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COBHAM C406-2 SERIES Specifications

1. 9 HLOH LON Nid YO 1 Nid OL SOAP HIMOd LAVY HIV AlddV 1 l Nid AVN L ld NOIL33NND2 VIA SI LL 113404 A TIVN2131NI lt Nid LL Sna 3dA92 OL NOWND2 SI Y 4A3H3 IHNWU 3143124313 1 Id lv O TIV 31 WNOILJO SI NOILJJNNO H 35MUSHLO LL O3HIM 51 9 3LOWF4 ANV 173 HI 033 JONNY ALI SSN ANNOYS 13 31 IN UNICO m 5 2 z j 0351 LON 41 5 OL Ld ILON 2259958 8 OKs 4WH HIV AHVNIA JNIHM Ad MJO 19 V ONIN JAMPINI JISNHILIU NIN L13 VIA ONNGH 031 Al HIIHM 9 UNY S Nid DL 518 SISSTHOOV AING 30 NOLIN 350 0321701995 HIM GINMVHOOHA 5 174 INDI 5 113 QARI AA AIND AVI SS AHO 553 00 Lila ve FIGURE D 2 ELT NAV INTERFACE TO ELT WIRING DIAGRAM 06 30 99 PAGE D
2. The switch assembly requires a space about 2 high by about 1 wide both on the panel surface and behind the panel Refer to Figure 3 8 Mark a cutout for the cockpit panel switch with the dimensions shown in Fig ure 3 8 Install the switch assembly by fitting it into the cutout marking the 4 screw holes and drilling them with a 28 1405 drill bit Use the 4 40 X 1 2 pan head phillips screws nuts amp lock washers pro vided Apply the For Aviation Emergency Use Only Unauthorized Use Prohibited ard that is supplied in the Installation Kit as near the switch installation as practi cal 3 6 Wiring the 406 System CAUTION Prior to installing the harness in the 12 pin receptacle feed the wire bundle through the rectangular hole in the mount ing frame cap The receptacle will not fit through the mounting frame cap harness entrance if the harness is installed prior to doing this 3 6 1 Fabricate the Cable NOTE If the ELT is to be used with an Artex ELT NAV Interface P N 453 6500 refer to the ARTEX ELT NAV Interface Installation and Operation Manual 570 4602 for wiring instructions Wires will need to be run which connect pins 9 10 11 and 12 of the ELT to the ELT NAV Interface unit DOCUMENT 570 5000 Fabricate a 5 wire harness 22 Gauge minimum long enough to reach between the ELT installation location and the cock pit panel switch location See Figure 3 9 Strip about 150 of
3. NOTE If the aircraft does not have electrical system i e no battery it is permissible to fabricate using 3 alkaline 9 volt batteries in series a substitute power source for the remote light Connect the positive side of power source to the 28vdc pin of the remote switch The alter ation should be noted in the log book and the battery should be checked peri odically and must be replaced every two years DOCUMENT 570 5000 3 6 5 Finishing Up With its switch in the OFF position down insert the ELT into the mounting tray at an angle so that the locking ears at the end opposite the direction of flight arrow fit into the mounting tray locking slots Press the ELT down into the mounting tray until fully seated Install the protective top cover on the ELT by fitting the cover locking slots over the locking ears on the ELT Push the cover toward the connector end of the ELT and seat it down in place on the ELT Insert the antenna coax cables through the end cap access holes and connect to the ELT unit Connect the 12 pin Molex connector to the ELT unit Slide the end cap into place over the mount ing tray and protective top cover and se cure the end cap to the mounting tray using the two thumbscrews Tie up excess slack in the coax cables yet leave enough slack so that the mounting tray cap can be easily removed Perform the tests as outlined herein It is VERY important that the cockpit switch panel l
4. Summarv of Minimum Requirements Specifications 121 5 MHz Specifications 243 0 MHz Specifications 406 025 MHz Transmitter Test ELT Batterv Pack Replacement SPECIFICATIONS 8 APPROVALS SPECIFICATION TABLES 06 30 99 PAGE Il 3 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 C406 2 Model Descriptions Approvals APPENDIX A DOCUMENTATION amp LICENSE DATA Available Documentation Radio Station License Data APPENDIX B REGISTRATION REQUIREMENTS Registration 406 MHz ELT CHANGE OF OWNERSHIP CHANGE OF REGISTRATION FORM U S APPENDIX C SYSTEM COMPONENT PART NUMBERS C 1 System amp Sub component Part Numbers APPENDIX D ELT NAV INTERFACE OPERATION ELT NAV Interface Capability ELT NAV Interface Communication Formats Installation and Checkout Process ELT to NAV Interface Information FIGURE D 1 ELT NAV INTERFACE INSTALLATION OVERVIEW FIGURE D 2 ELT NAV INTERFACE TO ELT WIRING DIAGRAM 06 30 99 PAGE Il 4 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 SYSTEM DESCRIPTION 06 30 99 PAGE 1 1 ARTEX AIRCRAFT SUPPLIES SYSTEM DESCRIPTION The ARTEX C406 2 series ELT s C406 2 and C406 2HM are a third generation ELT transmitting on 121 5 243 0 and 406 025 MHz The ELT s are designed to meet or exceed the requirements of TSO C91a TSO C126 and the mandatory automatic ELT re quirements of FAR Part 91 The ELT meets the requirements of Canadian Aviation Regulations CAR Part V Subpart
5. with ref er ence to an other part of the air frame not less than 0 3 me ters 1 foot nor more than 1 0 me ters 3 feet from the mountinglocation Inaddition RTCADocumentNum ber DO 182 rec om mends that all ELT sys tem com po nents which must survive a crash in tact should be at tached to the air frame in such a man ner that the attach mentsys tem can sup porta 100g load in the plus and mi nus di rec tions of the three prin ci pal axes of the air craft Further in stalla tion guidance canbe found in FAA Advisory Circular 43 13 2 Ac cept able Methods Tech niques and Practices Air craft Al ter ations Chap ter 2 para graph 28 deals specificallywith Emergency Transmitter installations Mount the ELT unit horizontally so that the rigidity requirements are met and the arrow on the mounting tray is aligned within 10 degrees of the longitudinal axis of the aircraft and pointed in the direction of flight Refer to page 3 19 amp Figure 3 13 for helicopter installations Finally in selecting a location for the ELT installation the following cautionary advice should be taken into consideration DOCUMENT 570 5000 CAUTION Avoid locating the ELT where it will be subjected to unprotected exposure to harsh chemica fluids such as deicing compounds They can promote cracking and fracturing of the ELT mounting frame and housing components by degrading and weakening the structural integrity of the housing an
6. 5 18IN LBS SWIICH 152 FEVALE CRM FING JIN CE AEREA El IV EXCENNCI 22 AWS VINIVIJM FIGURE 3 11 ELT TO REMOTE SWITCH INTERFACE DIAGRAM 06 30 99 PAGE 3 14 SUPPLIES DOCUMENT 570 5000 1 125DIA FIGURE 3 12 BUZZER BRACKET For installations using ELT NAV Inter face Crimp a male terminal pin ARTEX P N 151 6627 to one end of each of the wires which will run to the ELT NAV In terface unit P N 453 6500 On the other end of each of the wires which run to the ELT NAV Interface unit solder a connector pin ARTEX P N 151 2100 as described in the ELT NAV Interface Installation and Operation Manual 570 4602 NOTE This cable may be connected now or after installing either the ELT or the front panel switch assembly All wir ing must be installed in accordance with 43 13 1A 3 6 2 Connecting the ELT Refer to Figures 3 9 3 10 and 3 11 Feed the crimp terminated wires for the 12 pin connector through the rectangular hole in the mounting frame cap Fabricate a short jumper about 1 5 long and install male terminal pins on each end Install the jumper between pins 5 and 8 in the 12 pin receptacle In stall the remaining wires into the 12 pin receptacle as shown in Figures 3 10 and 3 11 Push the connector into place in side the mounting tray cap The mount ing frame cap acts as a retainer for the connector once the cap i
7. 7 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 THIS PAGE INTENTIONALLY LEFT BLANK 06 30 99 PAGE D 8
8. 7 oz UnitColor Orange UnitCoaxConnectors BNC 121 5 243 0 MHz andTPS 406 025MHz Mating plugdoesnotextendbeyondexteriorsurfaceofendcap Tolerances are0 030 inches Recommendedinterconnectharness wire gauge is22AWGminimum Pins5and8ofthe external connector must bejumperedtoenable G switch O Q gt N FIGURE 3 3 ELT OUTLINE DIMENSIONS 06 30 99 PAGE 3 4 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 LEACING EDGE PROTECTION OPTIONAL CORK GASKET 7 i 406 2 CONN 1215 243 MIZ CNN L 825 BNC 201 DIA HELE THRU SPLEI 0203 RLVULRED UN AIRCRAFT SPLUS 1600 DIA CON CLEARA CE HOLE REQUIRED IN AIRCRAFT PLCS la NOTES 1 3 LBS FINISH WHITE PCLYURETHANE PAINT FREGUE CIES 1215 243 9 406 MHZ NORMAL INPENANCE 50 POLARIZATION VERTICA RADIATIUN N UMNIDIRE TILINAL VSw 1215 2 204 Max 243VHZ 201 MAX 406442 LEA MATING CONNECTER BNC AND TPS FOWER 50 WA TS HAREWARE AND H10 32 SCREW TO MAXIMUM TRaE F 20 IN LES DURING INSTALLATION PROVIDE A 0 6240 5 80 DIAMETER OLE FOR CONNECTOR PROVIDE N6250 5 0 DIAMETER HILE FOR TPS CONNECTOR GASKET CORK AIRIPEZD RATING 6CO KNOTZ TAS 25 000 FT TOLERANCES XX 030 XXX 010 ANGLES ALL DIMENZILNS IN INCHES awn 3 4 110 337 OUTLINE 06 30 99 PAGE 3 5 A
9. Gs G SWITCH G SWITCH CHARACTERISTICS 85 C 55C 85 C 04 04 02 PAGE 5 2 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 VIBRATION 1065 5Hz TO 2 000Hz 1065 5Hz 2 000Hz SHOCK TEST 006s FOR 4 mSec FOR 4 msSec CRASHWORTHINESS 100Gs FOR 23 mSec HUMIDITV 95 FOR 50 HOURS 95 FOR 50 HOURS DROP 55085 FROM 6 INCHES CRUSH TEST 1 000 wes iooo LBS SPURIOUS EMISSIONS AS PER CFR TITLE 47 JAS PER RTCA DO 204 FCC PART 87 OHMS NOMINAL AT 150 OHMS NOMINAL VSWR 121 5 AND 243 0 MHz LESS THAN 15 5 1 OPERATING SPEED 110 320 350 KNOTS TAS 4110 320 350 KNOTS TAS 110 328 01 110 333 AND 110 328 01 110 333 AND 110 337 MACH 1 110 337 MACH 1 7 WITH BNC RG 142 WITH TPS AND CONNECTORS TNC CONNECTORS 09 07 00 PAGE 5 3 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 ANTENNA 110 320 7 5 OZ MAXIMUM 110 333 125 OZ MAXIMUM 110 328 01 1 LB 3 2 OZ MAXIMUM 110 337 1 LB 50 02 MAXIMUM MEASUREMENTS C406 2 Series ELT ELT WITH MOUNTING 11 74 L x 3 90 H x 3 82 W TRAY PROTECTIVE TOP COVER AND END CAP INSTALLED HEIGHT 110 320 16 50 BASE TO TIP HEIGHT 110 328 01 00 BASE TO TIP HEIGHT 110 333 10 BASE TO TIP HEIGHT 110 337 75 BASE TO TIP HEIGHT SPECIFICA C406 2 Series ELT TIONS TYPE OF CELL LITHIUM MANGANESE DIOXIDE VOLTAGE 12 0 VOLTS AMP HOUR RATING 10 0 AMP HOURS REPLACEMENT BATTERY PART NUMBER 4
10. RS 232 format must have a Start of Text STX an A identifier for latitude a B identifier for longitude and END of Text ETX The format expects carriage returns but will not operate if there are line feeds The following manufacturer s navigation systems are known to interface with the ELT NAV Interface system ARNAV SYSTEMS INC e R50 R50i STAR 5000 FMS 5000 Multi Functional Dis play MORROW eFLYBUDDY 2001 NMS BENDIX KING eKLN 88 KLN 90 TRIMBLE e NAV 1000 NAV 2000 TNL 2100 and TNL3100 The fol low ing Trimble sys tems all re quire a RS 422 to RS 232 adapter NAV 3000 TNL 1000 TNL 2000 TNL 20004 TNL 3000 2000 AP PROACH 2000 AP PROACH PLUS 2101 AP PROACH 2101 AP PROACH PLUS 2101 I O AP PROACH 2101 I O AP PROACH PLUS For other equipment models contact that equipment manufacturer to determine if their equipment supports the ARINC 429 or RS 232 format specified above 06 30 99 PAGE D 3 ARTEX AIRCRAFT SUPPLIES D 3 Installation and Check out Process All installation processes and interconnec tions to navigation systems should adhere to the guidelines set forth in the FAA Ad visory Circulars AC43 13 1A 43 13 2A 20 130A and 20 138 or later revisions of these documents It is very important that the the Global Positioning System Flight Management Computer GPS FMC manu facturer s installation instructions be con sulted regarding installation detail
11. a station license after submittal of the FCC Form 404 and while awaiting receipt of the sta tion license provided a copy of the sub mitted FCC Form 404 is kept in the aircraft Installation and use in countries other than the U S A shall be in accordance with that country s licensing regulations and in conjunction with the manual 04 11 01 PAGE A 2 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 APPENDIX B REGISTRATION REQUIREMENTS 06 30 99 PAGE B 1 ARTEX AIRCRAFT SUPPLIES B 1 REGISTRATION When a 406 025 MHz ELT is installed in an aircraft it is imperative that the aircraft owner register the ELT In the United States the National Oceanic and Atmo spheric Administration NOAA is the reg istration agency Each 406 025 MHz ELT contains a unique identification code that is transmitted to the satellite This helps the Rescue Coordination Center RCC determine whether an emergency actually has occurred The unique identification permits accessing a data base In the United States the data base contains the following e Owner s Name e Address Telephone Number e Aircraft Type AircraftRegis tration Number This data facilitates inquiries as to the whereabouts of the aircraft the existence of a flight plan and so forth The above information should be kept up to date with any changes to the data corrected i e change of address phone numbers etc The following address should be used
