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400 SERIES INSTALLATION MANUAL - Contrails

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1. MAINO 39N383434 NMOHS SLINA N3HIO dO SLNONId JHL J H3A3MOH Sd9 FHL J13NVd LNOY4 JHL NO NOLLVASOJNI 193NNOOS3INI LNONId 3Ld31dWOO 318VIIVAV SI NOILVIONONNV ONIHOLIMS 3AVS JHL 3ONIS 804 NOILVINAWNOOd SYsdNLOVANNVW OL 434339 Z SYOLVIONANNY YO S3HOLIMS 310W34 dO 3SN LNOHLIM Q3HSIldWO22V SVM 831435 OOF 3Hl JO NOILVOIJILS3O TVILINI Z OT OND OO Sd9 NO NOILONN4 ON 3AVH Z 1 SZ SNId lOOtd 9 Q310N 3SIAM3HIO SS31N Q M39NVl HO OMV FZ S3MIM TIV 71 S31ON S JLON 335 GZ 19313S JGOW OWA Y JLON 33S 9 INO MV j9V9N3 532117201 yy g Ze v HOvOMddV Sd9 SlI LG6Zd LZ6ld ld S6Z OM Z6L Om saynduog Jojpiounuuv d 007 94 OSL 94M GG wayshs 2 INT ie 6 ALVIONANNYV ALINO3INI o IG on bury xipueg Bury xipueg 99 S JLVIONNNNY HOVOMddV Sd9 r 31VIONDNNV IVNIWeH3L Jopolounuuy L J1VIONNNNY S80 5 8 ALVIONANNV OLAV Z 31ON 33S 4 O3S Sd9 LZ 19313S 3GON S80 Jopolounuuy Z 31VIONDNNV Sd9 9 QNV SALON 33S 5 31VIONDNNV 201A d9 201A e 1293135 393n0S 102 Jopolounuuy JLVIONANNVY LNIOdAVM 1dM 9SN 9 ALVIONANNVY 39VSS3M 10074 cO OV 100 061 N d W A941 erq Ob A 232d 6E A 2824 TVANYN NOLLVTTV LISNI SHTWAS 00t JO9UUOTI9 U ejeq ees ZEZ
2. SMO193NNOO 9 JNVMGYVH AOYY SJANIONI 99 v 64 65 0 sqi SL 1H9I3M SMOLO3NNOO 7 JYVMGYVH AOYY ONILNNOW 69 poz Gy 1H9I3M LINN ww HONI SNOISNAWIG S310N mi amp 0 0008 OL LL Ler i 1l i i ee 1 C i 69 0 S 6 roos 026 99 29 CE 2052 S86 ae 1 89 ogo z N Y LL E SEEN 2015 SO d tre cee MOV JGISNI SO 001 9690 9510 118 2 9601 7892 08901 0 OvZ OSv 6 zzi o s SL vv 2911 g szi m 1 O 9091 oze 9 q 1 S 8G1 0529 ez Le zit O 099 cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 W 91 01 4 282d 6 4 9Seq suoisueuiig 00t Sd9 v 3 enDi4 69 9091 SYOLOJNNOO 9 JYVMGYVH ONILNNOW SJANIONI NOILVOO1 99 v 090 sql 7 LHOIGM SMOIO3NNOO 29 JYVMGNVH MOVE ONILNNOW 64 z Sal g e 1H9I3M LINN Z ww
3. 9Vl4 TWOILYSA 9Vid TWOILYSA NMOG NIVA 9V14 IVM31Vl NIVW OV14 T1V331V1 NIVW LHOIN NIVW 1491 NIVW HOVOUddY 549 511 8 LNO 6cv ONIYV Sd9 V LNO 62 ONIYV Sd9 8 1 NI 62 ONINV Sd9 V L NI 627 ONINV Sd9 LNO 6 ONIMV STI YOA V 1nO 6 ONINV STI YOA ZH OS SND NINYV9 90A 82 SALON Z W31SAS 93219533 E E a A a A I 05 9v14 lVOILM3A hs 6z 9YJ4 TWOILYSA I VY S ES A A A 8z NMOG B LZ dn CJ VY VY Bn us T A A vc 9vii 1v331v1 ez ovii 1 d H I a E I LHOIM A ey sci zz 14314 lt H iz I l 39V9N3 N3ZIv201 z v X tojrdo4ny ost Pv 29 N y qaxv132 W31SAS AVN Z XAO Z 310N 4 OMINOO 3OMhOS Ido Z ES ES T 8 XM 6Zr Z Ly V XM 6zy 92 0 0 U 9 8 XM 1 677 82 A V XM 1 67 01 z x 8 XL 1 67 6z A 6v V XL 1 624 LL H H ay AVi3N 9NIHOLIMS Z 849 iz 10074 ONIHOLIMS Z AVN 4HA S 20A 82 S1I YOA Q3ZI933N3 2 2 A ES T g XN Z 6Z LZ D t
4. jION 33S AAN ama Qc 2 WHOM 01 J Z AVAA WHOM OI GI a cc P WE Z C ES OG g 6 S Sd9 Pid 1 33S B c n T STIJYOA T Yz gv D Z ZY C A 9Z ey w E GZ LZ A A ZZ Oc D D LZ v80Zd LOOT d V80Z IM Buly xipueg 9 YOLVLIS 590 d MOIVIS 590 3 MOIVIS 590 NIVW d dOLVIS SO NIV 9 YOLOY 590 H S80 JLVIONONNY HOVOdddv S9V j 1 43171 9v laa bv WOus Ol NIVN 914 NIVW 1441 00 NIAMVO W 93I T0 0t 100 061 N d ueq 88 4 23ed LE A 98eq TVONVW NOLLV TIV ISNI SATAAS 00 2euuo2Joju seuoiMS s1ojerounuuy 81 4 4 NOLLYTIVISNI livMONIV NV NI 3SN LON OG 300W ON3qQ NI LINN LYVIS OL GJGNNOND 38 AVW SZ 00Fd 103135 IAOW OWA G GNOOAS Yd4d JONO JAIM GNOOASITHIW v sindino 91 100td 1nO MYVW INIL v Og Y SNO JHL dO LNOYS AHL NO NOLING 109 SV 0 jNVS FHL 533435 HOLIMS V NOLLVIIVISNI 067 SN9 V NI GaSN 38 HOLIMS ON YOLVIONANNY YOLVIONMNNV HOLIMS Sd9 201A ANVIN3WON TVN2331X3 NV AON39V NOILVOIJILH3O XNOA GAYINDAY 38 AVA SYOLVIONNNNVY ANY S3HOIIMS 310W3M 3Hl 40 TIV YO ANOS MJI JO 913153 IVNNSON 5 1019 3HL Q3TIVISNI LON SI LINN
5. VNNALNV Sd9 O gr be L v OL 21 LL 6 9 81 re LS O1 Sn8 ONILHON IH Sn8 ONILHON Be z LL oz YIMOd LAVYONIV OQA 84 71 SS i el ava LINDHID Sd9 A A 0 M 62 E Z 310N 33S I A 82 NM J 12 T r x Z 92 SZ A A ZZ iz Loord Sd9 NOWWOO 1 L NI CZ SH Sd9 sNa NILHON IH 509 SNILHSIT1 aNNO X9 LAVYOUIV aNNOX9 LAVYONIV 43MOd LAVYOUIV 43MOd LAVYONIV OV14 WOILYSA OVI14 TWWOILYSA NAOGQ NIVA dn SV j Vi3lVl OV14 JVM31Vl NIVW WO84 t NIYW Ol LHOIN 1491 NIN AVO Figure F 12 GPS 400 Typical Installation Page F 25 Page F 26 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Rev M W 93I G ue q 87 4 98eq Z 4 9Sed 12euuoa19e1u euu uv pue BunuBir amod 1 4 4 007 Sd9 01 v0500 110 ANY V OZvY OND 01 22800 110 0 90800 110 v Og v SND 01 99800 010 0 08200 110 LYVd OL AINO S3llddv Y3MOd JLVNYSZLIV T1VNOILdO G4SN LON 34V SINdLNO 9Vvi4 ASSHL 41 vrv 900vd NO Qq3NIn034 SI NOILO3NNOO YIMOd ON SLNdLNO 82 900vd 91343905 39401530119 si 900vd 9v1443dhnS 201 80A FHL YAMOd 5301 VH 900 d LAdNI YAMOd l4JVsOsIV AHL LIN YOLOZNNOO 3114405 OSIY ONIGNL YNIY
6. 01 Oldnv SIN WOO Ol Q 8l A3M 1 WOO r OIQnV OIN L WOO LL g d 9 01 Olanv WOO 01 A N 61 IH Oldnv 1 WOO 6 g L Ove VWO id e Z NIAMVO omy 81 A v1 VOI 82 vs e 318V1 ANY v 31ON 33S N3MOd LAVYONIV LL NY SNV 81 00 4 NOWNO9 LNN XI 148 ZO 12 v8 zg Lg vv ZV VNN31INV FT IV Woo O rq yO0rd Japoouq YNNILNY 7 JO 4 ly 599 O 00rd QNhOMO M3MOd e 09 vO 3aniunv L ZO aaniuv LO 3aniuv Ol va 3aniuv Zk zg 30NLILIY LL ig 3qniulllv 6 3qnilllv 9 zv 3aqnllllV S Iv 3qnilllv yq 3qnilllv 9 1nO Zez SM OZ LS O1 9NILH N Ov LES X19 N NS V9 P IH Sn8 NILH N 6e 8 LL OZ 43MOd Ll4VHOMIV OGA SZ Yl 6l M3 V3N8 lIQ2NI9 OZ OND 2v14 3401530119 0 9V14 3901530119 Jj 6z Z 310N 33S gt A A 82 dn tL d LZ 9V14 AVN A A a 914 AVN Z WO34 A 92 01 GZ LH9IN A A zz 310N 33S 13431 AOLDOIPU LOOYd O1 Oldnv DIN WOO A3 OIN WOO IH Olanv OJIN WOO O1 WHO OOS IH Olanv NOD WHO 00S QN 0O49 L3VSOMIV aNNOX9 L3VsOMIV 43MOd LAVYONIV 43MOd l13VSOMIV VNN3INV WOO VNN3INV Sd9 NONNWOO i nilriv L NI 54 Sd9 O1 SNE NILHON IH S8 ONILHOM aNNOX9 L3VSOMIV aNNOX9 LAVYONIV 43MOd l13VSOMIV 43MOd LAVYONIV OV14 IWOILYSA OV14 TWOILYAA NIVA NMOd
7. A 4 1 T T i A ES A og 9V14 1VOILH3A 62 9V14 TWOILYSA Ly I J z x ES ES A aA 82 NMOG BE 12 dn 1 UO J Br m 2 ES S 9v11 A A vC 1 1 ovii lt u H Jd 2 1 l x I TR LHOIN A 29 cc 1 1 14314 aby le LZ 1 io vi 39V9N3 N3ZI1V201 ME q pc M M l EN Pim S N Lv V d 9y aaxv134 AVN 6v J 8r 32N3N343H O4 NMOHS SLINN S3HIO 40 SLANONId 100rd NOILVAYNOANI 193NNOOH31NI ANY LNONId 3131dWOO 804 NOILVINSNNOOG SHSYNLOVANNWW OL 33333 f z A ez NOI1V33dO 3N3dONd N04 Z OL 135 38 LSNW LINN Z 40 IGS QNV L OL 135 38 O v OZv O00v id L 3HL 40 STI YOA AYNI SNOILYXN IJNOO IOS 3HL NOLLVINHOJNI LNONId 304 3HuVMLJOS 29974 NOILVENDIANOD ANY NOILVIN3AQ2OQ 13qNVS OL X343 JIAVYNIIIANOO JOLENS IIANYS 3Hl 40 SNid INOS Z Q310N 3SIMYSHLO SSJINN 3N39NV1 YO vZ S3HIM TIV 7 S310N ES og 62 X 8z T vz J Z A 22 Z YAN Z ALON OMINOO 3OMhOS 102 Z 310N vl T 8 XM 9 62v L 6Zfr 9z EN T 8 XM 1 627 8 LY 1 627 OL 9v Er A AA 1 627 62 6v V XL 1 627 LL CAS 8v LOOvd AY13M ONIHOLIMS Z Sd9 LZ AY134 ONIHOLIMS Z AVN 4HA S 290A 82 STI YOA Q3ZI933N3 5 8 XM 2 67 LZ ae A ez
8. MJA 1NO3J MAIA 3815 YOLOANNOO UN i p 0 01 050 puro SOld v anis ze 8 b i 111 D N J 55 5 o a T vy LOL SOV 4 89 60 d 20l c co e d lj ume Sold v P cs IAN ONIMOOT 3135 8 w ue i 60 0001 012 2 1 a D A lt A S Z s z x Z alvid ONIMOVE P i 4h p 00 1 000 SIL1 _ 1227 L dolo d E p di JN3HdO3N 1343SVO 00 20000 S 2 Qs vMsSO4 9Gv NOIIVIAV VNN31INV 00 100 10 LNOLNO 5 09 1 6 0 QS vM3OJ Sold v 8 v 881709 E X OS Z 5060 007v 06871 lt INOX YOLOAJNNOO ONG 1 N i i Co Oo co Ha e 869 66 No e Ald LAN 00 08000 S1 JOVIASNA 40 dol NO NIMS 13 JN3HdO3N 13759 00 11000 8 QS VM3O4 Sold 91 29 X ce 0if VI CLCCI LLC vv Gv 68 1 cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 qIS v 401 Z ze zi Stt INDON 39NV IJ VNN3INV 98679 00 Zv100 110 W 93I 9 4 232d 4 282d suoisueuiig yoey BununolN SND Z 4 SHOLIO3NNOO JYVMGYVH MOVE NILNNON SJANTIONI NOILYOOT 99 64 90 SG L 1H9I3M SMOIO3NNOO JYVMGYVH MOV
9. LINA 531935 OOF 531435 OOF jHl NO 03 714510 38 AVW VIVO SLI ANY Q3TIVISN SI N31SAS AMOSIAQV lddV l V LVHL ONILVOIGNI 3Hl YVAN Q331n03N SI QNVOVId V LIND AVIdSIQ 10MINOO V LNOHLIM Q3TIVISNI SI SW31SAS 144 1 3S3Hl 40 ANY 4l S 440 Qq3q4in038 38 AVW HOL SI LINA AV IdSIQ 38 qinoHs 91 440 Q33I0033 38 AVW HOL SI LINN AVIdSIQ 1OMINOO HOIVMAMS V 41 N3dO QNV NO LINN HOSS3OOMd JHL NYNL Ol M3H13901 Q3193NNOO MOHS SNId HOLIMS M43MOd HOLVMAMS FHL 38 Q1nOHS LdNO QVOl NVAS V O LINN YOSSADOYUd HOLVMAMS AHL OL MS G3aLVOIGAd V NOILVTIVISNI JHL LON 440 LINN SIHL NNAL OL V NO LINN NOSS30ONd AVOL AHL OL MS Q31V2IQ3Q V NOILVTIVISNI NI LO 440 LINN SIHL N3fl OL N3dO NO LINN XOSSJOO d JHL NYNL OL qQ3qN nO439 ld HOLIMS YOSSIOONd QVOl 3Hl v QV3lSNI Q3193NNOO 38 AWW 15 ANY 05 100 4 l1NOd NI 627 ONIYV Sd9 JHL ASOdYNd YSHLONV 304 GASN AQV3MNIV SI 6F 87 1007 lNOd NI 687 ONINV Sd9 FHL AI Q310N 3SIMSH3HIO SSJINN 33934V1l YO vc S3MIM TIV 1 S310N NI SY Sd9 c LNO ZEZ SY Sd9 d3H9IH YO LLC 34VMLJOS 0gr OZzv 00 NIASVO 3 ALVIONANNY a 8
10. SJ LON N 9 N q N _ B B eZ Ge 91 9 2 zz NOWWOO ana L Z H 9 S ey ZHMOS 3NQG 13Tlv3Vd Ge Zl H LZ 8 3 ve LZ 9 ZV ZHMOOL 3NG 13T1VMVd ZZ LZ q 61 OV ZHMOOZ 3WG 13T1VMVd CZ 6 J 6 ZHMOOF 3WQ 13T1VMVd YZ gz g Ze bU L LS ZHM008 3NG 13T1V3Vd gs LI g LI 0 ey g ec ZHWI 3WG 131T1V3Vd 6 0 Y 6c ZS 6 LZ ZHWZz 3WG YVd 3GOW AVNM 3WQG NaS 01 c OZ ZHWr 3WG Nvd O3M NVHO 3Wd XJS LI L Z 8c 82 el vi ZHW8 3WG 13TlVMVd Zd LOSd LOSd ld ld LZ9d 900td 310N 310N 310N z 310N z 310N z 310N 0 SNO v9 Y V1M L68 068 JWG Ov 3na VZ9 NM OO4DN OO4DN 5 SUI OD Bury xipueg W 93 Qerq 04 4 9Seq 69 4 9Seq 12euuo2Jeju Bulun JWA 9po3 diis a98 ve 4 e1n614 cO OV 100 061 N d TVONVW NOILVTIVISNI SHINAS 007 MAINO 3ONd ddd8 NMOHS SLINA 83H10 40 SLAONId NOILVASOJ3NI LO3NNOO8SJINI ANY LNONId 3l3ldWOO NOILVINSNNOOG SYSEYNLOVANNVAW OL 83438 NOILVENDISANOO SIHL NI NOILYXJ3dO s3dOsHd N04 VIVO ONINNL ANG aoa LAdLNO OL GAYNSIANOD 38 LSNW OC SNO AHL NOILVENDISANOO SIHINI NOILVdsdO VLVG ONINNL JANG 3009 LAdLNO OL GAYNDISANOOD 38 LSNW OC SNO FHL G4LON 3SIAd3H1O SSdINO 89394V1 YO VC
11. 3ON3383434 NMOHS SLINN YSHLO 40 SInONId NOILVAASOANI 193NNOOS3INI QNV 3id1dWOO 404 NOILVINJADQODOQG SHYsYNLOVANANVAW OL 433339 v S431131 3SVO YdddN QJ3NITS3OND SV NMOHS SYOLVNOISSG Nid 3SVO S43MOI QV3lSNI Q3193NNOO 38 15 ANY OS 100vd LNOd cO OV 100 061 N d TVONVW NOILVTIVISNI SHISIJS 007 Z NI 627 ONINV Sd9 JHL ISOdYNd N3HIONV N04 GISN AGV331V SI 6 ANY 87 L007d 1HOd NI 627 ONINVY Sd9 JHL di 4 IN3INOO Q39NVHO S3l1VOIQNI 319NV123M Q3HSVQ S Q310N 3SIMN3HIO SS31N N39NV1 MO OMV FZ S3MIM 11 1 S310N axl 29280 01 A O NI ZZ Su Sd9 ZZS ec E 9G LINO ZZ SM Sd9 S ld Sc ansa Loord 0001 SVL 1uBisu DID JIV A 8 YSLLINSNVYL SYHV NUI OG 89 89 89 LZ EEE 6v 8 NI 62v ONINV Sd9 V YSLLINSNVYL SSHV nMI L9 L9 L9 91 9Z J 9v V NI 67 ONIMV Sd9 alr IM3SNI 8 LYISNI LM3SNI ld 91 LOOrd 601 9H Z J L6 1 8VSZ40Ll 9H Oz 0 O0 Z6 001 06 18 17 jeJesp 3S8 OHV Lov NYJ NINAM VO uou uou 191 lSMAeuoH sul o2 Buly xi
12. 61 C NOISHJA 34VMLJOS SLNN 531435 00v NOILVYNDISANOD SLXOd CE S8 21419345 51214113391 ONIMVAC SIHL 39Vd dVW AHL NO G4aAVIdSIG 38 OL VLVG 0O0S XM MOTIV LON TIIM 39YNOS ONIGVSH 399315 V 39 05 ONIGVSH VIs3S V JAVH ISAW 00S XA JHL NO JOYNNOS ONIGVIH TVLI9IC 81 9 C e 95 L 6S L6vd Loord 9 9 y QNV S3lON 33S 1004 S Zd 9 HOLIMS NV310 TVN331X3 1VNOlLdO OZ H 7 5 T Aq 8 Ly rS e Loord Y NI SM Sd9 Y cgc SM Sd9 gq3H9IH L 2 3HVMLd3O0S ocr ozry oor NIAMVO V JAVH LSNW LINN 531435 007 3Hl 39Vd S LINM 531035 OOF AHL NO d3AVIdSId 38 OL VLVG 00S XA X04 YACHO NI Q31ON SSJINN N3984V vc S3MIM TIY 6 SALON W 91 Qerq 86 4 9Seq 15 4 9Seq 199uuoo1 1ul JGued oipny gz J cO OV 100 061 N d TVONVW NOILVTIVISNI SHINAS 007 e 8I O1 OIGNV DIN WOO 3Nvd OIGNVY 1 LV 9NI QNnONO V OL Q3193NNOO o G IH DIN NOOMA3INI 38 GINOHS LI O1 V 3AVH LON S3OG 13NVd 9 IH OlGNY DIN WOD Oldnv di Q3193NNOO 38 LSNW SLNdLNO
13. V XM 2 67 6 M ve ES 900rd I ge x 3SN3S AVIAN 2 1 AVN Z ALON 8 T ponies l Sd j a q3XV133 pidsi 80 NS a 1951 L SU YOA E X 1 0g o A Iu 6c T 2 x 8c 9 1 my FA Le 1 ond A vZ HOLIMS z gc S24 zz XAJ ALON H IZ JONINOD 3ONhOS Ido Z ALON 8 XM 6ZY L A V XM g 6zy 92 x X Cope x 8 XM 1 627 82 A 4 A Ly V XM 1 67 01 O PEE 9v 2 QC pas 8 XL I 6ZY 62 A AS 6v V XL 1 674 LL J d Hy gr 10074 AVIAN SNIHOLIMS Z 549 z L v AV134 ONIHOLIMS Z AVN 4HA S 8Z Z S1 YOA G4ZIDN3N3 za 2 67 LZ es i x n puer ez V XY 2 67 6 te OU gt ve HP 3SN3S 2 1 AVN Z ALON SS 90074 S N d gOccNs Q3xv133 L Avjdsiq DUAE L STOA ISH3 624 ONI Y OV14 TWOILYSA 9Vid TWOILYSA NMOG NIVA dn NIVW 9Vi4 1V8H3lVl NIVW 9Vi4t 1V331V1 NIVW 1H9IM NIVA 1431 HOvONddV 599 511 8 INO 6 ONINV 599 V INO 6cv ONIYV Sd9 8 NI 627 ONINV 599 V NI 6zv ONhV Sd9 8 LNO 62v ONINV STI YOA V INO 6Zr ONRhIV STI YOA l OSY SND NINYV9 Figure F 23 ARINC 429 Sandel EHSI Interconnect 2 GNS 430 2 Sandel SN3308 Page F 47 Page F 48 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Rev M IN erq 06 4 28ed 6F 4 2824 19 uuooi lul StiHV ntll g1ed 41V ZEZ SH 67v ONIHV bZ 3 e1nBiJ
14. W 93I 29 4 9Seq 9 4 9Seq 99UU0919 U IgO IINH 0 4 9Jn 14 AINO dONd8Sddd4 NMOHS SLINA 83H1O 40 SLNONId NOILVNYOANI 193NNOOS3INI LNONId 3131dW02 NOILVIN3AQOOQ SYFYNLOVANNVW OL 33332 f 39Vd 911NOO S80 109 NIVW JHL 30 073135 390Nn0S 180 IHL NO4 Sd9 SAVMIV 1031345 ANY AVYOVIG WOLlLOS8 3Hl Yad SV TIVISNI N3lNlOd INY FHL HOLIMS 31VsNVd3S V JSN OL Q3MIS3Q SI dl 39Vd 911NOO S80 109 NIV JHL 4O 07313 3O8Nn0S 180 IHL NO4 109 MOVYL 10313S WVY9VIG dOL JHL Yad SV TIVLSNI OSY SNO 40 13NVd 1 84 3Hl NO NOLLNG 109 3Hl HOLIMS OL YSLNIOd INY 3Hl 303 Q3NIS3Q SI dl Z Q31O0N 3SIMN3HlO SSFINN 339NV1 HO OMV vZ S3MIM 11 L S310N C Gy ONAS 190 vy VIVO IdO NIVW e gy 49010 190 NIV Sd9 LOOf d 2 2 Se ONAS 180 N vc LE o _ B ze C e ONAS 190 viva 190 1 91 nm 61 C3 A We i muc CUM aT C _ _ EAS C Le VLVG 190 49019 180 LL L g 21 ME V AO O O GZ 40010 190 12694 12889 12884 L6ZZd TH 1 dAD
15. 1 TV OL GNNOdNOD 9Nb4201 Addy 9 Wid NOIO3NNOS JO MIA NV3u J JA NV3 TISHSHOVE N3AO SLVIdLAN dvNs S an ENSE 5508 HO193NNOO OLNI NOIIN3SNI 330438 u TI3HSXOvH H NOYHL S3NIM SS3NNVH O334 v OH NO G3N3IN3IO 310H HLM 3119 NO193NNOO of lo OL A1ddv ONIMOVE SAISSHGY MONI ae II NOLOANNOD O 1LSS00 110 jO lavd Z u _ is O Nee O Sd9 An8W3SSv 3lV1d OVA 0 9 900 110 jO lavd 1 LOO rd SALON NOIO3NNOO LAN of sje Er qNnoso a 00 S7000 Sz1 Z S 01315 WIO 06 0Z2200 0 OGO 00 zzooo ziz T CD Q O3M dl 0351 ION O 80 t0Z09 LLZ JSN z SSO8 VMLIX3 Y L0 9 000 SZI e 00 29000 zsz O L0 sooo o 1 Pd SS fe S sod Z AL M 2 ZI 7 209 112 S _ a SOld Z ZL vEZE9 L1Z 9 E 9 10 Mr nas RSS SO1d OZ 00 62000 99 xc PME eii aT OZ 82200 0 QgO3M SV 00 12000 9 84 368100 0 N ae m S RI n a LN 00 Z00 SL Z sold zZ 7 80 rv9209 112Z N IN 81 4 98eq LI A 9Sed suoisueuilg 1nojn2 senes oor 8 3 4 OVvONJ3 LON AVA SYOLOSNNOO 54445 OOv JHI JNVd LaVdOdIV Jl JO 39Vv3sf1S JHI ONI
16. 9V14 JVi31Vl NIVA S9V i 1V331V1 WONJ4 01 NIVA LHOIM NIV 1431 NIVA ONO NINYVO Figure F 11 GNC 420 Typical Installation Page F 23 Page F 24 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Rev M NONNWOO vO co LO vd ca Ld vv V LV vd 4epoouj 10 J8J8UJM V ONIMVHG L193NNOOS3INI YOLVOIGNI 3i1VisdOdHddV FHL OL 33438 d3MIS3O SI JOVANSLNI 590 NV dl S8ONM 007 Sd9 FHL ONISN 38 Ol Q33N TIIM SNOILO313S ASYNOD 590 007 Sd9 JHL OL JGVW LON SNOILO3NNOO S80 41 SNOILVYAdO HOVO3SddV NOISIO33d 9 3890104 N04 1VNOISIAOHd SI S9V14 NOILVIA3G TWOILYSA NOILO3NNOO NOILVOINENd dO LV TWNOILVYAdO LON 383M SLAdLNO NOILVIA3G WWOILYSA Sd9 AHL C Q310N ASIMYSHLO SSJINN 393984V1 9MV VC SAYIM TIY L GNNOYD s3MOd vo co 19 va c8 L yV V ACN LIL LV va INO cec 54 J lt lt lt lt lt lt lt lt lt lt LCS X19 NIWSVO 9V1i 3dO1S3q1 19 S9V 3j 3dO1S3Ql19 NMOG dnt 9V14 AVN S9V 3i AVN WOYs 01 1 914 3LON 33S 51 JOLDOIPU UOILOBIADN
17. 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page D 3 Rev M 0 6 2 SHADIN G FORMAT lt STX gt GA012 lt CR gt lt LF gt GB345 lt CR gt lt LF gt GC678 lt CR gt lt LF gt GD lt t gt 9012 lt CR gt lt LF gt GE lt t gt 3456 lt CR gt lt LF gt GF lt gt 78 lt CR gt lt LF gt GG lt gt 90 lt CR gt lt LF gt GH123 lt CR gt lt LF gt G1456 lt CR gt lt LF gt GJ lt gt 78 lt CR gt lt LF gt GK lt gt 901 lt CR gt lt LF gt GL234 lt CR gt lt LF gt GM5678 lt CR gt lt LF gt t GN90123 lt CR gt lt LF gt T GO4567 lt CR gt lt LF gt GP89012 lt CR gt lt LF gt GQ001 lt CR gt lt LF gt GR6789 0 lt CR gt lt LF gt T Ga lt gt 1234 lt CR gt lt LF gt Gb56 78 lt CR gt lt LF gt G 901 lt CR gt lt LF gt lt ETX gt Where GA ASCII characters 012 represents indicated Air Speed knots GB ASCII characters 345 represents true Air Speed knots GC ASCII characters 678 represents Mach Speed thousandths GD ASCII characters sign 9012 represents pressure altitude tens of feet GE ASCII characters sign 3456 represents density altitude tens of feet GF ASCII characters sign 78 represents outside air temperature Celsius GG ASCII characters sign 90 represents true air temperature Celsius GH ASCII characters 123 represents wind direction degrees from north GI ASCII characters 456 represents wind speed knots GJ
18. 6 6 BE P s vz 3SN3S AVi3H Z AVN Z 310N eo 900vd S N d V Apidsi 90 NS q3xv133 Iq l pups ST YOA OV14 TWOILYSA SV j TWOILYSA NMOd NIVW 14 1V331V1 NIVW 14 1V331V1 l1H9IM 1431 HovoNddV 549 511 8 LNO 62v ONINV Sd9 V LINO 627 ONIJV Sd9 8 NI 62v ONIYV 599 V NI 627 ONISV Sd9 8 LNO 6zv ONINV STI YOA V INO 6Zy ONINV STI YOA L Of SNO NINYV9 Figure F 22 ARINC 429 Sandel EHSI Interconnect 2 GNS 430 1 Sandel SN3308 Page F 45 Page F 46 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Rev M AMINO 3ON33343H HO4J NMOHS SLINN N3HlO 4O SLNONId NOILVNYOANI LOANNOOYSLNI ANY LNONId 3l31dWOO YO4 NOILVIN3ADQOOQ SYAYNLOVANNVAW OL 433332 f NOILVH3dO 33dONd Z OL 13S 38 LSNW LINN Z 3HL JO IGS FHL ANY 1 OL 13S 38 LSNW O r 0Zr 00Fr L 3HL 40 STIZYOA AYNI SNOILVHn9I4NOO IGS JHL NOILVAYOAN LNONId 304 JYVMLIOS NOILVYNSISNOD ANY NOILVLNANNOOd 13QNVS OL 33434 FIEVENSISANOD 8OEENS 13Q0NVS JHL 4O SNId AWOS Q310N 3SIMH3HIO SSFINN 33934Vl YO OMV vC S3MIM TV I
