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Garmin 420 GPS Receiver User Manual

1. 1 Appendix 400 SERIES RS 232 AVIATION DATA 1 11 04000004440000000000000000022004 C 1 Appendix D 400 SERIES RS 232 FUEL AIR DATA INPUT FORMATI I D 1 Appendix E 400 SERIES LRU INTERFACE OVERVIEW uuu l ul uq uq enne naja ga KAG E 1 Note Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A and GNC 420A except where specifically noted Page ii 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 FIGURE 2 1 FIGURE 3 1 FIGURE 3 2 FIGURE 3 3 FIGURE 3 4 FIGURE 3 5 FIGURE 3 6 FIGURE 3 7 FIGURE 3 8 FIGURE 3 9 FIGURE 4 1 FIGURE 4 2 FIGURE 4 3 FIGURE 4 4 FIGURE 4 5 FIGURE 4 6 FIGURE 4 7 FIGURE 4 8 FIGURE 4 9 FIGURE 4 10 FIGURE 4 11 FIGURE 4 12 FIGURE 4 13 FIGURE 4 14 FIGURE 4 15 FIGURE 4 16 FIGURE 4 17 FIGURE 4 18 FIGURE 4 19 FIGURE 4 20 FIGURE 4 21 FIGURE 4 22 FIGURE 4 23 FIGURE 4 24 FIGURE 4 25 FIGURE 4 26 LIST OF FIGURES GPS ANTENNA AND UNIT INSTALLATION CONSIDERATIONS eene 2 2 COANXIALCABDEJINSTALBEATION cett eet vo tue e aga D ka a ee a ame a ees 3 5 56 ANTENNA INSTALLATION DRAW ING iad aaa 3 9 430 MOUNTING RACK DIMENSION SNS aa ka an
2. 0 LY INFORMATION ONLY udio GARMIN PS Bendix King Bendix King dic GMA 340 Engineering KMA 24 KMA 24 PMA 6000 70 7 P4002 P1 Bottom P241 P241 500 OHM COM AUDIO 7 f 9 13 9 10 9 10 T 16 COM 1 COM 2 AUDIO 500 OHM COM AUDIO LO 19 t 3 10 14 GND LUG GND LUG GND LUG COM 1 COM 2 AUDIO COM MIC AUDIO HI 6 lt E 11 15 P H 3 E COM 1 COM 2 MIC AUDIO COM MIC KEY 4 12 30 R V R V C H COM 1 COM 2 MIC KEY COM MIC AUDIO LO 18 y 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 A INTERCOM MIC LO TRANSMIT INTERLOCK 14 lt SEE NOTE 3 COM TRANSFER SWITCH COM REMOTE TRANSFER 15 lt 3 430 ONLY 500 OHM VOR ILS AUDIO HI 16 17 19 12 13 12 13 P 13 NAV 1 NAV 2 AUDIO HI 500 OHM VOR ILS AUDIO LO 17 18 20 GND LUG GND LUG GND LUG NAV 1 NAV 2 AUDIO LO VLOC TRANSFER SWITCH VLOC REMOTE TRANSFER 28 lt NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED THE 420 430 IF THERE IS NO OTHER INTERCOM SYSTEM IN THE AIRCRAFT 2 CONNECTING TWO MICROPHONES TO MIC AUDIO HI LO OR INTERCOM MIC HI LO AT THE SAME TIME MAY RESULT 6 INTERCOM WIRING OPTION IN WEAK OR DISTORTED AUDIO MIC ISOLATION RELAYS ARE RECOMMENDED SO THAT ONLY ONE MIC IS ACTIVE AT A TIME MICROPHONE S
3. MAIN OBS ROTOR AAIN OBS C MAIN OBS STATOR D MAIN OBS STATOR E MAIN OBS STATOR F MAIN OBS STATOR C GPS ANNUNCIATE VLOC ANNUNCIATE P4001 21 22 23 24 17 27 28 29 50 18 52 51 55 54 GARMIN GARMIN GARMIN GARMIN 5 Bendix KingBendix King Bendix King Century Collins Collins Sperry Sperry GI 102 GI 102A 106 106A ST 180 206 Kl 525A KPI 552 B NSD360A331A 6P 331A 9G RD 550 RD 650 KPI 553 A B NSD1000 P1 P1 P1 P1 P1 P2061 P1 P2 P101 CD132 P1 1 2 P1 P2 P1 P2 Q a 11 11 11 11 27 1 17 29 4 F 4 J H 12 2 t2 12 43 N B H 18 28 3 E 3 2 9 9 9 9 26 E 7 J 33 26 1 A 1 10 10 10 10 42 S T K 34 27 2 B 2 x x 3 E 7 7 7 57 K 31 51 E Bf 8 8 8 8 38 F F 32 32 x gt E 37 P 39 E 38 S 36 Q m 15 15 14 K E JJ 27 33 5 C 5 2 14 14 28 M B HH 28 34 6 D 6 x x 15 15 36 H J FF 30 35 9 gt 16 16 55 J Ww 6 29 36 E 2 7 U 38 co w 8 1 1 1 1 22 X W 15 1 1 DD 6 J 1 2 2 2 2 24 7 N V 16 5 3 8 3 5 3 5 25 L 7 24 4 4 7 9 J H 5 5 5 5 39 Y 25 5 5 10 4
4. c oO 50 soe ax J UJ NOTES 1 DIMENSIONS INCH mm 2 UNIT WEIGHT 3 8 Ibs 1 72 kg 3 MOUNTING RACK HARDWARE amp CONNECTORS WEIGHT 1 1 lbs 0 5 4 CG LOCATION INCLUDES MOUNTING RACK HAR 0 kg RE amp CONNECTORS Figure 3 5 GPS 400 Mounting Rack Dimensions 400 SERIES INSTALLATION MANUAL Page 3 15 Page 3 16 blank P N 190 00140 02 Page Rev L 3 12 Mounting Rack Installation G 530 00053 0 Nd 4 PLCS 9 3 QQ 252 G Z EXTRA BOSS USE 211 60204 08 _ F REQ D N x e ES 2 N e AIR 24002 ES 22005 f 25 PIN P4001 jus 78 PIN AE a PM Ol P4006 44 PIN On k J 0 REAR VIEW OF CONNECTOR PLATE EXTRA BOSS USE 211 60204 08 F REQD E 400 SERIES INSTALLATION MANUAL P N 190 00140 02 D 1 NOTES AN DAR 1 PART OF 2 PART OF O 3 REMOVE A CONNECTO 4 FEED HAR BEFORE KEN 5 SNAP NUT 6 APPLY THR R 00245 00 212 00022 00 4 PLCS p FASTENERS 00351 VUS ESS WIRES SERTION LATE OVER 1 00676
5. S aaa Seats ada ict usu eai A tdt aa a ai a ndan Ba a uod 3 1 DATA BASE OP HONS poda kae Q el ee eae eae Su 3 4 3 3 MISCELLANEOUS OPTIONS uu au ug iiec espe teeth nt cade ae adde ct nasa 3 4 3 4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED 3 4 3 9 ANNTTENINA INS TATE aient dete ua ipee Qa e t i ber ace yka 3 4 3 0 CABLE INSTALLATION uuu u a agan n teneo odi eae ta 3 5 S RACK INSTALLATION ee uuu su Qan pet ct 3 6 3 8 400 SERIES UNIT INSERTION AND REMOVAL uuu uyu nennen u as a ense eras 3 7 3 9 COM ANTENNA INSTALLATION CHECK GNC 420 AND GNS 430 3 7 3 10 56 ANTENNA INSTALLATION DRAWING 3 9 SII MOUNTING RACK DIMENSIONS vse e 3 11 3 12 MOUNTING RACK INSTALLA TON decet ee e Een rh ened aS 3 17 3 13 RECOMMENDED PANEL CUTOUT DIMENSIONS aS 3 23 4 SYSTEM INTERCONNECTS TZ LPINCEDNCTION DIS not ue E E LE MI KU MEE 4 42 POWER LIGHTING ANDANIENNASu L u a nga ecg ese eei aN aa an 4 5 ane Por Susa 4 6 INDICATOR c 4 7 Z5 ANNUNCEXTORS
6. L 5 3 L A 1 L 1 322 5 nee L 4 2 L 4 18 L 4 47 L 5 4 L A52 ess L C 4 L ues l 323 L 4 3 L 4 19 L 4 49 L 5595 LI A 3 LI D 1 L L 3 4 L 4 4 L 4 20 L 4 51 L 5 6 L A 4 L I D 2 L Isles LI 3 5 L 4 5 L 4 21 L 4 53 L 5 7 LI A 5 L L 3 6 L 4 6 L 4 23 L 4 55 L 5 8 L A 6 L D 4 L A Pk wa L 4 7 L 4 25 L 4 57 L 5 9 LI B 1 LI E 1 L 4 L 3 8 L 4 8 L 4 27 L 4 59 L 5 10 L B 2 LED eases L PE L 3 9 L 4 9 L 4 29 L 4 61 L 5 11 E BO L 1 6 L 3 11 L 4 10 L 4 31 L 4 63 L 5 12 L B 4 E LI 3 13 L 4 11 L 4 33 L 4 65 L 5 13 LI B 5 l 1 8 LI 3 15 L
7. Title Any alteration of this certificate is punishable by a fine af not exceeding 1 000 ar imprisonment not exceeding 3 years oz both FAA Form Bll10 2i10 8H PAGE 1 ci 1 FAGES TTT thas cer lficate may be transferred sn accordance with FAR 21 47 Page B 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 nites States af America Department of Transportation Federal Abiation Administration Supplemental Type Certificate 8 00801 1 cani ead aerea ats Garmin International 1200 E 5151 St lathe KS 66062 therefor ws specified hereon mocis the aimcorttiness Awya chaypa ayat of Part 3 of he Civil Air Abepectatiorns rapa e Product Number A350 Piper Mou pana Dosanyption of Teo Design Change Installation of GARMIN GNC 420 in accordance with 1 GARMIN Dwg No 005 C0076 00 Revision B dated 6 17 99 Master Dwg List GNC 420 Installation in Piper PA32 and 2 FAA Approved Flight Manual Supplement AFMS for Piper PA32 GARMIN GNC 420 VHF Communication Transceiver GPS Receiver Revision A dated 7 6 99 or later FAA Approved Revisions of 1 or 2 Compatibility of this design change with previously approved modifications must be determined by the installer 1f the holder agrees to permit another person to use this certificate to alter the product the holder shail give the other person written evidence of that permission corti rtt and the supporting
8. and Class 303 Message Length Type Number 304G 7 MessageCharatersi 3 305G Message Characters 4 6 306G NAV WaypointAiportLatitude 307G 7 NAV Waypoint Airport Longitude sf ele Ground Speed EA m E m Magnetic Heading m Drift Angle m LateradScaleFacor Conic Arc Inbound Course N E E Conic Arc Inbound Course Left Right Hand Holding Pattern Azimuth 34 Left Right Hand Procedure Turn Azimuth 351G Distance To Destination Via Flight Plan 352G Estimated Time To Destination Via Flight Plan 371G 7 SpecficEqupmentiD fefefe 377 Equipment Hex ID Code tte ete The following labels are output on the VOR ILS ARINC 429 OUT port 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 400 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 lines in order to display traffic information on the 400 Series unit Page 4 12 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 6 2 Serial Data Electrical Characteristics 4 6 2 1 RS 232 PinName Connector Pin VO The RS 232 outputs conform to EIA Standard RS 232C with an output voltage swing of at least 5 V when dri
9. regreso of 3 Civil Air Coreg ieaie ial n AIO 2 Piper MM rrt PA M Posergulion ey aeger Change Installation of GARMIN ONS 430 Communication Transceiver f VOR ILS Receiver GPS Receiver in accordance with 1 Garmin Cerporation Master Drawing List Drawing No 005 00051 00 Revision dated September 22 1998 and 2 FAA Approved Airplane Flight Manual Supplement for Piper PA32 with GARMIN GNS 430 VHF Communication Transceiver VORALS Receiver GPS Receiver Document No 190 G0E 40 03 Revision A dated October 2 1998 or later FAA approved revision to 1 or 2 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 revved be ee ter ti fer ell PEREI ee eru deret rr edo or a lernvnudiarn dade t oremar ej e ral bg ya ys ey the ee ml rre lt orn rra eto of apnplrcatior November 26 1997 Rate reissued Bale of aasan ran October 02 1998 lt By ep the Ip tr pea p Signature C Dale Bleakney Program Manager Wichita Aircraft Certification Office
10. 5000 COM AUDIO LO P4002 5000 VOR ILS AUDIO HI P4006 5000 VOR ILS AUDIO LO P4006 5000 COM AUDIO and 5000 VOR ILS AUDIO each supply 100 mW into a 500 Q load These balanced outputs and the LO output must be connected 5000 COM AUDIO 15 the summation of the COM receiver audio COM sidetone audio and INTERCOM MIC audio 4 7 2 4 DISCRETE INPUTS PinNam Connector Pin VO TRANSMIT INTERLOCK P4002 COM REMOTE TRANSFER P4002 VLOC REMOTE TRANSFER P4006 These inputs are considered active if either the voltage to ground is 1 9 V or the resistance to ground is lt 375 Q These inputs are considered inactive if the voltage to ground is 11 33 V pc COM REMOTE TRANSFER and VLOC REMOTE TRANSFER are momentary inputs 4 7 3 COM VOR ILS Audio Configuration None 47 4 COM VOR ILS Audio Calibration and Checkout Refer to section 5 2 11 for the COM calibration 4 7 5 COM VOR ILS Audio Interconnect Refer to Figure 4 20 on page 4 59 for the audio panel interconnect 400 SERIES INSTALLATION MANUAL Page 4 15 P N 190 00140 02 Page Rev L 48 VOR ILS INDICATOR GNS 430 ONLY 4 8 1 VOR ILS Indicator Function NOTE Because the GNS 430 includes a CDI button that performs switching between GPS and VOR ILS on a remote indicator it is seldom necessary to use these outputs to drive an indicator It 15 only necessary when it is desired for a separate indicator to display VOR ILS deviation full time regardless of
11. In flight Loss of Cooling x Ae LLL Oversee 46 6 CtegoyA Equipment tested per DO 160C Par 7 3 1 and 7 3 2 Equipment tested without shock mounts to Categories B M amp N Explosion 90 Equipment identified as Category X no test required See report 005 00096 72 for details Fighting Salt Spray Equipment identified as Category X no test required Induced Signal Susceptibility Equipment tested to Category A Page A 4 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 A 4 Environmental Qualification Form GPS 400 NOMENCLATURE GPS 400 Airborne GPS System TYPE MODEL PART NO 010 00171 which includes 011 00504 00 TSO JTSO COMPLIANCE TSO C129a Class A 1 GPS MANUFACTURER S SPECIFICATION AND OR OTHER APPLICABLE SPECIFICATION 004 00044 00 MANUFACTURER GARMIN International Inc ADDRESS 1200 E 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 C LovTempmue 41 High Temperature 482 amp 433 Aude Decompression 42 TT 3 7 0 7 2 7 3 Temperature Variation L 6 Sek o Operational perDO 160C Pan 72 _ Gash Safety 73 fO Fauipmenrtested per DO 1600 Par 73 1 4732 TT Eq
12. Navigation and GPS Receiver equipment in certain installations GARMIN is issuing this letter to clarify the approval basis for accomplishing such mstallations without external switching or annunciation GARMIN obtained initial TSO and STC approval under 50 129 in conjunction with AC 20 138 for the GPS Receiver of the GNS 430 in a Piper Cherokee PA32 260 without external switching or annunciation The certification was accomplished under the jurisdiction 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 mode 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 detarmining 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 43D Follow on IFR airworthiness approval was accomplished under the STC process a
13. 91053XP 91802 Shadin F ADC 20 F ADC 2000 16 SHELI Electronics nternational FP 5L P400 42 RS Figure 4 11 RS 232 Serial Data Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 41 Page 4 42 blank Page Rev L 4 11 10 ARINC 429 EFIS Interconnect GPS ARINC 429 GPS ARINC 429 GPS ARINC 429 GPS ARI VOR ILS ARINC 429 OUT VOR ILS ARINC 429 NC 429 GPS GPS ARINC 429 VOR ILS VOR ILS I ARINC 428 ARINC 429 OUT ARINC 429 ARINC 429 ARINC 429 gt LRN LNAV 1 LRN LNAV 1 LRN LNAV 2 RN LNAV 2 RECEIVER ARINC 42 SMITTER SMITTE RECEIVER RECEIVER lt gt RECEIVER RECEIVER gt RECEIVER gt 4 TES ALL W TH A IF THE E 0 4 UN N O SDI CONFIGURATIONS LN GPS ARINC 429 PORT 4001 5 THE DEPICTED SELECTION OF THE A GARMIN GAD REFER TO THE GAD REFER TO MANUFACTURERS COMPLETE PINOUT EFIS 84 COURSE REQUIRED INTERCONNECT
14. Page 4 10 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 46 SERIAL DATA 4 6 1 Serial Data Function 4 6 1 1 RS 232 The 400 Series unit 15 capable of interfacing with other aviation instruments by transmitting RS 232 Type 1 often known as ARNAV format and Type 2 often known as Northstar format data on the GPS RS 232 OUT 1 port The data consists of the following refer to Appendix C for a detailed data format description 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 bearing desired track and cross track error to destination waypoint Destination waypoint identifier sequence in route position latitude and longitude and magnetic variation Magnetic variation and navigation and warning status Aviation RS 232 data may be transmitted with or without the current GPS altitude in feet Refer to section 222 2 The 400 Series unit can receive pressure altitude air data and fuel data from certain systems on the GPS RS 232 IN 1 port The 400 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 400 Series unit If two 400 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 Series
15. SN n N 3 1 79 f E 6 25 158 75 m I 6 32 160 5 O f 7 gt f tj Hl f f J I N ll a Y __ HI b Y L Y 125 3 18 1 762 44 75 51 130 o x 9 450 240 0 10 580 268 7 10 975 278 77 23 96 7 CSK INSIDE RACK 3 PLCS 0S y 332 8 42 SPECS PER SIDE i r C4 11 10 437 NOTES 1 DIMENSIONS INCH mm 2 UNIT WEIGHT 5 3 Ibs 2 5 bs 2 56 kg MOUNTING RACK HARDWARE amp CONNECTORS WEIGHT 4 CG LOCATION INCLUDES MOUNTING RAC SAU 1 4 lbs 0 64 kg amp CONNECTORS Figure 3 3 GNS 430 Mounting Rack Dimensions 400 SERIES INSTALLATION MANUAL Page 3 11 Page 3 12 blank P N 190 00140 02 Page Rev L O i O ey Ko Pu T b e H N 3 3 1 79 f N 6 250 158 75 6 320 160 5 1 E L E K H o U 2
16. 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 one byte result The ASCII coded decimal representation of that byte 15 given ranging from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 0 5 ARNAV EI FUEL FLOW SENTENCE The GARMIN GNC 400 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 e 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
17. 3 00029 00 20 PLCS gt 211 60204 12 4 2 PLCS Figure 3 8 GPS 400 Mounting Rack Installation Page 3 21 Page 3 22 blank Page Rev L 3 13 Recommended Panel Cutout Dimensions lt ND CNN wi il M N B lt 6 52 160 5 u s ar one 60 5 STACK CUTOUT RACK INSTALLED FROM FRONT OF AIRCRAFT PANEL ANTO NN 65 Vim LAIN 2 TERE Z fs OOo RADIO CUTOUT RACK INSTALLED FROM FRONT OF AIRCRAFT PANEL G 13 25 14971 75 19 1 6 32 160 5 a LAIN V 62 66 5 NOTES g M 2 62 66 5 2ADIO RAC NSTA 1 GAS Sic RADIO CUTOUT RACK INSTALLED DIMENSIONS INCH mm FROM BACK OF AIRCRAFT PANEL ONLY 2 IF THE FRONT LIP O MOUNTING RACK IS XU MUU CAU 25 MAXIMUM AIRCRAFT PANEL THICKNESS apa aso a 05 42 HE SURFACE OF THE AIRCRAFT PANEL THE 40 c 25 gt z 2 a A AKA IS 125 INCH 3 2 mm SERIES UNIT CONNECTORS MAY NOT FULLY ENGA LN x 68 17 3 75 19 Z 4 B a 8 157 0 Figure 3 9 400 Series Recommended Panel Cutout Dimensions 400 SERIES INSTALLATION MANUAL Page 3 23 Page 3 24 blank P N 190 00140 02 Page Rev L 4 SYSTEM INTERCONNECTS 41 PIN FUNCTION LIST 4 1 1 P4001 View of J4001 connector from back of unit 60 61 62 63 64 65
18. 4 39 155 232 SERIAL DATA INTERCONNECT Zuna ua ae 4 41 ARINC 9B BIS TINE RC a GAS 4 43 ARINC 429 SANDEL EHSI INTERCONN 1 400 SERIES UNIT 1 SANDEL SN33068 4 45 ARINC 429 SANDEL EHSI INTERCONNECT 2 GNS 430 1 SANDEL SN3308 4 47 ARINC 429 SANDEL EHSI INTERCONNECT 2 GNS 430 2 SANDEL 533308 4 49 ARINC 429 AIR DATA TRU AHRS INTERCONNECT Ecsta 4 5 ARINC 429 FLIGHT CONTROL INTERCONNECT R 4 53 TRAFFIC ADVISORY SYSTEM INTERCONNECT 4 55 WEATHER AND TERRAIN INTERCONNECT ONU 4 57 AUDIO PANELINLDERGONNIEGCL eese nsa REOR peer er Dum mayu aun ass 4 59 INDICATOR INTERCONNECT tenir etr ERE pmo ever e E 4 61 RMDOBLINTERCONIBET s tanaman edet tmd 4 63 KING SERIAL PANEL DME TUNING INTERCONNECT 4 65 KING SERIAL REMOTE DME TUNING INTERCONNECT 4 67 PARALLBL2 OF S DMB TUNING INTERCONNECT es 4 69 PARALLEL BCD SLIP CODE DME TUNING INTERCONNECT 4 7 Note Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A
19. LTN92 Indicator GI106 A__ NSD 1000 331A 6G RD650 L NI r X 9 C 21 21 7 TU KIA KA KIA 11114 j KPI327B _ KAB and Terrain 880 5 899 Skywatch HP __ WX Page E 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02
20. OF DME GNS OF DM A COMPLETE PIN PINOUTS BE CO FOR PARAI MODE FOR PROPER OPERATION W NFIGURED TRANSCEIVER O BE CO NFIGURED MODE FOR SCEIVER IUFACTURERS AND UNITS DOCUMENTATION FOR INFORMATION REFERENCE INTERCONNECT SHOWN FOR r mi CODE DE we 71 gt NN N N FN N N N N N MMON ATI A A E ECT SELECT SELECT Figure 4 25 Parallel 2 OF 5 DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 69 Page 4 70 blank Page Rev L 4 11 24 Parallel BCD Slip Code DME Tuning Interconnect NI N Bendix King Bendix King CNS 4 KN 61 KN 65 WINS C 4006 SEE P611 P651 PARALLEL DME 8MHZ 14 4 4 MO SER DME CHAN REQ PAR DME 4MHZ 20 gt 5 3 M1 SER DME RNAV MODE PAR DME 2MHZ 21 gt 2 6 M2 PARALLEL DME 1MHZ 55 1 7 M PARALLEL DME 800KHZ 57 gt 9 22 0 PARALLEL DME A400KHZ 59 8
21. Connector Pin VO MAIN LATERAL FLAG P4001 MAIN LATERAL FLAG 2 5V COMMON P4001 MAIN VERTICAL FLAG P4001 MAIN VERTICAL FLAG 2 5V COMMON P4001 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 mVpc When invalid information is present Flag IN VIEW the Flag output is 0 25 mVpc 400 SERIES INSTALLATION MANUAL Page 4 7 P N 190 00140 02 Page Rev L 4 4 2 4 Superflags PinName Connector Pin VO MAIN LATERAL SUPERFLAG P4001 MAIN VERTICAL SUPERFLAG P4001 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 Vpc when the flag is to be OUT OF VIEW The output voltage with respect to ground is less than 0 25 Vpc when the flag is to be IN VIEW 4 4 2 5 OBS PinNam Connector Pin VO MAIN OBS ROTOR C MAIN OBS ROTOR H GROUND MAIN OBS C and 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 3 Main Indicator Configuration Refer to section 5 2 10 for the main CDI OBS configuration 4 4 4 Main Indicator Calibration and Checkout Refer to section 5 2 10 for the mai
