised ICA The FAA inspector accepts the change by signing Block 3 and including the following statement The attached revised new Instructions for Continued Airworthiness date for the above aircraft or component major alteration have been accepted by the FAA superseding the Instructions for Continued Airworthiness date 17 Assistance Flight Standards Inspectors have the resources to respond to questions regarding the ICA 18 Implementation and Record Keeping For major alterations performed in accordance with FAA field approval policy the owner operator operating under Part 91 is respon
17. the following EFIS systems Sextant SMD 45 Page 5 2 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 SDI Common Common long range navigator only 429 data with SDI 0 is used LNAV 1 Number Pilot long range navigator Only 429 data with SDI 0 or SDI 1 is used LNAV 2 Number 2 Copilot long range navigator Only 429 data with SDI 0 or SDI 2 is used 5 2 2 RS 232 CONFIG Page Select the MAIN RS 232 CONFIG Page see Figure 5 2 If necessary change the selectable RS 232 inputs and or outputs to match that of the equipment installed in the aircraft CHANNEL INPUTS Figure 5 2 MAIN RS 232 CONFIG Page Selection Description Off No unit s connected to input of this channel Arnav ei fuel Serial fuel flow information from the following units ARNAV FC 10 FT 10 Electronics International FP 5L Crossfill Serial transfer of flight plans and user waypoints between two 500 Series units GDL 49 Serial data input for in flight access to weather and messaging Icarus alt Serial altitude data from the following units Icarus Instruments 3000 Sandia SAE5 35 Garmin GTX 327 Transponder Ryan TCAD Traffic information from a Ryan TCAD 9900B Series system Shadin adc Serial air data information from the following units Shadin ADC 200 200 2000 Shadin alt Serial altitude data from the following units Shadin 8800T 9000T 9200T Shadin fadc Serial air data and fuel flow information from the follo
18. 1 ARINC 429 2 GAMA 429 3 GAMA 429 Graphics 4 GAMA 429 Graphics w Int Label ParameterName 1 2 3 4 001 Distanceto Go BCD se fe oe 002 TimetoGo BCD de fe 2 GroundSpeed BCD Jje e 074G Data Record Header 07550 Active WptFrom ToData 100 SelctedCousei 100G Selected Course 5 Checksum 5 114 SDesiedTrack True 500 SERIES INSTALLATION MANUAL Page 4 11 P N 190 00181 02 Rev Label Parameter Name 112 3 4 115 Waypoint Bearing True 1 116 Cross Track Distance 1166 CrossTrackDistanie 121 Horizontal Command to Autopilot 125 Greenwich Mean Time BCD 1 147G Magnetic Variation 251 BDistanetoGo 251G DitanetoGo sd fe 252 TietoGo 1 2600 Date BCD sd te 2618 GPSDisreteWodi 275G LRNSteusWod 11115 3006 Station Declination Type Class Messagelength Type Number 1 3044 MessageCharacters i 3 305G MessaggeCharcters amp 6 lefele 30660 NAV Waypoint Airport Latitude 1 30786 NAV WaypointAiport Longitude 1 310 Presen
19. 115 00345 00 CONNECTOR KIT 011 00351 00 BACK PLATE ASSEMBLY 011 00671 00 GNS 530 PRODUCT INFO KIT K00 00060 00 2 Denotes alternate secondary power input available review installation drawing The connector kit 011 00351 0x includes a single 78 pin high density D connector for P5001 The second 78 pin connector on the back of the 500 Series unit P5050 is for future expansion and is not used at this time There is a separate P5050 connector kit 01 1 00558 00 not included with the 500 Series units The GPS 500 units are available under the following part numbers 3 12 GPS 500 CATALOG ACCESSORIES COLOR ALT PWR P N AVAILABL 010 00176 00 011 00562 00 010 00176 01 011 00562 00 010 00176 10 011 00562 10 010 00176 11 011 00562 10 1 The following accessories are included with the GNS 500 for those indicated with a Y above MOUNTING RACK 115 00345 00 CONNECTOR KIT 011 00351 03 BACK PLATE ASSEMBLY 011 00671 01 GNS 500 PRODUCT INFO KIT K00 00060 01 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 3 1 Rev The following installation accessories are available 1 GPS Antenna Options e GA 56 Antenna Kit without cable Mod 1 or later Garmin P N 010 10040 01 e This kit contains the following items ITEM GARMIN P N GA 56 ANTENNA SUB ASSEMBLY 011 00134 00 BACKING PLATE 115 00031 00 NUT SELF LOCKING 8 32 210 10004 09 ANTENNA GASKET 253 00
20. 42 CONFIG 5 2 18 GAD 42 CONFIG Page Only if 500 Series unit configured for GAD 42 interface Select the GAD 42 CONFIG Page see Figure 5 20 This page allows remote configuration of a GAD 42 Interface Adapter Unit For details of this function please refer to Section 5 of the GAD 42 Installation Manual P N 190 00159 00 Figure 5 20 GAD 42 CONFIG Page DATA LINK 5 2 19 MONITORING THE DATA LINK The Data Link is monitored on the Data Link Page There are four main page groups in the 500 Series software version 2 10 or higher NAV WPT AUX and NRST see the 500 Series Pilot s Guide for detailed information on the unit s Page Groups The Data Link Page Figure 5 21 appears in the sequence of AUX Pages For complete installation and configuration information refer to the GDL 49 installation manual Garmin P N 190 00231 00 Figure 5 21 Data Link Page 500 SERIES INSTALLATION MANUAL Page 5 15 P N 190 00181 02 Rev 5 3 ADDITIONAL GROUND TESTS 5 3 1 Connector Engagement Test 1 Turn on the 500 Series unit and turn on the avionics master switch if applicable 2 Place the 500 Series unit in the rack and engage the pawl mechanism 3 Turn the Allen screw of the locking pawl slowly clockwise until the 500 Series unit just comes on A T handle makes the turns easy to count but do not over tighten 4 Count the number of complete revolutions you can turn the Allen screw until it can not turn any more
21. 429 air data IRU AHRS interconnect Refer to Figure 4 16 on page 4 51 for the ARINC 429 flight control interconnect Refer to Figure 4 17 on page 4 53 for the Traffic Advisory System Interconnect and Figure 4 18 on page 4 55 for the Weather and Terrain Interconnect 500 SERIES INSTALLATION MANUAL Page 4 13 P N 190 0018 1 02 RevG 47 COM VOR ILS AUDIO GNS 530 ONLY 4 7 1 COM VORIILS Audio Function Activation of COM MIC KEY enables COM MIC AUDIO and causes the transceiver to transmit 500 COM AUDIO and 500 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 The COM REMOTE TRANSFER input may be used for EMERGENCY operation of the COM transmitter If the remote transfer switch is depressed for two seconds the active COM frequency changes to 121 50 MHz Once the emergency frequency is activated through COM REMOTE TRANSFER GNS 530 COM transceivers with Mod 2 incorporated ignore inputs from the front panel controls for COM selections only The pilot may exit this independent mode restoring COM selection control to the front panel knobs and buttons by momentarily depressing the COM REMOTE TRANSFER switch When TRANSMIT INTERLOCK is active the GNS 530 COM receiver sensiti
22. 500 Series unit can be configured to track 28 Vdc 14 Vdc 5 Vdc or 5 Vac lighting buses using these inputs Alternatively the 500 Series unit can automatically adjust for ambient lighting conditions based on the photocell Refer to section 5 2 5 4 2 2 3 Antennas Connector VO GPS ANTENNA P5003 COM ANTENNA P5004 VOR LOC ANTENNA P5005 GLIDESLOPE ANTENNA P5007 500 SERIES INSTALLATION MANUAL Page 4 5 P N 190 00181 02 Rev 4 2 3 Power Lighting and Antennas Configuration Refer to section 5 2 5 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 4 on page 4 27 for the power lighting and antennas interconnect 43 ALTIMETER 4 3 1 Altimeter Function Altitude input is required for GPS RAIM calculations and is useful for advisory vertical navigation VNAV calculations 4 3 2 Altimeter Electrical Characteristics PinName Connector Pin FALTITUDEAT 4 55001 69 ALTITUDEA S 5001 68 ALTITUDEB Po 66 ALTITUDE COMMON P5001 60 in These inputs are considered active if either the voltage to ground is 1 9 V or the resistance to ground 15 4375 These inputs are considered inactive if the voltage to ground is 11 33 Vdc Some transponders and other alt
23. ANNUNCIATOR Figure 4 6 Main Indicator Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 31 Page 4 32 blank Rev G 4 11 6 KI 209A Main Indicator Interconnect MIN 30 P5001 MAIN LEFT 21 RIGHT AL TO 39 MAIN FROM 26 MAIN LATERAL FLAG 23 MAIN LATERAL FLAG 24 MAIN UP 27 MAIN DOWN 28 MAIN VERTICAL FLAG 29 MAIN VERTICAL FLAG 30 GPS ANNUNCIATE 2 APPROACH ANNUNCIATE 5 MAIN OBS ROTOR H 52 MAIN OBS ROTOR C 31 MAIN OBS STATOR D 33 MAIN OBS STATOR F 34 MAIN OBS STATOR F 35 MAIN OBS STATOR G 36 P5006 VOR LOC COMPOSITE OUT 8 ILS ENERGIZE 29 GLIDESLOPE UP 32 GLIDESLOPE DOWN FLAG 31 GLIDESLOPE FLAG 30 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 PROPER CONNECTION OF THE RELAY ENGAGE IS DEPENDENT ON THE 3 TO CONNECT P5001 Bendix King K 209A P209A1 20 21 gt 43 gt 42 48 3 27 gt 26 a 23 gt 22 SEE NOTE 2 gt 9 10K OHM SEE NOTE 3 14 10 29 gt 28 gt 25 K 209A PINS 35 AND 36 INPUT OF ITS POWER SUPPLY VOLTAGE REFER TO 209 DOCUMENTATION FOR PROPER CONNECTION THE GNS 530 ADD TWO 10 KOHM 1 4 WATT RESISTORS PINS 33 AND 34 AND ONE BETWEEN P5001 INDICATOR ONE BETWEEN gt 24 Navigatior ior Indic LNAV LATERAL DEV LEFT IN LNAV
24. BW is less than 25 kHz for 25 kHz channeling 6 dB BW is greater than 2 778 kHz for 8 33 kHz channeling 60 dB BW is less than 7 37 kHz for 8 33 kHz channeling Spurious Response Greater than 85 dB Transmitter Power At Least 10 Watts 16 watts for A models Transmitter Duty Cycle Recommended 10 maximum Modulation Capability The modulation shall not be less than 70 and not greater than 98 with a standard modulator signal applied to the transmitter Carrier Noise Level Shall be at least 45 dB S N N Frequency Stability 0 000526 Demodulated Audio Distortion Less than 10 distortion when the transmitter is modulated at least 7096 Sidetone 1 4 Vays into a 500 load when the transmitter is modulated at least 70 Demodulated Audio Response Shall be less than 6 dB when the audio input frequency is varied from 350 to 2500 Hz C37d Class 4 amp 6 may not provide suitable COM transmit range for some high altitude aircraft Specifications shown apply at nominal input voltages of 13 75 Vdc or 27 5 Vdc as applicable and with a nominal 50 ohm resistive load at the antenna connector 500 SERIES INSTALLATION MANUAL Page 1 3 P N 190 00181 02 Rev 1 3 5 VOR Specifications GNS 530 Only TSO C40c JTSO 2C40c RTCA DO 196 EuroCAE ED 22B ICAO Annex 10 Volume Radio Navigation Aids Par 3 3 8 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 V
25. CR gt lt LF gt ZH123 lt CR gt lt LF gt Z1456 lt CR gt lt LF gt ZJ lt gt 78 lt CR gt lt LF gt ZK lt gt 901 lt CR gt lt LF gt ZL234 lt CR gt lt LF gt ZM5678 lt CR gt lt LF gt ZN90123 lt CR gt lt LF gt Z04567 lt CR gt lt LF gt ZP89012 lt CR gt lt LF gt ZQ345 lt CR gt lt LF gt ZR678 lt CR gt lt LF gt lt ETX gt Where ZA ASCII characters 012 represents indicated Air Speed knots ZB ASCII characters 345 represents true Air Speed knots ZC ASCH characters 678 represents Mach Speed thousandths ZD ASCII characters sign 9012 represents pressure altitude tens of feet ZE ASCII characters sign 3456 represents density altitude tens of feet ZF ASCII characters sign 78 represents outside air temperature Celsius ZG ASCII characters sign 90 represents true air temperature Celsius ZH ASCII characters 123 represents wind direction degrees from north ZI ASCII characters 456 represents wind speed knots ZJ ASCII characters sign 78 represents rate of turn degrees per second ZK ASCII characters sign 901 represents vertical speed tens of ft minute ZL ASCII characters 234 represents heading degrees from north ZM ASCII characters 5678 represents fuel flow right tenths gallons hour ZN ASCII characters 90123 represents fuel used right tenths gallons ZO ASCII characters 4567 represents fuel flow
26. DATES AND MAY BE REQUIRED THAT THEY HAVE IDENTICAL VERSIONS OF MAIN SOFTWARE 3 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY 4 REFER TO THE GTX 327 TRANSPONDER INSTALLATION MANUAL 190 00187 02 FOR COMPLETE INFORMATION Figure 4 10 RS 232 Serial Data Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 39 Page 4 40 blank Rev 4 11 10 ARINC 429 EFIS Interconnect IN 500 530 GPS ARINC 429 GPS ARINC 429 IN 1 IN 1 GPS ARINC 429 OUT GPS ARINC 429 OUT VOR ILS ARINC 429 OUT VOR ILS ARINC 429 OUT GPS ARINC GPS ARINC VOR ILS ARINC VOR ILS ARINC GPS ARINC 429 GPS ARINC 429 429 429 429 429 IN 1 1 OUT OUT OUT OUT A LNAV TRANSMITTER A LNAV TRANSMITTER B LRN LNAV 1 RECEIVER A LRN LNAV 1 RECEIVER B LRN LNAV 2 RECEIVER A LRN LNAV 2 RECEIVER B NAV 1 RECEIVER A NAV 1 RECEIVER B NAV 2 RECEIVER A NAV 2 RECEIVER B NOTE 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 THE SDI CONFIGURATIONS LNAV AND VOR ILS OF THE 1 500 530 MUST BE SET TO 1 AND THE SDI OF THE 2 UNIT MUST BE SET TO 2 FOR PROPER OPERATION F THE GPS ARINC 429 IN 1 PORT 25001 48 AND 49 IS ALREADY USED FOR ANOTHER
27. G 500 SERIES INSTALLATION MANUAL P N 190 00181 02 3 44 Mounting Rack Dimensions 0 04 0 710 0580 18 03 14 73 1 1 1 1 i 6 250 158 75 BEZEL 5 800 147 32 Z 6 320 160 53 RACK 2 8 71 12 i t 185 47 0 0 260 147 0 4 1 104 14 6 60 10 65 TO COAXES 269 2 L J 0 407 I D SUB STRAIN RELIEFS 1234 0 125 DIMPLES 48 50 04 i 4 600 0 985 116 84 TO 025 ES 25 02 DIMPLES E 0 985 4 580 25 02 1 841 116 33 146 76 BEZEL 2 4 60 96 NN Z 25 02 1 i 1 841 0 382 0 437 8 000 46 70 15 025 NOTES 11 10 203 20 DIMPLES 1 DIMENSIONS INCH mm 2 GPS 500 UNIT ONLY WEIGHT 5 7 LBS 2 6 KGS INSTALLED WITH RACK AND CONNECTORS WEIGHT 7 2 LBS 3 3 KGS VIDEO CARD CONNECTOR KIT WEIGHT 011 00558 00 0 11 LBS 0 05 KGS 4 CG LOCATION INCLUDES RADIO ONLY Figure 3 8 GNS 530 Mounting Rack Dimensions 500 SERIES INSTALLATION MANUAL Page 3 9 Page 3 10 blank P N 190 00181 02 Rev G 6 250 158 75 BEZEL 0 710 0 580 18 03 14 73 5 800 147 32 0 04 1 0 6 320 160 53 RACK 2 8 71 12 0252 4 1 104 14 10 65 TO COAXES 269 2 10 89 TO D SUB STRAIN RELIEFS 276 5 1 970 0 125 50 04 i T 0 407 10 34 025 DIMPLES i T 4 600 116 84 0 985 25 02 025 DIMPLE
28. Instructions for Continued Airworthiness This permission does not construe suitability of the documents It is the applicant s responsibility to determine the suitability of the documents for the ICA Following is a suggested ICA for a Garmin 500 Series unit installation Some of the checklist items do not apply in which case they should be marked N A Not Applicable In this sample square braces are used to indicate instances where explicit words should be substituted e g replace 500 Series unit with GNS 530 Instructions for Continued Airworthiness Garmin 500 Series unit 1 Introduction Aircraft that has been altered Registration N number Make Model and Serial Number Content Scope Purpose and Arrangement This document identifies the Instructions for Continued Airworthiness for the modification of the above aircraft by installation of a Garmin 500 Series unit Applicability Applies to aircraft altered by installation of the Garmin 500 Series unit Definitions and Abbreviations None N A Precautions None N A Units of Measurement None N A Referenced Publications Garmin 500 Series Installation Manual P N 190 00181 02 Garmin 500 Series unit Maintenance Manual P N 190 00181 05 for GNS 530 190 00181 65 for GPS 500 Garmin STC applicable STC number for the specific model installed refer to Appendix B of this manual Garmin Sample Flight Manual Supplement P N part number of t
29. KEY 4 THE 500 OHM AUDIO OUTPUTS ARE BALANCED OUTPUTS AND THE LO OUTPUTS MUST BE CONNECTED IF THE AUDIO PANEL DOES NOT HAVE A LO INPUT IT SHOULD BE CONNECTED TO A GROUND LUG AT THE AUDIO PANEL COM MIC AUDIO HI INTERCOM MIC HI COM MIC AUDIO LO IS NO OTHER INTERCOM WIRING OPTION P5002 4 INTERCOM SYSTEM IN THE AIRCRAFT USED FOR EMERGENCY OPERATION OF THE COM TRANSMITTER IF THE REMOTE TRANSFER SWITCH IS ACTIVE FOR TWO SECONDS THE ACTIVE COM FREQUENCY WILL CHANGE TO 121 50 MHZ REFER TO SECTION 4 7 1 MICROPHONE SWITCH DPDT 8 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION COM MIC JACK PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY I INTERCOM Figure 4 19 Audio Panel Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 57 Page 4 58 blank RevG 4 11 19 VOR ILS Indicator Interconnect IN 2 2 VOR LOC LEFT VOR LOC RIGHT VOR LOC TO VOR LOC FROM VOR LOC FLAG VOR LOC FLAG VOR LOC SUPERFLAG VOR LOC COMPOSITE OUT ILS ENERGIZE GLIDESLOPE UP GLIDESLOPE DOWN FLAG GLIDESLOPE FLAG GLIDESLOPE SUPERFLAG VOR OBS ROTOR H VOR OBS ROTOR C VOR OBS STATOR D VOR OBS STATOR E G VOR OBS STATOR F P5006 o 29 32 31 30 38 13 11 12 GARMIN GARMIN Bendix King Bendix King
30. LATERAL DEV RIGHT IN LNAV TO IN LNAV FROM IN LNAV LATERAL FLAG IN LNAV LATERAL FLAG IN VERTICAL UP IN LNAV VERTICAL DOWN IN LNAV VERTICAL FLAG IN LNAV VERTICAL FLAG IN RELAY ENGAGE LNAV FCS LOC ENGAGE IN OBS RETURN LNAV OBS EXCITATION IN LNAV OBS SIN OUT LNAV OBS COS OUT VOR LOC COMPOSITE NAV LOC ENGAGE IN NAV VERTICAL UP IN NAV VERTICAL DOWN IN NAV VERTICAL FLAG IN NAV VERTICAL FLAG IN 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT PINOUTS OF OTHER UNITS SHOWN FOR INFORMATION REFERENCE ONLY Figure 4 7 KI 209A Main Indicator Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 33 Page 4 34 blank RevG 4 11 7 KI 208A Main Indicator Interconnect Bendix King 208A P5001 P208A1 MAIN LEFT 21 N qQ 20 LNAV LATERAL DEV LEFT IN MAIN RIGHT 22 21 LNAV LATERAL DEV RIGHT IN x x MAIN TO 25 n 43 LNAV TO IN MAIN FROM 26 y 42 LNAV FROM IN x Y MAIN LATERAL FLAG 23 48 LNAV LATERAL FLAG IN MAIN LATERAL FLAG 24 gt 3 LATERAL FLAG IN x VOR ILS x N C l peo SEE NOTE 2 RELAY GPS APPROACH ANNUNCIATE 5 9 LNAV FCS LOC ENGAGE IN MAIN OBS ROTOR H 32 As 50 OBS RETURN MAIN OBS ROTOR C 31 L e 2 LNAV OBS EXCITATION IN MAIN OBS STATOR D 33 lt 15 LNAV OBS SIN OUT AIN OBS STATOR E 34 MAIN OBS
31. Lightning Direct Effects Equipment identified as Category X no test required Page A 4 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 4 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 151 Street Olathe Kansas 66062 NOTE The following information provides examples only It is not intended to be a comprehensive listing of all test conditions 4 SOS x Aa LLL 5 0 7 0 Equipment tested per DO 160C Par 7 2 1 7 2 7 3 Crash Safety Not Applicable In flight Loss of Cooling Cooling air not required Operational i Equipment tested without shock mounts to Categories L M amp Y Equipment identified as Category X no test required Fluids Susceptibility 11 0 Equipment tested to Category F with Ethylene Glycol De Icing Fluid Equipment identified as Category XXXX no test required Sand and Dust Equipment identified as Category X no test required 500 SERIES INSTALLATION MANUAL Page A 5 P N 190 00181 02 Rev This page intentionally left blank Page A 6 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 Appendix B STC Permission Consistent with N8110 69 or Order 81
32. MARK OUT 16 SEE NOTE 4 DEMO MODE SELECT 5 I 5 NOTE 5 5 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 6 P5001 PINS 73 1 AND 2 HAVE NO FUNCTION ON GPS 500 2 INITIAL CERTIFICATION OF THE 500 SERIES WAS ACCOMPLISHED 7 SINCE THE GNS 530 INCLUDES ONLY AN OBS ANNUNCIATOR WITHOUT USE OF ANY REMOTE SWITCHES OR ANNUNCIATORS NOT AN AUTO ANNUNCIATOR FOR THE NORMAL CASE SINCE THE SAME SWITCHING AND ANNUNCIATION IS AVAILABLE THE RELAY ARRANGEMENT SHOWN MAY 8E USED IF ON THE FRONT PANEL OF THE GPS HOWEVER IF THE DESIRED TO ANNUNCIATE AUTO UNIT IS NOT INSTALLED IN THE PILOT S NORMAL FIELD OF VIEW SOME OR ALL OF THE REMOTE SWITCHES AND ANNUNCIATORS 8 REFER TO MANUFACTURERS DOCUMENTATION FOR MAY BE REQUIRED BY YOUR CERTIFICATION AGENCY COMPLETE PINOUT AND INTERCONNECT INFORMATION 3 AN EXTERNAL MOMENTARY VLOC GPS SWITCH ANNUNCIATOR PINDUFS OTHER UNITS SHOWN POR REFERENCE ONLY OR ANNUNCIATOR WITH NO SWITCH MAY BE USED IN A GNS 530 INSTALLATION A SWITCH SERVES THE SAME PURPOSE AS THE CDI BUTTON ON THE FRONT OF THE GNS 530 4 TIME MARK OUT P5001 16 OUTPUTS A 1 MILLISECOND WIDE PULSE ONCE PER SECOND 5 DEMO MODE SELECT 5001 75 MAY BE GROUNDED TO START THE UNIT IN DEMO MODE DO NOT USE IN AN AIRCRAFT INSTALLATION Figure 4 9 Annunciators Switches Interconnect 500 SERIES INSTALLATION MANUAL Page 4 37 Page 4 38 blank P N 190 00181 02 RevG 4 11 9 RS 232 Serial Data Intercon