12. an au di ble buzzer and a fixed dual in put an tenna 06 30 99 PAGE 5 5 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 5 2 APPROVALS C406 2 e FAA TSO C126 Environmental Categories C1 BA204XRXXXXXZAZZ204BXXX TYPE AF e COSPAS SARSAT Certificate No 112 e JTSO 2C126 C406 2HM e FAA TSO C126 Environmental Categories C1 BA204XRXXXXXZAZZ204BXXX TYPE AF COSPAS SARSAT Certificate No 112 e JTSO 2C126 10 18 00 PAGE 5 6 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 APPENDIX A DOCUMENTATION amp LICENSE DATA 06 30 99 PAGE A 1 ARTEX AIRCRAFT SUPPLIES A 1 Available Documenta tion An available document which is highly recommended but not required is Docu ment No RTCA DO 182 entitled Emer gency Locator Transmitter ELT Equip ment Installation and Performance and may be obtained from RTCA Secretariat 1140 Connecticut Avenue N W Suite 1020 Washington D C 20036 4001 202 833 9339 CAUTION Installation in a pressurized aircraft constitutes a major modification con sult the Department of Transport Re gional Officer before proceeding DOCUMENT 570 5000 A 2 Radio Station License Data With a current Private Aircraft Radio Sta tion License no further station licensing is required for the ELT installation A Private Aircraft Radio Station license may be obtained by filing FCC form 404 The ELT may be installed used and tested for up to 30 days without
13. and all harness connections have been verified to be correct the con nector at the ELT end of the ELT to Remote Cockpit Switch harness should be sealed to prevent moisture from getting into the wire entry holes This can be done by applying an elec tronic grade non corrosive RTV i e GE RTV 162 around the wires entering the rear of the 12 pin connector 151 5012 re fer to Figure 3 11 Ensure each of the entry holes are filled with RTV This will prevent water from beading up and causing possible bridging between connector pins which could result in false activation of the ELT 3 9 Helicopter Installations The primary consideration to remember is that RTCA 168 Minimum Performance Standards Emergency Locator Trans mit ters paragraph 2 3 1 states that the pri mary sensor Delta V switch in the case of the ARTEX ELTs is intended to re spond to crash accelerations parallel to or coincidental with the longitudinal axis of the aircraft moving generally in a forward direction There are few guidelines aside from ex perience as to the best way to install an ELT in a helicopter The manufacturers have traditionally advised installing the ELT at a 45 degree angle relative to the longitudinal plane of the helicopter This DOCUMENT 4570 5000 was assumed to be the best mounting position given the unique flight character istics of helicopters Experience has shown however that the mounting angle tends to pre
14. insulation from the ends of each of the 5 cable wires Dress and tin the bare wires to prevent the strands from fraying during the crimp ter minal installation Fabricate an additional wire long enough to reach from pin 11 of the ELT connec tor to an aircraft ground point Strip and prepare as described above This wire will be crimped in the same terminal as the wire running from pin 11 of the ELT connector to the cockpit remote switch i e 2 wires terminated at the same point Refer to the depiction of pin 11 on Figure 3 10 As an alternative this wire may be spliced as described in AC 43 13 1A Section 445 Splices in Electric Wire if crimping both wires in a single terminal is not practical Remember the wires at the 12 pin connector end of the harness must be fed through the End Cap Assembly prior to installing the connector Refer to Figure 3 9 and Section 3 6 2 On one end of the cable use a Molex crimp tool Molex Tool 11 01 0008 or equivalent tool for 062 terminal pins and crimp the male terminal pins provided ARTEX P N 151 6627 to each of the cable wires which will mate with the 12 pin receptacle which connects to the ELT Remember there will be 2 wires at pin 11 This end will join to the Molex connector on the ELT unit On the other end of the cable crimp the female terminal pins provided ARTEX P N 151 6628 using Molex Tool or equivalent cited above to each of the 5 cable wires This end wi
15. not a measured check but it does provide con fidence that the antenna is radiating sufft cient power to aid search and rescue The aircrafts VHF receiver tuned to 121 5 MHz may also be used This re ceiver however is more sensitive and could pick up a weak signal even if the radiating ELT s antenna is disconnected Thus it does not check the integrity of the ELT system or provide the same level of confidence as does an AM radio 4 3 18 Step 9 Logbook Entry Enter the date the test technician s in itials and whether the ELT passed or failed into the aircrafts logbook 44 Summary of Minimum Requirements 4 4 1 Specifications 121 5 MHz e Fre quency 121 5MHz Fre quency Tol er ance 6 075 KHz e Modulation AM e Power Out put gt 23 0 dBm 4 4 2 Specifications 243 0 MHz e Fre quency 243 0 MHz e Frequency Tolerance 12 15KHz e Modulation AM DOCUMENT 570 5000 Power Out put gt 23 0 dBm 4 4 3 Specifications 406 025 MHz e Fre quency 406 025 MHz Fre quency Tolerance 2 KHz e Modulation Bi phase L Power Out put 37 0 dBm 2dBm 4 4 4 Transmitter Test Perform the transmitter tests by activat ing the ELT and listening on 121 5 MHz An amplitude modulation AM broadcast radio receiver should be used to deter mine if energy is being transmitted from the antenna see section 4 3 17 NOTE All ELT ON tests should be per formed within the first five m
16. not exceed Mach 1 110 333SPECIFICATIONS e Freq 121 5 243 0 amp 406 025 MHz e VSWR 1 75 1 Max for 121 5 243 0 MHz 1 50 1 Max for 406 025 MHz 04 11 01 PAGE 1 6 ARTEX AIRCRAFT SUPPLIES e Polarization Vertical e Radiation Pat tern Omnidirectional e Airspeed Rating Mach 1 e Connectors BNC amp TNC The 110 328 01 Blade Antenna refer to Figure 1 5 is intended for use by OEMs who have previously de signed this antenna into their applica tions on higher speed aircraft that do not exceed Mach 1 DOCUMENT 570 5000 110 328 01 SPECIFICATIONS e Freq 121 5 243 0 amp 406 025 MHz e VSWR 2 0 1 at 121 5 243 0 MHz 1 50 1 Max for 406 025 MHz e Polarization Vertical e Radiation Pattern Omnidirectional Airspeed Rating Mach 1 Connectors BNC amp TNC 06 30 99 PAGE 1 7 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 FIGURE 1 2 ROD ANT 110 320 FIGURE 1 3 BLADE ANT 110 337 06 30 99 PAGE 1 8 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 FIGURE 1 4 BLADE ANT 110 333 FIGURE 1 5 BLADE ANT 110 328 01 06 30 99 PAGE 1 9 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 THIS PAGEIN TEN TIONALLY LEFT BLANK 06 30 99 PAGE 1 10 AIRCRAFT SUPPLIES DOCUMENT 570 5000 C406 2 OPERATION 06 30 99 PAGE 2 1 ARTEX AIRCRAFT SUPPLIES 2 1 Operation One of the primary features of the C406 2 series ELT s are their simplicity of operation As long as the ELT is locked int
17. portions the au dio should sound like an ELT Set the unit switch to the OFF position 4 3 10 Step 5e Measure 406 025 MHz Power Note the power output is approximately 37 dBm 5 Watts Ensure adequate at tenuation is inserted in line between the ELT s 406 025 MHz output and the input to the spectrum analyzer to protect the analvzers input circuitry Connect the equipment as shown below ELT SPECTRUM TPS Bottom Applicable ANALYZER Connector Attenuator Set the Spectrum Analyzer as follows e Cen ter Freq 406 025 MHz Span 1 MHz e Resolution Band width 1 MHz Vertical Dis play 10dB Div e Sweep Auto e Peak Avg Peak Reference Level 30 dBm e Time Div 20ms e Max Hold On e Attenuator asrequired on Input Turn the ELT on and wait approxi mately 50 seconds for the 406 025 MHz transmitter to turn on transmitter sends out first signal at 50 seconds then every 50 seconds thereafter Determine the power output from the stored waveform The 406 025 MHz power output should 04 11 01 PAGE 4 6 ARTEX AIRCRAFT SUPPLIES be 37 dBm 2 dBm 3 16 W min to 7 94 W max 4 3 11 Step 5f Measure the 406 025 MHz Frequency Ensure that adequate attenuation rated for 406 025 MHz 37 dBm and 5 Watts is installed between the ELT s 406 025 MHz output and the input to the frequency counter to prevent damaging the fre quency counter s input circuitry Set up the equipment as sho
18. this chapter apply the bat tery expiration date label provided with the battery pack to the exterior of the ELT i e on the end cap or other visible location Enter pertinent battery replacement infor mation in the aircraft log book and fill out any other documentation required by local authority If you have any questions regarding the Battery Pack Replacement Procedure please contact Artex Aircraft Supplies 1 800 547 8901 04 11 01 PAGE 4 16 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 SPECIFICATIONS amp APPROVALS 06 30 99 PAGE 5 1 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 ELECTRICAL 121 5 243 0 MHz 406 025 MHz CHARACTERISTICS OPERATING FREQUENCIES 1215 8 243 0 MHz 406 025 MHz 0 005 2 KHz initial 5 KHz 5 years 2 parts 10E9 in 100ms MODULATION AMPLITUDE MODULATION A3X TRANSMITTER DUTY CONTINUOUS 440 mSec 1 or CYCLE 520 mSec 1 every 50 seconds 5 PEAK EFFECTIVE RADI Minimum 50mW 17dBm 5 Watts 2dB PERP ATED POWER PERP for 50 hours at EIRP for 24 hours at 20C or 100mW EIRP 20 20dBm for 48 hours at 20C OCCUPIED BANDWIDTH 25 KHz Maximum 20 KHz Maximum OPERATING TEMPERATUREJ 20C 55C 20C 55C AUTOMATIC ACTIVATION VELOCITY CHANGE OF VELOCITY CHANGE OF FOR 406 Series 45 Ft SECOND 45 Ft SECOND AUXILIARY G SWITCH AC 5 AUXILIARY G SWITCHESJS AUXILIARY G SWITCHES TIVATION FOR C406 2HM JACTIVATE AT 12 IN JACTIVATE AT12
19. 160 COUNTERSUNK HEAD 10 SS MACHINE SCREWS AND ASSOCIATED HARDWARE TORQUE MOUNTING FASTENERS TO 25 26 IN LBS MAXIMUM AIR SPEED MACH 1 FIGURE 3 6 BLADE ANTENNA 110 333 OUTLINE 08 01 01 PAGE3 7 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 IN Foo IN LEALIN 23 Anh N vat dase 25422 LET BEE ANTE Na The ae rs corey PER WI T 11 75 8 27 FANE 2 1 5 AND ANG 449 157 7 ELANZ ES 2 VERT ADA 3 RES 231 01 121 5 243MHz 1 5 1LORBETTER 406 025MHz 3 AIRSFR 2 MACH 1 145 B 3 A AC As NE ANZ IND F VAL A Efe ES ANG A LIE 245641 yAM FD 44 TINN D 0 MZUNT ANTENNA 7237 COUNTERSJNY 4242 119 55 MACHINE SCREWS AN ASSO 20 26 VAJN AC SEF W3 gt INSIALLA EIN NSIENE IN NEHEE DRAWNIGNOTTOSCALE 3 FIGURE 3 7 BLADE ANTENNA 110 328 01 OUTLINE 06 30 99 PAGE 3 8 ARTEX AIRCRAFT SUPPLIES e The mounts shall have max imum static lo cal de flec tion no greater than 2 5 mm 0 1in when a force of 450 newtons 100lbs is ap plied to the mount in the most flex i ble di rec tion De flec tion mea sure ments shall be made
20. 3 ex pires 5 years from he date h it is shi When installing a new battery pack move the paper backing from the rubber seal at the connector end of the battery pack It is recommended that this seal be coated with a non petroleum based sili cone grease i e GE G 635 to provide a moisture resistant seal once the battery is installed To replace reinstall the battery pack con nect the 8 pin connector to the header on the circuit board in the battery pack DOCUMENT 570 5000 Connect the 2 pin connector to the re cessed connector inside the ELT body This step will cause the ELT to activate Reset the ELT by toggling the ON OFF switch on the ELT from ON to OFF Reseat the battery pack on the ELT dressing the harness wires away from the standoffs to avoid pinching the wires be tween the battery pack and the standoffs Connect the SARSAT Beacon Test Set through a 30 dB minimum attenuator to the ELT s TPS connector Activate the ELT and allow the ELT to transmit 3 to 4 406 025 MHz bursts Thereupon verify that there is not a BAD FRAME or NORMAL BAD message on the Test Set display which would indicate a problem with the battery pack i e a bad IC on the battery circuit board Install the four Phillips head screws and tighten securely Do not over torque the screws Once the ELT has been tested as plicable and reinstalled in the aircraft as described in
