Home

GTXTM 330, GTXTM 330D TRANSPONDER INSTALLATION MANUAL

Contents

1. 25021 00 8 COT TI 1687 a 8 911 2272 619 99 1 9 27 897 22 11 AN 0 12 928 197221 88 8 4821 42711 LT bll 93 m 7 0821 70 11 97192 166 SNOISNIMIG 7 S YZI 06 7 Lr 218 0276 10 5279 0 091 0679 0 2761 9 59 1 15 AT9INISSV UOISTAOY querq 9884 9 9924 Ajquiassy 1401994 409 066 15 2 8 aunbi4 OO 00 94000 421 QO 18 02200 066 0 034 SV 0000 96 29 48100 066 DV 10193180 HLIM 3114405 LON OD 00 22000 212 6 532114 2 01 92209 117 03119915 LAN 939414 2 00 22000 212 0 ar yeze9 112 6 83381 02 0
2. LNONId 2 404 NOILVLNAWNDOd SYSYNLOVANNVW OL 43434 75831131 3572 YaddN SV NMOHS 6 1 91 5304 Nid 35 2 3 7 IOW 9 NI YSGNOdSNVYL AHL SJOVId 1 9 4 40 4015 1 15 SMOTIV 10984 262 54 29 1099 NI 78 2 38 914 43434 LINN 3143 009 007 5 OL NALSAS 2144 1 123 02 LON OG LAVMOYV GaSN SIL 508 627 Q334S H9IH 4 2144 SIL 500 SIL M JHL 5 1 0 19 VLVG 53 02 LVHL YOLVYLNJONOD VLVG SI 19 904 JHL z ISIMUIHLO 5531 439 1 YO SJYIM 11 71 5310 ER QJAYISIN 6r YILLINSNVUL AYNI 02 62 AYNI LY 2 8 92 8269 95 545 533 6 14914 YaLLINSNVYL 9 6 82 9 MILLINSNVAL Lz
3. 91 01 100 100 vz 2 552 54 123135 5 TYNUALXI 9 123135 123 02 SIL 310 335 202 82 2100 627 lt u og 100 627 A E H Ze Y 1 627 JIONOdSNVUL Z Ogg 19 335 9 100 100 2 NI 22 54 123135 5 123135 123 02 SIL 310 335 82 2100 627 310 335 og Z 100 627 A A NI 629 310 335 Y 10564 l 0686 19 NINSV9 12 1 Z0 L0Z00 061 066 XLO XIGNAddV UOISTAOY C0 L0C00 06 44814 91 0 9884 lt 1 0 9884 5 066 19945 6 2 Aejds q 77 2 941614 20 18100 06 N d NOILVTIVLSNI Y3GNOdSNVAL SI YO 38 LZS X19 OL 83434 5 ZZS XI 30 JHL 803
4. 9 2 330914 NOILOAS 335 4 9 2 TVIMIS FIONIS OSS X19 04 4 4 8 3543438 SLIOA OG 4 16737 30 534010 360 YAGOONA 4 530014 LNOHLIM 5 SV 0350 38 AYN 553 3 311 15 SNOILVTIVLSNI ONILSIXS 7530010 NOILVIOSI gt 3009 SNIVLNOO 0696 X19 3 1 p 43 0 ISIMMIHLO 5531 39 1 53 JION 335 SALON 4 JLON 445 NONNO9 2 YIGNOdSNVUL 29 vo 4 9 29 4 8 va 01 28 4 6 4 4 ZV a LV 4 2 vd 4 Z JION 335 lasta 40 194145 5 YAMOd QIHOLIMS 30 11111 LO va Jan 68 9 30 11111 VV LV 3 11111 OSS 19 5 XIGNAddV UOISIADY Z0 L0Z00 061 ZT 9884 9974 066 XLO 19945
5. 14 6 2 941614 OL 014 5 334 1 30141 5 QALSIML 19014 1 5 YOLONGNOD 319 5 0340134 5 MSHOIH 90 S NOISMJA 05 LSAW Ogg X19 JHL 5 SND NALSAS 0 X19 OL 013 5 731 19211330 15 4 58 30 045 94131545 OL 3 319 5 03014 5 051 1Y LINN 4 VLVG 1VINIS 3 13234 AINO NYO 549 72 HOLIMS 319901 lt 91530 TOGNAS 7 4310 ISIMMIHLO 5531 0 9 1 YO 534 TV 71 5310 2 lt 2 5 11 46 46 A 014 10084 IS TYNDIS 1 006 OND gt 20 ZZS 1X SSL 549 006 99 00 INO 25259 649 yz 2 NI 552 54 gt s 123135 ASGNVLS TVNYILXI TYNOIS a Ae a 1 YFIGNOdSNVUL 9 252 53 8 310 335 2 ALON 335 2 Ogg X 9
6. 25 25 2 6 Installation Approval Considerations for Pressurized Aircraft 2 1 GO ran aN sha aa ig ade 25 3 INSTALLATION PROCEDURE Ss NNN 9525 an 30 522 Post Installation n EREE 4 Or 42 Power and Lighting A 4A A 4 6 Data Electrical 51606 5 5 a 330 Installation Manual 190 00207 02 Page Revision 5 POST INSTALLATION CONFIGURATION AND CHECKOUT PROCEDURE
7. Figure 2 2 GTX 330 Unit Rack 115 00294 00 GTX 330 Installation Manual Page 2 7 190 00207 02 Revision K This page intentionally left blank Page 2 8 GTX 330 Installation Manual Revision K 190 00207 02 3 INSTALLATION PROCEDURE 3 1 Unpacking Unit Carefully unpack the equipment and make a visual inspection of the unit for evidence of damage incurred during shipment If the unit is damaged notify the carrier and file a claim To justify a claim save the original shipping container and all packing materials Do not return the unit to Garmin until the carrier has authorized the claim Retain the original shipping containers for storage If the original containers are not available a separate cardboard container should be prepared that is large enough to accommodate sufficient packing material to prevent movement of item within the container 3 2 Electrical Connections All electrical connections except for the antenna s and shield ground are made through a single 62 pin D subminiature connector see Figure 4 1 The card edge connector may be used to terminate shield grounds to the GTX 330 back plate Table 4 1 lists the electrical connections of all input and output signals See Appendix C for interconnect wiring diagrams and cable requirements for each signal Required connector and associated hardware are supplied in the connector kit P N 011 00583 00 CAUTION Check wirin
8. 3009 1311 4 103 0 74 0350 ATIVOIdAL 300N AGONVIS YNNILNV NI LINN LVHL ANNOYS OL 61 106 lt 64 ABGNVLS 79 YNNILNV WOLLO 2 0119373 2 5314 3 NOILVNINYSLIG 04 22 10664 1 5 49 11 10594 HOLIMS LVNOS 40 75 62 NOILOIS 335 2 0601 SI 5501 318 2 WNNIXYN JANNA SSINYYH OLNI 30 1 8 318 0 VNNILNV GINOHS 3572 NI 553 TWOILOVYd SV 4 SV 6 314 2 JHL 31004 5 335 08 SNA 9 29 05 NOWWOO ALITI ILVANOONI NMOND 513004 TIY 318 4 38 LON AYN 35104 NOISSINdANS 043 01 535114 NOISSAYddNs 9 vO 9 109 3 504 5143202 50 35 16 10664 NOISSAYddNS X19 AHL OL 5451 SdNV Ads 8 SI 104100 G3HOLIMS LNJUUNI 394005 3111058 72 5 ol 93811034 NAHM
9. 91912514 066 1 7 2 941614 CaSO SI dl 13 4 3 1 LNG 0350 38 OSIY 1431 2144 1 34 11 12313530 ANY 123135 OL 10114 MOTIV LON 5300 NMOHS 4 TANVd HL 5 103135 0411041 9 10114 49538 403 Ol 43334 0 5 ONILLNdLNO 3 5 31545 OIGNV 19 53100 10 lt 64 LAdNI 123135 8 0 OL 43434 531435 006 00 JNYS 3 OL WALSAS 2144 1 LOANNOO LON OG 13 035 SIL c0 L0C00 061 1091151 066 XLO SASTINd LNAGI LINSNVYL OL Ogg 19 AHL ASNVO TUM OL 21 10 123135 1 30 40 NOILOINNOO AYVLNSWOW 76 SNOILVTIVISNI 0350 ATIVOIdAL AGOW 15 OL NIHM lt lt 1 10 64 123135 AGONVIS NOILOJS 335 08 SNM 9 29 ONIN XIGNAE ALITI ILVANOONI STSGOW TIV 318 4003 38 LON AYN 15104 NOISSSYddNS 3JWG YFIGNOdSNVYUL WOYN
10. LOANNOOUSALNI 0 0 007061 066 XLO XIGNAddV C0 L0C00 06 4 9 2 984 5 2 enuen 066 XLO pardus 08 089 5 9 01022 XLD 5 9 OL 0131 5 YOLONGNOD 33861 5 QALSIML 11 2 2076 MS SLINN NI 1904 1 SLVWYO4 SIL M 2 LINN AWNVS OL NALSAS lt 9 530 1 5 2113 1 123 02 LON OG L4VYONIV NI GaSN SI SIL NIHM 5410 1 915 lt 1VNOIS 9 ZU lt CZ zez sy 267 6 ZZ 5 gt zz NI 262 54 8 SNO UILUIDS 100 31343518 9 gt 9y 123135 123 02 SIL NI 627 gg 205 A 100 677 2 310 335 NI 6S gp lt H is LNO 629 335 zr 00 lt 100 D 5101 OZXN 59495 005 007 10 UILUIDS LOANNOOUSALNI XIGNAddV UOISTADY 8 2 L O
11. gt 0 ta JONLILIV Lh gt 6 gt 41 gt 7 r u 00 d L 335 lt gt 0 1 0155344405 1 3 LL gt gp 123135 LOINNOO SIL 9 310 335 T T 6 82 8 2 100 87 og Z 100 629 Ly A gt a 1 NI gp H H ze Y 740074 gt cy IH 508 ONILHO A S A OL 508 A 82 3101 35 103135 YaLSVW SOINOIAV 2 310 315 4 100 G3HOLIMS 22 1 _____ g 22 12 09 YaMOd LIVYOUIV LAVYONIV 55 11 VS 4 96 2 YaMOd 13 3LON 33 gt 14 208 YIMOd 1 86 11 vs IZ 14 27 10554 0 56 LOANNOOUSALNI XIGNAddV 9 44814 7 0 9884 lt 2 ed 08 0 089 SND 01022 941614
12. 40 SLNONId LOANNOOUYSLNI ANY 1 3134140003 404 5434 OL 43334 77 3009 1311 VLVG 39044 OSIY NVO 3 9 FHL 0890 54 VIA YSHLONV OL LAdLNO OSIY NVO Ogg 19 OL VLIVG 39 NOILVANDIANOO VIA 03103135 44350 404 105 3304 05 1 35 1311 39 AVW VIVG SCNLILIV 72 51 10 5541 39 1 534 TIY 5310 2 x 100 A z LY 9QOld 252 594 LI LS LS LOLd 10064 10074 1 00 Hun Hun IX SSL 549 sees 005 sales 00 ulw UILUADS A AI I OM 549 01 100 292 54 6 S 100 252 5 9 L O 0002 240 4 10026 310 335 002 20 4 10006 10088 oq 40 lt 3921101795 NOWNO9 9 9 9 06 vo 21 21 9 23 l 8 4 01 01 01 01 28 6 6 6 6 18 S S L vv 5
13. 5 1 Opero 5 1 32 Coni mahon Pa eS E 5 5 3 Enhanced Surveillance a gn in 5 23 APPENDIX CERTIFICATION DOCUMENTS APPENDIX B ASSEMBLY AND INSTALLATION DRAWINGS APPENDIX INTERCONNECT DRAWINGS Page iv GTX 330 Installation Manual Revision K 190 00207 02 LIST OF ILLUSTRATIONS FIGURE PAGE 2 1 Antenna Considerations 2 1 NLR T 2 7 Rear Connector 4 1 4 2 Dual GTX 330 Single Encoder Serial Input 0 4 5 Ay GTA 33050 Update 4 9 55 5 1 paa ap AND a 1 B 2 GTX 330 Connector Rack Assembly Drawing 2 000000000000000000000000000000020000 B 3 B 3 GTX 330 Recommended Panel Cutout 10156 B 5 1 GTX 330 to 400 500 Series Units Typical Interconnect Wiring Diagram 1 C 2 GTX 330 to CNX80 GNS 460 Typical Interconnect Wiring Diagram
14. 1 5 1 6 3349349 53715 ISN LIM 123 SLOVINOO 3715430 4350 GINOHS 81 1334 01 40 5530 3 NI 04 SI HLONIT JHL ZZ GINOHS SNOILOANNOO 3S 3SIMYSHLO SSTINN 9 1 53 SALON 7 LV ze 914 01 100 8 JLON 335 18 H s IH 100 8 gt vz NI 252 54 5 4 310 335 T 77 LS TYNOIS lt 100 292 84 6 1 335 D 252 84 3LON 335 16 01553 44405 3 HOLIMS 504 1 1 gt 21 103135 1 30 TVNNALXI 2 310 315 6 29 100 YaMOd 22 1 22 LZ 22 gt og 2 13 22 13 OQA 89 11 ILVNUILIV TYNOILAO VS 4 gt 95 2 13949 22 109512 310 335 4 gt LAVYOMIV 66 11 vs 10912 10664 oge 19
15. 5 ANIM SMVL s4 zr _ 5 549 se 6 ade 82 L 549 lt 1 08 0058 2 00rd 59495 006 007 NINAVO9 3 JLVIONNNNV LL 549 sr Le 629 549 sr H H INO 549 17 A E E ce LNO 6277 549 Ze 10058 Hun 10074 91125 005 007 LNO LNO 194145 2 100 2602 5 100 194145 LOANNOO SIL INO INO 055 NINAVO 12 1 XIGNAddV UOISTADY 02 02 2884 61 0 9884 19945 2 6 2 941614 20 10000 061 066 XLO 194145 5 114100 YAMOd 5 Yo co t9 ca JONLILIV VV 11 095 19
16. C 3 C 3 GTX 330 to CNX80 GNS 480 and Simplified Interconnect Wiring Diagram C 5 C 4 GTX 330 Interconnect Wiring Diagram Discrete And Audio Connections C 7 C 5 GTX 330 Interconnect Wiring Diagram Serial Devices Connections C 9 C 6 GTX 330 Interconnect Wiring Diagram Altitude and Temperature 11 7 Dual Transponder Interconnect Wiring Diagram Dual Display Connections C 13 C 8 GTX 330 Interconnect Wiring Diagram Aircraft With TIS C 17 C 9 Dual TXP Interconnect Wiring Diagram Encoding Altitude Connections C 19 LIST OF TABLES TABLE PAGE Sek Bin 3 1 2227 Recommended 10015 FA aaa 3 1 4 4 1 4 2 Aircraft Power 5 2 4 3 223 Lighting aaa 4 3 44 Temperature 4 3 4 5 Encoded Altitude Pin Assignme
17. 17 Assistance Flight Standards Inspectors the resources to respond to questions regarding the 18 Implementation and Record Keeping For major alterations performed accordance with field approval policy the owner operator operating under Part 91 is responsible for ensuring that the ICA 15 made part of the applicable Section 91 409 inspection program for their aircraft This is accomplished when a maintenance entry 15 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 GTX 330 Airborne ATCRBS Mode S Transponder Equipment Unit 011 00455 oo 20 011 00455 30 011 00455 50 Notes See Section 2 2 for part number and complete TSO classification and description All versions of the 011 00455 are class 2A except 40 50 which are class and are obsolete Page A 4 GTX 330 Installation Manual Revision K 190 00207 02 UOISTAOY C0 L0C00 06 1 9924 5 066 066 19 L
18. 5 sd 2 45 UILUIDS 91299 1013 HOLIMS 1440 QJLNNON 13 01 100 2752 54 S 1 O IH 1 0 gt 193135 ASGNVLS TYNYILXI 3 9 Sd uud oO 9 Os pz Z 2562 55 100 ZZS 77 NI 22258 0 LS IVNOIS l OSS X19 5 XIGNAddV UOISTAY pZ D 9884 ET 9884 19945 6 2 941614 20 10000 061 066 XLO TVNOIS 92 54 100 262 54 193135 AGONVIS 104100 YAMOd 5 vO JONLILIV LO vd JONLILIV JONLILIV JONLILIV JONLILIV JQNLILIV JONLILIV 2 OFF 19 292 54 11 46 46 LOld 10064 10074 1X 00g OND 1 66 549 006 sees 007 UILUIDS ulog 549 16 gt 77 TVNOIS 42 gt 5 9
19. INVAJULV 49074 13 5 319 5 3013 5 519014 1 5 YOLONGNOD 33 1 315 3 348 GALVNINYSL 1 5 YOLONGNOD JJ9HL 939731 QALSIML LINN GNNOYD 9131 5 T YOLONGNOD FIONIS 03013 5 3104 319 15 HOLIMS SNOILVNOISAG IOEWAS 701 1134 LIV LIV 8 310 335 UILUIDS 01 262 54 100 2 lt 04 5 1 9 UILUIDS 5 9 2642 54 9 262 54 8 5 9 90 158 05 321110 LSNW OSE X19 FHL 6 35 SI 1 GINOHS 104 5 OSIY 5 YNNAINY AYN GSHOLIMS LYSIV 2143 841 3 0 1 12313530 123135 OL 10114 JHL MOTIV LON 5304 NMOHS 13 4 JHL 78 PALUN das 8096 X19 LON 108
20. 13 OIANY 0350 38 OSIY 104 5 8 9 3910913 OL 93334 LINN 31435 006 007 IWYS OL 31545 2144 81 34 11 10313530 123135 Ol 10114 MOTIV LON 5304 NMOHS NOLLVANDIANOI 13 4 IHL 9 ONIANYT SI JGOW 5302 14 YAWIL 1 4 40 4015 193135 AGONVIS NAHM SNIVNAY 1404 100 2 1904 JANN 0 MS SLINN NI L 1904 14 15 SMOTIV 66 29 10664 318 SLVNYO4 SIL M 9 NINYVS 5 Q3LON 5531 39 53 71 5410 T NYNLIM NYM LIV ze lt 9 335 NI le bey E Ore 0 6 gt 91 123135 8 15 1 3 3 JLVIONNNNV 1 549 lt 11464 Y 629 549 gp 2 657 19 2 0054 NIN4V9 100 MIO
21. Page 5 14 GTX 330 Installation Manual Revision K 190 00207 02 FORMAT Format This field determines how the pressure altitude 15 shown the GTX 330 display SELECTION DESCRIPTION FLIGHT LVL DEFAULT The pressure altitude is displayed in hundreds of feet For Flight Level example a pressure altitude of 12 300 feet is displayed as FL 123 FEET Pressure altitude is displayed feet METERS Pressure altitude is displayed in meters ID VFR Transponder Code This field is the four digit code that is selected when the user presses the GTX 330 VFR key In the United States 1200 1s the VFR code for any altitude The default is set to 1200 ALTITUDE ALERT DEVIATION Altitude Format This field determines the amount of altitude difference from selected altitude to generate an altitude alert deviation It is set to 200 feet the minimum altitude at the factory SQUAT SWITCH The squat switch field may be set to either YES or NO Second CONFIGURATION Page Selecting YES in this field sets the GTX 330 to use the squat switch to determine lift off Selecting NO sets the GTX 330 to use Automated Airborne Determination from other sources DELAY TIME This is the number of seconds the aircraft must be on the ground before the GTX 330 automatically switches to GND mode when it has a means of determining the aircraft 15 on the ground It has a range of 0 zero seconds to 99 seconds with the defa