19. The GNC 400 series software has been developed in accordance with DO 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 in accordance with D0 178B for Level D software as documented in EDE Prediction Program Software Accomplishment Summary GFN 005 001 62 04 Revision A A list of the technical data required by TSO C1292a and the other TSOs 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 110 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 Traceahility Matrix GPN 005 00077 64 Revision AJ 400 SERIES INSTALLATION MANUAL Page B 7 P N 190 00140 02 Rev M 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 Naviga
20. 3ZI9M3N3 511 ALISOdNOD 201 H0A ANNOYS 25 H3MOd S80 S9v14M3dnS S9V14 9 NOILVIA3G 133A WO34 0 L S9V14 NOILVIA3G 1V1 Oldnv STI YOA 900Vd YOLOANNOOD 057 NINAVS ISH3 SI43 6ZY ONIMV 43MOd LAVYONIV HOLIMS YSASNVEL WOO 310W38 HJAIJOSNVSHL WOO 3NOHdO32IN AV IdSIG Ya4SNVAL 31038 WOO Olanv WOO SIN WOO A33 OIN WOO 320 1831NI LINSNVAL X M3MOd SIN WOO8S3LNI ZOOVd MOLO3NNOO Og v OZY NIWMV9 TANVd Ol anv VN3831IX3 SYOLVIONNNNY SAHOLIMS 9 v STIIJYOA Sd9 ISH IGO NIVA IN HOvONddV Sd9 SlI INO ZzecSM Sd9 LNO 6cv ONIYV Sd9 NI 6 ONINV Sd9 L 5054 Sd9 SYOLVIONANNY S3HOLIMS 4009 AV39 S80 5971343415 SOV14 NOILVIA3O 183A Wous Ol c92SM Sd9 S9V14 NOILVIA3G LYI EDITORS sap LINO NVA ANIL sna ONILHON IHO X M3MOd LOOvd NHOLIO3NNOO Ogv OZv OOY NINYVD 43MOd LAVYONIV WALSAS TOYLNOOD IHON M3JZITVIM3S MO Viva Miv 13n4 Y4ALAWILIV INIGOONG 711358030 ocr NIN V9 NOILVLNSWNYLSNI 1VNH31X3 Sn8 SNILHOIT L3VNOMIV 43MOd LAVYOUIV Figure F 9 400 Series System Interface Diagram Page F 19 Page F 2
21. 9 14 V831Vl OV14 1V3831V1 WOds NIVW 1 914 NIVN 1431 OSV SNO NIASVO Figure F 10 GNS 430 Typical Installation Page F 21 Page F 22 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Rev M LINN qavoa WOO 3Hl NO 1NdNI YaMOd L3VMOMIV AHL O 90SG00 110 N d OZv OND 9d SIOA 82 71 01 90800 110 N d OZ OND 01 49800 110 N d VOZY 00 42800 110 N d VOZY 2 SLIOA 82 00 90S00 110 N d OZ OND 40 YSEWAN LYVd JHL NO IN3ON3d3Q SI ZO0O0rd OGA 11 38 AVW LO0vd QNVO8 NIV 3Hl OL LNdNI N3MOd LAIVYOUIV F SNIAV3Q L93NNOOS3INI NOLVOIQNI 31VlsddOsddV 3Hl OL 333389 Q3MIS3Q SI 30VJM3lNI 590 NV il SONY OCH JHL ONISN JGVW 38 OL Q33N THA 5 011937135 ASHYNOD S80 TIV OZ OND JHL OL JCVW LON SNOILO3NNOO 590 dl 5 SNOILVYAdO HOVOUddV 51934 9 3YdYNLN4 YOS IVNOISIAOHd SI 597154 ANY NOILVIASG 1V2I143A 40 NOILO3NNOO NOILVOIIEAd dO ANIL LV TWNOILVYSdO LON 393A SLAdLNO NOILVIASG WOILYSA Sd9 AHL Q310N ASIMYSHLO SSJINN 33984Vl HO vc SAYIM TIV L S310N
22. 400 SERIES INSTALLATION MANUAL RPS 400 GNC 420 A and GNS 430 A GNC and GNS are trademarks of Garmin Ltd or its subsidiaries and may not be used without the express permission of Garmin GAS 30 F er J ANG p Nds DEFAULT H GNS 430 Shown 190 00140 02 Revision M July 2004 Copyright 1998 2004 Garmin Ltd or its subsidiaries All Rights Reserved Except as expressly provided herein no part of this manual may be reproduced copied transmitted disseminated downloaded or stored in any storage medium for any purpose without the express prior written consent of Garmin Garmin hereby grants permission to download a single copy of this manual and of any revision to this manual onto a hard drive or other electronic storage medium to be viewed and to print one copy of this manual or of any revision hereto provided that such electronic or printed copy of this manual or revision must contain the complete text of this copyright notice and provided further that any unauthorized commercial distribution of this manual or any revision hereto is strictly prohibited Garmin International Inc 1200 E 151 Street Olathe KS 66062 USA Telephone 913 397 8200 Aviation Panel Mount Technical Support Line Toll Free 1 888 606 5482 Web Site Address www garmin com Garmin Europe Ltd Unit 5 The Quadrangle Abbey Park Industrial Estate Romsey 8051 9DL U K Telephone 44 1794 519
23. 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 e 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 ensuring that the ICA is made part of the applicable section 91 409 inspection program for their aircraft This is accomplished when a maintenance entry is made in the aircraft s maintenance record in accordance with section 43 9 This entry records the major alteration and identifies the original ICA location e g Block 8 of FAA Form 337 dated along with a statement that the ICA is now part of the aircraft s inspection maintenance requirements Page A 2 400 SERIES INSTALLATION MANUAL Rev M 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
24. such that carries are discarded to give a one byte result The ASCII coded decimal representation of that byte is given ranging from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 Page D 4 Rev M 400 SERIES INSTALLATION MANUAL P N 190 00140 02 0 6 3 SHADIN S FORMAT lt STX gt SA012 lt CR gt lt LF gt SB345 lt CR gt lt LF gt SC678 lt CR gt lt LF gt SD lt gt 9012 lt CR gt lt LF gt SE lt gt 3456 lt CR gt lt LF gt SF lt gt 78 lt CR gt lt LF gt SG lt gt 90 lt CR gt lt LF gt SH123 lt CR gt lt LF gt S1456 lt CR gt lt LF gt SJ lt gt 78 lt CR gt lt LF gt SK lt gt 901 lt CR gt lt LF gt SL234 lt CR gt lt LF gt SM5678 lt CR gt lt LF gt SN90123 lt CR gt lt LF gt S04567 lt CR gt lt LF gt SP89012 lt CR gt lt LF gt SQ345 lt CR gt lt LF gt SR67890 lt CR gt lt LF gt SS123 lt CR gt lt LF gt ST456 lt CR gt LF gt SU789012 lt CR gt lt LF gt SV lt E W gt 345 lt CR gt lt LF gt SA ASCII characters 012 represents indicated Air Speed knots SB ASCII characters 345 represents true Air Speed knots SC ASCII characters 678 represents Mach Speed thousandths SD ASCII characters sign 9012 represents pressure altitude tens of feet SE ASCII characters sign 3456 represents density altitude tens of feet SF ASCII characters sign 78 represents outside air temperature Celsius SG ASCII characters sign 90 represents true air te
25. 45 _ O High Temperature Mime PO Decompression 7 POR Humidity 60 apmenresedioCHegoyA x Sk OCS Equipment tested per DO 160C Par 7 3 1 and 7 3 2 Equipment tested without shock mounts to Categories B M amp N Eun 90 Category X no test required Magnetic Effect Equipment tested is Class Z Voltage Spike Equipment tested to Category A Audio Frequency Susceptibility Equipment tested to Category B Induced Signal Susceptibility Equipment tested to Category A Radio Frequency Emission Equipment tested to Category Z Salt Spray Equipment identified as Category X no test required Radio Frequency Susceptibility Equipment tested to Category T 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 5 P N 190 00140 02 Rev M A 5 Environmental Qualification Form GA 56 NOMENCLATURE GA 56 GPS Aviation Antenna TYPE MODEL PART NO 011 00134 00 Stud Mount 011 00147 00 Flange Mount TSO COMPLIANCE C129 Class A 1 MANUFACTURER S SPECIFICATION AND OR OTHER APPLICABLE SPECIFICATION 004 00015 00 MANUFACTURER Garmin International Inc ADDRESS 1200 E 151 Street Olathe Kansas 66062 NOTE The following information provides examples only It is not
26. 8 AVN V AYNI L AV 1dSIG 143 6Zr ONIMV YO4 NOILVIN3AQn20Q SYSYNLOVAANVW OL 333343 G IVONVA NOILYTIYLSNI Zf QV9 3Hl OL 33333 js4n00 d319313S Sd9 YO4 Q3MInOd3N SI Zr QVO NIWHNVO V 3NVd 10MINOO 5143 JHL VIA JSYNOD Sd9 FHL 40 NOIIO313S 1MOdd S LON S3OG 32V4N31NI 78 5143 SNITIOO Q312ld3Q0 FHL F Qv31SNI d3193NNOO 38 AVN LS QNV OGS 100vd 1MOd Z NI 6Zv ONINV Sd9 FHL 3SOdHfd N3HIONV 304 Q3Sn AQV3MTIV SI 67 ANY 87 10074 1MOd NI 6Zv ONIMV Sd9 JHL dl NOILVM3dO M3dOMd HOS Z OL 13S 38 LSNW LINN z JHL 40 IGS JHL QNV L OL 13S 38 LSNW 057 07 00 LZ 40 STIZYOA GNV AYNI SNOILVYNSISNOD IGS 3H1l Z Q310N 3SIMN3HIO SSJINN N39MV1 SAV 2 S3MIM TI S310N I E GZ 621 SZ INO 6Zv ONINV STIZYOA g SZ vz v LINO 6Zv ONINV STI YOA r A 6z AINO 08 9 900 c9 921 A O A A LY 8 LINO 6zv ONINV Sd9 79 ZZL 9 v LINO 627 ONINV Sd9 Ec 891 19 OZ A A 6v 8 NI 657 ONINV Sd9 Y 310N 33S 310N 33S LY 8v V NI 6Zv ONIMV Sd9 8zG9vd VZG9vd ld LOOrd S9v 9S v8 ndd Z 7 05 07 S43 7898 5143 Cit Oz Ocv 00v x puag sullloo NINHVSOS T SZ g
27. ASCII characters sign 78 represents rate of turn degrees per second GK ASCII characters sign 901 represents vertical speed tens of ft minute GL ASCII characters 234 represents heading degrees from north GM ASCII characters 5678 represents fuel flow right Twin only tenths gallons hour GN ASCII characters 90123 represents fuel used right Twin only tenths gallons GO ASCII characters 4567 represents fuel flow left or Single tenths gallons hour GP ASCII characters 89012 represents fuel used left or Single tenths gallons GQ ASCII characters 001 represents error log reason indicator 001 temp sensor error 000 no errors GR ASCII characters 6789 0 represents fuel remaining gallons Ga ASCII characters sign 12 34 represents barometric corrected altitude tens of feet Gb ASCII characters 56 78 represents current barometric pressure setting inches Hg G ASCII characters 901 represents checksum lt STX gt start transmit character 0x02 lt CR gt lt LF gt lt gt carriage return character Ox0d line feed character 0x0a sign indicator Ox2b or Ox2d lt ETX gt end transmit character 0x03 T Not available from Airdata Computer Note Checksum is calculated by adding each byte in the message including all characters from lt STX gt up to and including the error log reason indicator
28. INO 6Zv ONINV Sd9 V N3AI3034 Z AYNI M 9y V INO 6Zv ONINV Sd9 LOOFd dVMIS ONIM331S T1OM r 2 Z g 1VN3N39 OZr SO4V 6r 8 6zv ONINY Sd9 V 7VN3N39 OZ 947 a a ss ay V NI 6Zv ONINV Sd9 V N31SAS AVN M3AI3038 AYNI X LY INO 6Zv ONINV Sd9 V N3AI3934 1 AYNI X Z 9y V INO 6Zv ONINV Sd9 ZO rd 10 LOOFd i ozy dO L O v OZY 0OO0 LUSLS S 9 OOv 24M i Buly xipueg INAV O 3ONd 8343M N04 NMOHS SLINA 40 SLNONId NOILVWYOANI LOANNOOYFLNI ANY LNONId ALAIdNOO NOILVIN3ADnOOQ SYSYNLOVANNVAW Ol 433332 6 SLYOd ZEZ SM 39004 AHL ANY NO Q310d1l3S 38 NVO 1VW3Oj VIM3S LVHL HONS NOILVLINIT SIHL dAVH LON S3OQ 33l1V1 MO OZ C NOISH3A JYVMLIOS SLYOd 21412345 3S3Hl SAYINOAY YO 61 C NOISH3A JYVMLIOS NIVA SLINA 531435 OOF 40 NOILVYNDISNOD SLYOd CE 54 21419345 SilJILN3dI ONIMVAC 5 8 39Vd FHL NO G3AV1dSIG 38 OL VLVG HOLVMANS MOTIV LON TIHA 39O8nOS S9NIQV3H HN3dd3lS V 4J XNOS SNIQV3H IYIXJS YO V JAVH ISAW 3Hl 3ONnOS 9NIQV3H TVLIDIC V 3AVH LSNW LIND 531435 OO FHL 39Vd S LINM 531035 OOt 3Hl NO Q3AV IdSIGd 38 OL VIVQ HOIVMADS 304 s3Q0HO NI Z AOUNOS SNIQV3H IVLISIC V 3AVH LSNAW LINNA SJIXIS 007 JHL 39Vd S lIN 531035 AHL NO G3AVIdSId 38 OL Old3V31 GVOL NVAY N04 YACHO NI 9
29. J S KPI32 B P 6 Bendix King BF Goodrich Ryan Weather Traffic KTA 870 SKY497 Skywatch 9900B BX KMH 880 SKY899 Skywatch HP WX 500 Page E 2 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 Appendix F DRAWINGS AND INTERCONNECTS F 1 INTRODUCTION This section contains installation drawings to aid in the installation of a 400 series unit Additional information and notes included on the drawings can be used as reference information during installation F 2 DRAWING LIST The following drawings are included in this section Figure F 1 GA 56 Antenna Installation Drawing Figure F 2 GNS 430 Mounting Rack Dimensions Figure F 3 GNC 420 Mounting Rack Dimensions Figure F 4 GPS 400 Mounting Rack Dimensions Figure F 5 GNS 430 Mounting Rack Installation Figure F 6 GNC 420 Mounting Rack Installation Figure F 7 GPS 400 Mounting Rack Installation Figure F 8 400 Series Recommended Panel Cutout Dimensions Figure F 9 400 Series System Interface Diagram Figure F 10 GNS 430 Typical Installation Figure F 11 GNC 420 Typical Installation Figure F 12 GPS 400 Typical Installation Figure F 13 Power Lighting and Antenna Interconnect Figure F 14 Altimeter Interconnect Figure F 15 Main Indicator Interconnect Figure F 16 KI 209A Main Indicator Interconnect Figure F 17 KI 208A Main Indicator Interconnect Figure F 18 Annunciators Switches Interconnect Figu
30. SNOISN3AIG L S310N 12202 0008 Ol LL zev i i i PS ce 51 2 084 O i 60 08 ooze 9979 zo sz See 1 89 089 i E c 7 Y 3015 Yad 219 cec Move 3GISNI MSO 001 96 90 9510 m 8 84601 17892 0901 m O OvZ OGv 6 m cci 8v z9 1 sie StL e oze 9 lt H i 5 86 ocz 9 A 18 Z 099 cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 W 91 Z0 OV 100 061 N d erq z 1 4 28ed I 4 98eq TVOANVW NOLLVTTIV LISNI SHTWAS 00t uoneljeisu Of SND S 4 anG LNSLNOO Q39NVHO S31VOIGNI 3Sdl ld GSHSVG Z SH3N31SV4 q3Ov3sHl TWV OL QNnOdWOO 9NbI001 Ov3NHl A1ddV 9 Xvid NOLDJNNOD JO MIA NIN T a TI3HSMOV8 M3AO SLVIdLAN dvNS meee ne T aan SSO8 H0193NNOO OLNI NOLLN3SNI 30438 2 TISHSHOVE HONOYHL S3NIM SSINYVH 0335 v Nid 1 OH NO Q3N31N39 31Vld MOIO3NNOO of 900rd OL Aldd SNIMOV8 3AIS3HOV 3AOW3N LIM MOLO3NNOO 00 16 00 110 30 iMvd l O A18W3SSV ilvid HOVE 00 9
31. This ee ees page is also used for verifying electrical interfaces during installation and troubleshooting Information that is not being received by the 400 Series unit is dashed out Field L FF R FF Right Engine Fuel Flow Figure 5 4 MAIN INPUTS 2 Page T FF Total Fuel Flow T FOB Total Fuel on Board GPS SC GPS Selected Course GNS 430 Only CDI Status of the CDI key 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 5 5 INSTRUMENT PANEL SELF TEST Page 400 SERIES INSTALLATION MANUAL Page 5 5 P N 190 00140 02 Rev M 5 2 6 MAIN LIGHTING Page Select the MAIN LIGHTING Page see Figure 5 6 This page allows you to set display parameters that affect the display backlight and key lighting brightness The DISPLAY and KEY lighting characteristics are adjusted separately each with the following fields LIGHTING Shows the current level of display backlighting based on the lighting input source lighting bus voltage
32. 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 Rev M 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 1s installed in the pilot s normal field of view refer to the FAA letter in Appendix B Check that there 1s adequate depth for the rack in the instrument panel A location away from heating vents or other sources of heat generation 1s optimal 2 4 CABLING AND WIRING Coaxial cable with 50 Q nominal impedance and meeting applicable aviation regulations should be used for the installation A typical maximum cable length for the GPS antenna 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 1s ampl
33. etc may require external annunciators Sincerely CORD X C Dale Bleakney FAA Program Manager Wichita Aircraft Certification Office Page B 6 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 U 5 Department Small Airplane Directorate of Transportation Wichita Aircraft 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 Serics Notice 8110 60 Data Submittal Reference 1 GARMIN letter dated August 27 2002 2 FAA Notice 8110 60 GPS as a Primary Means of Navigation for Oceanic Remote Operations 3 FAA Information Memorandum GPS as a Primary Means of Navigation dated 2 11 97 Dear Mr Billings This is in reply to your letter of August 27 2002 requesting a separate letter of design approval for your upgrade to the GNC 400 series of products to comply with FAA Notice 8110 60 We concur that GARMIN Intemational has met the requirements of Notice 8110 60 in accordance with the additional guidance provided in the FA A Information pense GPS asa Means i Bi iur dated 2 11 97 and as agreed upon in for FDE GPN 05 00077 63 Revision GARMIN has previously received T8O C1292 Air Equipment Using the Global Positioning System GPS res Al TSO Poe for the GNC 400 series products through our office
34. 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 lt CR gt carriage return 0 0 Note Checksum is calculated by adding each byte in the message 1 through 14 D 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 0x20 12345 altitude in feet lt CR gt carriage return 0 0 400 SERIES INSTALLATION MANUAL Page D 1 P N 190 00140 02 Rev M D 4 SHADIN FUEL FLOW SENTENCE The Garmin 400 Series units shall be capable of receiving the following 55 byte message from the Shadin Fuel Flow Indicator 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 in the case of single engine aircraft 0060 0 fuel flow rate engine two asterisks
35. lulod VEA TOUR AOLDIIPU 769 99 IND 85 IN 622 OC SNO bury xipueg Bury xipueg Bury xipueg Bury xipueg ALON S NIANVO ONAS 190 N vc LL GY ONAS 190 NIVW V1VQ I8O 1 91 al 61 C vy VLVG 190 49019 180 LL L 8 21 a cy 40010 IdO Z69d LC8Sd LZ8Sd L6ZZd LOOF d ZH i lulod C E ON S A4OLDO DL 69 Vay Z8S IN 85 IN 677 OF TOG 00 Buy x pueg Buly x pueg Bury xipueg uy xipueg 1 NIASVO cO OV 100 061 N d TVONVW NOILVTIVISNI SHINAS 007 W 91 Z0 OV 100 061 N d erq 79 4 8 9 4 2824 TVOANVW NOLLVTIV LSNI SHTWAS 00t Buiuni JING elas Bury L 3 aunbiy 12 ZHWz 3WG Nvd 3QOW AVNH 3WG 33S ZZ NOWWOO oz ZHWr 3NG NVd O3M NYHO 3WQ XIS AINO 3ON3N3438 NOJ NMOHS SLINN M3HlO JO SLNONId NOLLVIASOANI 193NNOO331NI ANY LNONId 3131dWO09 NOILVIN3An2OQ SYIYNLOVAANVW OL 33333 81 40019 lvl33S 3OV3331NI SIHL JO NOllVM3dO N3dONd VLVG ONINNL INWA IVIXIS SNI INdLNO OL NOILVTIVISNI LY Q330914NO09 38 LSAW OSY SND FHL Z _ 6 viva Q310N 3SIMM3HlO 31 N39NV1 MO OMY FZ S3MIM 71 S310N 900fd Z AWN NOAN09 ANG P Do 9 N 12 ZHWZ 3WQ NYd 30ON AVNH 3
36. 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 is 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 Rev M This page intentionally left blank Page 3 8 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 4 SYSTEM INTERCONNECTS 4 1 PIN FUNCTION LIST 4 1 1 P4001 View of J4001 connector from back of unit 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 T8 o 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 eoo 000000000000009 909 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 MO 6 MESSAGEANNUNCATE Out 8 AUTOANNUNCIATE f Y Out 9 INTEGRITYANNUNCIATE Out Out MAIN TO MAIN FROM 2 5V COMMON MAIN OBS STATOR E 2 5V COMMON OBS MAIN OBS STATOHR F MAIN OBS STATOR G 2 5V COMMON OBS 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 Rev M
