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- Ameri-King Corporation

1. _____ E e EF New Annex Il EASA list Issue 10 25 Feb 2008 Page 1 of 7 Table 3 Sailplanes and Powered Sailplanes EU and non EU 5 of Aviation force lt lt and Comments bL Ee ___ 1947 State of Design Evaluation against Annex II criteria L 0 engnaly caudron Aa OOOO Ol Mq eee rrr Amsteur buit i Amateurbuir ommatzsch Anco c qo p c ee cm ie ehrmeijste 61 Favorit 2 10 Amateur built ________ 56 38 14 Amateur built ging im N E a e A e gt _ Ahrens ves ves i87 Amateur bulk ____ ___ __ es OO o Amateur buit _____ _____ ____ ____ 6 New Annex list Issue 10 25 Feb 2008 Page 2 of 7 193 194 Table 3 Sailplanes and Powered Sailplanes EU and non EU State of Design Of Aviation force lt lt and Comments Grunau Baby II b es cs es 10 Libelle Condor Iv 2 e HKS 1 Dui eS __ HKS 3 Ves ES 200 Experimental _ KSB KM 46 LL L IHFs mus res experimental
2. 103 Supplemental Inspection Procedure FAR Part 91 HT 4 2 3 Beport Al arin eco dotati eda tuse bd n eon pao usb UU Es 103 4 2 4 To report false alarms in the United States contact any of the 103 Excerpt from FAA AC 91 44A Paragraph 8 a which defines when Battery Replacement may be done under FAR 43 3 h as Preventive Maintenance 123 APPENDIX E WARRANTY AND SERVICE FAA Advisory Circular AC 13 2B Section 37 2 0000000 5 124 5 1 E E 104 222 te Lo 105 5 3 Factory Comprehensive Test 0 22222 2 105 APPENDIX F Registering a 406 MHz Beacon for 5 APPENDIX G International 406 MHz Beacon Registration Database IBRD Countries Allowing Individual Registration eene APPENDIX H ELT Coding Programming ID Reader and Maintenance Test P N 5 451 APPENDIX I RTCA DO 160D Environmental Qualification Forms eese APPENDIX J Approval FAA TSO C 126 C 91a Equipment Approval dated 07 24 2008 Approval EASA ETSO 2C 126 2C 91a EASA IM 210 1102 dated 20 2008 C Approval Transport Canada dated 1 1 26 2008 Approval Indust
3. 2 00 35 22221 Whip Antenna Installation 35 2 22 2 Rod Antenna Installation 40 2 2 2 2 3 Blade Antenna Installation 43 2222222 Integral Antenna Installation 46 2 9 2 4 2293 2 6 3 1 222 3 3 3 4 2 23 ELT remote unit location and installation 48 2 2 4 Wiring interconnecting harness 51 225 Audible Monitor Location and Installation 54 2 2 6 Wiring cable Installation eeeeeeeeeeeeeeese 55 Electtical In niei eu 55 Post installaHon de SE ao nl mtb NA 55 Battery installation and replacement sss 68 2 51 ELT main unit battery installation amp replacement 68 245 2 ELT remote unit battery installation amp replacement 71 FAA FOMM rr 72 SECTION III OPERATION Gencal 73 ODE 2 74 Transmitter T uncdonal Pest 2 74 3 3 0 Quick Operation Check eie pre 75 3 3 1 Main Switch ON OFF ARM 76 3 3 2 Transmitter ID Programming and Self Test 76 3 3 3 System Integration
4. diuM 05 Bury ueuy Figure 9 Integral Portable whip Antenna 451017 45 Antenna ground plane is not required JW Im e sl LUNA a i E NOISIA GIA 20 DZD 9 Oso 5 Qa mcm c3 3052727 5 O n ze C gt D D 3538 co Jr cr 70 D e zs 3 8a 5 lt gt OG OcrocroOza ed ee Ce Cx 5 45H39 co Ee 3 cos E woo a c LL amp lt oa gt TO dT C3 o 0000120 3U q JO 9 06 9ue d jejuozuoy euj ZHIN 820 90 Aouanbar4 ZH O Cpz pue Sz seiuenbeJ VAI 2 2 3 ELT REMOTE UNIT LOCATION AND INSTALLATION The ELT Remote Unit assembly must be mounted in the cockpit where the pilot can easily reach the switches and see the light Note The Remote Switch Unit 1s required by TSO C126 TSO C91a for AK 451 AF AP Configurations It is not optional It is strongly recommended that the Remote Unit be located in an area that is part of the pilots norm
5. rc 14 1 2 WT auo 14 P MEDI 6 ccc 14 1 2 2 Application and Equipment 22 222 17 18 18 1 2 4 1 User Location Protocols Long Message 18 1 2 4 2 Standard Location Protocols Long Message 19 1 2 4 3 National Location Protocols Long 19 1 2 4 4 User non location Protocols Short Message 19 1 3 Technical 19 1 4 Accessories SUDDIIGQ 24 LAL 55 vis 24 1 5 Li6euse fequitetilefibz sona tute ace 24 SECTION II INSTALLATION AND TEST 24 Unpacking and inspecting equipment 00 25 2 2 Mechanical rastallatiolt teas 29 2 2 ELT main unit location and installation 26 2 24 41 ELT Location 0 4 002 000 26 2 2 1 2 Mounting tray and Velcro Holder installation 29 2 2 2 Antenna location and 2 33 2224 Antenna location 33 22 2 2
6. Position Data Auxiliary Position Data County 0011 Aircraft to 15 min EP n Radiolocating to 4 sec Resolution Device Resolution Standard es coding ELTs with Type Approval Number and a Serial Number es Location ELT Protocols Bit Serial Position Data Auxiliary Position Data CI 0100 e Number to 15 min rm a 1101 to 4 sec Resolution Device Resolution Location Protocols Standard um ELTs with EE da and a Serial Number m ha ada 40 55 m 64 65 110 Air Op Serial Position Data Auxiliary Position Data 02101 Desig Number 1015 min Tm m 22818 Radiolocating Radiolocating diolcatin to 4 sec nator Resolution Device Resolution National E Location Protocols Bit and Country 1000 Identification Data 21 Bit Data Data Aux Position Data National 12 Bit Frame 1 Code Data to 2 min BCH 110 Flag Source Radioc 04 Use BCH Synch EL Device Resolution http www cospas sarsat org BeaconsTutorial tutorial map htm 139 3 ELT Maintenance Self Test To perform ELT Maintenance Self Test Use command 05 451 HyperTerminal File Edit View Call Transfer Help gt 05 self test mode VHF PLL locked VHF power output level PLL locked power output level Internal 3V3 Internal SY VHF Internal 7 3 406 Internal LDO status Battery Level EEPROM Distress ID EEPROM
7. 2 RF output power ELT shuts down completely Note The self test mode that transmits a 406 MHz test code pulse monitors certain system functions before returning to the ARM mode The 406 MHz test pulse 15 ignored by any satellite that receives the signal but the ELT uses this output to check output power and correct frequency e Self test is 520 ms long message burst on the 406 MHz signal Synchronization pattern 15 011 010 000 e Self test is then 121 243 MHz VHF Continuous Wave during 15 e During Self Test ELT swept Tone must be silent on the 121 5 MHz VHF Radio If No Antenna or No coaxial cable connected the ELT may or may not 5 flashes 2 4 5 ELT Self Test Schedule We recommend that the ELT be tested every month Follow the steps outlined above Total allowable test is 60 minutes as determined by FAR 91 207 and RTCA DO 204 After this time has been accumulated a 3 flash error may be presented after the self test The battery must be replaced at this point for the ELT to remain in compliance Always follow ELT testing requirements per local or national authorities 59 2 4 6 GPS Position Test If GPS is connected for using TS 451 Computer Test Set or equivalent Note Per FCC Regulation this test should be conducted inside a RF shielded room or an ELT RF shielded box Dummy 50 ohm Load should be used e Connect the AK 451 with ELT Computer Test Set TS 451 e Turn the switch of the ELT to ON p
8. 93 Figure 2 3 Dimensional Drawing for Mounting Tray for ELT Main Unit with Optional Multi axes Acceleration 107 3 5 Periodic Maintenance Instructions for Continued Airworthiness Figure 14 1e Wiring diagram for 451 with Optional Multi axes G switch tor Canadian inu mi se 94 with 4 wire interconnecting ELT Main Unit and Remote switch unit 108 3 5 Regular Periodic Maintenance 95 Figure 14 1f Wiring diagram for AK 451 with Optional Multi axes G switch 3 5 2 Power output test Performance Testing 95 with 2 wire interconnecting ELT Main Unit and Remote switch unit 109 3 5 3 Frequency Test Current Draw Test Performance Testing 97 Figure 14 16 Wiring diagram for retrofitting 451 with Optional 3 5 4 Audio Modulation Performance Testing 99 Multi axes G switch with 4 wire interconnecting ELT Main Unit 3 5 5 Transmitter Functional 99 and Remote switch unit Artex Pointer Kannad ACK Tech etc 110 3 5 6 Performance Test Marking and Log Book Entry 99 Figure 14 1h Wiring diagram for retrofitting AK 451 with Optional 3 5 7 DIIDDIDIS es ee en A UM E 99 Multi axes G switch with 2 wire interconnecting ELT Main Unit and Remote switch unit D amp M Narco Joliet etc
9. Connected 0 00 10 Auto detect 9600 8 N 1 SCROLL caes NUM Capture Print echo Figure 1 Note If you don t see the window above you may try the other USB port 2 2 Set the ELT main switch to position 2 3 Verify the LED ON light illuminates for 4 seconds 2 4 Atthe gt prompt type cn Password command then press Enter to go to main menu Must type this command within next 20 seconds after the command prompt appears Note 1 Please contact Ameri King for Password via Email or fax or call 133 Note 2 If there is no programming command input in this time window the ELT will enter the Self Test mode and you cannot program the ELT In this case set the ELT switch to position and start again from step 2 2 451 HyperTerminal J x File Edit wiew Call Transfer Help 212 AMERI KING AK V1 xx serial mode gt Password Must be typed in within 20 seconds connected 01 this menu 02 disconnect 03 read ID 04 read SN 05 selftest 06 write ID 19 read SEL
10. ne 2 S gE A c S 9 G y zz Ur D o 9 2 i 8 D 9 D 5 48s D E S E aa D S w on gt gt SN un D e 3 L om c _ gt ce Qua S wes S tg ip ue e d 26 amp 5 08 a Fos r 10 00 MAX Th Li configurations for composite aircraft because the Antenna ground plane is not The AK 451 AP with Integral Antenna and AK 451 S are the best ELT required Antenna specifications 451017 3A 1 Main Frequency 406 028 MHz 2 Homing Frequencies 121 5 and 243 0 MHz Power Output 25 Watts Mating Connector BNC Female Polarization e 121 5 MHz and 243 0 MHz Vertical 7 18 06 5 60 MAX Radiation Pattern 121 5 MHz and 243 0 MHz Omni directional BNC SERIES CONNECTOR PER MIL C 39012 in the horizontal plane e 406 028 MHz Hemispherical 014 Impedance 50 Ohms Nominal 218 x 016 DIA Elevation 5 to 60 CSK 391 DIA x 100 N6 PLACES Gain Vertical Plane Between 3dBi and 4dBi over 90 of the region bounded by the elevation angle 59 to 60 P ptus go M 7 1125 10 Gain Variation Azimuth lt 3 dB Figure 8 Blade Antenna 451017 3A 46 45 6 aunbi4
11. Kranich _________ __ ______ ____ o _____________ _ e Heini Ditmar ____ Loves _ SSS Herbert Gomolzig ves iso permen ing A Vogt _ __ _______ ________ ______ 17 ________ in ________ sc Wolfenbittel res 103 Amsteur butt Tres 1193 Amsteur buitt z en Rudolf Kaiser 1_______ _ __ _ dmund Schneider a Bitz B Schmetz gi lt ichtel amp Sachs Flugzeugbau K hler ocke Wulf Neihe SO en i per e EVEN RI 2 1 lt a 72 213 m no a i D ui New Annex Il EASA list Issue 10 25 Feb 2008 Page 3 of 7 Table 3 Sailplanes and Powered Sailplanes EU and non EU anufacturer Evaluation against Annex II criteria rm See of Aviation force lt Comments 13 E 04 2 ___ ____ _____ 289 Amateur built F 27 M A __ Lc 78 Experimental pecht ULL chempp Hirth 93 Minimoa 5 _____ ______ ves des E49 llis riz D u UJ D D u D UJ D b b D lt BA gt er m T er N Io c er er D pa ny
12. Series 150 250 400 420 430 500 520 530 HONEYWELL BENDIX KING INC KLN 88 KLN89 KLN89B KLN 90 KLN90B KLN94 KLN900 ARNAV SYSTEMS INC e R50 R501 STAR 5000 FMS 5000 MFD Multi Functional Display 91 MORROW FLYBUDDY 2001 NMS TRIMBLE NAV INC 1000 NAV 2000 TNL 2100 and TNL3100 The following Trimble systems all require a RS 422 to RS 232 adapter NAV 3000 TNL 1000 TNL 2000 TNL 2000A TNL 3000 2000 APPROACH 2000 APPROACH PLUS 2101 APPROACH 2101 APPROACH PLUS 2101 I O APPROACH 2101 I O APPROACH PLUS For other equipment models contact that equipment manufacturer to determine if their equipment supports the Aviation RS 232 format specified above 3 4 10 3 ELT FMC Interface and Checkout Process All installation processes and interconnections to navigation systems should adhere to the guidelines set forth in the FAA Advisory Circulars 43 13 2B 20 130A and 20 138 or later revisions of these documents It 1s very important that the Global Positioning System Flight Management Computer GPS FMC manufacturer s installation instructions be consulted regarding installation details that may be specific to the GPS FMC Refer to the installation instructions specific to the GPS FMC that you are connecting the ELT for specific instructions For all testing of the 406 MHz output only the test message that is transmitted at turn off 1s required to verify the ELT and ELT GPS Interface func
13. 1490 TL samarren ___ __ CCSstCS ____ __________ ____ __ _______ CS5 13 ies 1 New Annex Il EASA list Issue 10 25 Feb 2008 Page 10 of 19 Table 1 EU states of Design powered aircraft fixed wing Historic Development Role in armed Design Production State of Design TC event of Aviation 1 1 55 lt 1 1 75 and Comments Jungmann T 131 PA Jakowlew Yakovlev udi ELE PZL PZL 130 Orlik and An 2 all PZL built Yes but see BB 035 3 1 variants BB 176 1 Note production continued until RWD SR replica WSK Mielec PZL 1 Ee Aerostar Yak 52 including Yes DOSAAF No Tailwheel variants tailwheel variants and aircraft that have not served in DOSAAF are included New Annex list Issue 10 25 Feb 2008 Page 11 of 19 173 174 Table 1 EU states of Design powered aircraft fixed wing Historic Design Production State of Design TC event 1 1 55 lt 1 1 75 and Comments UU Jess Bucuresti IAR 823 po ci LLL ALI Aerodifusion SL Jodel CEA 011905 Treated as per French D1190 Hispano CASA HA 1 109 series _ _ L d _ CASA 101 Yes No TC military ILL Lo le SENE cuiii di 1 115 E New Annex Il EASA list I
14. 2 2 0 2 2 111 Figure 14 2c Wiring diagram for AK 451 with GPS Position and SECTION IV 3 inch T adapter with optional multi axes G switch with REGISTRATION AND RESPONSIBLE USE 4 wire interconnecting ELT Main Unit and remote switch unit 112 Figure 14 24 Wiring diagram for AK 451 with GPS Position and 4 1 Uses Meta LL P M Re D LEN D 100 3 inch T adapter with optional multi axes G switch with 2 wire interconnecting ELT Main Unit and remote switch unit 113 4 1 1 100 4 12 TCOISICE 100 APPENDIX 4 1 3 Registration in the United 2 100 4 1 4 Registration 101 Jick esum Dm ULM i E i 114 4 1 5 Registration outside of the United States and Canada 101 4 1 6 Change of ownership or contact information 101 APPENDIX B 4 1 7 do usu eco coe QU 102 4 1 8 SITO 5 ES MRNA ORA AA 102 Periodic Maintenance Check List with Compliance Cross References 115 4 2 102 AFPENDIX C 4 2 1 Respons c aE EOE 102 1 A recommended 4 2 2 Preventing false
15. M serial mode gt kkkkk connected 01 this menu 02 disconnect 03 read ID 04 read SN 05 selftest 06 write ID gt 06 30 97142CC1637FDFF9996CF583E8FRR8 success gt 19 read SEL VHF 20 SEL VHF Connected 0 00 58 Auto detect 9600 8 N 1 SCROLL CAPS Capture Print echo Figure 5 136 Table 1 List of all available Protocols Serial User Protocol coding ELTs with the beacon serial number User Location Protocol coding ELTs with the beacon serial number 5 epe eerie 83 S Cert Bit and i Auxiliary Emerg Code Frame Radiolocating or National Synch Device Use Bit and Auxiliary Position Frame 1 1 Radiolocating Data Synch Toda Device Sbetator uruni ELT User 3 letter Number 07 adiolocating or Nationa Code Natuse Device Lodel Use Location Location Protocols Protocols ELT Non Location Protocols Auxiliary Aircraft Radiolocating Device Position Position Add ELT 5 Cert Cert Auxiliary Emerg Code or Radiolocating or National Mat use Device TS Aircraft Auxiliary Country 5 Code 101 Registration Radiolocating Marking 42 bits Device un Auxiliary m Emery Code Registration Radiolocating Pads or National Marking 42 bits Device Ez Use 137 138 Standard Location Protocol coding ELTs with 24 bit Aircraft Address 85 86 106 107
16. ELT with Aircraft 24 bit Address Yes National Location PLB Ves PLB with Serial Number 2 Yes PLB with Serial Number 7 Yes National Short Format Mewage Yes National Long Format Message NOTES U applicable only to models AK 451 AF and 45 2 applicable only to models AK 451 S and AK 451 PLB applicable only to model AK 451 PLB 216 217 International Satellite System for Search and Rescue Systeme intemational de satellites pour les recherches et le sauvetage amp SARSAT COSPAS C307 268 F510 Ameri King Corp 16 October 2007 Mr Keith Van Ameri King Corporation 17881 Sampson Lane Huntingtom Beach 92646 USA Dear Mr Van Subject Cospas Sarsat Type Approval Certificate No 179 English I have pleasure of informing you that the subject Cospas Sarsat Beacon Models AK 451 AF AK 451 AP AK 451 S and AK 451 PLB have now been Cospas Sarsat Type Approved In this respect please find enclosed the original Cospas Sarsat Type Approval Certificate No 179 for the above model in English together with three certified copies and copies of the beacon model report that 15 published to the Cospas Sarsat website Please let us know if you wish to receive the French and Russian versions of this certificate The Secretariat remains at your disposal for any further assistance you may require
17. French Russ an International Satellite System For Search and Rescue SARSAT 5 Status Beacons Documentation 97142CC16321EEC2054CF50B0021E9 15 Hexadecimal ID 22 Hexadecimal amp 30 Hexadecimal Description Management 406 MHz Decode Program Version 3 1 Click here for the ITU List of MID Country Code Numbers ITEM BITS VALUE Message format long format 25 1 Protocol Location Protocol 26 0 Country code 369 Type of location protocol Standard Location ELT Serial Cospas Sarsat 179 27 36 0101110001 37 40 0100 41 50 10010110011 Serial Number 355 Latitude Sign North 51 64 00000101100011 65 0 Latitude Degrees 33 Latitude Minutes 45 66 72 0100001 73 74 11 Longitude Sign West 75 1 connected Longitude Degrees 118 76 83 01110110 Longitude Minutes 0 84 85 00 01 this menu 02 disconnect 03 read ID 04 read SN BCH 1 Encoded 86 106 010000001010100110011 Fixed bits 1101 Pass 107 110 1101 gt 06 30 ad bits SPA 3 3 3 J 3 3 3 JE 3 3 3 JE JE JE JE 3 JE JE JE JE 3 JE 3 JE 3 JE JE JE 3 JE JE JE JE 3 JE Position Data Enc x e Position Data Source 111 0 OMERT KING AK 1 xx x From External Navigation Device Aux Device 12
18. New Annex Il EASA list Issue 10 25 Feb 2008 Page 1 of 19 164 Table 1 EU states of Design powered aircraft fixed wing Historic Development Role in armed Design Production State of Design TC event of Aviation 1 1 55 lt 1 1 75 and Comments Yakovlev et Ves ____ Yes Zlin Moravan Z 131 C 104A Yes B 131 C6 106 and Zlin Yes 391 80181 2271 J Ye Ye e E 5 5 2 lt 1 52 4 2 12 ____ ____ _____ _____ 5 ______ _________________ Denmark D Sd s 4 65 ______ _ ________ DLL lt lt D lt D 5 5 ee for mss P lw 70 Vinka 90 TP Prototype 4 gt lt D T tu 212 E os Sa amp D b D o mn r p es fe 52 _____ _ 5555 Yes Yes 101 could be an error Model 110 is not Annex II oma 1 Is ap ECE S e I5 b a ct rt tu et 7 n3 0 9 e i o u New Annex list Issue 10 25 Feb 2008 Page 2 of 19 Table 1 EU states of Design powered aircraft fixed wing State of Design Evaluation against Annex II criteria Design Production State of Design TC 1 1 55 1 1 75 Comments _____ ____ ____ _ 512
19. m b o Korea l MEN 2 21 52227 lt b o Page 17 of 19 179 180 Table 1 EU states of Design powered aircraft fixed wing event 43213299 73 and Comments _______ Cygnet _____ pes fs __________ emini 1 19 12 lagister Mes ves 7 lessenger WII z gt 21 0 D D tu n b Do gE gt 5 5 2 Nipper Aircraft Ltd Slingsby 66 Nipper NAC 996 a RR DN Development prototypes Ves ves e __ E eee O Provost T 1 Yes Yes Yes piston Jet provost all Yes Yes Yes variants ____ ls _ 22222222 ____________ pL OL e v pL LL 40 Prentice roctor series Vega Gull ercival o 0 Q New Annex list Issue 10 25 Feb 2008 Page 18 of 19 181 Table 1 EU states of Design powered aircraft fixed wing Historic Design Production State of Design TC event 1 1 55 1 1 75 and Comments HEN Yes Yes Yes Including Slingsby built replicas ves ves D D D c Royal Aircraft Factory WI lt win Pioneer ulldog cottish Aviation omers Kendall opwith 0 0 lt D WWI NWI WWI NWII WII lt D up Dove iplane itfire all mar
20. 406 028 MHz 35 34 to 38 18 dBm 406 028 MHz RF Power 20 Equivalent Isotropic 100mW IO0dBW 121 5 243 0 min Radiated Power EIRP Emission Designator 6dBW AdB 406 028 MHz max 16K0GID for 406 028 MHz 3K20A3X for 121 5 MHz e BATTERY REQUIREMENTS Transmitter Main Unit Battery Pack consists of 4 cells LiMnO LiSO D Size Remote Unit DURACELL DL 1 3 NB or Equiv Lithium Cell AUTOMATIC CRASH ACTIVATION Velocity Change of 2 3 0 3 4 5 0 5 FPS per TSO C 126 DO 204A and ETSO 2C126 EUROCAE ED 62 requirement ANTENNA RADIATION CHARACTERISTICS Radiation on 121 5 243 0 MHz and 406 028 MHz Vertically polarized amp Omni directional in the Horizontal Plane e CRASHWORTHINESS 100g 23 ms 6 directions ACTIVATION MONITOR Manual ON and RESET functions are located on both ELT Main Unit and Remote Unit The two Green ON lights flashing located on the ELT Main Unit and Remote Switch Unit and a buzzer are to indicate when the ELT 15 transmitting Both ELT Main Unit and Remote Unit are self powered by their internal batteries Automatic activation 15 remained regardless whether the Cable Interconnect between the Main Unit and the Remote Unit is open or shortened GPS INTERFACE PROTOCOL Latitude Longititude Insert Messages Aviation RS 232 Baud Rate fixed 9600 Parity None Data Bits 8 Stop Bits 1 Garmin International Inc
21. Connect the Buzzer wiring to the Remote Switch Unite via T Adapter connector The rear of the buzzer can be sealed with RTV however the front must be left open Note If the Buzzer for AK 451 15 located inside the ELT Main Unit it is powered by the ELT Main batteries The ELT Main Batteries will continue to supply power to the Buzzer for 78 hours at 20 deg C at end of 5 years battery life Connect Harness With the harness installed See Fig 14 into the Remote Switch Unit Install the ELT in its mounting tray securing with the Velcro strap Connect the buzzer wires Note Splicing may be necessary on the buzzer wire If more than 4 long Connector is to be sealed with RTV after system has been tested Once all tests have satisfactorily been completed and all harness connections have been verified to be correct the connectors at the remote cockpit switch and the ELT should be sealed to prevent moisture from getting into the wire entry holes Seal using an electronics grade neutral cure non slumping RTV such as GE Silicones RTV162 Dow Corning 748RTV or Silastic 1080RTV Helicopter Installations Refer to aircraft manufacturer s data Type Approval or STC information and or national regulations regarding installation on helicopters The ELT may be installed in a helicopter with the ELT unit mounted with Direction of Flight arrow pointing downward at a 10 angle to the horizontal plane rather than parallel to it 54 2
22. Fertnan B niessler at aon at 6 Dokumente Nachweise Bauurkunden Engineering Order 4 01 04 2010 EONOO4 Instaliation Instructions 01 04 2010 NS Ground Test Repost GTNOOZ AppA Rev Maintenance Manual Supplement AMM EONDOOZ Bauvorschnflen des Baumusters wurden entsprechend 5 32 8 i Bestehende eingebaute nderungen wurden bei der Beurteilung 004 Installation Instructions Niessler Handelsagentur F Hanuschgasse 8 2345 Brunn a G 1 General The basic intend of this document is to provide the required information s to install an Ameri King AK 451 AF AP AWhi PorWW Emergency Locator Transmitter into an airplane listed in Section 2 Configuration The installation must be carried out by a qualified person installation work must be performed in accordance with the acceptable methods techniques and practices for aircraft alterations inspections and repair shown in FAA documents AC 2 Configuration 43 13 1 and 43 13 2 In combination to the current EONOOA Installation Instructions the Ameri King AK 451 Installation Manual P N IM 45 Rev NC 4 1c2 or later approved version must be used and complied with The modification illustrated in this Installation Instruction applies to all airplanes listed in this section The AK 451 main unit must be installed on the same location Pointer 3000 ELT Installation of the remote control sw
23. www D Leer series LLL 2 3 series including postwar production 24 11 Cub Special Pes a PA 12 Super Cruiser amp Yes Yes A 780 14 Family Cruiser A 797 PA 15 17 Vagabond Yes Yes A 800 and PA 16 Clipper A 805 New Annex Il EASA list Issue 10 25 Feb 2008 Page 8 of 10 190 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Evaluation against Annex II criteria uu cM lt omments Yes PA 16 Piper JSA PA 18 amp 19 Super Cub velopment 31 G 3 Los R lt D v lt J lt b o v po 1A2 But see note Production carried on beyond 1975 in small numbers but for consistency all Cubs and Super Cubs are regarded H aan A 20 22 Yes Yes Piper PA 23 Yes Yes 1A10 but Aztec models are not Annex II E Apache PA 23 250 PA E23 250 3 Seabee TCC Cis es ____ ______ 5 ___________ 21 22 series 1 ves Fe Stinson jV 77 _______ ____ 7 Yes 7 74 772 _______ __ S 1 11 62 1 1 1 Taylorcraft A B C D models 15 Yes Yes Yes A 643 18 19 L series A 696 New Annex EASA list Issue 10 25 Feb 2008 Page 9 of 10 19 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Evalu
24. 96 3 53 Frequency Test Current Draw Test Performance Testing NOTE Using of ELT Test set TS 451 or equivalent test equipment is acceptable The ELT Transmitter frequency may be measured as follows 3 5 3 1 Connect the Frequency Counter as shown below 3 5 3 2 Measure the 121 5 243 0 MHz frequency Select the Notch filter as appropriate 1 e 243 notch when measuring 121 5 MHz The ELT should be within 50ppm 6 075 KHz of 121 500 000 Hz Repeat with the 121 5 MHz Notch Filter The ELT frequency should be within 50 ppm 12 150 KHz of 243 000 000 Hz after 3 minutes of operation 3 5 3 3 Measure the 406 028 MHz frequency Ensure that adequate attenuation rated for 406 028 MHz 37 dBm and 5 Watts 15 installed between the ELT s 406 028 MHz output and the input to the frequency counter to prevent damaging the frequency counter s input circuitry Set up the equipment as shown below ELT BNC Connector Applicable Spectrum attenuator Analyzer Verify an initial frequency of 406 028 MHz 1 KHz after 3 minutes of operation Note Allow the unit to run 3 minutes before making the measurement to allow the oscillator to stabilize 97 3 5 3 4 Current draw tests CAUTION The following tests involve measurement of the lithium battery pack Exercise extreme caution to avoid causing a short circuit condition which will blow the fuse in the battery cell It is recommended th
25. Figure 3 To program 30 Hex ID to the ELT Long Messages At the command prompt type 06 30 Where X X 30 HEX Digits ID See Figure 4 AK451 HyperTerminal File Edit Call Transfer Help Dis 218 sole AMERI KING AK V1 xx FE FE FE FE FE FE FE FTE FE FE FE FE FE FE HE HE HE FE FE HE HE HE HE JE JE HE HEH HHH HH HHH HHH HHH HHH serial mode dk connected 01 this menu 02 disconnect 03 read ID 04 read SN 05 selftest 06 write ID 19 read SEL VHF 20 write SEL VHF ak 06 30 30 Hex Digits Figure 4 lO xl inl x 135 Example To program 30 Hex ID to the ELT Long Messages at the command prompt type 06 30 97142CC1637FDFF9996CF583E0FAAS A screen as shown in figure 5 below should appear indicating that the program 15 a SUCCESS 4 amp K451 HyperTerminal File Edit View Call Transfer Help JE AMERI KING AK V1 xx
26. GPS connector RJ 12 amp P amp C 451 0181 DC Ground Remue RESET SW Lo ON EW La Rampe ON Lighi Le 13 882 NOTE Optional Mil Spec M22759 18 or 35 24AWG at specified length is available Figure 14 2a Wiring Diagram for AK 451 with GPS Position and 3 inch T adapter with 4 wire interconnecting ELT Main Unit and Remote Switch Unit 66 NOTE Optional Mil Spec M22759 18 or 35 24AWG at specified length is available Figure 14 2b Wiring Diagram for 451 with GPS Position and 3 inch T adapter with 2 wire interconnecting ELT Main Unit and Remote Switch Unit 67 222 BATTERY INSTALLATION AND REPLACEMENT 2 5 1 ELT MAIN UNIT BATTERY INSTALLATION AND REPLACEMENT batteries are strongly advised to be serviced by Ameri King or its authorized service centers End users may return the entire ELT for replacing the batteries and post functional tests The Ameri King Corp Model 451 ELT is designed to use only with Ameri King lithium battery packages which have been tested per 5 126 TSO C9la requirements The use of any other battery will void all warranties of the ELT by Ameri King Corp The ELT does not meet the requirements of TSO C126 and TSO C91a or FAR 91 207 if used with any other type of battery Using any other battery is not allowed forbidden The Ameri King Battery Pack has a 10 years shelf life and 5 years useful life It will last for 78 hours at 20 deg C
27. Table 4 Rotorcraft EU and non EU State of Design Evaluation against Annex II criteria Historic Development of Role in armed Design Production State of Design TC and event Aviation forces 1 1 53 42 075 Comments 551 cs es es __ __________ Mk 60 Wessex ______ HEENEE ___ _____ 60 Westand Bell a7 variants __ fe fe USA Canada Model 47 2 3 Cobra TAH P Surplus Replica E SS Ma ES A Dornie Hiller Fairchild UH 12 OH 23 series Yes Sikorsky S 55 S 55B S 55C Yes Yes 1H4 piston engined variants Sikorsky B C D E F Yes Yes G H J piston engined variants New Annex EASA list Issue 10 25 Feb 2008 Page 2 of 2 201 Table 5 Balloons and Airships EU and non EU Type Evaluation against Annex II 1 1 559 a 3 Comments LBA 9004 type transferred pipi many only one modified prototype S N 1 equipped for scientific missions not transferred LAC AV 2 Hot Air Two for Experimental purposes no TC issued Designed for Gordon Bennet TCDS 150 TC 77 1985 o Initially registered as experimental o homebuilt No TC issued o Initially registered and evaluated as amateur built No TC issued B 01 01 proposed for Annex II by FOCA Switzerland o prototype New Annex EASA list Issue 10
28. Distress Config gt _ Connected 7 11 41 Auto detect 9600 8 N 1 SCRO CAPS NUM Capture Print echo Figure 6 Maintenance Self Test Maintenance Test includes the following tests VHF PLL locked PLL locked in F3 or F1 or F2 at fault 9 flashes VHF Power output level FI F2 VHF RF power level 17 dBm 121 5 243 MHz 7 flashes F3 PLL locked PLL locked in F3 or F1 or F2 at fault 9 flashes F3 Power output level RF power level 33 dBm 406 028 MHz 5 flashes Internal 3V3 Vcc supplies for F2 or F1 at fault 4 flashes Internal 5V VHF Vcc supplies for F3 F2 or F1 at fault 4 flashes Internal 7V3 406 Vcc supplies for F3 F2 or F1 at fault 4 flashes Internal LDO status Internal Data stored in Memory at fault 1 flash Battery level Battery voltage 1s low Useful Life Battery Voltage setting 3 flashes Distress ID stored in Memory at fault 2 flashes EEPROM Distress config stored in Memory at fault 2 flashes Test results will display as follows OK Tests pass KO Tests fail 140 4 Functional Test GPS Position Coordinates Simulation Ref E6557 CS Q5 AK 451B HyperTerminal BAX 7 Table F D 2 File Edit View Call Transfer Step 1 Click here for drop down menu SendFie Receive File Capture Text Send Text File Step 2 Click here to browse the In this example the Ameri King GPS Location file is o