22. 5 3 Enhanced Surveillance 5 The following table shows equipment connections required to meet Mode S Enhanced Surveillance EHS criteria Included are a list of parameters to other on board avionics equipment formats that are accepted Req d field denotes which formats are needed to make the 330 system Mode 5 5 capable It is the responsibility of the installing agency to determine whether the equipment that interfaces with the Garmin GTX 330 Mode S transponder actually provides the required output Make sure the interfacing equipment outputs the correct parameter to the GTX 330 to meet Mode S EHS See the vendor s specification for configuring the external data sources for the data they are capable of providing Parameter Label Re 4 AFCS GPS FMS EFIS Shadin Display Fuel Air Data AFCS Modes Barometric 234 Setting 235 FCU Selected Altitude FMS Selected 102 Yes Altitude Ground Speed Ground Track Angle Indicated Airspeed Inertial Vertical 365 No Velocity 205 320 Mach 2 wwe 8 x Heading 325 Yes x 20 vee ff x Te irspeed True Track Angle Rate Note 1 Supplying one selected altitude is sufficient Mode 5 EHS compliance Note 2 Supplying either Indicated Airspeed or M
23. 22 54 310 335 9 7 lt 2 5 2 5 0 335 08 2 087 SN9 Gd 2 S HOLIMS Y 1409 1444 29 QJLNNON 05 MIH9IH 9075 1405 3211110 LSNN OFF 19 FHL 4 9 08 2 SND MNALSAS NI 5 022 19 4 31 1 211 301 LSNW 54 30 045 1 4 2 94131545 OL 4 gt 8 and OSIY INIL LV LINN VLVG 1 1 35 AINO 549 JHL gt 01 ONILVY 3543 434 6 SLTOA OS 15 31 30 534014 35 LNdNI gt 3 03 gt 4 534014 JHL 9 LNOHLIM SV 0350 38 lt 553 0311 15 534014 SNOILVTIVLSNI 9 5 4 534014 NOILVIOSI 3002 34 111 SNIVLNOO 088 X19 A 5 5531 39 1 53 TIV 2 310 335 10 5310 4 4 310 335 29 NONNOO 4 05 4 gt 9 23 gt 12 4 gt 8 va 4 4 01 4 6 18 gt J 1 6 4 gt v Lv 4 gt 2 4 2 310 335 JO gt EN gt 16 10664 12 1 104110 Y3MOd G3IHOLIMS vO JAGNLILIV AGNLI
24. FIGILVANOO 38 LON AWN 365104 NOISSINdANS 5 MIHLONV 01 535104 01553 4405 109 3 11504 514322 50 35 16 10864 01553444015 4 8 2 38 914 OL 3434 LINN 531415 009 007 ANVS JHL OL NALSAS 2114 1 LON OG 0350 SI SIL NAHM 79 SI 123135 915 TWNYSLX3 NIHM 531435 005 007 JHL OL Z 1404 627 GALLINSNVYL 38 LON 5 82 Og 5 4 Z Z LNO 627 ANY 5 4 a 100 JSN SIHL 03103 0 SI 193135 815 315 JIONOASNVYL 530 14 ANY 1 9 14 40 4015 LYVIS GILYNOLNV SMOTIV 104 66 26 10864 84124135 15 1 JHL LINN AHL LINN OILVNOLNV 8 YO 12 10664 LAVYOMIV OL 031 1 10694 123135 SOINOIAV Ogg 19 JHL OL 82761 SL SI 104100 YAMOd 5 AHL LNAYYND 304 05 WNWIXVW 3111058 72 43411034 NAHM OMV 22 53215 350 04 34 LIM
25. IHL 5 915 ONISN 15 34 045 1 dl 2642 54 45 481 310 34 ON NOILVTIVLSNI 319 16 31 AINO JSN SIL 8350 LON LINN 531435 006 007 035 AHL OL 104100 292 54 LOANNOD 15 549 OL 43940 NI 53 1 Z 104100 LON SI VLIVG 5 31034 NI OSS 19 AYVNINd N3HM SNOLLVTIVISNI NI 304 S 5 012365 335 531 35 009 007 235 3HL OL 03103 9 NYO WILSAS 72104100 VIA 38 AVA YSHLO FHM 104100 627 ONIY LINSNVAL SIL NI GFTIVISNI SI SIL NOdN 3004 532 14 YANIL 1 9113 40 4015 ANY 1491 G3LVNOLNY SMOTIV LNANI 26 10664 627 71 5310 c0 L0C00 061 066 XLO NYNLIM LIV 25 A EIEEE 91 NI LIV Ie 9 310 335 F lt 3LON 335 NILSAS
26. GTK 330 3300 TRANSPONDER INSTALLATION MANUAL EFNA 9 gt S GARMIN Garmin Ltd or its subsidiaries 190 00207 02 Revision K June 2005 Copyright 2002 2005 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 151 Street Olathe KS 66062 USA Telephone 913 397 8200 Aviation Dealer Technical Support Line Toll Free 888 606 5482 www garmin com Garmin Europe Ltd Unit 5 The Quadrangle Abbey Park Industrial Estate Romsey SO51 9DL U K Telephone 44 0870 851241 RECORD OF REVISIONS 51 03 Software SW 3 03 20932 0
27. 9 keys CONTRAST This page is only displayed if manual contrast mode is selected in Configuration mode Contrast 15 controlled by the 8 and 9 keys DISPLAY This page is only displayed if manual backlighting mode 15 selected Configuration mode Backlighting is controlled by the 8 and 9 keys Page 5 4 GTX 330 Installation Manual Revision K 190 00207 02 5 2 Configuration Pages The configuration descriptions given in this section reflect software version 3 06 or higher Software version 4 01 is required for Mode S Enhanced Surveillance EHS When connecting the GTX 330 to a GNS 480 CNX80 the transponder can be configured from either the GNS 480 CNX80 or the GTX 330 Although possible from the GNS 480 CNX80 configuration from the GTX 330 front panel offers more functions and easier to interpret displays Holding down the FUNC key and pressing the ON key provides access to the configuration pages The FUNC key sequences forward through the configuration pages The START STOP key reverses through the pages stopping at the Menu page The CRSR key highlights selectable fields on each page When a field is highlighted the 0 9 keys enter numeric data and the 8 9 keys move through list selections Press the CRSR key to accept changes When a field is highlighted pressing the FUNC key moves to the next configuration page without saving the changes Changes made through the configuration pages are stored in EEPROM memory
28. Applies to aircraft altered by installation of the Garmin GTX 330 Definitions Abbreviations None N A Precautions None N A Units of Measurement None N A Referenced Publications Garmin GTX 330 Installation Manual P N 190 00207 02 Garmin GTX 330 Maintenance Manual P N 190 00207 05 Garmin STC STO1125WI Garmin GTX 330 Pilot s Guide P N 190 00207 00 Distribution This document should be a permanent aircraft record 2 Description of the Alteration Installation of the Garmin GTX 330 with interface to Encoding Altimeter or Blind Encoder Refer to Section 4 and Appendix C of this manual for interconnect information Antenna installation removal and replacement should be in accordance with applicable provisions of FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A 3 Control Operation Information Refer to the GTX 330 Pilot s Guide 4 Servicing Information N A Page A 2 GTX 330 Installation Manual Revision K 190 00207 02 10 11 12 13 14 15 16 Maintenance Instructions Maintenance of the GTX 330 is on condition only Periodic maintenance is not required Refer to the GTX 330 Maintenance Manual Troubleshooting Information Refer to the GTX 330 Maintenance Manual Removal and Replacement Information Refer to Section 2 of this manual If the unit is removed and reinstalled a functional check of the equipment should be conducted in accordance with Section 5 of this manual Diag
29. LVL Level Shows the current level of key lighting based on the lighting input source lighting bus voltage or the ambient light if the source is PHOTO and the settings on this configuration page This field has a range of 0 zero to 999 but is not a user entered field display only RSP TIME Response Time Sets the speed with which the brightness responds to ambient light changes only for AUTO key lighting mode The higher the number the slower the key lighting responds This field has a range of 0 to 7 and is set to 4 at the factory MIN Minimum Auto Only Sets the minimum brightness of the key lighting The higher the number the brighter the minimum brightness Key lighting minimum brightness has a range of 0 zero to 99 and 15 set to 8 at the factory It is prudent to verify that key lighting characteristics match those of other equipment in the aircraft panel under night lighting conditions KEY SRCE Key Lighting Source Auto Only SELECTION DESCRIPTION PHOTO Photocell DEFAULT Key lighting level 1s determined by the ambient light level as measured by the photocell on the GTX 330 Backlight level tracks a 14 Volt DC aircraft lighting bus Backlight level tracks 28 Volt DC aircraft lighting bus Backlight level tracks a 5 Volt DC aircraft lighting bus SLOPE Auto Only Sets the sensitivity of the key lighting brightness to changes in the input level The higher the number the brighter the key li
30. To exit the configuration pages turn the power off Then turn on again without holding the FUNC key for normal operation The configuration page sequence is as follows menu categories are listed in parentheses Jump To Menu Audio and Messages 1 Audio and Messages 2 Traffic Messages Display Mode Display Backlight Key Backlight Contrast ARINC 429 Input 1 First I O Configuration page ARINC 429 Input 2 Second I O Configuration page ARINC 429 Output RS 232 Input Output Operation Configuration 1 First Aircraft Configuration page Operation Configuration 2 Second Aircraft Configuration page Temperature Aircraft Address Flight ID Aircraft Type Gray Code Input External Switch State Analog Input RS 232 Input Display ARINC 429 Input Display 1 ARINC 429 Input Display 2 GTX 330 Installation Manual Page 5 5 190 00207 02 Revision K CONFIGURATION MENU CONFIGURATION MENU Page The TO menu page provides the capability to select a Configuration mode starting page without having to step through all of the pages Press the CRSR key and sequence through to the desired selection with the 8 and 9 keys Jump to the selection by pressing the CRSR key again with the desired selection highlighted FUNC key steps to the next configuration page after which the START STOP key reverses until stopping at the JUMP TO menu page SELECTION DESCRIPTION DIAGNOSTICS Jumps to Gray Code Input
31. 11 25 inches 286 mm measured from face of aircraft panel to rear of connector backshells GTX 330 GTX 330D Unit Weight 3 4 16 1 5 kg GTX 330 GTX 330D Rack Weight 4 2 Ibs 1 9 kg Installed with rack and connectors 1 6 3 Power Requirements Characteristic Specification Input Voltage Range 11 0 to 33 0 Vdc See the Environmental Qualification Form for details on surge ratings and minimum maximum operating voltages Power Input 22 Watts Typical 45 Watts Maximum Maximum Full TSO Reply 1 6 27 5 3 1 13 75 Rate 1200 PRF Code7777 0 85 A 27 5 Vdo LTA 8 13 75 Vdc 1 7 Installation Approval The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those installing 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 TSO articles must have separate approval for installation in an aircraft The article may be installed only if performed under 14 CFR Part 43 or the applicable airworthiness requirements For GTX 330 TSO compliance and STC see Appendix A For antenna TSO compliance refer to antenna manufacturer s literature Page 1 6 GTX 330 Installation Manual Revision K 190 00207 02 1 8 Aircraft Station Licensing Requirements The Telecommunications Act of 1996 effective February 9 1996 provides the FCC discretio
32. 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 NOTE Throughout this document references made to GTX 330 shall equally apply to the GTX 330D except where specifically noted GTX 330 Installation Manual Page 1 190 00207 02 Revision K This page intentionally left blank Page GTX 330 Installation Manual Revision K 190 00207 02 TABLE OF CONTENTS GENERAL DESCRIPTION a 1 2 1 35 TES System L4 Muma Suppression 5 nterface SUA LO 1 8 Aircraft Station Licensing EI Wy sta anna DINGS TAT DAINTREE 251 AMOI 22 stallar Mat 23 Installation Considerations
33. DC aircraft lighting bus ighti Backlight level tracks a 28 Volt DC aircraft lighting bus Backlight level tracks a 5 Volt DC aircraft lighting bus If a lighting bus any selection other than PHOTO 1s selected and the lighting bus control is turned to its minimum daytime setting the display brightness tracks the GTX 330 photocell SLOPE Auto Only Sets the sensitivity of the display brightness to changes in the input level The higher the number the brighter the display for a given increase the input level This field has a range of 0 zero to 99 with the default set to 50 OFFSET Auto Only 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 the panel 5 2 6 Key Lighting Page The key lighting mode 15 always the same as the display backlight mode so the mode must be changed on the Display KEY LIGHTING Page Backlight configuration page If the lighting mode is AUTO then the key lighting parameters can be edited on this page KEY Key Lighting SELECTION DESCRIPTION AUTO Automatic Key lighting is automatically controlled based on the parameters entered on this configuration page MAN Manual Key lighting is controlled manually by the pilot on the GTX 330 DISPLAY page GTX 330 Installation Manual Page 5 9 190 00207 02 Revision K