37. 3Hl NV SINdLNO GIONVIVE 34V SLAdLNO OIGNY WHO OOS JHL f N A3M DOIN WOO KINO 32N38343M HO4 NMOHS SLINM N3HlO 40 SLNONId IW WOO Ogv OZY FHL NOILVINMOANI 1923NNOOM3INI ANY LNONId 3131d4AOO WOO 200 ae aan DEC a A oe NOILVINJ3ADnOOG Se3snl9V4JnNVW OL 843434 8 1 H LIMS 3NOHdO32IW M JAIL V 1Y JAILOV SI OIN JNO AINO LVHL OS Q3Q0N3AWOO23M F Y NOILO3S OL 83438 SAVI3M NOILVIOSI OIN Q3LMOLSIO YO VAM NI ZHW OS IZI OL 39NVHO THA AON3hO38N4 WOO JAILOV 3Hl NOlldO ONIMIM WOON3INI 9 110S34 AVA JAIL 3AVS JHL LV OT IH OIN WOON3IN SQNOO3S 3AILOV SI HOLIMS N343SNVMI 310W3M JHL 4l JO OT IH OldnY JIN OL S3NOHdOWOIN OML ONILO3NNOO Z H3LLINSNVMI WOO 3HLl NOILVM3dO AON3OM3WN3 MOJ GSN LJVMOMIV 3HL NI N31SAS WOOM3INI M3HIO ON SI 3H3HL 4l AYN SLi ZOOFd LNdNI M34SNVMI 310WN34 WOO FHL Z q3sn 38 AINO GINOHS NOILONN4 WOOMN3INI 097 027 JHL S Q310N 3SIMN3HIO SS3IN NH39MV1l MO 9MV VZ S3MIM 1 S310N JE ud 8c M3JSNVMLI 310W3M DOTA HOLIMS M3JSNVMLI 201A O1 oidnv Z AVN 901 AN9 9N1 Sn1 02 81 A AE Q O1 OIQnV 511 WHO OOS IH Olanv Z AWN 1 d 21 21 61 41 91 IH Oldnv S1I HOA WHO 005 AINO 05 900rd p S M3JSNVMI 310N3M WOO 1 310N 335 HOLIMS N3JSNVMLI WOOD JION 44S s yl MOOTYHSLNI LINSNVML O1 DIN WOOS3INI Q LA O1 SIN WOOS3INI 9 QNV S SJLON 33S SIN WOOM3INI S IH OIN WOOS3INI O1 DIN z W
38. ALT PWR P N P N 1 AVAILABLE 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 K00 00056 00 Alternate secondary power input available review installation drawing Page 3 2 400 SERIES INSTALLATION MANUAL Rev M 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 248 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 PLATE 115 00080 00 SCREW 10 32 x 5 8 211 62212 14 ANTENNA GASKET 253 00011 00 2 Other accessories include the following ITEM GARMIN P N MOUNTING RACK 400 420 430 115 00243 00 GPS 400 BACK PLATE ASSEMBLY 011 00676 03 GPS 400 CONNECTOR KIT 011 00351 03 GNC 420 BACK PLATE ASSEMBLY 011 00676 01 GNC 420 CONNECTOR KIT 011 00351 01 GNS 430 BACK PLATE ASSEMBLY 011 0
39. 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 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 0D hex LF ASCII line feed character 0A 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 E00 0 or user defined magnetic heading magnetic variation as entered by user 400 SERIES INSTALLATION MANUAL Page C 1 P N 190 00140 02 Rev M The following table describes the Type 1 output sentence item designator id and it
40. C E 6z 621 A ec LINO 62v ONINV SII MOA 91 t D vz v INO 6Zv ONIMV STI YOA T AINO Of 9 921 900 79 ZZL d x S g A LY 1nO 62v ONINV Sd9 19 U a or v INO 6Zv ONINV Sd9 i OZ 6v 8 NI 647 ONINV Sd9 Y 1 33S JLON 33S LY D 8v V NI 6Zv ONIMV Sd9 g8zG9rvd VZG9vd ld LOOrd S97 9S v8g nda A os or S43 7898 5143 Og Oc 00 Buly xipueg sullloo INAVS IN erq pp 3 8ed o8ed SOEENS seues oor L 199uuo5Si lul ISH3 Ilepues 9NIHV LZ 3 AINO 3O9N38d34389 804 NMOHS SLINA YSHLO dO SLNONId NOILVASHOJNI L23NNOO83INI ANY LANONId dldldWOO dOd NOILVINAJAGOOQ SdsdyNLOVANNVW OL 9343439 E QV3ilSNI Q3193NNOO 38 AVN 1S QNV OG 100vd LNOd 6 ONIMV Sd9 AHL 3sSOd 4 d M3HIONV 404 qQ3S n AQV3MNIV SI 67 ANY 8v 100vd LNOd NI 6ZF ONINV Sd9 FHL 4 6 NI Q31ON ASIMYSHLO SSFINA 8398V YO VC Sd3dlA TIY cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 SALON 9V11 JVOILM3A A A 0 9V14 VOILM3A E 6Z NMOQ A A 82 dN 2 9v11 JvM3l1V1l FZ 9yJ4 JVN3alV1l Jj ez 1H9IM A CC 1431 d ze 3OVON3 3711 201 vi ojidojny
41. Connector P4001 continued Pin PinName O VO 52 RESERVED 1 eo 58 RESERVED 60 ALTITUDE COMMON GROUND 66 ALTITUDE BA gt M 68 ALTITUDE AQ 1 y y On 69 ALTITUDEAI tn 74 RESERVED 1 eo 76 RESERVED 1 eo 77 ARCRAFTGROUND i 78 AIRCRAFT GROUND j 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 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 Page 4 2 400 SERIES INSTALLATION MANUAL Rev M 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 o0 o 0o o o o eee 14 15 16 17 18 19 20 21 22 23 24 25 eooo0000000009 Pin PinName MO j 1 RESERVED j 2 RESERVED j 3 RESERVED Je 6 COMMICAUDIOH hn 8 RESERVED fe 9 RESERVED j 10 RESERVED U Je 18 RESERVED j 16 20 RESERVED KU fe 21 AIRCRAFTGROUND j 22 AIRCRAFTGROUND j j 28 RESERVED KU U j 24 RESERVED j 25 RESERVED dol 400 SERIES INSTALLATION MANUAL Page 4 3 P N 190 00140 02 Rev M 4
42. 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 451 SSCS High Temperature A 2 amp 483 Done 42 LE Hm 69 0 i es 5 Equipment tested without shock mounts to Categories B M amp N Explosion f 90 f Equipment dented as Category X no test required Fluids Susceptibility Equipment identified as Category X no test required Sand and Dust Equipment identified as Category X no test required Salt Spray Equipment identified as Category X no test required See report 005 00096 72 for details 400 SERIES INSTALLATION MANUAL Page A 3 P N 190 00140 02 Rev M Magnetic Effect Equipment tested is Class Z Induced Signal Susceptibility Equipment tested to Category A A 3 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 C
43. MANUAL Page 4 19 P N 190 00140 02 Rev M 4 10 3 DME Tuning Configuration Refer to section 5 2 12 for the DME tuning configuration 4 10 4 DME Tuning Calibration and Checkout None 4 10 5 DME Tuning Interconnect Refer to Figure F 31 on page F 63 for the King Serial Panel DME tuning interconnect Refer to Figure F 32 on page F 65 for the King Serial Remote DME tuning interconnect Refer to Figure F 33 on page F 67 for the parallel 2 of 5 DME tuning interconnect Refer to Figure F 34 on page F 69 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 F 33 on page F 67 Page 4 20 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 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 unit 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 tur
44. NI 6cvr ONIYV Sd9 V L NI 6cy ONIYV Sd9 HO LL 34VML3OS ocr O07v 00r NIAMVO 3 a 8 NI 6cvr ONIYV Sd9 V NI 6cy ONISV Sd9 YSHOIH Ll 3HVMLJOS O0gv Ozczv 00 NIAMVO HOLIMS 9 lt T v 310N 33S INO ALVIONANNY Ol44VeL 9 gt 831VNOS HO dWY1 1VNOlldO OL 310A ILONAN G o o HOLIMS 310 ILONAA I ES VNOILdO QNhOMNO ZEZ Sy 81 Z XL ZEZ SY J D 6S H XM ZEZ SY 6l 0 gs ld LOOFd JosseooJgd VOL X8 80066 uoy O1 HOLIMS Y3MOd G IH HOLIMS 33MOd r 915 440 v 1405 LZ LL 11V 1S31 Z A3M 1405 61 01 dl 6zv ey A ANTEE A 6v VL XL 627 zv g D 8v ld LOOvd O1 HOLIMS 33AOd IH HOLIMS M3MOd LL 915 390 v 1405 8 LE 11 1531 L A3M LJOS Sg 01 g XL 6zv 6 Z 310N 33S VI XL 62v ye 0 8v M3JH9IH MO 97 3MVMLJOS ld 0074 A81S SVL ez LL NI 1531 SYL 01 XL 6 nao SG A A Z 310N 33S XL v 6 nao 0 8v Old LOO d Buly xipueg 3 ALVIONANNY a 31VIONRNNV 8 NI 62 ONIYV Sd9 V NI 6cy Sd9 431H9lIH HO Ecc 34VML3OS 0gv Ozv 00 NIASVO Figure F 26 Traffic Advisory System Interconnect Page F 53 Page F 54 blank 400 SERIE
45. P N 190 00140 02 Rev M 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 1f 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 is 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 Page 5 10 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 5 2 11 COM SETUP Page GNC 420 and GNS 430 Only Select the COM SETUP Page see Figure 5 13 These values are set at the factory and seldom require calibration 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 whic
46. S3MIM L S3LON NONWOO ANG ZZ NOWWOO 0S ZHMOS 3Wd 131lVuVd 001 zy ZH3001 3WG 1371V3Vd 002 oy ZHMOOZ 3WG 1371V3Vd 00 6s ZHMOOP 3WQ 13TV3Vd 008 Lg ZH3008 3WG 1371V3Vd LW ZHWL 3Wa 131YMVd ZW LZ ZHWZ 3WG NVd 300W AVNN 3WQ 33S VN OZ ZHWr 3WG Nsvd O34 NYHO 3WG XIS gn yl ZHW8 3NG 1311 vMVd S 900td ING peuh 0 SN9 qog I9 I54Dd NIN AVS NOWWOO ANG e 21 ZZ NOWWOO 0S 9c 01 ZHXO0G 3WQ0 131T1YvNVd c S 9 Zv ZH3001 3WG 13T1V3Vd Zy ZHMOOZ 3WG 13T1V3Vd Ly 8 6s 7 13T1V3Vd oy 29 6 7 00 8 13T1V3Vd N m I ZHNI 3WQ q1311v3Vd ZW 91 iz ZHWZ 3WG NVd 300W AYNN 3WG 835 LA S c OZ ZHWr 3WG vd O34 NYHO 3WG XIS ON vi y yl ZHN8 3WQ 131 YWNVd LG9d 194 JION S 900 JA peur G9 NM L9 N OF SN9 Buly xipueg Bury xipueg dis _ NIASVO
47. SH 61 4 eJn614 MAINO 404 NMOHS SLINA YSHLO 4O SLNONId NOILYW NOJNI 1L23NNOO83INI ANY LAONId 3L31d4WNOO Od NOILLVINJADnOOQG SHSENLOVANNVW OL 83434 6 dHVMLIdOS NIV JO SNOISHSA 1VOILN3GI 3AVH LVHL Q3SInO3M 38 AVA S43LVd 419049 3SV8VIVG 1JVOILN3GI SAVH SLINA 531435 007 LVHL Q33In038 SI SNVId LHOM4 711355049 OL SINIOdAVM ASN ANY SNVId 1 9114 11355049 OL GALOANNOO SSONO 38 AVN cv L100vd Lr 100vd NO SANIT c c S8M 3Hl Q3TIVISNI 34V SLINM 531035 OOP 3MON YO OML dl Z Q31O0N ASIMYSHLO SSdIN O 439471 YO vc 534 TIY 1 S310N INO ZEZ SH 545 Lv cv NI SM 545 2 Z 310N 33S E NI ZZ SM Sd9 ZV Lv INO ZEZ SM Sd9 7 O1 100 292 54 7113 6 Z q Z TI3HS Y TI3HS SI A Aj IH INO Z9Z SM S 9 S r S 9 Z Z D LS NI ZZ SM Sd9 1S d3 0002 92dv 4 Z0916 G LXESOL6 dX SO 6 QO 89 1XvOZL6 004 03 01 14 000 10026 00Z 20V 4 p4opibiq 71 91161 1 1 0 1 9 JUIN sjueuunajsu 01 24 sjueuunJjsu 10006 10088 DID Aly en 4 s51u04429 3 UIPDYS uipous uipous uippus uippous df AVNMV snapo uippus JO JeZi Dil4eS epnill Vv NI Z Z
48. SM T13HS 6 q TI3HS r Aj IH NI Z Z SMN 91 S Zi H ra 6 G 91 NI VIVO U 95 INO ZZ SY 49 0 4 Ld TE 715 43 000 lt 92 4 Z0816 0 1 5016 dxesoie 10 8 1 00 II seuues 0004 0005 FOZ 00 JO lo29 00Z 2QVv 3 pippi 6iq 7 o14161q 7 0 4161g 1 9 HUIN sjueuinajsu 000 SNBuy tOlld Ill 49 561 dVWSd9 e ouv ds 51u04 29 3 UIPDYS uippus uippus uippus UIPDYS df jg 9 NIAMV9 NISI VO W 93I zp J 9Seq I A 9Seq 99UU0919 U 5143 6ct ONIHV 02 4 e1nBi4 8H3AI3O3M C AVN V SH3AI3934 AVN 8 8N3Al3934 V 43A132938 L AVN L AVN 8 43AI393H Z AVNTI NMI V 8N3AI303H 2 AVNI NYT 8 43Al39393 V 83A13938 AVNT N31 AVNT NT AVN AYNI Z AVI1dSIC 153 647 ONIMV 39N38933389 YOS NMOHS SLINA YSHLO dO SLNONId NOILVASHOJ3NI LOANNOOYFLNI ANY LAONId 3il31d4WOO cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 N3AI393M C AVN V S3AI3034 AVN 8 8N3AI3934 V 83Al3938 L AVN L AVN 8 H3AI303H Z AVNTI NNTI V M43AI3034 Z AVNT NSI AVNT NT AVNT N3T 8 8H3AI3934 V 83A13038
49. STORMSCOPE TEST PAGE k hkkk kk n A n S A AA AEAEE I naan 5 12 FIGURE 5 19 STORMSCOPE DOWNLOAD DATA 5 12 FIGURE 5 20 TRAFFIC PAGE SKYWATCH tiim tate alah tela a fest lun E sei cel rete 5 13 FIGURE 5 21 TRAFFIC PAGE TCAD cecssccssescssecssesssucsssecssecesuecesecssuesssecesvessuesssecesusesusestecesucessecssesssuessseseseesascesees 5 13 FIGURE 5 22 RYAN TCAD CONFIG ttes sedi 5 13 FIGURE 5 23 GAD 42 CONFIG PAGE uu u A aa ba Tae 5 13 PICORER 5 14 FIGURE F 1 GA 56 ANTENNA INSTALLATION DRAWING cette F 3 FIGURE F 2 GNS 430 MOUNTING RACK DIMENSIONS ettet F 5 FIGURE F 3 GNC 420 MOUNTING RACK DIMENSIONS ettet F 7 FIGURE F 4 GPS 400 MOUNTING RACK DIMENSIONS cette F 9 FIGURE F 5 GNS 430 MOUNTING RACK INSTALLATION cette F 11 FIGURE F 6 GNC 420 MOUNTING RACK INSTALLATION ctt F 13 FIGURE F 7 GPS 400 MOUNTING RACK INSTALLATION ctt F 15 FIGURE F 8 400 SERIES RECOMMENDED PANEL CUTOUT DIMENSIONS tenes F 17 FIGURE F 9 400 SERIES SYSTEM INTERFACE DIAGRAM cette F 19 FIGURE F 10 GNS 430 TYPICAL INSTALLATION ettet ttt n anns F 21 FIGURE F 11 GNC 420 TYPICAD INSTADEATION u elemtum ac test A F 23 FIGURE F 12 GPS 400 TYPICAL INSTALLATION cccccssecsssecssecsssecsseceseecsuccssecesucesnecssecesuesssecesucesuesasesesuesssecesees F 25 FIGURE F 13 POWER LIGHTING AND ANTENNA
50. confirm change Figure 5 8 DISPLAY Page AUX Group Note Leave CONTRAST MODE in Auto 5 2 7 DATE TIME SETUP Page Select the DATE TIME SETUP Page see Figure 5 9 DATE TIHE 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 DISCRETE INPUTS Page 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 MAIN DISCRETE 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 Rev M 5 2 9 MAIN DISCRETE OUTPUTS Page Select the MAIN DISCRETE OUTPUTS Page see Figure 5 11 This page allows you to verify the operation of any external annunciators and switches that are present in the installation Figure 5 11 DISCRETE TOGGLE MAIN DISCRETE OUTPUTS Page Verify That Th
51. ev DUANE See d ZHWZ 3WG 3vd 3QOW AVNN 3WQ 3 AVN 8v gv 2 NOWWOO 193135 119 09 118 01 c lt 9 N LSANDAY AVNY Ll 1 EPL C oz ZHWvr 3WQ Nuvd Od4 NVHO 3WQ XIS Ot sng 52019 21 21 e O C 8 40019 lVvl33S sna viva LL LL fadi 61 Vivd 3WQ lVl33S Lp Gd LZLSd YLS 10X ZLS 10X JO IVOIGNI JNC Buly xipueg Bury xipueg 0 SNO W 93 Qerq 89 4 9Seq 19 4 9Seq 19 uuoo4 lul FING S JO Z lallesed ee 3 199195 3009 qog Loads dO dS 159413S 3000 S X 3 ZHN OT V ZHN Ol NONNWOOD AWG ZH OS 4 00 HX OOL 001 4 00l HM 001 3 ZHN q ZHN Jc MN g ZHN V ZHN MAINO d39N3334339 4 NMOHS SLINA 43H10 NOILVASHOAJNI LO3NNOOSA3ANI cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 JO SINONId 3l3ldWOO 404 NOILVINSWNOOd SHSYNLOVANNVW OL 43434 YSAISOSNVEL ANG dO 1300N SIHL NOILVdsd0O amp ddOs8d AGOW ONITISANNVHO AWG 168 068 OOMVN GIYNDI4ANOD 38 LSNW OY SN9 JHL YAAISOSNVAL AWG dO 1400W SIHL NOIIVN3dO JdO d YO4 AGOW ONITISNNVHO AWC eC T3 Vavd o4 Q384091NO9 SOW OC SNO JHL c Q31ON SSFINA sN398Vl YO VC 534 TIY I
52. 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 Rev M P N 190 00140 02 D 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 D 6 1 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 ZMS5678 lt CR gt lt LF gt t ZN90123 lt CR gt lt LF gt t Z04567 lt CR gt lt LF gt t ZP89012 lt CR gt lt LF gt t ZQ345 lt CR gt lt LF gt ZR678 lt CR gt lt LF gt lt ETX gt Where SHADIN Z FORMAT 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 temperature Celsius ZG ASCII characters sign 90 re
53. of 90 Hz modulation d In the absence of both 90 Hz and 150 Hz modulation e In the absence of RF Page 1 6 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 14 TSOLIMITATIONS A limitation exists pertaining to TSO C36e Localizer and TSO C34e Glideslope The main board lateral deviation J4001 Pin 21 MAIN LEFT and J4001 Pin 22 MAIN RIGHT and vertical deviation J4001 Pin 27 MAIN UP and J4001 Pin 28 MAIN DOWN outputs exceed the respective TSO MOPS requirement for current response time due to 120 milliseconds of internal transport delay Except for this transport delay the output characteristics meet the TSO MOPS requirement Consequently these outputs should be used only in applications where the transport delay has been evaluated and found to meet installation requirements 15 LICENSE REQUIREMENTS The Telecommunications Act of 1996 effective February 8 1996 provides the FCC discretion to eliminate radio station license requirements for aircraft and ships The 400 Series unit installation must comply with current transmitter licensing requirements To find out the specific details on whether a particular installation is exempt from licensing please visit the FCC web site http wireless fcc gov aviation If an aircraft license is required make application for a license on FCC form 404 Application for Aircraft Radio Station License The FCC also has a fax on demand service to provide forms by fax The 400 Series un
54. parallel DME tuning For each of the parallel DME tuning discrete outputs the driver output voltage is not more than 1 0 V while sinking 20 mA The maximum off state leakage current with respect to ground is less than 10 WA NAV DME COMMON must be pulled low to indicate to the NAV module that it is the device channeling the DME NAV DME COMMON is considered active if either the voltage to ground is lt 1 9 V or the resistance to ground is 375 Q 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 Q These inputs are considered inactive if the voltage to ground is 11 33 Vpc NAV DME COMMON must be pulled low to indicate to the NAV module that it 1s the device channeling the DME 400 SERIES INSTALLATION
55. replace the back plate by positioning the tabs on the back plate in the slots of the left side of the rack viewing it from the cockpit and attaching it by replacing the two 4 40 screws 3 8 400 SERIES UNIT INSERTION AND REMOVAL The 400 Series unit 1s 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 1s 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 from the rack Be sure not to over tighten the unit into the rack The application of hex drive tool torque exceeding 15 inelbs can damage the locking mechanism 3 9 COM ANTENNA INSTALLATION CHECK 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
56. shall equally apply to the GNS 430A and GNC 420A except where specifically noted Page ii 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 FIGURE 2 1 GPS ANTENNA AND UNIT INSTALLATION CONSIDERATIONS ces 2 2 FIGURE 3 1 COAXIAL CABLE INSTAELATION tenen ebore 3 5 FIGURE 5 1 MAIN ARINC 429 CONFIG PAGE tette ttt ttr nti 5 FIGURE 5 2 MAIN RS232 CONFIG PAGE k kkk n k nn a a n a AAAA EEEE I aaan 5 3 FIGURE 5 3 MAIN INPUTS 1 PAGE I tco d ace cette cea tet ec a te ine 5 4 FIGURE 594 MAIN INPUTS 2 PAGE uU tee ee teak alert ei n LS OR NALE cal EL aqa aa 5 4 FIGURE 5 5 INSTRUMENT PANEL SELF TEST PAGE ttti 5 5 FIGURE 5 6 MAIN LIGHTING 5 5 FIGURE 5 7 MAIN LIGHTING PAGE DISPLAY LIGHTING FROM LIGHTING BUS 5 6 FIGURE 5 8 DISPLAY PAGE AUX emisse rn tale ire catalan 5 6 FIGURE 5 9 DATE TIME SETUP 5 6 FIGURE 5 10 MAIN DISCRETE INPUTS ttt ttti 5 6 FIGURE 5 11 MAIN DISCRETE OUTPUTS PAGE tette teens nodi 5 7 FIGURE 5 12 MAIN CDI OBS CONFIG PAGE ettet tette ettet ttt dett DEI 5 7 FIGURE 5 13 COM SETUP PAGE GNC 420 AND GNS 430 ONLY 5 9 FIGURE 5 14 VOR DISCRETE INPUTS GNS 430 ONLY 5 10 FIGURE 5 15 VOR LOC GS CDI PAGE GNS 430 ONLY ttti 5 10 FIGURE 5 16 VOR LOC GS ARINC 429 CONFIG PAGE GNS 430 ONLY 5 1 FIGURE 5 17 STORMSCOPE CONFIG PAGE ettet ttt ttt ttt ttti 5 12 FIGURE 5 18
57. the ARINC 429 air data IRU AHRS interconnect Refer to Figure F 25 on page F 51 for the ARINC 429 flight control interconnect Refer to Figure F 26 on page F 53 for the Traffic Advisory System Interconnect Refer to Figure F 27 on page F 55 for the Weather and Terrain Interconnect Refer to Figure F 27 on page F 55 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 Rev M 47 COM VORIILS 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 50092 VOR ILS AUDIO are 100 mW audio outputs that are intended to drive a headset or an audio panel Momentarily depressing the COM REMOTE TRANSFER button toggles the active and standby COM frequencies Momentarily depressing the VLOC REMOTE TRANSFER button toggles the active and standby VLOC frequencies The COM REMOTE TRANSFER input may be used for EMERGENCY operation of the COM transmitter If the remote transfer switch 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