29. FH P Subject ARLHWNREIDEELT 22 76 2 TRI 39 SEO ER ARO ATU C 9 ABLAAREOBNICEMENELEDCH 158 79 5 lt 79 AK 451 AF AK 451 AF AP AK 451 AP AK 451 S 36 Ameri King Corp WEB f Aa Hiroka Tel 03 5253 5908 PHS 26788 mailto h niiyama soumu go jp K K K K K K K K K K K K K K K K K K K K K K K K K K 212 RER 685 SERE 2 243EAHOG6EH A ztl ZLEX aii XE RE R AXE mH d RREI CO Cie AR RR GHA TERR SRRRAORS ARERR 8436 286 240 ITED BY 0402 51312 7 12 5 145 11605 158 HSC Z CETSUZUS 0Cc UI 0ciuxEAHY 6 aC 1 2 AK 451 AF AK 451 AF AP AK 451 AP AK 451 S 3 Ameri King Corp 4 7 EIC DUC 1 FEB ULES Federal Aviation Administration 2 TS0 091a TSO C126 213 This page 15 left blank on purpose This page 15 left blank on purpose 214 215 SARSAT COSPAS TYPE APPROVAL CERTIFICATE For a 406 Megahertz Distress Beacon for use with the Cospas Sarsa
30. GY20 amp 30 Minicab Yes Yes GY201 Home built amp Supercab series B _____ cs ves es P il GY201 II Caudron Renault Pre 1939 Yes Yes JN760 Lesen PS PS L Gardan GY100 Bagheera Prototype only R amp D TC 47 New Annex Il EASA list Issue 10 25 Feb 2008 Page 3 of 19 165 166 Table 1 EU states of Design powered aircraft fixed wing Historic Development Role in armed Design Production State of Design TC event of Aviation 11 55 611 75 and Comments Type special 101 110 es es TCDS 14815 Jodel Wassmer EAC SAN Alpavia D11 series SALS Yes Yes Mostly believed to competition be amateur built see Note 8 on page 1 CR Diis izssenes ves 5523 DR1050 1051 Yes Yes TCDS 34 TC 6 series 17 replica __ es es a Colibri Matra M360 Jupiter series Centreline No but Yes TC33 TCDS 99 bis thrust concept and 109 New Annex list Issue 10 25 Feb 2008 Page 4 of 19 167 Table 1 EU states of Design powered aircraft fixed wing State of Design Manufacturer Evaluation against Annex II criteria Design Production State of Design TC cr and Comments x Holste MH152 1521 153 qe cms 47 amp 57 Broussard M
31. e SIZE AND WEIGHT Main Unit 4 27 Wx2 95 Hx5 64 L 1165 140z Remote Unit 1 58 W x 0 65 H x 2 00 L 1 0 oz Transport Blade type 451 017 3 600 Knots airspeed 1 4 155 Business Rod type 451 017 2 350 Knots airspeed 0 5 Ib General Aviation whip type 451 017 1 300 Knots airspeed 0 25 Ib Portable Antenna 451 017 4 171 4 0 oz Mounting Tray amp Velcro holder 4 51 W x 0 75 H x 5 87 L 4 0 oz e MOUNTING HOLE SPACING Mounting Tray 4 Trapezoid Corners L1 2 76 L2 1 76 H 2 01 Remote Unit 4 Rectangular Corners 1 825 W x 0 490 H Fixed Antenna 7 5 1 Holes 0 500 Diameter for Blade Rod Whip respectively e CASE AND COLOR No Sharp Edges High Impact Flame Retorted Fire Resistant Waterproof High Temperature ABS Plastic Safety International Orange Color e GENERAL SPECIFICATIONS STANDARD CONDITIONS Operating Frequencies 406 028 MHz 0 001 MHz 121 500 MHz 0 005 243 000 MHz 0 005 Short term stability lt 2 x 10 7 100ms Medium slope 1 to 1x10 min Medium Residual variant lt 3 x 10 Modulation Characteristics Audio Sweep Frequency Download Sweeping 1600 300 Hz Sweep Rate 3 Hz 1 Hz Modulation Factor More than 0 85 Occupied Bandwidth Less than 25 Hz Voice Modulation Included Modulation Duty Cycle 33 55 Square Wave AM Continuous Peak Effective RadiatedSOmW 121 5 MHz 50mW 125 243 0 MHz 5W 1 58W
32. 17 3 3 4 Green ON Lights Buzzer Sound and Antenna check 80 3 3 5 Transmitter Functional Test for ELT S only 81 Periodic Maintenance Instructions for Continued Airworthiness 86 3 4 1 Seure INS PECON oro toa 86 3 4 2 Corrosion Inspection for Coaxial 86 3 4 3 Corrosion Inspection for Remote Wiring Modular Cable 86 3 4 4 Expiration Date eclesie een ta tte Pod es 86 3 4 5 Battery Leakage Check oec ete tutatus see heo mes EON audies 86 3 4 6 Operational REN Son tss 86 3 4 7 1 COCK 86 2472 Amenia C Decke sese fu ea 87 3 4 8 Verification of Digital 0 00000 87 3 4 9 Verification of Registration 4 4400 044 001 89 3 4 10 Verification of ELT GPS 0 2 00 90 3 4 10 1 ELT to GPS Interface Information 90 3 4 10 2 ELT GPS Interface Communication Formats 91 3 4 10 ELT FMC Interface and Checkout Process 92 3 4 10 4 24 Bit Address Installation Test mandatory for APPENDIX A Installations reprogramming by Ameri King s authorized dealer 92 Retrofit Instructions from AK 450 to 451 106 DATOS GPS Position
33. DOA STCs and with certain limitations previous FAA field approvals Supporting data such as stress analyses test reports sketches or photographs should be submitted with the FAA Form 337 The Ameri King IM 451 Installation Manual may be used as a supporting data These supporting data will be returned to the applicant by the local FAA district office since only FAA Form 337 15 retained as a part of the aircraft records at Oklahoma City 72 SECTION III OPERATION 31 GENERAL This section describes the operation of the ELT Emergency Locator Transmitter mo tdel AK 451 The following types are applicable for the model AK 451 a Automatic Fixed Fixed ELT AF See paragraph 1 2 1 a b Automatic Portable ELT AF AP with dual antennas See paragraph 1 2 1 b Automatic Portable ELT See paragraph 1 2 1 c d Survival ELT 5 See paragraph 1 2 1 d The AK 451 is a third generation ELT transmitting on 406 028 121 5 and 243 0 MHz The ELT 15 designed to meet or exceed the requirements of TSO C126 and TSO C91a and the mandatory automatic ELT requirements of FAR Part 91 The ELT meets the requirements of DOT Aviation Regulations Section 3 Chapter 3 Part 2 The ELT automatically activates during a crash and transmits the standard swept tone The Green ON lights flashing located on both the ELT Main Unit and the Cockpit Remote Switch unit and the buzzer sound periodically indicates when the ELT is
34. G switch Rod3 Antenna P N 451017 2A 1 and Portable Antenna P N 451017 45 ELT Set for Helicopter w Optional Multi Axes 6 Axes G switch AK 451 ELT Sets with GPS NAV Position DOCUMENT NO IM 451 REV NC 41 rmm APPLICABILITY Included Model Part Fixed Whip Or Fixed Rod Or Fixed Portable Whip Whip Antenna P N NO Antenna Antenna Blade Antenna Antenna GPS Whi Por Ton oti and 406 121 5 406 121 5 243 406 121 5 243 406 121 5 243 AK 451 23 AK 451 6 Portable Antenna P N 451017 45 Rod3 Antenna P N AK 451 A F AP w ELT Set with GPS NAV 451017 2 1 s 4 GPS Rod3 Por Position for Business Jet and AK 451 AP AK 451 7 Aircraft Portable Antenna AK 451 9 P N 451017 45 Rod4 Antenna P N AK 451 A F AP w ELT Set with GPS NAV 451017 2A M Mandatory The respective model must be accompanied by this antenna GPS Rod4 Por Position for Business Jet and 8 Selective The respective model must be accompanied by at least 1 of these AK 451 8 Aircraft Portable Antenna antennas P N 451017 45 Blade Antenna P N 451 w ELT Set with GPS NAV 451017 3A GPS Blade Por Position for Transport and AK 451 9 Aircraft Portable Antenna P N 451017 45 TS 451 Computer Test Set and ELT Coding Equipment for AK 451 Whip Antenna 451 w ELT Set for Helicopter with HEY and Garmin Garmin GPS 400W GPS Heli Whip
35. Make sure the rubber washer which forms a moisture seal between the Antenna base and the aircraft structure is in place before installing the Antenna Also make sure the serrated locking washing 15 in place 2 2 2 2 1 Whip Antenna Installation 451017 1B The 451017 1B Whip Antenna delivers optimum performance only when installed correctly To ensure adequate structural strength of the aircraft for associated air loading during flight use of a backing plate or doublers not supplied may be required Refer to FAA Advisory Circular 43 13 2B for guidance It is the responsibility of the installation agency to determine the appropriate and adequate antenna installation The 451017 1B Whip Antenna is designed to provide ELT transmissions from a single BNC Female Coaxial connector Location The 451017 1B must be mounted on the top of the aircraft to assure maximum visibility of satellites 406 MHz The best location is the upper aft portion of the fuselage It should be mounted vertically and away from projections such as a propeller tail surfaces or the shadow of larger antennas Refer to Fig 6 for a drawing of the antenna 35 Installation Preparation 1 Prepare the surface for antenna installations in such manner to ensure ground contact of less than 0 0030 If bare metal surfaces are needed for surface preparation they should be treated with Alodine amp 1200 or similar compound to eliminate aluminum oxidation 2 Drill 0
36. Message Other protocols are possible and the exact read outs of the Computer Test Set will vary Refer to the applicable operation manual included with the Computer Test Set or contact AMERI KING for assistance To verify the digital message perform the following steps Setup Use provided cable to connect the ELT RJ 12 port to the PC USB port 3 4 8 1 ELT ID Reading Stepl Double Click AK451 Icon to run the program The programming window appears as below AK 451B HyperTerminal File Edit View Transfer Help D 5 a EM Connected 0 01 25 ANSIV 9600 8 1 Note If you don t see the window above you may try the other USB port Step 2 Set the ELT main switch to ARM position Step 3 Verify the LED ON light illuminates for 4 seconds Step 4 At the gt _ prompt type Password command then press Enter to go to main menu Must type this command within next 20 seconds after the command prompt appears Note If there is no programming command input in this time window the ELT will enter the Self Test mode and you cannot program the ELT In this case set the ELT switch to OFF position and start again from step 2 2 88 451 HyperTerminal inl xl File Edit View Transfer Help p FE FE FE FE FE FE FE FE FE FE FE FE FE HE HE HE FE HE FE FE FE FE FE FE FE FE FE HE HE FE HE HE HE HE HE HE FE HE HE HE HE AMERI KING A
37. Section 7 Handling And Storage Do not store batteries in a manner that allows terminals to short circuit Batteries should be separated from other materials and stored in a non combustible well ventilated sprinkler protected structure with sufficient clearance between walls and battery stacks Do not place batteries near heating equipment nor expose to direct sunlight for long periods Batteries should be stored in a dry area at temperatures no higher than 85 194 F Air conditioning or cooling is not required unless excessively high temperatures above 90 C 194 F will be encountered Elevated storage temperatures above 72 162 F can result in reduced battery shelf life and service life and should be avoided Batteries should be kept as cool as possible in order to maximize shelf life and service life Batteries are not designed to be recharged Charging a battery may result in electrolyte leakage and or cause the battery to flame Never disassemble a battery Should a battery unintentionally be crushed thus releasing its contents rubber gloves must be used to handle all battery components Avoid inhalation of any vapors that may be emitted In the event of skin or eye exposure to the electrolyte refer to section 4 First Aid Measures More than a momentary short circuit will generally reduce the battery service life Batteries with fuses will no longer be functional after being shorted Extended short circuiting
38. this facilitates moving the ELT from one aircraft to another when performing routine maintenance etc WARNING The programming and labeling of the ELT must match the aircraft it 1s installed in The product label will have to be re marked to reflect the new programming and or country of registry if a 24 Bit address long message protocol ELT is reprogrammed Re registration may not be required if the contact information does not change however contact your local civil aviation or beacon registration authority when in doubt Both serialized long message and 24 Bit address long message re programmed ELT that is moved to another aircraft shall need to be re registered Online or by Mail The user must specify 24 bit long message programming when ordering the ELT Changing the programming protocol of the ELT can only be done at Ameri King or an authorized Ameri King Repair Station 3 4 10 2 ELT GPS Interface Communication Formats The only Aviation RS 232 format which is supported is limited to the following conditions Baud Rate fixed 9600 Parity None Data Bits 8 Stop Bits 1 In addition the RS 232 format must have 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 AK 451 GARMIN INTERNATIONAL INC
39. 150 milliamps mA When the 406 028 MHz module is on generating the 406 028 MHz burst the current may exceed 2 0 amps Turn the ELT OFF Disconnect the test harness P N TS 451 HN1 Reconnect the 2 pin module power harness Reinstall the battery pack as described in Section 4 3 4 98 3 5 4 AUDIO MODULATION PERFORMANCE TESTING Perform the transmitter tests by activating the ELT and listening on 121 5 MHz The audio swept tone should sound like an ELT 3 5 5 TRANSMITTER FUNCTIONAL TEST Perform Transmitter Functional Test per paragraph 3 3 above including all Test paragraphs 3 3 1 through 3 3 5 Note All ELT ON tests should be performed within the first five minutes of the hour 3 5 6 PERFORMANCE TEST MARKING AND LOG BOOK ENTRY Following satisfactory completion of all of the above Performance Testing the date on which the test was performed shall be marked on the external casing in a legible and permanent manner Enter the test date and Technician Initials as ELT Pass or Fail into the aircraft Log Book 3 5 7 SHIPPING In order to prevent accidental activation of the ELT during transit the ELT ON OFF ARM Main Switch must be set in the OFF position Note The ON OFF ARM Switch 16 lever locked type 99 SECTION IV REGISTRATION AND RESPONSBLE USE 4 1 REGISTRATION 4 1 1 Registration Importance It is mandatory that the owner of this 406 MHz ELT registers it with the National Authorities All 40
40. 1s very important that the installation be performed according to the following instructions Installation of the ELT 15 somewhat unique as is the installation of any TSO C126 and TSO C9la ELT it requires experience in sheet metal work and avionics Only licensed technicians should install the ELT Many problems associated with the older ELTs were due to poor installation Therefore duplicating a previous ELT installation with the AMERI KING ELT may not be acceptable Installations must be made by qualified personnel in accordance with FAA regulations Duplicating a previous installation may not be acceptable Refer to the Department of Transportation Regional ACO for detailed information Please refer to FAA AC 43 13 for guideline RTCA DO 182 recommends All ELT system components which must survive a crash intact should be attached to the airframe in such a manner that the attachment system can support a 100g load in the plus and minus directions of the three principal axes of the aircraft RTCA documents may be obtained from RTCA Inc 1828 L Street NW Suite 805 Washington DC 20036 Tel 202 833 9339 Fax 202 833 9434 www ttca org info rtca org 25 Note Installation in a pressurized aircraft constitutes a major modification Consult the Department of Transportation Regional Officer before proceeding Note Aircraft manufacturers may also have guidance on ELT installation refer to and follow any applicable Type
41. 2 6 WIRING CABLE INSTALLATION After installing the ELT Main Unit Antenna and Remote Unit in the aircraft install the Coaxial Cable between the ELT Main Unit and the Antenna The Cable should not cross any production break and must have a reasonable amount of slack at the ELT Main Unit This slack is necessary to allow for easy removal of the Coax Cable during maintenance and when needed as a Portable Device If a longer Coaxial Cable than the one supplied with the unit 6 feet it may be fabricated using RG 142 MIL C 17 Cable and AMP 227079 5 Connectors or King KC 59 162 BNC Connectors or their equivalent Insertion Loss of the Cable should not exceed 0 8 dBm Secure the Coaxial Cable using Tie Wraps or other appropriate methods Make sure the Cable is protected from abrasion RG 400 U or equivalent 1s acceptable The Remote Switch Unit is connected to the ELT Main Unit via means of RJ 12 Standard Type Modular Connectors The RJ 12 Connecting Cable is included with each ELT To install the Cable connect each modular plug at end of the Interconnecting Cable to the ELT Main Unit Jack and the ELT Remote Switch Unit Jack via T Adapter Connector See Figures 14 1 14 1 1 Connect buzzer wiring and GPS wiring harness assembly P N 4510042 to the ELT Remote Switch Unit via T Adapter Connector as well See Fig 14 1 14 1 1 14 1 2 and 14 2 Note All wiring harness assemblies P N 4510041 4510042 were Qualification tested including Flame Test p
42. 20 Registration AK 451 AF AP Portable Antenna P N 2 Australia AK 451 21 Country pua Asia Africa Registration and Brazil Anatel NC 4 1d Approval KV 11 30 08 updated Wiring diagrams Rod3 Por ELT Set 451017 2A 1 and added AK 451 3 for Business Jet Aircraft Portable Antenna P N NC 4 le Approval N KV 4 10 10 45 1017 48 Certificates AK 451 AF AP ELT Set Rod4 Antenna P N added Rod4 Por iur Busines 451017 2 and Portable AK 451 4 Antenna P N 451017 45 AK 451 AF AP ELT Set Blade Antenna P N Bla Por 451017 and Portable AK 451 5 Antenna P N 451017 4S ELT Set Auto Portable with Rod3 Antenna P N AK 451 AF AP AK 451 AP AK 45 1 10 porabile son Pus QUEE no Portable Antenna P N other iid did included 451017 48 permanently AK 451 S ELT Survival with portable attached to the unit AK 451 11 soft case ONLY no other accessories included AK 451 AF AP Whip Antenna P N Heli Whi Por ELT Set for Helicopter 451017 1B and Portable AK 451 15 Antenna P N 451017 45 AK 451 AF AP Rod3 Antenna P N Heli Rod3 Por ELT Set for Helicopter qu AK 451 14 451017 45 AK 451 AF AP Heli w 450000 1 Whi Por AK 451 12 AK 451 AF AP Heli w 450000 1 Rod3 Por AK 45 1 16 ELT Set for Helicopter Whip Antenna P N 451017 1B and Portable Antenna P N 451017 4S w Optional Multi Axes 6 Axes
43. 212 SAVE 7283 AFRCC Console For official mission correspondence only Tel 800 851 3051 103 SECTION V WARRANTY 54 LIMITED WARRANTY equipments manufactured by Ameri King Corp are guaranteed against defective materials and workmanship for a period of two years Any equipment found to be defective due to material and workmanship during this limited warranty will be repaired and put in original manufactured operating condition An option of extended third and fourth year limited warranty becomes valid at the end of this second year which will warrant to the original owner This Ameri King Corp warranty is void unless the Warranty Registration Card 15 filled out and returned to Ameri King Corp within 15 days after original installation Ameri King Corp s liability under this warranty is limited to servicing repairing replacing or adjusting any equipment returned prepaid to the factory by express written or oral authorization for that purpose and to repair or replace defective parts thereof This limited warranty does not include any damage caused by the leakage of batteries Repaired equipment will be returned to the equipment user freight pre paid Shipping charge will be paid one way only by Ameri King Corp Upon discovery of a condition believed to be caused by a defect in manufacturing Ameri King Corp without prior authorization Any equipment returned to Ameri King Corp without prior authorization
44. 25 Feb 2008 Page 1 of 2 202 Table 5 Balloons Airships EU and non EU Manufacturer ____ Evaluation against Annex II criteria GENE of Aviation forces IT5S8 Comments 1 Airship EE Flying Pictures Apoly 1 44000 ves prototype Western Balloons 20 Balloon ves LL O s1 Balloon _______ O 65 Balloon ______ DT prototype C E New Annex Il EASA list Issue 10 25 Feb 2008 Page 2 of 2 203 New ANNEX II from revision to Regulation 1592 2002 ANNEX II Aircraft referred to in Article 4 2 of Regulation 1592 2002 to be replaced Article 4 1 1a and 1b do not apply to aircraft falling in one or more of the categories set out below a historic aircraft meeting the criteria below i non complex aircraft whose initial design was established before 1 1 1955 and production has been stopped before 1 1 1975 ii aircraft having a clear historical relevance related to a participation in a noteworthy historical event or a major step in the development of aviation or a major role played into the armed forces of a Member State b aircraft specifically designed or modified for research experimental or scientific purposes and likely to be produced in very limited c aircraft of which at least 51 is built by an amateur or a non profit making association of amateurs for their own purposes and
45. 562 hole in aircraft skin Type of aircraft The 451017 1B Whip Antenna is designed for installation on fixed wing subsonic aircraft with reciprocating engines and is rated for a maximum airspeed of 300 KIAS Knots Indicated Airspeed at Sea Level Installation l Metal adapter plates are optional but they should be used if the curvature or compound radius of the aircraft skin is such that antennas cannot be directly installed vertically with their plates mounted flat to the aircraft outer surface Backing plates or doublers should be installed to ensure adequate structural strength for associated air loading during flight Refer to FAA Advisory Circular 43 13 2B for complete information a Remove the 1 2 28 hex nut and external tooth lock washer from the base of the antenna Insert antenna connector through mounting hole make sure the O ring remains in the base of the antenna connector flange groove and that the connector has sufficient clearance through the aircraft skin To mount the antenna place the lock washer and the hex nut on the inside of the aircraft and sandwich the aircraft skin between the base of the antenna and lock washer followed by the hex unit Tighten the hex nut to between 25 to 30 inch lbs 4 Apply a small smooth fillet with RTV sealant around the periphery of the antenna base to seal of moisture For maximum signal strength the length of the antenna coax to the ELT should be as short as possible use
46. 7 Below are the steps of inserting location coordinate ini x Send Tenere MET IMPORTANT NOTE o EE ONCE THE HEX DIGITS APPEAR THE SCREEN TURN THE UNIT OFF Fe IMMEDIATELY FAILURE TO DO SO WILL RESULT IN THE SIGNAL TO diae NOTIFY THE EMERGENCY RESCUE AUTHORITIES E Ameri King GPS Location 2 Step 1 Single click on this file Desktop Select Ameri King GPS Location l Single Click Transfer ME P Single Click Send Text File vehe PE My Computer wt LY My Network File name laces Files of type Tes file TXT Cancel gt 04 read SN 20 write SEL VHF Figure 9 141 142 To verify the coordinate in the 30 Hex digits message o Double click on 406MHz Decode Icon to open up the 406MHz Decode Program See Figure 11 o Enter last 30Hex digits last 30 digits of 36 into the 406 MHz Decode Program The 30 Hex digits are the numbers you just have seen from the ELT which appears after 50 seconds on the programming window In this example you have to select the 30 Hexadecimal round button and press Process button to decode these 30 Hex numbers AK451 HyperTerminal File Edit View Call Transfer Help Dis 218 sole e AMERI KING AK V1 serial mode
47. A confirmation letter a copy of the actual registration and a proof of registration decal will be mailed to you within two weeks When you receive these documents please check the information carefully and affix the decal to your ELT in the area marked Beacon Decal on the Bottom or Left Side of ELT If you do not receive confirmation contact NOAA for additional information at 1 888 212 7283 4 1 4 Registration in Canada The National Authority in Canada is the NSS National Search amp Rescue Secretariat Canadian residents can register online at http beacons nss gc ca For more information please contact the NSS at Canadian Beacon Registry CFB Trenton PO Box 1000 Stn Forces Astra ON KOK Phone 1 877 406 5 51 7671 Fax 1 877 406 FAX8 3298 Email cbr sarnet dnd ca Online www canadianbeaconregistry forces gc ca 4 1 5 Registration Outside of the United States and Canada In countries other than the United States 406 MHz ELTs are registered with that country s National Authority at the time of Purchase The Sales agent should assist in filling out the forms and sending to that country s National Authority To verify that the unit 15 properly programmed for that country view the UIN label on the side of the unit In the event that the ELT 15 not programmed for the country in which it has been purchased the sales agent 1f properly equipped can reprogram the unit for that country Go to https ww
48. Any equipment returned to Ameri King Corp should be accompanied by a failure report in writing giving full particulars in support of the claim This limited warranty does not cover or apply to any of the followings including misuses of the equipment installation or operation not in accordance with factory instructions accidences or negligent damage alterations of any manner repair by other factory changes in calibration occurring as a result of normal use of equipment the cost of labor material or other expense incidental to the repair installation removal from the aircraft or replacement of the equipment damaged during shipment or installation any personal injuries or damage to property resulting from the installation or the operation of the equipment user assumes the risks of all such injuries or damage In such cases the repair will be billed at cost An estimate will be submitted for approval before repair is initiated Any equipment that 15 returned for warranty and found not to be defective shall be charged a minimum handling and service charge and returned C O D 104 No warranty will be activated for Ameri King Corp products unless the installation is approved by an FAA Certified Installer and the warranty card is completed by the supplying dealer or upon receipt by Ameri King Corp of form s 337 or 8130 THE IMPLIED WARRANTY AND ALL OTHER IMPLIED WARRANTIES ARE HEREBY EXCULED AMERI KING CORP MAKES NO OTHER WARRA
49. Approval or STC data for your aircraft If located outside of the US follow all applicable regulations for your national authority By signing either the aircraft logbooks or the FAA Form 337 you are stating that the installation has been performed in accordance with the current FARs and with the steps and procedures outlined herein In Canada all installations must be performed in accordance with the Engineering and Inspection Manual Part II Chapter III Section 3 12 Remember Your Professional installation may save someone s life 221 ELT MAIN UNIT LOCATION AND INSTALLATION 2211 ELT LOCATION DETERMINATION Many of the original ELT installations are inadequate 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 ELT should be located there as well The tail section of an airplane is least likely to be damaged during a crash and therefore it provides a good mounting environment for the ELT unit Refer to Figure 1 for Direction Determination for Fixed Wing Aircraft and Helicopter respectively Accessibility of the unit is an important factor in the location of the ELT Mount the unit as far aft as practical but where it can be easily retrieved for maintenance The mounting surface must be extremely rigid therefore mounting the ELT directly to the aircraft skin is unacceptable Mounting an ELT directly to the aircraft skin induces c
50. Contact Skin Remove particles of lithium from skin as rapidly as possible Immediately flush with plenty of water for at least 15 minutes and get medical attention Eyes Immediately flush with plenty of water for at least 15 minutes and get immediate medical attention Section 5 Fire Fighting Measures Extinguishing Media Copious amounts of cold water are an effective extinguishing medium for lithium batteries Do not use warm or hot water Do not use Halon type extinguishing material Fire Fighting Procedures Use a positive pressure self contained breathing apparatus if batteries are involved in a fire Full protective clothing is necessary During water application caution is advised as burning pieces of lithium may be ejected from the fire Unusual Fire and Explosion Hazards Batteries may flame or leak potentially hazardous organic vapors if exposed to excessive heat or fire Hazardous combustion products Fire or excessive heat may produce hazardous decomposition products Damaged or opened batteries can result in rapid heating and the release of flammable vapors Vapors are heavier than air and may travel along the ground or be moved by ventilation to an ignition source and flash back ULTRALIFE BATTERIES MSDS023 FA1284 Rev F OCT 01 2007 Page 2 of 6 Rev Date 31 2007 220 Section 6 Accidental Release Measures Damaged batteries that are not hot or burning should be placed in a sealed plastic bag or container
51. ELT can be activated by using a quick rap with the palm A TSO C91a ELT can be activated by using a rapid forward throwing motion coupled by a rapid reversing action Manufacturer s instructions should be referred to prior to activation Verify that the ELT has been activated by use of a Wattmeter the airplane s VHFG Radio Communications Receiver when tuned to 121 5 MHz or other means See Note 1 Reinstall the ELT into its mount and verify the proper direction for crash activation Reconnect all cables They should have some slack at each end be properly secured to the Airplane structure for support and protection 121 Ta Activate the ELT using the ON of Test Switch A low quality Broadcast Radio Receiver should be sued to determine if energy is being transmitted from the Antenna When the Antenna of this Radio tuning dial on any setting is held about 6 inches from the activated ELT Antenna the ELT Aural tone will be heard see notes 2 and 3 Verify that all switches are properly labeled and positioned Note 1 This 15 not a measured check It only indicates that the G Switch is working Note 2 This 15 not a measured check but it does provide confidence that the Antenna 15 radiating with sufficient power to aid search and rescue The Aircraft s VHF Receiver tuned to 121 5 MHz may also be sued This Receiver however 15 more sensitive and could pick up a weak signal even if the radiating ELT s Antenna i
52. Main Unit Part No 4510041 5 52 Pin Color 1 Brown 2 Yellow 3 Green 4 Red 5 Black 6 Orange Note Pins 1 and 6 are not connected RJ11 6P4C RJ11 6PAC Pinout Pinout Figure 12 2 Interconnecting Wiring Cable between ELT Remote Unit and Main Unit Part No 4500041 4 53 2 2 5 Audible Monitor Location and Installation A warning buzzer 15 required for TSO C126 approval The buzzer P N 451018 is powered by the ELT system and therefore independent of the aircraft power system When the ELT 15 activated the buzzer beeps periodically The time between pulses lengthen after a predetermined transmitter on time While the buzzer may be located anywhere on the aircraft it is recommended that the buzzer be placed in the cockpit near to the Remote Switch Unit This buzzer operates in tandem with the ELT panel indicator and would serve as a redundant indicator Note RTCA DO 204 indicates installation in the cockpit The buzzer can be mounted on the instrument panel using the plastic bezel nut suggested mounting is with the buzzer orifice with an open hole on the instrument panel adjacent to the Remote Switch Unit The 2 mounting ears at its base may be used as an extra optional mounting secure on the instrument panel Another option 15 tie wrapped the Buzzer onto the Aircraft Wiring Harness or attached by velcro onto or behind the Instrument Panel or fasten directly onto the Remote Switch Unit See Figure 11 1