21. 455 50114 455 5012 1 The C406 2HM with Blade Antenna 455 5013 ___ The above part numbers are for complete systems which include the ELT a mounting tray a protective top cover an end cap a remote switch kit an antenna an installation kit a 6 foot to BNC coax cable a 6 foot TNC to TPS coax cable audible alert buzzer an Installation amp Operation Manual a warranty card and cable beacon registration card The bracketed extension following the part number is a variable three digit number that signifies the Country Code This identifies the county in which the ELT will be registered and for which the ELT is programmed The Country Code designations are established by the COSPAS SARSAT Secretariat When ordering a C406 system or main assembly it is necessary to inform ARTEX of the country of registry and the programming format quired so that the ELT can be programmed accordingly The part numbers for individual Line Replaceable components are listed below ITEM NO C406 2 C406 2HM Blade Antenna Blade Antenna Rod Antenna Battery Pack End Cap Protective Top Mounting Tray Remote Switch BNC BNC Coax Cable TNC TPS Coax Cable Buzzer Installation Kit Install Kit Manual DESCRIPTION Main Assembly C406 2 Main Assembly C406 2HM Antenna 406 Blade Antenna 406 Blade Antenna 406 Rod Battery Pack 406 Lithium Cap Assy Mounting Frame Frame Assy Protective Top Fra
22. 5000 Use the antenna outline drawings fig ures 3 4 through 3 12 to determine the hole pattern and drill size Two coax cables are provided with the C406 2 The BNC to BNC cable is for the 121 5 243 0 MHz transmitter and the TPS ELT end to TNC antenna end coax cable is used for the 406 025 MHz transmitter To eliminate confusion caused by wrong connections the coax cables were designed to connect only one way ensuring proper operation of the C406 2 Longer coax cables up to 20 feet may be constructed if the six foot cables pro vided are too short for the installation RG 400 or RG 142 may be used for fab ricating these cables 3 5 Mounting the Cockpit Light Switch Assembly The switch assembly must be mounted in the cockpit where the pilot can easily CAUTION Incorrect wiring of the Molex connector may damage the ELT cause continuous transmission or result in no remote reset Verify wiring against Figure 3 10 A continuity check is recommended to ensure good connections and proper pin location NOTE FEED THE WIRE 3JNDLE THROUGH 7 MGUNTING FRAME CAF POLE O INS R ING 12 PIN EX PINS INTO T E RECEPTACLE RESEPTAC PIN 1 TO REMOTE COCK T SWITCH AND GAJDUND FIGURE 3 9 ELT MOLEX CONNECTORINSTALLATION 08 01 01 PAGE 3 11 ARTEX AIRCRAFT SUPPLIES reach the switch and see the light The remote switch is required for the ELT to be TSO C126 approved It is not optional
23. 51 Airworthiness Manual Sec tion 551 104 In addition these ELT s are designed to meet the requirements of Eurocae ED 62 The C406 2 series ELT s employ a completely new transmitter which fea tures higher output power and a more integrated design The 121 5 243 0 MHz section of the transmitter is con tained in a module with the 406 025 MHz transmitter The top circuit board contains the microprocessor that con trols the module and ELT func tions The C406 2 is a dual output ELT as all previous models of Artex 406 MHz ELT s have been The ELT automatically activates dur ing a crash and transmits the stan dard swept tone on 121 5 and 243 0 MHz Every 50 seconds for 520 milli seconds long message protocol the 406 025 MHz transmitter turns on During that time an encoded digital message is sent to the satellite The information contained in that message is shown below e Serial Number Of The Trans mit ter or Aircraft ID CountryCode 1 0 Code DOCUMENT 570 5000 ePositionCoordinates when coupled to an ARTEX ELT NAV ELT NAV In ter face unit 453 6500 Refer to Appendix D ELT NAV Inter face Capability for a detailed discus sion of the interaction between the ELT the ELT NAV ELT NAV Interface unit and the aircraft navigation svstem The 406 025 MHz transmitter will op erate for 24 hours and then shuts down automatically The 121 5 243 0 MHz transmitter will continue to oper ate until
24. 52 0133 406 LITHIUM BATTERY PACK NUMBER PACK APPROVED BATTERIES AVAILABLE FROM ARTEX OR ANY DEALER ARTEX AIRCRAFT SUPPLIES INC 14405 KEIL ROAD N E AURORA OREGON 97002 P O BOX 1270 CANBY OREGON 97013 503 678 7929 800 547 8901 FAX 503 678 7930 web site www artex net e mail infor artex net 10 18 00 PAGE 5 4 ARTEX AIRCRAFT SUPPLIES 51 C406 2 Series MODEL DESCRIPTIONS Note The C406 2 series ELT s are di rectly compatible with the ELT NAV Inter face Unit 453 6500 406 2 The C406 2 Type AF Au to matic Fixed ELT which trans mits on 121 5 243 0 and 406 025 MHz The ELT is en closed within a multi piece hous ing con sisting of a mount ing tray a protectivetop cover and an end cap It is provided as a com plete svs tem which includes an in stalla tion kit are mote cockpit switch two coax ca bles an au di ble buzzer and a fixed dual in putan tenna DOCUMENT 570 5000 e C406 2HM The C406 2HM is a Tvpe AF Automatic Fixed ELT which trans mits on 121 5 243 0 and 406 025 MHz The ELT was de vel oped for he li cop ter installations and fea tures an ad di tional 5 G switches al low ing the ELT to be ac ti vated in any of six axes The ELT is en closed within a multi piece hous ing con sisting of a mount ing tray a protective top cover and an end cap It is pro vided as acom plete sys tem which includes an instal la tion kit are mote cock pit switch two coax bles
25. 7 10 30 13 FEB 1999 5 TEST PAGE 3 VIEW VERIFY FREQUENCY AND T jJ gt FLQ EP COUNTRY CODE Me sg 1 Frequency 406 025 MHz PASS COUNTRY 366 USA PAGE 4 VIEW MODE gt FLQ VERIFY HEX CODE ID Me sg 1 96E3 ADA9AS 2DC75B534AFFBFF 7FDFFC7883F58 3EOFAA8 ID 2 DC75B534AFFBFF PAGE 5 VIEW MODE VERIFY AIRCRAFT T ee gt FL Q EP ID ADA9A5 Me sg 1 S TD LOC ELT EXT GPS AIRCRAFT 9 5 FIGURE 4 3A BEACON TEST SET DISPLAYS 06 30 99 PAGE 4 10 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 PAGE 6 VIEW MODE ss EP Mes g STDLOC VERIFY HOMING FREQUENCY Homing 121 5 MHz BCH I9AID7 VALID PAGE 7 VIEW MODE T lt FL EP VERIFY LONG MESSAGE Me sg 1 Othe rinfo Long Mesg PAGE 8 VIEW MODE Pes EP VERIFY LATITUDE AND LONGI Mesa 1 Other nfo TUDE OF 45DEGREES 23 4 MIN 5 UTES NORTH 122 DEGREES 15 1 Lat 4 5N23 4 MINUTES WEST Long 122W15 1 PAGE 9 MENU OPTIONS PRESS Q TO RETURN TO SARSAT BEACON TESTER MAIN SCREEN PAGE Recv View Quit Erase Setup Output FIGURE 4 38 BEACON TEST SET DISPLAYS 06 30 99 PAGE 4 11 ARTEX AIRCRAFT SUPPLIES Page 3 is a frequency and country code page The frequency must read between 406 030 and 406 020 MHz to pass The programmed country code must be the same country as the aircrafts home base Verify that the second line of the display reads PASS Verify that the coun
26. A under certain circum stances TSO s parts manufacturing ap proval PMA FAA approved manufacturer s instructions kits and ser vice handbooks type certificate data sheets and aircraft specifications Other forms of approved data would be those approved by a designated engineering representative DER a manufacturer hold ing a delegation option authorization DOA STC s and with certain limitations previous FAA field approvals Supporting data such as stress analyses test re ports sketches or photographs should be submitted with the FAA Form 337 These supporting data will be returned to the applicant by the local FAA district office since only FAA Form 337 is retained as a part of the aircraft records at Oklahoma City DOCUMENT 570 5000 3 6 6 Buzzer Installation A warning buzzer is required for TSO C126 approval The buzzer p n 130 4004 is powered by the ELT unit and therefore is not dependent upon the aircraft battery for operation It is not signed to operate continuously but sounds at predetermined intervals and runs for shorter periods toward the end of battery life While the buzzer may be located any where on the aircraft it is recommended that the buzzer be placed near the ELT unit as it is loud enough to be heard outside the aircraft when the engine s is are off It is assumed that if the en gine s is are running then the cockpit light will warn the pilot Placing the buzze
27. CEMENT UNITS LRU 1 1 2 The 406 2 series svstem con sists of the following components ELT Unit e a G Switch e b Transmitter e c Microprocessor e d Miscellaneouscomponents e e ON Light f Trans mitter Module Battery Pack Fixed Antenna Connecting Coax Cable Mounting Tray Protective Top Cover Mounting Tray End Cap Cockpit Remote Switch Assembly Buzzer Installation Kit 1 22 TRANSMITTER CHAR ACTERISTICS The printed circuit assembly PCA of the C406 2 series ELT is unique in that the PCA has no RF function but rather only control functions for the RF module The PCA contains a one time programmable microprocessor that controls all the ELT functions ON OFF modulation 406 MHz digital message and RESET 06 30 99 PAGE1 3 ARTEX AIRCRAFT SUPPLIES All RF functions are contained in a separate module The transmitter oper ates simultaneously on 121 5 and 243 0 MHz with the carrier frequencies remaining within 0 005 under all en vironmental operating conditions Ap proximately every 50 seconds the 406 025 MHz transmitter transmits During this time the 121 5 and 243 0 MHz transmitter is momentarily turned off 1 2 1 121 5 243 0 MHz TRANS MITTER The AM modulation at 121 5 and 243 0 MHz is designated as 9 with the carrier amplitude modulated with an audio frequency sweeping down ward over a range of not less than 700 Hz within the range of 1 600 to 300 Hz The sweep repetition rate is b
28. DESCRIPTION OPERATION INSTALLATION AND MAINTENANCE MANUAL DOCUMENT NUMBER 570 5000 REV A Group 406 LOCATOR TRANSMITTERS C406 2 C406 2HM ES Q ERED ARTEXAIRCRAFTSUPPLIES INC REGISTEREDTO 1509001 ANDAS9100 FILENUMBER A10217 ARTEX AIRCRAFT SUPPLIES INC 14405 Keil Road N E Aurora Oregon 97002 Telf 503 678 7929 800 547 8901 Fax 503 678 7930 AIRCRAFT SUPPLIES DOCUMENT 570 5000 o ma lt lt A lt lt lt u Pe E lt lt lt lt ee lt lt lt DE 12 10 02 PAGE I 1 AIRCRAFT SUPPLIES DOCUMENT 570 5000 C 77 C ee C Y Y 4 i j lt lt CG C ns jmeww C 12 10 02 PAGE I 2 AIRCRAFT SUPPLIES DOCUMENT 570 5000 0300 i C lt lt lt 3 ee S oS Je lt _ sr eee C 406 MHz ELT Change of Ownership Change of Registra tion Form U S 570 1023 Rev B ooo ooo 04 04 02 PAGE l 3 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 2 ba Jee b le ATT REVISION HISTORV eee 4 77790 IT G on
29. ELT should be located there Statistics show that the tail section of an airplane is least likely to be dam aged during a crash and therefore provides a good mounting environment for the ELT unit Accessibility of the unit is an impor tant factor in the location of the ELT Mount the unit as far aft as practical 8 32x5 BSCREW 7 4PLCS 8FLATWASHER 4PLCS 8LOCKWASHER 4PLCS 8 32x1 4HEXNUT 4 PLCS DOCUMENT 570 5000 but where it can be easily retrieved for maintenance The mounting surface must be ex tremely rigid therefore mounting the ELT directly to the aircraft skin is un acceptable Mounting an ELT directly to the air craft skin induces crash hiding vibra tions and provides a very poor struct ural mounting surface The mounting location must be able to support 100 pounds of force in any direction with no appreciable distortion in the struc ture The following are the FAA guidelines for mounting an ELT per RTCA DO 183 Sec 3 1 8 The ELT shall be mounted to pri mary air craft load car ry ing struc tures such as trusses bulk heads longerons spars or floor beams EQUIPMENT MOUNTINGPLATE SS AIRFRAME FIGURE 3 2 MOUNTING TRAY INSTALLATION 04 11 01 PAGE 3 3 AIRCRAFT SUPPLIES DOCUMENT 570 5000 0 165DIA MOUNTING HOLES 4PLCS NOTES Allow5 inches minimumclearance for endcapremovaland installation UnitWeight 4lbs
30. IGURE 3 12 BUZZER BRACKET Power and Ground Finishing Up Buzzer Installation Transmitter Test Sealing the ELT Connector Helicopter Installations FIGURE 3 13 HELICOPTER INSTALLATION PERIODIC MAINTENANCE In the United States In Canada 06 30 99 PAGE Il 2 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 Periodic Maintenance Inspection Procedure FIGURE 4 1 PERIODIC MAINTENANCE CHECKLIST Step 1 Remove ELT Connections 4 4 Step 2 Remove ELT Step Remove Battery 4 4 Step 3b Replace Reinstall Battery Pack Step 4 G Switch Check Step 5a Electrical 8 5 Step 5b 121 5 243 0 MHz Power 4 5 Step 5c 121 5 MHz 4 6 Step 5d Audio Modulation 8 6 Step Measure 406 025 MHz 4 6 Step 5f Measure 406 025 MHz Frequency Step 5g Current Draw Tests FIGURE 4 2 TEST HARNESS CONNECTION Step 5h Verification of Digital Message FIGURE 4 3A BEACON TEST SET DISPLAYS FIGURE 4 3B BEACON TEST SET DISPLAYS 4 11 51 Reset EL Po ii e ae hein tee en 4 12 Step 6 Reinstall ELT Step 7 Installed Transmitter Test 413 Step 8 Antenna Test Figure 4 4 ELT Batterv Pack Exploded 4 14 Step 9 Logbook ENtrv nee 0 15