33. Minimum LNA Bandwidth 3 dB 20 dB 40 dB 3 Radiation Characteristics Polarization Operating Frequency Gain axis at 160 beam width Cross Pole Gain LHCP on axis at 160 beam width 4 Mounting Requirements Cable connection Mounting studs 40 MHz Maximum 100 MHz Maximum 250 MHz Maximum RHCP 1575 42 2 00 MHz 2 0 dBic Minimum 6 0 dBic Minimum 8 dBic Maximum 9 dBic Maximum BNC Female Four 8 32 UNC 2A studs 0 50 long Page 2 4 Rev G 500 SERIES INSTALLATION MANUAL P N 190 00181 02 3 INSTALLATION PROCEDURE 3 1 UNIT AND ACCESSORIES The GNS 530 units are available under the following part numbers 3 1 1 CATALOG P N 010 00182 00 GNS 530 011 00550 00 2 ACCESSORIES N OPERATING VOLTAGE 28 MINIMUM XMIT PWR 010 00182 01 011 00550 00 28 010 00182 10 011 00550 10 14 or 28 Vdc 010 00182 11 011 00550 10 14 or 28 Vdc 010 00182 30 011 00550 30 14 or 28 V 2 010 00182 31 011 00550 30 14 or 28 V 2 010 00285 00 011 00835 00 28 Vdc 010 00285 01 011 00835 00 28 Vdc 010 00285 10 011 00835 10 28 Vde 2 010 00285 11 011 00835 10 lt lt lt lt Z Z Z Z Z Z 2 2 4 2 4 2 4 28 Vde 2 1 The following accessories are included with the GNS 530 for those indicated with a Y above MOUNTING RACK
34. NOTE 42 429 TX 1A GPS ARINC 429 IN 1 B 49 c 43 429 TX 1B AIRCRAFT GROUND 78 gt DISPLAY GROUND ANNUNCIATE D 10 19 SCFT KEY 2 TEST ALT ANNUNCIATE E 11 21 SOFT KEY 4 OPR STB EC 4 POWER SWITCH HI 5 POWER SWITCH LO IN Ryan CAD P deser CAD rocessor 550 5001 ET SOFTWARE 2 11 OR HIGHER GPS RS 232 OUT 2 58 f 19 RS 232 RX 2 cy m Y GPS RS 232 IN 2 59 17 RS 232 TX 2 18 85 232 GROUND 2 OPTIONAL REMOTE MUTE SWITCH 5 REMOTE MUTE TO OPTIONAL LAMP OR SONALERT lt 6 TRAFFIC ANNUNCIATE OUT SEE NOTE 4 gt 16 SwITCH NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 6 IN ORDER FOR RYAN TCAD TRAFFIC TO BE DISPLAYED ON THE 2 THE SKYWATCH POWER SWITCH PINS SHOWN ON P1 IF THE GPS ARINC 429 IN 1 PORT 5001 48 AND 49 IS ALREADY USED FOR ANOTHER PURPOSE THE GPS ARINC 429 IN 2 PORT 5001 50 AND 51 MAY BE CONNECTED INSTEAD 7 SHOULD BE CONNECTED TOGETHER TO TURN THE PROCESSOR UNIT ON AND OPEN TO TURN THIS UNIT OFF IF A SKYWATCH CONTROL DISPLAY UNIT 15 NOT IN THE INSTALLATION A DEDICATED SWITCH MAY BE REQUIRED TO TURN THE SKYWATCH PROCESSOR UNIT ON AND OFF THE RYAN TCAD PROCESSOR SWITCH PIN P1 16 SHOULD BE Z GROUNDED TO TURN THE PROCESSOR UNIT ON AND OPEN JO TURN THIS UNIT OFF IF A RYAN TCAD DISPLAY UNIT IS NOT IN THE INSTALLATION A DEDICATED SWITCH MAY BE REQUIRED TO TURN THE TCAD PROCESSOR UNIT ON AND OFF 9 IF OF THESE TRAFFIC SYSTEMS IS INSTALLED WITHOUT A C
35. PURPOSE THE GPS ARINC 429 IN 2 PORT P5001 50 AND 51 MAY BE CONNECTED INSTEAD m 4 THE DEPICTED COLLINS EFIS 84 INTERFACE DOES NOT SUPPORT SELECTION OF THE GPS COURSE VIA THE EFIS CONTROL PANEL A GARMIN GAD 42 IS REQUIRED FOR GPS SELECTED COURSE REFER TO THE GAD 42 INSTALLATION MANUAL 5 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY Bendix King EFIS 84 EFS 40 50 DPU 84 SG 465 P5001 P4652A P4652B 48 lt Q N _ _ 47 3 SEE NOTE 49 lt 20 46 142 67 47 j En de 138 53 I Y 122 64 5006 126 63 530 ONLY m eh 125 16 23 129 29 38 go 25 Bendix King EFIS 84 EFS 40 50 DPL 84 SG 465 P5001 P1 P4652A P46528 48 47 3 SEE NOTE 49 lt 20 x 142 67 gt 138 53 46 gt 122 64 47 t 126 63 P5006 16 530 ONLY H 29 Z 3 Ga 25 c 129 25 MS NC 429 LNAV TRANSMITTER A LNAV TRANSMITTER B LRN LNAV 1 RECEIVER A LRN LNAV 1 RECEIVER B LRN LNAV 2 RECEIVER A LRN LNAV 2 RECEIVER B NAV NAV NAV NAV N RECEIVER RECEIVER RECEIVER RECEIVER A A Figure 4 11 ARINC 429 EFIS Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 41 Page 4 42 blank Rev G 4 11 11 ARINC 429 Sandel EHSI Interconnect 1 500 Ser
36. Power Input requirements Lighting Bus input and Antenna connections 4 22 Power Lighting and Antennas Electrical Characteristics Aircraft Power PinName Connector Pin AIRCRAFT GROUND Po 77 AIRCRAFT GROUND 5001 78 AIRCRAFT GROUND P8002 21 AIRCRAFT GROUND 5002 22 AIRCRAFT GROUND P5000 4 Optional alternate power applies only to GNS 530 part numbers 011 00550 30 GNS 530A 011 00835 10 and GPS 500 part number 011 00562 10 To operate the GNS 530 P N 011 00550 00 COM transceiver in a 14 volt aircraft A 14 to 28 volt converter such as a KGS Electronics models RB 126 or UC 14 28 or equivalent must be used The voltage converter should include exactly one short circuit protection device on its output such as a circuit breaker P5002 11 and P5002 12 supply power to the COM transmitter The other power input pins P5001 19 P5001 20 and P5006 44 accept 11 33 Vdc GNS 530 P N 011 00550 10 accepts 11 33 Vdc on all power inputs Refer to Figure 4 4 on page 4 27 A power connection on P5006 44 is only required if NAV SUPERFLAG or G S SUPERFLAG is utilized The power inputs P5001 19 and P5001 20 provide power for all functions of the 500 Series unit except the COM transmitter and the NAV amp G S SUPERFLAG outputs 4 2 2 2 Lighting Bus Connector Pin VO LIGHTING BUS HI P5001 LIGHTING BUS LO P5001 The
37. RE 4 23 RE 4 24 RE 4 25 RE 5 1 RE 5 2 RE 5 3 RE 5 4 RE 5 5 RE 5 6 RE 5 7 RE 5 8 RE 5 9 RE 5 10 RE 5 11 RE 5 12 RE 5 13 RE 5 14 RE 5 15 RE 5 16 RE 5 17 RE 5 18 RE 5 19 RE 5 20 RE 5 21 GPS ANTENNA INSTALLATION CONSIDERATIONS eee ee enne 2 2 CABDEINSTADEATION ertet errem E ESEE 3 4 56 ANTENNA INSTALLATION DRAWING 3 7 GNS 530 MOUNTING RACK DIMENSIONS eee ee eee nennen nennen enne 3 9 GPS 500 MOUNTING RACK DIMENSIONS eene ee eene en eren enne 3 11 GNS 530 MOUNTING RACK INSTALLATION e nnn e nen nennen 3 13 GPS 500 MOUNTING RACK INSTALLATION eee een ee emen rennen 3 15 500 SERIES RECOMMENDED PANEL CUTOUT DIMENSIONS sse 3 17 500 SERIES SYSTEM INTERFACE DIAGRAM eee ee GNS 530 TYPICAT INSTALDATIQN ert terea rir e es Re E GPS 500 TYPICAL INSTALLATION incor rene ern D dp baa OQ POWER LIGHTING AND ANTENNAS INTERCONNECT ALTIMETER INTERCONNECT Hee e e Pad UI e EAT UMS ass MAIN INDICATOR INTERCONNECT KI 209A MAIN INDICATOR INTERCONNECT KI 208A MAIN INDICATOR INTERCONNECT ANNUNCIATORS SWITCHES INTERCONNECT 5 232 SERIAL DATA INTERCONNECT ARINC 429 EFIS INTERCONNECT orrir niter tret enin pe orte tie oberen teen eed Doe ARIN
38. Refer to section 5 2 11 for the DME tuning configuration 4 10 4 DME Tuning Calibration and Checkout None 4 10 5 DME Tuning Interconnect Refer to Figure 4 22 on page 4 63 for the King Serial Panel DME tuning interconnect Refer to Figure 4 23 on page 4 65 for the King Serial Remote DME tuning interconnect Refer to Figure 4 24 on page 4 67 for the parallel 2 of 5 DME tuning interconnect Refer to Figure 4 25 on page 4 69 for the parallel BCD Slip Code DME tuning interconnect NOTE For the GNS 530 to tune a Narco DME 890 or IDME 891 or an ARC Cessna RTA 576A using parallel 2 of 5 unique wiring and configuration are required Refer to section 5 2 11 on page 5 12 and Figure 4 24 on page 4 67 Page 4 20 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 0 18100 061 N d GARMIN 500 530 CONNECTOR P5001 RMI AIRCRAFT POWER POWER amp GROUND MAIN 081 3 AIRCRAFT LIGHTING BUS gt LIGHTING BUS EXTERNAL INSTRUMENTATION lt TIME MARK OUT LEV NOLLV TIV LSNI SHISSS 005 GARMIN MAIN CDI HSI 400 500 SERIES l ops rs 232 n s DEVIATION amp FLAGS 6 GPS VOR ILS CPS RS 232 OUT 3 TO FROM C ROSSFILL VERT DEVIATION amp FLAGS Z SUPERFLAGS 7 wesbeig 5 seues 00 LLL S193NNOOHUZINI S3lH3S 00S ENCODING MAIN OBS 7 ALTIMETER 31 GRAY CODE ALTITUDE SWITCHES SWITCHES lt FUEL AIR DATA ANNUNCIATORS
39. degrees Ground speed in knots Distance to waypoint in tenths of nautical miles Cross track error where S L left or R right of course nnnn error in hundredths of nautical miles Desired track in tenths of degrees Destination waypoint identifier will be blank filled on right if less than 5 characters in identifier Magnetic variation where S E east or W west ddd tenths of degrees Nav valid flag status where f N nav flagged or nav valid T Warnings status only data transmitted are dashes Used to indicate end of Type 1 sentences lower case Distance to destination waypoint in tenths of nautical Lima miles The altitude is not output if the RS 232 port is configured as Avtn no alt The line feed character is not output if the RS 232 port is configured as Avtn no alt Page C 2 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 C 4 OUTPUT SENTENCE TYPE 2 The 500 Series Type 2 output sentence shall have the following general format id item designator 3 ASCII characters seq sequence number 1 binary byte wpt waypoint identifier 5 ASCH characters lat waypoint latitude 3 binary bytes lon waypoint longitude 4 binary bytes myar magnetic variation at waypoint 2 binary bytes CR ASCII carriage return character OD hex LF ASCII line feed character 0A hex Each waypoint in the route being navigated by the 500 Series unit shall h
40. of the VOR ROTOR C output Each pair is intended to read one of the two windings of the indicator s OBS stator 4 8 2 6 VOR LOC COMPOSITE Connector Pin VOR LOC COMPOSITE OUT P5006 8 Out With a Standard VOR Test Signal applied VOR LOC COMPOSITE OUT is 0 5 0 1 into a 10 load With a Standard Localizer Centering Test Signal applied VOR LOC COMPOSITE OUT is 0 350 0 05 Vrms into a 10 kQ load 4 8 2 7 ILS ENERGIZE Connector Pin VO The driver output voltage is not more than 1 0 V when sinking 20 mA The maximum off state leakage current with respect to GND is less than 10 HA 4 8 3 VOR ILS Indicator Configuration Refer to section 5 2 11 for the VOR LOC GS configuration 4 8 4 VOR ILS Indicator Calibration and Checkout Refer to sections 5 2 11 and 5 3 8 for the VOR LOC GS checkout 4 8 5 5 Indicator Interconnect Refer to Figure 4 20 on page 4 59 for the VOR ILS indicator interconnect 500 SERIES INSTALLATION MANUAL Page 4 17 P N 190 00181 02 Rev 4 9 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 500 Series unit s GPS navigation For the GNS 530 the MAIN OBI output may be configured so that it sends VOR ILS bearing information when VLOC is selected by the GNS 530 CDI key The VOR OBI output provides bearing information from the active waypoint fo
41. or OPER In standby mode verify that the Skywatch may be placed in self test mode by highlighting Test Mode and pressing ENTER on the 500 Series unit Refer to the BFG Skywatch installation manual for system checkout For Ryan TCAD see Figure 5 18 this page shows the current shield mode and altitude Verify that the TCAD shield mode may be changed Ground GND Terminal TML Standard STD En Route ENR or Unrestricted UNR and that the TCAD is reporting the correct altitude Refer to the Ryan TCAD installation manual for system checkout Figure 5 16 STORMSCOPE DOWNLOAD DATA Page TRAFFIC Test Mode Figure 5 17 TRAFFIC Page Skywatch TRAFFIC Figure 5 18 TRAFFIC Page TCAD Page 5 14 Rev 500 SERIES INSTALLATION MANUAL P N 190 00181 02 5 2 17 RYAN TCAD CONFIG Page Only if 500 Series unit configured for Ryan TCAD interface Select the RYAN TCAD CONFIG Page see Figure 5 19 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 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 1f a mute switch is installed are shown Refer to the Ryan TCAD installation manual for system checkout Figure 5 19 RYAN TCAD CONFIG Page GAD
42. range of 3 to 7 and is set to 4 at the factory MIN Minimum Sets the minimum brightness of the display The higher the number the brighter the minimum brightness Display minimum brightness has a range of 35 to 999 and is set to 80 at the factory Key minimum brightness has a range of 20 to 99 and is set to 40 at the factory It is prudent to verify that display and key lighting characteristics match those of other equipment in the panel under night lighting conditions 500 SERIES INSTALLATION MANUAL Page 5 5 P N 190 00181 02 RevG SLOPE Sets the sensitivity the brightness of the display has to changes in the input level The higher the number the brighter the display 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 PHOTO TRANS Photocell Transition Percentage When a lighting bus is used to control the lighting of the display see Figure 5 6 this parameter sets the point on the lighting bus control below which the display brightness tracks the 500 Series unit s photocell This field has a range of 0 zero to 99 and is set to 25 at the factory PHOTO SLP OFFST Photocell Slope Offset These fields are equivalent to the S
43. with the requirements for GPS primary means of navigation in oceanic and remote airspace when used in conjunction with the 500 Series Trainer Program incorporating the FDE Prediction Program This does not constitute an operational approval The Garmin 500 Series Main and GPS Software version 3 00 and higher incorporate Fault Detection and Exclusion FDE display interface and control satisfying the requirements for GPS as a Primary Means of Navigation for Oceanic Remote Operations per FAA Notice N8110 60 Fault Detection and Exclusion consists of two parts The fault detection function detects a satellite failure that can affect navigation The exclusion function refers to the capability of excluding one or more failed satellites and preventing them from affecting navigation FDE is provided for Oceanic and Remote Operations non precision approaches en route and terminal phases of flight FDE for non oceanic flight phases adhere to the same missed alert probability false alert probability and failed exclusion probability specified by N8110 60 500 SERIES INSTALLATION MANUAL Page 1 7 P N 190 00181 02 RevG The FDE function is built into the GPS 500 GNS 530 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 500 Series Trainer software includes an FDE Prediction Program to meet the requiremen
44. 0 1 inches of water Potential damage to your 500 Series unit may occur by using outside forced air to cool the equipment Therefore it is recommended that an electric forced air fan be installed of the indicated rating to cool this equipment Units tightly packed in the avionics stack heat each other through radiation convection and sometimes by direct conduction Even a single unit operates at a much higher temperature in still air than in moving air Fans or some other means of moving the air around electronic equipment are usually a worthwhile investment A 5 8 diameter air fitting is provided on the rear of the mounting rack for the purpose of admitting cooling air under such conditions If a form of forced air cooling is installed make certain that rainwater cannot enter and be sprayed on the equipment 2 6 MINIMUM INSTALLATION REQUIREMENTS Below is a list of required devices for TSO C129a category A1 and A2 certification For a specific list of equipment used in the initial STC obtain a copy of GNS 530 in Piper PA32 Documented Installation P N 190 00181 06 Deviations from that set of equipment should be approved by the FAA or the governing organization Pressure Altitude Device This device delivers pressure altitude data to the 500 Series unit This data can come from a parallel encoding altimeter blind encoder serializer or an air data system Manual Course Device Required for GNS 530 Only This device delivers the ma
45. 002 00 e GA 56 Flange Mount Antenna Kit Mod 1 or later Garmin P N 010 10040 02 e This kit contains the following items GARMIN P N MOUNT GA 56 ANTENNA 011 00147 00 SUB ASSEMBLY NUT PLATE 115 00080 00 1 SCREW 10 32 x 5 8 211 62212 14 ANTENNA GASKET 253 00011 00 2 Other accessories include the following GPS 500 SAMPLE AIRPLANE FLIGHT GNS 530 SAMPLE AIRPLANE FLIGHT 190 00181 04 MANUAL SUPPLEMENT A mounting rack is required for approved installations The following hardware is required for installation of the mounting rack but is not provided 6 32 Flat Head Screw 6 ea 6 32 Self locking Nut 6 ea Page 3 2 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 3 2 DATA BASE OPTIONS ITEM GARMIN P N DATA CARD WORLD WIDE 010 10201 00 DATA CARD AMERICAS 010 10201 01 DATA CARD INTERNATIONAL 010 10201 02 3 3 MISCELLANEOUS OPTIONS ITEM GARMIN P N CONNECTOR BNC MALE CLAMP 330 00087 00 LOW LOSS AVIATION ANTENNA 320 00003 00 EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR 15 FT LOW LOSS AVIATION ANTENNA 320 00003 02 EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR 30 FT GPS 1 57542 GHz NOTCH FILTER 330 00067 00 3 4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED The following installation accessories are required but not provided COM Antenna GNS 530 Only Shall meet TSO C37 and C38 Broad band 50 Q vertically polarized with coaxial cable VOR
46. 0A P N 011 00835 10 22 1 9 GNS 530 P N 011 00550 10 11 38 VOLTS DC P A NAV FLAC CIRCUIT GNS 530 P N 011 00550 30 p 530 ONLY BREAKER 5 A 44 2 AIRCRAFT POWER SEE NOTES 2 3 AND 6 4 THE 500 SERIES UNIT SHOULD BE CONFIGURED FOR THE CORRECT 5 LIGHTING BUS VOLTAGE 28 VDC 14 VDC 5 VDC OR 5 VAC P5003 POST INSTALLATION NO DAMAGE WILL OCCUR IF THE UNIT c IS CONFIGURED INCORRECTLY IN ADDITION LIGHTING LT ANTENNA CAN BE SET TO AUTOMATICALLY COMPENSATE FOR AMBIENT BEUUA NEZ LIGHTING CONDITIONS USING ITS PHOTOCELL A MANUAL 530 ONLY LIGHTING CONTROL OPTION IS ALSO AVAILABLE REFER TO s COMM THE POST INSTALLATION CONFIGURATION PROCEDURE ANTENNA 5 MAXIMUM ALLOWABLE WIRE GAUGE INTO P5002 PINS IS 530 ONLY 22 AWG FOR 18 AWG WIRE USE SPECIAL 18 AWG a Cyr TERMINATION SOCKET CONTACT 336 00023 00 SUPPLIED WITH Er CONNECTOR KIT PROTECT EXPOSED CONDUCTOR ON SPECIAL P5007 LARGE TERMINATION CONTACTS WITH 3 8 1 cm LENGTH OF 530 ONLY SHRINK TUBING ALSO SUPPLIED WITH CONNECTOR KIT G S 6 THE AIRCRAFT POWER INPUT 5006 44 PROVIDES POWER FOR THE VOR LOC SUPERFLAG P4006 15 AND GLIDESLOPE SUPERFLAG 5006 38 OUTPUTS ON P5006 44 NO POWER CONNECTION IS REQUIRED IF THESE FLAG OUTPUTS ARE NOT USED 7 OPTIONAL ALTERNATE POWER APPLIES ONLY TO PART NUMBERS 011 00550 30 AND 011 00855 10 GNS 530 A AND 011 00562 10 GPS 500 Figure 4 4
47. 1 15 73 CDISOURCE SELECT y 74 RESERVED 1 11 Ooa 75 MODE SELECT n 76 RESERVED 11 1 1 1 77 AIRCRAFTGROUND 78 AIRCRAFTGROUND Applies only to GNS 530 part numbers 011 00550 30 GNS 530A 011 00835 10 and GPS 500 part number 011 00562 10 For applications requiring secondary or alternate power bus input Page 4 2 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 4 1 2 P5050 View of J5050 connector from back of unit ee 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 e 99909 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 9999996996 6 6 6 2 3 4 5 6 7 8 9 10 e 1 11 12 13 14 15 16 17 18 19 20 1 59 SPARES 60 GPSRS2320UT5 Ct 61 GPSRS232IN5 1 Wm 63 GPS RS 232 IN 6 Not implemented at time of publication m 64 78 SPARES 4 1 3 P5002 GNS 530 Only View of J5002 connector from back of unit 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 Pin PinName 1 1 RESERVED 2 RESERVED j 3 RESERVED 0 4 COMMICKEY ti 5 INTERCOMMICHI 6 COMMICAUDIOH in 8 RESERVED 9 RESERVED 0 10 RESERV
48. 1 P4202 x x KK w l i i i i i 1 i i i 1 i i ji 1 l 1 ji 1 l 1 1 1 l l n 1 T 1 1 l L 1 1 j 1 1 I l 1 l T 1 LNAV LNAV AFCS ROLL LNAV LNAV Cor 1 RECEIVER A 1 RECEIVER B 420 GENERAL A 420 GENERAL B STEERING STRAP 2 RECEIVER A 2 RECEIVER B Figure 4 16 ARINC 429 Flight Control Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 51 Page 4 52 blank RevG 0 18100 061 N d GARMIN Bendix King KTA 870 KMH 880 NOLLV TIV LSNI SHISSS 00 19 uuo21 lul uiajs S AJOSIApY 9L LE oeuuo2J8ju W JS S 77 4 93ed oSeq D AY 500 530 P5001 P10 GPS ARINC 429 IN 1 A 48 54 CDU 429 A 7X GPS ARINC 429 IN 1 B 49 j Jg 55 CDU 429 B 7X ANNUNCIAI D 10 2 TAS TEST IN ANNUNCIAI E 11 gt 25 TAS STBY GARMIN Goodrich LARM SKY 497 50 0 500 530 P5001 P1 SOFTWARE 1 6 OR HIGHER GPS ARINC 429 IN 1 4B SEE 34 429 TX 1A GPS ARINC 429 IN 1 B 49 J 33 429 TX 1B AIRCRAFT GROUND 78 14 DISPLAY GROUND ANNUNCIATE D 10 gt 85 SOFT KEY 1 TEST ALT ANNUNCIATE E 11 82 SOFT KEY 4 OPR STB Pet NOTES 11 POWER SWITCH HI y 3 POWER SWITCH LO 5 Goodrich MIN od Ds SKY 899 530 P5001 PI GPS ARNC 429 IN 1 A 48 a SFE