34. Flight IDs STU vg 1 Press the CRSR key once to highlight the address field 2 Enter the aircraft address using the number keys Pressing a key repeatedly scrolls through the digit alpha characters for that key GTX 330 Installation Manual Page 5 17 190 00207 02 Revision K 3 Press the key to select the next alohanumeric entry field Enter the next character as stated in the previous step then move onto the next one repeating the process until the complete number is entered 4 When finished press the CRSR key to accept the number entry 5 Using the FUNC and or START STOP keys toggle through the pages to get off of then back onto the aircraft address page Verify that the address is correct Turn the unit off Power the unit back on the normal mode If the FLIGHT ID PWR UP ENTRY page was selected verify that the unit requests the correct page during system turn on An important factor to consider while configuring the GTX 330 15 this POWER UP ENTRY requires that a variable Mode S FLIGHT ID is entered each time the unit is powered on The selections SAME AS TAIL and CONFIG ENTRY are fixed Mode 5 PWR UP CONFIG ENTRY Page addresses The two fixed selections do not require any transponder interaction from the flight crew whereas POWER UP ENTRY always does PWR UP SAME AS TAIL Page Used for air to air communication with TCAS MODE S A C Type Page SELECTION DESCRIPTI
35. GTX 330 011 00583 00 SMP Install Rack GTX 330 115 00294 00 Sub Assy Backplate GTX 330 011 00582 00 For use with 330 For use with GTX 330D two required for diversity Note A transponder antenna approved to TSO C66 C74 that has been installed to meet the requirements of this manual may be approved for use with the GTX 330 GTX 330 Installation Manual Page 2 1 190 00207 02 Revision K 2 2 3 Additional Equipment Required e Cables The installer will supply all system cables including circuit breakers Cable requirements and fabrication are detailed in Section 3 of this manual e Hardware 6 32 x 100 Flat Head SS Screw MS24693 AN507R or other approved fastener 6 and 6 32 Self Locking Nut MS21042 or other approved fastener 6 Hardware required to mount the installation rack 1s not provided e Encoding Altitude Digitizer Use encoding altimeter manufacturer s instructions install according to FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A The Garmin GAE 43 Garmin P N 013 00066 00 can provide altitude data in either serial or parallel gray code format 2 3 Installation Considerations The GTX 330 can interface with equipment including altimeters Air Data Computer ADC and a temperature probe RS 232 and ARINC 429 provide a serial communication path between interfacing equipment Fabrication of a wiring harness is required Optional available discrete line inter
36. Manual Revision K 190 00207 02 4 2 Power and Lighting Function Power Input requirements and Lighting Bus input are listed the following tables The power input pins accept 11 33 Vdc AIRCRAFT POWER 2 is for connecting to an alternate power source such as on aircraft with two electrical buses Switched Power Out is a power source available for devices such as a remote digital altitude encoder Refer to Figures and C 2 for power and lighting interconnections 4 2 1 Aircraft Power Table 4 2 Aircraft Power Pin Assignments __ PinNumber 10 AIRCRAFT POWER 1 AIRCRAFT POWER 1 AIRCRAFT POWER 2 AIRCRAFTPOWER2 60 70 J gt 4 4 2 2 Lighting Bus The GTX 330 unit can be configured to track 28 Vdc 14 Vdc 5 Vdc or 5 Vac lighting bus using these inputs The GTX 330 can also automatically adjust for ambient lighting conditions based on the photocell Refer to Sections 5 2 5 and 5 2 6 for lighting configuration Table 4 3 Aircraft Lighting Pin Assignments ________ PinNumber I O 14 5 LIGHTING BUS 28 LIGHTING BUS 4 3 Temperature Inputs Table 4 4 Temperature Probe Pin Assignments _________ CURRENT Temperature input 15 used for Outside Air Temperature OA
37. page DISPLAY AUDIO Jumps to Audio Volume page CONFIG Jumps to ARINC 429 INPUT 1 page ACFT CONFIG Jumps to Operation Configuration 1 page Page 5 6 330 Installation Manual Revision K 190 00207 02 VOICE and VOLUME AUDIO MODE First Page Select desired VOICE The choice of OFF is not available for traffic TIS audio Make sure the volume level is sufficient for AUDIO MODE Second Page the aircraft environment involved MESSAGE Message 15 used as a test function only Message 0 is a continuous tone Message 1 15 a short tone and 2 through 5 are voice messages Choose each selection to listen to the message SELECTION DESCRIPTION VOICE MALE FEMALE Sets the voice to male or female Default is male voice VOLUME Volume is adjusted from 0 default to maximum with the 8 or 9 key MESSAGE 0 9 Selected audio tones and messages 0 Toggles a continuous tone on and off 1 Attention Tone precedes voice messages to attract the pilot s attention 2 Leaving Altitude when altitude monitor is active and the altitude deviation is exceeded 3 Traffic when a TIS traffic alert is received similar to a Traffic Advisory in TCAS terms 4 Timer Expired when the countdown timer expires 5 Traffic Not Available when TIS service is not available or out of range of an operating TIS Mode S site 6 through 9 are not used at this time ALTITUDE MONITOR Off tone or message COUNT D
38. the ADF sense antenna or any other communication antenna and six feet from the DME antenna D To prevent RF interference the antenna must be physically mounted a minimum distance of three feet from the GTX 330 NOTE If the antenna is being installed on a composite aircraft ground planes must be considered Conductive wire mesh radials or thin aluminum sheets embedded in the composite material provide the proper ground plane allowing the antenna pattern gain to be maximized for optimum transponder performance 2 4 2 Antenna Installation Install the antenna according to the antenna manufacturer s instructions and FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A GTX 330 Installation Manual Page 2 3 190 00207 02 Revision K 2 5 Cabling and Wiring Use MIL W 22759 16 or other approved wire AWG 24 or larger wire for all connections The standard pin contacts supplied in the connector kit are compatible with up to AWG 22 wire In cases where some installations have more than one unit sharing a common circuit breaker sizing and wire gauge is based on aircraft circuit breaker layout length of wiring current draw of units and internal unit protection characteristics Do not attempt to combine more than one unit on the same circuit breaker unless it 15 specified on aircraft manufacturer approved drawings In some cases a larger gauge wire such as AWG 18 or 16 may be needed for power connections If using 16 or 18 barre
39. to ground based radar on a frequency of 1090 MHz The GTX 330 is equipped with IDENT capability that activates the Special Position Identification SPI pulse for 18 seconds The GTX 330 replies to ATCRBS Mode A Mode C and Mode S All Call interrogation Mode A replies consist of any one of 4 096 codes which differ in the position and number of pulses transmitted Mode C replies include framing pulses and encoded altitude Mode S interrogations are selective The Mode S transponders can respond to a single directed interrogation from the ground station or another aircraft The GTX 330 with software version 4 01 meets Mode S Enhanced Surveillance EHS requirements Mode S Enhanced Surveillance is used predominantly in European airspace It provides information consisting of additional aircraft parameters see JAA NPA 20 12a to ground radar systems Fixed wing aircraft that can provide the list of eight Downlink Aircraft Parameters DAPs listed in BDS Registers 4 0 5 0 and 6 0 See Section 1 5 Interface Summary are considered to be Mode S EHS capable If these conditions cannot be met the aircraft will not be considered EHS capable Compliance with Enhanced Surveillance may require additional interface between aircraft systems and the GTX 330 GTX 330 Installation Manual Page 1 1 190 00207 02 Revision K 330 15 Level 2 transponder providing downlink of aircraft information Ground stations interrogate Mode 5 Trans
40. 0 64000 966 02 82200 0 OT 00 20000 921 10 69000 068 401 OL 20 10200 061 066 XLO 318 21144 7939 14 2 51013310 XVOD OL 04004402 9417201 AlddV 9 TISHSNOVE 83 0 JLVIALAN d NS CS YOLIINNOD OLNI 01143541 390339 TIAHSYIVA SIYIM SSINUVH 0334 Cy 3019340 00 8900 110 40 1484 ASSY 314143248 0066 X19 10 8900 110 40 1444 ASSV 066 X19 00 8900 110 30 OD 10 69000 066 VNNALNV WOLLOG OL 00 76200 411 53014 2 80 16209 112 59 NOILVTIVLSNIGNV AT9INISSV c0 L0C00 061 UOSAN 066 XLO 9 99 4 9974 SUOISUDWIG NOIND 066 XLH 2 91614 8179 89 867 229 161 SZ 39 9 3 ATINA LON AYN SYOLOINNOD zs 6217 SI LINN 13 4 LAVYOMIV 3 40 32 4805 JHL 4 1 GNIH3G SI 2 8 ONILNNON 40 1 4 AHL 4 2 Gane TINGE 20 HONI SNOISNINIG 71 907 09 1311 15 NOVY 100102 OIQVA NOILdO 0 091 0679 12111 056 8 29 LEZ e 1761 SZ po 4 717 so 13NVd 13 0 30
41. 00 Series unit through the ARINC 429 wiring All configured input data that is concentrated through the GTX 330 via ARINC 429 lines is received in the second 400 500 Series unit via ARINC 429 CHANNEL 2 while the GTX 330 1s active No data 1s received over ARINC 429 CHANNEL 2 while the GTX 330 is in remote standby Remote standby is usually used as part of a dual transponder installation 4 6 4 ARINC 429 Input Output The ARINC 429 Output 2 port J3301 pins 30 and 28 is at a high impedance when in remote standby therefore not active When two GTX 330s are installed the two ARINC 429 Output 2 ports may be hard wired together since the EXTERNAL STANDBY SELECT input 15 active for only one of the two GTX 330s at any given time The GTX 330 ARINC 429 Output 1 port is active when 3301 13 is grounded EXTERNAL STANDBY SELECT remote STANDBY In installations having a transponder combination of GTX 330 GTX 327 or GTX 330 other transponder the GARMIN and GARMIN W TIS formats from the ARINC 429 Output port J3301 pins 34 and 37 are available if the GTX 330 has SW 3 03 and above Table 4 9 ARINC 429 Pin Assignments 4 10 330 Installation Manual Revision K 190 00207 02 ARINC 429 outputs conform to ARINC 429 electrical specifications when loaded with up to 5 standard ARINC 429 receivers Refer to Figures C 1 C 3 C 5 C 7 and C 8 for the ARINC 429 se
42. 1 4 WO4 01311 15 OVE 100109 Olava C NOIldO 2 27 8971 30 1 4 QITIVLSNI 100102 80 15 NOILdO 0 091 0679 SONIMVYC NOILVTIVLSNI AT9INISSV UOISIADY 7 9 9864 170 1 SHUN 6996 0089 00 01 066 XLD L 941614 404 GASN SI LNdNI GAGYVOVId GINOHS 108 0350 38 OSIY AYN 5 LYTIV 2143 81 19313534 ANY 123135 OL 10114 MOTIV LON 5304 NMOHS ONIMIM OL 5 2 011235 335 2 0601 LV 57 SI 5501 318 2 WNWIXVN SSINYVH Y OLNI Q39V1 318 0 WNN3LNV GINOHS 3572 NI 553 TVOLLOVAd SV SV 5 318 JHL 31008476 5 193135 0311041 10114 40 5 404 4 93434 SONINYVM 9 4 41 SNJLSAS 3 10 19 11 631001 7 10 4 193135 ALAN 8 011235 33 08 SNJ 9 29 ALIMIGILVANOONI 513004 TIY
43. 2 8 4 03 Added Figure 4 9 330 327 w Dual Display 21954 102205 Added TIS TCAD combo and SW connector 22929 _ 032604 Revised to reflect Software 3 05 2528 100504 Revised to reflect Software 306 27691 1 0 08 Revised to reflect Software 401 29308 032105 Enhanced Surveillance Description 30440 _ 5305 Removed AFMS from AppendkA 31255 DOCUMENT PAGINATION Section Page Range 330 Installation Manual Revision K 190 00207 02 This manual reflects the operation of software version 4 01 Some differences in operation may be observed when comparing the information this manual to earlier or later software versions INFORMATION SUBJECT TO EXPORT CONTROL LAWS This document may contain information which is subject to the Export Administration Regulations EAR issued by the United States Department of Commerce 15 CFR Chapter VII Subchapter C and which may not be exported released or disclosed to foreign nationals inside or outside of the United States without first obtaining an export license A violation of the EAR may be subject to a penalty of up to 10 years imprisonment and a fine of up to 1 000 000 under Section 2410 of the Export Administration Act of 1979 Include this notice with any reproduced portion of this document This product its packaging and its components contain chemicals known to the State of
44. 4 OL 535104 NOISSAYddNS 09 3 11504 514300 SONIS 16 10664 553 4405 TVNYJLXI 19Vd NOILVANDIANOO 135 21901 ONIONVT NOdN NI 530 14 1 9115 4015 LYVLS SMOTIV 21 10 4 5 1 005 72 5 SSJINN 4398 1 YO SAYIM TIV 5310 01 LNO OIGNV IH LNO OlGNV 3 NALSAS 5 QANIM SMVL 47 NYNLIM LIV Ze lt A NI LIV 1 lt 310 335 aan 3LON 335 Ove 124145 1437 05 MOLVIONNNNV lt 61 1430Y 3 1 1431 30111111 ka LOOGd HUN 10074 Salas 006 007 194145 194 09 SIL 9 485 2 445 cl 103135 1 3 v J3LON 4343S gt l 124145 AGONVIS 1 1 5 lt gt 48 1 01553 4405 Is HOLIMS 5 OFS ALO 5 XIGNAddV DRAWINGS APPENDIX 404 5 SLINN 30 SLNONId