31. IRCRAFT SUPPLIES DOCUMENT 570 5000 PERIODIC MAINTENANCE 06 30 99 PAGE 4 1 ARTEX AIRCRAFT SUPPLIES 41 In the United States WHY To ensure continued reliability of your ELT it must be inspected for dam age and wear which could be caused by age exposed elements vibrations etc Even the best designed equipment if not properly maintained and cared for will eventually fall HOW OFTEN At least once every year unless required more frequently by FARs e g 100 hour inspections IS IT REQUIRED FAR Parts 91 207 91 409 and 43 Appendix D make detailed ELT inspections mandatory HOW DETAILED FAR 43 Appendix D i states in part that each person per forming an annual or 100 hour inspection shall inspect the following components of the ELT 1 ELT unit and mount for improper installation and insecure mounting 2 Wiring and conduits for improper routing insecure mounting and obvious defects 3 Bonding and shielding for im proper installation and poor condition 4 Antenna including trailing an tenna for poor condition insecure mount ing and improper operation 42 In Canada WHY To ensure continued reliability of your ELT it must be inspected for dam age and wear which could be caused by age exposed elements vibration etc Even the best designed equipment if not properly maintained and cared for will eventually fall DOCUMENT 570 5000 HOW OFTEN The ELT must be per f
32. RTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 1 7 N l STI SATELE SN FEX NES 1 TR 11 5 2430 ANE MII 201 5202 M 17 1 1 MAX EDR 22 05 4 bo IMS NOMINA CN AL HN Lk ZAT UN VESTICAL RO IU PLYUS HAL HHI i MATING ANS TOMA ANG TNG gt WE GIT 43 LOS i FIN SFT AVE F TM Sr 27 IN LPs 15 ON MALN ING ALL D MINEIONS IN INS ICE NAXIMLM SPOTT DATING 4 H ASH KNOTS TAR FIGURE 3 5 ROD AN TENNA 110 320 OUT LINE 06 30 99 PAGE 3 6 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 ACT UNPANTO IM COWES CN 9 LK S 05 78 _ N CONNECTOR FEMALE WEVA GREE TM 17 28 SP TACTO DA TO NU 7 NOTES 1 FREQUENCIES 121 5 243 0 AND 408 025 MHz 2 VSWR 2 0 1 OR BETTER 121 5 243MHz 1 5 10RBETTERO406 025MHz POLARIZATION VERTICAL RADIATION PATTERN OMNIDIRECTIONAL MATING CONNECTORS FEMALE AND TNC FEMALE FINISH GLOSS WHITE EPOXY TO UK DEFENSE STANDARD 80 161 WEIGHT 76 LBS NOMINAL IMPEDANCE 50 OHMS MOUNT ANTENNA USING
33. T test 4 Tune a receiver usually the aircraft radio to 121 5 MHz 5 Turn the ELT aircraft panel switch to ON wait for 3 sweeps on the receiver which takes about 1 second and then turn the switch back to the ARM OFF position while paying special attention to the LED activity upon entering the ARM OFF condition The microprocessor in the ELT checks the G switch automatic activation switch latching circuit pins 5 amp 8 on the 12 pin connector at the ELT the 406 025 MHz transmitter for proper RF output presence of valid navigation data ELT NAV Inter face and navigation system must be ac tive and a battery check If the ELT is working properly the sequence following entry to the ARMED OFF condition will result in the panel LED staying ON for approximately 1 second then extinguishing If a problem is detected the LED pro vides a coded signal following the initial 1 second pulse The coded signal and re lated problem are as follows the LED will flash in order of importance with ap proxi mately a 5 to 1 second pause between DOCUMENT 570 5000 each error code if multiple errors are present e a 1 flash in di cates G switch loop open fail ure 3 flashes in di cates a 406 025 MHz transmitter prob lem i e bad or un con nected coax an antenna prob lem low power out put or a pro gram ming error flashes in di cates there is no nav i ga tion data pres ent T
34. aced if the voltage under load is less than 12 0 vdc The battery pack must be replaced with a new one Af ter use in an emer gency e Afteraninadver tent activation ofun knownduration e When the to tal of all known trans mis sions ex ceeds one hour 06 30 99 PAGE 4 4 ARTEX AIRCRAFT SUPPLIES e On or before the battery replacement expiration date 4 3 4 Step 3b Replace Reinstall Battery Pack To replace reinstall the battery pack con nect the 8 pin connector to the header on the circuit board in the battery pack Con nect the 2 pin power harness to the ELT This step will cause the ELT to activate Reset the ELT by toggling the ON OFF switch on the ELT from ON to OFF Fit the battery pack into place dressing wires away from the standoffs to avoid pinching wires between standoffs and bat tery pack Install two screws diagonally from each other to secure battery pack during the tests that follow Note If the check out is going to clude with Step 4 below then reseat the battery pack on the ELT dressing the harness wires away from the standoffs to avoid pinching the wires between the bat tery pack and the standoffs Reinstall the four Phillips head screws and tighten se curely Do not over torque the screws 4 3 5 Step 4 G Switch Check NOTE The ELT cannot be activated this way unless pins 5 and 8 are jumpered this happens automatically when the unit is locked into the mo
35. all only be conducted during the first five minutes of any UTC coordinated uni versal time hour and restricted in dura tion to not more than five seconds 04 11 01 PAGE 2 2 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 ELT Unit INACTIVE ELT Unit ACTIVE Buzzer ON Panel Light ON Unit NO or Panel SW YES or Panel SW FIGURE 2 1 ELT FUNC TIONAL FLOW 06 30 99 PAGE 2 3 AIRCRAFT SUPPLIES DOCUMENT 570 5000 THIS PAGE INTENTIONALLY LEFT BLANK 06 30 99 PAGE 2 4 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 INSTALLATION 06 30 99 PAGE 3 1 ARTEX AIRCRAFT SUPPLIES PLEASE READ THE FOL LOWINGINSTRUCTIONS CAREFULLY TSO C126 PARAGRAPH D RE QUIRE MENTS The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those desir ing to install this article on a spe cific type or class of aircraft to determine that the aircraft installa tion conditions are within the TSO standards The article may be in Stalled only if further evaluation by the applicant documents an accept able installation and it is approved by the administrator The ELT is designed with the installer in mind Extra effort has been made to simplify the installation process Because of the critical nature of an ELT it is very important that the in stallation be performed according to the following instructions Installa
36. am seem 2115 12 10 02 12 10 02 PAGE l 4 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 Table of Contents SYSTEM DESCRIPTION SYSTEM DESCRIPTION LINE REPLACEMENT UNITS LRU TRANSMITTER CHARACTERISTICS 121 5 243 0 MHz TRANSMITTER 406 025 MHz TRANSMITTER FIGURE 1 1 G SWITCH CURVE FCC REQUIREMENTS Artex Antennas ROD ANTENNAS BLADE ANTENNAS FIGURE 1 2 ROD ANTENNA 110 320 FIGURE 1 3 BLADE ANTENNA 110 337 FIGURE 1 4 BLADE ANTENNA 110 333 FIGURE 1 5 BLADE ANTENNA 110 328 01 C406 2 OPERATION Operation Overall Functions FIGURE 2 1 ELT FUNCTIONAL FLOW INSTALLATION 2 3 1 Basic Overview FIGURE 3 1 ELT AND REMOTE SWITCH PANEL 06 30 99 PAGE Il 1 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 ELT Mounting Locations FIGURE 3 2 MOUNTING TRAY INSTALLATION a 3 3 Figure 3 3 ELT Outline Dimensions Figure 3 4 Blade Antenna Outline 110 337 Figure 3 5 Rod Antenna Outline 110 320 Figure 3 6 Blade Antenna Outline 110 333 Figure 3 7 Blade Antenna Outline 110 328 01 Antenna Mounting Locations FIGURE 3 8 REMOTE SWITCH OUTLINE DIMENSIONS Installing the Mounting Tray Installing the Antenna Mounting the Cockpit Light Switch Assembly FIGURE 3 9 ELT MOLEX CONNECTOR INSTALLATION Wiring the C406 2 System Fabricate the Cable FIGURE 3 10 WIRING DIAGRAMS FIGURE 3 11 ELT TO REMOTE SWITCH INTERFACE DIAGRAM Connecting the ELT Wiring Switch Assembly 9 Pin Connector F
37. an be viewed from the pilot s post tion Its intended function is to inform the pilot that the ELT is transmitting avoiding a situation where an aircraft is flying with its ELT transmitting 1 4 2 G SWITCH The crash force activation sensor or G Switch is designed to activate with a change of velocity of 4 5 fps 0 5 fps both under normal conditions and while being subjected to 30 G s of cross axis forces Figure 1 1 shows the plot of time versus G Force that the G Switch must be qualified to in order to meet ED 62 approval criteria The FAA has allowed the use of this G Switch under TSO C126 1 4 3 BATTERY PACK The Battery Pack for all the C406 2 series ELT s consists of 4 D size 06 30 99 PAGE1 5 ARTEX AIRCRAFT SUPPLIES Lithium Manganese Dioxide cells con nected in series In an effort to in crease the safety of the battery pack a number of features were designed into the battery pack To prevent the cells from being charged diodes are connected across each cell and fuses are connected to the output 1 4 4 REMOTE CONTROL The remote control cockpit panel switch provides MANUAL ON ARMED and RESET modes The remote control wiring between the con trol and the ELT is designed so that no combination of short circuits be tween the remote control monitor s associated wiring and the airframe will e Inhibit the equip ment from be ing au to maticallyactivated e Deactivate
38. d tray material These same chemical agents can also cause corrosion on electrical connections 3 2 Antenna Mounting Lo cations Locate a position where the antenna can be installed VERTICALLY up to 15 off the vertical plane is acceptable with at least 30 inches clearance from other antennas especially VHF mounted on the aircraft The coax cable should not cross any production breaks major structural sec tions in the aircraft so that in the event of a crash the ELT and the antenna are in same aircraft section This usually re quires placing the antenna directly above the ELT unit Do not bundle the ELT an tenna coax with any other VHF radio coax power harness or the ELT remote switch harness If the ELT transmitter and external an tenna are on opposite sides of an air frame production break the components should be secured to each other by a tether which can support a 100 G load ELT weight x 100 The interconnecting antenna to ELT coax cable should have sufficient slack on both ends that it will not be subjected to any tensile load and should be tied loosely to the tether Use only the ARTEX approved anten nas The ELT will not operate properly without being connected to the antenna for which it was designed 04 04 02 PAGE 3 9 ARTEX AIRCRAFT SUPPLIES 1 70 SIDE VIEW DOCUMENT 570 5000 1 00 REAR VIEW r GUT OUT PATTERN FIGURE 3 8 RE MOTE SWITCH OUT LINE DIMEN SIONS FAA Advis
39. ddress is designed to be used with the ELT NAV Interface unit and allows the ELT to inter face with the aircraft navigation system The Interface unit should be strapped for the 24 bit address binary 1 to ground or connected to a 24 bit address switch block which is configured to match the 24 bit switch block connected to the aircraft s Mode 5 transponder system The 24 bit strapping will allow the ELT to automati cally program itself to the aircrafts 24 bit address This feature will allow the ELT to be transferred between aircraft without having to reprogram or re register the ELT with the Search and Rescue author ity This makes maintenance of the ELT a simple matter of replacing the ELT The user must specify 24 bit long message programming when ordering the ELT Figure D 1 depicts the typical installation configuration of the ELT ELT NAV Inter face and related interconnections Figure D 2 shows the wiring interconnection for the ELT with an ELT NAV Interface D 2 ELT NAV Interface Communication Formats The ELT NAV Interface unit supports ARINC 429 and RS 232 data bus formats All ARINC 429 Standard and GAMA high or low speed serial bus formats are supported Labels 310 latitude and 311 longitude are required The only RS 232 format which is sup ported is limited to the following condi tions DOCUMENT 570 5000 Baud Rate fixed 9600 Parity None Data Bits 8 Stop Bits 1 In addition the
40. displayed on the GPS FMC system Verification of the lati tude and longitude is desirable but is not required 04 11 01 PAGE D 4 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 In addition the ELT transmitter test de scribed in Section 3 paragraph 3 7 of this manual 570 5000 must be per formed No error codes should be flagged by the ELT LED as described in step 5 of this paragraph D 4 ELT to NAV Interface Information For details on the installation and use of the ELT NAV Interface unit please contact ARTEX Aircraft Supplies Inc at the fol lowing Tel 503 678 7929 1 800 547 8901 or FAX 503 678 7930 to re quest the brochures and Installation and Operation Manual 570 4602 for the ELT NAV Interface unit 10 18 00 PAGE D 5 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 ELT NAV INTERFACE TO COCKPIT REMOTE SMICH ARINC 429 IRS 232 FIGURE D 1 ELT NAV INTERFACE INSTALLATION OVERVIEW 06 30 99 PAGE D 6 DOCUMENT 570 5000 ARTEX AIRCRAFT SUPPLIES 0111 INIT LON SNA Te TIVIH VI 51492720 HIHI V AAVH 15 MIN JANLIINOT NV 15 300 111Y1 XLA UNY 4015 VIVU NON ALI NVA 0096 03395 LIIN ISIN 2652 54 ONISA Jl LON A MOT HYH ONVINVIS ATIWNYALNI TAW