49. 10 4 Aviation Authority approved installers are hereby granted permission to use STC SA00864WI GNS 530 data to modify aircraft Please contact Garmin for GPS 500 STC information Pages B 3 and B 4 provide clarification as to the approval basis for the Garmin GNS 430 without external switching or annunciation There is a great degree of similarity between the switching and annunciation characteristics of the 500 Series units and of the GNS 430 In addition the following is excerpted from a Federal Aviation Administration FAA memorandum titled INFORMATION Q amp A from Seattle Avionics Workshop Navigation Related dated July 12 1999 The horizontal and vertical deviations display s and failure annunciation should be located within the pilot s primary field of view 1 within 15 degrees of the pilot s primary line of sight as should any indication requiring immediate aircrew action Other annunciations should be installed in the normal field of view e g a location in the center radio stack or other location on the pilot s panel within the field of view at a height suitable for normal viewing from the pilot s seated position This includes loss of integrity monitoring RAIM waypoint sequencing start of a turn turn anticipation TO FROM indication approach mode annunciation and automatic mode switching Pages B5 and B6 document the FAA design approval indicating compliance with FAA Notice N8110 60 As such the 500
50. 4 003 Bendix King KAD 280 480 Shadin ADC 2000 Airdata AHRS Heading altitude temperature and speed information from an Airdata AHRS system Traffic Advisory Traffic informaiton from the following traffic advisory systems BF Goodrich SKY497 Skywatch Skywatch HP Bendix King KTA 870 KMH880 BFG SkyWatch Traffic information from a BF Goodrich SKY497 Skywatch system EFIS Selected course heading and joystick waypoint information from the following EFIS systems Bendix King EFS 40 50 Certain versions of Collins EFIS may also be compatible with this format 500 SERIES INSTALLATION MANUAL Page 5 1 P N 190 00181 02 Rev G DATA IN 1 DATA IN 2 cont EFIS Airdata Selected course heading Joystick waypoint altitude temperature and speed information from the following systems Collins Pro Line 21 Flight control Selected course information from the following Flight Control systems Bendix King KFC 400 Garmin GAD 42 Selected course heading and true airspeed data from the Garmin GAD 42 Honeywell EFIS Selected course heading and joystick waypoint information from the following EFIS systems Honeywell Primus 1000 INS IRU Heading information from the following Inertial systems Bendix King KAH 460 Collins AHC 85 Honeywell Laseref Litef LTR 81 Litton LTN 90 100 LTN 91 LTN 92 Radar graphics Joystick waypoint information from a RADAR graphics unit Sandel EHSI Selected course and heading information from the follow
51. 500 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 ANTENNA CONSIDERATIONS Antenna installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such antenna installations incorporate alteration penetration of the cabin pressure vessel by connector holes and or mounting arrangements For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations it is recommended that the installer proceed according to any of the following listed alternatives 1 Obtain approved antenna installation design data from the aircraft manufacturer 2 Obtain an FAA approved STC pertaining to and valid for the antenna installation 3 Contact the FAA Aircraft Certification Office in the appropriate Region and request identification of FAA Designated Engineering Representatives DERs who are authorized to prepare and approve the required antenna installation engineering data 4 Obtain FAA Advisory Circular AC 183C and identify a DER from the roster of individuals in it 5 Contact an aviation industry organization such as the Aircraft Electronics Association for assistance 2 21 GPS ANTENNA LOCATION The GA 56 Antenna must be
52. 900 SERIES INSTALLATION MANUAL GPS 900 and GNS 9904 GNS is a trademark of Garmin Ltd or its subsidiaries and may not be used without the express permission of Garmin eb foBs Msc f AV PROC Garmin International Inc 190 00181 02 Revision G May 2003 Copyright 1998 2003 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 Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 Aviation Panel Mount Technical Support Line Toll Free 1 888 606 5482 Web Site Address www garmin com RECORD OF REVISIONS Revision Revision Description Date 2 10 00 Initial Initial Release 12684 sa 3 6 00 massa new installation Add n
53. AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY Figure 4 20 VOR ILS Indicator Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 59 Page 4 60 blank Rev G 4 11 20 RMI OBI Interconnect P5001 MAIN OBI CLOCK 43 e MAIN OBI DATA 44 MAIN OBL SYNC 45 VOR OBI CLOCK VOR OBI DATA VOR OBI SYNC MAIN OBI CLOCK MAIN OBI DATA MAIN OBI SYNC NOTES 118 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED IF IT IS DESIRED FOR THE RMI THE CDI BUTTON ON THE FRONT PANEL OF THE GNS 530 INSTALL AS PER THE TOP DIAGRAM AND SELECT TRACK CDI FOR THE OBI SOURCE FIELD OF THE MAIN CDI OBS CONFIG PAGE POINTER TO SWITCH WITH IF IT IS DESIRED TO USE A SEPARATE SWITCH FOR THE RMI POINTER INSTALL AS PER THE BOTTOM DIAGRAM AND SELECT ALWAYS GPS FOR THE OBI SOURCE FIELD OF THE MAIN CDI OBS CONFIG PAGE REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCF ONLY Bendix King Bendix King Bendix King Bendix King 229 KNI 582 KNI 582 KDA 692 Pointer 1 Pointer 2 P2291 P5821 P5821 P6921 12 8 7 11 19 17 16 E 11 55 24 M Bendix King Bendix King Bendix King Bendix King 229 KNI 582 KNI 582 KDA 692 Pointer 1 Pointer 2 P2291 P5821 P5821 P6921 12 8 7 11 19 17 16 L 11 33 24 M OBI OB
54. Bendix King Bendix King Bendix King Bendix King Bendix King Bendix King 102 A Gl 106 A 202 206 203 204 208 209 208A 209A 1 P1 P2021 P2061 P2031 P2041 P2081 P2091 P208A1 P209A1 e 11 11 N N LEFT V CE qo 12 J J RIGHT 9 3 E E e TO g 10 10 s s FROM 7 7 N N _ FLAG J g 8 8 F F FLAG E ES NAV SUPERFLAG c NAV SUPERFLAG LO Y Y 2 2 6 6 VOR LOC COMPOSITE 5 K K 4 4 10 10 ILS ENERGIZE E x S K 3 29 UP o 14 M M 6 28 DOWN 15 H H 9 x 25 GLIDESLOPE FLAG gt 16 J J 12 24 GLIDESLOPE FLAG r gt GLIDESLOPE SUPERFLAG e GLIDESLOPE SUPERFLAG LO A 1 1 o OBS A H We 2 2 2 2 es OBS C 3 3 L L 5 OBS D COS HI 5 5 u 085 E COS LO r 4 4 T T E OBS F SIN H 7 6 6 w w OBS G SIN LO r NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 LOWER CASE PIN DESIGNATORS ARE SHOWN AS UNDERLINED UPPER CASE LETTERS 3 THIS INTERCONNECT APPLIES ONLY WHEN IT IS DESIRED FOR A SEPARATE INDICATOR TO DISPLAY CNS 530 VOR ILS INFORMATION REGARDLESS OF THE CDI BUTTON STATUS 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT
55. Bendix King KDI 572 KDI 574 P5006 P5721 P5741 19 11 11 18 12 12 20 17 17 N C gt 33 33 22 48 48 M 49 49 15 15 Bendix King Bendix King KN 635 KDM 706 50 P651 P7061 19 6 9 18 F 8 20 Ce D 24 22 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED Zi THE GNS 530 MUST BE CONFIGURED AT INSTALLATION TO OUTPUT KING SERIAL DME TUNING DATA FOR PROPER OPERATION OF THIS INTERFACE REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY DATA BUS CLOCK BUS DME REQUEST Figure 4 23 King Serial Remote DME Tuning Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 65 Page 4 66 blank Rev G 4 11 23 Parallel 2 OF 5 DME Tuning Interconnect SER DME CHAN REQ PAR SER DME RNAV MODE PAR DME 2M PARALLEL DME 8MHZ HZ PARALLEL DME 1MHZ PARALLEL DME 800KHZ PARALLEL DME 400KHZ PARALLEL DME 200KHZ PARALLEL DME 100KHZ PARALLEL 5 DME COMMON NOTES 1 ALL WIRES 24 AWG O 2 THE GNS 530 MUST B DME CHANNELLI MODEL OF DME 3 THE GNS 530 M M CHANNELLI OF DME gt om E o 4 REFER TO MANUF COMPLETE PINOUT A PINOUTS OF OTH RGER UN CONFIGURED FOR FORMATION HOWN FOR REFERENCE ONLY RCONNECT
56. C 429 SANDEL EHSI INTERCONN 1 500 SERIES UNIT 1 SANDEL SN3308 ARINC 429 SANDEL EHSI INTERCONNECT 2 GNS 530 1 SANDEL SN3308 ARINC 429 SANDEL EHSI INTERCONNECT 2 GNS 530 2 SANDEL SN3308 ARINC 429 AIR DATA IRU AHRS INTERCONNECT ARINC 429 FLIGHT CONTROL INTERCONNECT TRAFFIC ADVISORY SYSTEM INTERCONNECT WEATHER AND TERRAIN INTERCONNECT AUDIO PANEL INTERCONNEGCT iret or e iie At dh iei epit or Tasa VOR ILS INDICATOR INTERCONNECT teet there t reb erii ipee re teria KING SERIAL PANEL DME KING SERIAL REMOTE DME TUNING INTERCONNECT PARALLEL 2 OF 5 DME TUNING INTERCONNECT PARALLEL BCD SLIP CODE DME TUNING MAIN ARINC 429 CONBIG PAGE ete te eret ito ined rete oe 5 1 MAIN RS 232 CONFIG PAGE tenet eite rette tret eret ore tene erae 5 3 MAIN ANBUTS PAGE 5 4 INSTRUMENT PANEL SELF TEST PAGE iternm nere err ete 5 5 MAIN LIGHTING PAGE tette temm mee teer 5 5 MAIN LIGHTING PAGE DISPLAY LIGHTING FROM LIGHTING BUS 5 6 DATE TIME SETUP PAGE MAIN DISCRETE I O PAGE MAIN CDI OBS CONFIG PAGE C
57. CPS ARINC 429 IN 1 GPS ARINC 429 IN 1 B 49 lt H 5 14 G8 27 G OR L 2 H GPS ARINC 429 IN 1 ALREADY USED FOR ANOTHER RT P5001 50 AND 51 MAY BE CONNECTED IN IE GPS ARINC 429 IN 2 EAD SIGNATORS ARE SHOWN AS ETTERS 3 LOWER CASE PIN DE UNDERLINED O MANUFACTURERS DOCUMENTATION FOR R COMPLETE PINOUT AND INTERCONNECT INFORMATI OF OTHER UNITS S N FOR REFERENCE ONLY Figure 4 15 ARINC 429 Air Data IRU AHRS Interconnect 500 SERIES INSTALLATION MANUAL Page 4 49 Page 4 50 blank P N 190 00181 02 Rev G 4 11 15 ARINC 429 Flight Control Interconnect Un GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 GPS ARINC 429 IN 1 GPS ARINC 429 OUT A GPS ARINC 429 OUT B GPS ARINC 429 IN 1 GPS ARINC 429 IN 1 P5001 46 47 48 49 48 49 Bendix King KFC 400 NAV SYSTEM 1 SEE NOTE 2 SEE NOTE 2 NAV SYSTEM 2 NOTES 1 2 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED IF THE GPS ARINC 429 IN 1 PORT P5001 48 AND 49 IS ALREADY USED FOR ANOTHER PURPOSE THE GPS ARINC 429 IN 2 PORT P5001 50 AND 51 MAY BE CONNECTED INSTEAD LOWER CASE PIN DESIGNATORS ARE SH UNDERLINED UPPER CASE LETTERS WN AS REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY KCP 420 P420
58. Compliance TSO C129a Class A 1 RTCA DO 208 Acquisition Time a Search the Sky without almanac without initial position or time 5 minutes AutoLocate with almanac without initial position or time 5 minutes Cold Start position known to 300 nm time known to 10 minutes with valid almanac 45 seconds Warm Start position known to 10 nm time known to 10 minutes with valid almanac and ephemeris 15 seconds Max Velocity 1000 kts Page 1 2 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 1 3 4 COM Transceiver Specifications GNS 530 Only Regulatory Compliance TSO C37d Class 4 amp 6 3 amp 5 for A models TSO C38d Class C E JTSO 2C37e JTSO 2C38e RTCA DO 186a ICAO Annex 10 Volume III Part Il Voice Communications Systems Par 2 3 3 Audio Output 100 mW minimum into 500 load Audio Response Less than 6 dB of Variation between 350 and 2500 Hz Audio Distortion The distortion in the receiver audio output shall not exceed 15 at all levels up to 100 mW AGC Characteristics The audio output shall not vary by more than 6 dB when the level of the RF input signal modulated 30 at 1000 Hz is varied from 5 uV to 450 000 Sensitivity S N N on all channels shall be greater than 6 dB when the RF level is 2 uV hard modulated 30 at 1000 Hz at rated audio O O cc NN 6 dB for 8 33 kHz channels Selectivity 6 dB BW is greater than 8 kHz for 25 kHz channeling 60 dB
59. ED S 11 AIRCRAFT POWER ln 12 AIRCRAFTPONER in 18 RESERVED S 14 TRANSMIT INTERLOCK 0 15 COMREMOTETRANSFER 16 SPARE 17 INTERCOMMICLO ln 20 RESERVED 21 AIRCRAFTGROUND 22 AIRCRAFTGROUND 23 RESERVED 24 RESERVED 25 RESERVED 1 5 500 SERIES INSTALLATION MANUAL Page 4 3 P N 190 00181 02 Rev 4 1 4 P5006 GNS 530 Only View of J5006 connector from back of unit 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 000000000 0 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 e 44 43 42 41 40 39 38 37 36 35 34 33 32 31 Pin PinName 14 RESERVED VOROBSROTORH GROUND Ou VOR OBS STATOR E G VOR LOC COMMON 1 in Out s 8 9 13 VOROBSSTATORD 19 SERIALDMEDATA 1 0 Ou 20 SERDME CHANREQ PARDME 4MHZ 21 SERDME RNAVMODE PARDME 2MHZ 22 DMECOMMON din 23 VOP ILS ARINC 4290UTB 28 VLOCREMOTETRANSFER in 34 RESERVED 35 85 91 o ln 36 VORILSARINC 429INA 0 0 ln 41 AIRCRAFTGROUND 44 AIRCRAFTPOWER ti Out In Out Out Out ut ut Page 4 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 4 2 POWER LIGHTING AND ANTENNAS 4 21 Power Lighting and Antennas Function The section covers the
60. EL TYPE The aircraft is using Aviation gas 5 8 Ibs gal Jet A The aircraft is using Jet A or Jet A 1 fuel 6 7 Ibs gal Jet B The aircraft is using Jet B JP 4 fuel 6 5 Ibs gal 5 2 3 MAIN INPUTS Page Select the MAIN INPUTS Page see Figure 5 3 This 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 500 Series unit is dashed out OAT Outside Air Temperature SAT Static Air Temperature TAT Total Air Temperature IAS Indicated Airspeed TAS True Airspeed W SPD Wind Speed T HDG True Heading W DIR GPS SC GPS Selected Course VLC SC VOR LOC Selected Course GNS 530 Only Figure 5 3 MAIN INPUTS Page Status of the CDI key GNS 530 Only Barometric corrected Altitude Density Altitude Pressure Altitude Left Engine Fuel Flow RFF Right Engine Fuel Flow T FF Total Fuel Flow T FOB Total Fuel on Board JOYSTICK Latitude and longitude of a WPT joystick waypoint sent by an EFIS or RADAR indicator Page 5 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 5 2 4 INSTRUMENT PANEL SELF TEST Page Select the INSTRUMENT PANEL SELF TEST Page see Figure 5 4 This page allows verification that the 500 Series unit is communicating properly with other instruments Compare on s
61. ENTENCE The Garmin 500 Series units shall be capable of receiving the following 13 byte message from the ARNAV or Electronics International Fuel Flow Indicators lt STX gt G0245100550 lt ETX gt Where lt STX gt start transmit character 0x02 hex G units designation 1 e Gallons Imperial gallons Liters Kilograms B pounds 0245 total fuel remaining in reverse order 1 ASCII coded decimal format 0x30 0x32 0x34 0x35 1 fuel remaining checksum modulo 10 sum of four total fuel remaining digits 0055 total fuel flow rate in reverse order 0 fuel flow checksum lt ETX gt end transmit character 0x03 NOTE Fuel remaining and fuel flow are 10 when units designation is gallons or imperial gallons For example 0245 gallons indicates 542 gallons 0245 liters indicates 5420 liters Checksum is the modulo 10 sum of the four fuel flow decimal digits converted to an ASCII numerical character e g checksum for 5678 would be ASCII 6 Page D 2 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 D 6 SHADIN FUEL AIRDATA COMPUTER SENTENCE The Garmin 500 Series units shall be capable of receiving the following message strings from the Shadin Fuel Airdata or Airdata Computer lt STX gt ZA012 lt CR gt lt LF gt ZB345 lt CR gt lt LF gt ZC678 lt CR gt lt LF gt ZD lt gt 9012 lt CR gt lt LF gt ZE lt gt 3456 lt CR gt lt LF gt ZF lt gt 78 lt CR gt lt LF gt ZG lt gt 90 lt
62. ES REQUIRED BUT NOT PROVIDED s 3 5 ANTENNAINSTALDLEATION eter e eme Dore em e er eene tpi Det 3S CABEEINSTALDDATION ehe tte ee mel ee ea eee D Pei 3 7 RACK i 3 8 500 SERIES UNIT INSERTION AND REMOVAL s 3 9 COM ANTENNA INSTALLATION CHECK GNS 530 3 10 56 ANTENNA INSTALLATION DRAWING eee een e enn enne nnne nennen enne 3 11 MOUNTING RACK 5 3 12 MOUNTING RACK INSTALLATION 3 13 RECOMMENDED PANEL CUTOUT DIMENSIONS nee ee ee eee eene eren 4 SYSTEM INTERCONNECTS A Ej dS FUNG TIONGLIS d E 4 1 4 2 POWER LIGHTING AND ANTENNAS g 4 5 43 ALTINELDER nne 4 4 MAIN INDICATOR i 4A SANNUNGIATORS S WITCHES ea Rescue p eben 4 6 SEREAT DAT Ait eie er eet NIE A ESO e sada senses tope aras o Cau ee 4 7 COM VOR ILS AUDIO GNS 530 ONLY 4 8 VOR ILS INDICATOR GNS 530 ONLY 4 9 2 S eei th rer eae 4 10 DME TUNING GNS 530 ONLY n nu eren ys 4 11 500 SERIES INTERCONNECTS ieser ertet P Ri P ne PEN eee 5 POST INSTALLATION CONFIGURATION amp CHECKOUT PROCEDURE 5 1 CONFIGURATION MODE 5 5 2 INSTALLATION CONFIGURATION PAGES 53 3 ADDITIONAL GROUND 5 e tte re enter deer ert peer rH 5 A
63. GPS NAV flag is out of view Select 121 150 MHz on the 500 Series COM transceiver Transmit for a period of 20 seconds Verify that the GPS NAV flag does not come into view Repeat steps 4 and 5 for the following frequencies 121 175 MHz 121 200 MHz e 131 250 MHz QVE pa ns 131 275 MHz 131 300 MHz 7 Repeat steps 3 through 6 for all COM transceivers installed in the aircraft 8 Ifthe GPS NAV flag comes into view refer to Section 2 2 7 for options to improve performance 500 SERIES INSTALLATION MANUAL Page 5 17 P N 190 00181 02 Rev 5 3 7 VHF COM Check GNS 530 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 ground station in close proximity Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical noise which would increase the squelch threshold If possible verify the communications capability on both the high and low ends of the VHF COM band It may be required by the governing regulatory agency to verify operation of the COM transmitter and receiver at the extents of a ground facility s service volume e g FAA AC 23 8A 5 3 8 VOR ILS Check GNS 530 Only Select a VOR channel within a 40 nautical mile range Liste
64. I OBI OBI OBI OBI CLOC DATA SYNC CLOC DATA SYNC K K Figure 4 21 RMI OBI Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 61 Page 4 62 blank Rev 4 11 21 King Serial Panel DME Tuning Interconnect E DATA SER DME CHAN REQ PAR DN MODE PAR DM CLOC RIA COMMON N RNAV MODE PAR 22 22 NAV ndix King KN 62 62A 14 14 CLOCK QU CHANN LARGER 25 GNS 530 BE CONFIGURED NSTA KING S TUNING DATA FOR O S INTERFACE 3 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION FOR REFERENCE ONLY S OF OTHER UNITS S Figure 4 22 King Serial Panel DME Tuning Interconnect 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 63 Page 4 64 blank Rev 4 11 22 King Serial Remote DME Tuning Interconnect SERIAL DME DATA SERIAL DME CLOCK SER DME CHAN REQ PAR 4 7 DME COMMON SER DME RNAV MODE PAR DME 2MHZ SERIAL DME DATA SERIAL DME CLOCK SER DME CHAN REQ PAR DME 4MHZ DME COMMON SER DME RNAV MODE PAR 2 DATA BUS CLOCK BUS RNAV REQUEST 10 BIT 50 BIT SELECT NAV 1 COMMON NAV 2 COMMON DME REQUEST Bendix King
65. LOC Antenna GNS 530 Only Shall meet TSO C40 and C36 Broad band 50 Q horizontally polarized with coaxial cable Glideslope Antenna GNS 530 Only Shall meet TSO C34 Broad band 50 Q horizontally polarized with coaxial cable or low loss splitter used with the VOR LOC antenna Headphones GNS 530 Only 500 Q nominal impedance Microphone GNS 530 Only Low impedance carbon or dynamic with transistorized pre amp 3 5 ANTENNA INSTALLATION For the COM VOR LOC and Glideslope antennas follow the manufacturers instructions The remainder of this section applies to the GPS antenna The GA 56 antenna outline and footprint dimensions are shown in Figure 3 2 page 3 7 1 Using the backing plate as a template mark the location of the mounting holes and the through hole for coaxial cable Drill or punch the holes 2 The antenna installation must provide adequate support for the antenna considering a maximum drag load of 5 lbs For the GA 56 antennas at subsonic speed Install a doubler plate to reinforce thin skinned aircraft Observe guidelines for acceptable installation practices as outlined in AC 43 13 2A 3 Sealthe antenna and gasket to the fuselage using a good quality electrical grade sealant Use caution to insure that the antenna connector is not contaminated with sealant Insure that the mounting screws are fully tightened and that the antenna base is well seated against the gasket CAUTION Do not use constructi