45. 82 2 2 2 49 0 021055 vogi 08 1995 5462 Buly 49194114 38 0 1 344 0 LNO 38044 1 344 00 2 INO 656 54 2 62 54 JONLILIV 22 300111 LO SONLILIV ca LG SCNLILIV Lv Figure 6 GTX 330 Interconnect Wiring Diagram Altitude Temperature Connections Page C 11 Page C 12 blank GTX 330 Installation Manual 190 00207 02 Revision K 1015 71 0 92884 61 0 9884 10 19945 5 jeng 12 2 9 941614 LIV 310 335 Ore NINSV9 3 549 549 549 INO 549 5911 5 006 007 01 100 2602 54 100 222 59 3 ALVIINNNNV 549 549 100 549 INO 549 n
46. IPTION F DEFAULT The altitude code input 15 not from an RS 232 source PS RS 232 ground speed from a GPS device ICARUS ALT RS 232 serial altitude from an Icarus Instruments 3000 ICRS ALT 25 t Reports Icarus Instruments 3000 altitude in 25 foot increments ADC NO ALT RS 232 serial air data information from Shadin ADC 200 200 2000 ADC W ALT RS 232 serial air data information from Shadin ADC 200 200 2000 plus altitude data SHADIN ALT Computers and Fuel Air Data Computers FADC W ALT RS 232 serial air data from Shadin 9628 family of Air Data Computers and Fuel Air Data Computers plus altitude data REMOTE RS 232 serial input remote data Reserved for future use RS 232 OUTPUT Altitude Source SELECTION DESCRIPTION DEFAULT for channel 2 No unit is connected to output of this channel ICARUS ALT DEFAULT for channel 1 RS 232 serial altitude from an Icarus Instruments 3000 REMOTE RS 232 serial output remote data Reserved for future use REMOTE TIS RS 232 serial output remote data with TIS 5 2 10 Operation Configuration Pages VS RATE Vertical Speed Rate First CONFIGURATION Page This field is the typical vertical speed for climb descent of the aircraft The settable number determines the rate of climb the GTX 330 assumes as liftoff for starting the flight timer and operational functions The range is 100 feet per minute to 9999 feet per minute and 15 set to 500 fpm at the factory
47. If EXTERNAL STANDBY 15 active during power up the word FAIL appears on the screen after 30 seconds SQUAT This field displays the state of the SQUAT SWITCH input The box is filled when the SQUAT SWITCH input is active the aircraft 15 on the ground as configured the SETUP 2 page 5 2 16 Analog Input Page The Analog to Digital Converter counts are shown on the display providing troubleshooting data ANALOG INPUT Page 14 5V LTG This field displays the input level of the 14 5 V lighting bus PHOTO This field displays the input level of the photocell LCD TEMP This field displays the input level of the LCD temperature sensor 28 This field displays the input level of the 28 lighting bus 330 Installation Manual Page 5 19 190 00207 02 Revision K This field displays the input level from the outside air temperature sensor UNIT TEMP This field displays the input level from the unit temperature sensor RS 232 INPUT Page Depending on the selected inputs on Channel 1 and Channel 2 from the RS 232 Input page ref para 5 2 9 this page displays the information received the channel If GPS is selected as an input ground speed be viewed GSPD latitude LAT longitude LON and track If ICARUS or SHADIN ALT 15 selected as an input pressure altitude PALT be viewed If FADC or ADC 15 selected as an input true or static air temperature SAT outside or tota
48. LIV LO va JONLILIV 19 JONLILIV 193135 5 110 550 54 NI 255 54 IYN IS Ogg 19 UILWUADS XIGNAddV
49. LL v 2 310 335 51 11824 Aa Naor 18 189 00 70006 0087 1092 0092 419 arg 098 72 100 292 54 2 2 QO 1964 1684 76 NIM 868 5649 Bury 627 549 Sl Lv LY LNO 549 91 9v 310 335 1014 10054 1 00 OND 1X SSL 549 006 selves 00 549 UIWADS 1 549 82 L 549 st 0 10054 106864 Hun 91125 006 007 NI 262 54 NI 8 2100 2100 Ogg 9 Figure 5 GTX 330 Interconnect Wiring Diagram Serial Devices Connections GTX 330 Installation Manual 190 00207 02 Page C 9 Page C 10 blank Revision K DRAWINGS APPENDIX 2642 5484 ANY 43 03 4 540 FHL 54 066 X19 AHL 03103 0 SI 41 lt 10 343414 404 NMOHS
50. NI 510 371543 0 0350 38 0100 5 81 1334 OL 40 5530 3 HLONIT 0 31 JHL JYSHM 73841 22 38 QINOHS 5 310 5 5531 39 1 534 15310 LIV LIV 01 JLON 335 Ove VN9 3 549 549 TH Hun sell9S 006 007 3 549 549 g LINO 549 100 549 L 5 5 006 007 NINYV9 c0 L0C00 061 10918151 066 XLO 1 2 VNNILNV 401 401 SALON dds AINO 0066 X19 2 YNNJLNV noloa 6 310 335 20554 ABET ESE 91 100 18 I st 100 rd 33 W3LSAS 5 ONIM YO SMYL 044 7 123135 06 NOWWOD 9 gt 8 12 HJLINLLIV
51. NOdSNVAL 006 007 0 45 1 01 110 255 55 5 1 O IH 100 AVS 5 gt vz 2 NI 262 55 gt 123135 AGGNVLS 3 JLVIONNNNV 4 4 gt 123135 123 02 SIL 629 549 e aS 100 Y 629 549 sr Kp Le Y 1NO 62 T LNO 627 549 Ly gt 629 100 627 549 H gt 29 Y 10084 Hun 00vd 10664 006 007 l OSS 19 LOANNOOUSALNI XIGNAddV UOSAN 81 0 92884 LI 9884 SVOL QVOL SIL Yessy 066 19 8 2 4 035 SI 1 dl 38 GINOHS 13 108 0350 38 OSIY AYN LNANI 5 OIGNV 19379 144 1 34 10313530 123135 OL 10114 MOTIV LON 5400 5 NOILVANDIANOO TANVd OIGNV 9 HOLIMS 193135 ALNW OIGNVY 311041 1014 40 NOlldld9S10 404 25577 43334 ONILLAdLNO SWALSAS 843 10 OIQNV Ogg X19 TIV SILAN 47 1059 LNdNI 123135
52. ON AC TYPE UNKNOWN lt 15 5K Lb gt 15 5K Lb or ROTOR MAX AIRSPEED UNKNOWN lt 75 kt lt 150 kt lt 300 kt or gt 300 kt AIRCRAFT TYPE Sets the AIRCRAFT TYPE Message to ROTOR to a weight of less than 15 500 pounds more than or equal to 15 500 pounds or unknown weight Defaults to less than 15 500 pounds MAXIMUM AIRSPEED Sets the AIRCRAFT AIRSPEED Message to a speed of less than or equal to 75 knots between 75 knots and 150 knots between 150 knots and 300 knots more than 300 knots or unknown airspeed Defaults to less than or equal to 150 knots Enter the aircraft s maximum cruising true airspeed capability Page 5 18 GTX 330 Installation Manual Revision K 190 00207 02 5 2 14 Gray Code Input GRAY CODE GRAY CODE INPUT Page This field shows the status 1 ground 0 open of each of the ten gray code altitude inputs This information may aid installation troubleshooting This page is not used in systems that contain serial altitude input DECODED ALTITUDE This field displays the gray code altitude input in feet Verify that it is the correct altitude 5 2 15 External Switch State Page IDENT EXTERNAL SWITCH Page This field displays the state of the EXTERNAL IDENT discrete input The box 15 filled when EXTERNAL IDENT is grounded STANDBY This field displays the state of the EXTERNAL STANDBY discrete input The box is filled when EXTERNAL STANDBY is grounded
53. ORT 2 15 inactive When TIS CONNECT SELECT is inactive 15 displayed on the 400 500 Series units the GTX 330 logs onto TIS service when a momentary ground is applied to P3301 46 When TIS 15 active momentary ground logs off of TIS service Refer to Figures C 1 C 3 C 4 C 7 and C 8 for TIS CONNECT SELECT connections and to Sections 5 2 2 5 2 3 5 2 8 and 5 2 9 for TIS configuration An AUDIO MUTE SELECT mute switch may be used to control TIS audio alerts TIS Traffic Mute must be clearly marked with MUTE ON MUTE OFF or TIS Audio ON Audio OFF labels The muting feature may be enabled through a Multi Function display In order to prevent inadvertent muting the status of muting must default to Mute off upon each power cycle Refer to Figures C 1 C 4 and C 8 for AUDIO MUTE SELECT connections and to Sections 5 2 2 and 5 2 3 for AUDIO configuration GTX 330 Installation Manual Page 4 7 190 00207 02 Revision K 4 6 Serial Data Electrical Characteristics The GTX 330 can be configured to include GPS Airdata AHRS EFIS Airdata and ADLP ARINC 429 inputs functioning as an ARINC 429 data concentrator Since the Garmin 400 500 Series products have only two ARINC 429 input ports the GTX 330 manages support for several equipment interfaces The GTX 330 has four ARINC 429 input ports making it capable of taking altitude air data heading EFIS selected course and possible future features and then concentrating it o
54. OWN TIMER Off tone or message PAGE CHANGE Enables Disables Altitude Monitor sub page when altitude deviation is exceeded 5 2 3 Traffic Information Page TRAFFIC INFORMATION Page TRAFFIC MESSAGES Sets the Traffic Messages to either Tone or Message Traffic Information Service TIS provides notification of close proximity traffic GTX 330 Installation Manual Page 5 7 190 00207 02 Revision K 5 2 4 DISPLAY MODE DISPLAY MODE Page SELECTION DESCRIPTION AUTO Automatic DEFAULT Display automatically changes between Positive mode during the day and Negative mode at night depending on ambient light level received by the photocell NGTYV Negative Display always has light characters on a black background regardless of ambient lighting PSTV Positive Display always has black characters on a light background regardless of ambient lighting LEVEL Sets the ambient light level for AUTO mode to change between negative and positive display The higher the number the brighter the ambient light level to change over This field has a range of 0 zero to 99 with the default set to 75 5 2 5 Display Backlight Page DISPLAY BACKLIGHT Page BKLT Backlight SELECTION DESCRIPTION AUTO Automatic DEFAULT Display backlighting is automatically controlled based on the parameters entered on this configuration page When AUTO is selected the DISPLAY page does not appe
55. T display and Density Altitude computations The type of temperature probe required is a current sensor type such as an EDMO P N 655 PROBE or Davtron P N C307PS Connect the red wire to pin 41 and the black wire to pin 44 The GTX 330 1 not configurable for different types of temperature sensors The temperature input specification is 1 microamp per degree Kelvin 1 wA K Refer to Figure 6 for the temperature probe interconnect and to Section 5 2 11 for probe configuration GTX 330 Installation Manual Page 4 3 190 00207 02 Revision K 4 4 Altitude Functions Parallel gray code altitude inputs are considered active if either the voltage to ground is lt 1 9 V or the resistance to ground 15 lt 375 These inputs are considered inactive if the voltage to ground 15 11 33 Vdc Refer to Figures C 6 and C 9 for parallel gray code and serial data altitude interconnections Carefully check encoder input lines for correct connection after wiring is complete The GTX 330 contains internal altitude code line isolation diodes to prevent the unit from pulling the encoder lines to ground when the transponder 15 turned off If two separate altitude encoders are connected to the GTX 330 one providing parallel gray code and the other serial data the unit selects only one for use at a time with serial data input receiving the highest priority For altimeters that can be connected in both serial data and parallel gray code format such as th
56. Used in Configuration mode 8 Reduces Contrast Display Brightness when the respective fields are displayed and enters the number eight into the Count Down timer Used in Configuration mode 9 Increases Contrast and Display Brightness when the respective fields displayed and enters the number nine into the Count Down timer Used in Configuration mode 5 1 2 Code Selection Code selection is entered with eight keys 0 7 providing 4 096 active identification codes Pushing one of these keys begins the code selection sequence The new code 15 not activated until the fourth digit 15 entered Pressing the CLR key moves the cursor back to the previous digit Pressing the CLR key when the cursor is on the first digit of the code or pressing the CRSR key during code entry removes the cursor and cancels data entry restoring the previous code You may press the CLR key up to five seconds after code entry 15 complete to return the cursor to the fourth digit The numbers 8 and 9 are used for code entry only for entering a Count Down time contrast and display brightness and data selection in the Configuration mode NOTE The selected identification code should be entered carefully either one assigned by air traffic control for IFR flight or an applicable VFR transponder code e Important Codes 1200 VFR code for any altitude in the US Refer to ICAO standards elsewhere 2000 VFR code commonly used in E
57. ach 15 sufficient Mode 5 EHS compliance Note 3 Supplying either True Airspeed or True Track Angle Rate is sufficient Mode S EHS compliance GTX 330 Installation Manual Page 5 23 190 00207 02 Revision K This page intentionally left blank Page 5 24 GTX 330 Installation Manual Revision K 190 00207 02 APPENDIX DOCUMENTS 1 51 United States of America Department of Transportation Federal Administration Supplemental Type Certificate Nam 5 01 125 certificate issued to Garmin International 1200 151 Street Olathe KS 66062 that the change in the type design for the following product with the limitations and conditions therefor as specified hereon meets the airworthiness requirements of Part 3 of the Civil Air Regulations Number 5 Make Piper 49 60 Deseroption of Design Change Installation of Garmin GTX 330 Mode 5 Transponder with Traffic Information System Capability Data Required 1 FAA Approved Airplane Flight Manual Supplement AFMS for Piper PA32 with Garmin GNS 430 VHF Communication Transceiver VOR ILS Receiver GPS Receiver 2 FAA Approved Airplane Flight Manual Supplement AFMS for Piper PA32 with Garmin GNS 530 VHF Communication Transceiver VOR ILS Receiver GPS Receiver dated 11 21 2002 or later FAA Approved Revisions to 1 or 2 imita