41. e ELT NAV Interface installation not be in conflict with the GPS FMC manufacturer s installation instructions in order to avoid an installation that may degrade the GPS FMC performance As a result the Post Installation checkout in the GPS FMC Installation Manual must be followed after installing the ELT NAV Interface box NOTE The updated hex ID must be verified for ELT s which are programmed for the 24 Bit Protocol and are installed with an ELT NAV Interface which is strapped for the aircraft address The ELT output must be verified for the correct air craft address and the ELT must be la beled with the new 15 digit hex code ID Refer to the ELT NAV Interface Manual 570 4602 Section 3 7 2 For this test the portable SARSAT Beacon Test Set Artex P N 453 0131 must be used The 406 MHz ELT output TPS connector in recessed area on front of ELT must be connected directly to the hand held tester via a coax cable and a 30 dB attenuator If using the existing antenna coax cable TPS to TNC a TNC to BNC adapter must be used to connect to the SARSAT Beacon Tester The portable SARSAT Beacon Test Set ARTEX P N 453 0131 must be used to perform the tests described in Section 4 paragraph 4 3 13 of this manual 570 0421 The hex code displayed on the tester should match the hex code which is on the ELT s product label If re ceived the latitude and longitude dis played on the tester should match the latitude and longitude
42. etween 2 and 4 Hz with a modula tion factor of at least 0 85 The modu FKEM 2 IM Ku FUE B D ARA I DOCUMENT 570 5000 lation applied to the carrier frequency has a minimum duty cycle of 33 and a maximum duty cycle of 55 The ARTEX C406 2 series ELT is designed for a constant power output at 121 5 and 243 0 MHz that will not be less than 23 dBm 200 mW dur ing the 50 hour operational period at both 20 degrees Centigrade and 55 degrees Centigrade 1 2 2 406 025 MHz TRANS MITTER A digital information message is sent to the satellite via the 406 025 MHz transmitter The modulation is phase modulated and classified as 16K0G1D Every 47 5 to 52 5 sec onds the 5 Watt transmitter is turned on for 440 mS short message or 520 mS long message MUST HMS 4 uk L RATION 455 MA HI LIE THLERARSO REAN FIGURE 1 1 G SWITCH CURVE 06 30 99 PAGE 1 4 ARTEX AIRCRAFT SUPPLIES The information sent to the satellite is programmed at the factory and con tains a unique number that can be used to identify the beacon 1 3 FCC REQUIREMENT The ELT shall maintain a frequency stability of 50 parts per million on 121 5 and 243 0 MHz This allows a variation of plus or minus 6 075 KHz at 121 5 MHz On any frequency removed from the assigned frequency by more than 50 perce
43. he ELT is working properly the se quence following entry to the ARMED OFF condition will result in the panel LED staying illuminated for approximately 1 second then extinguishing DOCUMENT 570 5000 If a problem is detected the LED pro vides a coded signal following the initial 1 second pulse The coded signal and related problem are as follows e a 1 flash in di cates a G switch loop open fail ure b 3 flashes in di cates a 406 025 MHz trans mitter problem i e bad or un con nected coax ca ble an an tenna prob lem low power out put or a pro gram ming error 5 flashes in di cates there is no nav i ga tion data pres ent This is most likely due to im proper wir ing be tween the sys tem interface connections im proper programming invalidnavigationdata or an ELT NAV In ter face unit 453 6500 is not be ing uti lized e d 7 flashes in di cates a bat tery prob lem i e bat tery us age time over an hour There is a sequence assigned to the problem report which is the same order as listed above If the G switch circuit has a failure there will be a single flash If there also is a 406 025 MHz transmit ter problem then after the single flash and a 1 second pause 3 flashes would appear NOTE For installations using the ELT NAV Interface there is an error con dition where the LED on the ELT and re mote switch will flash rapidly This occurs 2 minutes after power is applied to the ELT NAV In
44. his is most likely due to improper wiring between the systeminterfaceconnections im proper programming invalid navigationdata navigation sys tem not pow ered up an ELT NAV In ter face unit 453 6500 is not be ing uti lized d 7 flashes in di cates bat tery prob lem i e battery us age time overan hour There is a sequence to the problem re porting which is the same order as listed above That is if the G switch circuit has a failure there will be a single flash then 3 flashes would appear if there was a transmitter problem and so on NOTE For installations using the ELT NAV Interface there is an error con dition where the LED on the ELT and mote switch will flash rapidly This occurs 2 minutes after power is applied to the ELT NAV Interface if the ELT is not re sponding because either 1 the ELT is programmed for a protocol other than 24 bit and the ELT NAV Interface has been strapped for a 24 bit address or 2 the RS 232 TX line from the ELT pin 12 to the ELT NAV Interface pin 10 is not connected After initial installation Artex recom mends a monthly self test of the ELT by following the steps outlined in this section Testing of the ELT in excess of once a month is not recommended as 12 10 02 PAGE 3 18 ARTEX AIRCRAFT SUPPLIES the battery life will be shortened by ex cessive activations 3 8 Sealing the ELT Con nector Once all tests have satisfactorily been completed
45. ifferent battery pack b if a S TEST BAD or DATA ER ROR message appears there is a prob lem with the ELT i e a programming problem or a problem with the transmitter module or the battery pack c if there is no 406 025 MHz trans mit ter burst present check the 3 0 Amp fuse on the circuit board in the battery pack for an open condition If the fuse is good there is most likely a problem with the 406 025 MHz module or its intercon nections 24 Bit Address Protocol Long Mes sage Refer to Figure 4 3A and 4 3B for the Beacon Test Set display contents of each specific page described below Page 1 is the main menu screen Press V for view to see received message scroll using up and down arrow keys to view other messages Use left and right arrow keys to scroll between pages Page 2 contains the Date and Time that the message was received Also in cluded is an indication of whether the message was received properly Verify that the third or bottom line reads S TEST OK 04 11 01 PAGE 4 9 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 NOTE The example pages shown PAGE 1 MENU OPTIONS represent the long message format with 24 bit protocol Serialized protocol and other possible formats are not shown SARSAT BEACON TESTER Rev View Qut Ense Setup Output PAGE 2 VIEW MODE l lees ED VERIFY MESSAGE Mesg 1 Received At RECEIVED S TEST OK
46. ight immediately begins flashing continuously when the ELT is ac tivated If the light fails to start flashing immediately recheck the interface wiring between the ELT and the cockpit panel switch Brief the operator s of the aircraft on the contents of this ELT Installation and Operation Manual and demonstrate the described tests The manual should be kept either in the aircraft or with the air craft logbooks Make the appropriate logbook entries and fill out and submit FAA Form 337 04 11 01 PAGE 3 16 ARTEX AIRCRAFT SUPPLIES NOTE The TSO approval of the ELT does not constitute installation approval All ELT installations are subject to field approval for a given airframe by either an approved FAA DER or FSDO For instal lations outside of the US contact your lo cal civil aviation authority representative for details WARNING The signer of the FAA Form 337 is re sponsible for the accurate and complete installation of this ELT as defined pre viously Additional information regarding the com pletion of FAA Form 337 can be found in Advisory Circular AC 43 9 1E Para graph h 2 of this advisory circular de fines what is considered to be approved data for major alterations as follows Data used as a basis for approving major repairs or alterations for return to service must be FAA approved prior to its use for that purpose and includes FAR e g airworthiness directives AC s e g AC 43 13 1
47. in utes af ter the hour UTC 4 5 ELT Battery Pack Re placement NOTE The battery pack contains static sensitive parts take ESD precau tions before handling Remove the four screws from the battery pack Before pro ceeding further read the following advi sory to avoid damage to the ELT Also refer to Figure 4 4 WARNING The battery pack is con nected to the ELT via short interconnect harnesses which limit the distance of separation between the two components prior to disconnecting the harnesses Pro ceed as follows e Lay the ELT on its side Care fully lift the bat tery pack away from the ELT and lay along side the ELT unit 04 04 02 PAGE 4 15 ARTEX AIRCRAFT SUPPLIES e Carefullydisconnect the harness from the 8 pin con nec tor on the small cir cuit board in the bat tery pack Do not short connectorpins e Disconnect2 pinharness Inspect the battery pack and underside of ELT Battery cells components and connectors should be corrosion free The underside of ELT should be corrosion free Inspect for any broken wires or con nections Ensure the battery housing is free of cracks or other visible damage The battery pack must be replaced with a new one Afterusein an emergency e Afteraninadvertentactiva tion of un known duration When the to tal of all known trans mis sions ex ceeds one hour On or be fore the bat tery re place ment expiration date Note The bat tery pack 452 013
48. ity to automatically reprogram the ELT with the aircrafts 24 bit identification long message format This facilitates moving the ELT from one aircraft to another when performing routine maintenance etc WARNING the ELT must be re registered and the product label re marked to reflect the new programming and or countrv of registrv Contact ARTEX for details of marking and repro gramming The Interface unit will automaticallv re program the ELT if programmed for 24 bit protocol overwriting previously stored data every time the Interface unit deter mines from the aircraft s switch array en coded with the 24 bit address of the aircraft that the ELT has been replaced The standard choice of programming which ARTEX Aircraft Supplies Inc pro vides is serialized long message protocol col The serialized long message protocol can be used with or without the ELT NAV Interface unit The ELT NAV Inter face unit is required to interface with the aircraft navigation system and enables the ELT to transmit position data The ELT can be used without the ELT NAV Inter face unit however the serialized long message will not have position data in cluded 06 30 99 PAGE D 2 ARTEX AIRCRAFT SUPPLIES Fleet operators may request that the ELT be programmed with 24 bit long message protocol The interface with the aircraft navigation system which allows the ELT to transmit position data is unaffected by this protocol The 24 bit a
49. ivation of the ELT Activate the ELT and allow the ELT to transmit 15 to 30 seconds but not more than 40 seconds The SARSAT Beacon Tester will receive the test message transmitted at turn off If the 406 025 MHz oscillator is not warmed up and sta bilized a BAD FRAME message may occur which could be construed as a problem when in fact the message was generated because the oscillator had not warmed up If a BAD FRAME is re ceived repeat the activation and turn off procedure again For all testing of the 406 MHz output only the test message that is transmitted at turn off is required to verify the ELT and ELT NAV Interface function The test message contains all the information contained in the actual distress message except there is a cial digital test prefix that tells the COSPAS SARSAT satellites to ignore the message Note The initial display on the SARSAT Beacon Test Set can flag several prob DOCUMENT 570 5000 lems prior to advancing into the individual Page displays described later a if a BAD FRAME message appears after the 3rd or 4th transmit attempt the Beacon Test Set is not receiving trans mit data Verify that the SARSAT Beacon Test Set does not have a low battery Check the coax connection between the ELT s TPS connector and the SARSAT Beacon Test Set Check the internal ELT coax connection between the TPS con nector and the 406 025 MHz module Finally try a d