22. Z gt 7 22 j p m d E 4 22 210 10004 09 Po Pm 115 00080 00 48 32 SELF LOCKINC NUI AM NUT PLATE 4 PLCS gt N 3 v p NG k P P d ge e e 4 NG M CR 00 9 J 112 52 4 43 4 23 p NO CN F co l EN B L PG E s 60 15 2 N 2 o OQ WA rec D t 1 C LES D pi c 1 73 an deg i SF STUD 4 PLCS 0 50 12 70 SY N T BNC CONNECTOR BNC SIDE VIEW V EM V SIDE VIEW FRONT VIEW C mw s e PUE 0 813 20 64 2 PLCS WM C SS 1 m CO RE E aem m 5 20 188 4 78 4 PLCS 5 CEN PSS N RUN TOS FORWARD l 1 Z z PUE N Neo 4 4 a MOUNTING CUTOU Nul 1 2 600 66 04 REF MOUNTING CUTOUT Figure 3 2 GA 56 Antenna Installation Drawing 400 SERIES INSTALLATION MANUAL Page 3 9 Page 3 10 blank P N 190 00140 02 Page Rev L 3 11 Mounting Rack Dimensions i O PUN E N J Hu E N S L P f N D
23. 0245 liters indicates 5420 liters Checksum 15 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 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 6 SHADIN FUEL AIRDATA COMPUTER SENTENCE The GARMIN 400 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 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 ASCII 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 tem
24. 5 K1 PARALLEL DME 200KHZ 40 7 54 2 PARALLEL DME 100KHZ 42 gt 6 55 K3 PARALLEL DME 50KHZ 43 10 36 K50 DME COMMON 22 12 22 DME COMMON P4006 SEE NOTE 3 PARALLEL DME 8MHZ 1 gt 18 SER DME CHAN REQ PAR DME 4MHZ 20 14 SER DME RNAV MODE PAR DME 2MHZ 2 A PARALLEL DME 1MHZ 535 2 1 PARALLEL DME 800KHZ 57 800 PARALLEL DME 400KHZ 59 gt 400 PARALLEL DME 200KHZ 40 200 PARALLEL DME 100KHZ 42 100 PARALLEL DME SOKHZ 13 2 50 DME COMMON 22 DME COMMON NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 IHE GNS 450 MUST BE CONFIGURED TO OUTPUT SLIP CODE INC DATA FOR PROPER OPERATION IN THIS CONFIGURATION OO m 3 THE GNS 430 BE CONFIGURED TO OUTPUT BCD TUNING T OR PROPER OPERATION IN THIS CONFIGURATION E 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY Figure 4 26 Parallel BCD Slip Code DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL Page 4 71 Page 4 72 blank P N 190 00140 02 Page Rev L 5 POST INSTALLATION CONFIGURATION amp CHECKOUT PROCEDURE 5 1 CONFIGURATION MODE OPERATIONS With power applied to the aviation rack and the 400 Series unit turned off press and hold the ENT key and turn the unit on Release the ENT key when the display activates the un
25. Antenna must be on fap of Figure 2 1 GPS Antenna and Unit 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 GNC 420 and GNS 430 transmitters If a COM is found to be radiating the following can be done 1 Replace or clean the VHF COM rack connector to ensure good coax ground 2 Place grounding straps between the 400 Series unit VHF COM and a good ground 3 Shield the VHF COM wiring harness Page 2 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 2 2 8 COM VOR LOC and Glideslope Antenna Installation Instructions Install the COM VOR LOC and Glideslope antennas according to the manufacturer s recommendations Avoid running other wires and coaxial cables near the VOR LOC antenna cable 2 3 RACK CONSIDERATIONS Plan a location which gives the pilot complete and comfortable access to the entire keypad and which is plainly visible from the pilot s perspective Installation of remote switches and annunciators may not be required if the 400 Series unit is 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 Coax
26. UP 27 f MAIN DOWN 28 j MAIN VERTICAL FLAG 29 MAIN VERTICAL FLAG 30 L NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 SOME PINS OF THE SANDEL SN3308 ARE CONFIGURABLE 2 REFER TO SANDEL DOCUMENTATION AND CONFIGURATION P4006 SOFTWARE FOR PINOUT INFORMATION THE SD FIGU S LN LS OF T 1 VOR ILS ARINC 429 OUT A 24 E a V AY ANG ORALS PETI x 400 420 430 MUST BE SET TO 1 AND THE SDI OF THE 2 UNIT MUST BE SET TO 2 FOR PROPER OPERATION VOR ILS ARINC 429 OUT B 23 1 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION P4001 PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY GPS ARINC 429 IN 1 A 48 C GPS ARINC 429 IN 1 8 49 lt RELAXED GPS ARINC 429 OUT A 46 GPS ARINC 429 OUT 47 N C S GPS APPROACH 14 gt LOCALIZER ENGAGE MAIN LEF 21 179 m gt LEFT MAIN RIGHT 22 g H 27178 12 g gt RIGHT MAIN LATERAL FLAG 25 e LATERAL FLAG MAIN LATERAL FLAG 24 G Ma LATERAL FLAG MAIN UP 27 O a FUP MAIN DOWN 28 d J DOWN MAIN VERTICAL FLAG 29 N aA f VERTICAL FLAG MAIN VERTICAL FLAG 30 U H gi a VERTICAL FLAG ENERGIZED NAV SYSTEM 2 28 VDC 80EENS I PULS SND 199uuoo1 lul SHA I9pueS 627 ONIHV L LET C070t 100 061 N d NOILVTIVISNI SATUS 007 8OSENS lepues 0 SND Z 1 eu
27. 00 Y U IESIVE BACKING PLATE WITH HOLE THROUGH INTO CONNECTOR BACKSHELL 1 WITH CONNECTOR J PLA 2 330 00185 78 336 00021 00 AS REQD 2 211 63204 12 6 PLCS UT SUPPLIED 4 PLCS ASSEMBLY CONNECTOR KIT AND APPLY FOAM TO CENTERED ON AIR HOLE BACKSHELL AD LOCKING COMPOUND TO ALL THREADED 00184 25 AS REQD 4 PLCS 30 00228 20 2 56 00029 00 20 PLCS 2 211 60204 12 4 pirey 2 PLCS 330 00220 25 2 4 a 1 F c SE Figure 3 6 GNS 430 Mounting Rack Installation Page 3 17 Page 3 18 blank Page Rev L 2116020408 1 2 PLCS IET 00055 1 2JOU UUU ZN s 2 3 252 00062 00 NSW NEZ e SC EXTRA BOSS USE 211 60204 08 IF REQ D 7 COM d P4002 NK TA 25 PIN 400 M 78 PIN 17 REAR VIEW OF CONNECTOR EXTRA BOSS USE 211 60204 08 IF REQ D A PLATE lt 400 SERIES INSTALLATION MANUAL P N 190 00140 02 17125 00036 SHIELD GROUND 7 115 00243 00 NUT SUPPLIED TW WITH CONNECTOR 2 PLCS NOTES PART OF 011 00676 01 BACK PLATE ASSEMBLY 2 PART OF 011 00351 01 CONNECTOR K 3 REMOVE ADHESIVE BACKING AND APPLY FOAM TO CONNECTOR PLATE WITH HOLE CENTERED ON AIR FEED HARNESS WIRES THROUGH BACKSHELL BEFORE
28. 4 12 L 4 35 L 4 67 L 5 14 L B 6 Planas L 3 17 L 4 13 L 4 37 L 4 69 LI 3515s LI B 7 L Page A 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 This manual 15 written for software version 3 00 and 1s not suitable for earlier software versions Information in this document is subject to change without notice Visit the Garmin web site www garmin com for current updates and supplemental information concerning the operation of this and other Garmin products 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 Subchapter 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 with 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 Propos
29. 430 COM receiver sensitivity 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 4 7 2 COM VOR ILS Audio Electrical Characteristics 4 7 2 1 COM MIC KEY PinName Connector Pin 1O This input is considered active if either the voltage to ground 15 lt 1 9 V or the resistance to ground is lt 375 This input is considered inactive if the voltage to ground is 11 33 4 7 2 2 COM MIC AUDIO INTERCOM MIC AUDIO PinName Connector Pin VO X COM MIC AUDIO HI __ 4002 6 hn COM MIC AUDIO LO P4002 INTERCOM MIC HI P4002 INTERCOM MIC LO P4002 COM MIC AUDIO and INTERCOM MIC each have a 520 AC input impedance and supply the microphone with a 9 V bias through 620 Q COM MIC AUDIO is set in the factory for 275 mVgys to modulate the transmitter at 80 nominally The microphone gain adjustment is accessible through the top cover When 125 mVgygs 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 14 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 7 2 3 COM AUDIO VOR ILS AUDIO PinName Connector Pin VO
30. 5 5 INSTRUMENT PANEL SELF TEST Page 400 SERIES INSTALLATION MANUAL Page 5 5 P N 190 00140 02 Page Rev L 5 2 6 MAIN LIGHTING Page select the MAIN LIGHTING Page see Figure 5 6 This sud dus 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 Figure 5 6 MAIN LIGHTING Page light if the source is PHOTO and the settings on this configuration page This field has a range of 0 zero to 9999 SOURCE PHOTO Backlight level is determined by the ambient light level as measured by the photocell on the 400 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 400 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 range of 3 to 7 and 15 set to 4 at the factory MIN Minimum Sets the minimum brightness of the display The higher the number the bri
31. 9 V or the resistance to ground is lt 375 These inputs are considered inactive if the voltage to ground is 11 33 Some transponders and other altitude 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 1s required for each unit without internal diodes The 400 Series unit includes internal diodes for isolation of the encoder lines 4 3 8 Altimeter Configuration Refer to section 5 2 2 MAIN RS232 CONFIG page configuring various serial data equipment 4 3 4 Altimeter Checkout Refer to section 5 2 3 MAIN INPUTS 1 Page 4 3 5 Altimeter Interconnect Refer to Figure 4 2 4 3 4 4 and 4 11 for the altimeter interconnect using gray code or RS232 Page 4 6 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 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 CDT key on the bezel of the GNS 430 takes the place of remote NA V GPS switches and is used to toggle between display of GPS and VOR ILS navigation display on a remote indicator The Navigation source is
32. ALTITUDE B 11 ALTITUDE B2 12 ALTITUDE B4 10 ALTITUDE C 4 ALTITUDE C2 7 ALTITUDE C4 13 POWER GROUND eps n z 5 WU Altimeter or Blind Encoder FON 377 D4 ki T 7 ANTENNA A2 A4 OG B1 ANTENNA B2 B4 C1 OW 2 6 5 52 J L ANTENNA c4 COM TX CIRCUIT BREAKER COMMON 18 AWG AIRCRAFT POWER SEE NOTE 2 AND TABLE lt 5 28V 10A 14V 418 AWC GARMIN P1 A GMA 340 9 COM 1 AUDIO HI g 10 COM 1 AUDIO LO NQ a 11 COM 1 MIC AUDIO lt 12 COM 1 MIC KEY 10 COM 1 MIC AUDIO LO 17 1 AUDIO HI 5 H 18 NAV 1 AUDIO LO NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 AIRCRAFT POWER INPUT TO THE MAIN BOARD P4001 AND THE GNS 430 VOR ILS BOARD P4006 MAY BE 11 55 VDC THE AIRCRAFT POWER INPUT ON THE COM BOARD P4002 IS DEPENDENT ON THE PART NUMBER OF THE UNIT GNS 430 P N 011 00280 00 28 VOLTS DC GNS 430A P N 011 00836 00 GNS 430A P N 011 00856 10 GNS 430 P N 011 00280 10 GNS 430 P N 011 00280 30 14 28 VOLTS DC suomnel ejsu jeoid seues 009 TLL C070t 100 061 N d NOILVTIVISNI 007 uonejeijsu jeoid Oct OND S t eunBi4 97 7 2824 Z r 2824 Ady Sed GARMIN 420 MAIN LEFT MAIN RIGHT MAIN MAIN FROM MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN UP MAIN
33. ANNUNCIATE 8 gt OBS ANNUNCIATE gt Sur TERMINAL ANNUNCIATE gt GPS APR APPROACH ANNUNCIATE 5 c Ru 5 Bendix King Bendix King opilot t GPS INTEG syste 55 150 FC 200 INTEGRITY ANNUNCIATE 9 BE E E Computer KC 192 KC 295 P1 P1921 P2951 ILS GPS APPROACH 14 gt 52 LOCALIZER ENGAGE TIME MARK OUT 16 SEE NOTE 4 DEMO MODE SELECT 75 SEE NOTE 5 NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 6 P4001 PINS 75 1 AND 2 HAVE NO FUNCTION ON GPS 400 AND GNC 420 2 INITIAL CERTIFICATION OF THE 400 SERIES WAS ACCOMPLISHED WITHOUT USE OF ANY REMOTE SWITCHES OR ANNUNCIATORS 7 REFER TO MANUFACTURERS DOCUMENTATION FOR SINCE THE SAME SWITCHING AND ANNUNCIATION 15 AVAILABLE COMPLETE PINOUT AND INTERCONNECT INFORMATION ON THE FRONT PANEL OF THE GPS HOWEVER IF THE PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY UNIT 15 NOT INSTALLED IN THE NORMAL FIELD OF VIEW SOME OR ALL OF THE REMOTE SWITCHES AND ANNUNCIATORS MAY BE REQU UR CERTIFICATION AGENCY 5 AN EXTERNAL MOMENTARY VLOC GPS SWITCH ANNUNCIATOR OR ANNUNCIATOR WITH NO SWITCH MAY BE USED IN A GNS 450 INSTALLATION SWITCH SERVES THE SAME PURPOSE AS THE C BUTTON ON THE FRONT OF THE GNS 430 t TIME MARK OUT 4001 16 OUTPUTS A 1 MILLISECOND WIDE PULSE ONCE PER SECOND 5 DEMO MODE SELECT 4001 75 MAY BE GROUNDED TO START THE UNIT IN DEMO MODE DO NOT USE IN AN AIRCRAFT INSTALLATION Figure 4 10 Annun
34. ANTENNA COM ANTENNA VOR LOC ANTENNA GLIDESLOPE ANTENNA AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT GROUND AIRCRAFT GROUND 500 OHM COM AUDIO HI 500 OHM COM AUDIO LO COM MIC AUDIO HI COM MIC KEY COM MIC AUDIO LO 500 OHM VOR ILS AUDIO HI 500 OHM VOR ILS AUDIO LO AIRCRAFT GROUND 21 22 25 26 23 24 27 28 29 50 54 31 33 34 35 36 20 77 78 39 40 57 60 P4003 P4004 P4005 P4007 uonejeisu jeoid OS SND Z t pc r 2824 cc y 2824 Ady Sed 4002 11 12 21 22 4006 16 17 41 P4001 Navigation Indicator Q LEFT Jj J RIGHT TO J dj FROM C NAV FLAG J FLAG a UP H DOWN x Q Q GLIDESLOPE FLAG j t GLIDESLOPE FLAG A A OBS A H g y OBS C x x C 4 OBS D COS HI OBS E COS LO OBS F SIN HI H 21 OBS SIN LO GNS 430 CIRCUIT BREAKER BE Go NS lt 5 14 28 AIRCRAFT POWER 6 P3271 DARM LIGHTING BUS HI GARMIN GTX 327 LIGHTING BUS LO 20 RS 232 OUT 1 18 ALTITUDE D4 3 ALTITUDE A 5 ALTITUDE A2 6 ALTITUDE 4 9
35. DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT AIRCRAFT GROUND GROUND LIGHTING BUS HI LIGHTING BUS LO GPS RS 232 IN 1 ALTITUDE COMMON GPS ANTENNA COM ANTENNA AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT GROUND AIRCRAFT GROUND 500 OHM COM AUDIO HI S00 OHM COM AUDIO LO COM MIC AUDIO HI COM MIC KEY COM MIC AUDIO LO Navigation P4001 MEA Indicator 21 Q Q LEFT SEE NOTE 3 ae J RIGHT 25 TO 26 21 FROM 23 NAV FLAG 24 U 5 FLAG x 27 a UP 28 DOWN i SEE NOTE 2 29 GLIDESLOPE FLAG 30 E GLIDESLOPE FLAG x GNC 420 CIRCUIT BREAKER AES 19 A 14 28 VDC AIRCRAFT POWER 20 77 78 P3271 CAB A Z9 39 LIGHTING BUS HI GARMIN GTX 327 40 LIGHTING BUS LO 57 20 RS 232 OUT 1 18 ALTITUDE D4 3 ALTITUDE A 5 ALTITUDE 2 6 ALTITUDE A4 9 ALTITUDE gt 11 ALTITUDE B2 12 ALTITUDE BA 10 ALTITUDE 4 ALTITUDE C2 27 ALTITUDE 13 POWER GROUND P4003 PN 7 Iw GPS 1 ara Y ul Altimeter oi Blind Encoder P4004 B 2 lt COM A LT ANTENNA 2 A4 B B2 B4 C C2 C4 COM TX CIRCUIT P4002 BREAKER COMMON 18 AWG 7 11 AIRCR
36. INSERTION INTO CONNECTOR SNAP NUTPLATE OVER BACKSHELL APPLY THREAD LOCKING COMPOUND FASTENERS 3536 00021 00 AS REQD J 0 CY D 17212 00022 M 2 2 PLCS FN 2 530 00184 25 536 00022 00 AS REQD 336 00023 00 4 PLCS x 2 330 00185 78 IOLE TO ALL THREADED 2 N 330 00228 20 NI 556 00029 00 20 PLCS DN 211 60204 12 2 2 PLCS ___ 530 00220 25 DQ NGA _ 125 00046 00 2 8 Figure 3 7 GNC 420 Mounting Rack Installation Page 3 19 Page 3 20 blank Page Rev L NOT USED EXTRA BOSS 211 60204 08 IF REQD 1 330 00053 01 1 A25 ann SHIELD GROUND REAR VIEW OF CONNECTOR 400 SERIES INSTALLATION MANUAL P N 190 00140 02 EXTRA BOSS USE 211 60204 08 IF REQ D gt 27 DOOSO gt PART OF 011 006 AE PART OF 011 00551 03 52 2 NG 2 211 63204 12 2 RN 1 NUT SUPPLIED Ni RENE WITH CONNECTOR 76 03 BACK PLATE ASSEMBLY CONNECTOR KIT REMOVE ADHESIVE BACKING AND APPLY FOAM CONNECTOR PLATE WITH HOLE CENTERED ON AIR FEED HARNESS WIRES THROUGH BACKSHELL SERTION INTO CONNECTOR 6 APPLY THR BEFORE SNAP NUTPLATE OVER BACKSHELL EAD LOCKING COMPOUND TO ALL FASTENERS 00185 78 IREADED 00228 20 2
37. ITS POWER SUPPLY VOLTAGE ENTATION FOR PROPER CONNECTION ADD TWO 10K OHM 1 4 WATT RESISTORS ONE BETWEEN P4001 PINS 55 AND 34 AND ONE BETWEEN P4001 PINS 35 AND 36 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY Bendix King 209A P4001 P209A1 MAIN LEFT 21 E As 20 MAIN RIGHT 29 3 E 21 MAIN TO 25 4 Es 45 MAIN FROM 26 gt 42 IN LATERAL FLAG 23 oss 48 IN LATERAL FLAG 24 H gt 3 MAIN UP 27 4 27 AIN DOWN 28 go 26 RTICAL FLAG 29 Q gt 23 VERTICAL FLA 30 22 GPS ANNUNCIATE 2 gt SEE NOTE 2 APPROACH ANNUNCIATE 5 9 MAIN OBS ROTOR H 32 ames 50 MAIN OBS ROTOR C 31 Jg 2 x x MAIN OBS STATOR D 33 lt 15 10K OHM OBS STATOR E 34 AN MAIN OBS STATOR F 35 P lt V 14 10K OHM MAIN OBS STATOR G 36 KENAN SEE NOTE 3 P4006 VOR LOC COMPOSITE OUT 8 O gt 6 ILS ENERGIZE 29 gt 10 GLIDESLOPE UP 32 D 29 GLIDESLOPE DOWN FLAG 51 Ly go 28 GLIDESLOPE FLAG 30 N gt 25 g gt 24 tor LNAV LATERAL LEFT IN LNAV LATERAL RIGHT IN ATERAL FLAG IN ATERAL FLAG IN CAL UP IN CAL DOWN IN 4 CAL FLAG IN VERTICAL FLAG IN ELAY ENGAGE FCS LOC ENGAGE OBS RETURN OBS EXCITATION IN LNAV OBS COS OUT y V
38. Interconnect AIRCRAFT POWER 1 AIRCRAFT POWER 1 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 P4001 19 20 72 GNS 430 CIRCUIT BREAKER 430 GNC 420 CIRCUIT BREAKER 420 GPS CIRCUIT BREAKER 400 A 15 77 78 P4002 430 O 11 NLY 18 12 21 22 P4006 430 O 44 41 COM IX CIRCUIT BREAKER AWG 5 28 10A 14 V 18 AWG NLY NAV FLAG CIRCUIT BREAKER 8 A CN P4003 Lo P4004 430 O C GPS L ANTENNA P4005 430 NLY X 4007 430 NLY ey VLOC L_JANTENNA c G S N L ANTENNA 69 1 COMM L ANTENNA AIRCRAFT POWER SEE NOTES 2 AND 3 AIRCRAFT POWER SEE NOTE 7 LIGHTING BUS HI SEE NOTE 4 LIGHTING BUS LO AIRCRAFT POWER SEE TABLES AND NOTES 2 3 AND 5 AIRCRAFT POWER SEE NOTES 2 3 AND 6 NOTES ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 1 2 IT IS RECOMMENDED THAT ALL 400 SERIES UNIT POWER BE CONNECTED TO THE SAME POWER BUSS HOWEVER ALTERNATE POWER INPUT IS REQUIRED SEE NOTE 7 A
39. Mooney M20J incorporating dual GNS 430 receivers Approval was granted on the Mooney installation without the requirement for external switching or annuncialian under ihe same guidance aforementioned Inslallations 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 Cherokee PA32 250 approval reference STC SAOO0705WI dated October 2 1998 For tha Mooney M20J dual GNS 430 installation reference STC SAQO735WI dated January 19 1999 Also see the attached Wichita ACO latter affirming approval of the GNS 430 system without external switching or annunciation and guidance te consider when installing GNS 430 systems ta avoid external switching and annunciatian Sincerely Bill Stene Avionics Product Manager 400 SERIES INSTALLATION MANUAL Page B 5 P N 190 00140 02 Page Rev L 11 5 Department Small Airplane Directorate of Transportation Wichita Aircraft Certification Office Federal Aviation 1801 Airport Road Room 100 Administration Wichita Kansas 67209 January 25 1999 Mr Phil Straub GARMIN International 1200 E 1 51st 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 navigat
40. NOT ALLOW SKYWATCH DATA TO BE SPLAYED O HE MAP PAGE IDENTIFIES SPECIFIC RS 252 PORTS CONFIGURATION RIES UNITS WITH MAIN SOFTWARE VERSION 2 19 OR EARLIER HESE SPECIFIC PORTS MAIN SOFTWARE VERSION 2 20 SUCH THAT ANY SERIAL CAN SELECTED ON ANY OF THE FOUR RS 232 PORTS MANUFACTURERS DOCUMENTATION FOR TERCONNECT INFORMATION OUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY 12euuoaJo9ju W JS S AJOSIAPY 2211 9L LL t 4 11 17 Weather and Terrain Interconnect N T P4001 SOF OR HIGHER EE GPS RS 232 OUT 4 54 i gt 8 RS 232 RX NOTES E I 1 WIS N 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED P S 55 TERN 2 IN ORDER FOR WX 500 DATA TO BE DISPLAYED ON TH y 47 400 SERIES UNIT S MAP PAGE THE 400 SERIES UNIT MUST HAVE DIGITAL HEADING SOURCE OR THE WX 500 MUST HAVE A SYNCHRO OR CLEAR SERIAL HEADING SOURCE STEPPER HEADING SOURCE WILL NOT ALLOW SWITCH 500 DATA TO BE DISPLAYED ON THE MAP PAGE 6 EXTERNAL CLEAR 3 THIS DRAWING IDENTIFIES SPECIFIC RS 232 PORTS CONFIGURATIO OF 400 SERIES UNITS WITH MAIN SOFTWARE VERSION 2 19 OR EARLIER REQ