58. ar to the pilot MAN Manual Display backlighting is controlled manually by the pilot on the GTX 330 DISPLAY page No backlight parameters can be entered when the manual mode 15 selected LVL Level Shows the current level of display backlighting based on the lighting input source lighting bus voltage or the ambient light if the source is PHOTO and the settings on this configuration page This field has a range of 0 zero to 999 The level is set by pressing the 8 and 9 keys when MAN mode 15 selected When in AUTO mode the field is for display only RSP TIME Response Time Sets the speed with which the brightness responds to ambient light changes only for AUTO backlight mode The higher the number the slower the display responds This field has a range of 0 to 7 with the default set to 4 Page 5 8 GTX 330 Installation Manual Revision K 190 00207 02 Minimum Auto Only Sets the minimum brightness of the display The higher the number the brighter the minimum brightness Display minimum brightness has a range of 0 zero to 99 with the default set to 8 It is prudent to verify that display lighting characteristics match those of other equipment in the panel under night lighting conditions BKLT SRCE Backlight Source SELECTION DESCRIPTION PHOTO Photocell DEFAULT Backlight level is determined by the ambient light level as measured by the photocell on the GTX 330 Backlight level tracks a 14 Volt
59. are update connections P3301 XPDR CIRCUIT BREAKER 22 N AIRCRAFT POWER 1 21 11 33 VDC AIRCRAFT POWER 22 AWG power 25 TEST SELECT SWITCH REQUIRED FOR SW 3 05 AND BELOW TEST MODE SELECT 18 1 1 POWER GROUND 27 5 5 POWER GROUND 43 __ RS 232 IN 1 22 3 3 RS 232 OUT 1 25 2 2 9 D SUB CONNECTOR TO PCS PORT Figure 4 3 GTX 330 Software Update Connections GTX 330 Installation Manual Page 4 9 190 00207 02 Revision K 4 6 3 Aircraft with Both 5 Installed Refer to Figure C 8 for wiring connections If redundant traffic systems are desired the aircraft such as TIS and TCAD TCAS both systems cannot be connected to the same 400 500 Series unit to display traffic simultaneously In a multiple traffic system multiple 400 500 Series unit installation connect ARINC 429 CHANNEL 1 from the GTX 330 to only one of the 400 500 Series units and ARINC 429 CHANNEL 2 to the other 400 500 Series unit Connect the TIS CONNECT SELECT line from the GTX 330 to the 400 500 Series unit receiving TIS data The TCAD TCAS system may now be connected to the second 400 500 Series unit Refer to Section 5 for configuration Configure ARINC 429 output CHANNEL 1 for GARMIN W TIS and ARINC 429 output CHANNEL 2 for GARMIN TIS is then enabled over CHANNEL 1 when the GTX 330 is connected to a Garmin 400 5
60. ced by Tel 800 327 9473 M17 type 414 421 5300 numbers Fax 414 421 5301 www ecsdirect com Page 2 4 GTX 330 Installation Manual Revision K 190 00207 02 2 5 1 Cable Routing Considerations When routing cables observe the following precautions 2 6 All cable routing should be kept as short and as direct as practical Avoid sharp bends Avoid routing cables near power sources e g 400 Hz generators trim motors etc or near power for fluorescent lighting Avoid routing antenna cables near ADF antenna cable allow at least a 12 inch separation Installation Approval Considerations for Pressurized Aircraft Antenna and cable installations on pressurized cabin aircraft require FAA approved installation design and engineering substantiation data whenever such 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 15 recommended that the installer proceed according to any of the following listed alternatives Obtain approved antenna installation design data from the aircraft manufacturer 2 Obtain an FAA approved Supplemental Type Certificate STC pertaining to and valid for the subject antenna installation 3 Contact the FAA Aircraft Certification Office in the appropriate Region and req
61. de source for the particular aircraft Altitude reporting equipment order of precedence 1 ARINC 429 Air Data Computer label 203 if configured W ALT 25 2 ARINC 429 EFIS label 203 if configured W ALT 25 3 RS 232 data from GNS 480 CNX80 if so connected 4 RS 232 Fuel Air Data Computer if configured W ALT 25 5 Shadin Altitude Serializer Encoder if configured for 25 6 Icarus Altitude Serializer Encoder if configured for 25 7 Parallel wire Gray Code input 100 8 Shadin Altitude Serializer Encoder if configured for 100 9 Icarus Altitude Serializer Encoder if configured for 100 It is the installing agency s responsibility to determine that the installed encoder 15 compatible with the selected altitude reporting criteria either 100 or 25 Refer to Section 5 2 8 and 5 2 9 for the altitude data reporting configuration For additional information refer to GNS 480 CNX80 Installation Manual 560 0982 01 for the altitude data reporting configuration when connecting a GTX 330 to GNS 480 CNX80 4 5 Discrete Functions 4 5 1 Discrete Outputs External suppression should be connected if a DME 15 installed the aircraft avionics system The GTX 330 suppression I O pulses may not be compatible with all models of DME Known incompatible units include the Bendix King KN 62 KN 64 and KNS 80 These models have an output only suppression port and can be damaged by the GTX 330 mutual sup
62. e Garmin GAE 43 Garmin P N 013 00066 00 select one or the other but not both wiring connections Among the surveillance items the Mode S transponder will transmit to the ground stations and other aircraft are altitude reporting in 25 foot increments with the proper encoder In order to report altitude in 25 foot increments the GTX 330 must receive altitude from suitable altitude reporting devices through serial input connections Altitude input to the GTX 330 received from parallel wire gray code encoders is supplied to the unit in 100 foot increments and thus reported in 100 foot increments 4 4 1 Altimeter Inputs Table 4 5 Encoded Altitude Pin Assignments ______ Number 10 4 tin ALTITUDEAD 2 ALTITUDEA 4 ALTITUDEAS 5 ALTITUDEBI 7 h ATITUDEB2 9 8 4 6 ALTITUDECOMMON 50 RS 232 IN 2 4 4 2 Altimeter Calibration and Checkout Refer to Section 5 2 14 for the gray code altitude checkout Page 4 4 330 Installation Manual Revision K 190 00207 02 4 4 3 Altimeter Interconnect Dual GTX 330 Installation A dual GTX 330 installation can accept either parallel wire gray code altimeter input or RS 232 serial data input as shown in Figure 4 2 If transponder number 2 is a Garmin GTX 327 connect the RS 232 output from the altitude encoder to 3271 pin 19 refer to GTX 327 Transponder Installation Ma
63. eed ARINC 429 data SELECTION DESCRIPTION CHANNEL 1 DATA DATA SOURCE OFF ADLP GARMIN or GARMIN W TIS DEFAULTS to OFF ARINC 429 input channel 4 sets the ARINC 429 output channel to the same selection CHANNEL 2 DATA DATA SOURCE OFF GARMIN or GARMIN W TIS DEFAULTS to GARMIN W TIS See Figure C 5 Note 2 for description of Garmin format Do not select GARMIN W TIS if the aircraft contains another traffic detection system In aircraft having multiple traffic systems and multiple 400 500 Series units configure ARINC 429 output CHANNEL 1 for GARMIN W TIS and ARINC 429 output CHANNEL 2 for GARMIN TIS 15 then enabled over CHANNEL 1 The Garmin format is a data concentration function The following data is sent out at specified intervals using high speed ARINC 429 100 kHz The transmit data labels and their rates are as follows Equipment Identifier Page 5 12 GTX 330 Installation Manual Revision K 190 00207 02 The following data are sent out in packets approximately every 0 5 seconds at high speed 100 kHz in the specified sequence 330 Installation Manual Page 5 13 190 00207 02 Revision K 5 2 9 5 232 Input Output Page RS 232 INPUT Altitude Source GPS Data RS 232 INPUT OUTPUT Page This is the electrical source for the GTX 330 altitude and GPS data input Refer to Section 4 4 4 for altimeter data selection priority SELECTION DESCR
64. efore starting aircraft engine s GTX 330 Installation Manual Page 5 1 190 00207 02 Revision K 5 1 1 Function Selector Switches The function selection switches are OFF STBY ON ALT Powers otf 330 Pressing the 5 ON ALT key powers the transponder displaying the last active identification code Selects the standby mode When in standby mode the transponder does not reply to any interrogations Pressing and holding the STBY key selects ground GND mode if Automated Airborne Determination is not otherwise selected from another source When GND 1s annunciated the transponder does not respond to ATCRBS interrogations but replies to All Call interrogations Selects Mode A and Mode S In this mode the transponder replies to Mode A Mode and Mode 5 interrogations as indicated by the Reply Symbol but the replies do not include altitude information Selects Mode A Mode C and Mode S In ALT mode the transponder replies to identification altitude and Mode S interrogations as indicated by the Reply Symbol Replies to altitude interrogations include the standard pressure altitude received from an external altitude source which is not adjusted for barometric pressure The ALT mode may be selected in aircraft not equipped with an optional altitude encoder however the reply signal does not include altitude information Any time the function sw
65. equirements for the GTX 330 Mode 5 and 330D Diversity Mode 5 Transponder Throughout this manual the term 330 applies to both transponders unless otherwise stated 12 Equipment Description CAUTION The operation of cellular telephones or other cellular mobile devices aboard aircraft while airborne is prohibited by FCC rules Due to the potential for interference with onboard systems the operation of cellular communication devices while onboard an aircraft that 1s the ground 15 subject to FAA 14 CFR 91 21 FCC 47 CFR 22 925 prohibits airborne operation of cellular telephones installed in or carried aboard aircraft Cellular telephones must not be operated aboard any aircraft while the aircraft is off the ground When any aircraft leaves the ground all cellular telephones on board that aircraft must be turned off Cellular telephones that are on even in a monitoring state can disrupt GPS performance The Garmin GTX 330 is a panel mounted Non Diversity Mode S Transponder while the GTX 330D is a Diversity Mode S Transponder The GTX 330D employs two antennas one intended to be mounted on the top and the other on the bottom of the aircraft The design meets RTCA DO 181C and EUROCAE ED 73A specifications The GTX 330 transponder is a radio transmitter and receiver that operates on radar frequencies receiving ground radar or TCAS interrogations at 1030 MHz and transmitting a coded response of pulses
66. esponsible 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 assistance in locating a Service Center near you call Garmin Customer Service at one of the numbers shown below Products sold through online auctions are not eligible for rebates or other special offers from Garmin Online auction confirmations are not accepted for warranty verification To obtain warranty service an original or copy
67. faces are described in Section 4 5 2 Discrete Inputs and shown in installation diagrams provided in Appendix C 2 4 Antenna Installation 2 4 1 Location Considerations Antenna mounting should utilize the aircraft manufactures Type Certificated antenna location and style of antenna If a second diversity antenna is installed in the aircraft considerations for its mounting should be made as outlined in Figure 2 1 The antenna installation should be installed in accordance with Advisory Circular AC 43 12 2A Chapter 3 Note that penetration of the pressure vessel on the pressurized aircraft requires additional data not contained this manual See Section 2 5 Page 2 2 GTX 330 Installation Manual Revision K 190 00207 02 Place optional diversity antenna on top of aircraft Place main antenna on bottom of aircraft Figure 2 1 Antenna Installation Considerations The antenna s Garmin P N 010 10160 00 should be mounted away from major protrusions such as engine s propeller s and antenna masts It should also be as far as practical from landing gear doors access doors or other openings that could effect its radiation pattern B The main antenna should be mounted vertically on the bottom of the aircraft The optional second diversity antenna should be mounted vertically on top of the aircraft Horizontal separation must be no more than 7 6 meters 25 feet C Avoid mounting the antenna within three feet of