66. LOPE OFFSET fields described above with the exception that they only control the display lighting characteristics when the lighting bus control is below the level specified in the PHOTO TRANS field Both fields have a range of 0 zero to 99 and are set to 50 at the factory 5 2 6 DATE TIME SETUP Page Select the DATE TIME SETUP Page see Figure 5 7 Very infrequently it may be desirable to set the date and time of the 500 Series unit to aid in acquiring a GPS position Configuration mode is the only means by which the date and time for the 500 Series unit may be adjusted Note that the time must be UTC time and that the UTC date may be different from the date in the local time zone HAIN LIGHTING Figure 5 6 MAIN LIGHTING Page Display Lighting from Lighting Bus DATE SETUP Caution Changing to the wrong UTC date time will delay satellite acquisition Figure 5 7 DATE TIME SETUP Page Page 5 6 Rev 500 SERIES INSTALLATION MANUAL P N 190 00181 02 5 2 7 MAIN DISCRETE I O Page Select the MAIN DISCRETE I O Page see Figure 5 8 HAIN DISCRETE I 0 GRAY CODE If the encoding altimeter input is used verify that the DECODED ALTITUDE field indicates the correct EXTERNAL SHITCH STATE altitude EXTERNAL SWITCH STATE This allows you to verify the operation of any external switches that are present in the installation Figure 5 8 MAIN DISCRETE I O Page Verify That RMT CDI The box is f
67. M DEFECTS IN THE PRODUCT Some states do not allow the exclusion of incidental or consequential damages so the above limitations may not apply to you Garmin retains the exclusive right to repair or replace the unit or software or offer a full refund of the purchase price at its sole discretion SUCH REMEDY SHALL BE YOUR SOLE AND EXCLUSIVE REMEDY FOR ANY BREACH OF WARRANTY To obtain warranty service contact your local Garmin Authorized Service Center For assistance in locating a Service Center near you call Garmin Customer Service at one of the numbers shown below Products sold through online auctions are not eligible for rebates or other special offers from Garmin Online auction confirmations are not accepted for warranty verification To obtain warranty service an original or copy of the sales receipt from the original retailer is required Garmin will not replace missing components from any package purchased through an online auction Garmin International Inc Garmin Europe Ltd 1200 East 151 Street Unit 4 The Quadrangle Abbey Park Industrial Estate Olathe Kansas 66062 U S A Romsey SO51 9DL U K Phone 913 397 8200 Phone 44 1794 519944 FAX 913 397 0836 FAX 44 1794 519222 Page 1 8 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 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
68. N GNC 500 Series Notice 8110 60 Data Submittal Reference 1 GARMIN letter dated August 27 2002 2 FAA Notice 8110 60 GPS as a Primary Means of Navigation for Oceanic Remote Operations 3 FAA Information Memorandum GPS as a Primary Means of Navigation dated 2 11 97 Dear Mr Billings This is in reply to your letter of August 27 2002 requesting a separate letter of design approval for your upgrade to the GNC 500 series of products to comply with FAA Notice 8110 60 We concur that GARMIN International has met the requirements of Notice 8110 60 in accordance with the additional guidance provided in the FAA Information Memorandum GPS as a Primary Means of Navigation dated 2 11 97 and as agreed upon in GNC 400 500 Plan for Software Aspects of Certification for FDE GPN 005 00077 63 Revision A GARMIN has previously received TSO C129a Airborne Supplemental Navigation Equipment Using the Global Positioning System GPS Class Al TSO Authorization for the GNC 500 series products through our office The GNC 500 series software has been developed in accordance with DO 178B for Level C software as documented in GNC 500 Software Accomplishment Summary GPN 005 00096 15 Revision R The FDE Prediction Program software has been developed in accordance with DO 178B for Level D software as documented in FDE Prediction Program Software Accomplishment Summary GPN 005 00162 04 Revision A A list of the technical data required by TSO C129a
69. NC 429 IN 1 A GPS ARINC 429 IN 1 GPS ARINC 429 OUT GPS ARINC 429 OUT a gt ILS CPS APPROACH MAIN LEFT MAIN RIGHT MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG P5006 24 23 P5001 48 49 46 47 14 21 22 23 24 27 28 29 30 P5006 24 23 P5001 48 49 46 47 14 21 22 25 24 27 28 30 VoR ILS 1 RELAXED N C ENERGIZED VOR ILS 2 28 VDC i FCS SWITCH 1 VOR ILS 1 ot RELAXED i COPILOT NO HL v ENERGIZED VOR ILS 2 28 VDC NAV SYSTEM 1 RELAXED Scncel NOTE 27 NOTE NOI SN3508 2 2 Scncel P3 NO 27 29 10 28 26 NOTE NOTE SN3308 ARINC 429 EHSI Display 1 NAV 1 2 RELAY SENSE 428 2 RX A 429 2 RX 8 VHF NAV 2 SWITCHING RELAY GPS 2 SWITCHING RELAY 429 1 TX A 429 1 TX B 428 1 RX A 429 1 RX B 429 3 RX A 429 3 RX B CDI SOURCE CONTROL RCVR 1 2 ARINC 429 EHSI Display 2 NAV 1 2 RELAY SENSE 429 2 RX A 429 2 RX B VHF NAV 2 SWITCHING RELAY GPS 2 SWITCHING RELAY 429 1 IX A 429 1 1 429 1 RX A 429 1 RX B 429 3 RX A 429 3 RX B
70. NTERFACE Function Bendix King Garmin PS Engineering Audio Panel GMA 340 PMA 6000 E 2 GARMIN 500 530 LRU INTERFACE Function Bendix King Air Data Computer 2600 2601 2800 90004 003 Function Shadin Icarus JP Shadin Miniflo L Instruments Instrument Altitude Serializer or EDM 700 91204XT 38 D Fuel Air Data Digiflo L Digidata International Altitude Serializer or 91053XP 91802 F ADC 200 FP 5L Fuel Air Data 91053XT D F ADC 2000 Function Bendix King Autopilot System 55 Flight Control Function Bendix King Shadin Encoding Altimeter KEA 130A AT 3000 Miniflo L Or Blind Encoder KEA 346 Digiflo L Digidata 500 SERIES INSTALLATION MANUAL Page E 1 P N 190 0018 1 02 RevG Function Bendix King EFIS EFIS 40 50 EFIS 84 Displays SG 465 DPU 84 Function Sandel EHSI SN 3308 IRU AHRS Laseref LTN 90 100 HG 1075 AB LTN 91 HG 1095 AB LTN 92 Nay KI202A GII02 A NSD 360A 331A 6P RD 5504 Indicator 203 GI106 A NSD1000 331A 6G RD 650 KI204 KI206 KI 208 A KI209 A KI 525A KPI 522 B KPI 553 A B Function Bendix King BF Goodrich Weather Traffic KTA 870 SKY497 Skywatch 9900B BX and Terrain KMH 880 SKY899 Skywatch HP WX 500 Page E 2 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02
71. OM SETUP PAGE GNS 530 ONLY VOR DISCRETE INPUTS PAGE GNS 530 ONLY VOR LOC GS CDI PAGE GNS 530 VOR LOC GS ARINC 429 CONFIG PAGE GNS 530 5 12 STORMSCOPE CONFIG PAGE teet ertt tette eine thee rem e ene e ehe 5 13 STORMSCGOPE TEST PAGE eoar orisi seee reete nitent e teer 5 13 STORMSCOPE DOWNLOAD DATA PAGE esee eee e eene ene nennen nnn 5 14 TRAFFIC PAGE SKYWATGCH rte eintritt eret ea dieere rotto as 5 14 TRAFFIC eret rte eter oen 5 14 RYAN TOAD CONFIG PAGE S beet e eR RERO 5 15 1 ooa teh Ee ANT EIER REA THES 5 15 DATA LINK PAGE erre REED SO E EORR NERO a ER 5 15 Note Throughout this document references made to GNS 530 shall equally apply to the GNS 530A except where specifically noted 500 SERIES INSTALLATION MANUAL Page iii P N 190 00181 02 Rev 500 SERIES HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification Mod Levels for the GPS 500 and GNS 530 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 Authorize
72. ONTROL DISPLAY UNIT A PLACARD 5 REQUIRED NEAR THE 400 SERIES UNIT INDICATING THAT A TRAFFIC ADVISORY SYSTEM IS INSTALLED AND ITS DATA MAY BE DISPLAYED ON THE 10 500 SERIES UNIT IN ORDER FOR SKYWATCH DATA THIS DRAWING IDENTIFIES SPECIFIC RS 232 PORTS 500 SERIES UNT S MAP PAGE THE 500 SERIES UNIT MUST HAVE A DICITAL HEADING SOURCE TO BE DISPLAYED ON THE 500 SERIES UNIT S MAP PAGE THE 500 SERIES UNIT MUST A DIGITAL HEADING SOURCE OR THE SKYWATCH MUST HAVE A SYNCHRO OR SERIAL HEADING SOURCE A STEPPER HEADING SOURCE WILL NOT ALLOW SKYWATCH DATA TO DISPLAYED ON THE MAP PAGE HAVE CONFIGURATION OF 500 SERIES UNITS WITH MAIN SOFTWARE VERSION 2 04 OR EARLIER REQUIRES THESE SPECIFIC PORTS MAIN SOFTWARF VERSION 2 05 OR LATER DOES NOT HAVE THIS LIMITATION SUCH THAT ANY SERIAL FORMAT CAN BE SELECTED ON ANY OF THE FOUR RS 232 PORTS REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY REFER TO THE SKY 899 INSTALLATION MANUAL 4 11 17 Weather and Terrain Interconnect NOTES 1 2 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED IN ORDER FOR 500 DATA TO BE DISPLAYED ON THE 500 SERIES UNIT S MAP PAGE THE 500 SERIES UNIT MUST HAVE A GPS RS 232 OUT 4 GPS RS 232 IN 4 DIGITAL HEADING SOURCE OR THE WX 500 MUST HAVE A SYNCHRO OR SERIAL HEADING SOURCE A STEPPER HEADING SOURCE WILL NOT ALLOW WX
73. OR Course Deviation Flag must be flagged a inthe absence of an RF signal b inthe absence of the 9960 Hz modulation c inthe absence of either one of the two 30 Hz modulations d When the level of a standard VOR deviation test signal produces less than a 50 of standard deflection AGC Characteristics From 99 dBm to 13 dBm input of a Standard VOR Audio Test Signal audio output levels shall not vary more than 3 dB Spurious Response Greater than 80 dB VOR OBS Bearing Accuracy The bearing information as presented to the pilot shall not have an error in excess of 2 7 as specified by RTCA DO 196 and EuroCAE ED 22B Audio Output A minimum 100 mW into a 500 Q load Audio Response Less than 6 dB of variation between 350 and 2500 Hz Except the 1020 Hz Ident Tone is at least 20 dB down in voice mode The distortion in the receiver audio output shall not exceed 10 at all levels up to 100 mW Page 1 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 1 3 6 LOC Specifications GNS 530 Only Regulatory Compliance TSO 0966 JTSO C36e RTCA DO 195 Class A EuroCAE ED 46B Annex 10 Volume Radio Navigation Aids Par 3 1 4 Course Deviation Sensitivity 103 5 dBm or less for 60 of standard deflection The LOC Course Deviation Flag must be flagged a inthe absence of an RF signal b When either the 90 or 150 Hz modulating signals is removed and the other is maintained at its normal 20 C In the absence o
74. OR SERIALIZER gt GPS RS 232 IN 1 Ss x GPS ARINC 429 IN 1 20 GPS ARINC 429 OUT zit EXTERNAL FLIGHT CONTROL MAP DISPLAY SYSTEM ILS GPS APPROACH CARMIN 530 CONNECTOR P5002 ureJBeiq 8 uu9 s S seues 006 L p 93ed 93ed D AY INTERCOM lt MICROPHONE AIRCRAFT POWER gt t POWER amp GROUND w ANSCEIVE AUDIO PANEL COM TRANSCEIVER 1 COM vic KEY com AUDIO X AUDIO COM REMOTE TRANSFER REMOTE COM TRANSFER SWITCH CARMIN 530 CONNECTOR P5006 CDI HSI Z vor iLs AUDIO LAT DEVIATION amp FLAGS VOR ILS ONLY TO FROM 2 VERT DEVIATION amp FLAGS SUPERFLAGS 7 _ 2 VOR OBS lt gt AIRCRAFT POWER power amp GROUND voR Loc 1 ILS ENERGIZE RMI vor oai SERIAL DME CLOCK DATA 2 gt KING SERIAL DME REQUEST COMMON 2 lt TUNED DME ARINC 429 EFIS EHSI gt 2 VOR ILS ARINC 429 IN 3 von ILS ARINC 429 OUT PARALLEL DME TUNING S DME COMMON VLOC REMOTE TRANSFER lt REMOTE VLOC TRANSFER SWITCH N GPS ANTENNA GARMIN 500 530 CONNECTOR P5003 X ANTENNA GARM 550 CONNECTOR P5004 VOR LOCALIZER ANTENNA CARM 530 CONNECTOR P5005 GLIDESLOPE ANTENNA GARMIN 530 CONNECTOR
75. P5007 0 18100 061 N d NOLLV TTIV LSNI SHISSS 005 D AY pz y 93ed 9301 uonel eisu 80141 v OES SND e v anbi GNS 530 LEFT MAIN RIGHT MANN TO MAIN FROM MAIN LATERAL FLAG MAIN LATERAL FLAG UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG MAIN 085 ROTOR MAIN OBS ROTOR C MAIN OBS STATOR D MAIN OBS STATOR E MAIN OBS STATOR F MAIN OBS STATOR G AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT GROUND AIRCRAFT GROUND LIGHTING BUS HI LIGHTING BUS LO GPS RS 232 IN 1 ALTITUDE COMMON GPS ANTENNA COM ANTENNA VOR LOC ANTENNA GLIDESLOPE ANTENNA AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT GROUND AIRCRAFT GROUND 500 OHM COM AUDIO d 500 OHM COM AUDIO LO COM MIC AUDIO H COM MIC KEY COM MIC AUDIO LO 500 CHM VOR ILS AUDIO dl 500 OHV VOR ILS AUDIO LO AIRCRAFT GROUND P5006 P5001 29 30 32 31 GNS 530 CIRCUIT BREAKER 19 lt PUE 77 78 38 40 57 14 28 VDC AIRCRAFT POWER LIGHTING BUS HI LIGHTING BUS LO 60 P5003 P5004 j ANTENNA P5005 ANTENNA P5007 c QH 0 5 ANTENNA COM TX CIRCUIT ED BREAKER 18 AWG XI 5A 28V 10A 14V 418 AWG 11 12 Q GPS L ANTENNA P3271 oonu 11 13 Navigation Indicator
76. R ILS AUDIO HI P5006 5000 VOR ILS AUDIO LO P5006 500Q COM AUDIO and 5000 VOR ILS AUDIO each supply 100 mW into a 500 Q load These are balanced outputs and the LO output must be connected 5000 COM AUDIO is the summation of the COM receiver audio COM sidetone audio and INTERCOM MIC audio 4 7 2 4 DISCRETE INPUTS PinName Connector Pin VO TRANSMIT INTERLOCK P5002 COM REMOTE TRANSFER P5002 VLOC REMOTE TRANSFER P5006 These inputs are considered active if either the voltage to ground is 1 9 V or the resistance to ground is 375 These inputs are considered inactive if the voltage to ground is 11 33 COM REMOTE TRANSFER and VLOC REMOTE TRANSFER are momentary inputs 4 7 3 5 Audio Configuration None 47 4 COM VORIILS Audio Calibration and Checkout Refer to section 5 2 9 for the COM calibration 47 5 COM VOR ILS Audio Interconnect Refer to Figure 4 19 on page 4 57 for the audio panel interconnect 500 SERIES INSTALLATION MANUAL Page 4 15 P N 190 00181 02 Rev 4 8 VOR ILS INDICATOR GNS 530 ONLY 4 8 1 VOR ILS Indicator Function NOTE Because the GNS 530 includes a CDI button that performs switching between GPS and VOR ILS on a remote indicator it 1s 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 The VOR ILS
77. S pA gt 1 0 985 N 4 580 i A 502 BEZEL i 1 841 46 76 1 2 4 60 96 1 841 0 437 8 000 46 76 NOTES 11 10 203 20 1 DIMENSIONS INCH mm 2 GPS 500 UNIT ONLY WEIGHT 5 7 LBS 2 6 KGS INSTALLED WITH RACK AND CONNECTORS WEIGHT 7 2 LBS 3 3 KGS VIDEO CARD CONNECTOR KIT WEIGHT 011 00558 00 0 11 LBS 0 05 KGS 4 CG LOCATION INCLUDES RADIO ONLY 0 985 25 02 i 0 382 9 70 TO 025 DIMPLES Figure 3 4 GPS 500 Mounting Rack Dimensions 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 3 11 Page 3 12 blank Rev 3 12 Mounting Rack Installation 00 BACK PLATE CONNECTOR KIT 30 00220 50 Figure 3 5 GNS 530 Mounting Rack Installation 500 SERIES INSTALLATION MANUAL Page 3 13 Page 3 14 blank P N 190 00181 02 RevG REAR VIEW OF CONNECTOR PLATE Figure 3 6 GPS 500 Mounting Rack Installation 500 SERIES INSTALLATION MANUAL Page 3 15 Page 3 16 blank P N 190 00181 02 RevG 3 13 Recommended Panel Cutout Dimensions Figure 3 7 500 Series Recommended Panel Cutout Dimensions 500 SERIES INSTALLATION MANUAL Page 3 17 Page 3 18 blank P N 190 00181 02 Rev 4 SYSTEM INTERCONNECTS 4 1 FUNCTION LIST P5001 View of J5001 connector from back of unit ee 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78
78. STATOR F 45 14 LNAV OBS COS OUT MAIN OBS STATOR G 36 lt SEE NOTE 3 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION 2 PROPER CONNECTION OF THE RELAY ENGAGE INPUT OF PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY THE KI 208A IS DEPENDENT ON ITS POWER SUPPLY VOLTAGE REFER TO KI 208A DOCUMENTATION FOR PROPER CONNECTION 3 TO CONNECT THE 500 SERIES UNIT TO A KI 208A INDICATOR ADD TWO 10 KOHM 1 4 WATT RESISTORS ONE BETWEEN P5001 PINS 33 AND 34 AND ONE BETWEEN P5001 PINS 35 AND 36 Figure 4 8 KI 208A Main Indicator Interconnect Page 4 35 Page 4 36 blank RevG 500 SERIES INSTALLATION MANUAL P N 190 00181 02 4 11 8 Annunciators Switches Interconnect 2009 2059 5001 MESSAGE ANNUNCIATE 6 MSC WPT WAYPOINT ANNUNCIATE 3 gt Annunciator CDI SOURCE SELECT 73 lt VLOC GPS VLOC ANNUNCIATE 1 gt Switch SEE NOTES 3 AND 6 GPS ANNUNCIATE 2 Annuncictor OBS MODE SELECT AUTO GPS SFQ RELAXED ate Switch SEE NOTE 7 Anaunciator SEE NOTE 2 ENERGIZED 085 CBS ANNUNCIATE 7 428 VOC TERMINAL ANNUNCIATE 4 GPS APR APPROACH ANNUNCIATE 5 nnunelater 5 Bendix King Bendix King i 9 INTEGRITY ANNUNCIATE 9 System 55 KFC 150 KFC 200 J Computer KC 192 KC 295 P1 P1921 P2951 ILS GPS APPROACH 32 B AA LOCALIZER ENGAGE TIME
79. Series with Main SW 3 0 or later FAA approved SW meets the requirements for GPS primary means of navigation in oceanic and remote airspace when used in conjunction with the 400 Series Trainer Program incorporating the FDE Prediction Program FAA design approval does not constitute an operational approval Refer to N8110 60 when seeking operational approval for GPS as the primary means of navigation 500 SERIES INSTALLATION MANUAL Page B 1 P N 190 00181 02 Rev United States of America Department of Transportation Federal Asiation Administration Supplemental Type Certificate New SA00864 WI The do GARMIN International 1200 E 51st 51 Olathe KS 66062 ws net mal hereon meets the airworthiness regusrenmants of Tert 3 ey he Civil Air Pepelations Make Piper Model PA 32 of Posign Change Installation of GNS 530 or GPS 500 in accordance with 1 Installation Data referenced on Sheet 2 and 2 FAA Approved Airplane Flight Manual Supplement AFMS referenced on Sheet 2 imitations and Conditions Compatibility of this design change with previously approved modifications must be determined by the installer If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission surrendered Mammalia revoked or a termination date i otherwise established by the Administrator of the Fedra
80. VERTICAL FLAG 29 MAIN VERTICAL FLAG 30 Iw GPS CIRCUIT BREAKER d AIRCRAFT POWER 189 9 9 54 14 28 VDC AIRCRAFT POWER AIRCRAFT POWER 20 AIRCRAFT GROUND 77 AIRCRAFT GROUND 78 LIGHTING BUS 39 H LIGHTING BUS LIGHTING BUS LO 40 p LIGHTING BUS LO RS 232 1 57 Navigation Indicator LEFT SEE NOTE 3 RIGHT TO FROM NAV FLAG NAV FLAG UP DOWN GLIDESLOPE FLAG GLIDESLOPE FLAG ALTITUDE COMMON 60 P5003 GPS ANTENNA RS 232 OUT 1 ALTITUDE D4 ALTITUDE A1 ALTITUDE A2 ALTITUDE A4 ALTITUDE B1 ALTITUDE B2 ALTITUDE B4 ALTITUDE C1 ALTITUDE C2 ALTITUDE C4 POWER GROUND jeoid 009 Sd9 enBi4 9z p 93ed cc p oSeq D AY 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 THE GPS VERTICAL DEVIATION OUTPUTS WERE NOT OPERATIONAL AT TIME OF PUBLICATION CONNECTION OF VERTICAL DEVIATION AND FLAGS IS PROVISIONAL FOR FUTURE GPS PRECISION APPROACH OPERATIONS 5 IF OBS CONNECTIONS ARE NOT MADE TO THE GPS 500 THEN ALL OBS COURSE SELECTIONS WILL NEED TO BE MADE USING THE GPS 500 KNOBS IF AN OBS INTERFACE S DESIRED REFER TO THE APPROPRIATE MAIN INDICATOR INTERCONNECT DRAWING Altimeter or Blind Encoder D4 A1 A2 A4 B1 B2 B4 1 c2 C4 COMMON 4 11 3 Power Lighting and Antennas Interconnect AIRCRAFT POWER 1 AIRCRAFT POWER 1
81. as possible from all COM antennas and all COM transceivers including the 500 Series COM The GPS antenna i much less sensitive to COM antennas that use a 1 57542 GHz notch filter e Locate the 500 Series unit as far as possible from all COM antennas Anrenna masked by vertical T fait or dorsal fin ni Antenna must be on of Figure 2 1 GPS Antenna Installation Considerations If a COM antenna is found to be the problem a 1 57542 GHz notch filter Garmin P N 330 00067 00 may be installed in the VHF COM coax as close to the COM as possible This filter is not required for the GNS 530 transmitter If a COM is found to be radiating the following can be done Replace or clean VHF COM rack connector to ensure good coax ground 2 Place a grounding brace between the 500 Series unit VHF COM and ground 3 Shield the VHF COM wiring harness 2 2 8 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 Page 2 2 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 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 Installation of remote switches and annunciators may not be required 1f