41. OF REVISIONS Revision Revision Description Insertion Date 6 19 98 19 98 Initial Release Release ios meis E E 11 11 98 Add 18 AWG pin positioner and insertion extraction 10008 tools Add King Serial DME tuning interface _ os description Lr e enema ee OBI RS 232 Fuel Air Data Inputs 6 25 99 Reflect changes to configuration pages Misc corrections 11243 10 13 99 Add interface to BF Goodrich Stormscope and Skywatch 11871 and Ryan TCAD NL 4 27 00 Update installation accessory kits 13205 i 9 1 00 Add unit versions with 14 28 volt transmitter Update 14026 configuration pages 2 22 01 Update configuration pages 15207 5 22 02 Add gray unit and 16 watt versions Update 18149 configuration pages 12 13 02 Add Fault Detection and Exclusion 19779 1 LIST OF EFFECTIVE PAGES Page Rev Page Rev Page Rev Page Rev Page Rev Page Rev Page Rev Page Rev Susan 2 22 cite L 3 19 L 4 14 4 39 L 4 71 L 5 16 L B L lcu 2 3 ees E321 ns L 4 15 L 4 41 L 5 1 L 5 17 IP EQ m L L 2 4 L 3 23 L 4 16 4 43 SEA sas L 5 18 ro u L L 3 1 L 4 1 L 4 17 L 4 45
42. OR LARGER UNLESS OTHERWISE NOTED Collins Bendix King EFIS 84 EFS 40 50 DPU 84 SG 465 P4001 1 P4652A P4652B 48 E 47 SEE NOTE SEE NOTE 4 49 lt 20 gt 46 Q 42 67 47 H 38 53 T 2 22 64 P4006 D 26 63 430 ONLY 24 m 1 1 25 16 25 29 29 gt D gt 38 25 X Collins Bendix King EFIS 84 EFS 40 50 DPU 84 SG 465 P4001 P1 4652 P4652B 48 o _ 47 SEE NOTE SEE NOTE 4 49 SG 20 142 67 138 53 fy L C vi 46 122 64 47 Nor i Iw 126 65 x B P4006 16 430 ONLY 29 24 a N 125 38 23 129 25 xX TRANSM TRANSM AV AND VOR ILS OF THE 1 20 430 MUST BE SET TO 1 AND THE SD BE SET TO 2 FOR PROPER OPERATION PORT P4001 48 AND 49 IS ALREADY USED FOR ANOTHER PURPOSE THE GPS ARINC 429 AND 51 MAY BE CONNECTED DOCUMENTATION FOR NTERFACE DOES VIA THE EFIS CONTROL PANEL FOR GPS SELECTED INSTALLATION MANUAL SUPPORT INFORMATION m 2 LRN LNAV 1 RECEIVER LRN LNAV 1 RECEIVER LRN LNAV 2 RECEIVER LRN LNAV 2 RECEIVER RECEIVER A RECEIVER B U m Figure 4 12 ARINC 429 EFIS Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 43 Page 4 44 blank Page Rev L 4 11 11 ARINC 429 Sandel EHSI Interconnect 1 400 Series Unit 1 Sandel SN3308 VN 4 X r adio 24 gt 9 5 Z2
43. SEPARATE POWER BUS SHOULD BE USED THE FOLLOWING TABLE SHOWS WHICH 400 SERIES UNIT FUNCTIONS DEPEND ON WHICH POWER INPUTS i ALL 400 SERIES UNIT FUNCTIONS 4001 DEPEND ON THIS POWER INPUT P4002 COM TRANSMITTER P4006 NAV SUPERFLAG GLIDESLOPE SUPERFLAG THE AIRCRAFT POWER INPUT ON TH INPUTS IF AN AIRCRAFT POWER INPUT TO THE MAIN BOARD P4001 AND THE GNS 430 VOR ILS BOARD P4006 MAY BE 11 33 VDC E COM BOARD P4002 IS DEPENDENT ON THE PART NUMBER OF THE UNIT GNS 430 P N 011 00280 00 28 VOLTS DC GNS 430A P N 011 00856 00 GNS 430A P N 011 00856 10 GNC 420 P N 011 00506 00 GNC 420A P N 011 00837 00 GNC 420A P N 011 00837 10 Pd C 420 P N 011 00506 10 GNC 420 P N 011 00506 30 GNS 430 011 00280 10 GNS 450 P N 011 00280 50 14 28 VOLTS DC THE 400 SERIES UNIT SHOULD BE CONF GURED FOR THE CORRECT LIGHTING BUS VOLTAGE 28 VDC 14 VDC 5 VDC OR 5 VAC POST INSTALLATION IS CONFIGURED CAN BE SET TO AUTOMATICALLY LIGHTING CONDITIONS USING ITS PHOTOCELL A MANUAL LIGHTING CONTROL OPTION IS ALSO AVAILABLE REFER TO THE POST INSTALLATION CONFIGURATION PROCEDURE HRINK TUBING ON P4006 44 TERMINATIO INCORRECTLY IN ADDITION LIGHTING AXIMUM ALLOWABLE WIRE GAUGE 22 AWG FOR TERMINATION SOC CONNECTOR KIT L S COMPE 8 AWG WIRE USE S ET CONTACT 536 00025 00
44. SUPPLIED WITH PROTECT EXPOSED CONDUCTOR ON SPECIAL CONTACTS WITH 3 8 1 cm LENGTH OF ALSO SUPPLIED WIT NTO P4002 PINS IS CONNECTOR KIT NO POWER CONNECTION IF THESE FLAG OUTPUTS ARE NOT PECIAL 18 AWG NO DAMAGE WILL OCCUR IF THE UNIT SATE FOR AMBIENT THE AIRCRAFT POWER INPUT 4006 44 PROVIDES POWER FOR THE VOR LOC SUPERFLAG 4006 4006 538 OUTPUTS 5 AND GLIDESLOPE SUPERFLAG IS REQUIRED USED OPTIONAL ALTERNATE POWER APPLIES ONLY TO PART NUMBERS 011 00280 50 010 00856 10 GNS 430 A 011 00506 50 011 00837 10 GNC 420 A AND 011 00504 10 GPS 400 Figure 4 5 Power Lighting and Antennas Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 29 Page 4 30 blank Page Rev L 4 11 4 Altimeter Interconnect L A RX AAN f m V VA ATAF L ncoaincg A ere e P4001 D4 0 1 D4 gt A 2 2 31 2 N 5 65 x 9 P 9 32 64 lt 10 D 10 BA 65 lt 1 11 C1 A E C2 62 lt 15 15 GZ Figure 4 6 Altimeter Interconnect 400 SERIES INSTALLATION MANUAL Page 4 31 Page 4 32 blank P N 190 00140 02 Page Rev L 4 11 5 Main Indicator Interconnect MAIN LEFT MAIN RIGH MAIN MAIN FROM MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN LATERAL SUPERFLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG MAIN VERTICAL SUPERFLAG
45. Shall meet TSO C34 Broad band 50 Q horizontally polarized with coaxial cable or low loss splitter used with the VOR LOC antenna Headphones GNC 420 and GNS 430 Only 500 Q nominal impedance Microphone GNC 420 and GNS 430 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 9 Also refer to 190 00094 00 GA 56 Antenna Installation Instructions 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 Theantenna installation must provide adequate support for the antenna considering a maximum drag load of 5 Ibs 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 Seal the 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 construction grade RTV sealant or sealants containing acetic acid These sealants
46. Verify that the GPS NA V flag is out of view Select 121 150 MHz on the 400 Series COM transceiver 2 3 4 Transmit for a period of 20 seconds 5 Verify that the GPS flag does not come into view 6 Repeat steps 4 and 5 for the following frequencies e 121 175 MHz 121 200 MHz 131 250 MHz 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 400 SERIES INSTALLATION MANUAL Page 5 17 P N 190 00140 02 Page Rev L 5 3 7 COM Check 420 and GNS 430 Only A flight test is recommended after the installation is complete to ensure satisfactory performance To check the communications transceiver maintain an appropriate altitude and contact a ground station facility at a range of at least 50 nautical miles Contact a close ground station Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical noise which would increase the squelch threshold 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 430 Only Select a VOR channel within a 40 nautical
47. and GNC 420A except where specifically noted 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 111 Page Rev L LIST OF FIGURES CONTINUED FIGURE 5 1 MAIN ARINC 429 CONFIG PAGE FIGURE 5 2 MAIN RS232 CONFIG FIGURE 5 3 MAIN INPUTS 1 PAGE ettet FIGURE 5 4 MAIN INPUTS 2 PAGE tette tetti FIGURE 5 5 INSTRUMENT PANEL SELF TEST PAGE 2 ee FIGURE 5 6 MAIN LIGHTING FIGURE 5 7 MAIN LIGHTING PAGE DISPLAY LIGHTING FROM LIGHTING BUS FIGURE 5 8 DISPLAY PAGE AUX GROUP FIGURE 5 9 DATE TIME SETUP PAGE tette FIGURE 5 10 MAIN DISCRETE INPUTS FIGURE 5 11 MAIN DISCRETE OUTPUTS FIGURE 5 12 MAIN CDI OBS CONFIG FIGURE 5 13 COM SETUP PAGE GNC 420 AND GNS 430 ONLY FIGURE 5 14 VOR DISCRETE INPUTS GNS 430 FIGURE 5 15 VOR LOC GS CDI PAGE GNS 430 ONLY t FIGURE 5 16 VOR LOC GS ARINC 429 CONFIG PAGE GNS 430 ONLY FIGURE 5 17 STORMSCOPE CONFIG PAGE tne FIGURE 5 18 STORMSCOPE TEST FIGURE 5 19 STORMSCOPE DOWNLOAD DATA FIGURE 5 20 TRAFFIC PAGE SKYWATCH ertet FIGURE 5 21 TRAFFIC PAGE TCAD FIGURE 5 22 RYAN TCAD CONFIG PAGE FIGURE 5 23 GAD 42 CONFIG FIGURE 5 224 DATA EINK PAGE iie bes i od be iue Note Throughout this document references made to GNS 430 and GNC 420 shall equally apply to
48. annunciator output may be required to be active for some installations VLOC The GNS 430 CDI button 1s in the VLOC state and the VLOC ANNUNCIATE output is active If it is desired to disable the GNS 430 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 430 Only Always GPS The MAIN King Serial OBI outputs are always GPS This is useful if it is desired to switch a Bendix King KI 229 or KNI 582 RMI pointer independently from the GNS 430 CDI button Track CDI The MAIN King Serial OBI outputs are GPS or VOR and switchable by the GNS 430 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 430 CDI outputs V FLAG STATE Declutter The vertical deviation bar is parked in the full scale up position when GPS or VOR navigation 15 selected for output The exception is when the CDI is in VLOC mode and an ILS frequency 15 tuned in which case the vertical deviation bar parks in the centered position The vertical deviation bar parks in the centered position whenever it is flagged 400 SERIES INSTALLATION MANUAL Page 5 9 P N 190 00140 02 Page Rev L 5 2 11 COM SETUP
49. 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 COM ANTENNA LOCATION The GNC 420 or GNS 430 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 400 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 15 recommended 223 VOR LOC ANTENNA LOCATION The GNS 430 VOR LOC antenna should be well removed from all projections engines and propellers It should have a clear line of sight if possible The antenna must be mounted along the centerline of the aircraft minimizing the lateral offset 2 2 4 GLIDESLOPE ANTENNA LOCATION The GNS 430 Glideslope antenna should be well removed from all projections engines and propellers It should have a clear line of sight 1f possible 2 2 5
50. data chich is the basis for approval hall remain in esi until ml Peele of apptroatior November 10 1998 Labs pocis of visecance July 06 1999 Gate ene reves oa p of the brine x 2 WA Tina L Miller Program Manager Wichita Aircraft Certification Office Tiley Any alteration of this certificate 1 punishable by a fine of noL exceeding 51 020 imprisonment nat exceeding 3 years or boih FAA Fork 110 2 10 PAGE 1 of 2 PAGES This certificate may be transferred in accordance with FAN 21 29 400 SERIES INSTALLATION MANUAL Page B 3 P N 190 00140 02 Page Rev L dirriteh States of America Department of Transportation Federal Abiation Administration Supplemental Type Certificate pm SAQ00800WI 2 aprendo P Garmin International 1200 E 51st St Olathe KS 66062 tharefer as jpocifeed Karoon meols the aimworthiness of Bint 3 ofthe Civil Air ngarat Product gps Nambani A350 bake Piper eost PA32 Dasenjalion of Susa Change Installation of GARMIN GPS 400 in accordance with 1 GARMIN Dwg No 005 0084 40 Revision B dated 6 17 99 Master Dwg List GPS 400 Installation in Piper PA32 and 2 FAA Approved Flight Manual Supplement AFMS for Piper PA32 GARMIN GPS 400 Receiver Revision A dated 7 6 99 or later FAA Approved Revisions of 1 or 2 Compatibility of this design change with
51. eo ele gee NG a aaa gana a 3 11 CONC 420 MOUNTING RACK DIMENSIONS saa anaa aaa aa aia aga bag a ga paka eo ences 3 13 GPS 400 MOUNTING RACK DIMENSION aaa a teen Bag ted aa aa a a aaa aa A 3 15 ONS 490 MOUNTING RACK INSTALLA TION ses ua deseo cbe ot aa a aaa Sus aa ua dots 3 17 GNC 420 MOUNTING RACK INSTALLATION eon oet gana a roe reete hao 3 19 GPS 400 MOUNTING RACK INSTALLATION iu ua tod po Sae a aa A aaa an aee aa aa aaa ana 3 21 400 SERIES RECOMMENDED PANEL CUTOUT DIMENSIONS 3 23 400 SERIES SYSTEM INTERFACE DIAGRAM sesane e We a aa E 4 2 INS TALI LION sunman ott aga CRS EE 4 23 GNC 420 TX PICAL INSEAELA TION e eot ctor HOS aa atapa a a Ba ag 4 25 GPS 400 LY PIGAT INSTALLATION asas oit au I a nayana MER He 4 27 POWER LIGHTING AND ANTENNAS INTERCONNECT 4 29 ALTINIBETER INIBBSQONNEGT tha Qa tete 4 31 MAIN INDICATOR INTERCONN EG T ni gak ME hayama 4 33 IST 209 A MPAIN CEINDICAETOR INTERCONJINEG TI eeu she anay 4 35 208 MAIN INDICATOR INTERCONNECT bayan aaa baaanyak qas bas 4 37 ANNUNGIATORS SWITCHES INTERCONNBGCT epe ya na
52. gt DOR 43949 I a AS 4 4 C 4 TN sr 429 2 2 5 45 9 lt 429 1 X B 9 3 46 n 1 M im A7 5 4 28 KB ES T L pA Y 4 21 EF Z 4 J ES m 9 zx 7 24 F 5 5 27 5 28 E y S 29 gt ra gt I 2 Figure 4 13 ARINC 429 Sandel EHSI Interconnect 1 400 Series Unit 1 Sandel 533308 400 SERIES INSTALLATION MANUAL Page 4 45 Page 4 46 blank P N 190 00140 02 Page Rev L C070t 100 061 N d TVONVW NOILVTIVISNI SATUS 007 8OSENS lepues OS SND Z 1 euuooJeiu ISH3 5 627 ONIHV vL p e1n614 gr r oSeq Lp p 9894 Ady Sed VOR ILS 1 Sande RELAXED SN3308 T P3 M gt NOTE 2 NAV 1 2 RELAY SENSE VOR ILS ARINC 429 OUT A 24 _ gt 9 429 2 VOR ILS ARINC 429 OUT 23 27 429 2 RX B ENERGIZED VOR ILS 2 28 VDC gt 5 2 SWITCHING RELAY 21 GPS 2 SWITCHING RELAY P4001 GPS ARINC 429 IN 1 A 48 lt e 11 429 1 GPS ARINC 429 IN 1 B 49 e H 29 429 1 TX B GPS ARINC 429 OUT A 46 C a 10 429 1 RX A GPS ARINC 429 OUT 47 t j gt 28 429 1 RX B gt 26 429 3 RX A 7 429 3 RX B 5 5 APPROACH 14 gt NOTE 2 CDI SOURCE CONTROL MAIN LEF 2 gt NOTE 2 RCVR 1 2 MAIN RIGHT 22 MAIN LATERAL FLAG 23 MAIN LATERAL FLAG 24 i MAIN
53. sp gt lt gt 12345T lt gt 12ul lt CR gt Where RMS ASCII characters lt sp gt space 0x20 lt gt sign indicator Ox2b or Ox2d 12345 altitude in feet T ASCII character lt gt sign indicator 12 sensor temperature ul checksum of bytes 1 through 14 in hex ASCII 1 e FA CR carriage return 0 0 Note Checksum is calculated by adding each byte in the message 1 through 14 0 3 ICARUS ALTITUDE SENTENCE The GARMIN 400 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 lt sp gt space 20 hex 12345 altitude in feet lt CR gt CARRIAGE RETURN 0D HEX 400 SERIES INSTALLATION MANUAL Page D 1 P N 190 00140 02 Page Rev L 0 4 SHADIN FUEL FLOW SENTENCE The GARMIN 400 Series units shall be capable of receiving the following 55 byte message from the Shadin Fuel Flow Indicator 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 1 e ASCII coded decimal format 0x30 0x35 0x34 0x33 0x2e 0x32 sp space 0x20 0100 0 fuel flow rate total formatted as for total fuel remaining 0040 0 fuel flow rate engine one or asterisks
54. 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 430 front panel make the selections below and verify the interfaces as appropriate Figure 5 15 VOR LOC GS CDI Page The LAT VERT and SELECTED COURSE configurations only apply to installations where a CDI HSI 15 connected to the VOR LOC GLIDESLOPE pins on connector P4006 CDI LAT VERT FLAG 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 TO FR Verify That FROM The FROM flag is in view The TO FROM flag is hidden The TO flag is in view 400 SERIES INSTALLATION MANUAL Page 5 11 P N 190 00140 02 Page Rev L SELECTED COURSE Select 150 on the CDI HSI that is connected to the 400 Series VOR LOC GS OBS inputs The SELECTED COURSE field should indicate near to 150 and a Calibrate to 150 field appears Selecting this field calibrates the 400 Series to match the input source Verify OBS operation by checking that the course displayed on the 400 Series 15 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 tu
55. unit to the other The 400 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 400 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 1s a list of the configurations and the labels output for each one 1 ARINC 429 2 GAMA 429 3 GAMA 429 Graphics 4 GAMA 429 Graphics w Int Label ParameterName 122934 001 Distance to Go BCD 002 TimetoGo BCD 012 Ground Speed BCD j j 074G DataRecodHeader of 075G ActveWptFrom ToData felele 10 SelectedCourse1 100G Selected e fo 113G Message Checksum 114 Desired Track True fe fe fe 115 Waypoint Bearing True e ej 116 Cross Track Distance 116G 7 Cross Track Distance 121 Horizontal Command to Autopilot e 125 Greenwich MeanTime BCD sf 1470 Magnetic Variation 1 1 1 400 SERIES INSTALLATION MANUAL Page 4 11 P N 190 00140 02 Page Rev L Label ParameterName 1 2 34 251 DistancetGo J 251G _ DistancetoGo felele 252 TimetoGo sd e 260 114 26016 X GPSDisreteWod 275G _ LRN Status Word 300G Station Declination
56. 0 GNS 430A 011 00506 30 GNC 420 011 00837 10 GNC 420A and 011 00504 10 GPS 400 For applications requiring secondary or alternate power bus input Page 4 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 1 2 P4002 GNC 420 and GNS 430 Only View of J4002 connector from back of unit 1 2 3 4 5 6 7 8 9 10 11 12 13 o o o eee 14 15 16 17 18 19 20 21 22 23 24 25 eooo0000000009 Pin Name 7 o 1 RESERVED 1 2 RESERVED 1 3 RESERVED 6 COMMICAUDIOH ln 8 RESERVED o 9 RESERVED e 10 RESERVED j j 13 RESERVED P c 16 20 RESERVED U o 21 AIRCRAFT GROUND 22 AIRCRAFT GROUND j 23 RESERVED 1 24 RESERVED 25 RESERVED 400 SERIES INSTALLATION MANUAL Page 4 3 P N 190 00140 02 Page Rev L 41 3 P4006 GNS 430 Only View of J4006 connector from back of unit 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 o 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 44 43 42 41 40 39 38 37 36 35 34 33 32 31 CC Pin Pin Name 6 VOR LOC RIGHT VOR LOC COMMON OU 7 RESERVED 8 VOR LOC COMPOSITE OUT Out 9 VOROBSROTORC Out 34 RESERVED 41 AIRCRAFT GROUND Page 4 4 400 SE
57. 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 Page Rev L 400 SERIES INSTALLATION MANUAL P N 190 00140 02 INSTALLATION PROCEDURE 3 1 UNIT AND ACCESSORIES The 400 Series units are available under the following part numbers 3 1 1 GNS 430 A P N P N 430A 1 VOLTAGE XMIT PWR 010 00139 01 011 00280 00 Y BLACK 28 1 010 00139 10 011 00280 10 BLACK 14or28 Vdc 10W B B Z lt 010 00286 01 011 00836 00 010 00286 10 011 00836 10 010 00286 11 011 00836 10 1 The following accessories are included with the GNS 430 A for those indicated with a Y above 10 N 101 MOUNTING RACK 115 00243 00 CONNECTOR KIT 01 1 00351 00 BACK PLATE ASSEMBLY 011 00676 00 GNS 430 PRODUCT INFO KIT K00 00055 00 2 Denotes alternate secondary power input available review installation drawing 400 SERIES INSTALLATION MANUAL Page 3 1 P N 190 00140 02 Page Rev L 3 1 2 GNC 420 P N P N 420A 1 VOLTAGE XMIT PWR 010 00173 01 011 00506 00 Y BLACK 28 1 OW 010 00173 10 011 00506 10 N N 14 or 28 Vdc 010 00173 11 011 00506 10 2 lt 00173 14 or 28 2 010 00287 01 011 00837 00 GRAY 010 00287 11 011 00837 10 GRAY 28 Vdc 2 1 The following accessori
58. 2 COMFIG 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 23 GAD 42 CONFIG Page Page 5 14 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 5 2 24 MONITORING THE DATA LINK The Data Link is monitored on the Data Link Page There are four main page groups in the 400 Series software version 2 25 or higher NAV WPT AUX and NRST see the 400 Series unit Pilot s Guide for detailed information on the unit s Page Groups The Data Link Page Figure 5 24 appears in the sequence of AUX Pages To select the Data Link Page rotate the large right knob until a page from the AUX group is displayed To select the Data Link Page rotate the small right knob until the Data Link Page 15 displayed Select Data Link Status Figure 5 24 For complete installation and configuration information refer to the GDL 49 installation manual GARMIN P N 190 00231 00 Figure 5 24 DATA LINK Page 400 SERIES INSTALLATION MANUAL Page 5 15 P N 190 00140 02 Page Rev L 5 3 ADDITIONAL GROUND TESTS 5 3 1 Connector Engagement Test Turn on the 400 Series unit and turn on the avionics master switch if applicable Place the 400 Series unit in the rack and engage the pawl mechanism 3 Turn the Allen screw of the locking pawl slowly clockwise until the 400 Series unit just comes on A handle ma