53. Message e Serial User Protocol Coded with ELTs Unique Beacon Serial Number e Serial User Protocol Coded with the Aircraft Operator Designator and Serial Number e Serial User Protocol Coded with the Aircraft 24 Bit Address e Aviation User Protocol Coded with the Aircraft Nationality and Registration Marking Note 1 The AK 451 is pre programmed at the factory using ELT with C S type approval number and serial number Standard Location Protocol Long Message or Serial User Protocol Short Message for US aircraft Note 2 The 451 is pre programmed at the factory using ELT with 24 Bit aircraft address Standard Location Long Message or Serial User Short Message for Canadian aircraft Your 24 Bit aircraft address may be obtained from http www tc gc ca aviation activepages ccarcs aspscripts en quicksearch asp Note 3 There is no electronic connection between TCAS or Mode S systems and the ELT only the ID number is common The ELT may accept aircraft GPS NAV Lat Long position data then transmits the position data on the 406 MHz digital long messages 1 3 TECHNICAL CHARACTERISTICS SPECIFICATIONS CHARACTERISTICS APPROVALS FAA 126 C9 1a and EASA ETSO 2C126 2C91a BATTERIES 4500010 1 Battery Pack Lithium LiMnO2 90 Hrs lasting 4D cells Note For Canadian aircraft installation use 4500010 1 only 4500010 2 Battery Pack Lithium LiSO2 87 Hrs lasting 4D cells 19 PHYSICAL CHARACTERISTICS
54. P N 450 014 3l Figure 3 Mounting Tray with Velcro Holder and Portable Antenna for ELT AF AP 32 2 2 2 ANTENNA LOCATION AND INSTALLATION In order to meet the requirements of TSO C91a and FAR 91 207 an External Antenna must be used The Portable Antenna 1f supplied with the unit 1s for use only after the unit has been removed from the aircraft It is the responsibility of those desiring to install this article on a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards All antennas must have separate approval for installation in an aircraft The article may be installed only if further evaluation by the applicant documents an acceptable installation and it is approved by the FAA Administrator The article may be installed only if performed under 14 CFR parts 43 or the applicable airworthiness requirement For installations outside of the US contact your local civil aviation authority for guidance Ref TSO C126 paragraph D Please refer to FAA AC 43 13 for guideline 2 2 2 1 ANTENNA LOCATION DETERMINATION The mounting location of the External Antenna is determined to a great extent by the mounting location chosen for the ELT Transmitter The Antenna should be mounted as close to the ELT Transmitter as practical The Coaxial Cable connecting the Antenna to the ELT should avoid crossing aircraft production breaks 1 riveted fuselage sections The Antenna mus
55. Por GPS NAV Position CEU AK 45 1 24 AK 451 17 P N 451017 45 Rr Rod3 Antenna P N BendixKing KLN 94 AK 451 AF AP w GPS Heli SL Sai fo wal 451017 2A 1 Rod3 Por and AK 451 18 Portable Antenna P N 451017 48 Whip Antenna 7 Acc AK 451 AF AP w GPS Heli ELT Set for Helicopter P N 451017 1B M ne GNS 530W 450000 1 Whi Por w GPS amp Optional Multi Axes and LEES n 451 25 451 19 6 Axes switch Portable Antenna Garmin GPs 500W P N 451017 45 Rod3 Antenna P N ELT Set for Helicopter 451017 2A 1 O00 i w GPS amp Optional Multi Axes and 6 Axes G switch Portable Antenna P N 451017 4S 4500010 1 Battery Package Lithium LiMnO2 90 Hrs Lasting AK 451 AF AP w GPS Heli 450000 1 Rod3 Por AK 451 13 Whip antenna must have separate approval for installation in a Helicopter see para 2 2 2 Fach Ameri King ELT Set comes with dual Antennas a FREE Soft Case P N SC 451 and a FREE Accessory Set including Remote Switch Unit Pre Fabricated 25 Wiring Harness Assembly Audio Buzzer T Splitter and 6 Coaxial Cable Assembly TABLE OF CONTENTS REVISION P 2 Table Of C Onten a ___ gt 7 PISTOL BIOUTCS ded ies 12 SECTION I GENERAL INFORMATION
56. Project Management National Aircraft Certification Civil Aviation cc Industry Canada by email certification bureau ic gc ca 152 American Telecommunications Certification Body Inc 6731 Whittier Ave McLean 22101 REF ATCB006443 TECHNICAL ACCEPTANCE CERTIFICAT D ACCEPTABILITE CERTIFICATE TECHNIQUE CERTIFICATION No 2474A MS1PLAFAPS Single No DE CERTIFICATION ISSUED TO gt Ameri King Corp DELIVRE A 17881 Sampson Lane Huntington Beach CA 92648 TYPE OF EQUIPMENT b 287 Suffix PL PLB 287 Suffix AF ELT automatic fixed TYPE DE MAT RIEL 287 Suffix AP ELT automatic portable 287 Suffix S ELT survival TRADE NAME AND MODEL AK 451 PLB AF AP S MARQUE ET MODELE FREQUENCY RANGE b 406 028MHz fixed 121 5MHz fixed BANDE DE FR QUENCES EMISSION DESIGNATION 16K0G1D DESIGNATION D EMISSION R F POWER RATING b Min 3 16W 406Mhz 0 050 121 5MHz PUISSANCE NOMINALE H F 7 84W 406MHz 0 2W 121 5MHz ANTENNA 3 40Bi TEST LABORATORY b Compatible Electronics SITE NUMBER 2154C 1 LABORATOIRE D ESSAI 19121 EL TORO ROAD NUMERO DE SITE Silverado Lake Forest CA 92676 Tel 849 589 0700 Fax 849 589 7700 CERTIFIED TO SPECIFICATION RSS2B7 ISSUE Issue 1 CERTIFIE SELON LE CAHIER DES CHARGES EDITION Certificado de Homologa o Requerimento n 0057 09 Certification of equipment means only that the equipment has met the require
57. RJ12 6P6C Plug and Molex Amp Connector 2 pin Figure 14 1d Wiring Diagram for retrofitting AK 451 with 2 wire interconnecting ELT Main Unit and Remote Switch Unit D amp M Narco Joliet 65 24 58 58 2 RS 232 Qut 1 RS 232 1 RS 232 Qui 1 Gen RE 232 Out 1 Gen 5 232 Qut 1 Gen RS z32 Qui 1 Tx Data Hi Tx Data Hi Tx Data Hi Tx Data Hi Tx Data Hi Tx Data Hi 26 TT T8 TT 14 27 2T ASG Ground Ground AC Ground Ground Ground AA Ground LG audible Buzzer 44 8 vic 451 018 ELT Model AK 451 Remote Uni 451 004 24 58 58 2 RS 232 Qut 1 RS 232 1 RS 232 Gut 1 Gen R2 232 Out 1 Gen RS 232 Out 1 Gen RS 232 Oui 1 Tx Data Hi Tx Data Hi Tx Data Hi Tx Data Hi Tx Data Hi Tx Data Hi 26 TT T TT TR 14 27 2T Ground Ground Ground Ground Ground AA Ground LG audible Buzzer e vile 451 018 ELT Model 451 Remote Une 451 004 Ping DC Greond S23 Remote RESET SW Lo DS Recta ON EW La RESET Ramai ON Dighi Le Remote Remote DN LighbLo RB5 222 Txd Hi 0041 Remote Wiring Cable Assembly A Opsonal GPS connector Ri 23 Remos RESET SWALO Remote ON SPN La Remote DN LighbLo R5 232 Txd Hi A
58. SZD Development prototy Development prototy es Development prototy lt N N N wi o ra 00 N D D tu a CL D nu 2 v g D e Y UJ o 7 tu V N N z m D D E E New Annex Il list Issue 10 25 Feb 2008 Page 5 of 7 Table 3 Sailplanes and Powered Sailplanes EU and non EU State of Design Evaluation against Annex II criteria vec irae of Aviation force lt lt and Comments Development prototy es Development prototy SZD 51 0 Junior SZD 52 0 Jantar 15 N N x Y Ol qe D z 3 3 lt N 52 1 Jantar 15S 5 z 8 Switzerland S S 30 02 S 30 04 2 S 30 06 paeem ________ ageltiuazeuaba Moswey Werke Moswey Il series fs beo _________ nr senes 538504 Neukom Elfe series Prototype none on register M39 06 Spalinger ie senes L ____ ___ Ees 77 _ _ S 22 ipa SS _______ O ______ _ _ New Annex 11 EASA list Issue 10 25 Feb 2008 Page 6 of 7 197 19
59. Series 150 250 400 420 430 500 520 530 Honeywell Bendix King Inc e KLN 88 KLN89 KLN89B KLN 90 KLN90B KLN94 KLN900 21 Arnav Systems Inc e R50 R501 STAR 5000 FMS 5000 MFD Multi Functional Display Morrow FLYBUDDY 2001 NMS Trimble Nav Inc NAV 1000 NAV 2000 TNL 2100 and TNL3100 The following Trimble systems all require a RS 422 to RS 232 adapter NAV 3000 TNL 1000 TNL 2000 TNL 2000A TNL 3000 2000 APPROACH 2000 APPROACH PLUS 2101 APPROACH 2101 APPROACH PLUS 2101 I O APPROACH 2101 I O APPROACH PLUS ENVIRONMENTAL TEST SPECIFICATIONS RTCA DO 204 DO 183 TSO C126 C91a RTCA DO 160E ENV CAT 204 183 204 183 XR 204 183 XXSXXXXAC 204 183 BXXXX 204 TEMP AND ALTITUDE Low Temperature Category 20 C Operating 55 C Storage High Temperature 55 C Operating 85 C Storage OPERATING LIFE 5W 406 208 for 24 hrs 20 C 50mW 121 5 MHz 50mW 243 0 MHz Minimum Requirement throughout a 50 hour period at 20 C TEMP VARIATION Category B 109 minimum per minute e HUMIDITY Category A 95 RH 50 operating 9 SHOCK 500G 4 1msec Penetration of 55 Ibs mass 6 drops 4 surfaces e CRUSH 1000 Ibs 4 surfaces e VIBRATION 10G Sinusoidal 5 2000 Hz 3 axes WATERPROOF Category R 15 minutes Spray 6 sides E IMMERSION SALT WATER Category S 24 hours Immersion 160 hours at 4 55 C SA
60. Stark Flugzeugbau CP 301 series Yes Yes 564 SA 642 SA Schempp Hirth Milan GS 6a uc Nes 561 SA VFW Fokker FW P 149D license Yes Yes 568 5 production Treated as pre TC R amp D specials pending Russian TC and EASA validation 7 examples Established high performance GA design New Annex Il EASA list Issue 10 25 Feb 2008 Page 9 of 19 172 Table 1 EU states of Design powered aircraft fixed wing State of State of Design Manufacturer Evaluation against Annex II criteria Development Role in armed Design Production State of Design TC of Aviation 1 1 55 lt 1 1 75 and Comments Yes light jet A278 d ment Established Yes Yes Later manufacture high are amateur built performance GA desiqn T n e A lt N N x tu gt 2 et 5 D o gt 3 v o 2 T 7 tu o T Meteor SpA Piaggio ______________ R32 Chirri R42 Falco 308 L60 WWII m i i o 3 c tu FL3 FL54 FL55 N333 Riviera TI Ai Ves Ves lt O laggio _ n 0 ___ ____ ___ gt 15 Established high performance GA design Netherlands 511 ves SS CS _____ ZZ ____ S _____ _______
61. VHF 20 write SEL VHF ak gt _ Figure 2 2 5 program ELT Use command 06 Important Instructions Please provide the following information via Email or fax or call Ameri King in order to obtain 22 Hex Digit ID e Country Protocol required See Table 1 for List of all available Protocols e 24 Bit aircraft address if applicable Ameri King shall then provide 22 Hex Digit ID Short Message or 30 Hex Digit ID Long Message accordingly e The 06 command syntax 06 s 1 22 30 123456789ABCDEF 0 e To program 22 Hex Digits ID to the ELT Short Messages At the command prompt type 06 22 XXXXXXXXXXXXXXXXXXXXXX Where X X 22 HEX Digits ID See Figure 3 134 AK451 HyperTerminal l File Edit Call Transfer Help AMERI KING AK V1 xx HH serial mode ek connected 01 this menu 02 disconnect 03 read ID SN 05 selftest 06 write ID 19 read SEL VHF 20 write SEL VHF ak 06 22 X X 22 Hex Digits
62. Y ours sincerely Andryey Zhitenev Technical Officer Encls Original certificate no 179 English plus three certified copies The Cospas Sarsat Parties Canada France Russia and USA Beacon Test Facility Intespace Toulouse France International Cospas Sarsat Programme 700 de la Gaucheti re West Suite 2450 Montr al Qu bec H3B 5M2 Canada Tel 1 514 954 6761 Fax 1 514 9546750 Email mail zcospas sarsatint Website www cospas sarsat org 218 APPENDIX K MATERIAL SAFETY DATA SHEET FOR BATTERY MSDS023 Section 1 Chemical Product And Company Identification Ultralife Part Number U10013 U10014 Manufactured b Batteries UK Ltd Batteries Inc 18 Nuffield Wa 2000 Technology Pkw Newark NY 14513 2175 CAGE Code U6734 09959 Emergency Telephone Number Chemtrec for Spills Leaks Fires 1 800 424 9300 Abington Oxfordshire OX14 1TG England International 703 527 3887 Technical Contact Telephone Number 1 800 332 5000 Section 2 Composition Information on Ingredients Percent of Chemical Name CAS Exposure Limits Content Manganese Dioxide MnO 1313 13 9 None Listed 40 45 Lithium Metal Li 7439 93 2 None Listed 3 4 Propylene Carbonate C4H O 108 32 7 None Listed 4 5 Ethylene Glycol Dimethyl Ether 110 71 44 5 ppm TWA 3 4 Shipping Name 1 2 Dimethoxyethane 1ppm Pregnant Women Tetrahydrofuran C HsO 109 99 9 200 ppm TWA 3 4 Lithium
63. __ __ __________ vako seres Yes 5 5 Yes Yes Yes es gt z tu 3 c tu 15 5 9 d New Annex Il EASA list Issue 10 25 Feb 2008 Page 1 of 10 183 Table 2 Non EU states of Design powered aircraft fixed wing Evaluation against Annex II criteria Aviation lt omnmaenis Yak 18T is a different design from all other Yak lt ei Yes Yes Other Twin Commander types are EASA aircraft A 351 448 Y K Scout NENNEN 676 688 11 Yes Yes A 761 A 796 7 series see entry fo Yes Yes A 759 American Champion below to see affected models imos ____ gt _ _ A 8028 ann OOO _____ ___ S Tr E ____ ____ ves ves __ a ose 876 728 gt dE E A YO 58 L 3 7 65 Grasshopper 18 lllves rl ll 728 ______ 25 5 RN NEN 65 765 __ 11 _______ ____ d Rn New Annex 1 list Issue 10 25 Feb 2008 Page 2 of 10 184 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Evaluation against Annex II criteria aver of Aviation force lt lt omments L 23 Seminole ar Yes Cs _ 17 Staggerwing amp UC Yes Yes Yes ATC 560 43B ATC 602 ATC 604 TC 713 TC 638 A 649 TC 779 T 34 Mentor
64. activated The ON switch on the Remote Switch Unit allows you to turn on the ELT for testing The RESET Switch on the Remote Switch Unit enables to reset the ELT In normal operation the Main Switch on the ELT Unit must be selected at ARM position Note You cannot disarm or disable the unit from the cockpit you can only deactivate the ELT after it has been activated The ELT unit is able to withstand extremely harsh environments Units exactly like yours have been subjected to numerous 500G shock pulses 1000 pounds crash weights and severe penetrator tests and continue to operate normally Continued operation in a temperature range of 20 to 55 degrees Celsius is assured 73 3 2 OPERATION The AK 451 ELT Emergency Locator Transmitter is a state of the art Micro controller technology long lasting solid state based equipment It is an extremely reliable highest standard of quality designed to meet TSO C126 and TSO C91a requirements for critical application Both ELT main unit and Remote Switch are self powered by their own internal batteries Interface with aircraft electrical power system 15 not required With the main switch located on the ELT main unit set at position the AK 451 ELT is automatically activated upon sensing a change of velocity of 4 5 0 5 Feet Second along its longitudinal axis Automatic Fixed ELT AF Configuration It is also designed to be removed from the aircraft and used as a personal l
65. ai fe 00 gt gt E D E 22 D Es 4 2 S 2 gt gt b 22 3 D New Annex EASA list Issue 10 25 Feb 2008 Page 7 of 19 169 170 Table 1 EU states of Design powered aircraft fixed wing Historic Design Production State of Design TC event LES ISLI and Comments m 181 ww 716 SA Dittmar HD 153 series First German Yes 501 SA a c after A OO Ee EA330 L amp S R amp D status TC not completed ieseler Fi156 Storch WII 725 SA lug Werk GmbH FW190 replica Individual aircraft ocke Wulf FW44 Stieglitz wwf 726 SA okker Individual areran H M s 2527 TA pes ves 573 5 Hirth 35 all variants WII LFU 205 No Y Messerschmitt 5108 572 5 5 109 all variants Ye Individual aircraft Mezez reples f D n 21 E 9 5 07 ue 5 o New Annex Il EASA list Issue 10 25 Feb 2008 Page 8 of 19 171 Table 1 EU states of Design powered aircraft fixed wing Historic Development Role in armed Design Production State of Design TC event 1 1 55 lt 1 1 75 and Comments a ali Rhein Flugzeugbau RW3 P65 amp 75 Dutedfan A sos sA S Dlpuctedfan 1057 5A mE ds EE id STOL Elster B amp C Ves No Yes 584 5 Schempp Hirth
66. be taken when transporting or shipping the ELT S not to move the switch or to allow packing material to become lodged such as to toggle the switch Main Switch alternate alternate momentary positions ON Alternate position ELT S transmits immediately Green ON light on the main unit flashes 1 second ON 4 seconds OFF The ELT swept Tone must be heard on the 121 5 MHz VHF Radio OFF Alternate position The ELT S is turned off e SELF TEST Momentary position ELT S self test 1s confirmed after the switch is held for 25 seconds If the self test 1s passed the Green ON light must be extinguished ELT swept Tone must be silent on the 121 5 MHz VHF Radio The ELT S system is fully self tested 81 3 3 5 2 Transmitter Self Test Turn and hold the main switch from the OFF position to the SELF TEST position The Green ON light shall illuminate for 4 seconds then extinguish This 15 to allow coding programming during next 20 seconds window and self test for 1 second thereafter The ELT S may be coding programming during the aforementioned 20 seconds window period If no programming happened the ELT will then enter the Self Test Mode for 1 second thereafter Self test results after 4 20 1 25 seconds 15 If the self test is passed the Green ON LIGHT is steadily extinguished ELT swept Tone must be silent on the 121 5 MHz VHF Radio If the self test is failed the Green ON LIGHT flashes as shown belo
67. beacon may delay a rescue response Accurate up to date registration information will also be used to conserve resources by helping to eliminate false alert deployments as an inadvertent activation can be resolved with a phone call There is no charge for beacon registration This is a service provided by the U S National Oceanic and Atmospheric Administration NOAA All online registrations will be entered into the National 406 MHz Beacon Registration Database on the same day of entry Registration forms received via postal mail will be entered within 2 business days of receipt For online registrations a confirmation letter with your completed registration information form will be sent immediately via e mail or fax if provided Confirmation letters sent via postal mail should arrive within two weeks Once your registration confirmation is received please review all information Any changes or updates to your registration information can be done via the internet fax e mail or postal mail If you do not receive your registration confirmation from NOAA on the same day you submit it over the internet or within two weeks if you submit it by postal mail please call NOAA toll free at 1 888 212 SAVE 7283 or 301 817 4515 for assistance After initial registration or re registration you will receive a NOAA Proof of Registration Decal by postal mail This decal is to be affixed to the beacon and should be placed such a way that it is clea
68. do Regulamento para e Homologa o de Produtos para Talecomunicac es aprovado pala Fasoluz o Anatel n 242 da 30 de novembro de 2000 a Declara o de Conlarmidade emitida polo solicitante Esta homolkegacdo expedida em nome do solicitante aqui identificada v lida somente para o produto a seguir discriminado cuja deve observar as comdigdes estabelecidas na regulamenta o do serico ou aplica o a que se destina Tipo Transmissor de Radiobaliza Categoria AK 451 AF AK 451 AP AK 451 5 AK 451 PLB Sorvico Aplicacao Servi o Especial de Radiodeterminacaa sesta t cnicas b sicas See Constitui obriga o do fabricante do produto no Brasil providenciar identificac o do produto homologado nos termos do art 39 do Regulamento anexo Resolu o Anatel 242 todas as unidades comercializadas antes de sua ofotiva distribui o ao mercado assim como observar e manter as caracteristicas t cnicas que tundamentaram certifica o orginal As informa es constantes deste ceriificado de homologa o podem ser confirmadas no SGCH Sistema de Gest o de Homologa o disponivel portal da Anatel www anatel gov br Maximiliano Salvador Martinh o Gerente Geral de Certifica o Engenharia do Espectro 154 EASA Minor Change Approval Information to Design Change Installation of an Ameri King AK 451 A
69. eliminate aluminum oxidation NOTE The 451017 2 Rod Antenna bonds through the base plate not through the mounting screws 2 Use the 451017 2A outline drawing on Fig 7 to determine hole pattern and drill Size Type of aircraft The 451017 2A Rod Antenna 15 designed for installation on fixed wing subsonic aircraft with reciprocating or turbine engines and 15 rated for a maximum airspeed of 350 KTAS Knots True Airspeed at 25 000 feet Installation 1 Metal adapter plates are optional but they should be used if the curvature or compound radius of the aircraft skin is such that antennas cannot be directly installed vertically with their plates mounted flat to the aircraft outer surface 2 Backing plates or doublers should be installed to ensure adequate structural strength for associated air loading during flight Refer to FAA Advisory Circular 43 13 2B for complete information 3 Mount the antenna using four 100 countersink 48 32 stainless steel machine screws and associated hardware Tighten to 20 Ibs max 40 Apply a layer of anti corrosion bonding grease between aircraft skin and bottom of antenna Apply a small smooth fillet with RTV sealant around the periphery of the antenna base to seal out moisture For maximum signal strength the length of the antenna coax cable to the ELT should be as short as possible use of the standard 6 foot coax cable 15 recommended when possible 12 50 FRONT VIEW SIDE V
70. goods also known as hazardous materials the United States by the International Civil Aviation Organization ICAO International Air Transport Association IATA International Maritime Organization IMO and many government agencies such as the U S Department of Transportation DOT These organizations and agencies publish regulations that contain detailed packaging marking labeling documentation and training requirements that must be followed when offering shipping Ultralife s cells and batteries for transportation However small cells and batteries are not subject to certain provisions of the regulations e g Class 9 labeling and UN specification packaging if they meet specific requirements The regulations are based on the UN Recommendations on the Transport of Dangerous Goods Model Regulations and the UN Manual of Tests and Criteria These regulations also apply to shipments of cells and batteries that are packed with or contained in equipment Failure to comply with these regulations can result in substantial civil or criminal penalties Cell and Battery Testing Requirements The dangerous goods regulations require that each cell and battery design be subject to tests contained in Section 38 3 of the UN Manual of Tests and Criteria prior to being offered for transport Ultralife s cells and batteries have been tested and comply with all of the UN testing requirements Batteries or battery packs constructed from Ultralife s cells m
71. in that country To verify the country for which an ELT is programmed see the label with the UIN on the back of the unit Units that do not have a country specified on the UIN label are programmed for the United States For a list of the national authorities in your area please go to http www cospassarsat com Management listOfParticipants htm 4 1 3 Registration in the United States It 16 the Owner s responsibility and required by law to Register 406 MHz ELTs that are programmed for and purchased in the United States The National Authority that accepts registrations in the United States is the National Oceanic and Atmospheric Administration NOAA The owner should complete the enclosed registration form Do not confuse this with the Ameri King Corp Warranty Card and mail it with the pre addressed postage paid envelope to see Appendix F SARSAT BEACON REGISTRATION E SP3 RM 3320 FB 4 NOAA NESDIS 5200 Auth Rd Suitland MD 20746 4304 100 ELT registration is also available online at www beaconregistration noaa gov The information provided on the Registration Form is used only for rescue purposes The Registration Form should be filled out and mailed immediately Registration can be expedited by faxing the registration form or by completing the form online in the event the ELT is to be placed immediate use Typically registration forms will be entered in the 406 MHz ELT Registration Database within 48 hours of receipt
72. include e ON OFF ARM Main Switch Green ON Light RESET Push Button Switch The Remote Unit features include e ON Push Button Switch Green ON Light e RESET Push Button Switch functions of the 451 are under micro controller control A self test routine checks ELT operation and installation then presents the results as visual and auditory error code to aid in troubleshooting and to indicate status Software is approved per requirements of RTCA DO 178B for level D software The battery pack consists of four D size lithium and 15 field replaceable Rated life 15 5 years or one hour of use whichever comes first as specified by FAR 91 207 c Installation kits are available that contain all major components needed to install the beacon 1 2 2 Application and Equipment Limitation This manual constitutes FAA approved data as described in AC 43 9 1F paragraph h 2 and AC 43 210 chapter 2 paragraph 201 a 6 for major alterations Not all installations are major consult your local FAA ACO for clarification In Canada Installation of an ELT in an aeronautical product is carried out under a Supplemental Type Certificate STC This 1s a separate regulatory requirement and should therefore refer to Ameri King Document No 451 for the Operations and Instructions for Continued Airworthiness ICA The conditions and tests required for TSO approval of this article are minimum performance standard
73. o z o ct S 202 400 D lt b b UJ see Note 8 Page 1 1330 P 301A 301B 320 605 79 79 x CP 301 u o D u o 2 D sce son ages o Table 1 EU states of Design powered aircraft fixed wing State of Design Manufacturer Evaluation against Annex II criteria Development Role in armed Design Production State of Design TC of Aviation 1 1 55 lt 1 1 75 Comments Yes me Jm 63 TC 18 es 2n Yes TCS 7 un J D tu D D mz b oie ee 312 0 o 90 91 92 93 94 series lt 00 series S251 TCDS 8 Believed to be 52510 Antilope lt lt D o lt D lt D lt D lt 191 PAD S C1 vio HE ej Ol Ss ols CDS 53 TC 9 TC51 E gt 3 3 gt UO n e e S TCDS 135 64 VoWi 10 Albatros WWI A mn es ves No ves lt D 107 series r79B 502 amp 503 0131 all marks NWII Arado Blume WII D MEN 2 Ves Yes 153 Ses TCDS53 TC9 Zelant Gazuit Gazuit Valladeau Y Y 1020 1031
74. on the 121 5 MHz VHF radio No LED light illuminates No buzzer sound 56 Detail Operation Check 241 Monitor 121 5 MHz using the Aircraft Communication Receiver or a Portable Hand Held Receiver Important The Squelch must be turned all the way UP Max to hear he sweep tone on most receivers 2 4 3 Place the Main Switch on the front of the ELT Main Unit in the ON position and verify that the Audio Sweep Tone can be heard on the COM Radio Verify that both the Green ON lights located on the ELT Main Unit and the ELT Remote Unit are flashing Verify the buzzer 1s heard at a flash rate and a beeping sound of 1 second ON 4 seconds OFF Place the Main Switch the OFF position Verify that the Audio Sweep Tone is ceased and the two Green ON lights are extinguished 2 4 3 Place the Main Switch on the ELT Main Unit in the ARM position Wait for 25 seconds While seated at the Pilots normal operating position press the button on the Remote Switch Unit Verify that the Green ON lights 15 flashing and a beeping sound at a rate of 1 second ON 4 seconds OFF and is readily visible from the Pilots operating position Verify that the Audio ELT Sweep Tone can be heard on the Com Receiver Push the RESET button on the Remote Unit Verify that the Audio ELT Sweep Tone is ceased Verify the two Green ON lights are extinguished and the buzzer sound is silent Note Always perform the tests within the first 5 m
75. on the Main Unit should be left at ARM position and the ELT is ready to go Note 1 The ELT switch is make before break Return to OFF for at least 1 sec before changing positions Note 2 Press RESET anytime to turn off unwanted transmission 114 APPENDIX B PERIODIC MAINTENANCE CHECK LIST WITH COMPLIANCE CROSS REFERENCES REQUIREMENTS FAR 91 207 d 91 409 and 43 Appendix D Transport Canada Civil Aviation Part V Airworthiness Standards Chapter 551 104 d 1 VI Details of approved batteries and sources of supply Checks are to be performed every year FAR 91 207 d 91 409 and 43 Appendix D Transport Canada Civil Aviation Part V Airworthiness Standards Chapter 551 104 d 1 VI Battery replacement or recharge instructions Checks are to be performed every year TEST TEST PROCEDURE RESULT Paragraphs Approved Batteries Main ELT Unit Ameri King P N 4500010 1 Remote Switch Unit Duracell DL1 3NB Source of Supply Ameri King 2 5 1 ELT Main Battery Replacement instructions 2 5 2 ELT Remote 115 Unit Battery Replacement instructions 3 4 4 Expiration Date Check Note The Batteries for both Main ELT Unit and Remote Switch Unit are not rechargeable FAR 91 207 d 91 409 and 43 Appendix D Transport Canada Civil Aviation Part V Airworthiness Standards Chapter 551 104 d 1 VI Battery capacity test procedures Tests are to be performed every year FA
76. plus any required allowances may not exceed the design capacity of the structure intended to support it It is important to understand the operational characteristics of the aircraft and consider forces that occur during flight dynamic loading as well as those that occur when the aircraft 15 not in motion static loading For example an aircraft designed without flaps may employ a side slip procedure to lose altitude during which the direction of airflow across the fuselage is not in line with the aircraft longitudinal axis Antenna mountings on these aircraft need to be designed and evaluated for the direction of airflow that occurs during such an operation b Whenever possible an antenna should be mounted to a flat surface Minor aircraft skin curvature can be accommodated with the use of an appropriate gasket but if gaps over 0 020 appear between the base plate and mounting surface use of a mounting saddle is recommended Since antenna systems typically require a ground plane this may be a conductive surface that the antenna mounts to any separation of an antenna from its ground plane may impact performance Contact the manufacturer for recommendations if a gasket or mounting saddle is needed see figure below e Upper skin ref Ss SSS SS a Strnger Stringer 30L ref 30R ref Looking aft up i Scale Full OUT d Mounting screws must never be over torqued in an a
77. properly by its tab Verify the battery pack voltage 15 13 0 5 VDC Ensure that the O Ring seal and the gasket are in place See Figure 16 Place the Transmitter Assembly face down on a bench Press down on the battery case to compress the battery contact springs Replace the four battery retaining screws and lock washers and evenly tighten until the battery case 15 pulled flat against the Transmitter Assembly Remove any existing battery replacement date labels from the battery case and install the new label you prepared in step 3 above in a readily visible location on the ELT After battery replacement a transmitter function test must be performed as described in section 3 3 of this manual RETAINING TRANSMITTER ASSEMBLY SCREWS 4 LOCK WASHERS 4 BATTERY PACK FIXED OPERATION IN AIRCRAFT FORWARD WARNING FOR AVIATION EMERGENCY USE ONLY FOR NORMAL OPERATION MAIN CONTROL SWITCH MUST BE IN POSITION UNLICENSED OPERATION UNLAWFUL To Activate Lift amp flip the switch to the ON position Verify The red light flashes 1 sec on 4 sec off Self Test Lift amp flip the switch from OFF to position Verify The red light must illuminate for 4 sec then extinguishes Wait for an additional 21 sec Pass The red ON light must remain extinguished Fail The red light flashes Please see Operation M