58. 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 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 Connecto Pin _ This input is considered active if either the voltage to ground is lt 1 9 V or the resistance to ground is lt 375 Q This input is considered inactive if the voltage to ground is 11 33 4 7 2 2 COM MIC AUDIO INTERCOM MIC AUDIO PinName Connecto Pin 1O 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 made through Configuration Mode When a 125 mVgys 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
59. 0 blank 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Rev M 9d SLIOA SZ T 02 08200 110 N d OSY 01 08200 110 N d OSY SNS SN9 2 SLIOA 8c 01 92800 110 N d VOY 00 92800 110 N d VO F 00 08200 110 N d Og SN9 SN9 SN9 LINA AHL 40 YSEWAN LYVd JHL NO 3 SI ZOOVd GYVOE WOO JHL NO LNdNI N3MOd LAVYONIV JHL OdA 9 11 38 AVW 90079 GYVOE STI YOA Of SN9 JHL LOO0vd QNVO8 NIVA 3Hl OL LAdNI N3MOd LAVYONIV Z Q310N ASIMYSHLO SSFINN YO 9MV VC SAIM TIV I Lv S310N Ol dnV AVN 81 Q 21 OIGNY AWN 91 900td O1 olanv SIN WOO Ol a 81 A3M OIN 1 WOD 21 SIN WOO LL g 9 O1 olanv WOO 01 a 61 IH Oldnv WOO 6 L Ove VAS ld ec LZ NIWNHVO 81 AF1 VOL A8Z WS cl 318Vl ANY Z 310N 33S M3MOd LAVYONIV LI N Z SN 81 pe Z00rd NOWWOO LINONIO XL WOO v2 VNN31NY Po 69 S 9 LO LOOtd v8 zg VNN31NV 73 ig 901 S vy SoOOrd ZV VNN3INV 7 LV WOO G _ ka 700rd PUl g VNN31NV 73 AJO
60. 0676 00 GNS 430 CONNECTOR KIT 011 00351 00 400 SERIES ADDENDUM FOR TRAFFIC amp 190 00140 10 WEATHER INTERFACES GPS 400 PILOT S GUIDE GPS 400 QUICK REFERENCE GUIDE GPS 400 SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT GNC 420 PILOT S GUIDE GNC 420 QUICK REFERENCE GUIDE GNC 420 SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT GNS 430 PILOT S GUIDE GNS 430 QUICK REFERENCE GUIDE GNS 430 SAMPLE AIRPLANE FLIGHT MANUAL SUPPLEMENT NOTE A mounting rack is required for approved installations The following hardware is required for installation of the mounting rack but is not provided 6 32 Flat Head Screw ea 46 32 Self locking Nut 6 ea 190 00140 60 190 00140 61 190 00140 64 190 00140 20 190 00140 21 190 00140 24 190 00140 00 190 00140 01 190 00140 04 400 SERIES INSTALLATION MANUAL Page 3 3 P N 190 00140 02 Rev M 3 2 DATABASE OPTIONS ITEM GARMIN P N DATA CARD WORLD WIDE 010 10201 00 DATA CARD AMERICAS 010 10201 01 DATA CARD INTERNATIONAL 010 10201 02 3 3 MISCELLANEOUS OPTIONS ITEM GARMIN P N CONNECTOR BNC MALE CLAMP 330 00087 00 LOW LOSS AVIATION ANTENNA 320 00003 00 EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR 15 FT LOW LOSS AVIATION ANTENNA 320 00003 02 EXTENSION CABLE WITH RIGHT ANGLE BNC CONNECTOR 30 FT GPS 1 57542 GHz NOTCH FILTER 330 00067 00 3 4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED The following installation accessories are required but not provided COM
61. 1 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 o 0o 0o O O O O O O O O O 30 29 28 27 26 25 24 23 22 21 20 19 18 17 16 eoo0o000000000009 44 43 42 41 40 39 38 37 36 35 34 33 32 31 ee eo ol pol O o ol o o o ob oo Pin PinName 6 VORLOC RIGHT VORLOC COMMON Out 7 RESERVED 0 fe 8 VOR LOCCOMPOSITEOUT Ou 9 VOROBSROTORC Ou 34 RESERVD _ e 41 AIRCRAFTGROUND Page 4 4 400 SERIES INSTALLATION MANUAL Rev M 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 PinName Connector Pin 1O _ AIRCRAFT GROUND P4000 77 AIRCRAFT GROUND Poi 78 AIRCRAFT GROUND P400 21 AIRCRAFT GROUND P402 22 AIRCRAFT GROUND 1 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 incl
62. 1 to 31 Xo pod poo X undefined 1 if last waypoint in route a 1 if active to waypoint nnnnn route sequence number of waypoint unsigned binary Destination waypoint identifier will be blank filled on right if less than 5 characters in identifier S 0 north or 1 south ddddddd latitude degrees unsigned binary 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 Rev M 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 D 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 sp gt lt gt 12345T lt gt 12ul lt CR gt Where RMS ASCII characters
63. 15725 M81969 1 04 M81969 1 02 615724 M81969 1 02 Insertion extraction tools from ITT Cannon are all plastic others are plastic with metal tip 2 Non Garmin part numbers shown are not maintained by Garmin and consequently are subject to change without notice 3 Alternate contacts for 18 AWG wire As an alternative to the Positronic contacts listed and provided in the installation kit the installer may use contacts made by ITT Cannon under P N 031 1007 001 These contacts require the 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 For card edge connector pin contacts use AMP part number 90272 1 or equivalent crimping tool To prevent a possible short across the pins in the wiring harness Teflon shrink tubing P N 312 00005 05 provided in Connector Kit 011 00351 00 P4002 covers the oversized power and ground pin contacts P N 336 00023 00 pins 11 12 21 22 that protrude from the back of the connector shell Before crimping the pins onto the wire 1 Cut the tubing 312 00005 05 into 4 equal lengths 2 Slide a short piece of the tubing over the wire 3 Strip the wire and crimp the pin 336 00023 00 onto the wire 4 Insert the pin into the connector shell 5 Slide the tubing over the exposed portion of the pin and shrink using a heat gun Page 3 6 400 SERIES INSTALLATION MANUAL Rev M P N 190 001
64. 3401530119 S 0 dd f H 9e S S g 62 2V14 1VOILM3A A A NMOG 9 q 9 ve 82 HH 8 W 82 val v 8Z NMOG NIVW dnt S 9 S pu LZ rr 3 x vv e LZ dn NIVW 9v14M3d S AVN 9c S 8 _ _ _ _ _ _ _ _ A 9V14NadNS AVN 681 d e _ _ _ _ _ _ _ _ _ Li QV14NadNS 1VM31V1 NIV S E 2V14 AVN Ze z 5 3 4 8e 8 8 8 8 vz 9V14 1VH31V1 NIVNW 9V14j AVN Es 19 3 N Je L L L L Z 9V14 IWYSLV1 NIVW 2 WOus Zz 8 Z ZZ ve 3 1 ev 01 01 01 01 92 WON4 NIVW Ol y 92 7 3 9Z 6 6 6 6 g GZ Ol pm T LHOIN 3 gz 8l H 8 ey Zi zi 21 el zz LHOIN 1431 d 6c Ll I A N LC LE LE LL LL IZ 1430 1 ld Zd td ld z qo LOld Zd ld L90Zd Zd ld ld ld ld LOOYd OOOLGSN E V ESS Id OF FOE 00v AOLDOIPU 059 qu VOSS GY 96 VLes d9 VIES voogdsN 8 ZSS idw VSZS l IM 081 15 v90l 19 901 19 VZOL I9 zol 19 uoi DBIADN kaads Aueds Aunjueg Bury xipueg Bury xipuegBury xipueg 291 5 NINYVS NINYVS NINYVS NIASV9 NI NHVOS IN ueq pc 3 8ed cc 398eq OS9UUODJ9 U 403e2Ipu UIEN W607 IM 91 3 NI 9Vli IVOIL33A AVN NI 9Vid IWOILYSA AVN NI NMOG TVOILYSA AVN NI dfi 1VOIL83A AVN NI 39VON3 907 AVN ALISOdWOD 201 30A INO 509 S80 AVNI INO NIS S80 AYNI NI NOILVLIOXS S80 AYNI 590 NI 39VO9N3 201 594 AVNI 3SV9N3 AV13M NI 9Vl4i WOlldsA AYNI NI 9V
65. 38d 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 LowTememue 43 High Temperature asa eass Decompression 42 463 Humidity 60 Fauipnentesed io Sock x qw Equipment tested without shock mounts to Categories B M amp N Explosion f 90 Fadpmentidenifedos Category X no test required See report 005 00096 72 for details Salt Spray Equipment identified as Category X no test required Magnetic Effect Equipment tested is Class Z Page A 4 400 SERIES INSTALLATION MANUAL Rev M 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 Low Temperate
66. 40 02 DATA OUT Off GAMA 429 ARINC 429 data as defined by the General Aviation Manufacturers Association GAMA General Aviation Subset 2 Edition The output data includes navigation and flight plan information to the following systems Garmin GAD 42 Interface Adapter Bendix King EFS 40 50 Sandel SN3308 Collins EFIS 84 Garmin GTX 330 Certain other of Collins EFIS systems may also be compatible with this format GAMA 429 Graphics ARINC 429 data as defined by the GAMA General Aviation Subset 2 Edition including GAMA Graphics Protocol A This format outputs intersection symbols as generic waypoint symbols The output data includes navigation and flight plan information including graphical representation of flight plan procedures to the following EFIS systems Honeywell Primus 1000 GAMA 429 Graphics ARINC 429 data as defined by the GAMA General Aviation Subset 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 the GAMA General Aviation Subset 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 the GAMA General Aviation Subset b os Edition The output data includes navigation and flight plan information to the follo
67. 40 02 3 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 74 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 is 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 instrument panel The rack is 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
68. 400 SERIES INSTALLATION MANUAL Page 1 7 P N 190 00140 02 Rev M 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 The FDE function is built into the GPS 400 GNC 420 GNS 430 and does not require pilot interaction In contrast the FDE Prediction Program does require pilot interaction and must be used prior to oceanic remote area flights to predict FDE availability The 400 Series Trainer software Garmin Part Number 190 00176 00 includes an FDE Prediction Program to meet the requirements for GPS as a primary means of navigation for oceanic remote operations per N8110 60 The oceanic flight phase occurs on the GPS 400 GNC 420 GNS 430 when more than 200 nautical miles from the nearest airport All 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 18 LIMITED WARRANTY This Garmin product
69. 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 illuminates and remains illuminated until the turn is completed 3 When a 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 CDI key on GNS 430 bezel 4 5 1 4 VLOC ANNUNCIATE GNS 430 Only This annunciator output is driven when the unit is configured with a single CDI HSI and the VOR ILS data is being displayed on the CDI HSI This output parallels the VLOC annunciator on the display 4 5 1 5 GPS ANNUNCIATE GNS 430 Only Thi
70. 4O SLNONId NOILVASOANI 1923NNOO83INI LNONId 3L131d4WOO NOILLVINJADnOOG SHSYNLOVANNVW OL 33334 v Sd431131 3SVO YdddN Q3NITS3QOND SV NMOHS 34V SYOLVNOISSG 3SVO OZY OND YON OOF Sd9 OL AlddV LON OG ALVIONANNY 201A 1 100 ANY 31VIONRONNV Sd9 Z 100vd Z Q310N 3SIMN3HIO SS31N M39OMV1 MO AV FZ S3MIM 11 L S31ON YOLVIONANNVY 201A _ _ _ _ _ _ 81 S N JLVIONANNY 201A Z 1 335 YOLVIONNNNY 549 _ _ _ _ _ S N FLVIONANNY 49 NIS 9 8890 Zi 29 L L SZ X M lv 9 9 9 9 A 9 MOIVIS S80 NIV IH NIS 4 S80 LI 88 9 9 92 ih 8 n Or J S 4 MOIVIS SSO NIVNW _ a 502 3 S8O 01 eZ y d 6 S S ve 3 MOIVIS SHO IH 02 sgo 6 7 r r rZ 7 A 1 SZ o pe MOIVIS S80 y T 2 S80 9 44 91 ACN y Z Yz Z Z Z Z S o MOIOM SSO S80 9 aq S M X 5 ZZ Ze H MOLIOM SEO O1 9v1443df S 3dO1S3dl19 8 M _ _ _ _ _ _ J 92v1iM3dnS 3901530119 g f 2 81 9v14M3dnS 1VOILM3A NIVA ps A 2vV11 340153019 _ 9 62 99 M G 91 91 0 2v141 1VOIlLM3A 9v14
71. 599 HO e 00rd ANNOYS N3MOd 09 vO 3aqnilllv L m ZO 3aniuv LO 3qnilllv 0l va 21 zg 3aqnilllv LL 8 3aniuv 6 yv 3aniuv 9 ZV 3aqnilllv G LV 3aniuv yd 3aqnilllv 81 INO 92 SM 02 LS O1 SN ONILHON Or ES X19 NIIS VOS IH SNE NILH N 62 LLZ d 4 8 LL 04 YIMOd LAVYONIV OQA 8 1 MS 61 yayvayg LINDYID OY SNS NIS 9 580 A 9e IH NIS 4 S80 Sg sod 3 S80 A A IH SOO S80 2 580 Ls S80 d J Ze 9V14 3dO1S3Q 19 A A 0 9V14 340153419 D 6z A A 82 dnt LZ 2V14 AVN vC 9V144 AVN eZ WOW 44 A 92 01 D SZ 1 A A zz 14314 LZ AOLDOIPU LOOvd UOIJDBIADN QNNOYD L3VSOMIV O1 O1GNY S1I YOA WHO 005 IH Oldnv S1I YOA WHO 006 O1 OIGNVY DIN WOO A3 DIN WOO IH OIGNVY OJIN WOO O1 NOD WHO 00S IH NOD WHO OOS QNDnONO L3VSOMIV LAVYONIV 43MOd LAVYOUIV 431MOd LAVYOUIV VNN3INV 3idO S3Ql19 VNN3INV 201 HN0A VNN3INV WOO VNN3INV Sd9 NONNWOO L NI CEZ Sd Sd9 O1 SN ONILHONM IH SANG ONILHONM GNNOYD LAVYONIV GNNOYD LAVYONIV 43MOd LAVYOUIV 43MOd L3JVMOMIV 9 HOIVIS S80 3 MOIVIS 590 3 MOIVIS 590 a YyOLVLS S80 5 YOLOY 590 H XOLO 590 9V14 VOll43A OV14 1VOll43A NAMOG
72. 8 XM l 6ZYv QZ C LY V XM 01 9y 8 XL 6 62 C EET 6v V XL 67 LI gy Loovd 8 XM r eZ V XN 62y 92 D v d AINO OFr p osid 80 NS 900d l pups OV NMOd OV l LHOIN NIVA 1441 NIVN HovONddV 549 51 lt m m L NI L NI lt lt M AVOILYSA Yld IVOILS3A V843lVl NIVA SVl d NIVA 1 6 lt V NIHXY Sd9 INO 6cv JONIdMV Sd9 62v ONIdV Sd9 6 v ONIMY Sd 1nO 677 ONINV STIZYOA INO 677 ONINV STIZYOA OF 702 OOV 82 Z AVN Q3ZI933N3 OV14 WOILYSA SV i TWOILYSA NMOQG NIVW 9V14 1V331V1 NIVW OV14 1V331V 1 NIVW 1 914 1331 NIVW HovONddV 549 511 m 6zv ONINV SdS V LINO 62v ONIJV Sd9 m NI 6zv ONIYV Sd9 V L NI 627 ONIYV 599 LNO 62v ONINV STI YOA V INO 6Zv ONINV STI YOA TH SND NINYV9
73. 9 I3HSMOV8 H340 d3lV Id1I nN dV HOLO3NNOO OLNI NOILS3SNI 3804 TISHSMOVE HONOYHL S3MIM SS3NSVH O03 S 3g 33 NO GQ3331N39 FIOH 3lVl d YOLOANNOO OL WVO4 AlddV ONIMOVE SAISSHCV SAOWSY LIM YOLOSNNOO 10 18 00 110 40 l Vd MIGWASSV 3lV d MOVE L0 9 900 110 340 lNVd SALON CSOld Z MOLO3NNOO HLM 5 LAN 05 0 00 0 2 v SOld Z 00 zz000 ziz 1 SOld v Zzl ve ze9 l1Z 2 279 Sy tapes 00 67 00 6 1 g Q 03M 4l O vOcO9 LL JASN SSOH VMHIX3 cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 Vid YOLOANNOO 40 I ava NId SZ of 2004 ONnOs9 OQ T3IHS R L0 9 000 S L D SOld Z 0 034 4l 80 70 09 11 3SN SSOH 4r 00 29000 zs2 L0 6000 0 1 N se RS sod Z 80 7EZ09 11Z ees d Z cO OV 100 061 N d IN TVONVW NOILVTIVISNI SAINAS 007 erq 91 4 98eq SI 4 2824 uonej eisu 00b Sd59 4 4 LNSLNOD Q39NVHO S3I1VOIGNI 3Sdlld Q3HSVG 4 SM3N3ISV
74. 900 110 jO i1xvd 1 SALON Sold v MOIO3NNOO HLM andans A of Woo uds ONnOMO Sold v CSIHS 9 0 J OS O02200 O0 Q 03M 4l 80 v0c09 L1LIc 3SN SSOH 00 8 000 sz1 Z S 00 zz000 z1z P 3 S 00 97000 sz1 L0 9 000 SZ X2 sz ozzoo oee QO3M SV 00 12000 9 g v s8100 0 mas 00 29000 cSC IO SOld v 0 S 000 0 S o0 9v000 sz1 GE sz ozzoo oce Da S 219 9 zi veze9 11z 2 5219 Z Saye n d N z v8209 112 Ae a034 5 00 12000 96 Em T 8 98100 0 2 SOld OZ 00 62000 99 2 02 8cc00 0 Sold v 00 2000 99 gqo3M sv 00 z2000 99 SZ 8100 0 2 00 vc00 Sll ae bo sold O 80 7 209 112 5s it ce ANN W 93I pI 4 2884 E1 4 282d uonejeisu Bununon OZt OND 9 4 00 2v000 s21 sz 0zz00 o 2 Marec rum f SOld Z ZL v9209 112 Nee gt 5 SOld OZ 00 67000 9 OZ 82200 0 00 000 81 2 Sod v 00 92000 9c gO3M Sv 00 22000 9 SZ v8100 0 qO3M SV 00 12000 99 8 98100 0 LNSLNOO Q39NVHO SSLVOIGNI 13 Q3HSVGd 4 SH3JN3ISV qdqavdsHi TIV OL GNAOdWOO ONIMDOT Qv3sNHLl AlddV
75. 944 RECORD OF REVISIONS Date A Initial Release 9891 C Add 18 AWG pin positioner and insertion extraction 10008 tools Add King Serial DME tuning interface description 3 18 99 Add GNC 420 GPS 400 ARINC 429 GPS King Serial 10665 E 11243 F 10 13 99 Add interface to BF Goodrich Stormscope and Skywatch 11871 and Ryan TCAD G 4 27 00 Update installation accessory kits 13205 H 9 1 00 Add unit versions with 14 28 volt transmitter Update 14026 configuration pages J 2 22 01 Update configuration pages 15207 K 5 22 02 Add gray unit and 16 watt A versions Update 18149 configuration pages L 12 13 02 Add Fault Detection and Exclusion 19779 M 7 6 04 Added TSO limitation 26552 Page A 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 This manual 1s written for software version 4 02 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 1s subject to the Export Administration Regulations EAR issued by the United States Department of Commerce 15 CFR Chapter VII Subchapter C and which may not be exported released or disclosed to foreign nationals inside or outside of the United States without first obtai
76. Antenna GNC 420 and GNS 430 Only Shall meet TSO C37 and C38 Broad band 50 Q vertically polarized with coaxial cable VOR LOC Antenna GNS 430 Only Shall meet TSO C40 and C36 Broad band 50 horizontally polarized with coaxial cable Glideslope Antenna GNS 430 Only Shall meet TSO C34 Broad band 50 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 F 1 page F 3 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 The antenna 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 cauti
77. E OF MODIFICATION BULLETIN BULLETIN DATE NUMBER 9905 9 17 99 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 0019 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 0207 4 2 02 Remove excess solder from COM board 0211 6 4 02 Reduce input transients from Audio Panel LEVEL 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 MANUAL Page v P N 190 00140 02 Rev M This page intentionally left blank Page vi 400 SERIES INSTALLATION MANUAL Rev M 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 re
78. FR Verify That FROM The FROM flag is in view SELECTED COURSE Select 150 on the CDI HSI that is connected to the 400 Series VOR LOC GS OBS inputs The SELECTED COURSE field should indicate near to 150 and a Calibrate to 150 field appears Selecting this field calibrates the 400 Series to match the input source Verify OBS operation by checking that the course displayed on the 400 Series is within 2 of the selected course Do this at 30 intervals around the OBS card DME CHNL MODE This configuration allows you to set the format for DME tuning data output King Serial King Serial DME tuning data not operational for MAIN software versions 2 02 and lower for MAIN software versions 2 02 and lower 2 02 and lower Narco 890 891 2 of 5 parallel DME tuning compatible with the following DME units Narco DME 890 Narco DME 891 ARC Cessna RTA 476A 5 2 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 GS ARINC 429 COHF IG 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 Nu