59. 29 OUT B 47 is 7 429 3 RX B gt NOTE 2 CDI SOURCE CONTROL 4 NOTE 2 RCVR 1 2 NAV SYSTEM 1 RELAXED A N C q i O 9 ILS GPS APPROACH 14 gt LOCALIZER ENGAGE MAIN LEFT 21 as LEFT MAIN RIGHT 22 J H gt RIGHT MAIN LATERAL FLAG 23 E gd LATERAL FLAG MAIN LATERAL FLAG 24 j 7 M 4 LATERAL FLAG MAIN 0 27 lt UP MAIN DOWN 28 H H DOWN MAIN VERTICAL FLAG 29 gt VERTICAL FLAG MAIN VERTICAL FLAG 30 B a g VERTICAL FLAG ENERGIZED NAV SYSTEM 2 28 VDC NOTES ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 SOME PINS OF THE SANDEL SN3308 ARE CONFIGURABLE REFER TO SANDEL DOCUMENTATION AND CONFIGURATION SOFTWARE FOR PINOUT INFORMATION 3 THE SDI CONFIGURATIONS LNAV AND VOR ILS OF THE 1 400 420 430 MUST BE SET TO 1 AND THE SDI OF THE 42 UNIT MUST BE SET TO 2 FOR PROPER OPERATION 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY 80 NS lepues SND 199uuoo1 lul ISH3 lepues 627 9NIHV EL LET 4 11 14 ARINC 429 Air Data IRU AHRS Interconnect 48 49 N Shadin B amp D j amp D VO onnn nnn JU 27999 ka UUU 2600 2601 NIN S CONN J2 DB 15 J GN Bendix King KAU 461 3endix King 3end
60. 4 4 4 40 T B Y 26 6 6 BB 11 LK 6 6 6 6 41 X 25 7 7 eb 12 E gt N C 17 E SEE NOTE 2 gt N C 18 E NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 P4001 2 GPS ANNUNCIATE AND P4001 1 ANNUNCIATE DO NOT APPLY TO GPS 400 NOR GNC 420 3 LOWER CASE PIN DESIGNATORS ARE SHOWN AS UNDERLINED UPPER CASE LETTERS 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY Indicator LEFT RIGHT TO FROM FLAG NAV FLAG NAV SUPERFLAG NAV SUPERFLAG LO UP DOW 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 ANNUNCIATOR Figure 4 7 Main Indicator Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 33 Page 4 34 blank Page Rev L 4 11 6 209A Main Indicator Interconnect NOTES 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 PROPER CONNECTION OF THE RELAY ENGAGE INPUT OF REFER TO KI 209A DOCU 3 CONNECT THE GNS 430 TO A KI 209A INDICATOR HE KI 209A IS DEPENDENT ON
61. 400 SERIES INSTALLATION MANUAL GPS 400 420 A and amp NS 420 Ay GNC and GNS are trademarks of Garmin Ltd or its subsidiaries and may not be used without the express permission of Garmin B gt MENU CLR ENT DEFAULT NAV GNS 430 Shown uhi s GARMIN Garmin International Inc 1200 E 151 Street Olathe KS 66062 USA 190 00140 02 Revision L December 2002 Copyright 1998 2002 Garmin Ltd or its subsidiaries 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
62. 66 67 68 69 70 71 72 73 74 75 76 77 T8 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 1 11 12 13 14 15 16 17 18 19 20 Pin PinName 110 6 MESSAGEANNUNCIATE 8 AUTOANNUNCIATE 9 INTEGRITYANNUNCIATE 11 12 13 ILS GPS APPROACH JT 14 ILS GPS APPROACH AIRCRAFT POWER 2 TIME MARK OUT MAIN FROM 2 5V COMMON MAIN DOWN 2 5V COMMON MAIN VERTICAL FLAG MAIN OBS STATOR 2 5V COMMON OBS O MAIN VERTICAL FLAG 2 5V COMMON Applies only to part numbers 011 00280 30 GNS 430 011 00836 10 GNS 430A 011 00506 30 GNC 420 011 00837 10 GNC 420A and 011 00504 10 GPS 400 For applications requiring secondary or alternate power bus input 400 SERIES INSTALLATION MANUAL Page 4 1 P N 190 00140 02 Page Rev L Connector P4001 continued _ Pin PinName VO 52 RESERVED 58 RESERVED 60 ALTITUDE COMMON GROUND 66 ALTITUDE B gt y y Ohn 68 ALTITUDE A2 y y Ohn 69 ALTITUDEAI tn 74 RESERVED _ 76 RESERVED 12 77 AIRCRAFT GROUND 78 AIRCRAFT GROUND n n n ut ut ut ut ut ut n n n n ut n ut n ut n ut n n n n n n n n n n n n Applies only to part numbers 011 00280 30 GNS 430 011 00836 1
63. 80 10 30 10 mA 13 75 Vc not transmitting and GNC 420 011 00506 10 6 0 A Q 13 75 V transmitting Superflag Power Requirements 500 mA max per superflag output 27 5 Vac 1 0 A max 27 5 V on P4001 Main Superflags 1 0 A max 27 5 V on P4006 VOR LOC G S Superflags Software 7 RTCADO 178B level C Environmental Testing RTCA DO 160C For more details see Environmental Qualification Forms 1 3 3 GPS Specifications Regulatory Compliance TSO C129a 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 Dynamics 400 SERIES INSTALLATION MANUAL Page 1 3 P N 190 00140 02 Page Rev L 1 3 4 COM Transceiver Specifications GNC 420 and GNS 430 Only Regulatory Compliance TSO C37d Class 4 amp 6 3 amp 5 for A models TSO C38d Class C amp E JTSO 2C37e JTSO 2C38e RTCA DO 186a ICAO Annex 10 Volume III Part Il Voice Communications Systems Par 2 3 3 Audio Output 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 1596 at al
64. AFT POWER SEE NOTE 4 AND TABLE 5A 28 V 10A 14 V gt 48 AWG GARMIN Ira Pi GMA 340 7 Jj 9 COM 1 AUDIO 19 c 10 COM 1 AUDIO LO 6 1 11 COM 1 MIC AUDIO 4 12 COM 1 MIC KEY 18 10 COM 1 MIC AUDIO LO NOTES 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 RECISION APPROACH OPERATIONS e F OBS CONNECTIONS ARE NOT MADE TO THE GNC 420 THEN LL OBS COURSE SELECTIONS WILL NEED TO BE MADE USING gt TO THE APPROPRIATE MAIN INDICATOR INTERCONNECT DRAWING 4 AIRCRAFT POWER INPUT TO THE MAIN BOARD P4001 MAY BE 11 55 THE AIRCRAFT POWER INPUT ON THE COM BOARD P4002 IS DEPENDENT ON THE PART NUMBER OF THE UNIT GNC 420 P N 011 00506 00 28 VOLTS DC GNC 420A P N 011 00837 00 GNC 420A P N 011 00837 10 GNC 420 P N 011 00506 10 GNC 420 P N 011 00506 50 14 28 VOLTS DC THE GNC 420 KNOBS IF AN OBS INTERFACE IS DESIRED REFER C070t 100 061 N d NOILVTIVISNI 007 MAIN LEFT MAIN RIGHT MAIN TO MAIN FROM MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG AIRCRAFT POWER AIRCRAFT POWER AIRCRAFT GROUND AIRCRAFT GROUND LIGHTING BUS HI LIGHTING B
65. AGRAM AND SELECT TRACK CDI FOR THE OBI SOURCE FIELD OF THE MAIN CDI OBS CONFIG PAGE 5 IF IT IS DESIRED 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 CDI OBS CONFIG PAGE 4 REFER TO MANUFACTURERS DOCUMENTA COMPLETE PINOUT AND INTERCONNECT IN PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY ON FOR Figure 4 22 RMI OBI Interconnect 400 SERIES INSTALLATION MANUAL Page 4 63 Page 4 64 blank P N 190 00140 02 Page Rev L 4 11 21 King Serial Panel DME Tuning Interconnect NI Wal N 4 1g lt P 4 47 ME 19 e 5 5 JN 2 Y 2 4 4 lt TAA 4 JA S JME CLOCK 8 gt 4 OCK 2n A REOUFS SER DME C E 4MHZ 20 EQUES IA N C 2 JTPU SI CLOCK 18 J CHAN 4MHZ 22 SER 21 N C Figure 4 23 King Serial Panel DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL Page 4 65 Page 4 66 blank P N 190 00140 02 Page Rev L 4 11 22 King Serial Remote DME Tuning Interconnect ade p c DRE CISC 49 1 2 JM A OCK Z 2 LU CK TPA 47 e SER 0 lt S N C gt 55 55 10 B BIT
66. ATE 115 00080 00 SCREW 10 32 x 5 8 211 62212 14 ANTENNA GASKET 253 0001 1 00 2 Other accessories include the following amp WEATHER INTERFACES MANUAL SUPPLEMENT MANUAL SUPPLEMENT GNS 430 SAMPLE AIRPLANE FLIGHT 190 00140 04 MANUAL SUPPLEMENT NOTE A mounting rack is required for approved installations The following hardware 15 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 400 SERIES INSTALLATION MANUAL Page 3 3 P N 190 00140 02 Page Rev L 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 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 0006 7 00 3 4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED The following installation accessories are required but not provided COM Antenna GNC 420 and GNS 430 Only Shall meet TSO C37 and C38 Broad band 50 vertically polarized with coaxial cable VOR LOC Antenna GNS 430 Only Shall meet TSO 40 and C36 Broad band 50 Q horizontally polarized with coaxial cable Glideslope Antenna GNS 430 Only
67. C SUPERFLAG 15 SUPERFLAG Z 2 SUPERFLAG LO VOR LOC COMPOSITE OUT 8 Y Y 2 2 6 6 VOR LOC COMPOSITE ILS ENERGIZE 29 K K 4 4 10 10 ILS ENERGIZE GLIDESLOPE UP 32 E 13 K 3 29 UP GLIDESLOPE DOWN FLAG 31 14 M 6 28 DOW x GLIDESLOPE FLAG 30 2 15 H H 9 25 GLIDESLOPE FLAG H gt 16 J J 12 24 GLIDESLOPE FLAG GLIDESLOPE SUPERFLAG 38 GLIDESLOPE SUPERFLAG iit GLIDESLOPE SUPERFLAG LO VOR OBS ROTOR H 10 C 1 1 _ OBS A H VOR OBS ROTOR C 9 2 2 7 7 OBS C x VOR OBS STATOR D 13 lt 5 5 L L OBS D COS HI VOR OBS STATOR E G 11 5 5 P P B OBS E COS LO VOR OBS STATOR F 12 a 4 4 T T _ OBS F SIN HI 6 6 W W OBS G SIN LO NOTES ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 LOWER CASE PIN DESIGNATORS ARE SHOWN AS UNDERLINED UPPER CASE LETTERS THIS INTERCONNECT APPLIES ONLY WHEN IT IS DESIRED FOR A SEPARATE INDICATOR TO DISPLAY GNS 430 VOR ILS NFORMATION REGARDLESS OF THE CDI BUTTON STATUS CA 4 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY T Figure 4 21 VOR ILS Indicator Interco
68. 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 WO VOR LOC COMPOSITE OUT P4006 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 into a 10 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 1s less than 10 uA 4 8 3 VOR ILS Indicator Configuration Refer to section 5 2 13 for the VOR LOC GS configuration 4 8 4 VORIILS Indicator Calibration and Checkout Refer to section 5 2 13 for the VOR LOC GS checkout 4 8 5 VORIILS Indicator Interconnect Refer to Figure 4 21 on page 4 61 for the VOR ILS indicator interconnect 400 SERIES INSTALLATION MANUAL Page 4 17 P N 190 00140 02 Page Rev L 49 RMI OBI 4 9 1 RMI OBI Function The MAIN OBI output provides bearing information from the active waypoint for Bendix King Serial OBI devices based upon the 400 Series unit s GPS navigation For the GNS 430 the MAIN OBI output may be configured so that it sends VOR ILS bearing information when VLOC is selected by the GNS 430 CDI key The VOR OBI output provides bearing information from the active waypoint for Bendix King Serial OBI devices base
69. E AIRCRAFT POWER AH POWER amp GROUND DIO P CO JIC TRANSMIT INTERLOCK 1 MIC KEY 1 COM AUDIO 2 COM AUDIO COM REMOTE TRANSFER 1 GARMIN 4 SONNECTOR SZ vOR ILS AUDIO LAT DEVIATION amp FLAGS ro FRoM Z VERT DEVIATION amp FLAGS 2 gt SUPERFLAGS Z 6 2 VOR OBS AIRCRAFT POWER POWER amp GROUND voR LOC COMPOSITE gt LS ENERGIZE VOR OB SERIAL DME CLOCK DATA 22 DME REQUEST COMMON ZZ C 429 EFIS E HS 2 VOR ILS ARINC 429 IN VOR ILS ARINC 429 OUT PARALLEL DME TUNING 92 92ej191u Wa SAS seues OO L LEv REMOTE COM TRANSFER SWITCH DME COMMON VLOC REMOTE TRANSFER REMOTE VLOC TRANSFER SWITCI GA 56 GPS ANTENNA COM ANTENNA VOR LOCALIZER ANTENNA GLIDESLOPE ANTENNA LLY SLOANNOOUSALNI 31935 00 C070t 100 061 N d NOILVTIVISNI 007 GARMIN GNS 430 MAIN LEFT MAIN RIGHT MAIN TO MAIN FROM MAIN LATERAL FLAG MAIN LATERAL FLAG MAIN UP MAIN DOWN MAIN VERTICAL FLAG MAIN VERTICAL FLAG MAIN OBS ROTOR H 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
70. E ED 46B Receiver Audio Sensitivity At 103 5 dBm S N N shall not be less than 6 dB Course Deviation Sensitivity 103 5 dBm or less for 6096 of standard deflection The LOC Course Deviation Flag must be flagged in the absence of an HF signal When either the 90 or 150 Hz modulating signals is removed and the other is maintained at its normal 20 In the absence of both 90 and 150 Hz modulation 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 x 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 3 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 rec
71. 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 400 SERIES INSTALLATION MANUAL Page 2 1 P N 190 00140 02 Page Rev L 2 26 ANTENNA LIMITATIONS Garmin s GA 56 Antennas are recommended for installations where the airspeed of the aircraft 1s subsonic In such installations GA 56 Mod 1 or later must be used See the COM VOR LOC and Glideslope antenna specifications for their limitations 2 2 VHF COM INTERFERENCE OF GPS On many panel mounted installations VHF COM transceivers can radiate strong harmonics from the transceiver and its antenna The 400 Series COM does not interfere with its own GPS section However placement of the GA 56 GPS antenna relative to a COM transceiver and COM antenna including the GNC 420 or GNS 430 COM antenna is critical Use the following guidelines in addition to others in this document when locating the 400 Series unit and its antennas e GPS Antenna Locate as far as possible from all COM antennas and all COM transceivers including the 400 Series COM The GPS antenna is less susceptible to harmonic interference if a 1 57542 GHz notch filter 15 installed on the COM transceiver antenna output e Locate the 400 Series unit as far as possible from all COM antennas Antenna masked by vertical fin T fal or doma fin
72. From Glideslope Flag and Up Down The indicator s used in conjunction with the GNS 430 VOR ILS receivers shall be TSO d 400 SERIES INSTALLATION MANUAL Page 2 3 P N 190 00140 02 Page Rev L 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 0 15 thick 2 Electrical Characteristics LNA Supply voltage 4 5 0 5 Vpc LNA Supply Current 20 mA Maximum LNA Operating Frequency LNA Gain LNA Noise Figure LNA Output VSWR 50 LNA Input power at 1 dB Gain Compression 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 1575 42 2 00 MHz 20 dB Maximum 12dB Minimum 3 0 dB Maximum 2 1 Maximum 6 dB Minimum 40 MHz Maximum
73. N Cf ey NI a 9 450 240 0 a 0 580 268 7 m 10 975 278 77 2 156 100 CSK INSIDE RACK 3 PLCS PER SIDE 437 11 10 8 000 203 21 1 DIMENSIO UN WEIGHT INCH m m 4 5 bs 2 04 kg 5 MOUNTING RACK HARDWARE amp CONNECTORS 4 CG LOCATION INCLUDES amp CONNECTORS WEIGHT 1 3 Ibs 0 59 kg MOUNTING RACK HAR 400 SERIES INSTALLATION MANUAL Figure 3 4 GNC 420 Mounting Rack Dimensions P N 190 00140 02 Page 3 13 Page 3 14 blank Page Rev L O Ps Nub NS 3 2 81 ei Pr 5 6 250 158 75 n 6 320 160 5 L Pd 2 2 amp f MR 5 iv Nm NE 5 J Y 125 3 18 1762 44 75 4 8 122 9 450 240 0 _ 10 580 268 7 _ 10 975 278 77 2 156 93 96 CSK INSIDE RACK 3 PLCS PER SIDE 332 8 42 Je AE abend E l
74. NSTALLATION MANUAL Page Rev L P N 190 00140 02 Appendix C 400 Series RS 232 Aviation Data Format C 1 ELECTRICAL INTERFACE The output signals shall be compatible with RS 232C Data shall be generated at 9600 baud with a word length of 8 bits one stop bit and no parity C 2 GENERAL OUTPUT FORMAT The 400 Series RS 232 data shall have the following general format SIX ASCII start of text character 02 hex tls Type 1 output sentences see following paragraphs for description t2s One or more type 2 output sentences see following 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 dddd item data 1 to 10 printable ASCII characters CR ASCII carriage return character OD hex LF ASCII line feed character OA hex Each Type 1 sentence shall be output by the 400 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 400 Series unit automatic magnetic heading magnetic variation computed at last known position true heading magnetic variation of 00 09 or user defined magnetic heading magnetic variation as entered by user 400 SERIES INSTALLATION MANUAL Page C 1 P N 190 00140 02 Page Rev L The following table describe
75. NUAL P N 190 00140 02 Page v Page Rev L This page intentionally left blank Page vi 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 1 GENERAL DESCRIPTION 1 1 INTRODUCTION This manual describes the physical mechanical and electrical characteristics and the installation requirements for the 400 Series GPS 400 GNC 420 and GNS 430 Panel mounted units After installation of the 400 Series system FAA Form 337 must be completed by an appropriately certificated agency to return the aircraft to service 1 2 EQUIPMENT DESCRIPTION The 400 Series units are mark width 6 25 wide units and 2 66 high The display is a 128 by 240 pixel color LCD The units include two removable data cards one with a Jeppesen database and the second being an optional custom data card The GPS 400 15 a GPS receiver certifiable for en route terminal and non precision approach operations The GNC 420 A includes all the features of the GPS 400 and also includes an IFR certified airborne VHF communications transceiver The A model is a 28 Vdc unit with a 16 Watt COM transmitter The GNS 430 A includes all the features of the GNC 420 and also includes 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 400 Series product lens 15 coated with a spe
76. O 175B for Level C software as documented in GNC 400 Software Accomplishment Summary GPN 005 00077 15 Revision AL The FDE Prediction Program software has been developed 1 accordance with DO 178B for Level D software as documented Prediction Program Software Accomplishment Summary GPN 005 00162 04 Revisi n A A list of the technical data required by TSO C129a and the other T50s and the GARMIN documents s which satisfy each requirement for the GNC 400 series can be found in GNC 400 Traceability Matrix GPN 005 00077 62 Revision E A list of the technical data required by Notice 8110 60 and the GARMIN documents s which satisfy cach requirement for the GNC 400 series and the associated FDE Prediction Program is in the GNC 400 FDE Traceability Matrix GPN 005 00077 64 Revision A 400 SERIES INSTALLATION MANUAL Page B 7 P N 190 00140 02 Page Rev L Page 2 The GNC 400 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 Al TSO Authorization for the GNC 400 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 00 imary Means of Navigation for Oceanic Remote Operations for the followi
77. OR LOC COMPOSITE AV LOC ENGAGE IN AV VERIICAL UP IN AV VERTICAL DOWN IN AV VERTICAL FLAG IN AV VERTICAL FLAG IN Figure 4 8 209A Main Indicator Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 35 Page 4 36 blank Page Rev L 4 11 7 208A Main Indicator Interconnect P400 IN LEFT 21 Bendix King 208A P208A1 N LATE IN RIGHT 22 AK a M 4H TO 25 26 FLAG 23 2 24 R O I C ANNUNC T Z O UJ Un C 1 I gt e OBS ROTOR ROTO 07 v 1 gt O AJ VOR ILS 2t V AK gt V GP Cn UD m m Z mM No 5 H 32 H C 31 IE D 33 10K O A f E 34 lt NANAN F 35 10K 0 G 36 4727 5 1 2 208 5 206 5 ALL WIRES 24 A TION OF ANQ TO CONNECI ADD TWO 10K P4001 PINS 55 E 400 SERIES UNIT TO A 1 1 4 WATT RESISTORS FACTURERS DOC AND INTERCONNECT IG OR LARGER UNLESS OTHE
78. OULD BE 4 THE RYAN TCAD P GROUNDED TO TURN T TO TURN THIS UNI OT IN THE INSTA CONNECTED TOGET O TURN THIS UNI OT IN THE INSTA ROCESSOR SWITCH PIN HE PROCESSOR UNIT ON AND OPEN T OFF IF A RYAN TCAD LLATION A DEDICATED SW O TURN THE TCAD PROCESSOR UNIT ON A HER TO TURN THE PROCESSOR UNIT ON AND OPEN IF A SKYWATCH CONTROL DISPLAY UNIT IS LLATION A DEDICATED SW O TURN THE SKYWATCH PROCESSOR UNIT ON AND OFF TCH MAY BE REQUIRED 16 SHOULD DISPLAY UNIT IS TCH MAY BE REQUIRED D OFF 5 IF ANY OF THESE TRAFFIC SYSTEMS IS INSTALLED WITHOUT 400 SERIES UNIT 400 SERIES UNIT INDICATING THAT A TRAFF A CONTROL DISPLAY UNIT A PLACARD IS REQUIRED NEAR THE C ADVISORY SYSTEM IS NSTALLED AND ITS DATA MAY BE DISPLAYED ON THE 400 SERIES UNIT S MAP PAGE Ryan 9900B BX TCAD Processo RS 232 RX 2 RS 232 TX 2 RS 232 GROUND 2 REMOTE MUTE TRAFFIC ANNUNCIATE OUT SWITCH E HEADING SOURCE DOES NOT HAVE THIS LIMITATIO PINOUT AND HE SKY899 INSTALLATION MANUAL FOR RYAN TCAD TRAFFIC TO BE DISPLAYED ON THE THE 400 SERIES UNIT MUST HAVE i FOR SKYWATCH DATA TO BE DISPLAYED ON THE 400 SERIES UNIT S MAP PAGE THE 400 SERIES UNIT MUST HAVE HEADING SOURCE OR THE SKYWATCH MUST HAVE SYNCHRO OR SERIAL HEADING SOURCE STEPPER HEADING LL