50. ll join with the Molex connector on the cockpit panel switch assembly 06 30 99 PAGE 3 12 ARTEX AIRCRAFT SUPPLIES ELT UNIT CONNECTOR LIGHT RESET 1 RESET 2 EXTERNAL ON S SWITCH 1007 SWITCH LOOP 45 8 VDC FROM ELTINAV INTERFACE GROUND HORN HORN GROUND PININSERTIONVIEWOFMOLEX CONNECTORFORELTUNIT HOLE NUMBERINGISIDENTICALTOTHAT INSCRIBEDONACTUALCONNECTOR ORIENTATIONSHOWNISSAMEAS INSTALLATIONORIENTATION DOCUMENT 570 5000 COCKPIT PANEL SWITCH CONNECTOR NOTE BYPASS THE AIRCRAFT AND AVIONICS MASTER SWITCHES AND CONNECT POWER WIRE DIRECTLY TO BATTERY WITH A 1 AMP FUSE IN LINE OR CONNECT TO AIRCRAFT CLOCK CIRCUITRY MAXIMUM CUR RENT REQUIRED 15 ABOUT LINE MUST BE FUSED APPLY EITHER 14V TO PIN 28V TO PIN 3 BUT NOT BOTH NOTE PINS6 amp 9OFREMOTESWITCH AREINTERNALLYTIED IFAIRCRAFTGROUND INTEGRITYBETWEENTHEELTANDREMOTE SWITCHCANNOTBEGUARANTEED REMOTE SWITCHPINGISWIREDTOELTPIN11 OTHERWISETHECONNECTIONISOPTIONAL PININSERTIONENDOFMOLEX CONNECTORFORCOCKPITSWITCH ASSEMBLY HOLENUMBERINGIS IDENTICALTOTHATINSCRIBEDON ACTUALCONNECTOR ORIENTATION SHOWNISSAMEASINSERTION ORIENTATIONFORINSTALLEDSWITCH FIGURE 3 10 WIRING DIAGRAM 12 10 02 PAGE 3 13 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 CRIM FIN 5 6677 END CAP NOTE TIGHTENTHUMB NOTECONFIGURATION j SCREWSNO OFMOUNTINGTRAY TOP COVERANDENDCAP fer ff
51. load the G force level on the G switch The Delta V switch is required by TSO Cola to be far more sensitive and activate at a sig nificantly lower sustained G force than older TSO C91 ELTs ARTEX has found that in many cases the 45 degree mount ing angle can result in false activation of the ELT depending on the type and se verity of the aircraft maneuvers The same can be true of abrupt takeoffs and landings While the C406 2 may be installed in a helicopter Artex highly recommends use of the C406 2HM for helicopter installa tions These ELT s were especially de signed for rotary aircraft and contain an additional five G Switch module in addition to the primary crash sensor This feature allows for six axes of coverage ARTEX recommends that when installing a C406 series ELT whenever possible the ELT should be mounted parallel with the floor as shown in Figure 3 13 If space constraints do not permit mounting the ELT parallel with the floor the ELT may be tilted forward as much as 25 de grees The direction of flight arrow on the ELT s product label represents the direc tion in which the primary crash sensor is oriented NOTE Installation in a pressurized air craft constitutes a major modification con sult the Department of Transportation Regional Officer before proceeding 12 10 02 PAGE 3 19 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 FIGURE 3 13 ELT HELOCOPTER INSTALLATION 06 30 99 PAGE 3 20 ARTEX A
52. m to their respective con 04 11 01 PAGE 4 12 ARTEX AIRCRAFT SUPPLIES nections on the ELT Position the end cap and connector assembly onto the ELT and tighten the two thumbscrews se curely Visually inspect connections ensur ing that they are seated properly 4 3 16 Step 7 Installed Trans mitter Test Self Test Perform the transmitter tests by activat ing the ELT and listening on 121 5 MHz Be sure to follow the procedures as out lined under Transmitter Test in Section 3 page 3 17 of this manual If your ELT front panel in di ca tor light is wired through eitherthe aircraft mas ter or the avionics mas ter switch make sure these switches are turned on Tune a receiver usu ally the air craft ra dio to 121 5 MHz the ELT air craft panel switch to ON wait for 3 sweeps on the re ceiver which takes about 1 second and then turn the switch back to the ARM OFF positionwhile paying spe cial at tention of the LED activity uponentering the ARM OFF con dition To pass the test you must hear the 3 sweeps AND see the front panel light im mediately begin to flash continuously During the ON to OFF transition the mi croprocessor in the ELT checks the G Switch automatic activation switch latching circuit pins 5 amp 8 on the 12 pin connector at the ELT the 406 025 MHz transmitter for proper RF output that posi tion data is present and a battery check If t
53. me Assy Bottom Mounting 406 Remote Switch Kit Cable Coax BNC BNC 6 Ft Cable Coax TNC TPS 6 Ft Buzzer Installation Kit ELT Install Kit Standard Remote Switch Installation and Operation Manual PART 453 5000 __ 453 5001 L 1 110 333 110 337 110 320 452 0133 452 5052 452 3052 452 5050 345 6196 04 611 6013 04 611 6052 130 4004 455 7421 455 6196 570 5000 06 30 99 PAGE C 2 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 APPENDIX D ELT NAV INTERFACE OPERATION 06 30 99 PAGE D 1 ARTEX AIRCRAFT SUPPLIES D 1 ELT NAV Interface Ca pability ARTEX has enhanced 406 MHz ELT op eration by giving the C406 2 the capability of interfacing with an aircraft navigation system The C406 2 has the ability to receive position data longitude and latitude from the aircrafts on board navigation system The communication process between the ELT and the aircraft navigation system is made possible by installing an ARTEX ELT to NAV ELT NAV Interface unit 453 6500 The Interface unit also allows the ELT to be programmed with the aircraft s 24 bit address When used with ELT s that are programmed for 24 bit protocol the Inter face unit is strapped with the 24 bit ad dress or may be connected to a 24 bit address switch block which is set up to match the 24 bit address parity of the Mode 5 surveillance and communications system switch block Note There is no electronic connection between TCAS or Mode S systems a
54. move Coaxial and Wiring Connections and Inspect STEP 2 Remove ELT and Inspect Mounting STEP Remove ELT Battery Pack and STEP 3b Replace Reinstall Battery STEP 4 Activate Using Football Throw Method Then Reset STEP 5a Activate ELT in Attenuating Container STEP 50 Measure 121 5 4 243 0 MHz Power Output STEP 5c Measure 121 5 MHz ELT STEP 5d Listen to the Audio STEP Measure 406 025 MHz Power STEP 5f Measure 406 025 MHz E 50r Current Draw Tesligu uu u l ERE STEP 5h Verification of Digital STEP SE gt Reset ua imal Reinstall A era STEP 7 Perform Transmitter STEP 8 Perform Antenna sS EP 975 gt Logbook EMY nn tens iin NOTE FAR 91 207 d requires that the ELT be inspected
55. mp 12 5 power supply as power source The test equipment specified in the fol lowing steps is only a recommendation The use of other manufacturer s models of test equipment capable of providing equivalent measurement results is accept able Set the Spectrum Analyzer as follows e Center Freq 121 5MHz e Span 1 MHz e Resolution Band width 1 MHz 04 11 01 PAGE 4 5 ARTEX AIRCRAFT SUPPLIES e Vertical Display 10 dB Div e Sweep Auto Peak Avg Peak e Ref er ence Level 30 dBm e Time Div 20ms Adjust the reference amplitude to place the peak of the carrier slightly above the top graticule line Enable the fine amplitude adjustment Set the carrier peak to exactly the top of the reference line Read the displayed amplitude Repeat for the 243 0 MHz harmonic Change the Center Frequency to 243 0 MHz All other settings remain the same The minimum allowed amplitude on 121 5 MHz and 243 0 MHz is 23 dBm 200 mW 4 3 8 Step 5c 121 5 MHz Fre quency The ELT transmitter frequency may be measured as follows Connect the frequency counter as shown below ELT Frequency BNC Top Counter CONNCTOR If the 121 5 MHz carrier frequency is within specified parameters the 243 0 MHz frequency will also be within speci fied parameters The ELT should be within 50 ppm 6 075KHz of 121 500000 MHz DOCUMENT 570 5000 4 3 9 Step 5d Audio Modula tion During the swept tone
56. n con tained in the database that may be useful in the event of a crash is shown below e Type of Aircraft e Address of Owner e Tele phone Num ber of Owner e AircraftRegis tration Number e Alternate Emergency Contact Once the ELT is activated and the 406 025 MHz signal is detected from the satellite and a position is calcu lated the 121 5 243 0 MHz transmis sions are used to home in on the crash site Because aircraft communi cation radios are not capable of re ceiving 406 025 MHz transmissions the only method of monitoring the ELT is the blinking cockpit light the buzzer or the 121 5 243 0 MHz transmissions which may be monitored on the air craft communication transceiver The switch below the ELT cockpit light allows you to turn the unit on for testing and to reset the unit You can not disarm or disable the unit from the cockpit Cockpit operation is lim ited to deactivating the ELT after it has been activated or manually acti vating the ELT The C406 2 series ELT s are housed in a high impact fire resistant polycarbonate plastic case The ELT unit is able to withstand extremely harsh environments Units exactly like DOCUMENT 570 5000 yours have been subjected to numer ous 500g shock pulses 1000 pound crush weights and severe penetrator tests and continue to operate nor mally Continued operation in a tem perature range of 20 degrees C through 55 degrees C is assured 1 1 1 LINE REPLA
57. nd the ELT NAV Inter face only the ID number is common This feature was implemented in the ELT NAV Interface unit with fleet operators in mind ELT s are programmed with either a seri alized or 24 bit protocol Both will inter face with the ELT NAV Interface to provide position data as part of the 406 025 MHz distress message however only ELT s programmed with 24 bit proto col may be used with the 24 bit address function of the ELT NAV Interface see Section 4 3 16 In the event of a crash the ELT will transmit the converted position information from the navigation system such as the GPS flight management computer loran etc Geostationary satellites constantly DOCUMENT 570 5000 monitor the 406 025 MHz transmissions The crash site is instantly known due to the aircrafts navigation system position data communication with the ELT via the Interface unit Without the position data being transmitted it is necessary for the polar orbiting satellites to pass overhead using Doppler Shift technology to deter mine position In a worst case scenario this could be a 3 to 4 hour wait for a polar orbiting satellite to pass over In ad dition the accuracy of the position fix is much better i e 100 meters versus 1 to 2 kilometers for the standard 406 025 MHz system without interface coupling The Interface unit supports either ARINC 429 or RS 232 data bus formats An ad ditional feature of the Interface unit is the abil
58. nt up to and including 100 per cent of the authorized bandwidth the power is to be attenuated at least 25 dB On any frequency removed from the assigned frequency by more than 100 percent up to and including 250 per cent of authorized bandwidth the power is to be attenuated at least 35 dB On any frequency removed from the assigned frequency by more than 250 percent of the authorized bandwidth the power is to be attenuated at least 40 dB There are no equivalent FCC require ments for the 406 025 MHz frequency 1 4 TSO REQUIREMENTS To gain TSO approval of a 406 025 MHz ELT it is necessary to meet the requirements of TSO C126 The follow ing sections contain descriptions of components necessary to meet TSO C126 with the ARTEX C406 2 series ELT s DOCUMENT 570 5000 1 4 1 ACTIVATION MONITOR An aural and or visual monitor is pro vided to alert the pilot when the ELT has been activated and is transmitting The following requirements apply to the activation monitors a Aural Monitor The aural monitor provides a distinct signal enabling a search and rescue team to locate an aircraft with a transmitting ELT in a confined area with a large number of aircraft i e such as an airport The search and rescue team would listen for the aural monitor and easily locate and disable the offending ELT with out a great deal of effort b Visual Monitor The visual tor is designed to be installed so that it c
59. o its mounting tray it will activate in a crash Neither the cockpit switch nor the ELT unit switch can be positioned to pre vent automatic activation once the unit is mounted properly It also is designed against human error and misuse in regards to automatic acti vation The unit activates only when se cure ly mounted in its tray and has pins 5 amp 8 jumpered The ELT cannot be ac cidently activated by dropping rough han dling or during shipping When the ELT is activated the presence of the emergency swept tone and a flash ing front panel light indicates a normally functioning unit The front panel light must immediately begin to continuously flash upon ELT activation Under normal operation the switch con figuration on your front panel is the down position reading ARM The switch on the ELT unit will also be positioned down to read OFF Should an emergency arise to the degree that you want to manually activate your ELT reverse either switch so it is in the up ON position Remember that as long as the front panel and ELT switches are in the ARM OFF position the ELT will automatically activate on impact If your ELT is activated accidentally you will need to reset it Do this by mov ing the front panel switch to ON then immediately rocking it back to ARM You may also reset the ELT at the unit itself by positioning the switch on the ELT up to ON then immediately back down