79. H3H SI ONILNNOW 4 L A0 cas SUL Sh PE uu SNOISNSWIG L S3 ON 376118179 lc 44 89 i ES Sg 5 99 z9 Z IE OST mE 9 61 SZ i 9 89 0 6 091 Z 9 cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 Z HONI SZL S SS3NMOIHL 13NVd LJVMOMIV A nNIXV XINO TANVd L4VMOMIV JO MOVE Q3TIVISNI MOVM LNOLNO Oldvy ONO Lea CI3NVd LJVMOMIV JO LNOY4S WOMJ Q3TIVISNI MOVM LNOLNO OIQVM 13Nvd LJVMOMIV JO LINOMJ WOMJ Q3TIVISNI MOVM 1001029 MOVLS NOLS VNN31NV 3dO 1S3QI19 LOOVvVd YOLOANNOO OgY NINYVS GOOVd YOLOANNOO OSV NINYO WOO vOOvd MOLO3NNOO Ogv OZY NIWMV9 VNN3INV 33ZI1V201 80A N VNN31NV Sd9 9S VO O00rd MOLO3NNOO Ogcv OZY OOtY NIWHNVO HOLIMS H3JSNV3MI DOTA 310N3S JN G4ANNL d3TIvsvd 6 JWG e 1 435 OND INNAN FAN AINO SII MOA ISH IG9 Ya4SNVAL ALOWSY 201A NONWOO ONINAL ANG TaT1Vavd INO 62 NIXY STI YOA NI 62v ONINV STI YOA NONWOO 1S3nOo3M INA V1VQ 52019 lvl33S IGO
80. HS JO H19N31 WO 8 SIOVINOO NOILVNINNSL 398V1 1VI93dS NO YOLONGNOD Q3SOdX3 19310Nd LIM NOIO3NNOO 931199405 00 22000 92 LOVLNOD 134205 NOILVNINYSL OMY 81 1vio3ds ISN 34IM AV 8 YO4 MY SI SNId ZOOvd 39nv9 3MIM 318VMOTIV WAWIXVA d4nq3o0s4d NOIIVSHOSIJNOO NOILVTIVISNI 1SOd JHL OL 43434 J18VIIVAV OSIY SI NOILdO 1OMINOO NILH N V 1T139010Hd SLI ONISN SNOILIGNOD NILHON IN3IBWNV YOs ALVSNAdWOO ATIVOILVWOLAVY OL LAS 38 NVO ONILHOI1 NOILIOOV NI ATLOSYYNOON GAYNOIANOOD S LINQ SHEL dl 40220 TIIM 39VWAVO ON NOILVTIVISNI LSOd OVA S NO OQA S OQA vL OAA 82 39VI1OA SNA ONILHON 19344800 AHL 404 QG3s4f1914NOO 38 GI0OHS LINN 531435 OOvY JHL 02 08200 110 N d 087 SNO 01 08200 110 N d 057 SNO 02 90 00 110 N d 0 OND 90 SLIOA 82 7 OL 90S00 110 N d OZ OND 01 42800 110 N d VOZY ONS 00 42800 110 N d VOZv OND 00 90900 110 N d OZ OND 01 92800 110 N d YOY SN9 00 92800 110 N d YOY SNO 90 SLIOA 8c 00 08Z00 110 N d O SN9 LINQ 3HL 40 YSEWNN LYVd 3HLl NO IN3Q NddiGd SI ZOOvd GUYVOE WOO FHL NO 1 dNI N3MOd L4VYONIV FHL OGA 9 11 38 AVW 9007d QNVOS8 SII YOA OS SN9 FHL LO007d QNVOS8 FHL OL IndNI N3MOd LJVNOMIV OV1IANSdNS 3401530119 ovijs3dns AVN 900 d YALLINSNVYL WOO 00 YAMOd SIHL NO SNOILONN4 LINN 531435 00 17 1 43MOd HOIHM NO NdddG SN
81. HTEN 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 and 25 pin connectors must be crimped onto the individual wires of the aircraft wiring harness The following tables list contact part numbers for reference and recommended crimp tools 400 SERIES INSTALLATION MANUAL Page 3 5 P N 190 00140 02 Rev M Table 3 1 Pin Contact Part Numbers 78 pin conn 44 pin conn 25 pin connector P4002 Shield ground P4001 P4006 connector Connector Type High Density Pin Contact Standard Density Socket Contact 1 Pitch Card edge 22 28 AWG 18 AWG 20 24 AWG 20 24 AWG 336 00029 00 N A 583853 4 N A 031 1007 042 N A Table 3 2 Recommended Crimp Tools or equivalent Connector High Density Standard Density Type 22 28 AWG 18 AWG 20 24 AWG Hand Positioner Insertion Positioner Insertion Positioner Insertion Crimping Tool Extraction Extraction Extraction Tool Tool Tool Military P N M22520 2 01 M22520 2 09 M81969 1 04 M81969 1 02 M22520 2 08 M81969 1 02 9507 9502 3 M81969 1 04 9502 11 M81969 1 02 9502 5 M81969 1 02 ITT Cannon 995 0001 584 995 0001 739 N A 995 0001 604 980 2000 426 601966 1 601966 6 91067 1 N A 601966 5 91067 2 AFM8 M81969 1 04 K774 M81969 1 02 K13 1 M81969 1 02 615717 6
82. I 4 18 Z TO DMIE TUNINGE ONS 490 ONE 1 utc Ae ec reborn ean 4 19 5 POST INSTALLATION CONFIGURATION amp CHECKOUT PROCEDURE 5 CONEIGURATION MODE OPERATIONS tetas te pereo Eco uwa asas AER CES Hr E v t OR Sc eae 5 5 2 INSTALLATION CONFIGURATION PAGES ie eee ee S END ieu tutes 5 S S DDE TIONAL GROUND TESIS agina aa Ud bete duc etu Sato fud E 5 17 Appendix A CERTIFICATION DOCUMENTS ACOLDOONTINUED JATREWORTEHLDNESS ade oO lae eB pa pM 1 A 2 ENVIRONMENTAL QUALIFICATION FORM GNS 430 A 3 ENVIRONMENTAL QUALIFICATION FORM GNC 420 A 4 A 4 ENVIRONMENTAL QUALIFICATION FORM GPS 400 eese A 5 A 5 ENVIRONMENTAL QUALIFICATION FORM GA 56 A 6 Abpbendix DxsTC PERMISSION docete it uU mI Ie E UE ieee B 1 Appendix C 400 SERIES RS 232 AVIATION DATA C 1 Appendix D 400 SERIES RS 232 FUEL AIR DATA INPUT D 1 Appendix E 400 SERIES LRU INTERFACE E 1 Appendix DRAWINGS AND F 1 Note Throughout this document references made to GNS 430 and GNC 420
83. Inspectors to install and approve GARMIN GNS 430 Integrated VHF Communications VHF Navigation and GPS Receiver equipment in certain installations GAAMIN is issuing this letter to clarify the approval basis for accomplishing such installations without external switching or annunciation GARMIN obtained initial TSO and STC approval under 50 129 in conjunction with AC 20 138 tor the GPS Heceiver 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 io be from the airspeed indicator to and including the center radio stack Therefore mounting of the GNS 430 was accomplished in the pilots 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 determining factor in this approval 3 The GNS 430 CDI source information switching is accomplished internally therefore the switch used to determine tha source of CDI source information on the associated indicator is located on the GNS 430 Foll
84. LAVYOAIV O1 sN NILH N IH SNE NILHON L3VSOsMIV L3VsOsMIV YAMOd LJVsOMIV YAMOd L3JVsOMIV 43MOd LAVYOUIV 43MOd L4AVAONIV SUAE NIAMVOS 05 IN 91 Z0 OV 100 061 N d erq 08 4 28ed 67 A 2824 TVANYN NOLLVTTV LISNI SHTWAS 00t 2euuo2Joju Y L 4 MAINO JONd ddd NMOHS SLINA YSHLO 40 SLNONId NOILVASOJNI LO3NNOOS3INI ANY LNONId 3l3ldWOO 404 NOILVINSNNOOd SYFdNLOVANNVAW OL 83434 1 SASIMYSHLO 55 41 8398VI YO VC SAYIM TIY 71 SALON NONNOO 9 9 09 NONWOO VO Gl el L9 vO 3QALILIY Z9 I n l c9 co TV L LI 1 LI 9 LO AGNLILIV vq 01 q Ol v9 vg JACNLILIV ca 6 d 6 G9 ca 30dALILIY 9 S N S 99 tga Seb T vv Y N 19 VV ACNILILIV V 2 o 89 V 30ALILIY LV 2 8 69 IV 3Q lll Tv va V OL FQ 3anli1v ld ld Ld LOOVd 49poouj3 Pu JO iv vay vosi va 0ev 0Ocv 00 Iv 6uipoou3 DJJ8 Buly xipueg Bury xipueg NIAMVO W 93I TE A 9Seq TE A 9Seq cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 199uuoo191ul 10je2ipu UIEN SL 3 1N31NOO d39NVHO SALVOIGNI 45414 Q3HSVQ S MAINO 3O9N333433 NMOHS SLINA YSHLO
85. MMON 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 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 8 2 3 TO FROM PinName Connecto Pin X 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 Rev M P N 190 00140 02 4 8 2 4 Flag Pin 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 o Connector Pin IO 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 ROTOR C and H are a buffered 500 Hz ou
86. N GPS 400 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 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 kya suspended recoded or diate i othemwise estattished bg the Sbatmanisivaton of lhe Kemal 2 Bele of eom ox November 10 1998 radssteed gt Pals of tasaance July 06 1999 Lede amended Cr m 2 I Tina L Miller Program Manager Wichita Aurcraft Certification Office n Q o lt lt a gt lt J Title he ee es cC eee Any altarstion of this certificate is punishable by a fine of not exceeding 31 000 or imprisonment nor exceeding 3 years or bath FRA 6110 2 10 68 PAGE 1 of 2 PAGES This certificate may be transferred in accardance with FAR 21 47 Page B 4 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 l GARMI N INSTALLATION MEMORANDUM TO GARMIN Authorized Dealers FROM GARMIN International DATE January 25 1999 SUBJECT GNS 430 approval basis without external switching or annunciation CG Wichita Aircraft Certification Office Due to reluctance by GARMIN Authorized Dealers and FAA Flight Standard District Office Field
87. NCE TYPE 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 0D 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 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 0D hex LF ASCII line feed character 0A hex 400 SERIES INSTALLATION MANUAL Page C 3 P N 190 00140 02 Rev M 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 hex Two ASCII numeric characters representing route sequence number of waypoint 0
88. OILONJ LINA 531935 OOvY HOIHM SMOHS 319 ONIMOT1I04 3Hl ddsn 38 qinoHS 519 s3MOd JLVYEVdAS V Z 310N 33S Q3NInO3H SI LNAdNI N3MOd 31VNM3LTV NV di MJA3MOH 5509 N3MOd 3AVS JHL OL d3193NNOO 39 SLAdNI 43MOd LINN 531435 OOF 11 LVHL Q3O0N3WWOO33 SI Ll Q310N SSdIN 893938V1 VC S3MIM SALON 9 QNV Z S31ON 33S MN3MOd LiVMOMIV S ANY Z S310N S318VLl 33S 43MOd Ll4JVWOMIV SNE 9NILH9I r 310N 33S IH SNA 9NILH9SI 1 310N 33S N3MOd L3JVNOMIV ANY Z SALON 33S N3MOd LAVYOUIV cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 VNN3INV 73 r 5 9 Q AINO ogr L00td YNNIJLNY N 201A Q AINO ogr SOOrd VNN3INV 7 CQ AINO ogr voord VNN3INV 7 Sd9 O00rd L lv 9 AINO ogr lINOXIO 9714 AVN 900vd ZZ LZ 81 A 1 VOL 21 A 82 VS LL MY Slit yayva4a AINO ogr LINDMID XL WOO cOOvd Ov 6 8 LL G C E OZ WS 6l 00v H3 v3H8 LOOFd 1109419 Sd9 ozr M3MV3M8 LINDYID OZv ONO ogr YaNvaNE LINDYID OSY SN9 VNNALNVY 4d01S4q119 VNN31INV 907 404 VNNd3INV WWOO VNN3INV Sd9 L3VsOsMIlV 43MOd LAVYOAIV LJVeSOsIlV qN Os9 L3VesOsIlV 43MOd L4VsOslV 43MOd
89. OO I WOO 9N1 QN9 9NI QN9 901 01 A a 8l OldRnV 2IN WOO AJA 21 z WOO I WOO H 2 A M A M 0g37 1 A3M DIN WOO OlGNV SIN z WO2 L WOO 3 2 H d H d S1 11 w 9 IH Oldnv OIN WOO oianv z WOO WOO 901 QN9 901 QN9 901 AN9 01 A EREE Q 61 OIGNY WOO WHO oos IH Olanv Z WO2 L WOO 91 1 01 6 01 6 21 6 L IH Oldnv WOO WHO 005 woog ld ZOOVd 0 0009 Vd OF 0Z HYZ VW VW 6uueeuibu3 Org VW9 6uix xipueg Bury xipueg Sd NIAMV9 NIA AVS eubd oipny 2 IN Gpue q 09 4 23ed 65 4 2824 12euuo2Jeju 10je2Ipu STI HOA 6Z 4 9JnBi4 NIS 9 890 IH NIS 4 S80 SOO 3 SO IH SOO S80 2 S80 S80 9vi4s3dhS 3dO lS3Qd ll9 9 1443405 AdOISACI19 SV 3 3dO 1S3Ql 19 OV14 3dO1S3Q 19S NMOG T dat JZI9M43N3 SII 3llSOdWO2 201 30A 5 5 AVN 5 5 AVN 9 14 AVN 9Yld AVN NOd3i Ol LHOIN JO DOIDUu UOILOBIADN 3ON3834dd4 N04 NMOHS SLINA YSHLO dO SLNONId NOILVWHOANIT LOANNOOUALNI ANY LAONId 3131d4WOO NOILVINIWNOOG SYFYNLOVANNVW OL 33334 v snivis NOLLNG 109 IHL 40 SS31Q0NV93H NOLLVA3OAN SII YOA OS SND AVIdSIG OL YOLVOIGNI 31VNVd3S V Q3M4IS3Q SI N3HM AINO
90. Page 4 14 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 4 7 2 3 COM AUDIO VOR ILS AUDIO PinName Connecto Pin VO 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 are balanced outputs and the LO output must be connected 5000 COM AUDIO is the summation of the COM receiver audio COM sidetone audio and INTERCOM MIC audio 4 7 2 4 DISCRETE INPUTS PinNam Connecto 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 4 7 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 F 28 on page F 57 for the audio panel interconnect 400 SERIES INSTALLATION MANUAL Page 4 15 P N 190 00140 02 Rev M 4 8 VOR ILS INDICATOR GNS 430 ONLY 4 8 1 VOR ILS Indicator Function NOTE Because the GNS 430 includes a CDI button that performs switching between GPS and VOR ILS on a remote indicator it is seldom necessary to use these outputs to driv
91. ROUND 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 T handle makes the turns easy to count but do not over tighten 4 Count the number of complete revolutions you can turn the Allen screw until it can not turn any more 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 is not required to verify every data field with an ARINC 429 interface Corre
92. S INSTALLATION MANUAL P N 190 00140 02 Rev M IN Qerq 9c 4 9Seq SS A 282d 2 Uuu0319 U pue ISU1e AA Z 3 4 GNNOYD Q I3IHS NI Cec S c 1nO ce SM 9 ALON 33S AUT Boq el 9rs 10595 NIWAY VXM Sd9 SMd9 peoubuuj v9 098 d9M Buly xipueg 1nO cee 54 Sd9 NI cC 54 Sd9 YAHOIH YO S 505 L Sa3lM3S 9 GNNOYD ZEZ SM YVIIO IVNS31IX3 Z SM XM CEC 54 00S XM Ag INO ZEZ 54 Sd9 83H9IH YO Lec JYVMLIAOS ocr ozr oor NIAMVO cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 SV 38 AVW 140 CEC S8 FIEVIIVAV 43HlO ANY 350 NI AGV331V SI Z LYOd 4 NMOHS SI LINN 31435 007 JHL JO Z l1MOd SY Ol NOILO3NNOO 3O9N3334389 NO4 NMOHS SLINA YSHLO 40 SINONId NOILVAYOANI LOANNOOYALNI LAONId 3131dAO9 YO4 NOILVINAWNNDOG SYSYNLOVAANVA OL 433339 d3s 38 LON AVW l1NOd AWVS 3Hl 40 LAdNI SY ONIGNOdSAYYOO FHL SMd93 TIAMASNOH JHL MO4 QO330914NOO SI LYOd LAdLNO ZEZ SH NV il SiJOd cec SH AHL ANY NO d319d13S 38 NYO LVWYOS TWIddS LVHL HONS NOILVLINIT SIHL dAVH LON S3OQ 331V1 MO OCC NOISHJA dNVMIJOS SLYOd 21319395 ASAHL SAYINOAY
93. S INTERCONNECT 27 FIGURE 14 ALTIMETER INTERCONNECT ettet tette tette notte nodi F 29 FIGURE F 15 MAIN INDICATOR INTERCONNECT F 31 FIGURE F 16 KI 2094 MAIN INDICATOR INTERCONNECT cette F 33 FIGURE F 17 KI 208A MAIN INDICATOR INTERCONNECT innn F 35 FIGURE F 18 ANNUNCIATORS SWITCHES INTERCONNECT s F 37 FIGURE F 19 RS 232 SERIAL DATA INTERCONNECT cccecescssccoccsoeessucccuccsssessescsucesseeesecessesscesessessneesucesaneesess F 39 FIGURE F 20 ARINC 429 EFIS INTERCONNECT cccccscccsseccssecssecssuecssecssecesuecssecesucesuessecesucesseessesesnecateeesueeaseeenees F 41 FIGURE F 21 ARINC 429 SANDEL EHSI INTERCONN 1 400 SERIES UNIT 1 SANDEL SN3308 F 43 FIGURE F 22 ARINC 429 SANDEL INTERCONNECT 2 GNS 430 1 SANDEL 3308 F 45 FIGURE F 23 ARINC 429 SANDEL INTERCONNECT 2 GNS 430 2 SANDEL 13308 F 47 FIGURE F 24 ARINC 429 RS 232 AIR DATA IRU AHRS INTERCONNECT tenes F 49 400 SERIES INSTALLATION MANUAL Page iii P N 190 00140 02 Rev M LIST OF FIGURES FIGURE F 25 FIGURE F 26 FIGURE F 27 FIGURE F 28 FIGURE F 29 FIGURE F 30 FIGURE F 31 FIGURE F 32 FIGURE F 33 FIGURE F 34 ARINC 429 PLIGHT CONTROL INTERCONNECT Z reni Iden tane rsen Ee ege F 51 TRAFFIC ADVISORY SYSTEM INTERCONNEC D Z beet o e PE a eheu F 53 WEATHER AND TERRAIN INTERCONNEC PF Z uya a ee
94. S3llddV 193NNOOW3INI SIHL SH31131 3572 s3ddn Q3NITH3QNn SV NMOHS SYOLVNOISSG 3SVO N3MO1 Z Q310N 3SIMN3HIO SS3IN N39NV1 NO OMV FZ S3HIM TV SALON M M 9 9 A A P _ _ 1 4 _ _ _ d d S S 1 1 Sy Nu 7 2 2 Z a A 5 D I H _ _ _ _ E 2 _ u T vc 21 f 91 A GZ 6 H H Sl J 82 9 W WR v A A 62 _ I S 01 01 z X 9 9 z 2 A eS 2 J E 4 8 8 N N L L v S S 01 01 3 3 6 6 r Zk zi A A N N L LI I V60Zd I V80Zd L60Zd L80Zd LrOZd 0Zd 90Zd LZOZd ld ld V60Z IJ V80Z IM 602 M 802 IM voz I 902 b zoz p V 901 19 V ZOL I9 Buly xipueg Bury xipueg Bury xipueg Bury xipueg Bury xipueg Bury xipueg Bury xipueg xipueg NINHVO NIASVO cl LI 8e Og Ig 45 6 SI 900Vd cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 d MOIVIS 590 9 4 MOIVIS 590 YOLVLS 590 9 YOLOY 590 H YOLOY 590 SV 3ji8d3d S 3 90153 SV d 3 153 9V14 NMOG 340153019 dN 34015319 JZI9M43N3 SII INO ALISOdNOD 201 N0A 9v1443dnS 901 40 2v141 DOT YOA 2V14 201 M0A WOMJ 201 MOA Ol 201 30A LH9IN 201 80A 1441 201 M0A OSV SNO NINJ YO
95. WQ XJS v ET ZZ 1S30034 TENNVHO AVNY O AO C oz ZHWr 3WG MNVd O3M NVHO 3NG XIS sng 42012 bj i OAO gi 2019 JNA IVIXIS sng viva cl i a 61 VIVO lvl33S y 9d SE s Y9 NA VZ9 Z9 NM 1 t Bury xipueg 6utry xipueg un S N W A C0 0P 100 061 N d erq 99 4 23ed 69 4 93eq TVONVW NOLLV TIV ISNI SATAAS 00 12euuo24Je1u Buiuni JING jenas Bury ze 4 31n l4 A39Nd383448g 804 NMOHS SLINA YSHLO dO SLNONId NOILVWAOANT LO23NNOOS3INI QNV LNONId 3l3ldWOO NOILVLINSNNOOd SYaFdNLOVANNVAW OL 433384 AOVAYSLNI SIHL JO NOlIVH3dO 83dO8Sd YO4 VIVG ONINAL SANG IYIXJS ONIX INdLNO OL NOILVTIVISNI LV Q38fl9IHNOO 38 LSNW OC SNO AHL 6 Q31ON 3SIMN3HIO SS3IN s398V1 HO SAV vZ S3MIM TY 1 in B NI 9 dg ZHWZ 3WQ NVd 300W AVNY 3NG XIS 27 vc q C oz ZHWNy 3NG Nvd OdN NVHO 3WQ XIS sng 52019 8 d S O C gl 32019 1IVIXJS TOT mR sna viva 6 9 e ro 61 IWG jviW3s TN IND 90 4 9 Snes 4 904 Wa 9 N JN i Buly xipueg uly xipueg SNO FLOWS NIN AVS 1S3n03N ING SI SI z 2 NOWNOD Z AVN 6v
96. Y NILNNON 64 9S2 sdl S 1H9I3M LINN NM uu HONI SNOISN3AIG L S310N LZ coz 0008 zeve 69 oecz z sz toos oze 9979 099 co cz 586 1 89 089 301 Yad SOld MOV 3QISNI MSO 001 96 6 9910 S091 ee9 i 8 84 601 7892 0890 o Ovz 0576 ogi 1 s S vv 292 819 Stl O iii N j H H S 8Gl 9 O x 64 1 o i lt 1 l S N NUN 9 c0 07 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 IN ueq 8 4 98eq L 4 282d suolsu uuiq yoey OZt OND 3 enBiJ
97. age F 27 for the power lighting and antennas interconnect 43 ALTIMETER 4 3 1 Altimeter Function Altitude input is required for GPS RAIM calculations and is useful for advisory vertical navigation VNAV calculations 4 3 2 Altimeter Electrical Characteristics PinName Connecto Pin VO _ ALTITUDEA P4001 69 PALTITUDEA2 TOOT 68 m_ PALTITUDEBY Po 66 ln ALTITUDE COMMON P4001 60 n 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 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 is required for each unit without internal diodes The 400 Series unit includes internal diodes for isolation of the encoder lines 4 3 3 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 F 10 F 11 F 12 and F 19 for the altimeter interconne
98. 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 FUEL TYPE The aircraft is using Aviation gas 5 8 Ibs gal The aircraft is using Jet A 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 INSTALLATION MANUAL Rev M P N 190 00140 02 5 2 3 INPUTS 1 Page HAIN INPUTS 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 is not being received by the 400 Series unit is dashed out Figure 5 3 MAIN INPUTS 1 Page True Airspeed Wind Direction 5 2 4 MAIN INPUTS 2 Page Select the MAIN INPUTS 2 Page see Figure 5 4
99. at 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 is recommended 2 2 3 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 if possible 2 2 5 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 Rev M 2 2 6 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 o
100. ct 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 Track 149 5 Selected Course 149 5 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 15 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 400 SERIES INSTALLATION MANUAL Page 5 17 P N 190 00140 02 Rev M 5 3 4 Deviation amp Flags Check 5 3 4 1 Analog Deviation amp Flags The anal
101. ct using gray code or RS232 Page 4 6 400 SERIES INSTALLATION MANUAL Rev M 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 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 is preferred but not required For the 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 Connecto Pin 1O 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