79. Page 420 and GNS 430 Only Select the COM SETUP Page see Figure 5 13 These values are set at the factory and seldom require calibration FRE 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 Store Calibration used Figure 5 13 COM SETUP Page SPACING 25 0 kHz Selects traditional 25 kilohertz spacing 760 channel 8 33 kHz Selects 8 33 kilohertz channel spacing which 15 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 15 required to break squelch For GNS 430 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 1s 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 number the more signal 1s required to break squelch SIDE 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 t
80. RIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 2 POWER LIGHTING AND ANTENNAS 4 2 4 Power Lighting and Antennas Function The section covers the Power Input requirements Lighting Bus input and Antenna connections 4 2 2 Power Lighting and Antennas Electrical Characteristics 4 2 2 1 Aircraft Power _Pin Connector Pin 1O AIRCRAFT GROUND P4000 77 AIRCRAFT GROUND P4001 78 AIRCRAFT GROUND P400 21 AIRCRAFT GROUND P402 22 AIRCRAFT GROUND P4000 Jaj Optional alternate power applies only to part numbers 011 00280 30 GNS 430 011 00836 10 GNS 430 A 011 00506 30 GNC 430 011 00837 10 GNC 420 A and 011 00504 10 GPS 400 CAUTION To operate the GNC 420 P N 011 00506 00 or GNS 430 P N 011 00280 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 a circuit breaker on its output to supply power to P4002 11 and P4002 12 for the COM transmitter The other power input pins P4001 19 P4001 20 and P4006 44 accept 11 33 Vpc GNC 420 P N 011 00506 10 and GNS 430 P N 011 00280 10 accept 11 33 Vpc on all power inputs Refer to Figure 4 5 on page 4 29 A power connection on P4006 44 is only required if NAV SUPERFLAG and or G S SUPERFLAG is utilized The power inputs P4001 19 and P4001 20 provide power for all functions of the 400 Series unit
81. RIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 C 4 OUTPUT SENTENCE 2 The 400 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 ASCII characters lat waypoint latitude 3 binary bytes lon waypoint longitude 4 binary bytes mvar 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 400 Series unit shall have a Type 2 sentence output by the 400 Series unit approximately once every second If no route is being navigated by the 400 Series unit 1 e 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 400 SERIES INSTALLATION MANUAL Page C 3 P N 190 00140 02 Page Rev L The following table describes the Type 2 output sentence item designator id sequence number seq waypoint identifier wpt waypoint latitude lat waypoint longitude lon and magnetic variation at waypoint mvar fields Byte Format Description 76543210 ASCII character w 77 h
82. RWISE NOTED ETE PINOU THE RELAY ENGAGE DEPENDENT ON ITS POWER DOCUMENTATION FOR PROPER UNITS VOLTAGE CONNECT 208A INDICATOR ONE BETWEEN AND 34 AND ONE BETWE PINS 35 AND 56 AENTATION FOR FOR REF 20 21 DEV LEFT IN TERAL DEV RIGHT IN TO IN FROM IN LATERAL FLAG IN LATERAL FLAG IN cO 14 TION ONLY RETURN OBS EXC COS OUT O UJ 92 Figure 4 9 208A Main Indicator Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 37 Page 4 38 blank Page Rev L 4 11 8 Annunciators Switches Interconnect P4001 MESSAGE ANNUNCIATE 6 2 MSG WPT WAYPOINT ANNUNCIATE 3 gt Annunciator SOURCE SELECT 75 lt VLOC GPS VLOC ANNUNCIATE 1 z tch SEE NOTES 3 AND 6 GPS ANNUNCIATE 2 gt Annunciator OBS MODE SELECT 71 Q SEE NOTE 22 AUTO
83. SELECT 22 AR 22 48 48 a c 9 49 J Wi 4 x c 5 REQUESI f Lo N N if N j J Zz Ane 400 o N 19 O 6 9 BUS d S 49 8 L o e 2 A e SA Y 4 SER E HZ ZO 2 SER DME RN Figure 4 24 King Serial Remote DME Tuning Interconnect 400 SERIES INSTALLATION MANUAL Page 4 67 Page 4 68 blank P N 190 00140 02 Page Rev L 4 11 23 Parallel 2 OF 5 DME Tuning Interconnect SER DME CHAN SER DME RN PARALLEL N N N N N REQ PAR E MODE PAR E PARALLEL DME ARALLEL DME 800 ARALLEL DME 4 ARALLEL DME 2 ARALLEL D 1 PARALLE OR V MODEL MODEL NOTES 1 ALI 2 THE 3 THE DME 4 REFER GNS 430 DME CHANNELLING NOTE 2 Narco DME 890 NOTE 3j Narco IDME NOTE 476 3 V Cn e NO Q CN N Q CX N 54 55 56 P30 WN u Ce J CJ P301 51 12 0 11 N o M Ee gt UJ gI LARGER SE NOTED
84. SWLDCHDPBES agin i LER UE 4 9 DATA esit ARAS aaa Laka a asa Need u ua aa Na A 4 11 4 7 COM VOR ILS AUDIO GNC 420 AND GNS 430 ONLY Jai aasma naa a an Aa aa da a an aa Tag 4 14 4 5 V ORS INDICA TOR ON SASUONTLN asaba an uuu a a to 4 16 RMU OBL EOS uu teste CI MILAN MU C 4 18 ATO DIVE TINTING CNS V ONLY VAAN EASA EAE siib ana a dett 4 19 SERIES INTER ONNEC SE aso tha 4 2 5 POST INSTALLATION CONFIGURATION amp CHECKOUT PROCEDURE CONPIGURATIONMODEOPERATIONSQ u aa e tun Und 5 5 2 INSTALLATION CONFIGURATION PAGES tete bete Ee UN ome 5 5 9 AD DITIONAL GROUINID TES DS eue Rec eee Dini at ue eoa cue dai 5 16 Appendix A CERTIFICATION DOCUMENTS AJCONTINUED JAIBNVORTEINESS eb Maec bbs gc tu gto due 1 A 2 ENVIRONMENTAL QUALIFICATION FORM GNS 430 3 A 3 ENVIRONMENTAL QUALIFICATION FORM GNC 420 4 A 4 ENVIRONMENTAL QUALIFICATION FORM GPS 400 sess A 5 A 5 ENVIRONMENTAL QUALIFICATION FORM GA 56 00 000000100000000000000400000008 A 6 Appendix B S
85. TE INPUTS Page Verify That RMT CDI The box is filled in while a remote CDI source select switch is pressed RMT OBS The box is filled in while a remote OBS switch 1s pressed 400 SERIES INSTALLATION MANUAL Page 5 7 P N 190 00140 02 Page Rev L 5 2 9 MAIN DISCRETE OUTPUTS Page select the MAIN DISCRETE OUTPUTS Page see Figure 5 1 This page allows you to verify the operation of any external annunciators and switches that are present in the installation Figure 5 11 DISCRETE TOGGLE MAIN DISCRETE OUTPUTS Page Verify That APR The APR annunciator is active and inactive as selected on this page GPS The GPS source select annunciator is active and inactive as selected on this page MSG OBS VLOC The VLOC source select annunciator is active and inactive as selected on this page The WPT annunciator 15 active and inactive as selected on this page 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 5 2 10 MAIN CDI OBS CONFIG Page Select the MAIN CDI OBS CONFIG Page see Figure 5 12 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 400 Series unit front panel make the selections below and verify the interfaces as a
86. 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 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 5051 9DL U K Phone 913 397 8200 Phone 44 1794 519944 FAX 913 397 0836 FAX 44 1794 519222 Page 1 8 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 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 400 Series unit Any deviations from the installation instructions prescribed in this document shall be accomplished in accordance with the requirements set forth in FAA AC 43 13 2A and 14 CFR Part 43 Maintenance Preventive Maintenance Rebuilding and Alteration 2 2 ANTENNA CONSIDERATIONS Antenna installations on pressurized cabin aircraft require FAA approved installation desi
87. TION MANUAL Page Rev L P N 190 00140 02 5 2 3 MAIN INPUTS 1 Page HAIH IHPUTS 1 Select the MAIN INPUTS 1 Page see Figure 5 3 This page along with the MAIN INPUTS 2 Page allows you to monitor the data on ARINC 429 RS 232 and other electrical inputs This is used for verifying electrical interfaces during installation and troubleshooting Information that 1s not being received by the 400 Series unit is dashed out Figure 5 3 MAIN INPUTS 1 Page 5 2 4 MAIN INPUTS 2 Page Select the MAIN INPUTS 2 Page see Figure 5 4 This INPUTS 2 page is also used for verifying electrical interfaces during installation and troubleshooting Information that 1s not being received by the 400 Series unit 1s dashed out Right Engine Fuel Flow Figure 5 4 MAIN INPUTS 2 Page Total Fuel Flow T FOB Total Fuel on Board GPS SC GPS Selected Course GNS 430 Only GNS 430 Only JOYSTICK Latitude and longitude of a WPT Joystick waypoint sent by an EFIS or RADAR indicator 5 2 5 INSTRUMENT PANEL SELF TEST Page Select the INSTRUMENT PANEL SELF TEST Page see Figure 5 5 This page allows verification that the 400 Series unit is communicating properly with other instruments Compare on screen indications with the information depicted on connected instruments such as the CDI HSI RMI and or external annunciators It also displays fuel capacity amount on board and flow Set Full Fuel Figure
88. UIRES THESE SPECIFIC PORTS MAIN SOFTWARE VERSION 2 20 2 OR LATER DOES NOT HAVE THIS LIMITATION SUCH THAT ANY SERIAL FORMAT CAN BE SELECTED ON ANY OF THE FOUR RS 232 PORTS i 4 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 5 REFER TO MANUFACTURERS DOCUMENTATION FOR COMPLETE PINOUT AND INTERCONNECT INFORMATION Bendix King KGP PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE ONLY EP GA Enhancec 6 CONNECTION TO RS 232 PORT 2 OF THE 400 SERIES S UNIT IS SHOWN IF PORT 2 IS ALREADY IN USE ANY OTHER SOF OR HIGHER P1 AVAILABLE RS 232 PORT MAY BE USED AS WELL m SEE NOTES 3 AND 4 GPS RS 232 OUT 1 56 Q gt 6 GPS IN GDL 49 Data Link I x P4001 SEE NOTE 6 ARE 2 26 OR HIGHER P491 GPS RS 232 IN 2 59 za 7 RS 232 OUT 2 GPS RS 232 OUT 2 58 O O gt 6 RS 232 IN 2 18 SHIELD GROUND Figure 4 19 Weather and Terrain Interconnect 400 SERIES INSTALLATION MANUAL Page 4 57 Page 4 58 blank P N 190 00140 02 Page Rev L 4 11 18 Audio Panel Interconnect
89. US LO GPS RS 232 IN 1 ALTITUDE COMMON GPS ANTENNA Navigation uonejeijsu peoid L OOF SAD t r anliy WN 87 7 2824 Lc y 98eq Ady Sed ALL OBS COURSE SELECTIONS WILL NEED TO BE MADE USING THE GPS 400 KNOBS IF AN OBS INTERFACE IS DESIRED REFER TO THE APPROPRIATE MAIN INDICATOR INTERCONNECT DRAWING 081 Indicator 21 FLEFT SEE NOTE 3 22 2 FRIGHT 25 TO 26 I FROM 25 FLAG 24 Jj NAV FLAG 27 UP 28 DOWN i SEE NOTE 2 29 C GLIDESLOPE FLAG 30 GLIDESLOPE FLAG GPS CIRCUIT BREAKER 19 5 14 28 AIRCRAFT POWER 20 lt 77 4 40 LIGHTING BUS LO 57 RS 232 OUT 1 18 ALTITUDE D4 3 ALTITUDE A 5 ALTITUDE A2 6 ALTITUDE A4 9 ALTITUDE 11 ALTITUDE 2 12 ALTITUDE B4 ALTITUDE C ALTITUDE C2 M ALTITUDE C4 60 POWER GROUND P4003 re A A Altimeter o Blind Encoder D4 A A2 A4 B3 82 B4 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED C C2 2 THE GPS VERTICAL DEVIATION OUTPUTS WERE NOT OPERATIONAL C4 AT TIME OF PUBLICATION CONNECTION OF VERTICAL COMMON DEVIATION AND FLAGS IS PROVISIONAL FOR FUTURE GPS PRECISION APPROACH OPERATIONS 3 IF OBS CONNECTIONS ARE NOT MADE TO THE GPS 400 THEN 4 11 3 Power Lighting and Antennas
90. WITCH DPDT 3 RE TO MANUFACTURERS DOCUMENTATION FOR 5 CONNECT TRANSMIT INTERLOCK P4002 14 TO THE OTHER P4002 En ai Nah 2 2 21 POR TRANSCEIVER S MIC KEY TO MINIMIZE SQUELCH BREAKS ON SOM m COMPLETE PINOUT AND INTERCONNECT E 420 430 COM E i C JA PINOUTS OF OTHER UNITS SHOWN FOR REFERENCE 4 lt al a 4 THE 500 OHM AUDIO OUTPUTS ARE BALANCED OUTPUTS N C 9 AND THE LO OUTPUTS MUST BE CONNECTED IF THE AUDIO COM MIC AUDIO HI 6 55 A PANEL DOES NOT HAVE A LO INPUT IT SHOULD BE INTERCOM MIC HI 5 o COM MIC AUDIO LO 18 I INTERCOM 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 59 Page 4 60 blank Page Rev L 4 11 19 VOR ILS Indicator Interconnect GARMIN GARMIN Bendix King Bendix King Bendix King Bendix KingBendix KingBendix KingBendix KingBendix King GI 102 A GI 106 202 206 203 204 208 209 208A KI 209A P4006 P1 P1 P2021 P2061 P2031 P2041 P2081 P2091 P208A1 P209A1 VOR LOC LEFT 5 Q 11 11 N N LEFT VOR LOC RIGHT 6 2 2 J J RIGHT VOR LOC TO 1 2 9 9 E E TO VOR LOC FROM 2 10 10 S S E E FROM VOR LOC FLAG 3 2 7 7 N 3 NAV FLAG VOR LOC FLAG 4 8 8 F F 2 FLAG VOR LO
91. able and with a nominal 50 ohm resistive load at the antenna connector Page 1 4 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 1 3 5 VOR Specifications GNS 430 Only Regulatory Compliance TSO C40c JTSO 2C40c RTCA DO 196 EuroCAE ED 22B Receiver Audio Sensitivity At 103 5 dBm S N N shall not be less than 6 dB Course Deviation Sensitivity 103 5 dBm or less for 60 of standard deflection The VOR 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 Greater than 80 dB 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 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 400 SERIES INSTALLATION MANUAL Page 1 5 P N 190 00140 02 Page Rev L 1 3 6 LOC Specifications GNS 430 Only Regulatory Compliance TSO C36e JTSO C36e RTCA DO 195 CLASS A EuroCA
92. al deviation 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 42 EHSI Deviation Scaling Only if HSI CDI is driven by the 400 Series unit via serial data With the 400 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 400 Series unit s Default Navigation page Verify that the EHSI displays a similar half scale deviation 2 Repeat step 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 Series units in the aircraft For each 400 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 Series units 5 3 6 VHF COM Interference Check GNC 420 and GNS 430 Only Once the Signal Acquisition Test has been completed successfully perform the following steps 1 View the Satellite Status Page and verify that 7 to 8 satellites have been acquired
93. al to accomplish the 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 400 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 400 Series unit with GNS 430 Instructions for Continued Airworthiness GARMIN 400 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 400 Series unit Applicability Applies to aircraft altered by installation of the GARMIN 400 Series unit Definitions and Abbreviations None N A Precautions None N A Units of Measurement None N A Referenced Publications GARMIN 400 Series Installation Manual P N 190 00140 02 GARMIN 400 Series Maintenance Manual P N 190 00140 05 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 the applicable SAFMS refer to se
94. allation and 1s approved by the administrator For TSO Compliance see Appendix A 1 3 1 Physical Characteristics Bezel Height 2 66 in 67 mm Bezel Width 6 25 in 159 mm Rack Height Dimple to 2 69 in 68 mm dimple Rack Width 6 32in 160 mm Depth Behind Panel with 11 00 in 279 mm Connectors Measured from face of aircraft panel to rear of connector backshells 3 8 Ibs 1 7 kg rack and connectors 4 5 Ibs 2 0 kg rack and connectors 5 1 Ibs 2 3 kg GNS 430 Weight Installed with 6 5 Ibs 2 9 kg rack and connectors Page 1 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 1 3 2 General Specifications Operating Temperature Range 20 C to 55 C For more details see Environmental Qualification Form Input Voltage Range 22 to 33 V GNS 430 011 00280 00 and GNC 420 011 00506 00 Input Voltage Range 11 to 33 V GNS 430 011 00280 10 30 GNC 420 011 00506 10 30 GNC 420 A 011 00837 00 10 GPS 400 Main Connector 1 44 13 75 GNC 420 Connector GNS 430 Main Connector Power Requirements P4002 15 mA 27 5 V not transmitting COM Connector 3 0 A Q 27 5 V transmitting GNS 430 011 00280 00 GNS 430A 011 00836 00 10 and GNC 420 011 00506 00 GNC 420A 011 00837 00 10 Power Requirements P4002 15 mA 27 5 V not transmitting COM Connector 3 0 A Q 27 5 V transmitting _ or GNS 430 011 002
95. annunciated on the display above the CDI key The Navigation method 1s optionally annunciated externally by connecting to the VLOC ANNUNCIATE output P4001 1 and GPS ANNUNCIATE output P4001 2 GPS and VOR ILS navigation may be toggled externally when the CDI SOURCE SELECT input P4001 73 1s momentarily grounded See section 4 5 for more information on the external annunciators and switches An OBS resolver connection to the GPS 1s preferred but not required For GNS 430 an OBS resolver typically is connected to the MAIN OBS inputs for use with the GNS 430 VOR receiver 4 4 2 Main Indicator Electrical Characteristics 4 4 2 1 Deviation PinName Connector Pin VO MAIN RIGHT 2 5V COMMON P4001 MAIN UP P4001 MAIN DOWN 2 5V COMMON P4001 The deviation output is capable of driving up to three 1000 Q meter loads with 150 mV pc 10 for full scale deflection The drive circuit provides for more than full scale deflection with a maximum course deviation output voltage of 300 mVpc 10 4 4 2 2 TO FROM jPinName Connector Pin 10 MAIN TO P4001 MAIN FROM 2 5V COMMON P4001 The output is capable of driving up to three 200 Q meter loads When indicating TO MAIN TO is 190 40 mVpc with respect to MAIN FROM When indicating FROM MAIN is 190 40 mVpc with respect to MAIN FROM When invalid information is present Flag IN VIEW the TO FROM output is 0 10 mVpc 4 4 2 3 Flag PinName
96. aphics Joystick waypoint information from a RADAR graphics unit Sandel EHSI Selected course and heading information from the following EHSI system Sandel 50 3308 Page 5 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 DATA OUT Off No unit s connected to ARINC 429 output ARINC 429 Standard ARINC 429 output data non GAMA 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 of Collins EFIS systems may also be compatible with this format GAMA 429 Graphics ARINC 429 data as defined by the General Aviation Subset 276 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 2 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 GAMA General Aviation Subs
97. 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 If an 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 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 400 Series units are certified for IFR enroute terminal and non precision approaches The 400 Series initial certification was accomplished via STC s by Garmin in a Piper PA32 See Appendix B for copies of the STC s The 400 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 400 Series equipment as installed has been found to comply with the requirements for GPS primary means of navigation in oceanic and rem
98. cial anti reflective coating which 1s very sensitive to skin oils waxes and abrasive cleaners It is very important to clean the lens using an eyeglass lens cleaner which is specified as safe for anti reflective coatings one suitable product is Wal Mart Lens Cleaner and a clean lint free cloth CAUTION The use of cellular telephones while aircraft are airborne 1s prohibited by FCC rules Due to potential interference with onboard systems the use of cell phones while the aircraft 1s on the ground 15 subject to FAA regulations Part 91 21 FCC regulation 47 CFR Ch 1 Section 22 925 prohibits airborne operation of cellular telephones installed in or carried aboard aircraft Cellular telephones must not be operated while aircraft are off the ground When any aircraft leaves the ground all cellular telephones on board that aircraft must be turned off Cell phones that are on even in a monitoring state can disrupt GPS performance 400 SERIES INSTALLATION MANUAL Page 1 1 P N 190 00140 02 Page Rev L 1 3 TECHNICAL SPECIFICATIONS The conditions and tests required for TSO approval of the 400 Series are minimum performance standards It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable inst