78. the release of the data If you have any questions regarding this authorization contact Mr Carlton Woo Manager Technical amp Administrative Support Staff at telephone number 562 627 5300 or by e mail carlton woo g faa gov or FAX number 562 627 5210 Sincerely Manager Technical and Administrative Support Staff 149 European Aviation Safety Agency EUROPEAN TECHNICAL STANDARD ORDER ETSO AUTHORISATION EASA IM 210 1102 This European Technical Standard Order ETSO Authorisation is issued by EASA acting in accordance with Regulation EC No 216 2008 on behalf of the European Community its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation subject to conditions specified below to Ameri King Corporation 17881 Sampson Lane Huntington Beach 92648 United States in accordance with Commission Regulation EC No 1702 2003 Part 21 Section A Subpart O and ETSO 2C126 2C91a for AK 451 AF AP S Emergency Locator Transmitter with GPS Position interface P N 451 AP S DDP No 451 Revision NC 1 or Subsequent Revisions Deviations Use of DO 160E for environmental testing and use of 406 028 MHz instead of 406 025 MHz as operating frequency Conditions 1 The above ETSO Authorisation holder is only authorised to identify an Article with this ETSO marking whilst remaining in compliance with the conditions r
79. to use when handling leaking batteries 5 Turn off equipment if battery becomes hot Wait for battery to cool before removing from equipment 6 Use batteries only for the application for which they were designed 7 Take warning labels seriously and follow all safety precautions 8 Control battery fires in accordance with instructions on the MSDS Information Source RTCA Document No RTCA DO 227 June 23 1995 Appendix C Lithium Battery Safety Guidelines Ultralife Batteries Inc Li MnO Cells and Batteries January 14 2004 UBI 5135 Rev A All specifications subject to change without notice The information contained herein is for reference only and does not constitute a warranty of performance Contact Ultralife for latest information www ultralifebatteries com 225 2 4 Page 3 of 4 SAFETY PRECAUTIONS FOR LITHIUM MANGANESE DIOXIDE Li Mn0 CELLS AND BATTERIES Observe the following precautions when handling lithium cells and batteries A WHEN USING THE BATTERY 1 Do not store batteries with other hazardous or combustible materials 2 Do not heat or incinerate batteries Do not dispose of batteries with other waste unless permitted by applicable regulations 3 Do not open puncture crush disassemble or subject batteries to physical abuse 1 Lithium cells and batteries may get hot explode or ignite and cause serious injury if exposed to abuse conditions Be sure to follow the safety warnings listed be
80. transmitting The ELT can be tethered to a survivor or a life raft It is designed to aid the Cospas Sarsat satellite and SAR teams in locating the crash site or survivor s The model AK 451 AP consists of an ELT main unit with an integral antenna remote switch unit interconnect wiring assemblies an audible buzzer monitor a mounting tray velcro holders and portable soft case The ELT AF has an automatic activation G Switch It 15 activated automatically upon a crash or manually operated If for any reason a fixed mounting 15 not required the ELT AF AP be used as a Portable Device due to it 5 manual operated hand use Portability Check Local and or national regulations for this issue I5 d Survival ELT S Category A The ELT 5 shall survive the shock impact and crush tests after a crash This type of ELT does not have automatic activation G Switch and 16 intended to be removed from the aircraft It functions as an ELT P Flashing light indicator on the ELT 15 provided to alert the user that the ELT has been activated and 15 transmitting The ELT can be tethered to a survivor or a life raft It is designed to aid the Cospas Sarsat satellite and SAR teams in locating the crash site or survivor s The model AK 451 S consists of an ELT main unit with integral antenna and a portable soft case The ELT S has no automatic activation G Switch It is activated manually only 16 The Main Unit features
81. without d aircraft that have been in the service of military forces unless the aircraft is of a type for which a design standard has been adopted by aeroplanes helicopters and powered parachutes having no more than two seats a maximum take off mass as recorded by the i 300 kg for a land plane helicopter single seater or ii 450 kg for a land plane helicopter two seater or iii 330 kg for an amphibian or floatplane helicopter single seater or iv 495 kg for an amphibian or floatplane helicopter two seater provided that where operating both as a floatplane helicopter and as v 472 5 kg for a land plane two seater equipped with an airframe mounted total recovery parachute system vi 315 kg for a land plane single seater equipped with an airframe mounted total recovery parachute system and for aeroplanes having the stall speed or the minimum steady flight speed in landing configuration not exceeding 35 knots f single and two seater gyroplanes with a maximum take off mass not exceeding 560 kg New Annex Il EASA list Issue 10 25 Feb 2008 Page 1 of 2 204 g gliders with maximum empty mass of no more than 80kg when single seater 100kg when two seater including those which are foot h replicas of aircraft meeting the criteria of a or d above for which the structural design is similar to the original aircraft i unmanned aircraft with an operating mass of no more than 150 kg j any ot
82. 06 MHz distress beacons to e Obtain guidance regarding national regulations concerning beacon coding and registration it should be noted that there are many beacon message protocols which are compatible with the Cospas Sarsat System it 1s the responsibility of National Administrations to select the protocols for use within their jurisdiction and e Obtain the necessary forms to register the beacon 128 Process for Registering Beacon in Cospas Sarsat International 406 MHz Beacon Registration Database IBRD Your country may have elected to allow you to directly register your beacon in the International 406 MHz Beacon Registration Database IBRD available online at www 406registration com Click here for a list of these countries The IBRD became operational on the 16 January 2006 It provides capability to register 406 MHz distress beacons and has extensive online help capabilities Individual beacon owners may register their beacons and select their own passwords during the registration process if this use of the IBRD has been allowed by their national Administration You will need the following information to register a beacon Beacon Hexadecimal Identification 15 Hexadecimal characters Owner name and phone number Emergency contact name and phone number Vehicle type selectable from a menu Vehicle name MMSI call sign or identification number except for PLBs Cospas Sarsat will only accept beacon registration
83. 1 5 MHz homer 112 1 3 3 X 3 3 3 3 3 9 JE JE 3 9 JE 9 JE Y 3 9 JE JE 9 9 JE 9 JE JE JE 9 9 JE 9 9 9 JE 9 9 9 9 9 9 FE d E Latitude Offset Sign 113 0 Latitude Offset Minutes 2 114 118 00010 3 3 3 X 3 JE JE 9 9 JE JE JE I JE JE 9 9 9 9 9 JE 3 JE JE JE JE 9 9 9 9 9 9 9 9 9 9 Latitude Offset Seconds 48 119 122 1100 AMERT KING AK V1 xx Longitude Offset Sign 123 0 3 3 3 3 3 3C 3 JE 3 3 JE 3 JE 3 JE JE C JE JE 9 9 9 JE 9 9 9 9 9 9 Longitude Offset Minutes 0 124 128 00000 Longitude Offset Seconds 8 129 132 0010 2 Encoded 133 144 000111101001 BCH 2 Calculated N A 000111101001 FFFE2F97142CC16321EEC2054CF50B0021E9 30 Hex Digits coming from the ELT after 50 seconds Composite Latitude 33 70333333333333 Composite Longitude 117 99777777777778 Degrees Connected 0 10 34 Auto detect 9600 8 N 1 SCROLL CAPS NUM Capture Print echo Degrees North N A 115 10 2E285982C6FFBFF wm m Figure 10 Contact Us Related Sites Location 700 Gauchetiere West Suite 2450 Montreal Quebec 5M2 Canada Email mail cospas sarsat int Tel 1 514 954 6761 Figu
84. 13 30 Figure 2 1 Mounting Tray for ELT AF AP P N 450 013 31 Figure 2 1 Mounting Tray for ELT with integral antenna amp ELT S intret e bane aen auia 39 Figure 2 1 1 Optional Adapter Tray for ELT AF AP P N 450 013 1 38 Figure 2 2 Holder for ELT AF AP P N 450 014 3l Figure 2 2a Holder for ELT AP with integral antenna 30 Figure 2 3 Dimensional Drawing for Mounting Tray for ELT Main Unit with Optional Multi axes Acceleration Switch 107 Figure 3 Mounting Tray with Velcro Holder and Portable Antenna tor BET CAB AP 32 Figure 4 Reserved Figure 5 Antenna ground plane for nonmetallic 34 Figure 6 Whip Antenna 451017 1 enne 37 Figure 6 1 Reserved Figure 7 Rod Antenna 451017 2 0000000222 0 0000000000005 41 Figure 7 1 Rod Antenna 451017 2 2220200044400000 0 5 42 Figure 8 Blade Antenna 451017 3A esses nennen 45 Figure 9 Integral Portable Whip Antenna 451017 45 Ant ground plane is not 47 Figure 10 ELT Remote Switch Installation 49 Figure 10 1 Mounting bracket for ELT R
85. 2 The installation of this modification by third persons is subject to written permission of the approval holder and holding and disposal of the approved appropriate documentation 3 The approval holder shall fulfil the obligations of Part 21 Paragraph 214 108 MINOR CHANGE APPROVAL 10026863 Niessler Handelsagentur EASA Form 93 Issue 1 1 3 159 European Aviation Safety Agency This Approval shall remain valid unless otherwise revoked For the European Aviation Safety Agency Date of issue 18 08 2009 Roger HARDY Certification Manager General Aviation MINOR CHANGE APPROVAL 10028863 Miessler Handelsagentur EASA Form 83 Issue 1 2 2 160 Annex II Type EASA has produced this list of Annex II aircraft strictly for information purposes only It aims to describe the exclusions from the lists of EASA transferred aircraft EU and non EU It is based on information received from several authors internal and external to the Agency Whilst every care has been taken in preparing the contents of the list to avoid errors the Agency makes no warranty as to the accuracy completeness or currency of the content The Agency shall not be liable for any kind of damages or other claims or demands incurred as a result of incorrect insufficient or invalid data or arising out of or in connection with the use copying or display of the content to the extend permitted by European and national laws The information contained in the list shou
86. 4 CFR 21 611 a with minor changes submittal intervals not to exceed six months Notification of changes should be made prior to shipment As recipient of this authorization you are required to report any failure malfunction or defect relating to this authorization in accordance with the provisions of 14 CFR 21 3 The report should be communicated initially by telephone to the Manager Technical and Administrative Support Staff ANM 103L 562 627 5300 within 24 hours after it has been determined the failure has occurred and followed up with a written notice FAA Form 8010 4 Malfunction or Defect Report or other appropriate format is acceptable in transmitting the required details This authorization is not transferable to another person or location and is effective until surrendered withdrawn or otherwise terminated by the Administrator This authorization pertains only to manufacturing operations at the above address This office must be notified at least 30 days in advance of any proposed facility relocation to preclude interruption while awaiting quality control approval of that facility As required by 14 CFR 8 21 613 b you must also notify the FAA when you no longer manufacture a TSO approved article Please note that technical data retained by the FAA may be subject to Freedom of Information Act FOIA request As such this office will notify you of all such request pertaining to your data and afford you the opportunity to defend
87. 5 875 Optional Adapter Tray for ELT P N 450 013 1 for ACK Tech Artex Narco Pointer ELT Retrofit Figure 2 1 1 1B Whip Antenna Model 451017 Fieure 6 38 37 Figure 2 1a Mounting Tray for ELT AP with integral antenna and ELT S P N 450 013 2 39 2 2 2 2 2 Rod Antenna Installation 451017 2A The 451017 2A Rod Antenna delivers optimum performance only when installed correctly To ensure adequate structural strength of the aircraft for associated air loading during flight use of a backing plate or doubler not supplied may be required Refer to FAA Advisory Circular 43 13 2B for guidance It is the responsibility of the installation agency to determine the appropriate and adequate antenna installation The 451017 2A Rod Antenna is designed to provide ELT transmissions from a single BNC Female coaxial connector Location The 451017 2A Rod Antenna must be mounted on the top of the aircraft to assure maximum visibility of satellites 406 MHz The best location is the upper aft portion of the fuselage It should be mounted vertically and away from projections such as a propeller tail surfaces or the shadow of larger antennas Installation Preparation 1 Prepare the surface for antenna installations in such a manner to ensure a ground contact of less than 0 003 If bare metal surfaces are needed for surface preparation they should be treated with Alodine 1200 or similar application to
88. 6 MHz ELTs transmit a Unique Identifier Number UIN when activated This UIN is programmed in the ELT based on the country in which the Aircraft operates ELT Registration provides the Search and Rescue SAR forces with emergency contact information and will speed the launch of a rescue operation The National Authorities use the information to verify if an actual emergency exists Valuable Search and Rescue resources are wasted every year responding to false alarms For ELTS that not registered SAR authorities will not know who you or who to contact regarding additional information of your current situation This could delay the launch of a rescue operation A National Authority is the governmental body that 15 responsible for ELT Registration Database administration for the country for which the ELT is programmed Supplied with the ELT are pre stamped envelope and ELT registration form with 15 digit hex ID ELT programmed code and Country 3 digit code This hex ID must be the same as the 15 digit hex ID shown on the ELT name plate It is important to fill in the sticker This ELT belongs to A C Tail rd 4 1 2 Where to register The owner of a 406 MHz ELT should register it with the National Authority of which the ELT was programmed typically the country where purchased regardless of where you use your ELT Each ELT is programmed with a UIN for the country where the unit is shipped and will only be accepted for registration
89. 8 Table 3 Sailplanes and Powered Sailplanes EU and non EU Evaluation against Annex II criteria eyes gi eui a pedi of Aviation lt lt Comments 21 series pecs ves 56321 NUM series SS N N So 5 lt 5 NUNC Regarded as development aircraft 2 as hc lt chweitzer USA irmi uild Elliots of Newbury ON Shenstone Slingsby Swales All e 1 26 2 32 2 3 be Abbott Baynes Birmingham G Prototype only DIT 3 ih 0154 olaf 2 2 72 ert o 2 UE il WwW New Annex EASA list Issue 10 25 Feb 2008 Page 7 of 7 199 Table 4 Rotorcraft EU and non EU State of Design Evaluation against Annex II criteria Historic Development of Role in armed De oduction State of Design TC Eurocopter Alouette II Germany J Wagner FJ SKY TRAC Yes 3022 RC Helicopter Technik Italy Agusta Bell AB 47 all variants A85 86 113 114 100 112 115 125 148 88 A99 A127 A103 A110 _____ _____ oe Poland TOES BC 073 E E E a E s _ Wessex 5 fs 9 D ug lt lt P ois er ct tu er New Annex EASA list Issue 10 25 Feb 2008 Page 1 of 2 200
90. D WARNING FOR AVIATION EMERGENCY USE ONLY UNLICENSED OPERATION UNLAWFUL X D C SW UL UIN po U Verify ELT swept tone heard on 121 5 MHz VHF Radio Green ON LED is on after 4 sec for 1 sec then off 4 sec Self Test Lift amp flip the switch to ARM position Verify Green ON LED is on for 4 sec then off Wait for an additional 21 sec If Pass Green ON LED stays off No swept tone on 121 5 Radio If Fail Green ON LED flashes See Operation Manual for details eck G switch Next If pass Self Test shake ELT back and forth rapidly in direction of FORWARD arrow ELT must activate and swept tone heard on 121 5 Radio THIS SATELLITE ELT ONLY FLOATS W FLOATING COLLAR Front label for AK 451 AF AP with dual antennas and S xx WARNING USE ONLY DURING SITUATIONS OF GRAVE AND IMMINENT DANGER LITHIUM BATTERY PACK NON RECHARGEABLE P N 4500010 1 FOR USE ON Model AK 451 AF AP S RTCA DO 160E Environmental Categories FIXBQ27 227 227 XXXXXXXXXXXXXXXXXX Replace Replace Main battery Batteries pack after D one o culmulative hour of use or by date shown Battery type Lithium LiMnO2 NEVER CHARGE SHORT CIRCUIT PUNCTURE DEFORM INCINERATE OR OPEN DO NOT SUBMERGE IN WATER OR HEAT ABOVE 85 C REMOVE WHEN DISCHARGED Back label 84 WARNING FOR AVIATION EMERGENCY USE ONLY UNLICENSED OPERATION UNLAWFUL To Activate Li
91. Document IM 451 Rev NC 4 1e dated November 30 2008 INSTALLATION AND OPERATION MANUAL FOR MODEL 451 Series 406 MHz ELT Emergency Locator Transmitter with GPS NAV position AMERI KING CORPORATION 17881 Sampson Lane Huntington Beach CA 92648 Tel 714 842 8555 Fax 714 842 4235 Email ameriking9 aol com www ameri king com REVISION TABLE REVISION DESCRIPTION wu ui in DATE Add PLB Programming Para 1 2 1 d and Product Pictures NC 1 added 9 5 07 1 2 4 1 1 2 4 2 1 2 4 3 1 2 4 4 revised Para 2 4 5 deleted Add Volume 2 Ve 9 10 07 for AK 451 PLB for clarity Para 1 2 1 c and 3 1 c revised Para 3 3 5 added 9 11 07 Volume 2 Para 4 amp 4 3 2 revised nc 4 Para 1 2 1 b and TN K V 9 26 07 2 2 3 revised Pata 1 2 2 2 2 2 4 6 FAA form 337 revised TSO C142 KV 6 16 08 information RTCA DO 160E form for TSO C 227 deleted Revise Para AK 451 ELT Sets with no GPS NAV Position NC 4 1a 2 5 1 amp 3 5 to KV 10 22 08 meet Canadian Ameri King Descripien Antennas compliances P N p jede NC 4 1b EASA Review KV 10 31 08 AK 451 AF AP ELT Set for Whi Por General Aviation Whip A p Antenna P N AK 451 2 U S A Registration 451017 1B EASA T C AK 451 AF AP ELT Set for NC 4 1c approved KV 11 26 08 updated Whi Por Canada General Aviation Canadian AK 451
92. Dummy 50 ohm Load should be used Connect the 451 with ELT Computer Test Set TS 451 e Turn the switch of the ELT to ON position e Verify the following setting See Figure 20 From the Hyper Terminal window or the equivalent RS 232 window Click File Properties Settings tab Click OK to go back to Hyper Terminal window AK 451 Properties Connect Settings Function and ctrl keps act az Terminal keus Backspace key sends 6D Del C2 Etrl H Space Emulation ______ ANSI Telnet terminal Play sound when connecting or disconnecting Input Translation ASLII Setup Figure 20 Verify parameter setting Waiting for 50s verify the 36 Hex digits 1gnore first 6 digits The last 30 Hex digits will be used for Cospas Sarsat Decode program in order to see the Latitude Longitude Position 93 Note When used with ELT s that are programmed for Standard Location 24 bit protocol the ELT to be program itself to the aircraft s 24 bit address This feature will allow the ELT to be transferred between aircraft Re register the ELT with the Search and Rescue authority is required This makes maintenance of the ELT a simple matter of replacing the ELT Note There is no electronic connection between TCAS or Mode 5 systems and the ELT only the ID number is common 3 5 PERIODIC MAINTENANCE INSTRUCTION FOR CONTINUED AIRWORTHINESS FOR CANADIAN INSTALLAT
93. EU States of Design powered aircraft fixed wing Sailplanes and Powered Sailplanes EU and non EU Rotorcraft EU and non EU Balloons and Airships EU and non EU Change record from Issue 6 Issue 6 dated 6 August 2007 1 wN Removal of Apex Robin CEA DR220 221 250 253 from the list at the request of Apex and DGAC France borderline case and addition to list of EU transferred aircraft types Addition of Yak 50 on the basis of service with DOSAAF and similarity with Yak 52 CIS Addition of Netherlands state of design sailplanes on the basis of year of design and construction Addition of Gardan GY100 Bagheera France on the basis of it being an R amp D prototype Issue 7 dated 8 August 2007 1 Deletion of Dragonfly Model 333 from Italy rotorcraft at request of ENAC and TC holder due to weight increase New Annex Il EASA list Issue 10 25 Feb 2008 Page 2 of 3 162 Issue 8 dated 13 September 2007 1 Removal of certain American Champion Bellanca 7 series on the basis of their production continuing after 1975 some being in current production 2 Removal of AS202 32TP from Austria it is correctly listed under Switzerland 3 Correction of spelling of A Comte Switzerland 4 Correction of BG100 to BG135 UK sailplane 5 Removal of SZD 9 bis Bocian 1D E Polish sailplanes 6 Removal of Scheibe Bergfalke Spatz Specht and Sperber German sailplanes on the basis of the existing valid EASA TC
94. F AP Whi Por WW the Diamond Aircraft DV20 and DA20 A1 VLA oproval Note EASA Zulassungsvermerk Nr P EASA A C 12674 Page 1 2 155 Niessler Handelsagentur F Hanuschgasse 8 2345 Brunn a G Reference of Documents Installation and Operation Manual Dem AMM 4 EON 003 Installation Instructions Aircraft Maintenance Manual Supplement 24 07 09 24 0709 Page 2 2 156 European Aviation Safety Agency European Aviation Safety Agency MINOR CHANGE APPROVAL 10027068 Project reference 0010000519 001 Reference P EASA A C 12672 This Approval shall remain valid unless otherwise revoked This Minor Change Approval is issued by EASA acting in accordance with Regulation EC No For the European Aviation Safety Agency 216 2008 on behalf of the European Community its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation and in accordance with Commission Regulation EC No 1702 2003 to Date of issue 03 09 2009 Niessler Handelsagentur Roger HARDY Ferd Hanuschgasse 8 Certification Manager 2345 BRUNN AM GEBIRGE General Aviation AUSTRIA and certifies that the change in the type design for the product listed below with the limitations and conditions specified meets the applicable Type Certification Basis and environmental protection requirements when operated within the conditions and limitat
95. Far insormation on ma U S Search amp Rescue Satelle Axded Tracking system please vigil GOV OMB Auth Expires 127 APPENDIX G International 406 MHz Beacon Registration Database IBRD Countries Allowing Individual Registration Website www cospas sarsat com Path to this page English Beacons Beacon registration amp SARSAT COSPAS lt gt Home Description Status Beacons Documentation Management Registering a 406 MHz Beacon Register a beacon in the IBRD FAQs about beacon registration Countries allowing individual registration in the IBRD SAR Service Access to the IBRD Account and password request template User Guides It is crucial that 406 MHz distress beacons be registered in recognized beacon registration databases which will be accessible to search and rescue authorities at all times The information contained in these databases concerning the beacon its owner and the vehicle vessel on which the beacon is mounted is vital for the effective use of Search and Rescue resources The proper registration of a beacon could make the difference between success and failure of a search and rescue mission Click here for examples of how the registration information may be used to enable the proper SAR response Process for Registering a Beacon If the Administration has identified a Registration Point of Contact Contact the representative in your country responsible for 4
96. Ground P1 23 x RJ12 6P6C 2 Figure 14 1 Wiring Diagram for AK 451 with Optional Multi axes switch with 4 wire interconnecting ELT Main Unit and Remote Switch Unit 108 ON La Audible Buzzer 451 018 3 8 T Adapter 4510181 RJ12 6P6C RJ12 5P6C Remote Unit 451 004 450 0041 Remote Wiring Cable Assembly 1 Remote RESET SW Lo Remate QN SW Lo Remate ON Light La 3 B vdc Qui c o amp C5 B RJ12 6P6C P2 T Adapter RJ12 6P6C 451 0181 1 e 2 s 4 11 E _______ 4 2 p A Wiring between P1 and P2 must be as short as possible 12 max RJ12 6P6C ii to ensure no damage upon crash For crash safety Pinout 6 1 j 4 Figure 14 1f Wiring Diagram for AK 451 with Optional Multi axes G switch with 2 wire interconnecting ELT Main Unit and Remote Switch Unit 109 BLACK OM Lo Audible Buzzer 451 018 3 8 T Adapter 451 0181 1 R J12 6P8C 2 3 Remote Unit Remote ON SW Lo NAZ 451 004 450 0041 Remote Wiring Cable Assembly 5 232 Rxd Hi OPTIONAL MULTI DC Ground AXES G SWITCH Remate RESET SW Lo 1 Remote ON SW L 7 2 Zo Remote ON Light La E IL T i2 8 Vdc 4 ELT Model AK 451 RJ12 6P6C TAN RE 232 Fixd Hi RJ12 6P6C DC Ground A Existing Aircraft 4 wire or 5 wire ELT Systems Artex Pointer etc Pino
97. H260 Super TCDS 70 TC 21 Broussard Type 1 j 5130 MS138 15181 MS185 5230 MS315 15317 es es TCDS 66 MS341 3 ______ 5 WWII Yes Yes Yes J MS733 CDNI Yes Yes Yes TC 3 TCDS 19 production x Me108 Yes TCDS 45 lt er N ur 2 4 T D D a c m rt lt b o et Rebirth GA o o 5 m 2 tu gt 3 D I mi D o 0 tu o 2 o o w 5 2 tU D New Annex Il EASA list Issue 10 25 Feb 2008 Page 5 of 19 168 Table 1 EU states of Design powered aircraft fixed wing I Design Production State of Design TC and Comments 1100 series Ex Me208 Yes Yes Yes TCS 89 Rebirth GA post WWII 1200 series d O cs SALS Yes ALAT TCDS 5 amp 9 competition _ Yes ____ ____ 7 41 TCDS 48 Mes ves i vs es Yes Yes Yes TCDS 6 See Belgium m ves CDs 33 d es IrcDs18 Pes ves TCDS 28 Pes Ves TCDS 75 TC20 Yes Yes TCDS 46 TC 7 series i x ML250 Yes Yes TCDS 92 TC 29 Rubis otez _______ ___ 1 es 84 840 841 842 Yes Yes TCDS 104 TC 36 series New Annex Il EASA list Issue 10 25 Feb 2008 Page 6 of 19 T N E J
98. HIBITED 94 PERIODIC MAINTENANCE at least every year Note These tests should be performed only within an RF Screen Room or Facility providing shielding of RF Emissions Using of ELT Test set TS 451 or equivalent test equipment is acceptable 3 5 1 Regular Periodic Maintenance Test Perform Periodic Maintenance Test per paragraph 3 4 above including all Test paragraphs 3 4 1 through 3 4 10 In addition to the Periodic Maintenance requirements prescribed in Paragraph 3 4 the following Performance Testing must be performed at least every year to comply with Canadian Aviation Regulations CAR Standards Part V Airworthiness Manual 571 Appendix 3 5 2 Power Output Test Performance Testing NOTE Using of ELT Test set TS 451 or equivalent test equipment is acceptable 3 52 1 121 5 243 0 MHz Power Output Connect the equipment as shown below ELT BNC Applicable Spectrum Analyzer top attenuator Connector Note Use as fresh battery pack 12 5 0 5 nominal or a 2 amp 12 5 VDC power supply as power source The test equipment specified in the following steps 1s only a recommendation The use of other manufacturer s models of test equipment capable of providing equivalent measurement results is acceptable Set the Spectrum Analyzer as follows Center freq 121 5 MHz span 1 MHz Resolution bandwidth 1 MHz Vertical display 10dB Div Sweep Auto Peak Avg Peak Reference level 30 dBm Time D
99. IEW BNC CONNECTOR FEMALE 0 60 DIAMETER CONNECTOR CLEARANCE HOLE ___ 0 166 DIA THRU C SK 100 DEG x 0 325 DIA FAR SIDE 4PLCS 0 177 DIA CLEARANCE HOLE REQUIRED 2 90 1 625 BOTTOM VIEW MEASURING UNIT INCH Finish White Polyurethane Paint over Intumnescent Frequencies 121 5 243 0 406 0 MHz VSWR 121 5 MHz 1 3 1 max 243 0 MHz 1 3 1 max 406 0 MHz 1 3 1 max Polarization Vertical Radiation Pattern Omnidirectional Power rating 25 Watts Mating connector BNC Female Impedance 50 Ohms Nominal Figure 7 Rod Antenna 451017 2 41 35 01 1 38 30 004 ETCHING IDENTIFICATION Adh sive identification label ETSO 6901 10511 FLAT JOINT 045 35 01 77 1 38 THICKNESS 2 0 07 NEOPRENE FORM 800 0 8 1 2 OSE XI y ASE PLATE AG5 TREATED WITH CLEAR ALODINE 1200 21 7 0 85 3 25 0 004 1006 SI ZZ 0 005310 063 S b X PROFIL EMBASE BASEPLATE PROFILE 35 1 38 2 0 9101 LASS COMPOUND THERMO PLASTIC 122 4 8 Figure 7 1 Rod Antenna 451017 2A 1 42 2 2 2 2 3 Blade Antenna Installation 451017 3A Installations must be made by qualified personnel and in accordance with Federal Regulations The 451017 3A Blade Antenna delivers optimum performance only when installed correctly To ensure adequate structural strength of the aircraft for associated air loading during flight use of a backing plate or doublers not s
100. ION REFERENCES Canadian Aviation Regulations CAR Standards Part V Airworthiness Manual AWM 571 Appendix G Refer to Appendix B for Maintenance Check List with Compliance Cross References PURPOSE Instructions for continued airworthiness which shall include as a minimum details of approved batteries and sources of supply battery replacement or recharge instructions battery capacity test procedures 1f applicable transmission or functional test procedures procedures necessary to accomplish the performance tests specified in Chapter 571 Appendix and for 406 MHz ELTs instructions to verify the aircraft 24 bit address protocol as applicable Appendix G a Corrosion Inspection b Operational Testing c Performance Testing d Battery Replacement and Recharging e Shipping IMPORTANT NOTES The ELT must be performance tested within the 12 month period preceding installation in an Aircraft and within 12 months intervals thereafter The following Supplemental Installation Periodic Maintenance requirements must be complied with when installing the Model AK 451 ELT in Canadian Aircraft SUPPLEMENTAL INSTALLATION Installation and maintenance of the ELT must comply with Transport Canada Airworthiness Manual Chapter AWM 551 104 f 4 Transmitter Remote Control A Placard shall be fabricated and installed near the Remote Unit which states FOR AVIATION EMERGENCY USE ONLY UNAUTHORIZED OPERATION PRO