82. ation and flags must be checked with Glideslope Verify that the flags are hidden at the correct times and that the flag is in view at the correct times 5 3 4 2 EHSI Deviation Scaling Only if HSI CDI is driven by the 500 Series unit via serial data With the 500 Series unit locked onto a GPS fix activate an OBS waypoint about 20 nautical miles from the present position 1 With 5 0 nautical mile CDI sensitivity adjust the OBS course for approximately half scale deflection on the 500 Series unit s Default Navigation page Verify that the EHSI displays a similar half scale deviation 2 Repeat step 1 with 1 0 nautical mile CDI sensitivity The CDI sensitivity may be manually set on the AUX SETUP page using the CDI ALARMS menu item 3 Repeat step 1 with 0 3 nautical mile CDI sensitivity 5 3 5 Crossfill Check Only if dual units installed with RS 232 crossfill connected Turn on both 400 500 Series units in the aircraft For each 400 500 Series unit 1 Select the first AUX page titled FLIGHT PLANNING 2 Select CROSSFILL 3 Verify that the displayed status is Ready If Not Available is displayed there may be an RS 232 wiring problem between the two 400 500 Series units 5 3 6 VHF COM Interference Check GNS 530 Only Once the Signal Acquisition Test has been completed successfully perform the following steps View the Satellite Status Page and verify that 7 to 8 satellites have been acquired Verify that the
83. ave a Type 2 sentence output by the 500 Series unit approximately once every second If no route is being navigated by the 500 Series unit 1 the active route is empty the following Type 2 sentence is output approximately once every second id item designator 3 ASCII characters route sequence number is 01 seq sequence number 1 binary byte last waypoint flag is set route sequence number is 1 CR ASCII carriage return character OD hex LF ASCII line feed character 0A hex 500 SERIES INSTALLATION MANUAL Page C 3 P N 190 00181 02 RevG The following table describes the Type 2 output sentence item designator 1d sequence number seq waypoint identifier wpt waypoint latitude lat waypoint longitude lon and magnetic variation at waypoint mvar fields ASCII character w 77 hex Two ASCII numeric characters representing route sequence number of waypoint 01 to 31 X undefined 1 if last waypoint in route a 1 if active to waypoint nnnnn route sequence number of waypoint unsigned binary Destination waypoint identifier will be blank filled on right if less than 5 characters in identifier S 0 north or 1 south ddddddd latitude degrees unsigned binary undefined mmmmmm latitude minutes unsigned binary X undefined hhhhhhh hundredths of latitude minutes unsigned binary S 0 north or 1 south XXXXXXX undefined dddddddd longitude degrees uns
84. ber 2 1998 For tha Mooney M20J dual GNS 430 installation reference STC SA00735WI dated January 19 1999 Also see the attached Wichita ACO letter affirming approval of the GNS 430 system without external switching or annunciation and guidance to consider when installing GNS 430 systems to avoid external switching annunciatian Sincerely Cede Bill Stone Avionics Product Manager 500 SERIES INSTALLATION MANUAL Page B 3 P N 190 0018 1 02 RevG Q U S Department Small Airplane Directorate of Transporiation Wichita Aircraft Certification Office Federal Aviation 180 Airport Road Room 100 Administration Wichita Kansas 67209 January 25 1999 Mr Phil Straub GARMIN International 1200 E 15151 St Olathe KS 66062 Subject GNS 430 Follow On Installation Approval Reference GARMIN Installation Memorandum dated January 25 1999 Dear Mr Straub We have reviewed your Installation Memorandum dated January 25 1999 and concur with the contents The GNS 430 integrated navigation communication system incorporates adequate internal switching alerting and annunciation features within its display such that most typical installations will not require external switching or annunciation Extensive evaluations were conducted during initial certification of the GNS 430 to verify the suitability of the switching alerting and annunciation features of the system External annunciation of GPS receiver mode CDI source informat
85. but take care not to over tighten Three turns is the minimum for proper installation If fewer than three turns are possible the mounting rack should be moved aft such that the aircraft panel does not obstruct the unit from engaging in the rack 5 3 2 Verification of Self test Data Following normal power up the Data Base Page is displayed followed by the Instrument Panel Self Test Page Pressing the ENT key once then displays the Instrument Panel Self Test page refer to Figure 5 4 on page 5 5 During this time many of the electrical outputs are activated so the installation configuration and wiring may be verified Before approving the Instrument Panel Self test Page verify that the following parameters are displayed on equipment in the aircraft as listed below Electronic displays which monitor the 500 Series unit s ARINC 429 output may vary in how and where annunciations are displayed Generally it is not required to verify every data field with an ARINC 429 interface Correct display of a subset of the data without noting any discrepancies is typically adequate evidence of correct ARINC 429 operation Selected Course 500 Series unit displays the OBS value 149 5 if interfaced to an HSI with driven course pointer Present Position N 39 04 05 W 94 53 86 Waypoint Alert Active Phase of Flight En Route Message Alert Active Leg OBS Mode Leg Mode GPS Integrity Reflects actual GPS integrity Roll Steering if applicab
86. creen indications with the information depicted on connected instruments such as the CDI HSI RMI and or external annunciators It also Set Full Fuel displays fuel capacity amount on board and flow Figure 5 4 INSTRUMENT PANEL SELF TEST Page 5 2 5 LIGHTING Page HAIN LIGHTING Select the MAIN LIGHTING Page see Figure 5 5 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 This field has a range of 0 zero to 9999 Figure 5 5 MAIN LIGHTING PAGE SOURCE PHOTO Backlight level is determined by the ambient light level as measured by the photocell on the 500 Series unit If a lighting bus any selection other than PHOTO is selected and the lighting bus control is turned to its minimum daytime setting the display brightness tracks the 500 Series unit s photocell using additional parameters PHOTO TRANS and PHOTO SLP OFFST described below RESP TIME Response Time Sets the speed with which the brightness responds to the input level bus voltage or ambient light changes The higher the number the slower the display responds This field has a
87. ctions engines and propellers It should have a clear line of sight 1f possible The antenna must be mounted along the centerline of the aircraft minimizing the lateral offset 2 94 GLIDESLOPE ANTENNA LOCATION The GNS 530 Glideslope antenna should be well removed from all projections engines and propellers It should have a clear line of sight 1f possible 2 25 ELECTRICAL BONDING No special precautions need to be taken to provide a bonding path between the GPS antenna and the aircraft structure Follow the manufacturers instructions for the COM VOR LOC and Glideslope antennas 500 SERIES INSTALLATION MANUAL Page 2 1 P N 190 00181 02 Rev 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 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 500 Series COM does not interfere with its own GPS section However placement of the GA 56 GPS antenna relative to a COM transceiver and COM antenna including the GNS 530 COM antenna is critical Use the following guidelines in addition to others in this document when locating the 500 Series unit and its antennas e GPS Antenna Locate as far
88. d Garmin Sales and Service Centers are encouraged to access the most up to date bulletin and advisory information on the Garmin Dealer Resource web site at www garmin com using their Garmin provided user name and password SERVICE SERVICE PURPOSE OF MODIFICATION BULLETIN BULLETIN NUMBER DATE 0019 11 7 00 Replace fuse in COM circuit with a resistor 0101 2 16 01 Remote COM transfer 0111 7 9 01 Improves VLOC Morse code ident 0203 Rev B 8 12 02 Improve receiver audio compressor performance 4 2 02 Remove excess solder from COM board 6 4 02 Reduce input transients from Audio Panel Page iv 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 1 GENERAL DESCRIPTION 1 1 INTRODUCTION This manual describes the physical mechanical and electrical characteristics and the installation requirements for the 500 Series GPS 500 and GNS 530 panel mounted units After installation of the 500 Series system FAA Form 337 must be completed by an appropriately certificated agency to return the aircraft to service Note Throughout this document references made to GNS 530 shall equally apply to the GNS 530A except where specifically noted 1 2 EQUIPMENT DESCRIPTION The 500 Series units are mark width 6 25 wide units and 4 60 high The display is a 320 by 234 pixel color LCD The units include two removable data cards one with a Jeppesen database and the second being an optional custom data card T
89. e of a different crimp tool positioner than shown in the table with the part numbers as follows Daniels P N K250 Astro P N 616245 or ITT Cannon P N 980 0005 722 4 For the card edge connector pin contacts use AMP part number 90272 1 or equivalent crimping tool To prevent a possible short across the pins in the wiring harness Teflon shrink tubing P N 312 00005 05 provided in Connector Kit 011 00351 00 P4002 covers the oversized power and ground pin contacts P N 336 00023 00 pins 11 12 21 22 that protrude from the back of the connector shell Before crimping the pins onto the wire Cutthe tubing 312 00005 05 into 4 equal lengths 2 Slide a short piece of the tubing over the wire 3 Strip the wire and crimp the pin 336 00023 00 onto the wire 4 Insert the pin into the connector shell 5 Slide the tubing over the exposed portion of the pin and shrink using a heat gun 3 7 RACK INSTALLATION 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 Figures 3 3 and 3 4 starting on page 3 9 shows outline dimensions for the aviation rack for the various 500 Series units Install the rack in a rectangular 6 320 x 4 600 hole or gap between units in the instrument panel refer to Figure 3 7 page 3 17 The lower front lip of the rack should be flush wi
90. e present in the installation Figure 5 11 VOR DISCRETE INPUTS Page Verify That REMOTE XFR The box is filled in while a remote VLOC transfer switch is pressed 5 2 11 VOR LOC GS CDI Page GNS 530 Only VOR LOC GS CDI Select the VOR LOC GS CDI Page see Figure 5 12 This page allows you to verify and calibrate the CDI outputs both lateral LAT and vertical VERT from the VOR LOC Glideslope receiver as well as the OBS resolver input to the VOR receiver It also allows you to select the format for DME tuning data Using the controls on the GNS 530 front panel make the selections below and verify the interfaces as appropriate Figure 5 12 VOR LOC GS CDI Page The LAT VERT and SELECTED COURSE configurations only apply to installations where a CDI HSI is connected to the VOR LOC GLIDESLOPE pins on connector P5006 CDI LAT VERT Verify That The LAT VERT flag is hidden The LAT VERT flag is in view S FLG LAT VERT Verify That The LAT VERT superflag is hidden The LAT VERT superflag is in view 500 SERIES INSTALLATION MANUAL Page 5 11 P N 190 00181 02 Rev TO FR Verify That FROM 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 500 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 calib
91. ew installation accessory kits kits 9 22 00 Add unit versions with 14 28 volt transmitter Update configuration pages D 4 12 01 Add GPS 500 data Update configuration pages 15595 5 22 02 Add gray unit and 16 watt A versions Update configuration 18221 pages 12 13 02 Add Fault Detection and Exclusion 19978 5 5 03 Correct 28 volt and 11 33 volt part numbers 21002 229 etian G 4 2 G 4 17 4 43 G 522 eese 5 17 G Page A 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 This manual is written for main software version 4 00 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 INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations EAR issued by the United States Department of Commerce 15 CFR Chapter VII Subchapter C and which may not be exported released or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license A violation of the EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to 1 000 000 under Section 2410 of the Export Administration Act of 1979 Include this notice w
92. f both 90 and 150 Hz modulation d When the level of a standard localizer deviation test signal produces less than a 50 of standard deflection AGC Characteristics From 86 dBm and 33 dBm input of a Standard VOR Audio Test Signal audio output levels shall not vary more than 3 dB Selectivity Nose Bandwidth The input signal level required to produce the reference AGC voltage shall not vary more than 6 dB over the input signal frequency range of 9 kHz from the assigned channel frequency Skirt Bandwidth The input signal level required to produce reference AGC voltage shall be at least 70 dB greater than the level required to produce reference AGC voltage at the assigned channel frequency at 36 kHz from the assigned channel frequency Spurious Response Greater than 80 dB Centering Accuracy Typical 0 mV Max error 9 9 mV per RTCA DO 195 Audio Output A minimum 100 mW into a 500 Q load Audio Response Less than 6 dB of Variation between 350 and 2500 Hz Except the 1020 Hz Ident Tone is at least 20 dB down in voice mode Audio Distortion The distortion in the receiver audio output shall not exceed 10 at all levels up to 100 mW 500 SERIES INSTALLATION MANUAL Page 1 5 P N 190 00181 02 Rev 1 3 7 Glideslope Specifications GNS 530 Only Regulatory Compliance TSO C34e JTSO C34e RTCA DO 192 EuroCAE ED 47B 87 dBm or less for 6096 of standard deflection Centering Accuracy 0 0091 ddm or 0 27 8 mV Select
93. h 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 To remove the unit from the rack insert the hex drive tool into the access hole on the unit face and rotate counterclockwise until the unit is forced out about 3 8 and can be freely pulled from the rack Be sure not to over tighten the unit into the rack The application of hex drive tool torque exceeding 15 inelbs can damage the locking mechanism 3 9 COM ANTENNA INSTALLATION CHECK GNS 530 Check for insertion loss and VSWR voltage standing wave ratio VSWR should be checked with an in line type VSWR wattmeter inserted in the coaxial transmission line between the transceiver and the antenna The VSWR should be inserted as close to the transceiver as possible When rack and harness buildup is performed in the shop the coax termination may be provisioned by using a 6 inline BNC connection This would be an acceptable place to insert the VSWR Any problem with the antenna installation is most likely seen as high reflected power A VSWR of 3 1 may result in up to a 50 loss in transmit power Page 3 6 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 3 10 GA 56 Antenna Installation Drawing H Figure 3 2 GA 56 Antenna Installation Drawing Page 3 7 Page 3 8 blank Rev
94. he applicable SAFMS refer to section 3 1 of this manual Garmin 500 Series unit Pilot s Guide P N part number of the applicable Pilot s Guide Distribution This document should be a permanent aircraft record 2 Description of the Alteration Installation of the Garmin 500 Series unit with interface to external altitude encoder and CDI include other equipment systems as appropriate Refer to section 4 of this manual for interconnect information Antenna installation removal and replacement should be in accordance with applicable provisions of AC43 13 1B and 43 13 2A 3 Control Operation Information Refer to the 500 Series unit Pilot s Guide 4 Servicing Information N A 5 Maintenance Instructions Maintenance of the 500 Series unit is on condition only Periodic maintenance is not required Refer to the 500 Series unit Maintenance Manual 500 SERIES INSTALLATION MANUAL Page A 1 P N 190 00181 02 Rev Troubleshooting Information Refer to the 500 Series unit 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 Data Relative to Structural Fasteners Antenna installation
95. he GPS 500 is a GPS receiver certifiable for IFR en route terminal and non precision approach operations The GNS 530 includes all the features of the GPS 500 and also includes IFR certified airborne VHF communications transceiver and an IFR certified airborne VOR Localizer and Glideslope receivers The A model is a 28 Vdc unit with a 16 Watt COM transmitter GPS signals are received by Garmin s low profile GA 56 antenna P N 010 10040 0X CAUTION The 500 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 an eyeglass lens cleaner which is specified as safe for anti reflective coatings and a clean lint free cloth 1 3 TECHNICAL SPECIFICATIONS The conditions and tests required for TSO approval of the 500 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 For TSO Compliance see Appendix A 1 3 1 Physical Characteristics 4 60 in 117 mm Rack Width 6 32 in 161 mm Depth Behind Panel with 11 00
96. hen operating within 30 nautical miles of the departure or arrival airport and the CDI scale is the equivalent or 1 0 nm or less 4 5 1 9 APPROACH ANNUNCIATE When performing approach navigation the approach annunciator illuminates when approach is active 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 500 SERIES INSTALLATION MANUAL Page 4 9 P N 190 00181 02 Rev 4 5 1 11 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 500 Series unit 1s operating in the ILS or GPS Approach modes of operation 4 5 1 12 DEMO MODE SELECT This discrete input may be used to select Demo Mode on the 500 Series unit A low on this pin at time of unit power up invokes the Demo Mode Demo Mode allows the 500 Series unit to simulate reception of GPS satellite signals CAUTION Do not connect DEMO MODE SELECT in an aircraft installation 4 5 1 13 TIME MARK OUT Time Mark Out is a time reference pulse output once per second derived from GPS satellite signals 4 5 2 Annunciators Switches Electrical Characteristics 4 5 2 1 Annunciators PinName Connector Pin
97. ies Unit 1 Sandel SN3308 ARINC 429 OUT A ARINC 429 OUT B VOR ILS VOR ILS GPS ARINC 429 IN A GPS ARINC 429 IN B GPS ARINC 429 OUT A GPS ARINC 429 OUT B ILS GPS APPROACH MAIN LEFT MAIN RIGHT MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG Sandel SN3308 P3 26 7 SEE NOTE 2 429 3 429 3 RX B 429 1 429 1 TX B 429 1 RX A 429 1 RX B 21 22 25 24 NOTES 1 ALL JE WIRES 24 AWG OR LARGER UNLESS THE GPS ARINC 429 IN 1 OTHERWISE NOTED PORT P5001 48 AND 49 IS ALREADY USED FOR ANOTHER PURPOSE THE GPS ARINC 429 IN 2 PORT P5001 50 AND 51 MAY BE CONNECTED INSTEAD 3 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE INTERCONNECT INFORMATION ONLY LOCALIZER ENGAGE LEFT RIGHT LATERAL FLAG LATERAL FLAG UP DOWN VERTICAL FLAG VERTICAL FLAG Figure 4 12 ARINC 429 Sandel EHSI Interconnect 1 500 Series Unit 1 Sandel SN3308 500 SERIES INSTALLATION MANUAL P N 190 00181 02 Page 4 43 Page 4 44 blank RevG 4 11 12 ARINC 429 Sandel EHSI Interconnect 2 GNS 530 1 Sandel SN3308 GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B GPS ARINC 429 OUT A 6 5 3 LS GPS APPROACH MAIN LEFT MAIN RIGH MAIN LATERAL MAIN LATERA
98. igned binary XX undefined mmmmmm latitude minutes unsigned binary x undefined hhhhhhh hundredths of latitude minutes unsigned binary Two s complement binary in 16ths of degrees Easterly variation is positive MSB output first Page C 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 Appendix D 500 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 2 SHADIN ALTITUDE SENTENCE The Garmin 500 Series units shall be capable of receiving the following 17 byte message from Shadin Altitude Encoders Altitude Serializers and Altitude Converters RMS lt sp gt lt gt 12345T lt gt 12ul lt CR gt Where RMS ASCII characters sp space 0x20 lt gt sign indicator Ox2b or 0x2d 12345 altitude in feet T ASCII character lt gt sign indicator 12 sensor temperature ul checksum of bytes 1 through 14 in hex ASCII i e FA CR carriage return 4 Note Checksum is calculated by adding each byte in the message 1 through 14 D 3 ICARUS ALTITUDE SENTENCE The Garmin 500 Series units shall be capable of receiving the following 10 byte message from the Icarus Altitude Serializer ALT lt sp gt 12345 lt CR gt Where ALT ASCII characters sp space 0x20 12345 alt