99. ciators Switches Interconnect 400 SERIES INSTALLATION MANUAL Page 4 39 Page 4 40 blank P N 190 00140 02 Page Rev 4 11 9 RS 232 Serial Data Interconnect GTX 327 GARMIN GARMIN Eventide GPSMAP 195 GPS Ill Pilot Argus 3000 5000 7000 Goodrich Stormscope JP Shadin nstruments Miniflo L EDM 700 91204XT 38 D Digiflo L 91053XP Shadin F ADC 2000 Electronics F ADC 200 International FP 5LE P3271 SEE NOTE 4 P4001 GPS RS 232 OUT 1 56 GPS RS 232 IN 1 57 GPS RS 232 OUT 3 41 GPS RS 232 IN 3 42 5 DATA IN 16 1 GND 4 GARMIN Shadin Icarus GTX 327 8800T 9000T Instruments 92001 5000 20 7 2 15 15 SHEI NOTES O gt N 2 9 SHELI 2 JP Shadin Instruments Miniflo L EDM 700 91204 7 58 0 SHELL 2 SEE NOTE 2 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 IF TWO 5 252 LINES ON 4001 41 CONNECTED TO CROSSFILL FLIGHT O CROSSFILL FLIGHT PLANS IT IS 400 SERIES UNITS HAVE IDENTICAL MAY BE REQUIRED THAT THEY HAVE MAIN SOFTWARE 3 REFER TO MANUFACTURERS DOCUMENTA ETE PINOUT AND INTERCONNEC CO PINOUTS OF OTHER UNITS SHOWN 4 REFER TO THE GTX 327 TRANSPONDER MANUAL 190 0018 7 02 FOR COMPLET JR MORE 400 SERIES UNITS ARE REQUIRED DATABASE IDENTICAI INSTALLED 42 MAY BE CROSS AND USER WAYPOINTS THAT BOTH CYCLE DATES AND VERSIONS O INFORMATION REFERENCE ONLY NSTALLATION INFORMATION
100. ck 149 59 Selected Course 149 59 Distance to Go 10 0 nautical miles 4 minutes Active Waypoint GARMN Groundspeed 150 knots 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 5 3 3 Signal Acquisition Test Upon approval of the Data Base Page the Satellite Status Page is displayed If the unit is unable to acquire satellites relocate the aircraft away from obstructions which might be interfering with 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 400 Series unit and Is functioning properly see the Pilot s Guide for more information on the direct to function Page 5 16 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 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 vertic
101. cs when the lighting bus control 1s below the level specified the PHOTO TRANS field Both fields have a range of 0 zero to 99 and are set to 50 at the factory Figure 5 7 MAIN LIGHTING Page Display Lighting from Lighting Bus CONTRAST If contrast isn t acceptable place unit in Normal Mode On the AUX menu SETUP page 2 highlight DISPLAY and press ENTER The DISPLAY page is shown see Figure 5 8 Confirm that CONTRAST MODE is Auto Highlight CONTRAST LEVEL and adjust to best viewable color Press ENTER to confirm change Figure 5 8 DISPLAY Page AUX Group Note Leave CONTRAST MODE Auto 5 2 7 DATE TIME SETUP Page Select the DATE TIME SETUP Page see Figure 5 9 DATE SETUP Very infrequently it may be desirable to set the date and time of the 400 Series unit to aid in acquiring a GPS position Configuration mode is the only means by which the date and time for the 400 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 Caution Changing to the wrong UTC date time will delay satellite acquisition Figure 5 9 DATE TIME SETUP Page 5 2 8 MAIN DISCRETE INPUTS Select the MAIN DISCRETE INPUTS Page see Figure 5 10 if the encoding altimeter input 1s used Verify that the DECODED ALTITUDE field indicates the correct altitude EXTERNAL SWITCH STATE Figure 5 10 C E MAIN DISCRE
102. ction 3 1 of this manual GARMIN 400 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 400 Series unit with interface to external altitude encoder and CDI include other equipment systems as appropriate Refer to section 1 2 and sections 4 x 1 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 400 Series unit Pilot s Guide 4 Servicing Information N A 5 Maintenance Instructions Maintenance of the 400 Series unit 15 on condition only Periodic maintenance 15 not required Refer to the 400 Series Maintenance Manual 400 SERIES INSTALLATION MANUAL Page 1 P N 190 00140 02 Page Rev L Troubleshooting Information Refer to the 400 Series Maintenance Manual 7 Removal and Replacement Information Refer to section 3 8 of this manual If the unit is removed and reinstalled a functional check of the equipment should be conducted in accordance with section 5 3 of this manual 8 Diagrams Refer to sections 3 and 4 of this manual 9 Special Inspection Requirements N A 10 Application of Protective Treatments N A 11 Data Relative to Structural Fasteners Antenna installation removal and
103. d 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 78 pin conn 44 pin conn 25 pin connector P4002 P4001 P4006 Positronic 1 Shield ground connector Pitch Card edge 20 24 AWG 336 00029 00 N A 583853 4 N A N A 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 3 5 Page Rev L Table 3 2 Recommended Crimp Tools or equivalent Connector High Density Standard Density Type Wire Gauge 22 28 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 N A M81969 1 02 M22520 2 08 M81969 1 02 Positronic 9507 9502 3 M81969 1 04 9502 11 M81969 1 02 9502 5 M81969 1 02 ITT Cannon 995 0001 995 0001 N A N A N A 995 0001 980 2000 584 739 604 426 601966 1 601966 6 91067 1 N A N A 601966 5 91067 2 AFM8 M81969 1 04 K774 M81969 1 02 K13 1 M81969 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 alternat
104. d ARINC 429 nominally 12 5 kilobits per second High speed ARINC 429 nominally 100 kilobits per second 400 SERIES INSTALLATION MANUAL Page 5 1 P N 190 00140 02 Page Rev L 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 90004 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 information from the following traffic advisory systems BF Goodrich SKY497 Skywatch Skywatch HP Bendix King KTA 870 KMH 880 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 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 DATA IN 1 DATA IN 2 cont 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 gr
105. d upon the GNS 430 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 15 tuned which stows the needle or drives it to the 3 o clock position 4 9 2 RMI OBI Electrical Characteristics PinName Connector Pin VO PinName Connector Pin VO The output driver is active low The driver output voltage is not more than 1 0 V when sinking 20 mApc The maximum off state leakage current with respect to ground is less than 10 LA pc 4 9 3 RMI OBI Configuration For the GNS 430 refer to section 5 2 10 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 22 on page 4 63 for the RMI OBI interconnect Page 4 18 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 10 DME TUNING GNS 430 ONLY 4 10 1 DME Tuning Function The GNS 430 can channel a DME based on the tuned VLOC frequency The GNS 430 outputs 2 of 5 BCD or Slip parallel DME and King Serial DME channeling format When DME COMMON is held low the GNS 430 actively tunes the DME 4 10 2 DME Tuning Electrical Characteristics 4 10 2 1 Parallel DME Tuning Connector Pin VO These pins are outputs when the GNS 430 15 configured for 2 of 5 parallel DME tuning For each of the parallel DME tuning discrete outputs the driver output voltage is n
106. e view WX 500 status trigger count and heading Figure 5 18 STORMSCOPE TEST Page 5 2 17 STORMSCOPE DOWNLOAD DATA Page Only if 400 Series unit configured for BFG WX 500 Stormscope interface Select the STORMSCOPE TEST Page see Figure 5 19 STORHSCOPE DOHHLOAD DATA 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 Figure 5 19 STORMSCOPE DOWNLOAD DATA Page 400 SERIES INSTALLATION MANUAL Page 5 13 P N 190 00140 02 Page Rev L 5 2 18 TRAFFIC Page Only if 400 Series unit configured for BFG Skywatch or Ryan TCAD interfaces Select the TRAFFIC Page see Figure 5 20 This page TRAFFIC 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 Test Mode Figure 5 20 TRAFFIC Page Skywatch For BFG Skywatch see Figure 5 20 verify that the 400 Series
107. eiver audio output shall not exceed 1096 at all levels up to 100 mW 1 3 7 Glideslope Specifications GNS 430 Only Selectivity 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 Standard deflection 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 Inthe absence of 90 Hz modulation d In the absence of both 90 Hz and 150 Hz modulation e Inthe absence of Page 1 6 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 1 4 LICENSE REQUIREMENTS The following guidance is provided to help ensure the proper licensing of the GNC 420 GNS 430 COM 1 The Telecommunications Act of 1996 effective February 8 1996 provides the FCC discretion to eliminate radio station license requirements for aircraft At present an individual license to operate the 400 Series aboard a private aircraft 1s not needed in many circumstances Please see FCC Fact Sheet PR5000 or contact the FCC
108. es 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 waypoint the waypoint annunciator flashes for 10 seconds 4 When a 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 430 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 CDP key on GNS 430 bezel 4 5 1 4 VLOC ANNUNCIATE GNS 430 Only This annunciator output is driven when the unit 15 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 430 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 400 Series unit 4 5 1 7 AUTO ANNUNCIATE This annunciator output is driven to indicate GPS AUTO mode of operation This outp
109. es are included with the GNS 420 A for those indicated with a Y above MOUNTING RACK 115 00243 00 CONNECTOR KIT 011 00351 01 BACK PLATE ASSEMBLY 011 00676 01 GNC 420 PRODUCT INFO KIT 00 00057 00 2 Denotes alternate secondary power input available review installation drawing 3 1 3 GPS 400 CATALOG UNIT ACCESSORIES COLOR ALT PWR P N P N 1 AVAILABL E 010 00171 00 011 00504 00 BLACK 010 00171 01 011 00504 00 BLACK 010 00171 10 011 00504 10 010 00171 11 011 00504 10 1 The following accessories are included with the GPS 400 for those indicated with a Y above MOUNTING RACK 115 00243 00 CONNECTOR KIT 011 00351 03 BACK PLATE ASSEMBLY 011 00676 03 GPS 400 PRODUCT INFO KIT 00 00056 00 Alternate secondary power input available review installation drawing Page 3 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 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 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 48 32 210 10004 09 ANTENNA GASKET 253 00002 00 e GA 56 Flange Mount Antenna Kit Mod 1 or later Garmin P N 010 10040 02 This kit contains the following items ITEM GARMIN P N FLANGE MOUNT GA 56 ANTENNA 011 00147 00 1 SUB ASSEMBLY NUT PL
110. ession 42 TT enews 3 TT 7 0 722 7 3 Equipment tested to Category Equipment tested to Category A Equipment tested per DO 160C 7 3 1 and 7 3 2 Equipment tested without shock mounts to Categories B amp N Eun f oo Equipment identified as Category X moistmqumd Fluids Susceptibility Equipment identified as Category X no test required Humidity 6 Shoe f 70 Temperature Variation 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 400 SERIES INSTALLATION MANUAL Page A 3 P N 190 00140 02 Page Rev L Environmental Qualification Form GNC 420 NOMENCLATURE GNC 420 Airborne GPS COM System TYPE MODEL PART NO 010 00173 which includes 011 00506 00 TSO JTSO COMPLIANCE TSO C129a Class A 1 GPS TSO C37d Class 4 amp 6 JTSO 2C37e COM TX GNC 420 TSO C37d Class 3 amp 5 JTSO 2C37e COM TX GNC 420A TSO C38d Class C amp E JTSO 2C38e COM RECEIVER 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 Temperature 45
111. et 2 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 GAMA General Aviation Subset 274 Edition The output data includes navigation and flight plan information to the following EFIS systems Sextant SMD 45 SDI Common long range navigator only 429 data with SDI 0 is used Number 1 Pilot long range navigator Only 429 data with SDI 0 or SDI 1 is used SDI 2 15 used 5 2 2 MAIN RS232 CONFIG Page Select the MAIN RS232 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 Figure 5 2 MAIN RS232 CONFIG Page 400 SERIES INSTALLATION MANUAL Page 5 3 P N 190 00140 02 Page Rev L CHANNEL INPUTS 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 400 Series units If Crossfill is selected for a channel output then Crossfill is automatically selected for that channel s input Serial altitude data from the following units Garmin GTX 327 Icarus Instruments 3000 Shadin ADC 200 200 2000 Shadin 8800 9000T 9200T Shadin 9628XX X Fuel Air Data Computer Shadin fuel Serial fuel flow info
112. ex Two ASCII numeric characters representing route sequence number of waypoint 01 to 31 xlannnnn 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 right if less than 5 characters in identifier 0 north or 1 south ddddddd latitude degrees unsigned binary XX 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 unsigned binary XX undefined mmmmmm latitude minutes unsigned binary X undefined hhhhhhh hundredths of latitude minutes unsigned binary mvar Two s complement binary in 16ths of degrees Easterly variation is positive MSB output first Page C 4 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 Appendix D 400 Series RS 232 Fuel Air Data Input Format D 1 ELECTRICAL INTERFACE The input signals shall be compatible with RS 232C Data shall be input at 9600 baud with a word length of 8 bits one stop bit and no parity One message is received per second 0 2 SHADIN ALTITUDE SENTENCE The GARMIN 400 Series units shall be capable of receiving the following 17 byte message from Shadin Altitude Encoders Altitude Serializers and Altitude Converters RMS lt
113. except the COM transmitter and the NAV amp G S SUPERFLAG outputs 4 2 2 2 Lighting Bus PinName Connector Pin VO LIGHTING BUS HI P4001 LIGHTING BUS LO P4001 The 400 Series unit can be configured to track 28 14 5 Vpc or 5 Vac lighting buses using these inputs Alternatively the 400 Series unit can automatically adjust for ambient lighting conditions based on the photocell Refer to section 5 2 5 4 2 2 3 Antennas PinName Connector 10 GPS ANTENNA P4003 COM ANTENNA P4004 VOR LOC ANTENNA P4005 GLIDESLOPE ANTENNA P4007 400 SERIES INSTALLATION MANUAL Page 4 5 P N 190 00140 02 Page Rev L 4 2 3 Power Lighting and Antennas Configuration Refer to section 5 2 6 for lighting configuration 4 2 4 Power Lighting and Antennas Calibration and Checkout Refer to section 3 9 for the COM antenna checkout 4 2 5 Power Lighting and Antennas Interconnect Refer to Figure 4 5 on page 4 29 for the power lighting and antennas interconnect 4 3 ALTIMETER 4 3 1 Altimeter Function Altitude input is required for GPS RAIM calculations and is useful for advisory vertical navigation VNAV calculations 4 3 2 Altimeter Electrical Characteristics PinName Connector Pin VO ALTITUDEA P4001 69 In PALTITUDEA2 P4001 68 PALTITUDEBY 1 Po 66 ALTITUDE COMMON P4001 60 In These inputs are considered active if either the voltage to ground is 1
114. g 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 is now part of the aircraft s inspection maintenance requirements Page A 2 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 A 2 Environmental Qualification Form GNS 430 NOMENCLATURE GNS 430 Airborne GPS VOR ILS COM System TYPE MODEL PART NO 010 00139 which includes 011 00280 00 TSO JTSO COMPLIANCE TSO C129a Class A 1 GPS TSO C37d Class 4 amp 6 JTSO 2C37e COM TX GNS 430 TSO C37d Class 3 amp 5 JTSO 2C37e COM TX GNS 430A TSO C38d Class C amp E 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 Low Temperature aPC High Temperature in flight Loss of Cooling i54 AWme Decompr
115. ghter the minimum brightness Display minimum brightness has a range of 35 to 999 and 15 set to 80 at the factory Key minimum brightness has a range of 20 to 99 and 15 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 SLOPE Sets the sensitivity of the display brightness in proportion to changes in the input level The higher the number the brighter the display is for a given increase in the input level This field has a range of 0 zero to 99 and 15 set to 50 at the factory Page 5 6 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 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 HAIH LIGHT IHG PHOTO TRANS Photocell Transition Percentage When a lighting bus is used to control the lighting of the display see Figure 5 7 this parameter sets the point on the lighting bus control below which the display brightness tracks the 400 Series unit s photocell This field has a range of 0 zero to 99 and 15 set to 25 at the factory PHOTO SLP OFFST Photocell Slope Offset These fields are equivalent to the SLOPE OFFSET fields described above with the exception that they only control the display lighting characteristi
116. gn 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 1s recommended that the installer proceed according to any of the following listed alternatives 1 Obtain approved antenna installation design data from the aircraft manufacturer 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 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
117. i channel ARINC 429 DME channel 2 of that DME is tuned Page 5 12 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 5 2 15 STORMSCOPE CONFIG Page Only if 400 Series unit configured for BFG WX 500 Stormscope interface Select the STORMSCOPE CONFIG Page see Figure 5 STORHSCOPE CONFIG 17 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 400 Series unit is used with a WX 500 Figure 5 17 Stormscope the Synchro or Serial heading formats STORMSCOPE CONFIG Page may be used If another heading format is used lightning strike information is visible on the Weather Page but not on the Map Page 5 2 16 STORMSCOPE TEST Page Only if 400 Series unit configured for BFG WX 500 Stormscope interface Select the STORMSCOPE TEST Page see Figure 5 18 STORHSCOPE TEST This page shows current strike activity WX 500 status OS ear S 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 procedures for the WX 500 using this page to view strike data change the WX 500 mod
118. ial 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 is 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 15 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 400 Series unit should not be routed near components or cabling which are sources of electrical noise Do not route the COM antenna coax 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 400 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 0 1 inches of water Potential damage to your 400 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