60. ormance tested within the 12 month pe riod preceding installation in an aircraft and within 12 month intervals thereafter IS IT REQUIRED Yes For Canadian installations all maintenance shall be per formed in accordance with CAR s Part V Subpart 71 and Part VI Subpart 5 HOW DETAILED The same reference quoted above states five essential tests 1 The measured peak power after 3 minutes of operation 2 The measured frequency after 3 minutes of operation 3 The audio modulation which shall be recognizable as a typical ELT signal 4 The measured current draw in the OFF ARM position and in the ON position as specified by the ELT manu facturer and 5 The automatic activation system 4 3 Periodic Maintenance Inspection Procedure To comply with the above quoted FAA amp Canadian DOT regulations ARTEX Air craft Supplies provides the following main tenance procedures see Figure 4 1 Periodic Maintenance Inspection Check list These procedures include checks which are mandatory in Canada FAR 91 207 d states those inspection checks required in the United States In addition to the maintenance checks described in this chapter a monthly self test of the ELT is recommended Please refer to Section 3 page 3 17 of this manual for more information 04 11 01 PAGE 4 2 AIRCRAFT SUPPLIES DOCUMENT 570 5000 STEPS 5a THROUGH 5i ARE MANDATORY IN CANADA STEP 1 Re
61. ory Circular 43 13 2A Chapter 3 paragraphs 36 through 38 provides ad ditional guidance for antenna installations 3 3 Installing the Mounting Tray Refer to figures 3 2 amp 3 3 Before installing the tray be sure the mounting location meets the requirements established in ELT Mounting Locations NOTE Although the Top Cover also has 4 holes do not use for mounting the ELT Mark the 4 holes needed for the tray using the tray as a guide Be sure the arrow on the tray aligns within 10 de grees of the longitudinal axis of the air craft and in direction of flight Also make sure there is sufficient room in front of the tray to easily remove the front cap at least 5 is recommended 06 30 99 PAGE 3 10 ARTEX AIRCRAFT SUPPLIES If a reinforcement doubler plate is needed to meet the rigidity requirements fabricate one using the tray as a guide Drill the 4 marked holes with the 19 1660 drill bit and install the tray with the 8 32 X 5 8 pan head phillips screws nuts flat washers and lock washers pro vided 34 Installing the Antenna Ensure that the antenna mounting loca tion meets the requirements as described in Antenna Mounting Locations A doubler plate will most likely be nec essary for the antenna to meet rigidity specifications in Antenna Mounting Loca tions A 20 pound force applied in all direc tions should not cause an appreciable distortion in the aircraft skin DOCUMENT 570
62. r in the cockpit is not recommended due to the very distracting loud si ren type sound it produces when the ELT is intentionally or inadvertently activated Since the buzzer operates in tandem with the ELT cockpit switch panel light it would only serve as a redundant warning indicator in the cockpit environment One way of mounting the buzzer is to fabricate a right angle bracket using 092 inch aluminum as shown in figure 3 12 Wire the buzzer to the ELT as shown in the wiring diagram Figure 3 10 Con nect the positive terminal to pin 2 of the ELT connector and the negative terminal to ground 3 7 Transmitter Test 1 Always perform the tests within the first 5 minutes of the hour UTC as re quired by AC 43 13 1B 12 21 amp 12 22 Note 3 Be sure to notify any nearby control tower of your intentions 12 10 02 PAGE 3 17 ARTEX AIRCRAFT SUPPLIES 2 WARNING Do not allow test duration to exceed 5 seconds The ELT will transmit a 406 025 MHz signal after the ELT is ac tive approximately 47 seconds the satel lite system considers the transmission to be a valid distress signal 3 If your ELT front panel indicator light is wired through either the aircraft master or the avionics master switch make sure these switches are turned on NOTE If the ELT is installed with an ELT NAV In terface ensure that both the Interface and the aircrafts navigational system are active at least 30 seconds prior to the EL
63. s installed on the ELT Pin 1 as inscribed on the connector must be in the lower left hand corner as shown in Figures 3 10 and 3 11 3 6 3 Wiring Switch Assembly 9 pin Connector Before inserting the cable pins into the 9 pin connector for the cockpit switch as 06 30 99 PAGE 3 15 ARTEX AIRCRAFT SUPPLIES sembly strip and crimp a female terminal pin to a separate shorter wire for connec tion between pin 9 of the cockpit switch and aircraft ground Strip and crimp a fe male pin to a second wire for connection between aircraft power and the applicable power connection pin 1 or 3 on the cockpit switch connector Insert each of the female pins into the switch 9 pin connector which will connect to the cockpit remote switch as shown in the wiring diagram Figure 3 10 Push the connector into place on the remote switch NOTE Terminal pins may be removed by using Molex extraction tool 11 03 0002 or equivalent 3 6 4 Power and Ground The power source determines when the light functions but has no effect on the switch functions It is preferable to bypass the aircraft and avionics master switches and connect the power wire directly to the battery with a 1 amp in line fuse A better solution is connecting to the aircraft clock circuitry If your ELT front panel indicator light is wired through either the aircraft master or the avionics master switch make sure these switches are turned on during test ing
64. s that may be specific to the GPS FMC Refer to the installation instructions specific to the GPS FMC that you are connecting the ARTEX ELT NAV Interface unit to for spe cific instructions NOTE In order to verify either the 24 bit address mandatory or navigation po sition provided by the ELT NAV Interface that is being transmitted by the ELT the ELT will only need to be active long enough to perform the self test and should not be active for more than 5 sec onds The 406 MHz output should be connected to the hand held test set Artex P N 453 0131 via a coax cable and a 30 dB attenuator For any 406 MHz transmission after the ELT is active 47 5 seconds or more the satellite sys tem considers the transmission to be a valid distress signal The ELT transmits a test signal at turn off which contains the same information as the distress message except that the signal contains a prefix code that identifies it as a test message that will be ignored by the satellite sys tem should it be detected For all testing of the 406 MHz output only the test message that is transmitted at turn off is required to verify the ELT and ELT NAV Interface function Follow the installation instructions pro vided in the ARTEX ELT NAV Interface DOCUMENT 570 5000 Installation and Operation Manual 570 4602 for details regarding the installation of the ELT NAV Interface unit 453 6500 It is extremely important that th
65. t the 2 pin har ness e In stall the test har ness 611 0024 and an in line am teras shown Fig ure 4 2 Ensure the ELT is OFF Measure the current withthe am meter The mea sured cur rent should be 0 microamps uA and not more than 6 uA ON State Current Measure ment NOTE Current draw during this test may exceed 3 5 Amps during the 406 025 MHz burst Ensure the ammeter is set on the appropriate range to ac commodate this level of current e Activate the ELT allowto sta bilize The measured steady state cur rent should not ex ceed 200 milliamps mA When the 406 025 MHz mod ule is on gener ating the 406 025 MHz burst the current may ex ceed 3 5 Amps 12 10 02 PAGE 4 7 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 TEST HARNESS P N 0611 0024 CIRCUIT BOARD IN BATTERY PACK FIGURE 4 2 TEST HARNESS CONNECTION 06 30 99 PAGE 4 8 ARTEX AIRCRAFT SUPPLIES e Turn the ELT OFF Disconnect the test har ness 611 0024 Reconnectthe 2 pin module power har ness Reinstall the bat tery pack as de scribed in Sec tion 4 3 4 4 3 13 Step 5h Verification of Digital Message Set up the equipment as shown below SARSAT Beacon Connector Test Set ELT ac dB min TPS Bottom Attenuator NOTE If checking latitude longitude ensure that the aircrafts navigation sys tem and ELT NAV Interface are connected and powered at least 30 seconds prior to act
66. terface if the ELT is not re sponding because either 1 the ELT is programmed for a protocol other than 24 bit and the ELT NAV Interface has been strapped for a 24 bit address or 2 the RS 232 TX line from the ELT pin 12 to the ELT NAV Interface pin 10 is not connected 04 11 01 PAGE 4 13 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 IF INSTALLING A NEW BAT ERY PACK REFLATE EXPIRA KON LABEL WI H HE EXMRANON LABEL SUPPLIEL WI F THE NEW BAT ERY FAOK PLACE NEW LABEL HE EX ERKOR OF END WHERE ORIGINAL LABLL WAS PLAS OR WI LRE PIRA IKCAL TO PROVDF VI IBH ITY ELT ASSEMBLY NTE Pl 145 IS R CESSFR IN ELI ASSEIVIBLS RTV IDDLE BATTERY PACK A REMOVE I C FAFIR BACKING T IE CASKE I SIRIE APPLY HIN CA INC Or SILICONE GREASE C635 OR NALENT 1 KO CsASKEI PRIOR IC INSTALLATION bo SCREW WITH RING PART NUMBER 2 1 7 0604 4 FIGURE 4 4 ELT BATTERY PACK EXPLODED VIEW 06 30 99 PAGE 4 14 ARTEX AIRCRAFT SUPPLIES 4 3 17 Step 8 Antenna Test Action Notice A 8150 3 advises that A low quality AM broadcast receiver should be used to determine if energy is being transmitted from the antenna When the antenna of the radio tuning dial on any setting is held about 6 inches from the activated ELT antenna the ELT aural tone will be heard on the AM broadcast receiver This is
67. the 15 digit hex code displayed on the bottom line of Page 4 matches the 15 digit hex code printed on the ELT prod uct label If verifying received latitude lon gitude check Page 8 All other information displayed may be disregarded Short Message Programmed ELT s For ELT s that have been programmed for a Short Message protocol verify that S TEST OK is displayed on Page 2 verify on Page 3 that the frequency passes and that the correct country is displayed Verify that the 15 digit hex code displayed on the bottom line of Page 4 matches the 15 digit hex code printed on the ELT product label All other information displayed may be disre garded NOTE Contact your local Artex dealer for availability of Portable SARSAT Bea con Test Sets ARTEX p n 453 0131 or call Artex direct at 1 800 547 8901 4 3 14 Step 5i Reset ELT To RESET the ELT move the switch to the ON position then back to the OFF position 4 3 15 Step 6 Reinstall ELT Reinstall the ELT into aircraft as follows Insert the ELT into the mounting tray at an angle so that the locking ears at the end opposite the direction of flight ar row fit into the mounting tray locking slots Fit the protective top cover onto the ELT Ensure that the slots at the end of cover fit over the locking ears on the ELT prior to fitting cover into place at the connector end Feed the two coax cables through the holes in the end cap and connect the
68. the ELT af ter it has been ac tivated e Result in ad di tional power drain so that the ELT will not meet the min i mum Peak Effective Radiated Power PERP of 17 dBmorEquivalentlso tropic Radiated Power EIRP of 20 dBm through the 50 hour op er ation pe riod at any of the specifiedoperating temperatures 20 C to 55 1 5 ARTEX Dual Input An tennas All of the ARTEX 406 dual element antennas are designed to work with any of the ARTEX Dual output 406 ELT s including the C406 2 and C406 2HM DOCUMENT 570 5000 1 5 1 Rod Antenna Dual Input The 110 320 Rod Antenna refer to Figure 1 2 is intended for lower speed aircraft that do not exceed 350 knots TAS 110 320SPECIFICATIONS Freq 121 5 243 0 amp 406 025 MHz VSWR 2 0 1 Max for 121 5 243 0 MHz 1 5 Max for 406 025 MHz e Polarization Vertical e Radiation Pattern Omnidirectional Airspeed Rating 350 Knots TAS e Connectors BNC amp TNC 1 5 2 Blade Antennas Dual In put The 110 337 Blade Antenna refer to Figure 1 3 is the ARTEX antenna of choice for use on aircraft that do not exceed Mach 1 110 337SPECIFICATIONS e Freq 121 5 243 0 amp 406 025 MHz e VSWR 2 0 1 Max at 121 5 243 0 MHz 1 50 1 Max for 406 025 MHz e Polarization Vertical e Radiation Pattern Omnidirectional Airspeed Rating Mach 1 e Connectors BNC amp TNC The 110 333 Blade Antenna refer to Figure 1 4 is intended for use on air craft that do