102. cted 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 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 COHFIG 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 selecti
103. d 260 td 26016 X GPSDisreteWod 275G _ LRNStausWod fet 300G Station Declination and Class 303 MessageLlength Type Number 304G X MessageCharatersi 3 3056G MessageCharaters 4 6 30660 NAV WaypointAiportLatitude 307G NAV Waypoint Airport Longitude sf ele Ground Speed EA m E m Magnetic Heading m Drift Angle m LateradScaleFacor Conic Arc Inbound Course E N E 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 SpecficEqupmentiD fefefe 377 EqupmentHexIDCode 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 Rev M P N 190 00140 02 4 6 2 Serial Data Electrical Characteris
104. e APR annunciator is active and inactive as selected on this page The GPS source select annunciator is active and inactive as selected on this page MSG OBS VLOC The VLOC source select annunciator is active and inactive as selected on this page The WPT annunciator is 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 appropriate 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 Rev M 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 th
105. e an indicator It is only necessary when it is desired for a separate indicator to display VOR ILS deviation full time regardless of the CDI button status The VOR ILS indicator displays both lateral and vertical To From indications lateral and vertical flags and superflags GNS 430 connector P4006 always outputs the VOR Localizer Glideslope navigation information The VOR ILS pins on GNS 430 connector P4006 are used to drive an indicator that displays VOR ILS information at all times regardless of the 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 X 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 is less than 3 Vpc when the flag is to be IN VIEW 4 8 2 2 Deviation 2 Connecto Pin X VOR LOC RIGHT VOR LOC COMMON P4000 6 Out GLIDESLOPE DOWN FLAG GLIDESLOPE P4006 CO
106. e 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 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 rea
107. e 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 mile range Listen to the VOR audio and verify that no electrical interference such as magneto noise is present Check the tone identifier filter operation Fly inbound or outbound on a selected VOR radial and check for proper LEFT RIGHT TO FROM and FLAG indications Check the VOR accuracy Verify that the flag is hidden with a valid received station and that the flag 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 400 SERIES INSTALLATION MANUAL Page 5 19 P N 190 00140 02 Rev M This page intentionally left blank Page 5 20 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 Appendi
108. ed there may be an RS 232 wiring problem between the two 400 Series units 5 3 6 VHF COM Interference Check 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 on the 400 Series unit Verify that the GPS NAV flag is out of view Select 121 150 MHz on the COM transceiver Transmit for a period of 30 seconds Verify that the GPS NAV flag does not come into view e nr dee coe US Repeat steps 4 and 5 for the following frequencies 25 kHz COM channel spacing e 121 175 MHz 121 200 MHz 131 250 MHz 131 275 MHz 131 300 MHz 8 33 KHz COM channel spacing e 121 190 MHz e 130 285 MHz e 131 290 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 Page 5 18 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 5 3 7 VHF COM Check GNC 420 and GNS 430 Only A flight test is recommended after the installation is complete to ensure satisfactory performance To check the communications transceiver maintain an appropriate altitude and contact a ground station facility at a range of at least 50 nautical miles Contact a close ground station Press the squelch disable button to defeat the automatic squelch feature and listen for any unusual electrical nois
109. em data dddd fields If data for these sentences is invalid or unavailable dashes are used to fill in all non blank character positions Ident 1 byte Data 10 bytes Description 1234567890 ee S d d mmh h Current latitude where s N north or S south dd degrees mm minutes hh hundredths of minutes s mmnhh Current longitude where s E east or W west ddd degrees mm minutes hh hundredths of minutes 4 Distance to waypoint in tenths of nautical miles s n n n n Cross track error where s L left or R right of course nnnn error in hundredths of nautical miles GL eee C C C C C 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 NAE OT s I lower case d d qd d qd q Distance to destination waypoint in tenths of nautical Lima miles The line feed character is 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 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 C 4 OUTPUT SENTE
110. ent that can be interfaced with the Garmin 400 Series units This is not a complete listing however it only represents those units listed in Appendix F 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 pT 260 Lo 2800 9004 003 _ Function Shadin Icarus RNAV Shadin Miniflo L Instruments T Altitude Serializer or 8800T 3000 FC 10 EDM 700 91204XT 38 D Fuel Air Data 900T J FI o P 920T 0 Function Shadin Shadin Shadin Electronics Digiflo L Digidata International Altitude Serializer or 91053XP 91802 F ADC 200 FP 5L Fuel Air Data 91053XT D 2000 Flight Control KFC200 1 KOP 1 Or Blind Encoder 346 Digifll digitata 400 SERIES INSTALLATION MANUAL Page E 1 P N 190 00140 02 Rev M Bendix King EFIS EFIS 40 50 EFIS 84 Displays SG465 DPU 84 EHSI SN 3308 po HGIOSAB LTN9I po HGI05AB LTN92 LJ Indicator 203 91106 NSD 1000 331A 6G_ RD650 J p p L I C 6 j C X pn KI28A L j _ J KIWA l j
111. erated while aircraft are off the ground When any aircraft leaves the ground all ground based cellular telephones on board that aircraft must be turned off Ground based ell 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 Rev M 13 TECHNICAL SPECIFICATIONS The conditions and tests required for TSO approval of the 400 Series are minimum performance standards It is the responsibility of those desiring to install this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable installation and is approved by the administrator For TSO Compliance see Appendix A 1 3 1 Physical Characteristics Rack Width 632in 160mm _ Depth Behind Panel with 11 00 in 279 mm Connectors Measured from face of aircraft panel to rear of connector backshells GPS 400 Weight Unit only 3 8 lbs 1 7 kg rack and connectors rack and connectors GNS 430 Weight Installed with 6 5 lbs 2 9 kg rack and connectors Page 1 2 400 SERIES INSTALLATION MANUAL Rev M 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 Humidity 95 non condensing Al
112. esents East W represents West 234 5678 SY lt L R gt 90 lt CR gt lt LF gt Sa lt gt 1234 lt CR gt lt LF gt Sb56 78 lt CR gt lt LF gt S 901 lt CR gt lt LF gt lt ETX gt Where represents current longitude degrees minutes hundredths of minutes SY ASCII character L represents Left R represents Right 90 represents drift angle degrees Sa ASCII character sign 1234 represents barometric corrected altitude tens of feet Sb ASCII character 56 78 represents current barometric pressure setting inches Hg S ASCII character 901 represents checksum lt STX gt start transmit character 0x02 lt CR gt lt LF gt lt gt carriage return character 0x0d line feed character 0x0a sign indicator Ox2b or Ox2d lt ETX gt end transmit character 0x03 400 SERIES INSTALLATION MANUAL P N 190 00140 02 Page D 5 Rev M Note Checksum is calculated by adding each byte in the message including all characters from lt STX gt up to and including the error log reason indicator such that carries are discarded to give a one byte result The ASCII coded decimal representation of that byte is given ranging from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 Page D 6 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 Appendix E 400 SERIES LRU INTERFACE OVERVIEW The following tables provide a quick overview of some of the equipm
113. field has a range of 0 zero to 99 and is set to 50 at the factory Page 5 6 400 SERIES INSTALLATION MANUAL Rev M 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 LIGHTING 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 is 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 characteristics when the lighting bus control is below the level specified in the PHOTO TRANS field Both fields have a range of 0 zero to 99 and are set to 50 at the factory 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 1s Auto Highlight CONTRAST LEVEL and adjust to best viewable color Press ENTER to
114. ft Comification Office Tithe Any 2 eraricn of this cercaficate is punishable by a fine not exceeding 1 000 or Lnpriscnsest mot exceeding 3 years Dz Bock FORM El 110 68 PAGE 1 of 2 Pass This cortificzte nay b transferred in accordance wirh FAR 27 47 Page B 2 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 Sales of America Department of Transportation Federal Aviation Administration Supplemental Type Certificate Td LA ft SADOSDIWI Hes eed treo aed fo GARMIN Intemational 1200 E 51a St Olathe KS 66062 that the change un the tyne design for the following preduard ith the maaf conditons Zarah a hereon meet the airworthiness PI Pme af anl 3 ey the Civil Air ege doc Poduri Type imer A3SQ y sn s Piper Hodet P 32 260 Bosamgudion af Type ragen Chaage Installation of the GARMIN GNC 420 or GNC 420A in accordance with GARMIN Master Drawing List G05 CO0 76 00 Revision C dated 04 26 02 or later FAA Approved revision and Airplane Flight Manual Supplement for Piper PA 32 with GARMIN GNC 420 Revision A dated 7 5 99 or later FAA Approved revision Baniations and Compatibility of this design change with previously approved modifications must be determined by the installer If the halder agrees to permit another person to use this certificate to alter the product the holder shall give the other person writ
115. h is required in some areas of the world CAUTION 8 33 kHz channels are not authorized for use in the United States SQ 250 Sets the squelch threshold for 25 kHz channel spacing operation May be set to any value between 0 zero and 63 The higher the number the less signal 1s 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 is required to break squelch SQ 833 Sets the squelch threshold for 8 33 kHz channel spacing operation May be set to any value between 0 zero and 63 The higher the 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 The sidetone audio output level is 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 if you are done with configuration Verify That The box is filled in while the COM push to talk switch 1s pressed XFR The box is filled in while a remote COM transfer switch is pressed The box is filled in while the COM is receiving a signal The box is filled in while the COM
116. ies units are available under the following part numbers 3 1 1 430 A P N P N 430A 1 VOLTAGE XMIT PWR 010 00139 01 011 00280 00 N 011 00280 10 011 00280 10 011 00280 30 GRAY 2 2 EE gt gt O IO AT 011 00280 30 GRAY GRAY c gt 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 UJ 2 C lt 010 00286 00 011 00836 00 MOUNTING RACK 115 00243 00 CONNECTOR KIT 011 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 Rev M 3 1 2 GNC 420 A P N P N 420A 1 OLTAGE XMIT PWR 010 00173 10 0110050610 N Z GRAY ACK LACK GRAY GRAY 1 The following accessories are included with the GNS 420 A for those indicated with a Y above UJ 010 00173 30 011 00506 30 010 00173 31 011 00506 30 010 00287 00 011 00837 00 UJ s 010 00287 01 011 00837 00 UJ Q MOUNTING RACK 115 00243 00 CONNECTOR KIT 011 00351 01 BACK PLATE ASSEMBLY 011 00676 01 GNC 420 PRODUCT INFO KIT K00 00057 00 2 Denotes alternate secondary power input available review installation drawing 3 1 3 GPS 400 CATALOG UNIT ACCESSORIES COLOR
117. ility 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 section 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 is on condition only Periodic maintenance is not required Refer to the 400 Series Maintenance Manual 400 SERIES INSTALLATION MANUAL Page A I P N 190 00140 02 Rev M T
118. in the case of single engine aircraft 0123 4 fuel used total 0045 4 fuel used engine one asterisks in the case of single engine aircraft 0078 0 fuel used engine two asterisks in the case of single engine aircraft 123 checksum of bytes 2 through 51 lt ETX gt end transmit character 0x03 Note Checksum is calculated by adding each byte in the message 2 through 51 such that carries are discarded to give a one byte result The ASCII coded decimal representation of that byte is given ranging from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35 0 5 ARNAV El FUEL FLOW SENTENCE The Garmin 400 Series units shall be capable of receiving the following 13 byte message from the ARNAV or Electronics International EI 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 0245 liters indicates 5420 liters Checksum is the modulo 10 sum of the four fuel
119. intended to be a comprehensive listing of all test conditions Low Temperaire 4 OOOO High Temperature Hm 6 tested Category Equipment tested per DO 160C 7 2 1 eee Vibration Equipment tested without shock mounts to Categories C L M amp Y Equipment identified as Category X no test required Fluids Susceptibility 11 0 Equipment tested to Category F with Ethylene Glycol De Icing Fluid sand and Dust 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 Lightning Induced Transient Susc 220 quipment identified as Category XXXX no test required Lightning Direct Effects Equipment tested to Category 2A Page A 6 400 SERIES INSTALLATION MANUAL Rev M 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 SA00705WI GNS 430 and GNS 430A SA00801 WI GNC 420 and GNC 420A and SA00800WI GPS 400 data to modify aircraft 400 SERIES INSTALLATION MANUAL Page B 1 P N 190 00140 02 Rev M Buited States of Amer ice Department of Transportation Hederal Abiation Administration Supplemental Type Certificate a FH e SAQUTOSWI This tidad ta GARMIN International 1200 E 51st St Olathe KS 6560652 ri theed the cha
120. is 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 is selected the selected course is 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 Only The GNS 430 CDI button is in the GPS state and the GPS ANNUNCIATE output is active This annunciator output may be required to be active for some installations VLOC The GNS 430 CDI button is 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 400 SERIES INSTALLATION MANUAL Page 5 9
121. is warranted to be free from defects in materials or workmanship for two years 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 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 a
122. it owner accepts all responsibility for obtaining the proper licensing before using the transponder 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 6 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 7 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 remote 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
123. l not vary more than 3 dB Spurious Response Greater than 80 dB VOR OBS Bearing Accuracy The bearing information as presented to the pilot shall not have an error in excess of 2 7 as specified by RTCA DO 196 and EuroCAE ED 22B the 1020 Hz Ident Tone is at least 20 dB down in voice mode The distortion in the receiver audio output shall not exceed 10 at all levels up to 100 mW 400 SERIES INSTALLATION MANUAL Page 1 5 P N 190 00140 02 Rev M 1 3 6 LOC Specifications GNS 430 Only Regulatory Compliance TSO C36e JTSO C36e RTCA DO 195 CLASS A EuroCAE 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 60 of standard deflection The LOC Course Deviation Flag must be flagged a inthe absence of an RF signal b When either the 90 or 150 Hz modulating signals is removed and the other is maintained at its normal 20 c Inthe 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 From 86 dBm and 33 dBm input of a Standard VOR Audio Test Signal audio output levels shall not vary more than 3 dB Selectivity Nose Bandwidth The input signal level required to produce the reference AGC voltage shall not vary more than 6 dB over the input signal frequency range of 9 kHz from the assigned channel frequency Skirt Bandwidth The input signal level requi
124. ld IWOILYSA AYNI NI NMOG IVOILJ3JA AYNI NI dA IWOILYSA AYNI NI 9Vl4 IV8H31Vl AVNI NI OV14 V3431Vl AYNI NI WOd4st AYNI NI OL AVN NI LHOIY AAG 1VS83IVI AVNI NI L431 AAG WasalV1 AYNI cO OV 100 061 N d TVONVW NOILVTIVISNI SHINAS 007 92 ANY S SNId LOOVd N33M138 JNO ANY 55 SNId lOO0vd N33M138 SHOLSISSN 7 1 WHOM OL OML QAY JOLOSIPU JOLVOIONI V60Z IM V OL OSY SND JHL 193NNOO OL NOILO3NNOO N3dOMd N04 NOILVIN3AQ2OQ V60Z IM OL X343 39VI10A ATddNS N3MOd SLI NO IN3QN3d3Q SI V60Z DM JHL AINO 3ON38dd38M NMOHS SLINA YSHLO JO SLINONId JO LNdNI 39VON3 AVISN JHL JO NOILO3NNOO NadONd Z NOLLVAMOJNI 123NNOON3INI LNONId 3131d4WO2 NOILVIN3ADn2OQ SYIYNLOVANNVW OL 33333 F Q310N 3SIMN3HIO SS31N N39NV1 NO OMV vZ S3MIM 11 S310N vz A 5 SZ 0 9V14 3401530119 82 A O4 Ie 2v11 NMOQ 3401534119 6Z J Zs dn 3901530119 Ol 6Z 371943N3 1 9 8 INO 31lSOdWOO 201 30A 9004 JlON 33S AAN 98 9 MOIVIS S80 2 E WHOM OL al e CY 4 S 4 MOIVIS S8O NIVW ca J A NAN re 3 MOIVIS S8O NIV E 2 WHOM OL T S ce MOIVIS SEO NIV x 2 um Z A A Ts 9 MOLON SAO OG Ze MOLOM SEO NIV 6 JLYIONNNNY HOYONddY 310N 33S ALVIONANNY 549 ZZ A A 0 9 14 1VOILN3A NIV ez J 6Z 9V14 1VOILN3A NIV 92 A A gz NMOG NIV i