101. IS 2 000 la 4 6 0 5 050 Figure 11 Remote Audio Buzzer Monitor P N 451018 R O50 4 PLS Drill 187 3 PLS Figure 10 1 Mounting bracket for ELT Remote Unit Continued 49 50 Figure 11 1 Buzzer may be fastened directly onto the Remote Switch Unit 2 2 4 Wiring interconnecting harness The wiring cable is 25 feet long if the cable is too long looping the wire in order to have shorter wiring 1s acceptable Please contact Ameri King if you need shorter or longer wiring cables Use only Ameri King supplied interconnects wiring cables 51 Note The interconnecting wiring is a straight wiring configuration i e Pin 1 to 1 Pin 2 to 2 Pin 3 to 3 and Pin 4 to 4 Pin 5 to 5 To verify straight wire configuration look at both Modular plugs RJ 12 side by side both clips of the plugs must be on the same side You must see wiring color codes Yellow Green Red Black Orange alternatively on both plugs The wiring configuration 15 not a telephone application Telephone application 15 a cross wire configuration 1 e Pin 1 to 6 Pin 2 to 5 and Pin 3 to 4 To convert from cross wire to straight wire configuration just simply reverse either plug upside down Pin Color 1 Brown 2 Yellow 3 Green 4 Red 5 Black 6 Orange Note Pins 1 and 6 are not connected RJ12 6P6C RJ12 6P6C Pinout Pinout Figure 12 1 Interconnecting Wiring Cable between ELT Remote Unit and
102. K 1 xx x serial mode E Password Must be typed in within 20 seconds connected 01 this menu 02 disconnect 03 read ID 04 read SN 05 selftest 06 write ID 19 read SEL 20 write SEL VHF gt _ Step 5 To read ELT ID Use command 03 Step 6 View message ensure that all applicable information is correct country code aircraft ID etc Step 7 The 15 digit ID hex ID for example 2E28598228FFBFF should match what is shown on the ELT product label This 1s the 15 digit hex ID Unique Identification Number or UIN that is used to register the ELT 3 4 9 Verification of Registration Note This verification is not mandatory per FAR 91 207 d however Ameri King strongly recommends that it be performed as part of periodic maintenance at least every year Check ELT for signs of registration In the US NOAA supplies beacon registration label that 15 applied to the ELT when it is registered The following address should be used to register and obtain information on how to register 406 MHz ELT s in the United States SARSAT BEACON REGISTRATION E SP3 RM 3320 FB 4 NOAA NESDIS 5200 Auth Rd Suitland MD 20746 4304 http www sarsat noaa gov 89 The Ameri King website also contains information
103. LT SPRAY Category S 48 hours exposure to the Salt Fog and 48 hours drying 22 Figure B 3 D view of ELT 23 1 4 ACCESSORIES SUPPLIED 141 INSTALLATION KIT PART NO DESCRIPTION 450004 Remote Switch Control Unit 4510041 or 4500041 Remote Wiring Cable Assy 451013 or 450013 450013 1 Mounting Tray 451014 or 450014 Velcro Holder 4510171 Coaxial cable assembly 451018 Audible Buzzer Monitor 4510181 T Adapter connector 451017 1 2A 3A 45 Antenna Assembly 4510131 Optional Floating Collar 5 451 Soft Case SC 451 T Tether 1 5 FCC LICENSE REQUIREMENT In the U S A Not required per FCC Note Radio station license of the aircraft 15 required by telecommunication regulations in several European countries 24 SECTION II INSTALLATION AND TEST 2 1 UNPACKING AND INSPECTING EQUIPMENT Handle with extreme care when unpacking the equipment Visual inspection of the equipment for evidence of damage incurred during shipment Any claim should be promptly filed with the transportation company Save the shipping container to substantiate the claim Retain the container and packaging material for possible future use 222 MECHANICAL INSTALLATION The ELT is designed with the installer in mind All accessories which are required for complete ELT system installation are provided including Mounting Tray Velcro Holder Coaxial Cable Assembly and Wiring Cable Assembly Because of the critical nature of an ELT it
104. Lycoming Fixed Pitch Sensenich or McCauley Propeller 7 series as follows A 759 7ECA w 100HP Continental O200A McCauley propeller 7EC w 90HP Continental and 1300 1450 or 1500 Ibs gross weight 7CCM 7DC S7DC S7EC TGC 7GCB 7GCBA 7HC 7JC 7KC New Annex Il EASA list Issue 10 25 Feb 2008 Page 5 of 10 187 Table 2 Non EU states of Design powered aircraft fixed wing Evaluation against Annex II criteria MEME ae ea eo E el ee a ava of Aviation force lt omments ee E ee Rearwin Consolidated Fleet series Convair ________ DL s ves ves Curtiss P 30 series e wm __ ______ _ __ _ _ _ He BE ___ O I A 669 feiss ____ ___ ves ves A792 pes ves ves uam fe e e e Ercoupe 415 series F A 787 1 Forney Alon A 2 Univair 2 718 Fairchild Model 24 UC 61 A 706 Forwarder A 707 220 JPT 19A WWII Ses ves 24 series Yes Yes A 535 A 706 A 707 Universal New Annex Il EASA list Issue 10 25 Feb 2008 Page 6 of 10 188 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Ev
105. NTY OR REPRESENTATION OF ANY KIND WHATSOEVER EXPRESSED OR IMPLIED AND ALL IMPLIED WARRANTIES INCLUDING ANY WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE ARE HEREBY DISCLAIMED AMERI KING CORP S MAXIMUM LIABILITY HEREUNDER IS LIMITED TO THE PURCHASED PRICE OF THE PRODUCT IN NO EVEN SHALL AMERI KING CORP BE LIABLE FOR ANY DAMAGES OF ANY NATURE ARISING FROM THE SALE OR USE OF THE PRODUCT WHETHER BASED IN CONTRACT TORT STRICT LIABILITY OR OTHERWISE 5 2 REPAIR SERVICE equipments manufactured by Ameri King Corp must be repaired at the facility of Ameri King Corp The entire repair service shall be performed and completed within 3 days upon repairing estimate 15 approved by equipment user or installation dealer IMPORTANT NOTE In order to prevent accidental activation of the ELT during transit the ELT ON OFF ARM Main Switch must be set in the OFF position Note The ON OFF ARM Switch is lever locked type 5 3 FACTORY COMPREHENSIVE TEST SERVICE Factory Comprehensive Test Service including Digital Message GPS Position G Switch activation levels testing RF Peak Effective Radiated Power Operating Carrier Frequency Modulation Characteristics Duty Cycles and Activation Monitor are available There is a service charge for this service equipments returned for Factory Comprehensive Test Service must be sent freight prepaid 105 APPENDIX A RETROFIT INSTRUCTIONS FROM AK 450 TO AK 451 Old Model
106. No AK 450 AF AP ELT 121 5 243 MHz New Model No AK 451 AF AP ELT 406 121 5 243 MHz RETROFIT INSTRUCTIONS 1 Swap the followings items ELT with mounting tray Antenna with Coaxial Cable Remote Switch Unit with Buzzer Note 1 All mounting holes and cut out holes are exactly the same Note 2 Wiring Harness between ELT and Remote Switch Unit is exactly the same i e Do not change the wiring harness It is OK to use the existing AK 450 wiring Note 3 Adding a new Buzzer to be mounted anywhere in the cockpit i e Tie wrap into the aircraft Wiring Harness or Fasten onto or behind the instrument Panel or fasten on the Remote Switch Unit 2 Register with NOAA or IBRD or National via on line or mailing the Registration Form using the provided pre stamped envelop 106 To remote switch control unit P N 450004 451 0041 450 0041 Remote 5 Cable Assy 25 Length 3 450 000 1 Optional Multi Axes Acceleration Switch AK 451 ELT Main Unit 5 25 230 DIA HOLE 6 SCREW 4 PLS C FORWARD A L Notes 1 The Mounting Tray for both ELT Main Unit and Optional Multi axes Acceleration Switch must be installed on the Horizontal Plane The Optional Multi axes Acceleration Switch must be installed next to the ELT Main Unit for crash safety 2 In addition to the main Acceleration Switch which located inside the ELT Main Unit the remote Optional Multi axes Acceleration Switch Assy conta
107. Paragraph d Part 43 Appendix D i FAR Part 91 407 14 CFR Parts 25 and 29 Docket No 26180 Amendment Nos 25 82 29 33 FAA ACTION NOTICE A 8150 3 FAA Part 91 207 d Each emergency locator transmitter required by paragraph a of this section must be inspected within 12 calendar months after the last inspection for 1 Proper installation 2 Battery corrosion 3 Operation of the controls and crash sensor and 4 The presence of a sufficient signal radiated from its antenna INSPECTION d Each emergency locator transmitter must be inspected within 12 calendar months after the last inspection for INSPECTION 1 Proper installation According to the ELT mfg instructions and According to FAA supplemental inspection procedures in Notice A8310 1 According to AC91 44A INSPECTION Remove all interconnections to the ELT unit and ELT antenna Visually inspect and confirm proper seating of all connector pins Special attention should be given to coaxial center conductor pins which are prone to retracting into the connector housing e Remove the ELT from the mount and inspect the mounting hardware required mounting hardware should be installed and secured INSPECTION 2 Battery corrosion Gain access to the ELT battery and inspect No corrosion should be detectable Verify the ELT battery 15 approved and check its expiration date INSPECTION 3 Operation of the controls and crash sensor and Activate the ELT using
108. Perchlorate LiClO 7791 03 9 None Listed 1 Important Note The materials in this section may only represent a hazard if the integrity of the battery is compromised or if the battery is physically or electrically abused Product Emergency Locator Transmitter ELT Battery Pack containing lithium manganese dioxide cells Each battery pack has a net weight of 1 6 lbs Electrochemical system Each battery pack contains 13 2 grams of lithium metal Each battery pack is diode protected and fused ULTRALIFE BATTERIES MSDS023 FA1284 Rev F OCT 01 2007 Page 1 of 6 Rev Date 31 2007 219 Section 3 Hazards Identification 3 1 Emergency overview May leak and or flame if opened recharged connected improperly or disposed of in fire 3 2 Potential health effects Skin contact may cause irritation and absorption Contact with raw lithium may cause burns Routes of entry Inhalation or ingestion of electrolyte may have toxic effects Acute exposure Electrolyte may irritate skin and eyes Effects of chronic exposure Electrolyte contains a teratogen 3 3 Perchlorate Material special handling may apply See www dtsc ca gov hazardouswaste Section 4 First Aid Measures Electrolyte Contact Skin Immediately flush with plenty of water for at least 15 minutes If symptoms are present after flushing get medical attention Eyes Immediately flush with plenty of water for at least 15 minutes and get medical attention Lithium Metal
109. R 91 207 d 91 409 and 43 Appendix D Transport Canada Civil Aviation Part V Airworthiness Standards Chapter 551 104 d 1 VI Functional Test Procedures These functional test procedures are recommended by Ameri King to be performed every 1 2 months FAR 91 207 d 91 409 and 43 Appendix D Procedures Necessary To Accomplish The Performance Tests Specified In Chapter 571 Appendix G A Corrosion Inspection Inspections are to be performed every year 2 5 1 ELT Main Battery Replacement instructions Step 2 Battery Voltage Test 3 3 1 Switch ON OFF ARM Operation 3 3 2 Transmitter ID Programming and Self Test 3 3 3 System Integration Test 3 3 4 Green ON Lights and Buzzer Sound Functions 3 3 5 Transmitter Functional Test For ELT S only 3 3 5 1 Main Switch ON OFF SELF TEST Operation 3 3 5 2 Transmitter Self Test 3 4 2 J Corrosion Inspection For Coaxial Cable 3 4 3 Corrosion Inspection For Remote Wiring Modular Cable 116 Operational Testing The periodicity of operational checks is at the operator s discretion but the check shall only be conducted during the first five minutes of any UTC These test procedures are recommended by Ameri King to be performed every 1 2 months C Performance Testing These Tests are required for Canadian compliance only Tests are to be performed every year 3 4 6 Operational Test 3 4 7 1 G Switch Check 3 4 7 2 Antenna C
110. al instrument scan Mark a cutout for the cockpit panel switch with the dimensions shown in Figure 10 Install the Remote Unit assembly by fitting it into the cutout using four 4 40 screws and Nylock nuts If the unit is to be mounted in a location that does not have a flush mounting surface 1 e beneath the panel glare shield an angle bracket should be fabricated See Figure 10 1 TSO C126 RTCA DO 204 paragraphs 1 3 and 2 2 6 1 state A remote control to operate and monitor the transmitter shall be required if the ELT unit is not readily accessible from the pilot s position Note For Canadian aircraft installation a placard displaying the following warning will be placed near the ELT remote unit FOR AVIATION EMERGENCY USE ONLY UNAUTHORIZED OPERATION PROHIBITED 48 ELECTRICAL SPECIFICATIONS TEST CONDITION TEMP 25 C FBPB2925A 2FERT Operating Voltage Min Sound Output at 30 cm Resonant Frequency Lead Wire Lead pin material perating Temperature Storage Temperature a Value Applying at Rated Voltage 00 DIMENSIONS UNIT Inch 1 580 E MOUNTING BRACKET FABRICATE IF NEEDED TT 490 1 600 Unit Connector is RJ12 or P N 1480 3190 Tyco Inc with 606 181 male pin Qty 2 Tyco Inc Mating Connector P N 1480 7200 Tyco Inc with 606 171 female pin 2 Inc Housing Material ABS777 AIMIERIEING CORP 83 PART 450004 e 71 c MLADE IM L
111. aluation against Annex II criteria ayan of Aviation orce omments Great Lakes 2 1 1 and 2 Yes Although limited production occurred after lt Yes Yes Yes a 2 ____ _ Mes __ __________ PF Hellcat es SF Bearcat Korea es es Tdi Tgerest Korea CdS LL TBM Avenger ww es es es __________ 21 Goose ww cs es a Pit Widgeon ves ves _______ __ ves __ Ctandc2 es ves LLL es sj E __ ___ __ ________ _____ 763 P __ _ DL D E ___ A 584 E dw _ ____ ____ _ SS e A TS edan M18 Mite Naval Aircraft N3N 3 Yes Yes Yes A 2 569 roy dI D m D La T6 SNJ etc series New Annex Il EASA list Issue 10 25 Feb 2008 Page 7 of 10 189 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Evaluation against Annex II criteria oo NEN Development Role in armed Production State of Design TC and EVEN DI eji OPES __________ 62 ____________ ________ 68 CV __________ 86 Sabre Korea __ Yes M Jovis vienam Tres lves lvee __ LIE m davionseries es es A782 D Uu D v lt
112. an applied force Consult the ELT manufacturer s instructions before activation The direction for mounting and force activation is indicated on the ELT 119 INSPECTION A 91 ELT can be activated by using a quick rap with the palm TSO C91a ELT can be activated by using a rapid forward throwing motion coupled by a rapid reversing action INSPECTION Verify that the ELT 15 activated using a wattmeter the airplane s VHF radio communications receiver tuned to 121 5 MHZ or other means INSPECTION Reinstall the ELT into its mount and verify the proper direction for crash activation Reconnect all cables They should have some slack at each end and should be properly secured to the airplane structure for support and protection INSPECTION 4 The presence of a sufficient signal radiated from its antenna Activate the ELT using the on or ELT test switch A low quality amplitude modulation AM broadcast radio receiver should be used to determine if energy is being transmitted from the antenna continue INSPECTION When the antenna of the AM broadcast radio receiver tuning dial on any setting 15 held about 6 inches from the activated ELT antenna the ELT aural tone will be heard INSPECTION Verify that all switches are properly labeled and positioned TEMPORARY REMOVAL An aircraft may be operated during any period for which the transmitter has been temporarily removed for inspection repair modification or replace
113. ance of the antenna may become distorted and nulls may appear in the antenna radiation pattern This in turn may cause erratic navigational readings or signal drop out The electrical bonding of the antennas to the aircraft skin 15 best accomplished by direct metal to metal contact of the antenna base to the aircraft skin To accomplish this the aircraft paint in the mounting area will need to be removed If bare metal surfaces are needed for surface preparation they should be treated with Alodine 1200 or similar compound to eliminate aluminum oxidation After installing the blade antenna make sure the electrical bonding of the antenna base blade to the aircraft meets the requirement of less than 0 0030 Type of aircraft The 451017 3A Blade Antenna 15 designed for installation on fixed wing subsonic aircraft with reciprocating engines and is rated for a maximum airspeed of 600 KIAS Knots Indicated Airspeed at Sea Level 43 Installation 1 Mounting the Blade antenna using 10 32 SS machine screws and associated hardware and torque to 20 in lbs For BNC connector drill a 0 6250 5 8 diameter hole The most important in installing Blade antenna is the electrical bonding between the base plate antenna and the aircraft skin metal to metal rather than thru the mounting screws as some other antennas A layer of anti corrosion bonding grease should be applied between the aircraft skin and the base of the antenna Metal adapt
114. and Yes Yes Yes 26 Model 45 5A3 agN m Model 35 Bonanza V Yes Yes A 777 models TC d to tail variants 35 A35 3A15 are not Annex II B35 C35 D35 E35 235 G35 35R ______ 39 Airacobra WWII a ES aan 263 Kingcobra WWII LTC 21 Model 14 series ers es A773 New Annex 11 EASA list Issue 10 25 Feb 2008 Page 3 of 10 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Evaluation against Annex II criteria aver of Aviation force lt lt ommaents Cessna L 19 O 1A Model Yes Yes Yes SAS 305 Bird dog series now Regal Air 305 3A14 L Eso Bobeat cio 75712752 140 series Yes Yes 5A2 A 768 70 series irs res A799 t ted __ 126 Champion 11 series Yes Yes A 761 __________ ______ D o hs ______ Yes 7 series as follows Yes but see A 759 Production of note some models continued TECA w 108 HP to 1980 but listed as Lycoming 235 1 Annex II to avoid s n Fixed Pitch Sensenich split TGCAA w 150 HP Lycoming Fixed Pitch Sensenich or McCauley Propeller New Annex Il EASA list Issue 10 25 Feb 2008 Page 4 of 10 185 186 Table 2 Non EU states of Design powered aircraft fixed wing State of Design Evaluation against Annex II criteria LOLOS 7GCBC w 150 HP Lycoming Fixed Pitch Sensenich or McCauley Propeller w 150 HP
115. anual for detail fault code analysis This satellite ELT only floats w floating collar Figure 15 Battery Replacement for ELT Main Unit 69 Figure 16 1 Battery Cell Replacement for ELT Main Unit Actual View 70 2 5 2 ELT REMOTE UNIT BATTERY INSTALLATION AND REPLACEMENT INSTRUCTIONS The ELT Remote Unit is designed to be powered by a Duracell DL1 3NB 3 Volt Lithium Batteries Under normal operating conditions the Lithium battery must be replaced every five years If the ELT is activated for an unknown period of time the lithium battery must be replaced To install or replace the Remote Unit Battery follow these steps Remove the three Retaining Screws that secure the top and bottom half of the remote unit Figure 17 Loosen the two Switch Retaining nuts located on the front of the unit Figure 17 Carefully remove the top half of the Remote unit exposing the battery compartment Figure 17 If replacing an old battery carefully inspect the battery contacts for dirt or corrosion IF the contacts need cleaning use only non abrasive electrical contact cleaner and a stiff brush Badly corroded contacts should be replaced Insert the battery with the polarity as shown in Figure 17 The polarity is also engraved on the bottom of the battery compartment Replace the top half of the remote unit and replace the three retaining screws and tighten the two switch retaining nuts The next remote battery replacement date shoul
116. aritime Dangerous Goods IMDG Code These batteries have been tested and passed United Nations Manual of Tests and Criteria 38 3 requirements They must be shipped as a Class 9 UN3090 material in an approved Packaging Group 2 container For details regarding an exception to shipping this product as Class 9 please see 49 CFR 173 185 c Certified on behalf of Ultralife Batteries Inc by Jennifer Dimock Environmental Health and Safety Manager Ultralife Batteries Inc FA1305 Rev 09 27 04 Ultralife Batteries inc 2000 Technology Parkway Newark 14513 315 332 7100 Fax 315 331 7800 www ultralifebatteries com 229 Certificate Number TDG 0002 Date November 10 2004 Issue Initial Release Transportation Assessment Trials Part Number 110013 U10015 Lithium Content 3 4 grams Regulations e United Nations Recommendations on the Transport of Dangerous Goods Model Regulations e European Agreement Concerning the International Carriage of Dangerous Goods by Road ADR e U S Code of Federal Regulations CFR 49 parts 100 185 Transportation of Hazardous Materials e International Air Transport Association IATA Dangerous Goods Regulations e International Civil Aviation Organization ICAO Technical Instructions for the Safe Transport of Dangerous Goods by Air e International Maritime Organization International Maritime Dangerous Goods IMDG Code These batteries have b
117. at end of 5 years battery life FAR 91 207 c 1 requires that ELT batteries be replaced when the transmitter has been in use for more than one cumulative hour The label sticker for expiration date of the batteries must be affixed on the outside of the ELT battery case and recorded in the aircraft logs xx WARNING USE ONLY DURING SITUATIONS OF GRAVE AND IMMINENT DANGER LITHIUM BATTERY NON RECHARGEABLE P N 4500010 1 FOR USE ON Model AK 451 AF AP S RTCA DO 160E Environmental Categories F1XBQ27 227 227 XXXXXXXXXXXXXXXXXX Replace Replace Main battery Batteries pack after d cumulative hour of use or by date shown Battery type Lithium LiMnO2 NEVER CHARGE SHORT CIRCUIT PUNCTURE DEFORM INCINERATE OR OPEN DO NOT SUBMERGE IN WATER OR HEAT ABOVE 85 C REMOVE WHEN DISCHARGED Battery Box Silkscreen The owner or operator may perform Battery replacement provided that the accessibility removal and reinstallation of the ELT can be considered simple as prescribed in Advisory Circular 91 44A Paragraph 8 a See Appendix B 68 The following is a step by step instruction for replacing ELT Battery Pack P N 4500010 Series 1 Using the 3 32 Hex Driver supplied with the ELT remove the 4 retaining screws and split lock washers that attach the battery case to the ELT Transmitter Assembly See Figure 15 Insure both battery connectors are locked in
118. at only an experience technician perform these tests A test harness P N TS 451 HN 1 may be ordered from Ameri King Corp at 714 842 8555 All tests must be performed in an RF screen room or with the ELT in a shielded container that will substantially attenuate the RF signal ON state current measurements must be made with the RF outputs loaded with 50 ohms rated for 5 watts either a resistive load or equipment with 50 ohm impedance padded with 10 dB 5 Watt attenuator 1 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 Press the RESET Switch to Reset the unit OFF Mode Current Measurement e Remove the battery pack as described in Section 2 5 1 e Disconnect the 2 pin harness e Install the test harness P N TS 451 HN 1 and inline ammeter as shown in Fig 4 2 e Ensure the ELT is OFF e Measure the current with the ammeter The measured current should be 0 microamps uA ARM Mode Current Measurement e Measure the current with the ammeter The measured current should be not more than 20 uA ON Mode Current Measurement Note Current draw during this test may exceed 2 0 Amps during the 406 028 MHz burst Ensure the ammeter is set on the appropriate range to accommodate this level of current e Activate the ELT by select ON allow it to stabilize The measured steady state current should not exceed
119. at were originally designed for civil purposes but which were subsequently used by the military except where a discrete military variant can be identified Certain aircraft some Jodel series Emeraude series including Smargd and Linnet have been declared as Annex II because of direct similarity with the original Jodel D11 and CP30 aircraft even though design production of later variants may not fit in with the 1955 1975 criterion Similarly the Beagle Airedale has also been accepted as Annex II as a direct development of the Auster series which are clearly Annex II Complex multi piston engined transport aircraft DC 4 DC 6 Constellation ATL 98 etc are declared Annex II on the basis of their historical significance New Annex Il EASA list Issue 10 25 Feb 2008 Page 1 of 3 10 Tables Table 1 Table 2 Table 3 Table 4 Table 5 161 Some aircraft e g PA 18 An 2 had very long production runs and are declared as Annex II even though production continued after 1975 This is because the vast majority of aircraft were built before 1975 they were designed before 1955 and can claim some historical importance In addition it is undesirable to have some examples of an aircraft type split between Annex II and The list includes some ex military types examples of which did not serve with the military This is to also avoid splitting some aircraft types between Annex II and EASA EU States of Design powered aircraft fixed wing Non
120. ation against Annex II criteria Development Role in armed Design State of Design TC and aver Aviation lt lt omments 24 e n D A 699 A 700 lt D Yugoslavia peu 56 DE igo lt D D u New Annex EASA list Issue 10 25 Feb 2008 Page 10 of 10 192 Table 3 Sailplanes and Powered Sailplanes EU and non EU State of Design Manufacturer Austria kaflieg Wien FV Oberlerchner Oberlerchner pilka Wettstein Spatz W Zentralwerkstatte C Evaluation against Annex II criteria ment Role in armed State of Design 116 Once F15 92 Historic event 5 E Pa D lt 8415 O E 2 x Q D O lt D lt lt b x t D lt D N a Ad a 2 D D Izenz Fauvel c gt lt roo gt cIc afo 2 2 Dio a D lt D lt lt L 230 ct 2 gt marks 109 107 16 116 etc 4 D D All sailplanes designed before 1955 manufactured before Arsenal 4111 CR 60 Fauconnet 5 e TCDS 37 E E TCDS 74 901 5 series ay TCDS 37 _
121. ations International This MSDS conforms to European Union EU the International Standards Organization ISO and the International Labour Organization ILO and as documented in ANSI American National Standards Institute Standard Z400 1 1993 Section 16 Other Information The information contained herein is furnished without warranty of any kind Users should consider this data only as a supplement to other information gathered by them and must make independent determinations of the suitability and completeness of information from all sources to assure proper use and disposal of these materials and the safety and health of employees and customers ULTRALIFE BATTERIES MSDS023 FA1284 Rev F OCT 01 2007 Page 6 of 6 Rev K Date OCT 31 2007 Page 1 of 4 SAFETY PRECAUTIONS FOR LITHIUM MANGANESE DIOXIDE Li Mn0 CELLS AND BATTERIES A GENERAL 1 Lithium Manganese Dioxide Li Mn05 primary non rechargeable cells and batteries have higher energy on a weight and volume basis than conventional batteries such as carbon zinc and alkaline Li MnQ gt cells have a typical open circuit voltage of 3 3 volts and a normal operating voltage range of 2 5 to 3 0 volts depending on device current drain and ambient operating temperature The chemical components that are responsible for their superior energy density may also contribute to an increased safety hazard if they are misused or abused Li MnO batteries can be used with minima
122. creates high temperatures in the cell High temperatures can cause burns in skin or cause the cell to flame Avoid reversing battery polarity within the battery assembly To do so may cause cell to flame or to leak The use of old and new batteries or batteries of varying sizes and types in the same battery assembly should be avoided The batteries electrical characteristics and capabilities vary and damage may result to batteries or electrical equipment ULTRALIFE BATTERIES MSDS023 FA1284 Rev F OCT 01 2007 Page 3 of 6 Rev K Date OCT 31 2007 22 Section 8 Exposure Controls Personal Protection No engineering controls are required for handling batteries that have not been damaged Personal protective equipment for damaged batteries should include chemical resistant gloves and safety glasses In the event of a fire SCBA should be worn along with thermally protective outer garments Section 9 Physical And Chemical Properties Not Applicable Section 10 Stability And Reactivity 1 This product is stable under ordinary conditions of use and storage 2 It is not recommended that this product be stored above 85 194 F 3 Damaged batteries will react with water Non discharged batteries contain elemental Lithium This is water reactive This reaction gives off heat and hydrogen gas A thermal reaction may occur 4 Hazardous decomposition products Carbon Monoxide CO and Hydrogen Flouride HF Section 11 Toxicologica
123. d ELT swept Tone must be silent on the 121 5 MHz VHF Radio If the self test is Failed the Green ON light flashes as defined below 1 flash Internal Data stored in Memory at fault 2 flashes Distress ID stored in Memory at fault 3 flashes Battery voltage is low lt Useful Life Battery Voltage setting 4 flashes Vcc supplies for F2 or F1 at fault 5 flashes F3 RF power level 33 dBm 406 028 MHz 7 flashes F1 F2 VHF RF power level 17 dBm 121 5 243 MHz 9 flashes PLL locked in F3 or F1 or F2 at fault Continuous flash no F3 F2 F1 RF output power ELT shuts down completely Note The self test mode that transmits a 406 MHz test code pulse monitors certain system functions before returning to the ARM mode The 406 MHz test pulse is ignored by any satellite that receives the signal but the ELT uses this output to check output power and correct frequency Self test is 520 ms long message burst on the 406 MHz signal Synchronization pattern is 011 010 000 Self test is then 121 243 MHz VHF Continuous Wave during Is During Self Test ELT swept Tone must be silent the 121 5 MHz Radio e If No Antenna or No coaxial cable connected the ELT may or may not 5 flashes 3 3 3 System Integration Test The test consists of turning the unit ON and then resetting it to verify that the Transmitter Latch Circuit Batteries and associated equipment are operating properly Reg
124. d Remove the old ELT holder or tray and install the AK 451 mounting tray in its place Stainless steel hardware 15 recommended Use hardware conforming to an accepted standard such as AN or Mil Spec 27 Compatible patterns See Figure 2 1 1 include ACK Technologies E 01 Artex 100 110 G406 C406 and B406 series ELT 200 series Narco ELT 910 ELT 10 Pointer model ELT 3000 ns e NEM IE ae 8 Direction of Flight Center line of Aircraft Fuselage ELT longitudinal axis must be within 10 degrees of center line with arrow on the Battery case pointing in the direction of flight Figure 1 Direction Determination for Fixed Wing Aircraft 28 Helicopter Installations The AK 451 15 or AK 451 12 may be mounted so that the arrow aligns with the longitudinal axis of the aircraft If necessary the ELT may be tilted Nose down up to 10 degrees see Figure 1 1 The ELT mount may be rotated about the aircraft center axis 1 the ELT can be mounted on the floor walls or over head so long as it points to the front of the aircraft Also refer to aircraft manufacturer s data Type Approval or STC information and or national regulations regarding installation on helicopters degrees Horizontal plane Vertical plane Figure 1 1 Direction Determination for Helicopter 2 2 1 2 MOUNTING TRAY AND VELCRO HOLDER INSTALLATION After selecting a suitable location m