68. ftware Update 5 When the GTX 330 is installed an aircraft an optional RS 232 serial data connector should be installed in the aircraft for future software upgrades negating the need to remove the transponder from the aircraft panel The connector can be mounted anywhere convenient for access such as under the instrument panel on a remote avionics shelf or in the instrument panel itself Be sure to label the connector for Software Update Do not include the Test Mode Select switch in the aircraft See Figure 4 3 for software update connections If the GTX 330 installation interfaces with GNS 480 80 in the aircraft the GNS 480 CNX80 must be turned off during GTX 330 software upload due to loading of RS 232 port 1 The installation of an optional software upgrade connector 18 highly recommended If the connector is wired the aircraft transponder removal and reinstallation for software upgrade 1s not required CAUTION If the unit is removed from the aircraft and operated always connect J3302 and J3303 for GTX 330D to an antenna or a 50 Q 5 Watt load The GTX 330 transmits Mode S acquisition squitter replies about once per second whether interrogations are received or not Beginning with SW version 3 06 the GTX 330 software can be updated in the Configuration mode as well as in Test mode Updating software in Configuration mode does not require the TEST MODE SELECT switch See Figure 4 3 for softw
69. g connections for errors before inserting the GTX 330 into the rack Incorrect wiring could cause internal component damage Table 3 1 Pin Contact Part Numbers Hi Density 62 pin D Subminiature connector P3301 Power Only Power Only Garmin P N 336 00044 01 336 00044 00 336 00021 00 Table 3 2 Recommended Tools Density 16 18 amp 20 AWG 22 28 _____ Crimping Tool Positioner Insertion Positioner Insertion Note 3 Extraction Tool Extraction Note 2 Tool Military P N M22520 2 01 81969 1 04 22520 2 09 81969 1 04 9502 11 81969 1 04 9502 3 81969 1 04 739 601966 1 91067 1 601966 6 91067 1 8 81969 1 04 81969 1 04 615717 81969 1 04 615725 81969 1 04 330 Installation Manual 3 1 190 00207 02 Revision 1 Non Garmin numbers shown not maintained by Garmin consequently subject to change without notice 2 Extracting the 16 18 and 20 AWG contact requires that the expanded wire barrel be cut off from the contact It may also be necessary to push the pin out from the face of the connector when using an extractor due to the absence of the wire A new contact must be used when reassembling the connector 3 Contact Garmin for crimp instructions for use with 16 AWG contact 3 3 Circuit Breaker Placard Install a Circuit Breaker Placard labeled Transponder or Transponder 1 Transponder 2 as approp
70. ghting for a given increase the input level This field has a range of 0 zero to 99 and is set to 50 at the factory OFFSET Auto Only Adjusts the key 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 Page 5 10 GTX 330 Installation Manual Revision K 190 00207 02 5 2 7 Contrast Configuration MODE 5 CONFIGURATION Page SELECTION DESCRIPTION AUTO Automatic DEFAULT Display contrast 15 automatically compensated for LCD temperature and other factors offset can be entered in the contrast level adjustment described below MAN Manual Display contrast is manually adjusted either here or by the pilot using the GTX 330 CONTRAST page CONTRAST LEVEL ADJUSTMENT This is a slider bar graph control Use the 8 key to move the graph to the left decreasing the numbers and contrast level Use the 9 key to move it to the right increasing the numbers and contrast level In manual contrast mode this is a direct adjustment of the display contrast In automatic contrast mode this adjusts the offset to the automatically compensated contrast with the default set to an offset of 50 5 2 8 ARINC 429 Configuration Pages 429 ARINC 429 INPUT First Page ARINC 429 INPUT Pages configure
71. hiness Other than for regulatory periodic functional checks maintenance of the GTX 330 15 on condition only Refer to the GTX 330 Maintenance Manual Garmin P N 190 00207 05 Periodic maintenance of the GTX 33015 not required 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 GTX 330 unit installation Some of the checklist items do not apply in which case they should be marked N A Not Applicable INSTRUCTIONS FOR CONTINUED AIRWORTHINESS GARMIN GTX 330 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 GTX 330 Applicability
72. is made for unit software upgrade by means of RS 232 data through rear connector pins The installation of an optional connector is highly recommended If the optional connector is placed in the aircraft transponder removal and reinstallation for software upgrade 15 not required The software can be changed while the unit 15 still mounted inside the aircraft CAUTION The GTX 330 lens is coated with a special anti reflective coating that is very sensitive to skin oils waxes and abrasive cleaners CLEANERS CONTAINING AMMONIA WILL HARM THE ANTI REFLECTIVE COATING It is very important to clean the lens using a clean lint free cloth and an eyeglass lens cleaner that is specified as safe for anti reflective coatings 1 3 TIS System Capabilities The GTX 330 also provides uplink information such as Traffic Information Service TIS TIS is a ground based service providing relative location of all ATCRBS Mode A and Mode C transponder equipped aircraft within a specified service volume The TIS ground sensor uses real time track reports to generate traffic notification TIS provides a graphic display of traffic advisory information in the cockpit for non TCAS equipped aircraft Advisory traffic information 15 available to aircraft equipped with a Mode 5 data link such as the Garmin GTX 330 transponder Advisory traffic information may be displayed on a Garmin 400 500 Series unit The GTX 330 unit can also be incorporated in installations with other c
73. itch is in the ON or ALT position the transponder becomes an active part of the Air Traffic Control Radar Beacon System ATCRBS The transponder also responds to interrogations from TCAS equipped aircraft IDENT Pressing the IDENT key activates the Special Position Identification SPI Pulse VER FUNC for 18 seconds identifying the transponder return from others on an air traffic controller s screen During the IDENT period the word IDENT appears in the upper left corner of the display Sets the transponder code to the pre programmed VFR code selected in Configuration mode Set to 1200 at the factory Pressing the VFR key again restores the previous identification code Changes the page shown on the right side of the display Display data includes Pressure Altitude Flight Time Altitude Monitor Count Up and Count Down timers In the Configuration mode steps through the function pages START Starts and stops the Altitude Monitor Count Up Count Down and Flight timers STOP In Configuration mode steps through functions in reverse Page 5 2 Revision K GTX 330 Installation Manual 190 00207 02 CRSR Initiates entry of the starting time for the Count Down timer and cancels transponder code entry Selects changeable fields in Configuration mode CLR Resets the Count Up Count Down and Flight timers Cancels the previous keypress during code selection and Count Down entry
74. l air temperature TAT indicated air speed IAS true air speed TAS density altitude DALT pressure altitude PALT current barometric pressure BARO and vertical speed VSPD can be viewed SELECTION DESCRIPTION GSPD Ground speed knots PALT Pressure altitude in feet If ADC W ALT or FADC W ALT format selected 5 2 18 ARINC 429 Channels Pages 330 receives of following sets of ARINC 429 ARINC 429 CHANNELS 2 data either ARINC 429 receivers 1 2 or 3 The labels chosen when selected in ARINC 429 INPUT Section 5 2 8 The received data may be at either LOW or HIGH speed The ARINC 429 CHANNELS 3 and 4 default is LOW The transmit data labels and their rate are as follows Page 5 20 GTX 330 Installation Manual Revision K 190 00207 02 5 Static Air degrees EFIS DISPLAY SYSTEM EF AD 234 306 307 320 328 330 Installation Manual Page 5 21 190 00207 02 Revision K GPS FMS NAVIGATION SYSTEM GPS __ tabel Pata Selected Altitude feet Ground Speed knots Track Angle If ADC W ALT or EF AD W ALT format selected AUTOMATIC FLIGHT CONTROL SYSTEM AFCS Selected Altitude feet Barometric Setting hPa Barometric Setting Hg 271 AFCS Pitch Discretes Page 5 22 GTX 330 Installation Manual Revision K 190 00207 02
75. l contacts ensure that no two contacts are mounted directly adjacent to each other This minimizes the risk of contacts touching and shorting to adjacent pins or to ground Ensure that routing of the wiring does not come in contact with sources of heat RF or EMI interference Check that there is ample space for the cabling and mating connectors Avoid sharp bends in cabling and routing near aircraft control cables The following table lists examples of the recommended antenna cable vendors and the type of cable to be used for specific lengths of cable Any cable meeting specifications is acceptable for the installation The following table is for reference only and lists some suitable cable types along with the maximum length based on an assumed loss figure of 0 2 dB per connector Any 50 Q double shielded coaxial cable assembly that meets airworthiness requirements and the 1 5 dB maximum loss figure including connectors may be used Max Length Insertion loss ECS Type MIL C 17 Type feet m dB 100ft 6 1 3 1 86 M17 128 RG400 7 7 3 2 32 3 142 9 2 0 2 79m M17 112 RG304 12 6 0 3 81m 311601 M17 127 RG393 15 5 4 4 71 311501 19 9 4 6 03m 311201 30 3 6 9 24m 310801 Supplier Vendor Electronic See currentissue RG types are information Cable Specialists of Qualified obsolete and 5300 W Franklin Products List are shown for Drive 17 Franklin WI 53132 repla
76. n the ARINC 429 OUT 2 port This line 15 then wired to an ARINC 429 input port on the 400 500 Series products TIS data 16 included on the same high speed ARINC 429 bus Airborne Data Link Processor ADLP is reserved for future data link applications ADLP requires an ARINC 429 input and output The ADLP interface allows the Mode S data link transponder to function An ADLP performs functions requiring sending and or receiving data from ground sensors via Mode S interrogations and replies NOTE The GTX 330 is currently FAA approved to display TIS traffic information on Garmin 400 500 Series GNS 480 CNX80 and MX20 products only 4 6 1 RS 232 Input Output Table 4 8 RS 232 Pin Assignments __ Number RS 232 OUT 1 RS 232 1 RS 232 OUT 2 RS 232 IN 2 RS 232 outputs conform to EIA Standard RS 232C with an output voltage swing of at least 5 when driving a standard RS 232 load Refer to Figures 4 3 C 2 C 3 C 5 C 6 C 7 and C 8 for RS 232 serial data interconnect and to Sections 5 2 9 and 5 2 17 for RS 232 serial data configuration When connecting two GTX 333 transponders to a GPS the unit can only receive RS 232 serial data from one unit at a Use DPDT switch for connecting both serial data and External Standby Select Refer to Figure C 9 Sheets 2 and 3 Page 4 8 GTX 330 Installation Manual Revision K 190 00207 02 4 6 2 85 232 Input Output So
77. n to eliminate radio station license requirements for aircraft and ships The GTX 330 installation must comply with current transmitter licensing requirements To find out the specific details on whether a particular installation 15 exempt from licensing 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 GTX 330 owner accepts all responsibility for obtaining the proper licensing before using the transponder CAUTION The UHF transmitter in this equipment is guaranteed to meet Federal Communications Commission acceptance over the specified operating temperature range Modifications to Garmin equipment not expressly approved by Garmin could invalidate the license and make it unlawful to operate the equipment For non US installations consult the local spectrum management agency requirements GTX 330 Installation Manual Page 1 7 190 00207 02 Revision K 1 9 Limited Warranty This Garmin product 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 r