125. mber 2 Copilot VOR ILS receiver Only 429 data with SDI 0 or SDI 2 is used 400 SERIES INSTALLATION MANUAL Page 5 13 P N 190 00140 02 Rev M 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 15 tuned Directed freq 2 If the GNS 430 is connected to a multi channel ARINC 429 DME channel 2 of that DME is tuned 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 COHMFIG 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 and the headi
126. mperature Celsius SH ASCII characters 123 represents wind direction degrees from north SI ASCII characters 456 represents wind speed knots SJ ASCII characters sign 78 represents rate of turn degrees per second SK ASCII characters sign 901 represents vertical speed tens of ft minute SL ASCII characters 234 represents heading degrees from north SM ASCII characters 5678 represents fuel flow right tenths gallons hour SN ASCII characters 90123 represents fuel used right tenths gallons SO ASCII characters 4567 represents fuel flow left tenths gallons hour SP ASCII characters 89012 represents fuel used left tenths gallons SQ ASCII characters 345 represents error log reason indicator SR ASCII characters 67890 represents fuel remaining tenths gallons SS ASCII character 123 represents ground speed knots ST ASCII character 456 represents track degrees SU ASCII character 789012 represents distance to waypoint hundredths nautical miles SV ASCII character E represents East W represents West 345 represents magnetic variation tenths degrees SW lt N S gt 67 8901 lt CR gt lt LF gt SW ASCII character N represents North S represents South 67 8910 represents current latitude degrees minutes hundredths of minutes SX lt E W gt 234 5678 lt CR gt lt LF gt SX ASCII character E repr
127. n VO MAIN OBS ROTOR C MAIN OBS ROTOR H GROUND MAIN OBS ROTOR C and H are a buffered output that is intended to drive the OBS rotors MAIN OBS STATOR D and MAIN OBS STATOR F are each phase and amplitude shifted version of the MAIN ROTOR C output Each pair is intended to read one of the two windings of the indicator s OBS stator 4 4 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 main CDI OBS checkout 4 4 5 Main Indicator Interconnect Refer to Figure F 15 on page F 31 for the generic main indicator interconnect Refer to Figure F 16 on page F 33 for the interconnect between a GNS 430 and a Bendix King KI 209A Refer to Figure F 17 on page F 35 for the interconnect between a GPS 400 or GNC 420 and a Bendix King KI 208A Page 4 8 400 SERIES INSTALLATION MANUAL Rev M 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 1s 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
128. n Office Enclosure Page B 8 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 Q U S Department Small Airplane Directorate d Bob vedi Wichita Aircraft Certification Office ederai Aviation 1801 Airport Road Room 100 Administration Wichita Kansas 67209 July 24 2002 Mr Ric Sleigh GARMIN International 1200 East 151st Street Olathe KS 66062 Subject Amendment July 24 2002 of Supplemental Type Certificate STC SA00801 WI Reference 1 FAA Project Number ST2165WI A 2 GARMIN letter dated July 19 2002 Dear Mr Sleigh Enclosed is an Amendment to Supplemental Type Certificate STC SA00801WI amended on July 24 2002 indicating our approval of the GARMIN GNC 420 or GNC 420A installation on Piper PA 32 260 airplanes Also enclosed is the FAA Approved GARMIN Master Drawing List 005 C0076 00 Revision C dated 04 26 02 or later FAA Approved revision A copy of FAA Approved Airplane Flight Manual Supplement for Piper PA 32 with GARMIN GNC 420 Revision A dated 7 6 99 or later FAA Approved revision has already been provided to you A copy of the drawing list and data listed therein will be retained in our files Sincerely A gt Harvey E Nero Program Manager Wichita Aircraft Certification Office Enclosures 400 SERIES INSTALLATION MANUAL Page B 9 P N 190 00140 02 Rev M This page intentionally left blank Page B 10 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02
129. n 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 4 02 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 HAIH ARINC 429 COHFIG 5 21 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 MAIN ARINC 429 CONFIG Page SPEED Low Standard low speed 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 Rev M DATA IN 1 DATA IN 2 _ No unit connected to this ARINC 429 input Airdata Altitude temperature and speed information from the following Airdata
130. ne tea ey too te Pete cud F 55 AUDIO PANEL INTERC ONNEBG T L umu F 57 VORAES INDICATOR INTERCONNECT e e F 59 RMVOBLINTERCONNEC Desk sre eee h hiya haykapas sau F 61 KING SERIAL PANEL DME TUNING INTERCONNECT F 63 LIST OF FIGURES CONTINUED KING SERIAL REMOTE DME TUNING INTERCONNECT eese F 65 PARALLEL 2OF 5 DME TUNING INTERCONNECT scrisoare F 67 PARALLEL BCD SLIP CODE DME TUNING INTERCONNECT F 69 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 iv Rev M 400 SERIES INSTALLATION MANUAL 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 is 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 SERVICE PURPOS
131. ng 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 mode 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 WX 500 Stormscope interface Select the STORMSCOPE TEST Page see Figure 5 19 STORHSCOPE DOHMLOAD 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 Page 5 14 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 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 altitude mode below BLW normal NORM above ABV or unrestri
132. nge the bype design for the folloeing prodescd with the fundadeons and CORRETO A therefor eg eet Aeron nerd the o ane atid Away eyes ay ied 3 aff the Civil Air Virga respi Type Meander AMSO p s n Piper pA 32 260 oft theage Installation of GARMIN GAS 430 or GNS 430A in accordance with GARMIN Master Drawing List Drawing No 005 00051 00 Revision V dated O4 25 02 or later FAA approved revision and FAA Approved Airplane Flight Manual Supplement for Piper PA37 wilh GARMIN GNS 430 Document No 190 00140 03 Revision B dated 10 22 99 or later FAA approved revision and Condilicns Compalibilily of this design change with previously approved modifications must be determined by the installer f 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 eas d the dean hander as fhe Pede fer anl PEIER cu ne mr d decns reel verae na oa peole an n termination dade s odremido expl luo bg the Jbdminustoater of the ratto ll Pesado Bade inf ting November 26 1997 Sade vecsseed fale af vidoes October 02 1998 Kade October 29 1999 July 25 2002 vibes of the A Signature Harvey E Nero Program Manager Wichita Aircra
133. ning 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 Proposition 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 i P N 190 00140 02 Rev M TABLE OF CONTENTS 1 GENERAL DESCRIPTION C TION es hss aloe paku 1 1 2 HOUTPMENT DESCRIPTIO N nectare NE Eo s Dese uou cdd 1 1 TECHNICAL SPECIE IG A TION uu ua urbes m LE eee a ee 1 2 EETSOEMITATION eut tc Diana Sel Au ADD ES 1 7 LS IEICE NSE REQUIREMENTS eco eatis eel ec a a Ge ech ee 1 7 eo QM GLO M 1 7 IT FAULT DETECTION AND EXCLUSION E ee ee 1 7 jop WARRANTY eec usui d ena LA LEM AI M E 1 8 2 INSTALLATION DIN OND GHI ERR 2 22 ANTENNA CONSIDERATIONS cidit tee E tei e 2 23 RACK CON STD ERA IO NS os iniit tabo dH das Os tuni hou
134. nuary 25 1999 and concur with the contents The GNS 430 integrated navigation communication system incorporates adequate internal switching alerting and annunciation features within its display such that most typical installations will not require external switching or annunciation Extensive evaluations were conducted during initial certification of the GNS 430 to verify the suitability of the switching alerting and annunciation features of the system External annunciation of GPS receiver mode CDI source information leg sequencing loss of integrity RAIM message and waypoint alert are not required in most installations where the GNS 430 display is located in the center area of the vertical instrument panel For most aircralt 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 pilots seated position will not require external switching or annunciators This area is generally defined as between the airspeed Indicator on the left the center radio stack or left side of dual center radio stack arrangements on the right and vertically such that it is not blocked by the glareshield on top and not below the instrument panel or blocked by throttles control yoke etc on the bottom Installations located outside of this arca i e in a center pedestal on the opposite side of the aircraft from the pilot s station on a tilt panel behind throttles
135. og 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 JILS and vertical 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 4 2 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 Repeatstep 1 with 1 0 nautical mile CDI sensitivity The CDI sensitivity may be manually set on the AUX SETUP page using the CDI ALARMS menu item 3 Repeat step 1 with 0 3 nautical mile CDI sensitivity 5 3 5 Crossfill Check Only if dual units installed with RS 232 crossfill connected Turn on both 400 Series units 1n 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 display
136. om the aircraft manufacturer 2 Obtain an FAA approved STC pertaining to and valid for the antenna installation 3 Contact the FAA Aircraft Certification Office in the appropriate Region and request identification of FAA Designated Engineering Representatives DERs who are authorized to prepare and approve the required antenna installation engineering data 4 Obtain FAA Advisory Circular AC 183C and identify a DER from the roster of individuals in it 5 Contact an aviation industry organization such as the Aircraft Electronics Association for assistance 2 2 1 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 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 fl
137. on 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 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 400 SERIES INSTALLATION MANUAL Page 5 15 P N 190 00140 02 Rev M 5 2 21 MONITORING THE DATA LINK The Data Link is monitored on the Data Link Page There are four main page groups in the 400 Series software version 2 25 or higher NAV WPT AUX and NRST see the 400 Series unit Pilot s Guide for detailed information on the unit s Page Groups The Data Link Page Figure 5 24 appears in the sequence of AUX Pages To select the Data Link Page rotate the large right knob until a page from the AUX group is displayed To select the Data Link Page rotate the small right knob until the Data Link Page Figure 5 24 DATA LINK Page is 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 Page 5 16 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 5 3 ADDITIONAL G
138. on known to 300 nm time known to 10 minutes with valid almanac 45 seconds d Warm Start position known to 10 nm time known to 10 minutes with valid almanac and ephemeris 15 seconds Max Velocity 1000 kts Dynamics ess 400 SERIES INSTALLATION MANUAL Page 1 3 P N 190 00140 02 Rev M 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 100 mW minimum into a 500 Q load Audio Response Less than 6 dB of variation between 350 and 2500 Hz Audio Distortion The distortion in the receiver audio output shall not exceed 15 at all levels up to 100 mW AGC Characteristics The audio output shall not vary by more than 6 dB when the level of the RF input signal modulated 30 at 1000 Hz is varied from 5 uV to 450 000 uV Sensitivity S N N on all channels shall be greater than 6 dB when the RF level is 2 uV hard modulated 30 at 1000 Hz at rated audio m O OO O O ee 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 Transmitte
139. on to insure that the antenna connector is not contaminated with sealant Insure that the mounting screws are fully tightened and that the antenna base 1s well seated against the gasket Page 3 4 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 CAUTION Do not use construction grade RTV sealant or sealants containing acetic acid These sealants may damage the electrical connections to the antenna Use of these type sealants may void the antenna warranty 3 6 CABLE INSTALLATION 1 Route the coaxial cable to the rack location keeping in mind the recommendations of Section 2 Secure the cable in accordance with good aviation practice 2 Trim the coaxial cable to the desired length and install the BNC connector 330 00087 00 per the cabling instructions on Figure 3 1 If the connector is provided by the installer follow the connector manufacturer s instructions for cable preparation GASKET x i HUT X PLACE MUT AND GASKET OVER CABLE AND STRIP JACKET TU DIMENSION SHOWA COMB OUT BRAID AND TRIM DIELECTRIC TO 3 DIMENSION SHOWN tii siwa dhe 3 PULL BRAID WIRES FORWARD AND TAPER TOWARD CENTER CONDUCTOR PLACE CLAMP OVER BRAID amp ND PUSH BACK AGAINST CABLE JACKET 4 FOLD BACE BRAID OVER CLAMP AS SHOWN TRIM OFF EXCESS SOLDER CONTACT TO CENTER CONDUCTDR 68 3 INSERT CABLE CLAMP AND GASKET INTO CONNECTOR BODY MAKING SURE THAT SHARP EDGE OF CLAMP SEATS PROPERLY AND TIG
140. 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 is set to 4 at the factory MIN Minimum Sets the minimum brightness of the display The higher the number the brighter the minimum brightness Display minimum brightness has a range of 35 to 999 and 15 set to 80 at the factory Key minimum brightness has a range of 20 to 99 and is set to 40 at the factory It is prudent to verify that display and key lighting characteristics match those of other equipment in the panel under night lighting conditions 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
141. ow on IFR airworthiness approval was accomplished under the STC process on a Mooney M204 incorporating dual GNS 430 receivers Approval was granted on the Mooney installation without the requirement for external switching or annunciation under the same quidance aforementioned Installations which deviate from this guidance may have additional requirements imposed such as external annunciation The GNS 430 provides interfaces for such installations For the Piper Charokee PA32 260 approval reference STC SA00705W dated October 2 1998 For tha Mooney M20J dual GNS 430 installation reference STC SAO0735W dated January 19 1999 Also see the attached Wichita ACO letter affirming approval of the GNS 430 system without external switching or annunciation and guidance to consider when installing GNS 430 systems to avoid external switching and annunciatian sincerely Sethe Bill Stone Avionics Product Manager 400 SERIES INSTALLATION MANUAL Page B 5 P N 190 00140 02 Rev M Q U S Department Small Airplane Directorate of Transportation Wichita Aircraft Certification Office Federal Aviation 180 Airport Road Room 100 Administration Wichita Kansas 67209 January 25 1999 Mr Phil Straub GARMIN International 1200 E 141st 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 Ja
142. presents 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 lt CR gt lt LF gt lt gt carriage return character Ox0d line feed character 0x0a sign indicator Ox2b or Ox2d lt ETX gt end transmit character 0x03 T 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 from 0 0x30 0x30 0x30 to 255 0x32 0x35 0x35
143. pueg SMHV NJI Z 1 33S i T T 8 M3LLIASNVML 9 6 8 el 8 Z 8 6v 8 NI 62v ONINV Sd9 V M3LLIASNVML n G LZ LI v 9 Or L m 8v V NI 6Zv ONIMV Sd9 Ligvd 118 LOZd NNOO SW If SL zr LOOvd L8 20 L8Z 20 00 rv0006 008Z L09Z 0097 000 20 O00Z 2v 0 FOC 00 Buly xipueg 6ury xipueg 09 g8 09 8 09 g8 009 g8 UIPDUS ulppus Jejnduuo5 NINY MS W A C0 0P 100 061 N d erq 25 4 98eq S 4 2824 TVONVW NOLLV TIV ISNI SATAAS 00 12euuo21J9ju 1u 1IJ 6 ONIHV Sc 4 3ONd 33dd84 804 NMOHS SLINA 83HlO dO SLNONId NOILVASOANI LO23NNOOS3INI ANY LNONId 3Ll31dWOOD 804 NOILVIN3ARnOOG SYsdNLOVANNVAW OL 84343384 v Sd3ll31 ASVO Yd4ddN Q3NITS3ONR SV NMOHS 34V SHOLVNOISSG 3SVO 83MOI QV31SNI Q3193NNOO 38 AVN 15 ANY 0S 100 d LYOd Z NI 6zv ONIMV Sd9 JHL 3sOdM d N3HLONV N04 GASN AQV3MIV S 6 100 4 LYOd NI 6Zr ONINVY Sd9 JHL jl Z T a 6r 8 NI 6zv ONINY Sd9 Q310N 3SIMN3HIO 53131 N39NV1 9MV FZ S3MIM TIV L jlON 335 S310N gy V NI 6Zv Sd9 M3AI3038 Z AYNI 4 LY
144. push to talk switch is pressed 400 SERIES INSTALLATION MANUAL Page 5 11 P N 190 00140 02 Rev M 5 2 12 VOR DISCRETE INPUTS Page 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 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 is 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 Page 5 12 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 TO
145. r Power At Least 10 watts 16 watts for A models Transmitter Duty Cycle Recommended 10 maximum Modulation Capability The modulation shall not be less than 70 and not greater than 98 with a standard modulator signal applied to the transmitter Carrier Noise Level Shall be at least 45 dB S N N Frequency Stability 0 0005 Less than 10 distortion when the transmitter is modulated at least 70 at least 70 varied from 350 to 2500 HZ C37d Class 4 amp 6 may not provide suitable COM transmit range for some high altitude aircraft Specifications shown apply at nominal input voltages of 13 75 Vdc or 27 5 Vdc as applicable and with a nominal 50 ohm resistive load at the antenna connector Page 1 4 400 SERIES INSTALLATION MANUAL Rev M 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 in the absence of either one of the two 30 Hz modulations 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 shal