125. d be recorded on one of the adhesive labels supplied and affixed to the ELT in a readily visible location BATTERY INSIDE SEE MANUAL FOR REPLACEMENT INSTRUCTIONS Retainning BOTTOM A Screws 3 Figure 17 Battery Replacement for ELT Remote Unit 7 2 6 FAA Form 337 For most installations an FAA Form 337 will be required for FAA registration Additional information regarding the completion of FAA Form 337 can be found in Advisory Circular AC 43 9 1F Instructions for Completion of FAA Form 337 AC 43 210 Standardized Procedures for Requesting Field Approval of Data Major Alterations and Repairs provides further guidance This manual constitutes FAA approved data as described in 43 9 1F paragraph h 2 and AC 43 210 chapter 2 paragraph 201 a 6 for major alterations Not all installations are major consult your local FAA ACO for clarification 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 ACs e g AC 43 13 2B under certain circumstances TSOs parts manufacturing approval PMA FAA approved manufacturer s instructions kits and service 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 holding a delegation option authorization
126. dence due to transmitting on both 243 0 MHz Military and 121 5 MHz Civilian bands for immediate ground search dispatch narrowing the searching time The AK 451 ELT Emergency Locator Transmitter is micro controller based equipment It is extremely reliable equipment designed to meet TSO C126 and TSO C91A requirements batteries operated and self contained The ELT Emergency Locator Transmitter is designed only for emergency use The model AK 451 may be used as one or more of the following ELT types a Automatic Fixed ELT AF The ELT AF is designed to be permanently attached to the aircraft before and after a crash Aural and flashing light monitors are provided to alert the flight crew that the ELT has been activated and 15 transmitting It 15 designed to aid the Cospas Sarsat satellite and SAR teams in locating a crash site The model AK 451 AF consists of an ELT main unit an aircraft fixed antenna coaxial cable assembly remote switch unit interconnect wiring assembly a T adapter connector an audible buzzer monitor a mounting tray and velcro holders The ELT AF has an automatic activation G Switch It is activated automatically upon a crash or manually operated 14 b Automatic Portable ELT AF AP with dual antennas The ELT AF AD is designed to be rigidly attached to the aircraft before the crash but readily removable from the aircraft after a crash It functions as an ELT AF during a crash sequence T
127. dio Note 3 Because the ELT radiates on the emergency frequency the Federal Communications Commission allows these tests to be conducted only within the first 5 minutes after any hour and limits the tests to 3 sweeps of the Transmitter Audio Modulation IMPORTANT NOTE IN NORMAL CONFIGURATION THE MAIN SWITCH LOCATED ON THE ELT MAIN UNIT MUST BE SELECTED AT ARM POSITION AT ALL TIMES 3 4 8 Verification of Digital Message Note This test is not mandatory per FAR 91 207 d however Ameri King strongly recommends that it be performed as part of periodic maintenance at least every year Verify the 406 MHz digital message using a Computer Test Set or equivalent capable of receiving and decoding the message Ameri King suggests the Ameri King ELT Computer Test Set P N TS 451 Contact your local Ameri King dealer for availability of the Computer Test Set or call Ameri King Follow instructions provided with the computer test set The AMERI KING AK 451 has a self test feature which is encoded such that it will be ignored by the SAR satellite system This 15 digit number is used to register the ELT with the appropriate 406 MHz ELT registration authority In the US the National Oceanic and Atmospheric Administration NOAA maintain the database of registered ELT s 87 Note For the following example the programming protocol is assumed to be Standard Location Protocol ELT with C S type approval number and Serial Number Long
128. e 722 Automatic activation via G switch Self test mode one burst 520 ms or 440 ms subject 10 format lag ELT Remote Unit P N 450004 and Remote Audio Buzzer Monitor P N 451018 e Approved for use with external aircraft antennae blade 451 017 34 rod AK 451 017 2A and whip AK 451 017 1B 9 Approved for use with potable whip antenna AK 451 Lomas Approved Beacon taeon x is Aem for with the message protocols indicated with Yes and black text below USER LOCATION USER PROTOCOLS 5 A PROTOCOLS x Dam PROTOCOLS No Maritime with MMSI No Maritime with MMSI 7 Standard Location EPIRB with MMSI No Maritime with Radio Call Sign N Maritime with Radio Call Siga Sandan Location EPIRI with Serial EPIRB Float Free with Serial Number No Float Free with Serial Number Standard Location ELT with 24 bit t EPIRB Non Float Free with Serial Standard Location ELT with Aircraft No EPIRB Non Float Free with Serial Number NG No Radio Sign Radio Call Sign Pamiara ELT with Serial Standard Location PLB with Serial Yes Aviation Yes Aviation Yes Numi 3 Yes ELT with Serial Number Yes ELT withSerlalNumber No National Location EPIRA ELT with Aircraft Operator and Serlal vus ELT with Aircraft Operator and wee Ve Numi amp ial Number National Location ELT Yes ELT with 24 bit Address
129. e Contact Ultralife for latest information www ultralifebatteries com R E NM Ultralife Batteries Inc Li MnO Cells and Batteries January 14 2004 UBI 5135 Rev All specifications subject to change without notice The information contained herein is for reference only and does not constitute a warranty of performance Contact Ultralife for latest information www ultralifebatteries com 226 227 Page 4 of 4 B WHEN DISCHARGING THE BATTERY Do not discharge the battery using any device except for the specified device When the battery is used in devices other than the specified device it may damage the battery or reduce its life expectancy If the device causes an abnormal current to flow it may cause the battery to become hot explode or ignite and cause serious injury Refer to the technical data sheets for the temperature ranges over which the battery can be discharged Use of the battery outside this temperature range may damage performance of the battery or may reduce its life expectancy While considerable effort has been taken to accurately represent the information contained herein Ultralife does not guarantee its accuracy or completeness Information may contain errors omissions inaccuracies or outdated information and Ultralife disclaims any obligation to update such information Ultralife makes no repres
130. e nearest suitable airport and set the Main Switch to the OFF position In either case the unit should be inspected by qualified facility as soon as possible The Aircraft may be operated with the ELT removed for inspection or repair subject to the conditions of FAR 91 207 In the event of an accident ensure that the External Aircraft Antenna has no damage 79 Important If the ELT is accessible after the accident place the Main Switch in the ON position and monitor it on 121 5 MHz for proper operation if possible If the Antenna is broken off of the Aircraft the ELT Unit should be removed and the portable antenna to be used If the ELT Unit 15 to remain at the Aircraft site it should be placed on a large metallic portion of the airframe with its Antenna pointing skyward The Green ON lights should be flashing after the accident If the ELT is to be taken along as the Portable Unit when leaving the scene of the accident place the Main switch the ON position and keep the Antenna vertically oriented as much as possible The ELT Green ON light should be flashing 3 3 4 Green ON lights Buzzer sound and Antenna check 3 3 4 1 Green ON Lights and Buzzer Sound Functions Green ON lights located on the ELT main unit and remote switch unit In ON mode Green ON LED flashes continuously 1 second ON 4 second OFF and the Buzzer sound periodically The ELT swept Tone must be heard on the 121 5 MHz VHF Radio This is to indicate t
131. ed By Country Code Country Name 40 1 Afghanistan 201 Albania Andorra 202 Azores 301 Belarus 216 Vatican 608 Moldova 4 408 405 364 Tun A0 ais 327 Dominican Republic Islands 514 515 Cape Verde Cayman Islands Republic 616 St Lucia 615 Montserrat 323 Nicaragua 351 352 353 270 Czech Republic 354 355 356 Panama 355 leo 2 621 EI Salvador 325 Trinidad 327 Dominican Republic 364 Turks And Caicos Islands 625 405 Bangladesh Bahrain 130 NO Gabon Republic PP 351 352 353 E 357 31 372 357 371 312 434 Guatemala 44 Turkmenistan Senegal Kenya 666 1 _ 69 669 1 Swaziland 63 Senegal 451 674 47 Tanzania 66 Somali 671 450 510 644 434 1 Turkmenistan 60 Swaziland 642 453 274 510 Micronesia 69 Falkland Islands i 262 Montenegro 612 can gt Republic 131 132 APPENDIX H ELT CODING PROGRAMMING ID READER AND MAINTENANCE TEST P N TS 451 Important Note These tests should be performed only within an RF Screen Room or Facility providing shielding of RF Emissions 1 Setup Use provided cable to connect the ELT RJ 12 port to the mini PC USB port 2 ELT Coding Programming 2 Double Click 451 Icon to run the program The programming window appears as below amp K451 HyperTerminal 101 x File Edit Call Transfer Help
132. een tested and passed United Nations Manual of Tests and Criteria 38 3 requirements They must be shipped as a Class 9 UN3090 material in an approved Packaging Group 2 container For details regarding an exception to shipping this product as Class 9 please see 49 CFR 173 185 c Certified on behalf of Ultralife Batteries Inc by Jennifer M Dimock Environmental Health and Safety Manager Ultralife Batteries Inc FA1305 Rev 09 27 04 Ultralife Batteries Inc 2000 Technology Parkway Newark 14513 315 332 7100 Fax 315 331 7800 www ultralifebatteries com 230
133. eeting all of the above requirements drill and mount the ELT Mounting Tray as shown in Figures 2 2 3 and 3 Mark the 4 holes in trapezoidal locations needed for the tray using the tray as a guide Be sure the tray aligns within 10 degrees of the longitudinal axis of the aircraft and in direction of flight The mounting Tray may be mounted on the Horizontal plane or Side wall or Overhead as long as the FORWARD Arrow direction shown on the ELT is adhered Note The purpose of 4 holes in trapezoidal configuration 15 to assure that both the ELT and mounting tray will be placed in the correct direction with the arrow FORWARD direction marking on the ELT must be adhered Therefore make sure the direction of the 4 mounting holes in trapezoidal configuration is correct If a reinforcement Doubler plate is needed to meet the rigidity requirements of paragraph 2 2 1 1 fabricate one using the tray as a guide 29 i 1 102 4 400 4 260 2 800 2 630 5 770 i 1 0 070 0 500 Figure 2 2a Holder for ELT AP with integral antenna P N 450 014 1 30 Counter Sink Hole For 4 40 or 48 32 Flat Head Screws 135 250 Counter Sink Hole 4 15 1 26 Figure 2 1 Mounting Tray for ELT AF AP P N 450 013 I Material Aluminum 5052 2 Latch ring amp hook material Stainless steel 3 Surface finish Yellow chem film vellow anodize Figure 2 2 Holder for ELT AF AP
134. emote Unit Continued 49 Figure 11 Remote Audio Buzzer Monitor P N 451018 2 50 Figure 11 1 Buzzer may be fastened directly onto the Remote Switch Unit 51 Figure 12 1 Interconnecting Wiring Cable between ELT Remote Unit and Main Unit Part No 451001 2 0 52 Figure 12 2 Interconnecting Wiring Cable between ELT Remote Unit and Main Unit Part No 4500041 esee 53 Figure 13 Verify parameter eene 60 Figure 14 1a Wiring diagram for AK 451 with A wire interconnecting ELT Main Unit and Remote Switch 62 Figure 14 1b Wiring diagram for 451 with 2 wire interconnecting ELT Main Unit and Remote Switch Unit sess 63 17 Figure 14 1c Wiring Diagram for retrofitting AK 451 with 4 wire interconnecting ELT Main Unit and Remote Switch Unit Artex Pointer Kannad ACK Tech 00000000000 64 Figure 14 1d Wiring Diagram for retrofitting AK 451 with 2 wire interconnecting ELT Main Unit and Remote Switch Unit DAEM Narco Joliet i 65 Figure 14 1e Wiring diagram for AK 451 with Optional Multi axes G switch with 4 wire interconnecting ELT Main Unit and Remote switch unit 108 Figure 14 1f Wiring diagram for AK 451 with Optional Multi axes G switch with 2 wire interconnecting ELT Main Unit and Remote switch unit 109 Figure 14 1g Wiring dia
135. enna 15 radiating with sufficient power to aid search and rescue The Aircraft s VHF Receiver tuned to 121 5 MHz may also be used This Receiver however 15 more sensitive and could pick up a weak signal even if the radiating ELT s Antenna 15 disconnected Thus it does not check the integrity of the ELT System or provide the same level of confidence as does an AM Radio 61 BLACK ON Lo Audible Buzzer 12 6P6C ELT Model AK 451 Remote Unit 451 004 RJ12 6P4C Pinout RS 232 Rxd Hi RS 232 Rxd Hi 1 1 a Remote RESET SW Lo DC Ground 2 E Yellow 2 Remote ON SW Lo Remote RESET SW L0 lel neenon Remote ON Light Lo 5 Black 88 5 RS 232 Txd Hi 6 450 0041 6 Remote Wiring Cable Assembly RJ 12 6P6C RJ 12 6 6 T Adapter 451 0181 Figure 14 1a Wiring Diagram for AK 451 with 4 wire interconnecting ELT Main Unit and Remote Switch Unit 62 ON Lo Audible Buzzer 3 6 451 018 RJ 12 6P6C ELT Model AK 451 Remote Unit 451 004 RJ12 6P4C Pinout 1 R amp 232 Rxd Hi DC Ground Remote RESET SW Lo Remote QN SW Lo RS 232 Rxd Hi DC Ground _ Remote RESET SW Lo Remote ON Light Lo Remote ON Light Lo 3 6 Vde Qut on 0 R3 232 Txd Hi 451 0181 NOTE Optional Mil Spec M22759 18 or 35 24AWG at specified length is available Figure 14 1b Wiring Diagram for AK 451 with 2 wire interconnect
136. entations or warranties as to the completeness accuracy adequacy currency or reliability of this information and shall not be liable for any lack of the foregoing Furthermore the information does not constitute legal advice on battery design and should not be considered legal advice nor substitute for obtaining battery design advice directly from Ultralife engineers Ultralife Batteries Inc Li MnO Cells and Batteries January 14 2004 UBI 5135 Rev All specifications subject to change without notice The information contained herein is for reference only and does not constitute a warranty of performance Contact Ultralife for latest information www ultralifebatteries com 228 ULTRALIFE BAT MR IE SING Certificate Number TDG 0003 Date November 10 2004 Issue Initial Release Transportation Assessment Trials Part Number U10014 010016 Lithium Content 3 4 grams Regulations e United Nations Recommendations on the Transport of Dangerous Goods Model Regulations European Agreement Concerning the International Carriage of Dangerous Goods by Road ADR e U S Code of Federal Regulations CFR 49 parts 100 185 Transportation of Hazardous Materials e International Air Transport Association Dangerous Goods Regulations e International Civil Aviation Organization ICAO Technical Instructions for the Safe Transport of Dangerous Goods by Air e International Maritime Organization International M
137. er TSO C126 RTCA DO 204 requirements Avoid running this cable near sources of strong EMI RFI radiation Secure the Cable along its run with Tie wraps or other suitable methods The interconnecting cable may be shortened or a longer cable of up to 200 feet may be used if required Wiring per M22759 18 or 35 24 AWG or equivalent is acceptable 2 3 ELECTRICAL INSTALLATION Please refer to FAA AC 43 13 for guideline Since both the ELT Main Unit and the Remote Unit have their own internal batteries there 15 no electrical connection required between the entire ELT system and the Aircraft Electrical Power System The audible buzzer 15 powered by the Remote Unit internal battery 2 4 POST INSTALLATION TEST Please refer to FAA AC 43 13 for guideline After completing the mechanical installation ensure the ELT Main Unit must be mounted with the FORWARD arrow marking adhered The following Post Installation Function Tests must be performed Regulations require that Transmitter Tests only be done during the first 5 minutes of each hour and must not last for more than 3 audio sweeps 1 5 seconds If you are at a location where there is an FAA Control Tower or other monitoring facility notify the facility before beginning the tests Note Press RESET anytime to turn off unwanted transmission 55 240 QUICK OPERATION CHECK Note Refer to Appendix A 1 for Quick Operation Check in sequence order 2 4 0 1 ELT Main Switch ON position ELT s
138. er plates are optional but they should be used if the curvature or compound radius of the aircraft skin 15 such that antennas cannot be directly installed vertically with their plates mounted flat to the aircraft outer surface Backing plates or doublers should be installed to ensure adequate structural strength for associated air loading during flight Refer to FAA Advisory Circular 43 13 2B for complete information Remove the 1 2 28 hex nut and external tooth lock washer from the base of the antenna Insert antenna connector through mounting hole make sure the O ring remains in the base of the antenna connector flange groove and that the connector has sufficient clearance through the aircraft skin To mount the antenna place the lock washer and the hex nut on the inside of the aircraft and sandwich the aircraft skin between the base of the antenna and lock washer followed by the hex unit Tighten the hex nut to between 25 to 30 in Ibs Apply a small smooth fillet with RTV sealant around the periphery of the antenna base to seal of moisture For maximum signal strength the length of the antenna coax to the ELT should be as short as possible use of the standard 6 foot coax 1s recommended when possible 44 The antenna ground plane 53 e 5 ci gt S p g E gt 5 D un 5 E nm tg m S s Ss g 79 2 5b Se
139. er than crewmembers in an aircraft that has been maintained rebuilt or altered in a manner that may have appreciably changed its flight characteristics or substantially affected its operation in flight until an appropriately rated pilot with at least a private pilot certificate flies the aircraft makes an operational check of the maintenance performed or alteration made and logs the flight in the aircraft records c The aircraft does not have to be flown as required by paragraph b of this section if prior to flight ground tests inspection or both show conclusively that the maintenance preventive maintenance rebuilding or alteration has not appreciably changed the flight characteristics or substantially affected the flight operation of the aircraft FAA Action Notice A 8150 3 1 Remove all interconnections to the ELT Main Unit and ELT antenna Visually inspect and confirm proper seating of all connector pins Special attention should be given to coaxial center conductor pins which are prone to retracting into the connector housing Remove ELT from the mount and inspect the mounting hardware required mounting hardware should be reinstalled and secured Gain access to the ELT battery and inspect No corrosion should be detectable Verify that the ELT battery is approved and check its expiration date Activate the ELT using applied force The direction for mounting and force activation is indicated on the ELT A TSO C9la
140. etained for the Issue of this Authorisation 2 This ETSOA does not constitute an installation approval It is the responsibility of those installing this article to determine that the aircraft installation conditions are within the ETSO standards This Authorisation shall remain valid unti surrendered or revoked For the European Aviation Safety Agency Date of Issue November 20 2008 Certification Manager Parts amp Appliances Form issue 1 150 i Transport Transports Canada Canada Ottawa Ontario ONS Your fie Wob r f rence Our Notre r f renca November 26 2008 5012 E3 9 4511642 Mr Keith Van Q C Manager Ameri King Corporation 17881 Sampson Lane Huntington Beach CA USA 92648 Subject Approval of Ameri King Corporation AK 451 AF AK 451 AP and AK 451 S Emergency Locator Transmitters Reference Ameri King Corporation letter to Transport Canada Civil Aviation TCCA dated August 1 2008 RDIMS 4511642 attachment Dear Mr Van This correspondence is in response to the referenced letter whereby Ameri King Corporation requested TCCA approval of the above subject Emergency Locator Transmitters ELT The documents submitted in support of this request have been reviewed and found to be in compliance with the relevant Canadian Standards This letter constitutes an airworthiness approval by Transport Canada for the ELT models indicated below that are eligib
141. ft amp flip the switch to the position Verify ELT swept tone heard on 121 5 MHz VHF Radio Green LED is on after 4 sec for 1 sec then off 4 sec Self Test Lift amp flip the switch to ARM position Verify Green ON 15 on for 4 sec then off Wait for an additional 21 sec If Pass Green ON LED stays off No swept tone on 121 5 Radio If Fail Green LED flashes See Operation Manual for details Check G switch Next If pass Self Test shake ELT back and forth rapidly in direction of FORWARD arrow ELT must activate and swept tone heard on 121 5 Radio THIS SATELLITE ELT ONLY FLOATS W FLOATING COLLAR Front label for AK 451 AP with integral antenna QV MO FIXED OPERATION IN AIRCRAFT FOR NORMAL OPERATION MAIN CONTROL SWITCH MUST BE IN ARM POSITION Side label for AK 451 AP with integral antenna 85 34 PERIODIC MAINTENANCE INSTRUCTIONS FOR CONTINUED AIRWORTHINESS REFERENCES FAR Part 91 207 Part 43 Appendix D 1 FAR Part 91 207 Paragraph d FAR Part 91 407 Refer to Appendix B for Maintenance Check List with Compliance Cross References PURPOSE To insure continued reliability of your ELT it must be inspected for damage 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 fail IMPORTANT NOTES The following inspections must be performed a mini
142. g AK 451 with optional Multi axes G Switch with 2 wire interconnecting ELT Main Unit and Remote Switch Unit D amp M Narco Joliet 111 55 55 2 13 E 5 232 Qui 1 RS5 232 Dut 1 iR5 232 Out 1 Gen R5 232 Out 1 Gen R5 232 Out 1 Gen 5 232 1 Tx Data Tx Data Hi Tx Gata H Tx Data Hi Tx Data Tx Data Hi 17 78 FT fe 14 27 zr NC Ground AN Ground ASS Ground AAC Ground AC Ground ANG Ground ON Lop Audible Buzzer ET 451018 ELT Model AK 451 Remote Une 451 004 232 Rxd Hi Gresnd DC Ground Remote ON S W Lo Remote ON Ligrm Le 3 07 de Out Remote Remote ON SW Lo OM Light La 5 222 Tad Hi 451 D181 3in T Adapter 4510181 T Adapter 451 0181 PN Optional GPS connector OPTIONAL MULTI AXES G SWITCH 450 000 1 zin Remote Wiring Cable Assembly 450 0041 RJ12 6PEC NOTE P N 450 0041M Optional Mil Spec M22759 18 or 35 AWG at specified length is available Figure 14 2c Wiring Diagram for AK 451 with GPS Position and 3 inch T adapter with Optional Multi axes G Switch with 4 wire interconnecting ELT Main Unit and Remote Switch Unit 112 BENODUKING GPs iso 5052050 usse TEN 24 55 56 2 13 5 232 Qui 1 R5 232 Out 1 RS 232 Out 1 Gen R5 232 Out 1 Gen R5 232 Out 1 Gen 5 232 1 Tx Dita Tx Data Hi Tx Ga
143. gn Manufacturer Comper avilland 51 53 60 80 83 84 87 90 DHC 1 Chipmunk all marks UK built Comet racer Vampire all marks Venom all marks Mosquito DH89 Dominie Devon Sea Devon Dove Sea Heron Heron A to D TEIZ D gt u D New Annex Il EASA list Issue 10 25 Feb 2008 Evaluation against Annex II criteria ____ m IRSE e p f ____ ____ fe e pe e Yes Yes WII WII lt opo NWII lt D lt Em WWII BED UK to Australia p 8 27 E xp lt wenn lt b lt Page 16 of 19 Table 1 EU states of Design powered aircraft fixed wing LLL Edgar Percival EP9 Prospector English Electric Canberra all marks Swordfish Firefly FLS Sprint 160 s n m gt tu er New Annex EASA list Issue 10 25 Feb 2008 Evaluation against Annex II criteria Historic ji Design Production State of Design TC event 1 1 55 lt 1 1 75 jand Comments _ es ves ______ es 5 Yes Annex II on the basis of the original French design fs _____ gt s _ mnm Wil ves ves orea WWII Yes Yes Yes Ves West wes lt M v D e lt b v lt b lt lt
144. gram for retrofitting AK 451 with Optional Multi axes G switch with 4 wire interconnecting ELT Main Unit and Remote switch unit Artex Pointer Kannad ACK Tech etc 110 Figure 14 1h Wiring diagram for retrofitting AK 451 with Optional Multi axes G switch with 2 wire interconnecting ELT Main Unit and Remote switch unit D amp M Narco Joliet 111 Figure 14 2a Wiring Diagram for AK 451 with GPS Position and 3 inch T adapter with 4 wire interconnecting ELT Main Unit and Remote Switch ei a 66 Figure 14 26 Wiring Diagram for AK 451 with GPS Position and 3 inch T adapter with 2 wire interconnecting ELT Main Unit and Remote Switch eoo tetas 67 Figure 14 2c Wiring diagram for 451 with GPS Position and 3 inch T adapter with optional multi axes switch with 4 wire interconnecting ELT Main Unit and remote switch unit 112 Figure 14 24 Wiring diagram for AK 451 with GPS Position and 3 inch T adapter with optional multi axes G switch with 2 wire interconnecting ELT Main Unit and remote switch unit 113 Figure 15 Battery Replacement for ELT Main 022 2 00 69 Figure 16 Battery Pack Replacement for ELT Main Unit Actual View 70 Figure 16 1 Battery Cell Replacement for ELT Main Unit Actual View 70 Figure 17 Bat
145. hat the ELT has been manually activated In ARM mode Green ON light flashes continuously 1 second 4 second OFF and the Buzzer sound periodically ELT swept Tone is heard on the 121 5 MHz VHF Radio This is to indicate that the ELT has been auto activated by the G switch 3 3 4 2 Antenna Check A low quality AM Broadcast Radio Receiver or Equivalent Test Equipment should be used to determine if energy is being transmitted from the Antenna When the Antenna of this Radio tuning dial on any setting 15 held about 6 inches from the activated ELT Antenna the ELT Aural tone will be heard see note below The ELT must be reset by pressing either the RESET push button located on the ELT Main unit or the ELT Remote Unit Note This is not a measured check but it does provide confidence that the Antenna 15 radiating with sufficient power to aid search and rescue The Aircrafts Receiver tuned to 121 5 MHz may also be used This Receiver however 15 more sensitive and could pick up a weak signal even if the radiating ELT s Antenna 1s disconnected Thus it does not check the integrity of the ELT System or provide the same level of confidence as does an AM Radio 80 3 3 5 TRANSMITTER FUNTIONAL TEST FOR ELT S ONLY The ELT S should be tested every month 3 3 5 1 Main Switch ON OFF SELF TEST Operation The ELT S has an OFF position This allows the beacon to be handled or shipped without nuisance activation Care should
146. he aircraft mounted antenna may be disconnected and a portable antenna mounted on the ELT mounting tray is then attached to the ELT mentioned procedures require no tools Flashing light indicator on the ELT 15 provided to alert the user that the ELT has been activated and is transmitting The ELT can be tethered to a survivor or a life raft It is designed to aid the Cospas Sarsat satellite and SAR teams in locating the crash site or survivor s The model AK 451 AF AP consists of an ELT main unit an aircraft fixed antenna a portable antenna coaxial cable assembly remote switch unit interconnect wiring assembly a T adapter connector an audible buzzer monitor a mounting tray velcro holders and portable soft case The ELT AF AP has an automatic activation G Switch It is activated automatically upon a crash or manually operated If for any reason a fixed mounting 15 not required the ELT AF AP be used as a Portable Device due to it 5 manual operated hand use Portability Check Local and or national regulations for this issue c Automatic Portable ELT AP with integral antenna The ELT is designed to be rigidly attached to the aircraft before the crash but readily removable from the aircraft after a crash It functions as an ELT AF during a crash sequence All mentioned procedures require no tools Flashing light indicator on the ELT 15 provided to alert the user that the ELT has been activated and 15
147. heck 3 4 8 Verification of Digital Message 3 4 9 Verification of Registration 3 4 10 Verification of ELT GPS interface if equipped 3 5 1 Regular Periodic Maintenance Test 3 5 2 Power Output Test 20 3 dBm at 121 5 amp 243 MHz 35 34 to 38 18 dBm 5W 1 58W at 406 028 MHz 3 5 3 Frequency Test 121 5 MHz 6 075 KHz 243 MHz 12 150 KHz 406 028 MHz 1 KHz 3 2 9 ATER Current Draw Tests 3 5 4 Audio Modulation 3 5 5 Transmitter Functional Test 3 5 6 Performance Test Marking and Log Book Entry Oo D 117 D Battery Replacement And Recharging Checks are to be performed every year E Shipping Transport Canada Civil Aviation Part V Airworthiness Standards Chapter 551 104 d 1 VI Verify the aircraft 24 bit address This Test is required for Canadian compliance only Tests are to be performed every year 2 51 ELT Main Battery Replacement Check 2 5 2 ELT Remote Unit Battery Replacement Check 3 4 4 Expiration Date Check 3 4 5 Battery Leakage Check 3 5 7 Shipping 3 4 8 Verification of Digital Message 3 4 10 4 24 Bit Address Maintenance Test Test Equipment Test Set TS 451 or equivalent is Test Equipment Spectrum Analyzer or equivalent s Test Equipment DC Current Meter or equivalent 118 APPENDIX C EMERGENCY LOCATOR TRANSMITTER RECOMMENDED SUPPLEMENTAL INSPECTION PROCEDURE FAR PART 91 OPERATIONS FAR Part 91 207
148. her aircraft which has a maximum empty mass including fuel of no more than 70 kg New Annex EASA list Issue 10 25 Feb 2008 Page 2 of 2 205 European Aviation Safety Agency MINOR CHANGE APPROVAL 10026866 Project reference 0010000546 001 Reference P EASA A C 12674 This Minor Change Approval is issued by EASA acting in accordance with Regulation EC No 216 2008 on behalf of the European Community its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation and in accordance with Commission Regulation EC No 1702 2003 to Niessler Handelsagentur Ferd Hanuschgasse 8 2345 BRUNN AM GEBIRGE AUSTRIA and certifies that the change in the type design for the product listed below with the limitations and conditions specified meets the applicable Type Certification Basis and environmental protection requirements when operated within the conditions and limitations specified below Original Product TC Number TCDS IM A 439 amp 223 TC Holder DIAMOND AIRCRAFT INDUSTRIES Model DV 20 DA 20 A1 EASA Certification Basis JAR VLA Description of Design Change Installation of an Ameri King Corporation AK 451 ELT as replacement for a Pointer 3000 Associated Technical Documentation EON 003 Engineering Order dated 24 07 09 EON 003 Installation Instructions dated 24 07 09 003 Maintenance Manual Supplement dated 24 07 09 Limitati