78. nts 22525 dana 4 4 4 6 Discrete Outputs PIN ASSionimenmts at acetate ase aes a 4 6 Aa Discrete Inputs ASS iG NiS 4 7 45022552222 4 8 4 9 BRING 429 Pin 4 10 330 Installation Manual Page v 190 00207 02 Revision GTX 330 HARDWARE MOD LEVEL HISTORY The following table identifies hardware modification Mod Levels for the GTX 330 and GTX 330D Mode S Transponders 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 1s 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 MOD SERVICE SERVICE PURPOSE OF MODIFICATION LEVEL BULLETIN BULLETIN NUMBER DATE GTX 330D Only Switch Diplexer Assembly reworked to prevent 200 volt supply line from shorting to the chassis Page vi GTX 330 Installation Manual Revision K 190 00207 02 1 GENERAL DESCRIPTION 1 1 Introduction This manual presents the mechanical and electrical installation r
79. nual P N 190 00187 02 Refer to Figure C 9 Sheet 1 for dual GTX 330 gray code altimeter interconnections Refer to Figure C 9 Sheets 2 and 3 for dual altimeter interconnections to a GNS 480 CNX80 The GNS 480 CNX80 can receive digital data from only one transponder at a time Due to system configuration dual transponders must be identical 1 dual GTX 330s in a system with one GNS 480 CNX80 GARMIN GIX 330 1 P3271 RS 232 IN 2 24 GARMIN gt 45 O 1 RS 232 OUT H De 5 885 232 OUT LO GARMIN 1 550 2 5271 RS 232 IN 2 24 2 Figure 4 2 Dual GTX 330 Single Encoder Serial Input Connections For complete dual installations containing two encoders it 1s best to connect one encoder to each transponder GTX 330 Installation Manual Page 4 5 190 00207 02 Revision K 4 4 4 Altimeter Selection Priority The installer must be aware of the GTX 330 priority for selecting encoded altimeter interconnections The GTX 330 searches in this sequence for altitude and stops when it finds a valid pressure altitude input Only approved devices may provide altitude to the GTX 330 in accordance with 14 CFR 91 217 In addition all altitude reporting devices installed the aircraft must meet certification requirements of 14 CFR 91 413 The installer must select an altitude reporting device that is a certified altitu
80. of the sales receipt from the original retailer is required Garmin will not replace missing components from any package purchased through an online auction Garmin International Inc Garmin Europe Ltd 1200 East 151 Street Unit 5 The Quadrangle Abbey Park Industrial Estate Olathe Kansas 66062 U S A Romsey 5051 9DL U K Phone 913 397 8200 Phone 44 0870 851241 FAX 913 397 8282 FAX 44 0870 851251 Page 1 8 GTX 330 Installation Manual Revision K 190 00207 02 2 INSTALLATION OVERVIEW 2 1 Introduction This section provides hardware equipment information for installing the GTX 330 Mode S Transponder related hardware and optional accessories Installation of the GTX 330 should follow the data detailed in this manual Cabling 15 fabricated by the installing agency to fit each particular aircraft The installation should follow the guidance of FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A where applicable 2 2 installation Materials The GTX 330 is available under the following part numbers 2 2 1 Configurations Available Catalog Unit Part Diversity Front Install TSO Class Part Number Kit Docs Number GTX 330 010 00230 00 011 00455 00 2 1 121 010 GTX 330 010 00230 01 011 00455 00 2 1 121 010 GTX 330 010 00230 20 011 00455 20 2 1 121 010 Note Documentation includes pilot s guide and warranty registration card 2 2 2 Equipment Available Garmin PIN Sub Assy Connector Kit
81. ompatible control display units such as the Garmin GNS 480 CNX80 and MX20 Multifunction Display MFD Page 1 2 GTX 330 Installation Manual Revision K 190 00207 02 Surveillance data includes transponder equipped aircraft within the coverage volume Aircraft without an operating transponder are invisible to TIS TIS displays traffic within seven nautical miles from 3000 feet below to 3500 feet above the requesting aircraft The pilot sees the location relative direction and altitude of other aircraft 1 4 Mutual Suppression Pulses Other equipment on board the aircraft may transmit in the same frequency band as the transponder such as DME or another transponder Mutual suppression is a synchronous pulse that is sent to the other equipment to suppress transmission of a competing transmitter for the duration of the pulse train transmission The transponder transmission may be suppressed by an external source and other equipment on board may be suppressed by the transponder This feature is designed to limit mutual interference 1 5 Interface Summary The GTX 330 provides the following interface connections via the rear connector e Ten 10 encoding altimeter inputs e External IDENT input e External STBY input useful for dual transponder installations e External suppression pulse input e Switched power output of up to 1 5 amps for digital altitude encoder power e Aircraft power input 11 to 33 Volts e Aircraft dimming bu
82. ponders individually using a 24 bit ICAO Mode 5 address which is unique to the particular aircraft In addition ground stations may interrogate a GTX 330 for its Transponder data capability and the aircraft s Flight ID which may be the registration number or other call sign The GTX 330 makes the maximum airspeed capability set via configuration pages see Section 5 available to TCAS systems on board nearby aircraft to aid in the determination of TCAS advisories In addition to displaying the code reply symbol and mode of operation the GTX 330 screen displays pressure altitude density altitude temperature and timer functions depending on equipment connections and configuration selection The unit also features an altitude monitor TIS traffic advisories and flight timers A voice or tone audio output announces altitude deviation TIS traffic advisory and count down timer expiration The GTX 330 features multiple transmit receive ARINC 429 and RS 232 data ports The unit concentrates data from three ARINC 429 inputs gray code RS 232 input data and discrete inputs to the high speed ARINC 429 output bus used by display systems such as the Garmin 400 Series 500 Series units The GTX 330 is configured with all key controls The layout of the front panel keys and displays segregates the transponder s primary functions from the secondary functions The unit can be configured so the aircraft avionics master bus can turn the unit on Provision
83. pression output In this case leave the suppression pin open Table 4 6 Discrete Outputs Pin Assignments _________ Pin Number VO ALTITUDE ALERT EXTERNAL SUPPRESSION I O This output is considered active if either the voltage to ground is lt 1 9 or the resistance to ground 15 lt 375 This output is considered inactive if the voltage to ground 15 11 33 Vdc Page 4 6 GTX 330 Installation Manual Revision K 190 00207 02 4 5 2 Discrete Inputs Table 4 7 Discrete Inputs Pin Assignments _ Pin Number EXTERNAL IDENT SELECT EXTERNAL STANDBY SELECT SQUAT SWITCH IN TIS CONNECT SELECT AUDIO MUTE SELECT These inputs are considered active if either the voltage to ground 15 lt 1 9 or the resistance to ground 15 lt 375 These inputs are considered inactive if the voltage to ground 15 11 33 Vdc EXTERNAL IDENT SELECT remote IDENT is a momentary input Refer to Figure C 4 for the squat switch interconnect and to Sections 5 2 10 and 5 2 15 for the squat switch configuration EXTERNAL STANDBY SELECT remote STANDBY is a momentary input used when two GTX 330 systems are installed in an aircraft Refer to Figures C 4 C 7 and C 9 for the EXTERNAL STANDBY SELECT interconnect and to Sections 5 2 15 for verifying external standby configuration When EXTERNAL STANDBY SELECT 15 grounded ARINC 429 OUT PORT 1 remains active while P
84. raft address page Verify that the address is correct The unit now contains a Mode S address and may be turned off To power the unit on in the normal mode press only the ON ALT or STBY key without holding the FUNC key or turn on with the avionics master switch MODE S ADDRESS AIRCRAFT REGISTRATION PAGE SELECTION DESCRIPTION US TAIL N Registration Number HEX Hexadecimal code address 5 2 12 2 MODE S Flight ID Pages Flight ID can be entered in TSO Class 2 units P N 010 00230 010 00293 When a Flight ID Number contains a space the GTX 330 automatically removes spaces in data transmission For operation requiring the flight crew to enter an aircraft identification designator each time the unit 15 powered up select the page identified as FLIGHT ID PWR UP ENTRY When this choice is selected and the crew enters the Flight ID correctly the flight number call sign for radio contact with ATC 15 the same flight identification that the GTX 330 S transponder replies to ATC radar interrogations SELECTION DESCRIPTION SAME AS TAIL If address is a US registration number FLT ID can be the same POWER UP ENTRY Enter FLT ID every time the unit 15 turned on in normal mode CONFIG ENTRY Enter FLT ID in Configuration mode only The screen depicted here shows the FLIGHT ID PWR UP ENTRY choice 2 after the CRSR key is pressed and the unit is ready to receive the flight identification For entering all Mode S
85. rams Refer to Section 2 Section 4 and Appendices B and C of this manual Special Inspection Requirements N A Application of Protective Treatments N A Data Relative to Structural Fasteners Antenna installation removal and replacement should be in accordance with applicable provisions of FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A Also refer to Section 2 of this manual Special Tools N A This Section is for Commuter Category Aircraft Only A Electrical loads Refer to Section 1 6 3 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 FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A Overhaul Period No additional overhaul time limitations Airworthiness Limitation Section N A Revision To revise this ICA a letter must be submitted to the local FSDO with a copy of the revised FAA Form 337 and revised ICA The FAA inspector accepts the change by signing Block 3 and including the following statement The attached revised new Instructions for Continued Airworthiness date for the above aircraft or component major alteration have been accepted by the FAA superseding the Instructions for Continued Airworthiness date 330 Installation Manual Page 3 190 00207 02 Revision
86. rial data interconnect and Sections 5 2 8 and 5 2 18 for ARINC 429 serial data configuration GTX 330 Installation Manual Page 4 11 190 00207 02 Revision K This page intentionally left blank Page 4 12 GTX 330 Installation Manual Revision K 190 00207 02 5 POST INSTALLATION CONFIGURATION AND CHECKOUT PROCEDURE Perhaps the most important factor in the GTX 330 transponder configuration and checkout is the Mode S address entry Refer to Section 5 2 12 for Mode S address entry pages Be sure to check all aircraft control movements before flight is attempted to insure that the wiring harness does not touch any moving part Verify proper operation of the transponder during a flight test under VFR conditions If the unit detects an internal failure mode the word FAIL 1s displayed on the screen Make sure an approved device 15 installed for reporting altitude accordance with 14 CFR 91 217 Refer to Section 4 4 4 for altimeter data selection priority 5 1 Operation The coverage you can expect from the GTX 330 is limited to line of sight Low altitude or antenna shielding by the aircraft itself may result in reduced range Range can be improved by climbing to a higher altitude It may be possible to minimize antenna shielding by locating the antenna where dead spots are only noticed during abnormal flight attitudes GARMIN IDENT 5 1 330 The GTX 330 should be turned off b
87. riate as indicated in FAA Advisory Circular AC 43 13 2A paragraph 27c 4 3 4 Post Installation Checkout After the installation is complete refer to Section 5 for system configuration Verify proper operation of the transponder by testing in accordance with Appendix F to 14 CFR Part 43 ATC Transponder Tests and Inspections Page 3 2 GTX 330 Installation Manual Revision K 190 00207 02 4 SYSTEM INTERCONNECTS 4 1 Pin Function List 4 1 1 J3301 21 20 19 18 17 46 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 42 41 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 45 44 43 4 1 43301 Table 4 1 P3301 Pin Assignments 6 In 8 9 2 2 _ 27 POWER GROUND 1 Denotes Active Low Ground to activate 330 Installation Manual Page 4 1 190 00207 02 Revision K Table 4 1 3301 Pin Assignments Cont d Pin 38 RESERVED 1 39 RESERVED MO 41 43 POWER GROUND 2 47 AUDIO MUTE SELECT 51 RESERVED 1 _ 52 1 54 ___ 55 SPARE 57 __ 0 58 RESERVED 1 59 60 AIRCRAFTPOWER2 1 Denotes Active Low Ground to activate Page 4 2 330 Installation