119. ing KTA 870 KMH 880 CDU 429 A TX CDU 429 B TX TAS TEST IN TAS STBY Goocrich SKY 497 SOFTWARE 1 6 OR HIGHER 429 429 1B DISPLAY GROUND SOFT KEY 1 TEST ALT SOFT KEY 4 OPR STB POWER SWITCH HI POWER SWITCH LO 9 uuoo21 81u ulejs S 21611 8 t 4 98 99 4 t Bed Ady Sed N CARM GARM NA LASA 100 420 450 SOFTWARE 2 11 OR HIGHER GPS RS 232 OUT 2 GPS RS 232 IN 2 NOTES 429 1A 429 TX 1B DISPLAY GROUND SOFT KEY 2 TEST ALT SOFT KEY 4 OPR STB POWER SWITCH HI POWER SWITCH LO P4001 P10 48 54 2 49 55 10 2 11 25 P4001 P1 N 34 ae SEE NOTE 2 49 U 33 78 14 10 85 11 gt 82 11 SEE NOTE 3 3 P4001 P1 a 44 is SEE NOTE 2 49 43 78 10 10 gt 4 19 11 21 4 SEE NOTE 3 5 P4001 P1 58 C 19 E 59 Q 17 18 zh OPTIONAL REMOTE SWITCH gt C 5 TO OPTIONAL LAMP OR SONALERT lt 6 SEE NOTE 4 gt 16 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 IF THE GPS ARINC 429 IN 1 PORT 4001 48 AND 49 IS ALREADY USED FO R ANOTHER PURPOSE THE GPS ARINC 429 IN 2 PORT P4001 50 AND 51 MAY BE CONNECTED INSTEAD 3 THE SKYWATCH POWER SWITCH PINS SHOWN ONP1 SH
120. ion 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 information leg sequencing loss of integrity RAIM message and waypoint alert are not required in most installations where the GNS 430 display 15 located in the center area of the vertical instrument pancl For most aircraft a location in the center radio stack or other location on the pilot s panel within the normal field of view at a height suitable for normal viewing from the pilot s 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 siack arrangements on the right and vertically such that it is not blocked by the glareshield on top and not below the instrument panel or blocked by throttles control yoke etc on the bottom Installations located outside of this area 1 e in 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 Sincercly FE C Da
121. it is now in the configuration mode After the data base pages the first page displayed 1s the MAIN ARINC 429 CONFIG page While in Configuration Mode pages can be selected by ensuring the cursor 1s off and rotating the small right knob To change data on the displayed Configuration 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 25 All Configuration Pages shown apply to the GNS 430 but not all apply to the GPS 400 or GNC 420 Those pages and fields that apply only to certain 400 Series units are denoted as such HAIN ARINC 429 CONF IG 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 spee
122. ition 65 If you have any questions or would like additional information please refer to our web site at www garmin com prop65 400 SERIES INSTALLATION MANUAL Page 1 P N 190 00140 02 Page Rev L TABLE OF CONTENTS 1 GENERAL DESCRIPTION INTRODUCTIO N a 1 1 I2 BOUIBMERTDESCILIPTIDN 1 1 LS EB CHINICAL SPECIFICATIONS ajak aes 1 2 VALICENSE REQUIREMENTS a 1 7 Se PK TLATEN akan a 1 7 Lo PAULA DETECTION AND anaa ota 1 7 LIMLEED WARE oett unu a 1 amp 2 INSTALLATION ZINE ROD UC 2 1 2 2 ANTENNA CONSIDERA TIONS 2 1 252 RACK CONSIDERATION Sse ur k kaanan 2 3 2A CAS GING ANDE WIRING uuu u 2 3 GOLING AIR asana c 2 3 2 6 MINIMUM INSTALLATION Su Suma aa aga 2 3 3 INSTALLATION PROCEDURE
123. ive 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 use 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 Forthe card edge connector pin contacts use AMP part number 90272 1 or equivalent crimping tool 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 3 4 and 3 5 starting on pages 3 11 3 13 and 3 15 show outline dimensions for the aviation rack for the various 400 Series units Install the rack in a rectangular 6 320 x 2 700 hole or gap between units in the instrument panel refer to Figure 3 9 page 3 23 The lower front lip of the rack should be flush with or extend slightly beyond the finished aircraft panel CAUTION If the front lip of the mounting rack 1s behind the surface of the aircraft panel the 400 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 15 Exercise caution when installing the rack into the instrume
124. ix King KDC 481 24811 B b np an Zo o No AR D PORT P4001 CA TION ETE PINOUT AND INTERCONNECT INFOR 0075 OF OTHER UNITS SHOWN FOR REFERENCE vi f a ivi J ONLY G2 gt 20 50 JU C Figure 4 16 ARINC 429 Air Data IRU AHRS Interconnect Page 4 51 Page 4 52 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page Rev L 4 11 15 ARINC 429 Flight Control Interconnect R 429 3 429 SINIO 4209 N Figure 4 17 ARINC 429 Flight Control Interconnect 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page 4 53 Page 4 54 blank Page Rev L C070t 100 061 N d NOILVTIVISNI 007 GARMIN 00 420 430 420 436 SOFTWARE 2 25 OR HIGHER GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B ANNUNCIATE D ANNUNCIATE E GARMIN 400 420 430 SOFTWARE 2 11 OR HIGHER GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B AIRCRAFT GROUND ANNUNCIATE D ANNUNCIATE CAD GA M N A AZM 00 420 430 SOFTWARE 2 11 OR HIGHER GPS ARINC 429 IN 1 A GPS ARINC 429 IN 1 B AIRCRAFT GROUND ANNUNCIATE D ANNUNCIATE Bendix K
125. kes 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 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 Self Test Page is displayed followed by the Data Base Page Pressing the ENT key once then displays the Instrument Panel Self Test page refer to Figure 5 5 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 Data Base Page verify that the following parameters are displayed on equipment in the aircraft as listed below NOTE Electronic displays which monitor the 400 Series unit s ARINC 429 output may vary in how and where annunciations are displayed Generally it 1s not required to verify every data field with an ARINC 429 interface Correct display of a subset of the data without noting any discrepancies 1s typically adequate evidence of correct ARINC 429 operation Self test Value Course Deviation Half scale left deviation TO indication flag pulled Glideslope Vert Deviation Half scale up deviation flag pulled Bearing to Waypoint 135 Desired Tra
126. l 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 uV Sensitivity S N N on all channels shall be greater than 6 dB when the HF level is 2 uV hard modulated 30 at 1000 Hz at rated audio 3 uv 6 dB for 8 33 kHz channels Selectivity 6 dB BW is greater than 8 kHz for 25 kHz channeling 60 dB 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 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 0005 Demodulated Audio Distortion Less than 10 distortion when the transmitter is modulated at least 7096 Sidetone 1 4 Vus into a 500 Q load when the transmitter is modulated at least 7096 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 applic
127. le Bleakney FAA Program Manager Wichita Aircraft Certification Office Page B 6 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 U S Department Small Airplane Directorate of Transportation Wichita Certification Office Federal Aviation 1801 Airport Road Room 100 Administration Wichita Kansas 67209 September 9 2002 Mr Robert W Billings GARMIN INTERNATIONAL 1200 East 15184 Streci Olathe KS 66062 Subject GARMIN GNC 400 Series Notice 8110 60 Data Submittal Reference 1 GARMIN letter dated August 27 2002 2 FAA Notice 8110 60 GPS as a Primary Mcans 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 400 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 GPS as Primary is Pis si dated 2 11 97 and as agreed upon in arc Aspects of Certifies for EDE GPN 005 0007 7 63 GARMIN has previously received TSO C1292 1 Equipment Using the Global Positioni g Systei GNC 400 series products through our office The GNC 400 series software has been developed in accordance with D
128. m 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page D 3 Page Rev L This page intentionally left blank Page D 4 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 Appendix E 400 Series LRU Interface Overview The following tables provide a quick overview of some of the equipment that can be interfaced with the GARMIN 400 Series units This 1s not a complete listing however it only represents those units listed in Section 4 of this manual When installing equipment on the aircraft always refer to the manufacturers documentation for complete pinout and interconnect information E 1 GARMIN 420 430 LRU INTERFACE Bendix King Audio Panel KMA 24 GMA 340 PMA 6000 KMA 24H E 2 GARMIN 400 420 430 LRU INTERFACE KDC41 2000 41220 po 9000003 Function Shadin Icarus JP Shadin Miniflo L Instruments Instrument Altitude Serializer or 8800T 3000 FC 10 700 91204XT 38 D Fuel Air Data 90007 FTO 90744 Digiflo L Digidata International FuelAirData 91053XT D F ADC 2000 Flight Control KFC200 TT KFC40 2 po KP Or Blind Encoder KEA 346 Digifo L Digidata 400 SERIES INSTALLATION MANUAL Page E 1 P N 190 00140 02 Page Rev L Bendix King EFIS EFIS 40 50 EFIS 84 Displays SG465 DPU 84 EHSI SN 3308 4 HGIOUSAB 211 HGl105AB
129. may damage the electrical connections to the antenna Use of these type sealants may void the antenna warranty Page 3 4 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 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 GASET 1 PLACE NUT AND GASKET OVER CABLE AND STRIP JACKET E TO DIMENSION SHOWN e COMB OUT BRAID AND TRIM DIELECTRIC DIMENSION SHOWN 1 4 PULL BRAID WIRES FORWARD AND TAPER TOWARD CENTER CONDUCTOR PLACE CLAMP OVER BRAID AND PUSH BACK x AGAINST CABLE JACKET 4 FOLD BACK BRAID OVER CLAMP AS SHOWN TRIM OFF EXCESS BRAID SOLDER CONTACT TO CENTER CONDUCTOR D re 2 INSERT CABLE CLAMP AND GASKET INTO CONNECTOR ROBY MAKING SURE 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 400 Series back plate CAUTION 4 Feed wires through the connector backshells before insertion into the 78 44 and 25 pin connectors 5 Contacts for the 78 44 an
130. mile range Listen to the VOR audio and verify that no electrical interference such as magneto noise 15 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 1s 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 84 5 3 9 DME Tuning Check GNS 430 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 groundspeed and time are displayed Page 5 18 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 Appendix A CERTIFICATION DOCUMENTS A 1 Continued Airworthiness This section provides assistance to the installing agency in preparing Instructions for Continued Airworthiness ICA in response to Bulletin Number HBAW 98 18 Checklist for Instructions for Continued Airworthiness for Major Alterations Approved Under the Field Approval Process effective 10 7 98 Aviation Authority approved installers are hereby granted permission to reference appropriate service instructions and excerpts from this Installation Manu
131. n CDI OBS checkout 4 4 5 Main Indicator Interconnect Refer to Figure 4 7 on page 4 33 for the generic main indicator interconnect Refer to Figure 4 8 on page 4 35 for the interconnect between a GNS 430 and a Bendix King KI 209A Refer to Figure 4 9 on page 4 37 for the interconnect between a GPS 400 or GNC 420 and a Bendix King KI 208A Page 4 8 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 5 ANNUNCIATORS SWITCHES 4 5 1 Annunciators Switches Function Initial certification of the 400 Series units was accomplished without use of any remote switches or annunciators since the same switching and annunciation is available on the front panel of the 400 Series unit However if the 400 Series unit is not installed in the pilot s normal field of view some or all of the remote switches and annunciators may be required by your certification agency Appendix B includes an FAA letter granting permission to install GNS 430 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 1s in a turn the waypoint annunciator illuminat
132. ng GNC 400 series models and FDE Prediction Program GARMIN Part _ Model Number GPN Description GPS 400 010 00171 GPS Receiver System GNC 420 010 00173 GPS Recetver 10W VHF Comm System GNC 420A 010 00287 GPS Receiver 16W VHF Comm System GNS 430 010 00139 GPS Receiver 10W Comm VOR LOC Glide Slope GNS 430A 010 002864 GPS Receiver 16W VHF Comm VOR LOC Glide Slope System EDEPRDCT 006 A0072 00 Prediction Program Software Revision B As agreed upon in GINC 400 500 Plan for Software Aspects 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 Occanic Remote operation approval the AFM S must be amended per Notice 8110 60 paragraph 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 400 series of products If you have questions regarding this authorization please contact me at 516 946 4134 Sincerely 2 pc UA Roger A Souter Aerospace Salet Engineer Electrical and Mechanical Systems Wichita Aircraft Certification Officc Enclosure Page B 8 400 SERIES I
133. ning data output King Serial King Serial DME tuning data not operational for MAIN software versions 2 02 and lower Parallel 2x5 2 of 5 parallel DME tuning Parallel BCD Shifted BCD Binary Coded Decimal parallel DME tuning not operational for MAIN software versions 2 02 and lower Parallel slip Slip code parallel DME tuning not operational for MAIN software versions 2 02 and lower Narco 890 891 2 of 5 parallel DME tuning compatible with the following DME units Narco DME 890 Narco DME 91 ARC Cessna RTA 476A 5 2 14 VOR LOC GS ARINC 429 CONFIG Page GNS 430 Only Select the VOR LOC GS ARINC 429 CONFIG Page see Figure 5 16 This page configures the VOR ILS ARINC 429 output and input ports YOR LOC G5 ARINC 429 COHFIG Figure 5 16 VOR LOC GS ARINC 429 SPEED CONFIG Page Low Standard low speed ARINC 429 nominally 12 5 kilobits per second High speed ARINC 429 nominally 100 kilobits per second 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 430 is connected to a multi channel ARINC 429 DME channel 1 of that DME is tuned Directed freq 1 should be selected if a single channel ARINC 429 DME 1s tuned Directed freq 2 If the GNS 430 is connected to a mult
134. nnect 400 SERIES INSTALLATION MANUAL Page 4 61 Page 4 62 blank P N 190 00140 02 Page Rev 4 11 20 RMI OBI Interconnect Bendix King Bendix King Bendix King Bendix King Kl 229 KNI 582 KNI 582 KDA 692 SE N O E Pointer 1 Pointer 2 P2291 P5821 P5821 P6921 MAIN OBI CLOCK 43 gt 12 8 7 11 OBI CLOCK MAIN OBI DATA t4 19 17 16 OBI DATA MAIN OBI SYNC 5 Cs 11 33 24 M OBI SYNC SEE NOTE 5 Bendix King Bendix King Bendix King Bendix King IC bi 229 KNI 582 KNI 582 KDA 692 P4006 VLOC Pointer Z1 Pointer 2 A P2291 P5821 P5821 P6921 VOR OBI CLOCK 25 C I E e es C C 12 8 7 11 OBI CLOCK NI VOR OBI DATA 27 C3 O E P Se D C 19 17 16 L OBI DATA M 25 VOR OBI SYNC 26 PN o 15 5 C 11 35 24 OBI SYNC Ned e i P4001 aS MAIN OBI CLOCK 43 e MAIN OBI DAT t4 3 MAIN OBI SYNC 45 5 1 ALL WIRES 24 AWG OR LARGER UNLESS OTHERWISE NOTED 2 IF IT IS DESIRED FOR THE RMI POINTER TO SWITCH WIT THE CDI BUTTON ON THE FRONT PANEL OF THE SNS 450 INSTALL AS PER THE TOP DI
135. nt panel The rack 15 designed to facilitate removal of the 400 Series for use in Demo Mode outside the aircraft Deformation of the rack may make it difficult to install and remove the 400 Series unit 3 Install the rack in the aircraft panel using six 6 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 the slots of the left side of the rack viewing it from the cockpit and attaching it by replacing the two 44 40 screws Page 3 6 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 3 8 400 SERIES UNIT INSERTION AND REMOVAL The 400 Series unit is installed in the rack by sliding it straight in until it stops about 1 inch short of the final position A 3 32 hex drive tool is then inserted into the access hole at the bottom of the unit face Rotate the hex tool clockwise while pressing on the left side of the bezel until the unit 1s firmly seated in the rack 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 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 f
136. o the maintenance manual This Mic Gain software adjustment is effective for GNS 430 s n 97107371 and above and GNC 420 s n 97202086 and above NOTE The sidetone audio output level 15 independent of the COM volume knob on the 400 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 1f you are done with configuration Verify That The box is filled in while the COM push to talk switch is pressed XFR The box is filled in while a remote COM transfer switch is pressed The box is filled in while the COM 15 receiving a signal The box is filled in while the COM push to talk switch is pressed Page 5 10 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 5 2 12 VOR DISCRETE INPUTS GNS 430 Only Select the VOR DISCRETE INPUTS Page see Figure 5 14 This page allows you to verify the operation of an external VLOC transfer switch that may be present in the installation Figure 5 14 VOR DISCRETE INPUTS Page Verify That REMOTE XFR The box is filled in while a remote VLOC transfer switch is pressed YOR LOC GS CDI 5 2 13 VOR LOC GS CDI Page GNS 430 Only Select the VOR LOC GS CDI Page see Figure 5 15 This page allows you
137. of navigation for oceanic remote operations per N8110 60 The oceanic flight phase occurs on the GPS 400 GNC 420 GNS 430 when more than 200 nautical miles from the nearest airport operators using the GPS 400 GNC 420 GNS 430 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 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 FROM DEFECTS IN
138. or the Traffic Advisory System Interconnect Refer to Figure 4 19 on page 4 57 for the Weather and Terrain Interconnect Refer to Figure 4 19 on page 4 57 for RS 232 serial data interconnects with the GARMIN GDL 49 Satellite Data Link Transceiver 400 SERIES INSTALLATION MANUAL Page 4 13 P N 190 00140 02 Page Rev L 47 COM VOR ILS AUDIO GNC 420 AND GNS 430 ONLY 4 7 1 COM VOR ILS Audio Function and Emergency Mode Activation of COM MIC KEY enables COM MIC AUDIO and causes the transceiver to transmit 5000 COM AUDIO and 50042 VOR ILS AUDIO 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 1s depressed for two seconds the active COM frequency changes to 121 50 MHz Once the emergency frequency is activated through COM REMOTE TRANSFER GNS 430 and GNC 420 COM transceivers with Mod 2 incorporated ignores 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 GNC 420 or GNS
139. ot 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 55 considered active if either the voltage to ground 15 lt 1 9 V or the resistance to ground is 375 These inputs are considered inactive if the voltage to ground is 11 33 4 10 2 2 King Serial DME Tuning PinName Connector Pin VO NAV SER DME DATA P4006 NAV SER DME CLOCK P4006 SER DME CHAN REQ PAR DME 4MHZ P4006 SER DME RNAV MODE PAR DME 2MHZ P4006 NAV DME COMMON P4006 These pins are inputs when the GNS 430 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 lt 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 1s the device channeling the DME 400 SERIES INSTALLATION MANUAL Page 4 19 P N 190 00140 02 Page Rev L 4 10 3 DME Tuning Configuration Refer to section 5 2 12 for