69. the unit has exhausted the batterv power which tvpicallv will be at least 72 hours The ELT NAV Interface unit allows the ELT to communicate with the air craft s navigation system and receive position data longitude and latitude which the ELT will transmit in the event of a crash Programming the ELT with the 24 bit long message protocol allows the ELT to be auto matically programmed by the ELT NAV Interface with the aircraft s 24 bit ad dress The ELT NAV Interface unit must be strapped binary 1 bits tied to ground with the same 24 bit ad dress as the ICAO or Mode S transponder system 24 bit address This gives the ELT the ability to be moved from one aircraft to another without the need for manual gramming of the ELT This is advanta geous for fleet operators since the ELT NAV Interface unit will automati cally reprogram the ELT with the new aircraft s 24 bit address identifica tion One advantage of the 406 025 MHz transmitter is that it will produce a much more accurate position typically 1 to 2 kilometers as compared to 15 to 20 kilometers for 121 5 243 0 MHz 04 11 01 PAGE 1 2 ARTEX AIRCRAFT SUPPLIES transmitters When coupled with the aircrafts navigation system the position accuracy improves to approximately 100 meters The ELT also transmits a digital message which allows the search and rescue authorities to con tact the owner operator of the aircraft through a database Informatio
70. tion DOCUMENT 570 5000 of the ELT is somewhat unique it re quires experience in sheet metal work and avionics Only licensed techni cians should install the ELT Many problems associated with the older ELTs were due to poor installa tions Many of those poor installa tions occurred at the factory on new airplanes Therefore duplicat ing a previous ELT installation with the ARTEX ELT may not be accept able In addition to the procedures outlined herein the installer must adhere to the guidelines established in FAA Advisory Circular 43 13 2A Ac ceptable Methods Techniques and Practices Aircraft Alterations Spe cifically Chapters 1 through 3 11 and 13 By signing either the aircraft logbooks or the FAA Form 337 you are stat ing that the installation has been per formed in accordance with the current FARs and with the steps and proce dures outlined herein 2 EMERGENCY USE ONLY gt TEST RESET PRESS ON WAIT 1 SECOND FIGURE 3 1 ELT AND RE MOTE SWITCH PANEL 06 30 99 PAGE 3 2 SUPPLIES In Canada all installations must performed in accordance with Cana dian Aviation Regulations CAR Part V Subparts 37 51 and 71 ELT Mounting Lo cations Many original ELT installations are in adequate as far as unit location and surface rigidity are concerned Just because the old ELT was located in a particular position doesn t mean the new
71. to OFF DOCUMENT 570 5000 2 2 Overall Functions Figure 2 1 shows the functional flow for the ELT The ELT unit is considered to be either ACTIVE or INACTIVE When INACTIVE the unit lies in a state of rest and performs no functions Taking the unit from the INACTIVE to the AC TIVE state requires a positive switch transition from one of three sources e Panel Mounted Switch e Unit Mounted Switch e G switch Upon entering the ACTIVE state the unit shall meet all the requirements as described herein To exit the ACTIVE state and enter the INACTIVE state a RESET condition must be entered This may be accomplished in one of two ways a The front panel switch may be tog gled from the ARMED RESET position to ON and then back to ARMED RE SET or if the switch is already in the ON position it must be placed into the ARMED RESET position b The ELT unit switch may be moved from the OFF position to the ON post tion and then back to the OFF position If the switch is already in the ON post tion it must be placed into the OFF position lt should be remembered that the ELT can not be RESET if either the panel mounted switch or the unit switch is in the ON position The periodicity of operational checks is at the operator s discretion however a monthly test is recommended The check sh
72. to register and obtain information on how to register 406 MHz ELT s in the United States DOCUMENT 570 5000 NOAA NESDIS SARSAT Operations Division Code E SP3 Federal Building 4 Washington DC 20233 Following this page B 2 you will find a registration form 570 1023 that can be used to register your 406 MHz ELT or to transfer ownership within the United States For Canadian Installations the ELT must be registered with the Canadian Beacon Registry of the National Search and Res cue Secretariat 275 Slater Street 4th floor Ottawa Ontario K1A 0K2 Telephone 613 996 1505 or 800 727 9414 Fax 613 996 3746 WARNING If the ELT is moved to a different aircraft than which it was origi nallv registered with the ELT must be re registered and the product label re marked to indicate the new program ming and or new countrv of registrv If the 406 025 MHz ELT is to be used in a countrv other than the United States the Civil Aviation Authoritv in the applica ble countrv must be contacted to obtain the correct registration form 04 11 01 PAGE B 2 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 APPENDIX C SYSTEM COMPONENT PART NUMBERS 06 30 99 PAGE C 1 ARTEX AIRCRAFT SUPPLIES DOCUMENT 570 5000 C 1 SYSTEM 8 SUB COMPONENT PART NUMBERS The C406 2 series ELT s are available in four basic versions The C406 2 with Rod Antenna The C406 2 with Blade Antenna The C406 2HM with Rod Antenna 455 5010
73. tructive to the mounting hardware and ELT housing causing cracking fracturing and breakage 4 3 3 Step 3a Remove Bat tery Pack NOTE The battery pack contains static sensitive parts take ESD precau DOCUMENT 570 5000 tions before handling Remove the four screws from the battery pack Before pro ceeding further read the following advi sory to avoid damage to the ELT For detailed instructions refer to Section 4 5 and Figure 4 4 WARNING The battery pack is con nected to the ELT via short interconnect harnesses which limit the distance of separation between the two components prior to disconnecting the harnesses Pro ceed as follows e Lay the ELT its side Care fully lift the bat tery pack away from the ELT and lay along side the ELT unit e Care fully dis connect the harness from the 8 pin con nec tor on the small cir cuit board in the bat tery pack Do not short connector pins e Dis con nect 2 pin har ness from the ELT body Inspect the battery pack and the under side of the ELT The battery cells com ponents and connectors should be free of corrosion The underside of the ELT should be corrosion free Inspect for any broken wires or connections Ensure the battery housing is free of cracks or other visible damage Verify the battery expiration date If the battery pack has not expired it may be reinstalled However for optimum perfor mance it is recommended that the bat tery be repl
74. try code is the same as the aircraft s home base Page 4 contains the complete message in Hexadecimal notation The third line is an ID string that is unique to the beacon being tested Verify that ID string on the third line matches the ID printed on the product label of the 406 ELT NOTE For ELT s installed with an ELT NAV Interface where the Interface is used to encode the 24 bit aircraft address the ELT will be automatically re programmed by the Inter face and will need to be re labeled with the new 15 digit hex ID string Page 5 describes the protocol type the type of beacon and the aircraft ID or unit serial number Verify that the aircraft D matches the 24 bit address of the aircraft you will need to convert the aircrafts Oc tal code to Hex Page 6 contains information on the hom ing transmitter and error checking Page 7 contains information confirming that the long message position data is present Page 8 contains the position data as re ceived from the navigation system Verify that the position data is present for lati tude and longitude if using ELT NAV In terface Page 9 is the main menu screen which is reached by pressing Q Serialized Protocol Long Message For ELT s that are programmed with se rialized protocol verify that S TEST DOCUMENT 570 5000 is displayed on Page 2 verify on Page 3 that the frequency passes and that the correct country is displayed Verify that
75. unting tray with the connector in place Because of the potential physi cal damage which could occur through an improper jumper it is recommended that this step be performed only by an experienced technician mechanic See Installation section of this manual for pin layout diagram A test plug may be obtained from ARTEX p n 151 2012 to use in performing this test While monitoring 121 5 MHz on an AM receiver and with the unit switch in the DOCUMENT 570 5000 OFF down position activate the ELT by using a rapid forward throwing mo tion in the direction of the arrow fol lowed by a rapid reversing action Verify activation via the aural swept tone on the receiver Following activation RESET the unit by toggling the ON OFF switch to ON then back to OFF 4 3 6 Step 5a Electrical Check Activate the ELT As the unit will be on for three minutes it is recommended that it be placed in a container capable of substantially attenuating RF signals Re member that all tests must be performed within the first five minutes after the hour UTC Universal Coordinated Time Mont tor the following performance criteria for three minutes power output must be made at the end of the three minute pe riod 4 3 7 Step 5b 121 5 243 MHz Power Output Connect the equipment as shown below ELT SPECTRUM BNC Top ANALYZER CONNECTOR Note use a fresh battery pack 12 5 volts nominal or a 4 a
76. within 12 calendar months after the last inspection for 1 Proper installation 2 Battery corrosion 3 Operation of controls and crash sensor 4 The presence of a sufficient signal radiated from its antenna See 4 3 17 Step 8 Antenna Test FIGURE 4 1 PERIODIC MAINTENANCE CHECKLIST 06 30 99 PAGE 4 3 ARTEX AIRCRAFT SUPPLIES Note the step numbers i e Step 1 Step 2 etc which follow correspond to those listed in Figure 4 1 4 3 1 Step 1 Remove ELT Connections Loosen the thumbscrews on the end cap Pull the end cap away from the ELT Lift up the Protective Top Cover and push away from the connector end of the ELT to remove Lay Protective Top Cover aside Remove all interconnec tions to the ELT unit and ELT antenna Visually inspect and confirm proper seat ing of all connector pins Special atten tion should be given to coaxial center conductor pins which are prone to retract ing into the connector housing 43 2 Step 2 Remove ELT Lift the ELT up from the connector end careful use of a flat blade screw driver as a lever makes this step easier to re move the ELT unit from its mounting tray Inspect the mounting hardware Ensure the hardware is free of cracks or other obvious damage All required mounting hardware should be installed and secured and must meet the integrity requirements as defined herein CAUTION Do not usecontact cleaner on ELT components Such chemical agents can be highly des
77. wn below ELT lt TPS Bottom pplicable Counter Connector Attenuator 7 Verify an initial frequency of 406 025 MHz 2 KHz NOTE Allow the unit to run 30 seconds before making the measurement to allow the oscillator to stabilize 4 3 12 Tests Step 5g Current Draw CAUTION The following tests involve measurements of the lithium battery pack Exercise extreme caution to avoid causing a short circuit condition which will blow the fuses on the battery pack It is rec ommended that only an experienced tech nician perform these tests A test harness p n 611 0024 may be ordered from ARTEX Aircraft Supplies at 1 800 547 8901 All tests must be performed in an RF screen room or with the ELT in a shield ed container that will substantially attenuate the RF signal DOCUMENT 570 5000 All ON state current measurements must be made with the RF outputs load ed with 50 ohms rated for 5 Watts either a resistive load or equipment with 50 ohm impedance padded with 10 dB 5 Watt attenuator i e a spectrum analyzer NOTE The ELT may activate turn ON when the various connections are initially made during the following current tests This is normal Reset the unit to OFF if this happens by toggling the ON OFF switch to ON and back to OFF ARM OFF State Current Measurement Remove the bat tery pack as de scribed in Sec tion 4 3 3 Dis connec

COBHAM C406-2 SERIES Specifications

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