99. illed in while a remote CDI source select switch is pressed RMT OBS The box is filled in while a remote OBS switch is pressed DISCRETE TOGGLE This allows you to verify the operation of any external annunciators that are present in the installation Verify That 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 INTEG The INTEG annunciator is active and inactive as selected on this page The MSG annunciator is active and inactive as selected on this page The OBS annunciator is active and inactive as selected on this page The TERM annunciator is active and inactive as selected on this page VLOC The VLOC source select annunciator is active and inactive as selected on this page WPT ILS GPS APR The ILS GPS APPROACH output is active and inactive as selected on this page NOTE This output is connected to the autopilot ILS ENGAGE input not to an annunciation and therefore this is for bench testing purposes only 500 SERIES INSTALLATION MANUAL Page 5 7 P N 190 00181 02 RevG 5 2 8 CDI OBS CONFIG Page Select the MAIN CDI OBS COMFIG Page see Figure 5 9 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 500 Series unit front panel make the selections below and verify the interfaces as appropriate
100. in 279 mm Connectors Measured from face of aircraft panel to rear of connector backshells rack and connectors GNS 530 Weight Installed with 8 5 Ibs 3 9 kg rack and connectors 500 SERIES INSTALLATION MANUAL Page 1 1 P N 190 00181 02 Rev 1 3 2 General Specifications Operating Temperature Range 20 C to 55 C For more details see Environmental Qualification Form 9596 non condensing Altitude Range 1 500 ft to 50 000 ft Input Voltage Range 11 to 33 Vdc GPS 500 011 00562 00 10 GNS 530 011 00550 10 30 GNS 530 011 00550 00 GNS 530A 011 00835 00 10 Power Requirements P5001 1 8 A 27 5 maximum GNS 530 Main Connector 3 6 A Q 13 75 Vdc maximum Power Requirements P5002 15 mA Q 27 5 not transmitting COM Connector 3 0 A 27 5 transmitting GNS 530 011 00550 00 GNS 530A 011 00835 00 10 Power Requirements P5002 15 mA Q 27 5 Vdc not transmitting COM Connector 3 0 A 27 5 transmitting GNS 530 011 00550 10 15 mA 13 75 not transmitting 6 0 A 13 75 Vdc transmitting Superflag Power Requirements 500 mA max Per superflag output 27 5 1 0 A max 27 5 Vdc on P5001 Main Superflags 1 0 A max 27 5 on P5006 VOR LOC G S Superflags RTCA DO 178B level C Environmental Testing RTCA DO 160C For more details see Environmental Qualification Forms 1 3 3 GPS Specifications Regulatory
101. indicator displays both lateral and vertical To From indications lateral and vertical flags and superflags GNS 530 connector 5006 always outputs the VOR Localizer Glideslope navigation information The VOR ILS pins on GNS 530 connector 5006 are used to drive an indicator that displays VOR ILS information at all times regardless of the CDI selection on the GNS 530 VOR LOC COMPOSITE OUT is a standard VOR Localizer Composite output signal which may be used to drive the Left Right TO FROM and Flag indications of certain navigation indicators that contain an internal converter The ILS ENERGIZE output goes low when the VLOC frequency is channeled to a localizer channel 4 8 2 X VOR ILS Indicator Electrical Characteristics 4 8 2 1 Superflags PinName Connector Pin VOR LOC SUPERFLAG P5006 GLIDESLOPE SUPERFLAG P5006 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 3 Vdc when the flag is to be OUT OF VIEW The output voltage with respect to ground is less than 3 Vdc when the flag is to be IN VIEW 4 8 2 2 Deviation PinName Connector Pin VOR LOC RIGHT VOR LOC COMMON P5006 6 Out GLIDESLOPE DOWN FLAG GLIDESLOPE P5006 81 Out COMMON The deviation outputs are each capable of driving up to three 1000 2 meter loads with 150 mVdc 10 with respect to 2 5 V Common for full scale deflecti
102. ing EHSI system Sandel SN3308 DATA OUT Off GAMA 429 ARINC 429 data as defined by the General Aviation Manufacturers Association GAMA General Aviation Subset 2 Edition The output data includes navigation and flight plan information to the following systems Garmin GAD 42 Interface Adapter Bendix King EFS 40 50 Sandel SN3308 Collins EFIS 84 Certain other versions of Collins EFIS may also be compatible with this format GAMA 429 Graphics ARINC 429 data as defined by the GAMA General Aviation Subset 2 Edition including GAMA Graphics Protocol A This format outputs intersection symbols as generic waypoint symbols The output data includes navigation and flight plan information including graphical representation of flight plan procedures to the following EFIS systems Honeywell Primus 1000 GAMA 429 Graphics ARINC 429 data as defined by the GAMA General Aviation Subset oe w Int Edition including GAMA Graphics Protocol A The output data includes navigation and flight plan information including graphical representation of flight plan procedures GAMA 429 ARINC 429 data as defined by the GAMA General Aviation Subset ye Pro Line 21 Edition The output data includes navigation and flight plan information to the following EFIS systems Collins Pro Line 21 GAMA 429 Sextant ARINC 429 data as defined by the GAMA General Aviation Subset oe Edition The output data includes navigation and flight plan information to
103. ion Current latitude longitude and GPS altitude in feet see Note below Current velocity vector ground speed and direction of velocity vector over the ground Distance to waypoint Cross track error Desired track Destination waypoint identifier Bearing to destination waypoint Magnetic variation Navigation and warning status Waypoint sequence in route Waypoint position latitude and longitude and magnetic variation Aviation RS 232 data may be transmitted with or without the current GPS altitude in feet Refer to section 5 2 2 The 500 Series unit can receive pressure altitude air data and fuel data from certain systems on the GPS RS 232 IN 1 port The 500 Series unit can communicate with a Ryan TCAD 9900B system using the GPS RS 232 OUT 2 and GPS RS 232 IN 2 lines to display traffic information on the 500 Series unit If two 400 or 500 Series units are installed in an aircraft the GPS RS 232 OUT 3 and GPS RS 232 IN 3 lines may be cross connected to crossfill flight plans and user defined waypoints from one 400 or 500 Series unit to the other The 500 Series unit can communicate with a BF Goodrich WX 500 Stormscope using the GPS RS 232 OUT 4 and GPS RS 232 IN 4 lines to display lightning strike information on the 500 Series unit 4 6 1 2 ARINC 429 The data output on the GPS ARINC 429 OUT port depends on the configuration refer to section 5 2 1 Below is a list of the configurations and the labels output for each one
104. ion leg sequencing loss of integrity RAIM message and waypoint alert are not required in most installations where the GNS 430 display is located in the center area of the vertical instrument panel For most aizcrali a location in the center radio stack or other location on the pilot s panel within the normal field of view at height suitable for normal viewing from the pilots seated position will not require external switching or annunciators This area is generally defined as between the airspeed indicator on the left the center radio stack or left side of dual center radio stack arrangements on the right and vertically such that it is not blocked by the glareshicld on top and not below the instrument panel or blocked by throttles control yoke etc on the bottom Installations located outside of this arca i e in a center pedestal on the opposite side of the aircraft from the pilot s station on a tilt panel behind throttles etc may require external annunciators Sincerely C Dale Bleakney FAA Program Manager Wichita Aircraft Certification Office Page B 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 e U S Department Small Airplane Directorate Wichita Aircraft Certification Office of 1801 Airport Road Room 100 Federal A Wichita Kansas 67209 Administration September 4 2002 Mr Robert W Billings GARMIN INTERNATIONAL 1200 East 151st Street Olathe KS 66062 Subject GARMI
105. ith any reproduced portion of this document WARNING This product its packaging and its components contain chemicals known to the State of California to cause cancer birth defects or reproductive harm This Notice is being provided in accordance with California s Proposition 65 If you have any questions or would like additional information please refer to our web site at www garmin com prop65 500 SERIES INSTALLATION MANUAL Page i P N 190 00181 02 RevG TABLE OF CONTENTS 1 GENERAL DESCRIPTION LUINFRODUGLDION ettet 1 2 EQUIPMENT 1 3 TECHNICAL 1 4 LICENSE REQUIREMENTS see VS CERTIFICATION hr ere REESE 1 6 FAULT DETECTION AND EXCLUSION FDE t I EEIMITED WARRANTY ee rer DR RE E RI a a EUR 2 INSTALLATION ZL INTRODUCTION dert rer rte eren pee et et ied a 2 2 ANTENNA CONSIDERATIONS i 2 3 RACK 5 2 4 CABLING AND 25 COOLING HAIR i oie eiit ttt tte 2 6 MINIMUM INSTALLATION REQUIREMENTS 3 INSTALLATION PROCEDURE UNIT AND ACCESSORIES em DO RO DO e tdeo eqs 3 2 DATA BASE 3 3 MISCELLANEOUS OPTIONS 3 4 INSTALLATION ACCESSORI
106. itude encoder receivers do not have internal isolation diodes to prevent the unit from pulling the encoder lines to ground when the unit is off These units require a diode added to the installation harness for each encoder line The anode should be connected on the receiving unit s side and the cathode should be connected on the encoder side A set of diodes is required for each unit without internal diodes The 500 Series unit includes internal diodes for isolation of the encoder lines 4 3 3 Altimeter Configuration None 4 3 4 Altimeter Calibration and Checkout Refer to section 5 2 7 for the gray code altitude checkout 4 3 5 Altimeter Interconnect Refer to Figure 4 2 on page 4 23 and Figure 4 5 on page 4 29 for the altimeter interconnect Page 4 6 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 4 4 MAIN INDICATOR 4 4 4 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 530 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 The Navigation method is optionally annunciated externally by connecting to the VLOC ANNUNCIATE output P5001 1 and GPS ANNUNCIATE output P5001 2 GPS and VOR ILS na
107. itude in feet CR carriage return 0x0d 500 SERIES INSTALLATION MANUAL Page D 1 P N 190 00181 02 Rev D 4 SHADIN FUEL FLOW SENTENCE The Garmin 500 Series units shall be capable of receiving the following 55 byte message from the Shadin Fuel Flow Indicator lt STX gt K0543 2 lt sp gt 0100 0 lt sp gt 0040 0 lt sp gt 0060 0 lt sp gt 0123 4 lt sp gt 0045 4 lt sp gt 0078 0 lt sp gt 123 lt ETX gt Where lt STX gt start transmit character 0x02 K units designation 1 e Gallons Liters Kilograms B pounds 0543 2 total fuel remaining i e ASCII coded decimal format 0x30 0x35 0x34 0x33 0x2e 0x32 sp 0x20 0100 0 fuel flow rate total formatted as for total fuel remaining 0040 0 fuel flow rate engine one or asterisks in the case of single engine aircraft 0060 0 fuel flow rate engine two asterisks in the case of single engine aircraft 0123 4 fuel used total 0045 4 fuel used engine one asterisks in the case of single engine aircraft 0078 0 fuel used engine two asterisks in the case of single engine aircraft 123 checksum of bytes 2 through 51 lt ETX gt end transmit character 0x03 Note Checksum is calculated by adding each byte in the message 2 through 51 such that carries are discarded to give a one byte result The ASCII coded decimal representation of that byte is given ranging from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 D 5 ARNAV El FUEL FLOW S
108. ivity Standard deflection 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 shall be at least 60 dB down a With a standard deflection FLY DOWN condition 90 Hz dominant the output shall be 78 mV 7 8 mV b With a standard deflection FLY UP condition 150 Hz dominant the output shall be 78 mV 7 8 mV The unit Flags a When the level of a standard deviation test signal produces 50 or less of standard deflection of the deviation indicator b In the absence of 150 Hz modulation C In the absence of 90 Hz modulation d In the absence of both 90 Hz and 150 Hz modulation e Inthe absence of RF Page 1 6 Rev 500 SERIES INSTALLATION MANUAL P N 190 00181 02 14 LICENSE REQUIREMENTS The following guidance is provided to help ensure the proper licensing of the GNS 530 COM within the United States and its territories Outside the United States the operator must verify compliance with any applicable communications regulations for the area in which the equipment is operated 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 500 Series unit aboard a private aircraft is not needed i
109. l Aviation Fate of applrcation November 14 1998 Lule Arqe Hale of tssteance 2 March 21 2000 Pate amended April 13 2001 By linn of the I gnata SEE ger Harvey E Nero Program Mana Wichita Aircraft Certification Office te aay alteration of this certificate is panishable by a of not exceedizg 1 408 cr imprisonment ot exceeding 1 years v Loth FAR Yom 8110 2110 40 PAGE 1 of 2 PAGES This cert ficele mey be tracafersed in accordance with FAR 47 Page B 2 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 J GARM e INSTALLATION MEMORANDUM TO GARMIN Authorized Dealers FROM GARMIN International DATE January 25 1999 SUBJECT GNS 430 approval basis without external switching or annunciation CC Wichita Aircraft Certification Office Due to reluctance by GARMIN Authorized Dealers and FAA Flight Standard District Office Field Inspectors to install and approve GARMIN GNS 430 Integrated VHF Communications VHF Navigation and GPS Receiver equipment in certain installations GARMIN is issuing this letter to clarify the approval basis for accomplishing such installations without external switching or annunciation GARMIN obtained initial TSO and STC approval under TSO C128 a in conjunction with AC 20 138 tor the GPS Receiver of the GNS 430 in a Piper Cherokee PA32 260 without external switching or annunciation The cartification was accomplished under the ju
110. le Flight Director commands 0 bank level flight for 5 seconds commands increasing right bank at 1 second for 5 seconds commands 5 right bank for 5 seconds commands decreasing right bank at 1 second for 5 seconds until command is 0 bank again This cycle repeats continuously Page 5 16 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 5 3 3 Signal Acquisition Test Upon approval of the Instrument Panel Self test Page the Satellite Status Page is displayed If the unit 1s 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 Once GPS position information is available use the DIRECT TO key to activate the navigation function to a nearby airport NAVAID or intersection Ensure that any connected equipment is transmitting and or receiving data from the 500 Series unit and is functioning properly see the Pilot s Guide for more information on the direct to function 5 3 4 Deviation amp Flags Check 5 3 4 1 Analog Deviation amp 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 devi
111. mounted on top of the aircraft For best performance select a location with an unobstructed view of the sky above the aircraft when in level flight Figure 2 1 illustrates a typical GPS antenna installation The antenna should be located at least three feet from transmitting antennas such as VHF COM HF transmitter DME Transponder and Radar For rotorcraft locate the GA 56 Antenna as far as possible from the main rotor hub This reduces the percentage of time the blade blocks the antenna Also mount it as far below the blade surface as possible if installing the antenna under the blade This reduces signal distortion caused by the blades 2 2 2 ANTENNA LOCATION The GNS 530 COM antenna should be well removed from all projections engines and propellers The ground plane surface directly below the antenna should be a flat plane over as large an area as possible 18 inches square minimum The antenna should be mounted a minimum of six feet from any DME or other COM antennas four feet from any ADF sense antennas and three feet from the 500 Series and its GPS antenna If simultaneous use of two COM transceivers is desired Spit COM or simulcomm use of the TX interlock function is mandatory In addition the COM antennas should be spaced for maximum isolation A configuration of one topside antenna and one bottom side antenna is recommended 2 2 3 VOR LOC ANTENNA LOCATION The GNS 530 VOR LOC antenna should be well removed from all proje
112. n Page press the small right knob CRSR to turn on the cursor Turn the large right knob to change between data fields Turn the large or small right knob to change a field that the cursor is on Once you have made the desired selection press the ENT key to accept the entry 5 2 INSTALLATION CONFIGURATION PAGES The Configuration Pages described in the following sections are in the order found when rotating the right small knob clockwise starting at the MAIN ARINC 429 CONFIG page Use the procedure described in section 5 1 to get to this page NOTE The configuration pages shown here reflect MAIN software version 2 10 All configuration pages shown apply to the GNS 530 but not all apply to the GPS 500 Those pages and fields that apply only to certain 500 Series units are denoted as such HAIN ARINC 429 CONFIG 5 2 1 MAIN ARINC 429 CONFIG Page 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 Figure 5 1 SPEED MAIN ARINC 429 CONFIG Page Low Standard low speed ARINC 429 nominally 12 5 kilobits per second High speed ARINC 429 nominally 100 kilobits per second DATA IN 1 DATA IN 2 Off No unit connected to this ARINC 429 input Airdata Altitude temperature and speed information from the following Airdata systems B amp D 2600 2601 2800 9000
113. n many circumstances Please see FCC Fact Sheet PR5000 or contact the FCC at 1 800 322 1117 for more information 2 No license change is required for an aircraft which already has a station license per FCC 404 Instructions dated 1994 3 Ifan aircraft license is required or desired contact the FCC at 1 800 322 1117 to request FCC Form 404 Application for Aircraft Radio Station License to apply for FCC authorization The FCC also has a Fax on Demand service to provide forms by FAX at 202 418 0177 This equipment has been type accepted by the FCC The bandwidth emission designator is 6K00 A3E CAUTION THE VHF TRANSMITTER IN THIS EQUIPMENT IS GUARANTEED TO MEET FEDERAL COMMUNICATIONS COMMISSION ACCEPTANCE OVER THE OPERATING TEMPERATURE RANGE MODIFICATIONS NOT EXPRESSLY APPROVED BY GARMIN COULD INVALIDATE THE LICENSE AND MAKE IT UNLAWFUL TO OPERATE THE EQUIPMENT 1 5 CERTIFICATION The GPS receivers in the 500 Series units are certified for IFR enroute terminal and non precision approaches The 500 Series initial certification was accomplished via STC s by Garmin in a Piper PA32 See Appendix B for copies of the STC s The 500 Series units have been qualified to RTCA DO 160 Section 22 lightning requirements Special installation considerations are required refer to the Environmental Qualification Forms in Appendix A 1 6 FAULT DETECTION AND EXCLUSION FDE The 500 Series equipment as installed has been found to comply