146. r later must be used See the COM VOR LOC and Glideslope antenna specifications for their limitations 2 2 7 GPS INTERFERENCE On some installations VHF COM transceivers Emergency Locator Transmitter ELT antennas and Direction Finder DF receiver antennas can re radiate through the GPS 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 ELT antenna and DF receiver 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 ELT antennas and DF receiver antennas The GPS antenna is less susceptible to harmonic interference if a 1 57542 GHz notch filter 1s installed on the COM transceiver antenna output e Locate the 400 Series unit as far as possible from all COM antennas Ante moked by vertical fin fai or domo fin E Wig NET pus Za ian Pe el CAPIT Antenna must be on t p of olrcroft 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
147. r of the mounting rack for the purpose of admitting cooling air under such conditions If a form of forced air cooling is installed make certain that rainwater cannot enter and be sprayed on the equipment 2 6 MINIMUM INSTALLATION REQUIREMENTS Below is a list of required devices for TSO C129a category 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 400 SERIES INSTALLATION MANUAL Page 2 3 P N 190 00140 02 Rev M HSI CDI Indicator or EFIS This device displays Nav Flag Left Right To From Glideslope Flag and Up Down The indicator s used in conjunction with GNS 430 VOR ILS receivers shall be TSO d Qualified GPS Antenna This antenna must be one of those listed in the accessories list or meet the following requirement
148. re F 19 RS 232 Serial Data Interconnect Figure F 20 ARINC 429 EFIS Interconnect Figure F 21 ARINC 429 Sandel EHSI Interconnect 1 400 Series Unit I Sandel SN3308 Figure F 22 ARINC 429 Sandel EHSI Interconnect 2 GNS 430 1 Sandel SN3308 Figure F 23 ARINC 429 Sandel EHSI Interconnect 2 GNS 430 2 Sandel SN3308 Figure F 24 ARINC 429 RS 232 Air Data IRU AHRS Interconnect Figure F 25 ARINC 429 Flight Control Interconnect Figure F 26 Traffic Advisory System Interconnect Figure F 27 Weather and Terrain Interconnect D D D OU UO DL LD UO DL 0 UO DL DL L D D oO LD D D UD UD L Figure F 28 Audio Panel Interconnect 400 SERIES INSTALLATION MANUAL Page F 1 P N 190 00140 02 Rev M Figure F 29 VOR ILS Indicator Interconnect Figure F 30 RMI OBI Interconnect Figure F 3 1 King Serial Panel DME Tuning Interconnect Figure F 32 King Serial Remote DME Tuning Interconnect Figure F 33 Parallel 2 OF 5 DME Tuning Interconnect Figure F 34 Parallel BCD Slip Code DME Tuning Interconnect L D D D DU L Page F 2 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 W 91 p d 2884 c 3 282d Duimea4q uonejjeisu 96 V5 1 4 o4nDiJ LNOLNO r099 009 Z 4 Quay Od 96 01 0SZ SOld I SLS Og H LT S v 98109 N r 334 So1d zlv9 0z 180 7 _
149. red 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 the 1020 Hz Ident Tone is at least 20 dB down in voice mode The distortion in the receiver audio output shall not exceed 10 at all levels up to 100 mW 1 3 7 Glideslope Specifications GNS 430 Only Regulatory Compliance TSO C34e JTSO C34e RTCA DO 192 EuroCAE ED 47B Sensitivity 87 dBm or less for 60 of standard deflection Centering Accuracy 0091 ddm or 0 7 8 mV 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 In the absence
150. roubleshooting 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 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
151. s 1 DO 160C Environmental Conditions The antenna shall meet the environmental conditions listed below and shall conform to the test requirements of RTCA DO 160C Environmental Condition Category Description Temperature operating F2 55 to 70 C ground survival F2 55 to 85 C Altitude F2 55 000 feet Temperature Variation A 10 C per minute Humidity C 95 at 55 C Vibration CLMY Turbo Reciprocating Helicopter Waterproofness S Continuous Stream Fluids F Deicing Fluid Lightning 2A Direct Effects Icing C 0 15 thick 2 Electrical Characteristics LNA Supply voltage 4 5 0 5 Voc LNA Supply Current 20 mA Maximum LNA Operating Frequency 1575 42 2 00 MHz LNA Gain LNA Noise Figure LNA Output VSWR 50 Q 20 dB Maximum 12dB Minimum 3 0 dB Maximum 2 1 Maximum LNA Input power at 1 dB Gain Compression 6 dB Minimum LNA Bandwidth 3 dB 20 dB 40 dB 3 Radiation Characteristics Polarization Operating Frequency Gain on axis at 160 beam width Cross Pole Gain LHCP on axis at 160 beam width 4 Mounting Requirements Cable connection Mounting studs Page 2 4 Rev M 40 MHz Maximum 100 MHz Maximum 250 MHz Maximum RHCP 1575 42 2 00 MHz 2 0 dBic Minimum 6 0 dBic Minimum 8 dBic Maximum 9 dBic Maximum BNC Female Four 8 32 UNC 2A studs 0 50 long 400 SERIES INSTALLATION MANUAL P N 190 00140 02 3 INSTALLATION PROCEDURE 3 1 UNIT AND ACCESSORIES The 400 Ser
152. s 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 output 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 400 SERIES INSTALLATION MANUAL Page 4 9 P N 190 00140 02 Rev M 4 5 1 11 INTEGRITY ANNUNCIATE The integrity annunciator illuminates when the GPS receiver detects a position error or is unable to calculate the integrity of the position 4 5 1 11 1 ILS GPS APPROACH Output Sinks 500 mA when GPS navigation is
153. scale deflection with a maximum course deviation output voltage of 300 mVpc 10 4 4 2 2 TO FROM jPinName Connector Pin IO _ 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 TO 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 f Connector Pin O 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 Rev M 4 4 2 4 Superflags PinName Connector Pin 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 Pi
154. 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 11 2 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 simulate reception of GPS satellite signals CAUTION Do not connect DEMO MODE SELECT in an aircraft installation 4 5 1 11 3 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 Connecto Pin X MESSAGE ANNUNCIATE P4001 6 Out AUTOANNUNCDIATE P4001 8 Out INTEGRITY ANNUNCIATE P4001 9 Ou All outputs sink up to 500 mA when activated 4 5 2 2 Switch Inputs PinName Connecto Pin 1O _ 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 Q These inputs are considered inactive if the voltage to ground is 11 33 4 5 2 3 TIME MARK OUT PinName Connector Pin X TIME MARK OUT ou
155. served for future expansion The GPS 400 is a GPS receiver certifiable for IFR 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 GPS 400 Series product lens is coated with a special anti reflective coating which 1s very sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings CAUTION The use of ground based cellular telephones while aircraft are airborne is prohibited by FCC rules Due to potential interference with onboard systems the use of ground based cell phones while the aircraft 1s on the ground is subject to FAA regulation 14 CFR 91 21 FCC regulation 41 CFR 22 925 prohibits airborne operation of ground based cellular telephones installed in or carried aboard aircraft Ground based cellular telephones must not be op
156. ses adu iE EE 2 3 ZU CPB TIN GIN WIRING NS adeste tete Le te 2 3 2 OO eB RN LO ERE RT 2 3 2 6 MINIMUM INSTALLATION REQUIREMENT S i u a u uu N u u iay a 2 3 3 INSTALLATION PROCEDURE S P UNPPERNDSACCESSORIPSu uum eh see eater ae aha dud c de s aG uh Sua 3 1 32 DATA BASE OPTION Toce 3 4 23 3 MISCELLANEOUS OPTIONS obrna ss as y mD ass Le CU CUL 3 4 3 4 INSTALLATION ACCESSORIES REQUIRED BUT NOT PROVIDED 3 4 So ANTENNA INSTALLA TION cast cata ee ete aba bh DU De d stade Soa Ld ecd secte ius 3 4 SC ABLE INSTALLATION shane eats yeas E necs 3 5 S L RACKINSTALEATION n MEE UII I IE as 3 7 3 8 400 SERIES UNIT INSERTION AND REMOVAL L enini ees be teret est e voee ba eee das 3 7 3 9 COM ANTENNA INSTALLATION CHECK GNC 420 AND GNS 430 3 7 4 SYSTEM INTERCONNECTS Z I PINAEUNC TION DIST ZEE m S e ex aia iud 4 42 POWER LIGHTING AND ANTENNAS S Qum Sans u am a bka a I ee 4 5 ER reri ecu m M UEM UG an fa ae ALS 4 6 Job NMATN TNDIC MEDI 4 7 25 ANNUNCDIATORSSWLIPICHBSU3su II UE EM ME asa 4 9 RL D A eut detto Ae Lu cA LEE 4 11 4 7 COM VOR ILS AUDIO GNC 420 AND GNS 430 ONLY sees 4 14 ES VOR DIES INDICATOR GONS2430 ONEY Josee domes RO ott er RC Desa toot aera oet REL 4 16 KERM TOB E E EUM esM M A LM CAL
157. ssistance 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 Rev M 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 design and engineering substantiation data whenever such antenna installations incorporate alteration penetration of the cabin pressure vessel by connector holes and or mounting arrangements For needed engineering support pertaining to the design and approval of such pressurized aircraft antenna installations it 1s recommended that the installer proceed according to any of the following listed alternatives 1 Obtain approved antenna installation design data fr
158. 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 EFIS Selected course heading and joystick waypoint information from the IN 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 um information from the following systems Collins Pro Line 21 Bendix King KFC 400 Garmin GTX 330 Garmin and Garmin w TIS This is a Garmin data concentration format Only high speed ARINC 429 should be used Garmin GTX 330 Garmin GAD 42 Selected course heading and true airspeed data from the Garmin GAD 42 Honeywell EFIS Selected course heading and joystick waypoint information from the following EFIS systems Honeywell Primus 1000 INS IRU Heading information from the following Inertial systems Bendix King KAH 460 Collins AHC 85 Honeywell Laseref Litef LTR 81 Litton LTN 90 100 LTN 91 LTN 92 Joystick waypoint information from a RADAR graphics unit Sandel EHSI Selected course and heading information from the following EHSI system Sandel SN3308 Page 5 2 400 SERIES INSTALLATION MANUAL Rev M P N 190 001
159. ten evidence of thal permission Hin emm red und the spportiag data which the hasi fow approved hall renan tn feed until surrenderert Mr severa revoked or w date os clherwise ni a anal by the tbutrinestoatan nf the nares s biden chala r bake of application November 10 1998 Kade recsecoet December 13 2001 Gude of Asecnce July 06 1999 Veale amended July 24 2002 tovs of the nasiq uie Aty alteration cf this certificate is punishable by a fine of Bst excerding 1 000 or imprisonment aot mrcasdimy 3 years or both FAM Plax 81 3 Z11C h amp PAGE 1 ol 2 PAGFS This certi icate say be transferred is accordance with FAR 21 47 400 SERIES INSTALLATION MANUAL Page B 3 P N 190 00140 02 Rev M dirriteh States of America Department of Transportation Hederal Abiation Administration Supplemental Type Certificate eif SAQ00800WI gt caperent do Garmin International 1200 E 51st St Olathe KS 66062 as jpocifeed Karoon meets the aimworthiness of Bint 3 ofthe Civil Air Product 5 bake Piper eost PA32 Dasenjalion of Igre Susa Change Installation of GARMIN GPS 400 in accordance with 1 GARMIN Dwg No 005 C0084 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 GARMI
160. the GNS 430 CDI key The VOR OBI output provides bearing information from the active waypoint for Bendix King Serial OBI devices based upon the GNS 430 VOR receiver When a localizer channel is tuned on the VLOC window there is a bit in the data stream set to indicate that a localizer frequency is tuned which stows the needle or drives it to the 3 o clock position 4 9 2 RMI OBI Electrical Characteristics PinName Connecto Pin O PinName Connecto Pin O 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 F 30 on page F 61 for the RMI OBI interconnect Page 4 18 400 SERIES INSTALLATION MANUAL Rev M 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 PinName Connecto Pin VO _ These pins are outputs when the GNS 430 is configured for 2 of 5
161. tics 4 6 2 1 RS 232 PinName Connecto Pin 1O The RS 232 outputs conform to EIA Standard RS 232C with an output voltage swing of at least 5 V when driving a standard RS 232 load 4 6 2 2 ARINC 429 PinName Connecto 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 F 19 on page F 39 for the RS 232 serial data interconnect Refer to Figure F 20 on page F 41 for the ARINC 429 Bendix King EFS 40 50 interconnect Refer to Figures F 21 F 22 and F 23 starting on page F 43 for the ARINC 429 Sandel EHSI interconnects Refer to Figure 4 16 on page 4 51 for
162. tion 5 2 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 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 Parameter Name 1 2 3 4 001 DistancetoGo BCD st fe fe 002 TimetoGo BCD eel 012 Ground Speed BCD st fe fe 113G Message Checksum Desired Track True Waypoint Bearing True Cross Track Distance Magnetic Variation m 400 SERIES INSTALLATION MANUAL Page 4 11 P N 190 00140 02 Rev M Label Parameter Name sd 11 2 3 4 251 DitacetoGo sd 251G _ BDistneetoGo felele 252 TimetoGo s
163. tion for Occanic Remote Operations for the following 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 Receiver 10W Comm System GNC 420A 010 00287 GPS Receiver 16W VHF Comm System GNS 430 010 00139 GPS Receiver 10W VHF Comm VOR LOC Glide Slope GNS 430A 010 0028564 GPS Receiver 16W VHF Comm VOR LOC Glide Slope System FDEPRDCT 006 A0072 00 FDE Prediction Program Software Revision B As agreed upon in GNC 400 500 Plan for Software Aspects of Certification for FDE GPN 005 00077 63 Revision A these changes have becn 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 A Spc UA Roger A Souter Aerospace Salet Engineer Electrical and Mechanical Systems Wichita Aircraft Certificatio
164. titude Range 1 500 ft to 50 000 ft Input Voltage Range GPS 400 11 to 33 Voc Input Voltage Range 22 to 33 Vpc GNS 430 011 00280 00 and GNC 420 011 00506 00 Input Voltage Range 11 to 33 Vpc 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 A 13 75 Voc GNC 420 Main Connector GNS 430 Main Connector Power Requirements P4002 15 mA 27 5 Vpc not transmitting COM Connector 3 0 A 27 5 Voc 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 Vpc not transmitting COM Connector 3 0 A 27 5 Voc transmitting GNS 430 011 00280 10 30 10 mA 13 75 not transmitting GNC 420 011 00506 10 6 0 A 13 75 Voc transmitting Superflag Power Requirements 500 mA max per superflag output 27 5 Vpc 1 0 A max Q 27 5 Vpc on P4001 Main Superflags 1 0 A max 27 5 on P4006 VOR LOC G S Superflags Software RTCA DO 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 b AutoLocate with almanac without initial position or time 5 minutes c Cold Start positi
165. tput 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 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 Vrms into a 10 load With a Standard Localizer Centering Test Signal applied VOR LOC COMPOSITE OUT is 0 350 0 05 into a 10 kQ load 4 8 2 7 ILS ENERGIZE Connector Pin VO X 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 WA 4 8 8 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 VOR ILS Indicator Interconnect Refer to Figure F 29 on page F 59 for the VOR ILS indicator interconnect 400 SERIES INSTALLATION MANUAL Page 4 17 P N 190 00140 02 Rev M 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
166. tputs 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 F 18 on page F 37 for the annunciators switches interconnect Page 4 10 400 SERIES INSTALLATION MANUAL Rev M P N 190 00140 02 4 6 SERIAL DATA 4 6 1 Serial Data Function 4 6 1 1 RS 232 The 400 Series unit is capable of interfacing with other aviation instruments by transmitting RS 232 Type 1 often known as ARNAV format and Type 2 often known as Northstar format data on the GPS RS 232 OUT 1 port 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 sec
167. ude 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 F 13 on page F 27 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 except the COM transmitter and the NAV amp G S SUPERFLAG outputs 4 2 2 2 Lighting Bus PinNam Connector Pin VO LIGHTING BUS HI P4001 LIGHTING BUS LO P4001 The 400 Series unit can be configured to track 28 Vpc 14 Vpc 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 Connector WO 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 Rev M 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 F 13 on p
168. wing 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 is 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 Rev M 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 Garmin GTX 327 Icarus Instruments 3000 Shadin ADC 200 200 2000 Shadin 8800T 9000T 9200T Shadin 9628XX X Fuel Air Data Computer Shadin fuel Serial fuel flow information from the following units Shadin 91204XM Digital Fuel Management System Shadin 91053XM Digital Fuel Management System JP Instruments EDM 700 or EDM 760 Engine Monitor 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
169. x 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 Manual 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 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 Applicab
170. z E LZ dn 9 14 1VM31V1 NIVW 8 Z 9YJ4 1VM31V1 NIVW zv A A 92 WO3MJ4 NIV gy Jj H SZ Ol NIVW LZ A A ez LHOIN NIVA OZ H LZ 13314 NIVA IV60Zd Loord V60Z IM OF SNS NIASIVO UOILOBIADN W 93 G ue q 9 4 9Seq 982d 120uuo2491u J01e2Ipu UEN W807 Ix 41 4 INQ SOO S80 AYNI INO NIS S80 AYNI NI NOILVIIOX3 S8O AYNI Nanlad 590 NI 39VON3J 901 594 AVNI JOVONA AViI3s NI 9Vl41 Wa4slv NI OV14 1Vs83lVl NI NOsSi c NI NI 1 4 AAG IVS3lVI NI 1331 A38 Was bv JOLDOIPU DOIADN Uu ol AVN AYNI AVN AVN AYNI AVN 3ON343438 NMOHS SLINA YSHLO 4O SLNONId NOILVASOANI NOILVINAJADQOOQ SadsniovdnNVW OL 43434 193NNOO983INI QNV 3ldJlidWOO LOOVd JNO ANY VE ANY S SNId N33A 148 cO OV 100 061 N d TVONVW NOILVTIVISNI SAINAS 007 Of NY S SNid LOOVd SMOlISIS3H v L WHOM OL QQV HOLVOIQNI V80Z IX V OL LINNA S3lM3S OO V AHL LOANNOOD OL 5 ADVLIOA AlddNS S43MOd 51 JO LNdNI NOILOANNOO amp ddOsd AOS NOILVINAWNNOOG V80c IM OL 83434 NO 1 SI V8Oc IM AHL JOVONS AV 1384 3Hl dO NOILOANNOO Y4dOdd C 4SIMYSHLO SSFTINA 4394 1 YO vc 534 TIY I SALON

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