140. ote airspace when used in conjunction with the 400 Series Trainer Program incorporating the FDE Prediction Program This does not constitute an operational approval The Garmin 400 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 15 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 60 400 SERIES INSTALLATION MANUAL Page 1 7 P N 190 00140 02 Page Rev L The FDE function is built into the GPS 400 GNC 420 GNS 430 and does not require pilot interaction In contrast the FDE Prediction Program does require pilot interaction and must be used prior to oceanic remote area flights to predict FDE availability The 400 Series Trainer software Garmin Part Number 190 00176 00 includes an FDE Prediction Program to meet the requirements for GPS as a primary means
141. 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 1s 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 1s a list of required devices for TSO C129a category Al and A2 certification For a specific list of equipment used in the initial STC obtain a copy of GNS 430 in Piper PA32 Documented Installation P N 190 00140 06 The FAA or the governing organization should approve deviations from that set of equipment Pressure Altitude Device This device delivers pressure altitude data to the 400 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 430 Only This device delivers the manual course select to the 400 Series unit which is required for the GNS 430 VOR receiver and optional for the 400 420 430 GPS receiver Course information can come from an analog resolver or from an EFIS EHSI via ARINC 429 serial data HSI CDI Indicator or EFIS This device displays Nav Flag Left Right To
142. perature 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 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 Ox0d line feed character 0x0a sign indicator 0x2b or Ox2d lt ETX gt end transmit character 0x03 Not available from Airdata Computer Note Checksum 15 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 fro
143. ppropriate Figure 5 12 MAIN CDI OBS CONFIG Page CDI LAT VERT NAV FLAG LAT VERT Verify That The LAT VERT flag is hidden The LAT VERT flag is in view Page 5 8 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 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 400 Series unit s MAIN OBS inputs The SELECTED COURSE field indicates near to 150 and a Calibrate to 150 field appears Selecting this field calibrates the 400 Series unit to match the input source Verify OBS operation by checking that the course displayed on the 400 Series unit is within 2 of the selected course Do this at 30 intervals around the OBS card 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 for GPS When OBS mode 15 selected the selected course 1s entered on the controls of the 400 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 display device press MENU on the MAIN CDI OBS CONFIG page and select Ignore SEL CRS for VLOC CDI GNS 430 Onl The GNS 430 CDI button is in the GPS state and the GPS ANNUNCIATE output is active This
144. 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 deseri iya suspended recoded or a lamination diate othemwise estattished the Ibarra irepl of lhe E Bele of apyleoation November 10 1998 Pals of tasaance July 06 1999 Gede amended Ky damotion of the Sbdminisimalor e 2 Tina L Miller Program Manager Wichita Certification Office a m Title i eS SS SSS Any altarstion of this certificate is punishable by a fine of not exceeding 51 409 or imprisonment nor exceeding 3 years or bath FRA 6110 2 10 68 PAGE 1 of 2 PAGES This certificate may be transferred accardance with FAR 21 47 Page B 4 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 2 INSTALLATION MEMORANDUM TO GARMIN Authorized Dealers FROM GARMIN International DATE January 25 1888 SUBJECT GNS 430 approval basis without external switching or annunciation CC Wichita Aircraft Certification Office A A M M Due to reluctance by GARMIN Authorized Dealers and FAA Flight Standard District Office Field Inspectors to install and approve GARMIN GNS 430 Integrated Communications
145. 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 400 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 je 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 responsible for ensurin
146. rmation 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 WX 500 Lightning strike information from a BF Goodrich WX 500 Stormscope CHANNEL OUTPUTS Off No unit s connected to output of this channel Aviation Serial position altitude velocity and navigation data to the following units GARMIN 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 400 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 FUEL TYPE The aircraft is using Aviation gas 5 8 Ibs gal The aircraft is using Jet or Jet A 1 fuel 6 7 Ibs gal The aircraft is using Jet B JP 4 fuel 6 5 Ibs gal Page 5 4 400 SERIES INSTALLA
147. rom the rack Be sure not to over tighten the unit into the rack The application of hex drive tool torque exceeding 15 in lbs can damage the locking mechanism 3 9 COM ANTENNA INSTALLATION CHECK GNC 420 AND GNS 430 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 1s 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 1s most likely seen as high reflected power A VSWR of 3 1 may result in up to a 50 loss in transmit power 400 SERIES INSTALLATION MANUAL Page 3 7 P N 190 00140 02 Page Rev L This page intentionally left blank Page 3 8 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 3 10 GA 56 Antenna Installation Drawing 011 00134 004 ANTENNA AVIATION ARA GA56 FORWARD 011 00147 00 GA56 ANTENNA FLANGE MOUNT g A p p Wy OD gt 255 00002 00 pom GASKET NEOPRENE 255 0001 1 00 GASKET NEOPRENE o 2 gt a 28 PA P d c ON RSBABL SKIN Ms Ts p AIRCRAFT SKIN ON 5 JN TOP O USELAG TOP OF FUSELAGE WA D lt AAN
148. s the Type 1 output sentence item designator id and item data 4444 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 NN Les 5 mmhh Current latitude where S N north or S south dd degrees mm minutes hh hundredths of minutes s mmhhh Current longitude where s E east or W west ddd degrees mm minutes hh hundredths of minutes asa Distance to waypoint in tenths of nautical miles s n n nn Cross track error where s L left or R right of course nnnn error in hundredths of nautical miles NEN LLL IEEE ou C C C C cC Destination waypoint identifier will be blank filled on right if less than 5 characters in identifier Bearing to destination waypoint in tenths of degrees 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 Warnings status only data transmitted are dashes Used to indicate end of Type 1 sentences lower case d ddddd Distance to destination waypoint in tenths of nautical Lima miles The line feed character 15 not output if the RS 232 port is configured as Avtn no alt The altitude is not output if the RS 232 port 15 configured as Avtn no alt Page C 2 400 SE
149. te reception of GPS satellite signals CAUTION Do not connect DEMO MODE SELECT 1n an aircraft installation 4 5 1 14 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 VO MESSAGE ANNUNDIATE 1 P4001 6 Out AUTO ANNUNGIATE P4001 8 Out INTEGRITY ANNUNCIATE P4001 9 Ou outputs sink up to 500 mA when activated 4 5 2 2 Switch Inputs _Pin Name Connector Pin VO OBS MODE SELECT CDI SOURCE SELECT P4001 DEMO MODE SELECT P4001 These inputs are considered active if either the voltage to ground is 1 9 V or the resistance to ground is lt 375 These inputs are considered inactive if the voltage to ground is 11 33 4 5 2 3 TIME MARK OUT PinName Connector Pin VO X TIME MARK OUT outputs a 1 ms 1 Us wide pulse once every 1 0 2 ms TIME MARK OUT isa 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 8 for the switches checkout Refer to section 5 2 9 for the annunciators checkout 4 5 5 Annunciators Switches Interconnect Refer to Figure 4 10 on page 4 39 for the annunciators switches interconnect
150. the CDI button status The VOR ILS indicator displays both lateral and vertical To From indications lateral and vertical flags and superflags GNS 430 connector 4006 always outputs the VOR Localizer Glideslope navigation information The VOR ILS pins on GNS 430 connector 4006 are used to drive an indicator that displays VOR ILS information at all times regardless of CDI selection on the GNS 430 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 VORIILS Indicator Electrical Characteristics 4 8 2 1 Superflags PinName Connector Pin VO VOR LOC SUPERFLAG P4006 GLIDESLOPE SUPERFLAG P4006 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 Vpc when the flag is to be OUT OF VIEW The output voltage with respect to ground 15 less than 3 Vpc when the flag is to be IN VIEW 4 8 2 2 Deviation _Pin Connector Pin 1O X VOR LOC RIGHT VOR LOC COMMON P4000 6 Out GLIDESLOPE DOWN FLAG GLIDESLOPE P4006 COMMON The deviation outputs are each capable of driving up to three 1000 Q meter loads with 150 mVpc 10 with respect to 2 5V Common for f
151. the DME tuning configuration 4 10 4 DME Tuning Calibration and Checkout None 4 10 5 DME Tuning Interconnect Refer to Figure 4 23 on page 4 65 for the King Serial Panel DME tuning interconnect Refer to Figure 4 24 on page 4 67 for the King Serial Remote DME tuning interconnect Refer to Figure 4 25 on page 4 69 for the parallel 2 of 5 DME tuning interconnect Refer to Figure 4 26 on page 4 71 for the parallel BCD Slip Code DME tuning interconnect NOTE For the GNS 430 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 13 on page 5 11 and Figure 4 25 on page 4 69 Page 4 20 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 C070t 100 061 N d NOILVTIVISNI SATUS 007 weibeiq aveau SONOS OOP L N Olue q zc v oSeq 1 9894 Ady Sed AIRCRAFT POWER POWER amp GROUND MAIN OBI AIRCRAFT LIGHTING BUS Zl LIGHTING BUS EXTERNAL INSTRUMENTATION TIME MARK OUT es x T Manse IN AT DEVIATION amp FLAGS 2 GPS RS232 OUT 3 TOZEROM JZ VERT DEVIATION amp FLAGS 1 gt SUPERFLAGS gt MAIN OBS amp EN ALTIMI GRAY CODE ALTITUDE SWITCHES 2 ANNUNCIATORS 9 2 1 GPS RS232 IN 1 D e f GPS ARINC 429 IN 1 2 GPS ARINC 429 OUT ATE GPS RS232 OUT 1 gt 7 4 1 ILS GPS APPROAC INTERCOM MICROPHON
152. the GNS 430A and GNC 420A except where specifically noted Page iv 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 400 SERIES HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification Mod Levels for the GPS 400 GNC 420 and GNS 430 Mod Levels are listed with the associated service bulletin number service bulletin date and the purpose of the modification The table 15 current at the time of publication of this manual see date on front cover and is subject to change without notice Authorized 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 BULLETIN NUMBER SERVICE BULLETIN DATE 9 17 99 PURPOSE OF MODIFICATION CDI HSI deviation error GNS 430 P N 011 00280 00 GNC 420 P N 011 00506 00 GPS 400 P N 011 00504 00 11 07 00 Replace fuse in COM circuit with a resistor GNS 430 P N 011 00280 10 GNC 420 P N 011 00506 10 GNS 530 P N 011 00550 10 0101 2 16 01 Remote COM transfer 0203 Rv B 8 12 02 Improve receiver audio compressor performance 4 2 02 Remove excess solder from COM board Note Throughout this document references made to GNS 430 and GNC 420 shall equally apply to the GNS 430A and GNC 420A except where specifically noted 400 SERIES INSTALLATION MA
153. ty Equipment tested to Category F with Ethylene Glycol De Icing Fluid Sand and Dust 0 Equipment identified as Category X no test required Voltage Spike Equipment identified as Category X no test required Salt Spray Equipment identified as Category X no test required Magnetic Effect Equipment identified as Category X no test required Induced Signal Scil 190 __ Radio Frequency Suscepibiliy 200 ______Fauipmenttestedto Category T Radio Frequency Emission 210 FapmeselioCaegyZ Tishing Dires 230 EqupmeniesedoCusoy2A Page 6 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 Appendix B STC Permission Consistent with N8110 69 or Order 8110 4 Aviation Authority approved installers are hereby granted permission to use STC s SA00705 WI GNS 430 SA00801 WI GNC 420 and SA00800WI GPS 400 data to modify aircraft 400 SERIES INSTALLATION MANUAL Page B 1 P N 190 00140 02 Page Rev L Jiniteh States of America Beparinent of Transportation Medera Abiation Administration Supplemental Type Certificate Number SA00705 WI do Garmin International 1200 E 51st St Olathe KS 66062 Por ha the rhage tu Mee 2 the fhe peel tra and therefor ta specified rro lhe
154. uipment tested without shock mounts to Categories B M amp N 50 Equipment identified as Category X moistmqumd ___ Fluids Susceptibility Equipment identified as Category X no test required Sand and Dust Equipment identified as Category X no test required Voltage Spike Equipment tested to Category A See report 005 00096 72 for details Magnetic Effect Equipment tested is Class Z Salt Spray Equipment identified as Category X no test required Audio Frequency Susceptibility Equipment tested to Category B Induced Signal Susceptibility Equipment tested to Category A 400 SERIES INSTALLATION MANUAL Page A 5 P N 190 00140 02 Page Rev L A 5 Environmental Qualification 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 LovTewemue 481 T High Temperature 432 4433 OOO In flight Loss of Cooling Hm 60 e OO Vibration Equipment tested without shock mounts to Categories C L M amp Y Equipment identified as Category X no test required Fluids Susceptibili
155. ull scale deflection The drive circuit provides for more than full scale deflection with a maximum course deviation output voltage of 300 mVpc 10 4 8 2 3 TO FROM PinName Connector Pin VO VOR LOC TO VOR LOC FROM VOR LOC COMMON P4006 The output is capable of driving up to three 200 Q meter loads When indicating TO the output is 225 75 mVpc When indicating FROM output is 225 75 mVpc When invalid information is present Flag IN VIEW the TO FROM output is 0 10 mV pc Page 4 16 400 SERIES INSTALLATION MANUAL Page Rev L P N 190 00140 02 4 8 2 4 Flag PinName Connector Pin VO VOR LOC FLAG P4006 VOR LOC FLAG VOR LOC COMMON P4006 GLIDESLOPE FLAG P4006 GLIDESLOPE DOWN FLAG GLIDESLOPE P4006 31 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 mVpc When invalid information is present Flag IN VIEW the Flag output is 0 25 mVpc 4 8 2 5 OBS _Pin Connector Pin VO VOR OBS ROTOR C P4006 9 Out VOR OBS ROTOR H GROUND P4006 VOR OBS STATORD P4006 VOR OBS STATOR F P4006 VOR OBS STATOR E G VOR LOC P4006 11 Out COMMON VOR OBS C and 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 of the VOR ROTOR
156. unit can change the Skywatch operating mode STBY 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 400 Series unit Refer to the BFG Skywatch installation manual for system checkout TRAFFIC For Ryan TCAD see Figure 5 21 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 21 TRAFFIC Page TCAD 5 2 19 RYAN TCAD CONFIG Page Only if 400 Series unit configured for Ryan TCAD interface Select the RYAN TCAD CONFIG Page see Figure 5 22 RYAN TCAD COHF IG 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 if a mute switch is installed are shown Refer to the Ryan TCAD installation manual for system checkout Figure 5 22 RYAN TCAD CONFIG 5 2 20 GAD 42 CONFIG Page Only if 400 Series unit configured for GAD 42 interface Select the GAD 42 CONFIG Page see Figure 5 23 This GAD 4
157. uooJeiu ISH3 I8pueS 627 SL r eJn61J Olue q 0 oSeq 6 8 Ady Sed 3 VOR ILS 1 Sandel RELAXED PNSSDB P N C e T NOTE 2 1 R E P4006 E gt NOTE 2 NAV 1 2 RELAY SENSE VOR ILS ARINC 429 OUT A 24 are 9 429 2 RX A VOR ILS ARINC 429 OUT B 25 Le l9 27 429 2 RX B ENERGIZED VOR ILS 2 28 VDC 5 VHF NAV 2 SWITCHING RELAY 21 GPS 2 SWITCHING RELAY P4001 GPS ARINC 429 IN 1 A 48 11 429 1 TX GPS ARINC 429 IN 1 B 49 29 429 1 TX B GPS ARINC 429 OUT A 46 a 10 429 1 GPS ARINC 429 OUT 47 e gt 28 429 1 RX B 26 429 3 RX A J gt 7 429 3 RX B ILS GPS APPROACH 14 E gt NOTE 2 CDI SOURCE CONTROL MAIN FEET 21 2 RCVR 1 2 MAIN RIGHT 22 H MAIN LATERAL FLAG 23 MAIN LATERAL FLAG 24 j E MAIN UP 27 MAIN DOWN 28 MAIN VERTICAL FLAG 29 MAIN VERTICAL FLAG 30 VOR ILS 1 2 pM RELAXED gt P3 Ae N C COPILOT 2 1 2 RELAY SENSE P4006 lt C VOR ILS ARINC 429 OUT A 24 f 217 9 429 2 RX A VOR ILS ARINC 429 OUT B 23 yov 27 295Z KAB I ENERGIZED VOR ILS 2 28 vDC gt i lt 5 VHF NAV 2 SWITCHING RELAY 1 PS 2 S G P4001 E 2 GPS 2 SWITCHING RELAY GPS ARINC 429 IN 1 A 48 lt 0 11 429 1 TX A GPS ARINC 429 IN 1 B 49 29 995 T XS 10 429 1 RX A 28 429 1 RX B GPS ARINC 429 OUT A 46 2 gt 26 429 3 RX A GPS ARINC 4
158. ut is active when neither the OBS nor SUSP annunciations are on the display 4 5 1 8 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 9 TERMINAL ANNUNCIATE When performing approach navigation the terminal annunciator is illuminated when 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 10 APPROACH ANNUNCIATE When performing approach navigation the approach annunciator illuminates when approach 15 active 4 5 1 11 INTEGRITY ANNUNCIATE The integrity annunciator illuminates when the GPS receiver detects a position error or 1s unable to calculate the integrity of the position 400 SERIES INSTALLATION MANUAL Page 4 9 P N 190 00140 02 Page Rev L 4 5 1 12 ILS GPS APPROACH Output Sinks 500 mA when GPS navigation is selected and GPS approach is active or when VLOC navigation is selected and an ILS channel has been selected This output may be connected to the ILS Engage input of an autopilot or flight director to provide higher autopilot gain while the 400 Series unit is operating in the ILS or GPS Approach modes of operation 4 5 1 13 DEMO MODE SELECT This discrete input may be used to select Demo Mode on the 400 Series unit A low on this pin at time of unit power up invokes the Demo Mode Demo Mode allows the 400 Series unit to simula
159. ving a standard RS 232 load 4 6 2 2 ARINC 429 _Pin Name Connector Pin VO X 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 15 5 2 16 and 5 2 1 7 for the Stormscope configuration Refer to section 5 2 18 for the Skywatch configuration Refer to sections 5 2 18 and 5 2 19 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 15 5 2 16 and 5 2 17 for the Stormscope checkout Refer to section 5 2 18 for the Skywatch checkout Refer to sections 5 2 18 and 5 2 19 for the TCAD checkout 4 6 5 Serial Data Interconnect Refer to Figure 4 11 on page 4 41 for the RS 232 serial data interconnect Refer to Figure 4 12 on page 4 43 for the ARINC 429 Bendix King EFS 40 50 interconnect Refer to Figures 4 13 4 14 and 4 15 starting on page 4 45 for the ARINC 429 Sandel EHSI interconnects Refer to Figure 4 16 on page 4 51 for the ARINC 429 air data IRU AHRS interconnect Refer to Figure 4 17 on page 4 53 for the ARINC 429 flight control interconnect Refer to Figure 4 18 on page 4 55 f

Garmin 420 GPS Receiver User Manual

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