114. n to the VOR audio and verify that no electrical interference such as magneto noise is present Check the tone identifier filter operation Fly inbound or outbound on a selected VOR radial and check for proper LEFT RIGHT TO FROM and FLAG indications Check the VOR accuracy Verify that the flag is hidden with a valid received station and that the flag is in view when there is not a received station It may be required by the governing regulatory agency to verify operation of the VOR receiver at the extents of a ground facility s service volume e g FAA AC 23 8A 5 3 9 DME Tuning Check GNS 530 Only Select a VOR ILS channel that corresponds to 1 a DME station within a 40 nautical mile range or 2 the frequency of a DME ground tester Verify that the DME locks on to the signal and a valid distance ground speed and time are displayed Page 5 18 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 Appendix A CERTIFICATION DOCUMENTS 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 Aviation Authority approved installers are hereby granted permission to reference appropriate service instructions and excerpts from this Installation Manual to accomplish the
115. nect GPS RS 232 OUT 1 GPS RS 232 IN 1 GPS RS 232 OUT 3 GPS RS 232 IN 3 P4001 56 57 41 42 GARMIN GARMIN Eventide BF Goodrich JP Shadin Shadin Shadin Sha Sha Electronics 939 GTX 327 GPSMAP 195 GPS Argus 3000 Stormscope Instruments Miniflo L Digiflo i igi F ADC 200 International 5000 7000 Series EDM 700 91204XT 38 D 91053XP 91053XT D 91802 F ADC 2000 FP 5L P3271 1 1 P302 2 5 DATA IN 16 5 2 9 12 H 12 5 16 RS 232 IN dl 13 1 GND 4 SHELL 2 2 D 2 9 SHELL RS 232 IN LO GARMIN Shadin Icarus ARNAV JP Shadin Shadin Shacin Shadin Shodin Electronics GTX 327 88007 9000T Instruments FC 10 Instruments Miniflo L Digiflo L Digiflo L Digidate 200 International 9200T 3000 FT 10 EDM 700 91204XT 38 D 91053XP 91053 0 9 802 F ADC 2000 FP 5L Q 0 EE 20 7 2 2 1 6 5 J 5 6 15 RS 232 OUT HI 7 13 15 SHELL 4 SHELL 2 2 2 9 SHELL RS 232 OUT LO m P4001 Qo 42 GPS RS 232 IN 3 SEE NOTE 2 41 GPS RS 232 OUT 5 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED IF TWO OR MORE 400 500 SERIES UNITS ARE INSTALLED THE RS 232 LINES ON 5001 41 AND 5001 42 MAY BE CROSS CONNECTED TO CROSSFILL FLIGHT PLANS AND USER WAYPOINTS TO CROSSFILL FLIGHT PLANS IT IS REQUIRED THAT BOTH 400 500 SERIES UNITS HAVE IDENTICAL DATABASE CYCLE
116. ng i GMA 340 Engineering KMA 24 KMA 24H PMA 6000 70 71 P5002 P1 Bottom P241 P241 500 OHM COM AUDIO HI 7 SEE AGE C 9 13 9 10 9 10 T 16 COM 1 COM 2 AUDIO HI 500 OHM COM AUDIO LO 19 o gt 10 14 GND LUG GND LUG GND LUG COM 1 COM 2 AUDIO LO COM MIC AUDIO HI 6 a 11 15 P H P H 3 E COM 1 COM 2 MIC AUDIO COM MIC KEY 4 12 30 R R V C H COM 1 COM 2 MIC KEY COM MIC AUDIO LO 18 10 14 GND LUG GND LUG GND LUG COM 1 COM 2 MIC AUDIO LO INTERCOM MIC HI 5 INTERCOM MIC SEE NOTES 5 AND 6 INTERCOM MIC LO 17 x INTERCOM MIC LO TRANSMIT INTERLOCK 14 lt SEE NOTE 3 COM TRANSFER SWITCH SEE NOTE 7 COM REMOTE TRANSFER 15 lt P5006 530 ONLY 500 OHM VOR ILS AUDIO HI 16 SEE ote gt 17 19 12 13 12 13 P 13 NAV 1 NAV 2 AUDIO HI 500 OHM VOR ILS AUDIO LO 17 J gt 18 20 GND LUG GND LUG GND LUG NAV 1 NAV 2 AUDIO LO VLOC TRANSFER SWITCH VLOC REMOTE TRANSFER 28 6 o 4 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 5 THE GNS 530 INTERCOM FUNCTION SHOULD ONLY BE USED 7 THE COM REMOTE TRANSFER INPUT 5002 15 MAY BE IF THERE 2 CONNECTING TWO MICROPHONES TO MIC AUDIO HI LO OR INTERCOM MIC HI LO AT THE SAME TIME MAY RESULT 6 IN WEAK OR DISTORTED AUDIO MIC ISOLATION RELAYS ARE RECOMMENDED SO THAT ONLY ONE MIC IS ACTIVE AT A TIME 3 CONNECT TRANSMIT INTERLOCK 5002 14 TO THE OTHER TRANSCEIVER S MIC KEY TO MINIMIZE SQUELCH BREAKS ON HE GNS 530 COM COM MIC
117. nual course select to the 500 Series unit which is required for the GNS 530 VOR receiver and optional for the 500 530 GPS receiver Course information can come from an analog resolver or from an EFIS EHSI via ARINC 429 serial data HSUCDI Indicator or EFIS This device displays Nav Flag Left Right To From Glideslope Flag and Up Down The indicator s used in conjunction with the GNS 530 VOR ILS receivers shall be TSO d 500 SERIES INSTALLATION MANUAL Page 2 3 P N 190 00181 02 Rev 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 Category Description Temperature operating F2 55 to 70 C ground survival F2 55 to 85 C Altitude F2 55 000 feet Temperature Variation A 10 C per minute Humidity C 95 at 55 C Vibration CLMY Turbo Reciprocating Helicopter Waterproofness S Continuous Stream Fluids F Deicing Fluid Lightning 2A Direct Effects Icing C 0 15 thick 2 Electrical Characteristics LNA Supply voltage 4 5 40 5 LNA Supply Current 20 mA Maximum LNA Operating Frequency 1575 42 2 00 MHz LNA Gain 20 dB Maximum 12dB Minimum LNA Noise Figure 3 0 dB Maximum LNA Output VSWR 50 Q 2 1 Maximum LNA Input power at 1 dB Gain Compression 6 dB
118. number the more signal is required to break squelch SIDETN Sets the sidetone audio output level May be set to any value between 0 zero and 63 MIC Sets the Mic Gain output level May be set to any value between 0 zero and 63 This adjusts the output for differences in microphones used Should adjustment be necessary refer to the maintenance manual The MIC field in the COM SETUP page is only available in GNS 530 s n 78404161 and above The sidetone audio output level is independent of the COM volume knob on the 500 Series unit Store Calibration Select this field and press the ENT key to accept the squelch threshold and sidetone audio settings on this page If you wish for the squelch and sidetone settings to return to their previous values do not select this field Simply change to the next configuration page or turn off the unit if you are done with configuration Verify That The box is filled in while the COM push to talk switch is pressed The box is filled in while a remote COM transfer switch is pressed The box is filled in while the COM is receiving a signal The box is filled in while the COM push to talk switch is pressed Page 5 10 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 5 2 10 VOR DISCRETE INPUTS Page VOR DISCRETE 1 0 GNS 530 Only Select the VOR DISCRETE INPUTS Page see Figure 5 11 This page allows you to verify the operation of an external VLOC transfer switch that may b
119. of Certification for FDE GPN 005 00077 63 Revision A these changes have been approved as minor TSOA design changes and GARMIN may distribute this upgrade upon receipt of this Letter of Design Approval Additionally the Service Bulletin addressing this software upgrade will indicate that for those aircraft installations that desire Oceanic Remote operation approval the AFM S must be amended per Notice 8110 60 paragraph 6c We will retain your letter and the data listed in the enclosure We have received data that is new for this application Other related documentation is already on file for the previously approved GNC 500 series of products If you have questions regarding this authorization please contact me at 316 946 4134 Sincerely Roger Souter Aerospace Safcty Engineer Electrical and Mechanical Systems Wichita Aircraft Certification Office Enclosure Page B 6 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 Appendix C 500 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 500 Series RS 232 data shall have the following general format SIX ASCII start of text character 02 hex tls Type output sentences see following paragraphs for description t2s One or more type 2 output sentences see follo
120. on The drive circuit provides for more than full scale deflection with a maximum course deviation output voltage of 300 mVdc 10 4 8 2 3 TO FROM PinName Connector Pin VOR LOC TO P5006 VOR LOC FROM VOR LOC COMMON P5006 The output is capable of driving up to three 200 Q meter loads When indicating TO the output is 225 75 mVdc When indicating FROM output is 225 75 mVdc When invalid information is present Flag IN VIEW the TO FROM output is 0 10 mVdc Page 4 16 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 4 8 2 4 Flag Connector Pin VO VOR LOC FLAG P5006 VOR LOC FLAG VOR LOC COMMON P5006 GLIDESLOPE FLAG P5006 GLIDESLOPE DOWN FLAG GLIDESLOPE P5006 81 Out COMMON The Flag output is capable of driving up to three 1000 Q 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 5 OBS Connector Pin VO VOR OBS ROTOR C P5006 Out VOR OBS ROTOR H GROUND P5006 VOR OBS STATOR D P5006 VOR OBS STATOR F P5006 VOR OBS STATOR E G VOR LOC P5006 11 Out COMMON VOR OBS ROTOR C and H are a buffered 500 Hz output that is intended to drive the OBS rotors VOR OBS STATOR D and VOR OBS STATOR F are each phase and amplitude shifted version
121. on grade RTV sealant or sealants containing acetic acid These sealants may damage the electrical connections to the antenna Use of these type sealants may void the antenna warranty 500 SERIES INSTALLATION MANUAL Page 3 3 P N 190 00181 02 Rev 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 GASKET bs 1 PLACE NUT AND CASKET DVFR CABLE AND STRIP JACKET NUT ES TO DIMENSION SHDWwN 18 2 COMB OUT BRAID AND TRIM DIELECTRIC TO DIMENSION SHOWN 1 1 F 3 PULL BRAID VIRES FORWARD AND TAPFR TOWARD CENIER CONDLCTOR PLACE CLAMP OVER BRAID AND PUSH BACK mi AGAINST CABLE JACKET 4 FOLD BACK BRAID OVER CLAMP 25 SHOWN TRIM OFF EXCESS SRAID SDLDFR CONTACT TO CENTER CONDUCTOR t 5 INSERT CABLE CLAMP AND GASKFT N7D CONNECTOR EDDY MAKING SLRE THAT SHARP EDGE OF CLAMP SEATS PROPERLY AND TIGHTEN NUT Figure 3 1 Coaxial Cable Installation 3 The card edge connector may be used to terminate shield grounds to the 500 Series back plate CAUTION 4 Feed wires
122. play device press MENU on the MAIN CDI OBS CONFIG page and select Ignore SEL CRS for VLOC Page 5 8 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 CDI GNS 530 Only GPS The GNS 530 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 VLOC The GNS 530 CDI button is in the VLOC state and the VLOC ANNUNCIATE output is active GPS Only The GNS 530 CDI button has been disabled NOTE If it is desired to disable the GNS 530 CDI key press MENU on the MAIN CDI OBS CONFIG page and select Ignore CDI key This causes the field above the CDI key to always display GPS regardless of CDI key presses This may be necessary for certain EFIS systems where navigation sensor selection must be accomplished on the EFIS or its control panel OBI SOURCE GNS 530 Only Always GPS The MAIN King Serial OBI outputs are always GPS This 1s useful if it is desired to switch a Bendix King KI 229 or KNI 582 RMI pointer independently from the GNS 530 CDI button Track CDI The MAIN King Serial OBI outputs are GPS or VOR and switchable by the GNS 530 CDI button This is useful if it is desired the Bendix King KI 229 or KNI 582 RMI pointer to display the same navigation source as the GNS 530 CDI outputs VERT CDI Flag Up The vertical deviation bar is parked in the full scale up position when GPS or VOR navigation is selected fo
123. ppendix A CERTIFICATION DOCUMENTS CONTINUED AIRWORTHINESS essen eee A 2 ENVIRONMENTAL QUALIFICATION FORM GNS 530 A 3 ENVIRONMENTAL QUALIFICATION FORM GPS 500 A 4 ENVIRONMENTAL QUALIFICATION FORM GA 56 Appendix B STC PERMISSION Appendix 500 SERIES RS 232 AVIATION DATA C 1 Appendix D 500 SERIES RS 232 FUEL AIR DATA INPUT FORMAT eee D 1 Appendix E 500 SERIES LRU INTERFACE OVERVIEW u uu E 1 Note Throughout this document references made to GNS 530 shall equally apply to the GNS 530A except where specifically noted Page ii 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 LIST OF FIGURES FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU FIGU RE 2 1 RE 3 1 RE 3 2 RE 3 3 RE 3 4 RE 3 5 RE 3 6 RE 3 7 RE 4 1 RE 4 2 RE 4 3 RE 4 4 RE 4 5 RE 4 6 RE 4 7 RE 4 8 RE 4 9 RE 4 10 RE 4 11 RE 4 12 RE 4 13 RE 4 14 RE 4 15 RE 4 16 RE 4 17 RE 4 18 RE 4 19 RE 4 20 RE 4 21 RE 4 22
124. r Pin GPS RS 232 OUT 4 P5001 54 Out The RS 232 outputs conform to EJA Standard RS 232C with an output voltage swing of at least 5 V when driving a standard RS 232 load 4 6 2 2 ARINC 429 PinName Connector Pin The GPS and VOR ILS ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers 4 6 3 Serial Data Configuration Refer to section 5 2 1 for the main GPS ARINC 429 configuration Refer to sections 5 2 13 5 2 14 and 5 2 15 for the Stormscope configuration Refer to section 5 2 16 for the Skywatch configuration Refer to sections 5 2 16 and 5 2 17 for the TCAD configuration If the GDL 49 satellite data link transceiver has been installed refer to the GDL 49 Installation Manual 190 00231 00 for Configuration Mode Operations 4 6 4 Serial Data Calibration and Checkout Refer to section 5 3 2 for the serial data checkout Refer to sections 5 2 13 5 2 14 and 5 2 15 for the Stormscope checkout Refer to section 5 2 16 for the Skywatch checkout Refer to sections 5 2 16 and 5 2 17 for the TCAD checkout 4 6 5 Serial Data Interconnect Refer to Figure 4 10 on page 4 39 for the RS 232 serial data interconnect Refer to Figure 4 11 on page 4 41 for the ARINC 429 Bendix King EFS 40 50 interconnect Refer to Figures 4 12 4 13 and 4 14 starting on page 4 43 for the ARINC 429 Sandel EHSI interconnect Refer to Figure 4 15 on page 4 49 for the ARINC
125. r Bendix King Serial OBI devices based upon the GNS 530 VOR receiver When a localizer channel is tuned on the VLOC window there is a bit in the data stream set to indicate that a localizer frequency is tuned which stows the needle or drive it to the 3 o clock position 4 9 2 RMI OBI Electrical Characteristics PinName Connector Pin PinName Connector Pin The output driver is active low The driver output voltage is not more than 1 0 V when sinking 20 mAdc The maximum off state leakage current with respect to ground is less than 10 uAdc 4 9 3 RMI OBI Configuration For the GNS 530 refer to section 5 2 8 for the MAIN OBI source configuration 4 9 4 RMI OBI Calibration and Checkout None 4 9 5 RMI OBI Interconnect Refer to Figure 4 21 on page 4 61 for the RMI OBI interconnect Page 4 18 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 4 10 DME TUNING GNS 530 ONLY 4 10 1 DME Tuning Function The GNS 530 can channel a DME based on the tuned VLOC frequency The GNS 530 outputs 2 of 5 BCD or Slip parallel DME and King Serial DME channeling format When DME COMMON is held low the GNS 530 actively tunes the DME 4 10 2 DME Tuning Electrical Characteristics 4 10 2 1 Parallel DME Tuning PinName Connector Pin These pins are outputs when the GNS 530 is configured for 2 of 5 parallel DME tuning For each of the parallel DME tuning discrete outputs the dri
126. r output The exception is when the CDI is in VLOC mode and an ILS frequency is tuned in which case the vertical deviation bar is parked in the centered position Flag Center The vertical deviation bar is parked in the centered position whenever it is flagged 500 SERIES INSTALLATION MANUAL Page 5 9 P N 190 00181 02 Rev 5 2 9 COM SETUP Page GNS 530 Only Con SETUP Select the COM SETUP Page see Figure 5 10 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 10 COM SETUP Page SPACING 25 0 kHz Selects traditional 25 kilohertz spacing 760 channel 8 33 kHz Selects 8 33 kilohertz channel spacing which is required in some areas of the world CAUTION 8 33 kHz channels are not authorized for use in the United States SQ 250 Sets the squelch threshold for 25 kHz channel spacing operation May be set to any value between 0 zero and 63 The higher the number the less signal is required to break squelch For GNS 530 units with serial number 200 or lower the operation of the SQ 250 setting is reversed The higher the SQ 250 number the more signal is required to break squelch SQ 833 Sets the squelch threshold for 8 33 kHz channel spacing operation May be set to any value between 0 zero and 63 The higher the
127. r the interconnect between a GNS 530 and a Bendix King KI 209A Refer to Figure 4 8 on page 4 35 for the interconnect between a GPS 500 and a Bendix King KI 208A Page 4 8 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 4 5 ANNUNCIATORS SWITCHES 4 5 1 Annunciators Switches Function Initial certification of the 500 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 500 Series unit However if the 500 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 Appendix B includes an FAA letter granting permission to install GNS 530 without external switches and annunciators 4 5 1 1 MESSAGE ANNUNCIATE When a new status message is available the Message Annunciator flashes When status messages remain effective the Message Annunciator illuminates 4 5 1 2 WAYPOINT ANNUNCIATE The waypoint annunciator output is driven in the following manner 1 When the aircraft is within 10 seconds of reaching the turning point for a course change the waypoint annunciator flashes 2 When the aircraft is in a turn the waypoint annunciator illuminates and remains illuminated until the turn is completed 3 When user arrival alarm is set and the aircraft is within the circle defined by the arrival alarm radius at the arrival
128. rates the 500 Series to match the input source Verify OBS operation by checking that the course displayed on the 500 Series is within 2 of the selected course Do this at 30 intervals around the OBS card DME CHNL MODE This configuration allows you to set the format for DME tuning data output King Serial King Serial DME tuning data not operational for MAIN software versions 2 02 and lower Parallel 2x5 for MAIN software versions 2 02 and lower 2 02 and lower Narco 890 891 2 of 5 parallel DME tuning compatible with the following DME units Narco DME 890 Narco DME 891 ARC Cessna RTA 476A 5 2 12 VOR LOC GS ARINC 429 CONFIG Page GNS 530 Only Select the VOR LOC GS ARINC 429 CONFIG Page see Figure 5 13 This page configures the VOR ILS ARINC 429 output and input ports VOR LOC GS ARINC 429 CONFIG Figure 5 13 VOR LOC GS ARINC 429 CONFIG Page Low Standard low speed ARINC 429 nominally 12 5 kilobits per second High speed ARINC 429 nominally 100 kilobits per second Page 5 12 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 SDI Common VOR ILS receiver only 429 data with SDI 0 is used VOR ILS 1 Number 1 Pilot VOR ILS receiver Only 429 data with SDI 0 or SDI 1 is used VOR ILS 2 Number 2 Copilot VOR ILS receiver Only 429 data with SDI 0 or SDI 2 is used DME MODE Directed freq 1 If the GNS 530 is connected to a multi channel ARINC 429 DME channel 1 of that DME is
129. risdiction of the Wichita Aircraft Certification Office with the basis for approval as follows 1 The GNS 430 was panel mounted in the center radio stack Normal field of view has been interpreted to be from the airspeed indicator to and including the center radio stack Therefore mounting of the GNS 430 was accomplished in the pilot s normal field of view 2 GPS receiver made CDI source information leg sequencing loss of integrity RAIM message and waypoint alert annunciations are located on the GNS 430 display Color and size of these annunciations were chosen to provide optimal recognition and color association with the related condition Both color and size were a determining factor in this approval 3 The GNS 430 CDI source information switching is accomplished internally therefore the switch used to determine the source of CDI source information on the associated indicator is located on the GNS 430 Follow on IFA airworthiness approval was accomplished under the STC process on a Mooney M2DJ incorporating dual GNS 430 receivers Approval was granted on the Mooney installation without the requirement for external switching or annunciation under the same guidance aforementioned installations which deviate from this guidance may have additional requirements imposed such as external annunciation The GNS 430 provides interfaces for such installations For the Piper Charokea PA32 260 approval reference STC dated Octo