88. s input voltage e Aircraft master switch turn on option e Serial altitude or GPS groundspeed input e Serial altitude input Reduces wire count vs parallel wire gray code altimeter interface e Software update input e Supports Comm A and Comm B protocol e Temperature Altitude Hold and Density Altitude e Digitally recorded voice and discrete warning annunciator activated by Altitude Hold when limits are exceeded e Diversity GTX 330 is available with or without the diversity feature GTX 330 Installation Manual Page 1 3 190 00207 02 Revision K The GTX 330 supports the following list of Binary Data Selector BDS registers BDS 0 0 Air Initiated Comm B AICB BDS 1 0 Data Link Capability Report BDS 4 0 Selected Vertical Intention BDS 5 0 Track and Turn Report BDS 6 0 Heading and Speed Report BDS 1 7 Common Usage Ground Initiated Comm B GICB Capability Report BDS 1 8 Mode 5 Specific Services GICB Capability Report BDS 1 9 Mode S Specific Services GICB Capability Report BDS 1 D Mode 5 Specific Services Protocols MSP Capability Report BDS 2 0 Aircraft Identification BDS register information is presented for the installation agency to understand the functionality of the GTX 330 and make a determination that the unit complies with the requirements of their civil aviation authorities No further wiring or configuration programming is required for the unit Note that BDS 3 0 i
89. s only required for transponders compatible with ACAS TCAS II The GTX 330 does not support BDS 3 0 1 6 Technical Specifications 1 6 1 Environmental Qualification Form It is the responsibility of the installing agency to obtain the latest revision of the GTX 330 Environmental Qualification Form The form is available directly from Garmin under the following part number GTX 330 Environmental Qualification Form Garmin part number 005 00131 03 To obtain a copy of this form see the dealer OEM portion of the Garmin web site www garmin com The following tables present general environmental specifications For detailed specifications see the Environmental Qualification Form Page 1 4 GTX 330 Installation Manual Revision K 190 00207 02 1 6 1 Electrical Specifications 95 50 for 6 hours 85 38 for 16 hours Tested to Category DO 160D 74 dBm nominal for 90 replies Mode S Altitude Capability 25 Foot increments from 1000 to 50 175 feet with suitable serial data altitude 100 Foot increments from 1000 to 62 700 feet Mode S Capability Selective Identification Codes Aircraft Type External Suppression Input Low lt 0 5 V High 2 8 Audio Output 4 04 Vrms to 7 85 Vrms into a 500 Q load Note Refer to Paragraph 2 2 1 Configurations Available for TSO class GTX 330 Installation Manual Page 1 5 190 00207 02 Revision K 1 6 2 Physical Characteristics Depth Behind Panel with Connectors
90. self test routine and displays a Jump to Diagnostics page 3 Press the FUNC key repeatedly to toggle through the pages until you come to the address entry page For a shortcut select the Aircraft Configuration Menu page see para 5 2 1 and then CRSR 9 9 9 CRSR and the FUNC key three a The page that appears is either ADDRESS US TAIL N MODE S US TAIL Page MODE S Address HEX Page It 15 not necessary for the installer to convert a US aircraft registration number N number to a Hex address The GTX 330 converts the US registration number to hexadecimal automatically 4 select between Hex or Tail number press the CRSR key then 8 or 9 key to move to the correct selection 5 For entering either the address hex code or the US registration number press the CRSR key 1 time This highlights the address field Page 5 16 GTX 330 Installation Manual Revision K 190 00207 02 6 address using the number keys Press key repeatedly to scroll through the digit alpha characters that key 7 Press the CRSR key to select the next numeric entry field Enter the next character as stated in the previous step then move onto the next one repeating the process until the complete number is entered 8 When finished press the CRSR key to accept the number entry 9 Using the FUNC and or START STOP keys toggle through the pages to get off of then back onto the airc
91. t 45 30 From Bottom Page 2 6 330 Installation Manual Revision K 190 00207 02 2 8 2 Mechanical Installation Avoid installing the unit near heat sources If this is not possible insure that additional cooling is provided Allow adequate space for installation of cables and connectors The installer will supply and fabricate all of the cables All wiring must be in accordance with FAA Advisory Circulars AC 43 13 1B and AC 43 13 2A 1 Assemble the connector rack kit according to Figure B 2 Install the rack assembly according to the dimensions given in Figure and paragraph 1 6 2 Physical Characteristics Mounting brackets are not supplied due to the wide range of mounting configurations available Suitable mounting brackets may be fabricated from sheet metal or angle stock To insure a sturdy mount rear support for the unit must be provided 2 Looking at the bottom of the transponder make sure the front lobe of the locking mechanism 15 a vertical position This can be accomplished by using a 3 32 hex wrench through the face plate 3 Slide the unit into the rack until the front lobe of the unit touches the rack 4 Turn the hex wrench clockwise until unit is secured in the rack Continue turning until tight Do not overtighten the screw 5 remove the unit from the rack turn the 3 32 hex wrench counterclockwise until it disengages from the rack
92. the ARINC 429 input ports Each port can be configured independently for the desired function s The ARINC 429 IN 1 INPUT allows ARINC 429 INPUT Second Page automated start and stop of the flight timer and places the transponder in ground GND mode upon landing The same input data source cannot be selected for multiple input channels 1 through 3 ADLP is included for future use SPEED Channel 1 3 SELECTION DESCRIPTION Standard low speed ARINC 429 nominally 12 5 kilobits per second High High speed ARINC 429 nominally 100 kilobits per second DATA Channel 1 4 through AHRS Attitude and heading information 3 EF AD NO ALT Selected course heading temperature joystick waypoint and speed information EF AD W ALT Selected course heading temperature joystick waypoint and speed information plus altitude data Airborne Data Link Processor is available only channel 4 330 Installation Manual Page 5 11 190 00207 02 Revision K 429 OUTPUT The 330 be configured to include GPS Airdata AHRS EFIS Airdata and ADLP ARINC 429 inputs ARINC 429 OUTPUT Page functioning as an ARINC 429 data concentrator Refer to Section 4 6 SERIAL DATA ELECTRICAL CHARACTERISTICS for details The ARINC 429 OUTPUT Pages configure the ARINC 429 output ports Each port can be configured independently for the desired function s Both ARINC 429 outputs send high sp
93. tions and Conditions Compatibility of this design change with previously approved modifications must be determined by the installer If the holder agrees to permit another person to use this certificate to alter the product the holder shall give the other person written evidence of that permission Descriptive data pertaining to this design change are considered inadequate for duplication of other products This approval is limited to only the installation made in Piper model PA 32 260 Serial Number 32 7100002 This STC does not permit manufacturing of parts for multiple installations certificate and lhe supporting dala utich ts the basis for approval shall remain in until surrendered suspended revoked or a termination date ts otherwise established by the Sbdinrinistrator of lhe Federal Rviation Administration Yate rh anplicat or Mach 11 2002 Dale reissued yf Duele of issuance December 12 2002 Yate amended lhe Signature Harvey E Nero FAA Program Manager Wichita Aircraft Certification Office Title Any alteration of thie certificate punishable by a fine of not exceeding 51 000 imprisonment not exceeding 3 years or both FAA Form 8110 2 10 68 PAGE 1 of 2 PAGES This certificate may be transferred in accordance with FAR 21 47 GTX 330 Installation Manual Page A 1 190 00207 02 Revision K A 2 Continued Airwort
94. uest 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 select and contact a DER from the roster of individuals identified thereunder 5 Contact an aviation industry organization such as the Aircraft Electronics Association and request their assistance GTX 330 Installation Manual Page 2 5 190 00207 02 Revision K 2 7 Cooling The 330 meets all applicable TSO requirements without air cooling The application forced air cooling to the rear air nozzle of the 330 15 highly recommended to provide beneficial cooling to the unit The GTX 330 was designed to handle a constant interrogation of 450 Pulse Repetition Frequency PRF per second with short periods of 1200 Rate limit is set at 1200 A typical radar site would interrogate the transponder once every 5 to 10 seconds for approximately 100 milliseconds at a 400 PRF rate In very high traffic areas with multiple ground stations and TCAS traffic it is possible to have long term PRF rates above 450 PRF 2 8 GTX 330 Installation 2 8 1 Viewing Angle Ensure that any mounting location will offer sufficient viewing angle The display has been proven to meet specifications when seen within the following envelope of viewing positions Direction Viewing Angle Left and Righ
95. ult set to 24 seconds AUTO FLIGHT TIMER Available choices are MAN CLEAR and ACCUM Selecting CLEAR resets flight time to zero and starts the flight timer when lift off is sensed Manual selection DEFAULT Flight timer START STOP 15 controlled manually by the pilot Automated flight START STOP resets to zero at every lift off Automated flight timer START STOP accumulates meaning it continues counting up at lift off GTX 330 Installation Manual Page 5 15 190 00207 02 Revision K 5 2 11 Temperature SENSOR INSTALLED TEMPERATURE Page Sets the Sensor to YES NO Default 15 NO UNITS Sets the units to degrees Fahrenheit or Centigrade Default 15 degrees 5 2 12 Mode Address Entry Pages It is VERY important to enter the Mode S address correctly in the GTX 330 When the unit is turned on for the first time or an invalid address 1s recognized the unit prompts the user to enter a valid aircraft address Once the aircraft address is entered the unit remains on the same mode as before 5 2 12 1 US TAIL and Hex ADDRESS Entry Pages For first turn on proceed to step 5 Otherwise begin at step 1 with the unit turned off 1 enter the configuration pages press and hold the FUNC key while powering the unit 2 Power the unit by pressing the ON ALT STBY key or turn with the avionics master switch while holding the FUNC key The unit performs a
96. un Seles 006 007 Ld 8 47 10084 Sd 8 17 10084 7100 4 5 SI YO NV 38 GINOHS LNG 0350 38 OSIY AVW LAdNI GIHOLIMS 14319 2144 1 300 12313530 123135 01 10114 MOTIV LON 5300 NMOHS TANVd JHL 5 086 AHL 30 404 AAILOV 38 193145 AGGNVLS 5 13 11901 38 OL SLINN Ogg 19 SLAdLNO 5 SIHL NAHM JONVOAdNI HOIH SI SI LAdNI 193135 AGGNVLS 1404 100 Ogg 9 FHL 8 2 384914 OL 43434 53 435 006 007 JWYS OL 2144 1 YSHLONV LON 04 14 AHL 035 SI SIL ONIGNVT NOdN 9 1 530 14 1 9114 40 4015 LYVIS SMOTIV LNANI 66 72 5 SSIINN 1 53 SALON
97. urope Refer to ICAO standards 7000 VFR code commonly used in Europe Refer to ICAO standards 7500 Hijack code Aircraft is subject to unlawful interference 7600 Loss of communications 7700 Emergency Avoid selecting code 7500 and all codes in the 7600 7777 range These codes trigger special indicators in automated facilities An aircraft s transponder code is used for ATC tracking purposes therefore exercise care when making routine code changes GTX 330 Installation Manual Page 5 3 190 00207 02 Revision K 5 1 3 Function Display PRESSURE ALT Displays the altitude data supplied to the GTX 330 feet hundreds of feet 1 e flight level or meters depending on configuration FLIGHT TIME Displays the Flight Time controlled by the START STOP key or by one of four airborne sources squat switch GPS ground speed recognition airdata airspeed recognition or altitude increase as configured during installation The timer begins when the GTX 330 determines that the aircraft is airborne ALTITUDE MONITOR Controlled by START STOP key Activates a voice alarm and warning annunciator when altitude limit 15 exceeded OAT DALT Displayed when the GTX 330 is configured with temperature input Displays Outside Air Temperature and Density Altitude COUNT UP TIMER Controlled by START STOP and CLR keys COUNT DOWN TIMER Controlled by START STOP CLR and CRSR keys The initial Count Down time is entered with the 0

Download Pdf Manuals

Related Search

Related Contents

必ずお読みください - アイ・オー・データ機器    ダウンロード    SIRÈNE ÉLECTRONIQUE COMPACTE SC 298  Voloci NiMH User`s Manual  National-向け施工説 CHA42 改訂 081011.ai  User Manual - AAS Technology  I agree with the terms of use of this web site  Tripp Lite S502-20N User's Manual  

Copyright © All rights reserved. Failed to retrieve file