149. imilar materials recommend you use contact plating such as gold plating on the terminals before disposal D USE OF THE BATTERY 6 Immediately discontinue use of the battery if while using or storing the battery the battery emits an unusual smell feels hot changes color or shape or appears abnormal in any other See next section on Safety Warnings for Lithium Manganese Dioxide Cells and Batteries way Contact Ultralife if any of these problems are observed E PLEASE NOTE T Do not place the battery in microwave ovens high pressure containers or on induction cookware The performance and life expectancy of batteries depends heavily on how the batteries are used In order safety be sure to consult with Ultralife in advance regarding battery storage and 8 In the event the battery leaks and the fluid gets into one s eye do not rub the eye Rinse well specifications and equipment structures when designing equipment that includes these with water and immediately seek medical care If left untreated the battery fluid could cause atteries damage to the eye Refer to the MSDS for additional safety and handling instructions Ultralife Batteries Inc Li MnO Cells and Batteries January 14 2004 UBI 5135 Rev All specifications subject to change without notice The information contained herein is for reference only and does not constitute a warranty of performanc
150. ing point at least 24 inches in every direction Many times this is not possible but an effective plane can be constructed as follow A doubler layer of sheet metal such as aluminum can be mounted under the aircraft skin Alternatively four or more radials fastened to the underside of the fuselage skin can be used to fashion a ground plane Each radial can metallic type 22 AWG wire etc Tape should be at least 1 inch wide and each radial 24 minimum The ground plane connects to the shield of the RF antenna connector Resistance between the ground plane and shield connection should be maintained at 0 003Q maximum A star washer should be used between the antenna connector housing and ground plane Take precautions to guard against corrosion loosening etc Ground Plane On fabric covered aircraft or aircraft with other types of nonmetallic skin the manufacturer s recommendations should be followed in order to provide the necessary ground plane An acceptable method of accomplishing this is by providing a number of metal foil strips in a radial position from the antenna base and secured under the fabric or wood skin of the aircraft See diagram below Figure 5 Antenna ground plane for nonmetallic aircraft Note THE LENGTH OF EACH FOIL RADIAL SHOULD BE AT LEAST EQUAL TO THE ANTENNA LENGTH An effective light weight ground plane formed from radial strips of copper foil A doubler may be required to reinforce the installation f
151. ing ELT Main Unit and Remote Switch Unit 63 BLACK ON Lo Audible Buzzer RJ 12 6P6C ELT Model AK 451 6 5 4 3 2 Remote Unit 1 451 004 RJ12 6P4C R amp 232 Rxd Hi Pinout DC Ground RS 232 Rxd Hi 1 DC Ground Remote ON SW La Remate RESET SW Lo BE 2 NE 3 Remote ON Light Lo Remote ON SW Lo BE NS 3 EA 4 T 3 6 Vde Out Remote ON Light Lo l 4 5 RS 232 Txd Hi N 6 RJ 12 RJ 12 6 6 T Adapter 451 0181 x Remote RESET SW Lo E IN Existing Aircraft 4 wire or 5 wire ELT Systems Artex Pointer etc 6 in Wiring Adapter with RJ12 6P6C Plug and Molex Amp Connector 4 pin NOTE Optional Mil Spec M22759 18 or 35 24AWG at specified length is available Figure 14 1c Wiring Diagram for retrofitting AK 451 with 4 wire interconnecting ELT Main Unit and Remote Switch Unit Artex Pointer Kannad ACK Tech 64 ON Lo Audible Buzzer RJ 12 ELT Model AK 451 9 5 4 3 2 Remote Unit 1 451 004 RJ42 6P4C i RS 232 Rxe Hi Pinout EN DC Ground RS 232 Rxd Hi 4 E DC Ground Remote RESET SW La Remote ON SW Lo Remote RESET SW Lo Remote ON Light Lo 1 2 3 Remote ON Light L f 5 ET NES 5 RS 232 Txd Hi 5 6 2N RJ 12 6P6C RJ 12 T Adapter 451 0181 AN Existing Aircraft 2 wire ELT Systems Joliet Narco D amp M etc PEN Wiring Adapter with
152. ins 6 separated individual acceleration switches that allows opearation an different axes Lacking of the remote optional multi axes acceleration switch assy has no effect to the ELT operation This multi axes sensing using active axis parallel to the longitudinal axis of the aircraft moving in the forward direction Part No 450000 1 Dimensional Drawing for Mounting Tray for ELT Main Unit with Optional Multi axes Acceleration Switch Figure 2 3 107 DC Ground Remote ON 54N Lo NC OPTIONAL MULTI AXES G SWITCH 450 000 1 ELT Model AK 451 5 232 Rxd Hi Dc Ground Remote RESET SW Lo Remote ON SW Lao Remote ON Light Lo 5 232 Txd Hi DC Ground NC Remote NIC OPTIONAL MULTI AXES G SWITCH 450 000 1 ELT Model AK 451 5 232 Rxd Hi DC Ground Remote RESET 5W Lo Remote ON EW Lo Remote ON Light Lo RS 232 Txd Hi ON Lo Audible Buzzer R 232 Rxd Hi Dc Ground 451 018 3 6 T Adapter RJ12 68P6 451 0181 J 5 1 RJ12 6P8C 4 2 a 3 1 Remote Unit id d 1 451 004 450 0041 Remote Wiring Cable Assembly Remote RESET SW La Remote ON SW Lo Remote ON Light Lo 3 Out RJ12 6P6C T Adapter 451 0181 Wiring between P1 and P2 must be as short as possible 12 max to ensure no damage upon crash For crash safety RJ12 6P6C Pinout RS 232 Rxd Hi DC
153. inutes of the hour Notify any nearby control tower of your intensions in accordance with AC 43 13 2B Section 12 22 Note 3 If outside of the US always follow all local or national regulations for testing of ELT s Warning Do not allow test duration to exceed 5 seconds Any time the ELT is activated it is transmitting a 121 5 MHz distress signal If the unit operates for approximately 50 seconds a live 406 MHz satellite distress signal is transmitted and is considered valid by COSPAS SARSAT satellite system 2 44 ELT Self Test Place the main switch position from OFF to The buzzer sounds and the 2 ELT Green ON lights shall illuminate for 4 seconds then extinguish After 25 seconds 406 MHz test signal 15 transmitted However it is specially coded as a self test signal that is ignored by the COSPAS SARSAT satellites Verify that both the ELT Green lights located on the ELT Main Unit and the ELT Remote Unit must remain extinguished and no buzzer sound after 25 seconds Verify Audio ELT Sweep Tone 15 silent on the Com Receiver 57 Activate the ELT using applied force The direction forward force activation 15 indicated on the ELT The AK 451 AF AP ELT can be activated by using a rapid forward throwing motion coupled by a rapid reversing action Verify that the ELT has been activated by use of the Wattmeter the Airplane s Radio Communications Receiver when tuned to 121 5 MHz or other mea
154. ions specified below TC Holder SEE APPLICATION FOR LIST Model REFER TO LIST OF MOTOR Model GLIDERS AND GLIDERS IN THE Model EON001 INSTALLATION Model INSTRUCTIONS AND ATTACHED Model APPLICATION EASA Certification Basis CS 22 Description of Design Change Installation of an Ameri King corporation AK 451 ELT as replacement for a Pointer 3000 Associated Technical Documentation EON 001 Engineering Order dated 24 07 09 EONO01 Installation Instructions dated 24 07 09 001 Maintenance Manual Supplement dated 24 07 09 Limitations None Conditions 1 Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product 2 The installation of this modification by third persons is subject to written permission of the approval holder and holding and disposal of the approved appropriate documentation 3 The approval holder shall fulfil the obligations of Part 21 Paragraph 21 A109 MINOR CHANGE APPROVAL 10027068 Niessler Handelsagentur EASA Form 83 Issue 1 MINOR CHANGE APPROVAL 10027068 Niessler Handelsagentur 2 2 EASA Form 93 Issue 1 1 2 157 158 European Aviation Safety Agency MINOR CHANGE APPROVAL 10026863 Project reference 0010000520 001 Reference P EASA A C 12673 This Minor Change Approval is i
155. itch is mandato usuall 0 Revision 0 Seite 1 2 208 Job 15 71 18 TDI 18 8672 18 150 18 7445 150 2 Job 15 73 PA 18 18 6112 PA 18 150 18 7609058 150 2 PA 18 18 6111 18 150 18 4401 55 13 430 18 18 5587 18 150 18 7505 131 131 120 18 18 5500 18 150 18 8872 131 131 117 18 18 156 18 150 18 7736 131 T 131 111 18 18 6882 18 150 18 8691 T 131PA T 131 114 PA 18 105 18 2415 PA 18 150 18 8629 131 T 131 124 PA 18 150 18 7694 18 150 18 8119 131 T 131 102 18 150 1042 18 150 18 8009053 131 131 103 18 150 18 7510 18 150 18 8826 131 131 126 18 150 18 4291 18 150 1809019 131 131 110 PA 18 150 18 6336 18 180 18 8115 131 131 112 PA 18 150 18 5513 18 180 18 6765 T 191PA 131 122 19 18 1459 T 131PA T 131 115 19 18 1582 131 131 118 19 18 2056 T 131PA T 131 109 3 Approval Niessler Handelsagentur as the holder of the current Minor Change Approval is responsible for the instructions for continued airworthiness of this change In case of any known issues rising due to this modification inform Niessler Handelsagentur so that appropriate actions can be taken 004 Page 2 of 3 01 04 2010 209 Email Response from EASA Ameri King regarding Acceptability of FAA Form 8130 3 Export Form in EU Europe Union From Ameri King Corp
156. ith The form 8130 3 16 filled once by you for each unit or each lot produced In accordance with the old bilateral agreements it will be accepted in all EU member states including the specific areas having the specific tax status like Canary Island Norway Switzerland and Iceland As the import country is not mentioned at all on the certificate it is issued once by you when manufacturing the unit like our Form One We assume that the 8130 3 will be accepted in all the named countries based on the grandfathered existing bilateral agreement with the main players in EU and the US Due to the fact that the new bilateral 15 not in place we cannot guarantee that especially as some countries seem not to be accepted by the US side to be eligible to export into the US Unless you state FOR DOMESTIC SHIPMENTS ONLY on the Form 8130 3 the Form issued at the end of the production process is intended to be used for import into the EU system as well In general the form 15 issued after production and kept for the life time of the unit Please come back to me if there are complaints from the European customers Best regards Friedhelm EASA European Aviation Safety Agency Parts and Appliances Section Friedhelm RUNGE 49 221 89990 4084 friedhelm runge easa europa eu 211 Japan Civil Aviation Board Approval From 3rili mailto h niiyama soumu go jp Sent Wednesday April 07 2010 10 52 AM To Yasuhiro Kato Cc Takashi Eno
157. ith GPS Position AK 451 AF AP 406 MHz ELT Emergency Locator Transmitter 406 121 5 243 0 MHz with GPS Position AK 451 AP S 406 MHz ELT Emergency Locator Transmitter 406 121 5 243 0 MHz with GPS Position Note This TSO Authorization do not constitute the TSO C142 or 42 for Non Rechargeable Lithium Cells and Batteries This TSO Authorization do not include 8 91 or C126 for the Antennas Your Quality Control System as defined in your Quality Control Manual currently on file at the Los Angeles Manufacturing Inspection District Office is considered satisfactory for production of this article at your Huntington Beach California facility Purpose Aviation Safety Professionalism Technical Excellence Pride Highest Quality 148 t Carlton W As required by the TSO the following statement must be furnished with each manufactured unit The conditions and tests required for TSO approval of this article are minimum performance standards It is the responsibility of those installing this article either on or within a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standard TSO articles must have separate approval for installation in an aircraft The article may be installed only if performed under 14 CFR part 43 or the applicable airworthiness requirements Any design changes to this TSO article must be forwarded to this office as outlined in 1
158. iv 20ms 95 e Adjust the reference amplitude to place the peak of the carrier slightly above the top graticule fine e Enable the fine amplitude adjustment Set the carrier peak to exactly the top of the reference line Read the displayed amplitude e Repeat for the 243 0 MHz harmonic change the Center Frequency to 243 0 MHz other settings remain the same e The minimum allowed amplitude on 121 5 MHz and 243 0 MHz is 20 dBm after 3 minutes of operation 3 5 2 2 406 028 Power Output Note The power output is approximately 35 34 38 18 dBm Ensure adequate attenuation is inserted in line between the ELT s 406 028 MHz output and the input to the spectrum analyzer to protect the analyzer s input circuitry Connect the equipment as shown below ELT BNC Applicable attenuator Spectrum Analyzer Connector Set the Spectrum Analyzer as follows Center freq 406 028 MHz Span 1 MHz Resolution bandwidth 1 MHz Vertical display 10dB Div Sweep Auto Peak Avg Peak Reference level 30 dBm Time Div 20ms Max hold On Attenuator as required on Input Turn the ELT on and wait approximately 50 seconds for the 406 028 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 406 028 MHz power output should be 35 34 38 18 dBm 3 42W min to 6 58W max after 3 minutes of operation
159. ks Nalrus ackaroo imy replica 3 A a D lt b D lt D hruxton lt ______ _____ peii ZE 9S gt lt gt gt 0 al 23 Nestland sander New Annex EASA list Issue 10 25 Feb 2008 Page 19 of 19 182 Table 2 Non EU states of Design powered aircraft fixed wing D State of Design anufacturer Evaluation against Annex II criteria of Aviation 9 Br Pre Comments a De Havilland DHC 1 Chipmunk es A 22 DHC 2 Mk III DHC 2 Beaver Mk I and II L 20 Viking Turbo Beaver is not DHC 3 Otter Viking All models eet ir p henyang CIS An 2 ra 2 D D tu 2 I tu j Y D D 4 nne See Consolidated Fleet USA ho gt gt lt lt lt io 8 d un es Russian built aircraft not orphan ___ ___ ____ ___ _____ 2 st ves es ___ _________ 56 ____ ____ ____ _________ Lavochkn ____ tt 11 jve es es e korea _ ves___ ves ves SS MiG 15 series Korea es es ves es Polikarpov Po 2allvarans Es ____ f T _ TS9 TS e ves anc replicas __ ____ ___
160. l e Use care when leaving your ELT and with whom you leave it with Ensure that they are aware of the device and know the ramifications of causing a false alarm A lot of false alarms are generated by curious individuals e Maintain your ELT Ensure that the batteries are within their expiration date and that all manufacturer recommendations are followed e Finally realize that the COSPAS SARSAT satellites are very good at what they do detecting emergency ELTs An activation of a 406 MHz for just a few seconds will usually be detected After a few minutes it will usually be detected and located This is good if you re in distress but if you re not you just generated a false alarm 4 2 3 Report false alarms Should there be an inadvertent activation or false alarm it must be reported to the nearest search and rescue authorities The information that should be reported includes the ELT Unique Identifier Number UIN Date Time duration and cause of activation as well as location of ELT at the time of activation Outside the United States contact your National Authority 4 2 4 report false alarms in the United States contact any of the following Atlantic Ocean Gulf of Mexico USCG Atlantic Area Command Center Tel 757 398 6390 Pacific Ocean Area USCG Atlantic Area Command Center Tel 510 437 3700 USCG HQ Command Center From any location Tel 800 323 7233 RR Tel 1 888
161. l Information 1 Irritancy The electrolytes contained in this battery can irritate eyes with any contact Prolonged contact with the skin or mucous membranes may cause irritation 2 Sensitization No information is available at this time 3 Carcinogenicity No information is available at this time 4 Reproductive toxicity No information is available at this time 5 Teratogenicity This product contains a known teratogen as indicated in the chemical information in section 2 6 Mutagenicity No information is available at this time Section 12 Ecological Information Not applicable to this material product Section 13 Disposal Considerations Batteries must be completely discharged prior to disposal and or the terminals must be taped or capped to prevent short circuit This product does not contain any materials listed by the United Stated EPA as requiring specific waste disposal requirements When completely discharged it is not considered hazardous Disposal of large quantities of lithium power cells may be subject to Federal State or Local regulations Consult your local state and provincial regulations regarding disposal of these batteries ULTRALIFE BATTERIES MSDS023 FA1284 Rev F OCT 01 2007 Page 4 of 6 Rev Date 31 2007 222 Section 14 Transport Information Ultralife s lithium metal primary cells and batteries and lithium ion cells and batteries are classified and regulated as Class 9 dangerous
162. l risk if attention is given to both safety and enhanced performance capability 2 Personnel who use or handle Li Mn0 cells and batteries must be familiar with their properties safety precautions handling procedures and transportation and disposal requirements For information on transportation regulations for lithium batteries refer to Ultralife document UBI 5120 Ultralife Batteries Lithium Battery Transportation Regulations 3 Insure that batteries are protected from heat short circuits compaction mutilation or other abusive physical or electrical conditions during storage use and disposal Dispose of lithium batteries in accordance with all applicable federal state and local regulations 4 Contact Ultralife for questions regarding the proper use and limitations of cells and batteries HANDLING Observe the following guidelines when handling lithium cells and batteries 1 Store batteries in a cool dry ventilated area 2 Keep batteries in their original packaging until ready for use Do not store cells or batteries loosely in boxes or bins 3 Use special care in handling batteries Make sure they are not punctured crushed mishandled disassembled or exposed to storage temperatures exceeding the maximum specified temperature on the product technical data sheet 4 Inspect batteries prior to use and do not use if there is any evidence of leakage or deformity Consult the Material Safety Data Sheet MSDS for precautions
163. ld not be construed as legal advice Aircraft listed are within the definition of Annex II to Regulation 1592 2002 Because of the subjective nature of Annex II the proposed revision see at the end of this table has been used to aid in interpretation of the current Annex II only compliance with paragraphs a and d are considered This list has been produced in conjunction with the NAAs of the State of Design Not every type of aircraft pre 1939 or sailplanes pre 1955 is listed because these can be considered to be Annex II on the basis of their being significant steps in aviation development Sailplanes are listed and in the case of Germany the list is exhaustive This is not the case for some other countries and if an NAA has not provided a list the criteria designed before 1955 built before 1975 has been used In many cases the NAA assessment of significant step in development has been taken Aircraft for which a civilian TC or equivalent approval is known this is listed The absence of a TC number does not mean that the aircraft has no formal civilian approval just that at the time of writing there was no immediate evidence of this fact Warbird rebuilds that are believed to be underway in the EU are listed and this includes aircraft currently not airworthy but which could be put back into airworthy condition Warbird rebuilds in non EU countries of types not yet seen in the EU are not included The list does not include aircraft th
164. le for installation on Canadian registered aircraft TCCA will communicate this airworthiness approval to Industry Canada Model Number Reference AK 451 AF TSO C126 C9la AK 451 AP TSO C126 C91a 451 5 TSO C126 C91a NOTE The approved battery pack for the above ELTs is the Lithium Manganese Dioxide LiMnO Part No 4500010 1 It is noted that ELTs require a Radio Equipment RE approval by Industry Canada IC in order to qualify for use in Canada Accordingly Ameri King Corporation is requested to apply directly to Industry Canada to obtain this RE approval Please forward proof of the approval by IC to Mr J M J Levesque at the address shown Canada E 151 24 immediately below Upon receipt of this evidence Transport Canada will then include the subject ELT models on the Approved Emergency Locator Transmitters list showing the only equipment eligible for installation on Canadian registered aircraft This list is available at http www tc gc ca CivilAviation certification elt htm Mr J M J Levesque Senior Project Manager National Aircraft Certification Branch AARDE Civil Aviation Transport Canada Tower C Place de Ville 3 Floor 330 Sparks Street Ottawa Ontario 0 5 Should you require further information please do not hesitate to contact Swan telephone at 613 952 4439 by facsimile at 613 996 9178 or by email at paul swan g tc gc ca J D Turnbull Chief
165. low 4 Do not damage cell fill ports or glass to metal seals as electrolyte leakage can result Do not place the battery in fire or heat the battery Do not install the battery backwards so the polarity is reversed e Do not connect the positive terminal and negative terminal of the battery to each other with any metal object such as wire Do not carry or store battery together with bracelets necklaces hairpins or other metal objects 5 Do not charge primary lithium batteries Charging is considered severe abuse and may result in venting fire or explosion under some conditions 6 Donotuse a lithium battery any application except the one for which it is intended 7 Do not short circuit battery terminals High current may lead to excessive heating e Do not pierce the battery with nails strike the battery with a hammer step on the battery or otherwise subject it to strong impacts or shocks 8 Donotreplace fuses if they activate e Do not solder directly onto the battery Do not expose battery to water or salt water or allow the battery to get wet C INSTALLATION 2 Do not disassemble or modify the battery The battery contains safety and protection devices 1 Installing Battery Packs in the Equipment To avoid damage to the battery pack make which if damaged may cause the battery to generate heat explode or ignite sure the battery pack is positioned away from heat sources in the equipment 3 Do not place the battery in
166. ment subject to the following TEMPORARY REMOVAL No person may operate the aircraft unless the aircraft records contain an entry which includes the date of initial removal the make model serial number and reason for removing the transmitter and a placard located in view of the pilot to show ELT not installed TEMPORARY REMOVAL No person may operate the aircraft more than 90 days after the ELT is initially removed from the aircraft FAA Part 43 Appendix D 1 Each person performing an annual or 100 hour inspection shall inspect where applicable the following components of the radio group 1 Radio and electronic equipment for improper installation and insecure mounting 120 2 Wiring conduits for improper routing insecure mounting and obvious defects 3 Bonding and shielding for improper installation and poor condition 4 Antenna including trailing antenna for poor condition insecure mounting and improper operation Sec 91 407 Operation after maintenance preventive maintenance rebuilding or alteration a No person may operate any aircraft that has undergone maintenance preventive maintenance rebuilding or alteration unless 1 It has been approved for return to service by a person authorized under Sec 43 7 of this chapter and 2 The maintenance record entry required by Sec 43 9 or Sec 43 11 as applicable of this chapter has been made b No person may carry any person oth
167. ments of the above noted specificaten License applications where applicable to use certified equipment are acted on accordingly by the issuing office and will depend on the existing radio environment service and locaton of operation This certificate is issued on condition that the holder complies and will continue to comply with the requirements of the radio standards specifications and procedures issued by Industry Canada DATE OF ISSUE November 26 2008 La certification du saxjnibe seulement que le mal nel satisfait aux exigences de norme indigu e ci dessus Les demandes de licences n cessaires pour l utilisabon du mat riel certifi sont trait es en cons quence par le bureau de d livrance et d pendent des conditions radio ambianies du service et de l amplacement d exploitation Le pr sent certificat est d livr condition que le titulaire satisfasse et continue de satisfaire aux exigences et aux proc dures d Industrie Canada WM LL William H Graff President 153 Pagina de 2 REPUBLICA FEDERATIVA DO BRASIL AG NCIA NACIONAL DE TELECOMUNICACOES ANATEL Certificado de Homologacao Intransferivel N 0693 09 5085 Validade 31 03 2011 Emiss o 31 03 2008 Solicitante Fabricante HAVES AVIACAO LTDA AMERI KING CORP RUA MAJOR CAETANO COSTA 0201205 SANTANA SAMPSON LANE 17881 02012 050 SAO PAULO SP HUNTINGTON BEACH Este documento homologa nos termos
168. mum of one time every year 341 y Secure Inspection Inspect the ELT Main Unit and Mounting Tray to insure all fasteners and mechanical assemblies are secure 3 4 2 Corrosion Inspection for Coaxial Cable Inspect the Coaxial Cable connecting the ELT Main Unit to the Antenna for cuts or abrasions on its outer Jacket Disconnect the BNC connectors on each end Examine both the BNC connectors and the mating plug on the Antenna and the ELT Main Unit for any signs of corrosion 3 4 5 Corrosion Inspection for Remote Wiring Modular Cable Inspect the Remote Wiring Modular Cable connecting the ELT Main Unit to the Remote Unit of signs of wear or abrasion on its outer jacket Remove the Modular Connecting Cable and inspect and jack and plug assembly for corrosion 344 Expiration Date Check Check the expiration date of the ELT Main Unit and the Remote Unit Batteries Replace if necessary 3 4 5 Battery Leakage Check Remove the Battery Case and inspect the Battery Compartment for signs of corrosion or battery leakage If any battery leakage 15 present all batteries must be replaced The Battery useful life is 5 years 3 4 6 Operational Test After completing the above inspections a Functional Test as described in Paragraph 3 3 must be performed to verify proper operation 3 4 7 1 G Switch Check Ensure that the Main Switch on the ELT main unit must be selected at ARM position at all times Activate the ELT using applied force The direction for m
169. n the desktop which contains the coordinate of a location Sen erii Note You can use Notepad Editor Program to modify the coordinate of this location pecca Fue connected 01 this menu 02 disconnect 03 read ID 04 read SN Ameri King GPS Location Text file 05 selftest 06 write ID 19 read SEL VHF 20 write SEL VHF gt Ameri King GPS Location Notepad 3 3 3 3 3 3 3 3 3 3 3 3 3 3 JE 3 3 JE 3 JE 3 3 JE JE JE 3 9 JE JE 3 JE JE 3 3 3 JE 3 3 9 File Edit Format View Help RMERI KING AK V1 B LAN 33 4219 3 X 3 3 JE 3 X JE JE 3 X JE 3 X 9 9 X X JE 3 3 X X X IE 3 9 Bw 117 5984 L Figure 8 e Inserting Ameri King GPS Location Coordinate See Figure 9 l single Click on Ameri King GPS Location The file contains the coordinate of Ameri King GPS Location 2 Set the switch of the ELT to ON position 3 single Click on button to insert the coordinate of Ameri King GPS Location to the ELT 4 DO NOT turn the ELT off Wait for 50 seconds and you will receive 30 Hex digits Ignore the first 6 digits coming from the ELT that contains the coordinate of the Ameri King GPS Location See Figure 10 Use the 406MHz Decode Program to verify the coordinate input Figure
170. nique ID number Owner Operator Information Name _________________________ E mail Telephone Oe ar Fax a Fas L este Li Hema Oter L Lese ar Fax Mailing Address City State Province ZIP Postal Code Country Aircraft Information Registration Tail Number Survival Equipment Usage Deployable Commercial Non commercial Government Miltary L Government Non miltary Fixed Type O Singie engine Propeller Singie engine Jet Multi engine Mutti engine Jet Helicopter other Aircraft Manufacturer Model Color Seating Capacity Principal Airport Additional Data Radio Equipment Check all that apply Jur Hr 1588 Contact Information indicate someone other than the owner Mame of Primary 24 Hour Emergency Contact Mame of Alternate 24 Hour Emergency Contact JANIS Telephone Telephone cotum 12 3 Home viori 0 Fux omae lean CI Home C Far Cenaa ote Ci look CI Ceia C Fax L ote Signature H you have any questions about this form or with ELT registration general please call 1 E88 212 S AVE 7283 or 301 817 4515
171. ns see Note 1 The ELT must then be reset by pressing either the RESET push button located on the ELT main unit or the ELT Remote Unit Note 1 This is not a measured check It only indicates that the G Switch 15 working 58 Detail Test Procedure for ELT ID Programming and Self Test Turn the main switch from the OFF position to the position The Buzzer sound and the 2 Green ON lights shall illuminate for 4 seconds then extinguish This 15 to allow coding programming during the next 20 seconds window and self test for 1 second thereafter The ELT may be ID coding programming during the aforementioned 20 seconds window period If no programming happened the ELT will then enter the Self Test Mode for 1 second thereafter Self Test takes 25 sec Self test results after 25 seconds 15 If the self test is passed the Green ON light is steadily extinguished and no buzzer sound ELT swept Tone must be silent on the 121 5 MHz VHF Radio If the self test is failed the Green ON light flashes as defined below 1 flash Internal Data stored in Memory at fault 2 flashes Distress ID stored in Memory at fault 3 flashes Battery voltage is low Useful Life Battery Voltage setting 4 flashes Vcc supplies for F2 or F1 at fault 5 flashes RF power level 33 dBm 406 028 MHz 7 flashes F1 F2 VHF RF power level 17 dBm 121 5 243 MHz 9 flashes PLL locked in F3 or F1 or F2 at fault Continuous flash
172. nts Cospas Sarsat T 001 47 CFR Part 87 FCC requirements Note Per FCC regulations 47 CFR 2 902 the ELT 15 tested per Verification method Note The AK 451 15 certified to meet the requirements of FAA 5 126 91 and EASA 5 2 126 EUROCAE ED 62 For use outside the US or EASA member states contact your local civil aviation authority for ELT requirements 1 2 4 Programming Ameri King will program in any protocol at no charge The AK 451 supports all available worldwide ELT protocols in long message and short message For a complete ELT protocol please see C S document G 005 and T 001 available at www cospas sarsat com For use outside the US please contact your local civil aviation authority for accepted or required programming protocols The AK 451 supports the following protocols 1 241 User Location Protocols Long Message Coding ELT with beacon serial identification Coding ELT with aircraft operator designator and a serial number Coding ELT with aircraft 24 bit address Coding ELT with aircraft nationality and registration marking 18 1 2 4 2 Standard Location Protocols Long Message Coding ELT with 24 bit address Coding ELT with Type approval number and a serial number Coding ELT with aircraft operator designator and a serial number 1 2 4 3 National Location Protocols Long Message e National Location Protocol Coding for ELTs 1 2 4 4 User non location Protocol Short