130. sible for ensuring that the ICA is made part of the applicable section 91 409 inspection program for their aircraft This is accomplished when a maintenance entry is made in the aircraft s maintenance record in accordance with section 43 9 This entry records the major alteration and identifies the original ICA location e g Block 8 of FAA Form 337 dated along with a statement that the ICA 1s now part of the aircraft s inspection maintenance requirements Page A 2 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 A 2 Environmental Qualification Form GNS 530 NOMENCLATURE GNS 530 Airborne GPS VOR ILS COM System TYPE MODEL PART NO 010 00182 which includes 011 00550 TSO JTSO COMPLIANCE TSO C129a Class A 1 GPS TSO C37d Class 4 amp 6 JTSO 2C37e GNS 530 COM TX TSO C37d Class 3 5 JTSO 2C37e 530A COM TX TSO C38d Class amp JTSO 2C38e COM RECEIVER TSO C40c JTSO 2C40c VOR RECEIVER TSO C36e JTSO C36e LOCALIZER RECEIVER TSO C34e JTSO C34e GLIDESLOPE RCVR MANUFACTURER S SPECIFICATION AND OR OTHER APPLICABLE SPECIFICATION 004 00044 00 MANUFACTURER Garmin International Inc ADDRESS 1200 E 151 Street Olathe Kansas 66062 NOTE The following information provides examples only It is not intended to be a comprehensive listing of all test conditions LowTemeue HghTemwenue 3828433 x Decompression Hwy
131. t Position Latitude 1 311 Present Position Longitude 312 GrondSped 1 TrackAnge True 1 314 TrmeHeadng 1 315 WidSped 316 WindAnge Tru 320 MagneticHeadng si Drift Angle 3260 LeteralScaleFactr 33 ConicArcInboundCouse Conic Arc Radius 332 Conic Arc Course Change Angle Airport Runway Azimuth 334 Airport Runway Length in Feet 335 Left Right Hand Holding Pattern Azimuth 340 Left Right Hand Procedure Turn Azimuth 3510 Distance To Destination Via Flight Plan 4 3520 Estimated Time To Destination Via Flight Plan 3718 SpeciicEqupmentD lefe 377 Equipment Hex ID Code 19111131 The following labels are output on the VOR ILS ARINC 429 OUT port Page 4 12 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 The labels recognized on the GPS ARINC 429 IN 1 or GPS ARINC 429 IN 2 ports depend on the configuration refer to section 5 2 1 The 500 Series unit can receive traffic data from a BF Goodrich SKY497 Skywatch system using the GPS ARINC 429 IN 1 or GPS ARINC 429 IN 2 ports in order to display traffic information on the 500 Series unit 4 6 2 Serial Data Electrical Characteristics 4 6 2 1 RS 232 PinName Connecto
132. th or extend slightly beyond the finished aircraft panel CAUTION If the front lip of the mounting rack is behind the surface of the aircraft panel the 500 Series unit connectors may not fully engage Make sure that no screw heads or other obstructions prevent the unit from fully engaging in the rack refer to the Connector Engagement Test section 5 3 1 page 5 16 Exercise caution when installing the rack into the instrument panel The rack is designed to facilitate removal of the 500 Series for use in Demo Mode outside the aircraft Deformation of the rack may make it difficult to install and remove the 500 Series unit 500 SERIES INSTALLATION MANUAL Page 3 5 P N 190 00181 02 RevG 3 Install the rack in the aircraft panel using six 746 32 flat head screws and six self locking nuts The screws are inserted from the inside through the holes in the sides of the rack 4 Ifthe back plate was previously removed see step 1 replace the back plate by positioning the tabs on the back plate in the slots of the left side of the rack viewing it from the cockpit and attaching it by replacing the two 4 40 screws 3 8 500 SERIES UNIT INSERTION AND REMOVAL It may be necessary to insert the hex drive tool into the access hole and rotate the mechanism 90 counterclockwise to insure correct position prior to placing the unit in the rack The 500 Series unit is installed in the rack by sliding it straight in until it stops about 1 inc
133. the 500 Series unit 1s installed in the pilot s normal field of view refer to the FAA letter in Appendix B Check that there is adequate depth for the rack in the instrument panel A location away from heating vents or other sources of heat generation is optimal 2 4 CABLING AND WIRING Coaxial cable with 50 Q nominal impedance and meeting applicable aviation regulations should be used for the installation A typical maximum cable length for the GPS antenna 1s 40 feet The installer should insure that the attenuation does not exceed 10 dB at 1 5 GHz for the specific installation Check that there is ample space for the cabling and mating connectors Avoid sharp bends in cabling particularly the COM antenna cable and routing near aircraft control cables Cabling for the 500 Series unit should not be routed near components or cabling which are sources of electrical noise Do not route the COM antenna cable near any ADF antenna cables Route the GPS VOR LOC and Glideslope antenna cables as far as possible away from all COM transceivers and antenna cables 2 5 COOLING AIR The 500 Series units meet all TSO requirements without external cooling However as with all electronic equipment lower operating temperatures extend equipment life On the average reducing the operating temperature by 15 20 C 25 to 35 F doubles the mean time between failure MTBF Recommended airflow rating is 1 CFM cubic foot per minute at a pressure equivalent to
134. through the connector backshells before insertion into the 78 44 and 25 pin connectors 5 Contacts for the 78 44 and 25 pin connectors must be crimped onto the individual wires of the aircraft wiring harness The following tables list contact part numbers for reference and recommended crimp tools Table 3 1 Pin Contact Part Numbers P5001 5008 P5006 connector Positronic Page 3 4 500 SERIES INSTALLATION MANUAL Rev P N 190 00181 02 Table 3 2 Recommended Crimp Tools or equivalent Connector High Density Standard Density Type 22 24 AWG 18 AWG 20 24 AWG Hand Positioner Insertion Positioner Insertion Positioner Insertion Crimping Extraction Extraction Extraction Tool Tool Tool Tool Military P N M22520 2 01 M22520 2 09 M81969 1 04 M81969 1 02 M22520 2 08 M81969 1 02 A 9502 11 81969 1 02 584 739 604 426 N A N A 8 K42 M81969 1 04 K774 M81969 1 02 K13 1 81969 1 02 615717 615725 M81969 1 04 N A M81969 1 02 615724 M81969 1 02 Insertion extraction tools from ITT Cannon are all plastic others are plastic with metal tip 2 Non Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice 3 Alternate contacts for 18 AWG wire As an alternative to the Positronic contacts listed and provided in the installation kit the installer may use contacts made by ITT Cannon under P N 031 1007 001 These contacts require the us
135. tput is capable of driving up to three 1000 Q 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 500 SERIES INSTALLATION MANUAL Page 4 7 P N 190 00181 02 RevG 4 4 2 4 Superflags PinName Connector Pin MAIN LATERAL SUPERFLAG P5001 MAIN VERTICAL SUPERFLAG P5001 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 5 OBS Connector Pin VO MAIN OBS ROTOR C P5001 MAIN OBS ROTOR H GROUND P5001 MAIN OBS ROTOR C and H are a buffered output that is intended to drive the OBS rotors MAIN OBS STATOR D and MAIN OBS STATOR F are each phase and amplitude shifted version of the MAIN ROTOR C output Each pair is intended to read one of the two windings of the indicator s OBS stator 4 4 8 Main Indicator Configuration Refer to section 5 2 8 for the main CDI OBS configuration 4 4 4 Main Indicator Calibration and Checkout Refer to section 5 2 8 for the main CDI OBS checkout 4 4 5 Main Indicator Interconnect Refer to Figure 4 6 on page 4 31 for the generic main indicator interconnect Refer to Figure 4 7 on page 4 33 fo
136. ts for GPS as a primary means of navigation for oceanic remote operations per N8110 60 The oceanic flight phase occurs on the GPS 500 GNS 530 when more than 200 nautical miles from the nearest airport All operators using the GPS 500 GNS 530 as primary means of navigation in oceanic remote areas under FAR parts 91 121 125 and 135 must utilize the FDE Prediction Program prior to conducting a flight in these areas 1 7 LIMITED WARRANTY This Garmin product is warranted to be free from defects in materials or workmanship for one year from the date of purchase Within this period Garmin will at its sole option repair or replace any components that fail in normal use Such repairs or replacement will be made at no charge to the customer for parts or labor provided that the customer shall be responsible for any transportation cost This warranty does not cover failures due to abuse misuse accident or unauthorized alteration or repairs THE WARRANTIES AND REMEDIES CONTAINED HEREIN ARE EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES EXPRESS OR IMPLIED OR STATUTORY INCLUDING ANY LIABILITY ARISING UNDER ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE STATUTORY OR OTHERWISE THIS WARRANTY GIVES YOU SPECIFIC LEGAL RIGHTS WHICH MAY VARY FROM STATE TO STATE IN NO EVENT SHALL GARMIN BE LIABLE FOR ANY INCIDENTAL SPECIAL INDIRECT OR CONSEQUENTIAL DAMAGES WHETHER RESULTING FROM THE USE MISUSE OR INABILITY TO USE THIS PRODUCT OR FRO
137. tuned Directed freq 1 should be selected if a single channel ARINC 429 DME is to be tuned Directed freq 2 If the GNS 530 is connected to a multi channel ARINC 429 DME channel 2 of that DME is tuned 5 2 13 STORMSCOPE CONFIG Page Only if 500 Series unit configured for BFG WX 500 Stormscope interface Select the STORMSCOPE CONFIG Page see Figure 5 14 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 and that the other displayed parameters are correct Verify that all the boxes in the lower portion of the page are green When a 500 Series unit is used with a WX 500 Stormscope the Synchro or Serial heading formats may be used If another heading format is used lightning strike information is visible on the Weather Page but not the Map Page or Arc Page Figure 5 14 STORMSCOPE CONFIG Page 5 2 14 STORMSCOPE TEST Page Only if 500 Series unit configured for BFG WX 500 Stormscope interface Select the STORMSCOPE TEST Page see Figure 5 15 STORHSCOPE TEST This page shows current strike activity WX 500 status WK TEST CELL and the heading supplied by the WX 500 The WX 500 mode may be changed to Demo Noise monitor Self test Strike test or Weather Verify that the WX 500 mode can be changed Refer to the WX 500 manual for specific installation test proced
138. ures for the WX 500 using this page to view strike data change the WX 500 mode view WX 500 status trigger count and heading Figure 5 15 STORMSCOPE TEST Page 500 SERIES INSTALLATION MANUAL Page 5 13 P N 190 0018 1 02 RevG 5 2 15 STORMSCOPE DOWNLOAD DATA Page Only if 500 Series unit configured for BFG WX 500 Stormscope interface Select the STORMSCOPE DOWNLOAD DATA Page see Figure 5 16 This page shows raw data downloadable from the WX 500 Optional sets of data include WX 500 software version environmental conditions configuration and fault data Verify that the configuration data is correct as intended To request which packet of data to display highlight the data group title and use the small right knob to select the desired group 5 2 16 TRAFFIC Page Only if 500 Series unit configured for BFG Skywatch or Ryan TCAD interfaces Select the TRAFFIC Page see Figure 5 17 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 3 Current altitude ALT 4 Altitude limits being imposed LIM A and LIM B 5 Heading and barometric BARO and radio RAD altitude status For BFG Skywatch see Figure 5 17 verify that the 500 Series unit can change the Skywatch operating mode STBY
139. ver output voltage is not more than 1 0 V while sinking 20 mA The maximum off state leakage current with respect to ground is less than 10 uA NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling the DME NAV DME COMMON is considered active if either the voltage to ground is 1 9 V or the resistance to ground is 375 Q These inputs are considered inactive if the voltage to ground is 11 33 Vdc 4 10 2 2 King Serial DME Tuning Connector Pin VO NAV SER DME DATA P5006 NAV SER DME CLOCK P5006 SER DME CHAN REQ PAR DME 4MHZ P5006 SER DME RNAV MODE PAR DME 2MHZ P5006 NAV DME COMMON P5006 These pins are inputs when the GNS 530 is configured for King Serial DME tuning When NAV SER DME DATA or NAV SER DME CLOCK is asserted high and driving a 360 Q load the driver output voltage is not less than 8 V and when asserted low shall not be greater than 10 mV SER DME CHAN REQ PAR DME 4MHZ SER DME RNAV MODE PAR DME 2MHz and NAV DME COMMON are considered active if either the voltage to ground is lt 1 9 V or the resistance to ground is 375 These inputs are considered inactive if the voltage to ground is 11 33 NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling the DME 500 SERIES INSTALLATION MANUAL Page 4 19 P N 190 0018 1 02 RevG 4 10 3 DME Tuning Configuration
140. vigation may be toggled externally when the CDI SOURCE SELECT input P5001 73 is momentarily grounded See section 4 5 for more information on the external annunciators and switches An OBS resolver connection to the GPS is preferred but not required For the GNS 530 an OBS resolver typically is connected to the MAIN OBS inputs for use with the GNS 530 VOR receiver 4 4 2 Main Indicator Electrical Characteristics 4 4 2 1 Deviation PinName Connector Pin MAIN RIGHT 2 5V COMMON P5001 MAIN UP P5001 MAIN DOWN 2 5V COMMON P5001 The deviation output is capable of driving up to three 1000 Q meter loads with 150 mVdc 10 for full scale deflection The drive circuit provides for more than full scale deflection with a maximum course deviation output voltage of 300 mVdc 10 4 4 2 2 TO FROM PinNam Connector Pin MAIN TO P5001 MAIN FROM 2 5V COMMON P5001 The output is capable of driving up to three 200 Q meter loads When indicating TO MAIN TO is 190 40 mVdc with respect to MAIN FROM When indicating FROM MAIN TO is 190 40 mVdc with respect to MAIN FROM When invalid information is present Flag IN VIEW the TO FROM output is 0 10 mVdc 4 4 2 3 Flag PinNam Connector Pin MAIN LATERAL FLAG P5001 MAIN LATERAL FLAG 2 5V COMMON P5001 MAIN VERTICAL FLAG P5001 MAIN VERTICAL FLAG 2 5V COMMON P5001 The Flag ou
141. vity is decreased This input is intended to reduce interference from other transmitters in the aircraft The TRANSMIT INTERLOCK input should be connected to the PTT input of other transmitters in the aircraft If connected to multiple PTT inputs these connections must include diode isolation or multiple radios transmit simultaneously 47 2 COM VORIILS Audio Electrical Characteristics 4 7 2 1 COM MIC KEY PinName Connector Pin This input is considered active if either the voltage to ground is 1 9 V or the resistance to ground is 375 Q This input is considered inactive if the voltage to ground is 11 33 Vdc 4 7 2 2 COM MIC AUDIO INTERCOM MIC AUDIO PinName Connector Pin COM MIC AUDIO HI P5002 6 COM AUDIO LO P5002 INTERCOM MIC HI P5002 INTERCOM MIC LO P5002 COM MIC AUDIO and INTERCOM MIC each have a 520 Q AC input impedance and supply the microphone with a 9 V bias through 620 COM MIC AUDIO is set in the factory so that 275 mVrms modulates the transmitter to 8096 nominally The microphone gain adjustment is accessible through the top cover When a 125 mVrms signal at 1000 Hz is applied to the INTERCOM MIC input the level on the COM AUDIO output is not less than 7 07 Vrms Page 4 14 500 SERIES INSTALLATION MANUAL Rev G P N 190 00181 02 4 7 2 3 COM AUDIO VOR ILS AUDIO PinName Connector Pin 5000 COM AUDIO HI 5000 COM AUDIO LO P5002 5000 VO
142. waypoint the waypoint annunciator flashes for 10 seconds 4 When user arrival alarm is not set and the aircraft is within 10 seconds of reaching the arrival waypoint the waypoint annunciator flashes 4 5 1 3 CDI SOURCE SELECT GNS 530 Only This discrete input may be used to toggle between display of GPS and VOR LOC Glideslope information on the MAIN external CDI HSI A momentary low on this pin performs the same function as pressing the CDI key on the GNS 530 bezel 4 5 1 4 VLOC ANNUNCIATE GNS 530 Only This annunciator output is driven when the unit is configured with a single CDI HSI and the VOR ILS data Is being displayed on the CDI HSI This output parallels the VLOC annunciator on the display 4 5 1 5 GPS ANNUNCIATE GNS 530 Only This annunciator output is driven when the unit is configured with a single CDI HSI and the GPS data is being displayed on the CDI HSI This output parallels the GPS annunciation on the display 4 5 1 6 OBS MODE SELECT This discrete input may be used to toggle between GPS OBS and GPS AUTO modes of operation A momentary low on this pin performs the same function as pressing the OBS key on the 500 Series unit 4 5 1 7 OBS ANNUNCIATE This annunciator output is driven to indicate GPS OBS mode of operation This output is active when the OBS or SUSP annunciation is on the display 4 5 1 8 TERMINAL ANNUNCIATE When performing approach navigation the terminal annunciator is illuminated w
143. wing paragraphs for description ETX ASCII end of text character 03 hex C 3 OUTPUT SENTENCE TYPE 1 The Type 1 output sentences shall have the following general format id item designator single ASCII alphabetic character item data 1 to 10 printable ASCII characters CR ASCII carriage return character 0D hex LF ASCII line feed character hex Each Type 1 sentence shall be output by the 500 Series unit approximately once every second The track desired track and bearing to waypoint angles and the magnetic variation are output according to the current mode of the 500 Series unit automatic magnetic heading magnetic variation computed at last known position true heading magnetic variation of E00 0 or user defined magnetic heading magnetic variation as entered by user 500 SERIES INSTALLATION MANUAL Page C 1 P N 190 0018 1 02 RevG The following table describes the Type 1 output sentence item designator 1d 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 Ident 1 byte Data 10 bytes Description 1234567890 aaaaa Current GPS altitude in feet s dd mmhh Current latitude where S N north or S south dd degrees mm minutes hh hundredths of minutes Current longitude where S E east or W west ddd degrees mm minutes hh hundredths of minutes Track in whole
144. wing units Shadin 9628XX X Fuel Air Data Computer Shadin fuel Serial fuel flow information from the following units Shadin 91204XM Digital Fuel Management System Shadin 91053XM Digital Fuel Management System JP Instruments EDM 700 or EDM 760 Engine Monitor Lightning strike information from a BF Goodrich WX 500 Stormscope 500 SERIES INSTALLATION MANUAL Page 5 3 P N 190 00181 02 CHANNEL OUTPUTS Selection Description Off No unit s connected to output of this channel Aviation Serial position altitude velocity and navigation data to the following units Garmin GPSMAP 295 GPSMAP 195 or GPS III Pilot Argus 3000 5000 or 7000 Moving Map Electronics International FP 5L Fuel Flow Computer non TSO d JP Instruments EDM 700 or EDM 760 Engine Monitor Shadin 91204XM Digital Fuel Management System Shadin 91053XM Digital Fuel Management System Shadin 9628XX X Fuel Air Data Computer Stormscope Series II with Navaid Moving Map Garmin GDL 49 Satellite data link transceiver Garmin GTX 327 Transponder Avtn no alt Serial position velocity and navigation data to the following units Horizon DDMP Crossfill Serial transfer of flight plans and user waypoints between two 500 Series units HW EGPWS Serial communication to a Bendix King Honeywell KGP 560 EGPWS Ryan TCAD Serial communication with a Ryan TCAD 9900B Series system WX 500 Serial communication to a BF Goodrich WX 500 Stormscope FU

Garmin GNS 430 GPS Receiver User Manual

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