173. ocating device when it is necessary to leave the scene of the accident Automatic Portable ELT AP Configuration and survival ELT s configuration In the event of a crash the 451 activates automatically and transmits the standard swept tone on 243 121 5 MHz lasting until battery power is gone This 243 121 5 MHz signal 15 mainly used to pinpoint the beacon during search and rescue operations For the first 24 hours of operations a 406 MHz signal is transmitted at 50 second intervals This transmission lasts 520 ms and contains identification data programmed into the beacon and is received by COSPAS SARSAT satellites The aircraft GPS NAV latitude longitude data position will also be transmitted 1f GPS NAV 15 connected with the ELT The transmitted data 1s referenced in a database maintained by the national authority responsible for ELT registration and used to identify the beacon and owner Accuracy Doppler positioning is employed using both 121 5 MHz and 406 signals Position accuracy of the 121 5 MHz signal is within an area of approximately 15 20 km radius about the transmitter Due to the better signal integrity of the 406 MHz its location accuracy is within about a 1 2 km radius If the GPS NAV position data 15 transmitted the accuracy of the AK 451 will narrow to 22 meters typically 3 3 TRANSMITTER FUNTIONAL TEST The ELT should be tested every month 74 WARNING Do not allow test duration to exceed 5 second
174. of the standard 6 foot coax 15 recommended when possible Composite Aircraft Installation Except for preparation instructions and installation of a ground plane installation 15 the same Refer to FAA Advisory Circular 43 13 2B Section 310 for complete information See Appendix C 36 5 750 cra F 2 952 4 265 5 500 5 750 ur ue er 0 2 875 m d 4 1 0 41 IN 1 CESS E 2 D MF FF GF B FF FG 240 2221 21221 21214 15 approximately Main Frequency 406 028 MHz Homing Frequency 121 5 MHz FREQUENCY 406 028 and 121 5 MHz 3 Power Qutput 25 Watts 4 Mating Connector BNC connector 9 Polarization e 121 5 MHz Vertical e 406 028 MHz Linear or right hand circular 6 Radiation Pattern e 121 5 MHz Omni directional in the horizontal plane e 406 028 MHz Hemispherical 7 Impedance 90 Ohms Nominal 8 Elevation 5 to 60 9 Gain Vertical Plane Between 3dBi and 4dBi over 90 of the region mE bounded by the elevation angle 5 to 60 10 Gain Variation Azimuth 3 dB 11 Approvals TSO C126 C91a DIAGRAM NUMBER elt Van Whip Antenna 451017 1B Figure 6 Whip Antenna 451017 18 9 DIAGRAM S p 5 500 4 265 2 950 2 2 010 0 125 0 250 4
175. omeone attempts to register a ELT reported as stolen NOAA or your national authority will notify the appropriate Police Department Visit the COSPAS SARSAT website for more detailed information www cospas sarsat org 4 2 RESPONSIBILITY 4 2 1 Responsible Use The Ameri King AK 451 should only be used in situations of grave and imminent danger What exactly does this mean Technically speaking you should only activate your ELT when all other means of self rescue have been exhausted This means you have tried to use your cellular satellite phone signaling mirrors strobe lights or any other safety device you may have When all else fails and you feel your situation has truly become extreme ask yourself the following questions Am I in danger of losing life limb eye sight or valuable property if I am not rescued soon Amlin danger of not surviving the night or upcoming hours if not rescued soon If you answer yes with confidence to these questions it is time to activate your ELT 102 4 2 2 Preventing False Alarms e Ensure that your ELT is registered with NOAA or your national authority This does nothing to reduce false alarm rates but does have a dramatic effect on the impact of a false alarm If the ELT is properly registered the situation will be resolved with a phone call most of the time It will also help speed rescue in an actual distress Test your ELT in accordance with the recommendations enclosed in this manua
176. on registering beacons in other countries http www Ameri King com NOTICE FOR ELTS THAT HAVE A COUNTRY OF REGISTRATION OTHER THAN THE USA PLEASE CONTACT THE APPROPRIATE CIVIL AVIATION AUTHORITY IN THAT COUNTRY FOR GUIDELINES AND DOCUMENTATION NEEDED TO ASSURE PROPER REGISTRATION Logbook Entry Enter the date the test technician s initials and whether the ELT passed or failed into the aircraft s logbook 3 4 10 Verification of ELT GPS interface if equipped Note This test is not mandatory per FAR 91 207 d however Ameri King strongly recommends that it be performed as part of periodic maintenance at least every year 3 4 10 1 ELT to GPS Interface Information For details on the installation and use of the ELT Computer Test Set TS 451 please contact Ameri King Corporation to request the brochures and Operation Manual for the ELT Computer Test Set When used with ELT s that are programmed for Standard Location 24 bit protocol the ELT to be program itself to the aircraft s 24 bit address This feature will allow the ELT to be transferred between aircraft This makes maintenance of the ELT a simple matter of replacing the ELT Note There is no electronic connection between TCAS or Mode S systems and the ELT only the ID number is common The AK 451 receives position data longitude and latitude from the aircraft s on board GPS system The ELT may be programmed with the aircraft s 24 bit address When used with ELT s that are
177. ons None Conditions 1 Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product 2 The installation of this modification by third persons is subject to written permission of the approval holder and holding and disposal of the approved appropriate documentation 3 The approval holder shall fulfil the obligations of Part 21 Paragraph 214 109 MINOR CHANGE APPROVAL 10026866 Niessler Handelsagentur EASA Form 93 Issue 1 1 2 206 European Aviation Safety Agency This Approval shall remain valid unless otherwise revoked For the European Aviation Safety Agency Date of issue 18 08 2009 Roger HARDY Certification Manager General Aviation MINOR CHANGE APPROVAL 10026866 Miessler Handelsagentur EASA Form 83 Issue 1 2 2 207 nderungen Reparaturen Ersatzteile hang B f r LTH 49 I 2 nderungen Reparaturen und Ersatzteile Flugtechnik an historischen Luftfahrzeugen una NON DU Verordnung 2005 an sterreichischen Luftfahrzeugen Die Genehmigung der Daten Bauteile ersetzt entsprechend Instandhaltungsbestimmungen Abschnitt V ZLLV 2005 und die Fa Tel O664 230 7557 Niessler Fax 02236 323 tae
178. or flashes meaning Next in order to check G Switch Throw the ELT forward and backward 2 3 times the ELT must activate ELT swept Tone must be heard on the VHF Radio 0121 5 MHz The 2 LED lights flashing 4 sec OFF 1 sec ON synchronized with the Buzzer sound 4 sec OFF 1 sec ON Next Press either RESET Button no ELT swept tone heard on the 121 5 MHz VHF radio Both LED Lights and Buzzer must be extinguished Next Press the ON Switch on the Remote Switch Unit ELT swept Tone must be heard on the VHF Radio 2121 5 MHz The 2 LED lights flashing 4 sec OFF 1 sec ON synchronized with the Buzzer sound 4 sec OFF 1 sec 3 3 0 3 For normal operation leave the ELT Main Switch ARM position at all times No ELT swept tone heard on the 121 5 MHz VHF radio No LED light illuminates No buzzer sound 75 Detailed Operation Check 3 3 1 Switch ON OFF ARM Operation In normal operation the Main Switch located on the ELT main unit must be in the ARM position In the event of a crash an acceleration activated crash censor G switch turns the ELT on automatically when the ELT experiences a change in velocity or deceleration of 4 5 fps 0 5 fps Activation is also accomplished by means of the cockpit mounted remote control unit or the ON switch on the ELT main unit To reset the ELT press either RESET switch on the remote control panel or on the main unit The ELT has an OFF position This allo
179. or near fire on stoves or other high temperature locations Do not 2 cea to Dropping Be xis to use a battery pack locking mechanism to place the battery in direct sunlight or use or store the battery inside cars in hot weather Doing Buc e battery pack from being ejected if the equipment is dropped or receives a sudden so may cause the battery to generate heat explode or ignite Using the battery in this manner may also result in a loss of performance and a shortened life expectancy 3 Preventing Short Circuits and Reversed Connections Use a terminal structure that makes it unlikely the terminals will be shorted by metallic objects such as rings necklaces clips hairpins etc Structure the battery and the terminals to the battery in such a way that the battery pack cannot be put in backwards when installed in the equipment 4 Inclusion in Other Equipment If the battery is built into other equipment use caution to 4 Ifthe device is to be used by small children the caregiver should explain the contents of this strictly avoid designing airtight battery compartments document to the children and provide adequate supervision to ensure the device is being used appropriately 5 Terminal Materials in the External Equipment Use materials that are highly resistant to corrosion such as nickel or nickel plated copper If contact resistance is an issue we 5 When the battery is discharged insulate the terminals with adhesive tape or s
180. or resistance to impact vibration ice washing etc and can serve as connection points for the radials Specific antenna installation instructions follow Also AC 43 13 2B paragraph 310 provides additional guidance for antenna installations 34 2 2 2 2 ANTENNA INSTALLATION Please refer to FAA AC 43 13 for guideline After determining the Antenna mounting location per paragraph 2 2 2 1 install the Antenna as shown in Figures 6 7 8 and 9 l Drill a diameter hole or pattern holes in the aircraft structure at the Antenna mounting location 2 Install the Antenna and determine if the Antenna meets the static load requirements If not a Double should be fabricated A 100 time of antenna weight force applied in the direction shown in Figure 3 should not cause an appreciable distortion in the aircraft skin 3 Antenna is being mounted on a non conductive portion of the airframe a supplementary ground plane must be installed The supplemental ground plane must have a minimum diameter of 36 and be centered about the base of the Antenna This maybe provided using a conductive metallic coating painted on the inside ofthe aircraft structure SPRAYLAT Series 559 or equivalent or may be fabricated out of aluminum foil and attached to the inside of the aircraft structure A Doubler Plate should be used to provide increased surface contact area between the ground plane and the Antenna 4 Assemble of the Antenna as shown in Figure 3
181. oration To EASA European Aviation Safety Agency Attn Mr Runge Friedhelm Subject Request for Guideline Acceptability of FAA Form 8130 3 Export Form in EU Application Authorized Release Certificate FAA Form 8130 3 New TSO Article Date October 2 2009 Dear Runge Please advise if the FAA form 8130 3 export form issued to any of 27 EU countries equivalent to EASA form 1 is acceptable in all of the 27 European countries 27 1 Separate 8130 3 export form for each of the 27 countries is not necessary Member states 27 countries Austria Belgium Bulgaria Cyprus Czech Republic Denmark Estonia Finland France Germany Greece Hungary Ireland Italy Latvia Lithuania Luxembourg Malta Netherlands Poland Portugal Romania Slovakia Slovenia Spain Sweden UK note Canary Islands Spain Azores and Madeira Portugal French Guiana Guadeloupe Martinique and Reunion France are sometimes listed separately even though they are legally a part of Spain Portugal and France Thank you for your prompt response Keith Van Engineering Manager Ameri King Corp 17881 Sampson Lane Huntington Beach CA 92648 USA Phone 714 842 8555 Fax 714 842 4235 ameriking9 aol com www ameri king com 210 From Runge Friedhelm lt friedhelm runge easa europa eu gt To Keith Van lt ameriking9 aol com gt Date Wed Oct 7 2009 4 44 am RE Request for Guideline Acceptability of FAA Form 8130 3 Export Form in EU Dear Ke
182. osition e Verify the following setting See Figure 13 From the Hyper Terminal window or equivalent RS 232 window Click File gt Properties gt Settings tab Click OK to go back to Hyper Terminal window AK 451 Properties Connect Ta Settings Function arrow and ctrl keys as Terminal keys Backspace key sends Del C2 Ctl H Space Ctrl H E mulation Auto detect v Telnet terminal ID ANSI Backscroll buffer lines Play sound when connecting ar disconnecting Input Translation ASLII Setup Figure 13 Verify parameter setting Waiting for 50s verify the 36 Hex digits ignore first 6 digits The last 30 Hex digits will be used for Cospas Sarsat Decode program in order to see the Latitude Longitude Position IMPORTANT NOTE IN NORMAL OPERATION THE MAIN SWITCH LOCATED ON THE ELT MAIN UNIT MUST BE SELECTED AT ARM POSITION AT ALL TIMES 60 2 4 7 Antenna Check A low quality AM Broadcast Radio Receiver or Equivalent Test Equipment should be used to determine if energy is being transmitted from the Antenna When the Antenna of this Radio tuning dial on any setting 15 held about 6 inches from the activated ELT Antenna the ELT Aural tone will be heard see note below The ELT must be reset by pressing either the RESET push button located on the ELT Main unit or the ELT Remote Unit Note This is not a measured check but it does provide confidence that the Ant
183. ounting and force activation 15 indicated on the ELT AK 451 AF AP ELT can be activated by using a rapid forward throwing motion coupled by a rapid reversing action Verify that the ELT has been activated by use of the Wattmeter the Airplane s VHF Radio Communications Receiver when tuned to 121 5 MHz or other means see Note 1 The ELT must then be reset by pressing either the RESET push button located on the ELT main unit or the ELT Remote Unit 86 Note 1 This 15 not a measured check It only indicates that the G Switch 15 working 3 4 7 2 Antenna Check A low quality AM Broadcast Radio Receiver or Equivalent Test Equipment should be used to determine if energy is being transmitted from the Antenna When the Antenna of this Radio tuning dial on any setting 15 held about 6 inches from the activated ELT Antenna the ELT Aural tone will be heard see notes 2 and 3 The ELT must be reset by pressing either the RESET push button located on the ELT Main unit or the ELT Remote Unit Note 2 This is not a measured check but it does provide confidence that the Antenna 1s radiating with sufficient power to aid search and rescue The Aircraft s Receiver tuned to 121 5 MHz may also be used This Receiver however 15 more sensitive and could pick up a weak signal even if the radiating ELT s Antenna 1s disconnected Thus it does not check the integrity of the ELT System or provide the same level of confidence as does an AM Ra
184. programmed for long message 24 bit protocol which is set up to match the 24 bit address parity of the Mode S surveillance and communications system switch block Note There is no electronic connection between TCAS or Mode S systems and the ELT only the ID number is common This feature was implemented in the ELT with fleet operators in mind ELT s are programmed with either a serialized or 24 bit protocol The ELT transmits position data as part of the 406 025 MHz distress message 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 monitor the 406 025 MHz transmissions The crash site 15 instantly known due to the aircraft s navigation system position data 90 communication with the ELT Without the position data being transmitted it 1s necessary for the polar orbiting satellites to pass overhead using Doppler Shift technology to determine position In a worst case scenario this could be a 3 to 4 hour wait for a polar orbiting satellite to pass over In addition the accuracy of the position fix is much better i e 22 meters with GPS Nav Position data versus 1 to 2 kilometers for the standard 406 028 MHz system without GPS NAV Position data The ELT accept Aviation RS 232 data bus formats By reprogramming the ELT with the aircraft s 24 bit identification or serialized long message format
185. rash hiding vibration and provides a very poor structural mounting surface The mounting location must be able to support 100 pounds of force in any direction with no appreciable distortion in the structure It must also be able to withstand a 350 pound force in any direction without tearing or breaking the aircraft structure Please refer to FAA AC 43 13 for guideline 26 Following are the FAA guidelines for mounting TSO C91a ELT per RTCA DO 183 paragraph 3 1 8 1 ELT shall be mounted to primary aircraft load carrying structures such as trusses bullheads longerons spars or floor beams 2 The mounts shall have a maximum static local deflection no greater than 2 5 mm 0 1 in when a force of 451 Newtons 100165 15 applied to the mount in the most flexible direction Deflection measurements shall be made with reference to another part of the airframe not less than 0 3 meters 3 feet from the mounting location In addition RTCA Document number DO 182 recommends that all ELT system components which must survive a crash intact should be attached to the airframe in such a manner that the attachment system can support a 100g load in the plus and minus directions of the three principal axes of the aircraft The ELT must be mounted with the arrow which is printed on the battery case pointing in the direction of flight The ELT should be mounted with its longitudinal axis aligned within 10 degrees of the longitudinal axi
186. re 11 NOTE 1 BCH 1 Encoded and BCH 1 Calculated MUST have the same value 2 BCH 2 Encoded BCH 2 Calculated MUST have the same value 143 144 APPENDIX I Fungus 1 DO 160D ENVIRONMENTAL QUALIFICATION FORM NOMENCLATURE ELT EMERGENCY LOCATOR TRANSMITTER TYPE MODEL PART NO AK 451 SERIES MANUFACTURER AMERI KING CORPORATION HUNTINGTON BEACH CA 92648 ENVIRONMENTAL CATEGORIES Audio Frequency Susceptibility EINEN F1XBA 204 183 204 183 XR 204 183 XXSZXXX A C 204 183 BC XXXX C 204 Induced Signal Susceptibility SECTION TEST CONDUCTED CONDITIONS 4 5 2 In Flight Loss of Cooling EU EE MEN Wwe 00 Operational Shock and Crash Per DO 204 183 Safety m X weeme we _ Fluids Susceptibility DO 204 183 Radio Frequency Susceptibility Per DO 204 183 Lightning Induced Transient Susceptibility Lightning Direct Effects Sand and Dust 145 146 APPENDIX J Approval FAA TSO C 126 C 91a Equipment Approval dated 07 24 2008 Approval EASA ETSO 2C 126 2C 91a EASA IM 210 1102 dated 11 20 2008 Approval Transport Canada dated 11 26 2008 Approval Industry Canada ID 2474A A451PLAFAPS dated 11 06 2008 Approval Brazil Certificado Anatel dated 03 31 2009 Approval EASA Minor Change Approval P EASA A C 12674 dated 7 24 2009 Approval EASA Minor Change Approval 10027068 dated 9 3 2009 Approval EASA Minor Change Appro
187. rly visible If for some reason you do not receive the registration decal within two weeks please 6 call NOAA toll free at 1 888 212 SAVE 7283 or 301 817 4515 Failure to register re register as required every two years or to notify NOAA of any changes to the status of your 406 MHz beacon could result in penalties and or fines being issued under Federal Law The owner or user of the beacon is required to notify NOAA of any changes to the registration information at any time By submitting this registration the owner operator or legally authorized agent declares under penalty of law that all information in the registration information is true accurate and complete Providing information that is knowingly false or inaccurate may be punishable under Federal Statutes Solicitation of this information is authorized by Title 47 Parts 80 87 and 95 of the U S Code of Federal Regulations CFR Additional registration forms can be found on the NOAA SARSAT website www sarsat noaa gov or www beaconregistration noaa gov 125 Please note NOAA will complement or update your registration information accordingly if your registration has expired and credible information is provided from SAR sources NOAA will also seek information from other databases to update and or complement the existing information for an expired beacon registration Although the information provided will become a matter of public record there is no intent to circulate be
188. ry Canada ID 2474A A451PLAFAPS dated 11 06 2008 Approval Brazil Certificado Anatel dated 03 31 2000 Approval EASA Minor Change Approval P EASA A C 12674 dated 7 22 2009 3 a bus inita eus Approval EASA Minor Change Approval 10027068 dated 9 3 2000 Approval EASA Minor Change Approval 10026863 dated 8 18 2000 Approval EASA Minor Change Approval 10026866 dated 8 18 2000 Approval Austria for Historic Aircraft like PA 18 19 Series B cker T131 JOB I5 65513 d ated 4 16 2010 unio Get peior o ette Email Response from EASA to Ameri King regarding Acceptability of FAA Form 8130 3 Export Form in EU Europe Union dated 10 22009 sect trea Approval Japan Civil Aviation Board Approval coming soon Approval COSPAS SARSAT Type Approval Certificate No 179 daed 0924 DOT aeta esos APPENDIX K Material Safety Data Sheet for 125 11 List of Figures Fiure A Front vie wor BIET onde nis 23 Bice ts GAD view oto etaient hes PES d URL RENI 23 Figure 1 Direction Determination for Fixed Wing 1 28 Figure 1 1 Direction Determination for Helicopter 22 0004 29 Figure 2 Mounting Tray for ELT AF AP P N 451 0
189. s 7 Addition of SZD 31 SZD 35 SZD 39 SZD 40X SZD 41 SZD 50 1M SZD 51 0 SZD 52 0 SZD 52 1 Polish sailplanes on the basis of their being regarded as prototypes or development aircraft 8 Correction to add Breguet to 900 901 series sailplanes France instead of Nord SNCAN Issue 9 dated 11 February 2008 1 Addition of Table non EU balloons and airships to Table 5 2 Addition of Russian balloons Interavia 61TA 70TA 80TA and A S Dirizhalstroy DS AT8 2 Annex II adopted lieu of original Annex II from Regulation 1592 2002 Issue 10 dated 25 February 2008 Removal of Scheibe SF23A to EU product list with SAS Alphabetical order layout introduced for ease of search Addition of Aviamilano P 19 Scicciolo and Macchi 160 m New Annex 11 EASA list Issue 10 25 Feb 2008 Page 3 of 3 163 Table 1 EU states of Design powered aircraft fixed wing Evaluation against Annex II criteria Development Role in armed Design Production State of Design TC of Aviation forces 1 1 55 1 1 75 and Comments Austria Arge Ph nix EN Krobath Oberlerchner 1314 _______ _____________ oro Belgium Yes Mostly amateur p 1 7 ves SSS fen he rier es 74 Aero 45 145 Super Aero Yes Yes 45 series Kero Vodochody MiG 15 Yes L29 Delfin Ves es S 0 40 Meta Sokol DEM Yes Yes First GA post Yes P
190. s A false alarm may be generated Any time the ELT is activated it is transmitting a 121 5 MHz and 243 0 MHz distress signal If the ELT operates for approximately 50 seconds a live 406 MHz distress signal is transmitted and is considered valid by the Cospas Sarsat satellite system Any time that the ELT Main Switch is lifted and flipped from to a 406 MHz self test signal is transmitted after 25 seconds however it is specially coded as a self test signal that is ignored by the COSPAS SARSAT satellites Note Press RESET anytime to turn off unwanted transmission 3 3 0 QUICK OPERATION CHECK Note Refer to Appendix A 1 for Quick Operation Check in sequence order 3 3 0 4 ELT Main Switch ON position ELT swept Tone must be heard on the Radio 2121 5 MHz The 2 LED lights flashing 4 sec OFF 1 sec synchronized with the Buzzer sound 4 sec OFF 1 sec ON 3 3 0 2 ELT Main Switch ARM position Both LED Lights and Buzzer must illuminate and sound for 4 sec then extinguish This 15 to make sure LED and Buzzer are properly powered Note Press RESET anytime to turn off unwanted transmission The ELT will then automatically enter Self test mode Self test takes 25 sec If ELT Self test is passed No light illuminate no buzzer sound If ELT malfunctions the LED Lights and buzzer will show 1 flash 2 flashes 3 flashes or 4 flashes etc Refer to Operation Manual of trouble shooting err
191. s It is the responsibility of those desiring to install this article on a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards TSO articles must have separate approval for installation in an aircraft The article may be installed only if further evaluation by the applicant documents an acceptable installation and it is approved by the FAA Administrator The article may be installed only if performed under 14 CFR parts 43 or the applicable airworthiness requirement For installations outside of the US contact your local civil aviation authority for guidance Ref TSO C126 paragraph D Lithium battery safety concerns include the possibility of fire venting violently and venting of toxic gases Ref TSO C126 paragraph 5 a 2 17 The AK 451 ELT described in this manual was designed tested and certified as a complete system including the following components ELT Transmitter w integral battery ELT Mounting Tray and Velcro Holder ELT Antenna and Coaxial Cable Assembly ELT Remote Switch and Remote Wiring Cable Assembly ELT Audible Buzzer Monitor unit and T Adapter Connector Note Only Ameri King approved system components may be used for a TSO approved system 1 2 3 Certification The 451 has been certified to the following e FAA TSO C126 FAA 5 91 ETSO 2C126 per European Aviation Safety Agency EASA FAR Part 9 mandatory automatic ELT requireme
192. s disconnected Thus it does not check the integrity of the ELT System or provide the same level of confidence as does an AM Radio Note 3 Because the ELT radiates on the emergency frequency the Federal Communications Commission allows these tests to be conducted only within the first 5 minutes after any hour and limits the tests to 3 sweeps of the Transmitter Audio Modulation 122 APPENDIX D EXCERPT FROM FAA AC 91 44 PARAGRAPH 8 WHICH DEFINES WHEN BATTERY REPLACEMENT MAY BE DONE UNDER FAR 43 3 AS PREVENTIVE MAINENANCE The pilot can do the replacement if the preventive maintenance limitations of Part 43 3 h of the FAR are complied with For example a portable type ELT that 15 readily accessible and can be removed and reinstalled in the Aircraft by a simple operation should be considered Preventive Maintenance Fixed type ELT installations are often permanently mounted in a remote area of the Aircraft near flight control cables vital Aircraft components and critical attachments to the Aircraft structures Installations of this nature require an external Antenna and often a remote ON OFF transmitter control switch that is usually located near the pilot s flight position This type installation is complex and battery replacement should be accomplished by a Certificated Mechanic or Certificated Repair Station 123 APPENDIX E FAA ADVISORY CIRCULAR AC43 13 2B SECTION 303 a The antenna s structural load
193. s of the aircraft fuselage Avoid mounting the ELT near sources of strong EMI RFI radiation See Fig 1 If this is a new installation or if the current installation 15 unacceptable find a location per the following RTCA suggests the aft section of the fuselage Statistically this 1s the least likely section of the aircraft to receive damage in a crash It 15 also near the antenna connection minimizing cable length between the transmitter and antenna Maintain access for maintenance If possible avoid locating the ELT where it will be subjected to chemical fluids such as deicing compounds cleaning fluids etc Over time these may attack the plastic and metal components The mounting location must conform to the requirements of RTCA DO 204 and AC 43 13 2B DO 204 Sec 3 1 8 states ELT shall be mounted to primary aircraft load carrying structures such as trusses bulkheads longerons spars or floor beams not aircraft skin The mounts shall have a maximum static local deflection no greater than 2 5 mm 0 1 in when a force of 450 Newton s 100 16 is applied to the mount in the most flexible direction Deflection measurements shall be made with reference to another part of the airframe not less than 0 3 meters 1 foot nor more than 1 0 m three feet from the mounting location Separate mounting hole patterns are provided so that if the AK 451 15 replacing existing ELT listed below the original mounting holes can be use
194. s submitted via the online facilities of the IBRD Beacon registrations submitted in paper format or via other communication facilities will not be accepted Cospas Sarsat Secretariat mail cospas sarsat int is available to answer questions from National Administrations concerning beacon coding and registration matters Administration User Accounts The IBRD 1s freely available to users with no access to national registration facilities and to Administrations who wish to avail themselves of the facility to make their national beacon registration data more available to SAR services SAR Services and others wishing to query the IBRD will require passwords issued by the Cospas Sarsat Secretariat In order to acquire appropriate passwords to access the IBRD National Administrations should e Designate a National IBRD Point of Contact and e Request that the Cospas Sarsat Secretariat allocate user identifications and passwords to their National IBRD Point of Contact The password and user identification request must be provided in writing to the Database Administrator ie the Cospas Sarsat Secretariat and must carry the signature of the Cospas Sarsat IMO ICAO Representative of the Administration For a letter template please click here Contact Us Related Sites Location 700 de la Gaucheti re West Suite 2450 Montreal Quebec H3B 5M2 Canada Email mail cospas sarsat int Tel 1 514 954 6761 129 Sorted By Country Name Sort
195. sed Verify the ELT audio sweep tone ceased G Switch Check Activate the G switch by using a rapid forward throwing motion coupled by a rapid reversing action Verify that the ELT has been activated by use of the Wattmeter the Airplane s VHF Radio Communications Receiver when tuned to 121 5 MHz or other means see Note 1 The ELT must then be reset by pressing either the RESET push button located on the ELT main unit or the ELT Remote Unit Note 1 This 15 not a measured check It only indicates that the G Switch is working Note In normal configuration the main switch on the ELT Main Unit must be selected to the ARM position Whenever both the Green ON lights located on the Main Unit and the Remote Switch Unit flash and the Buzzer sound periodically they indicate the ELT is transmitting If the ELT be accidentally activated by turbulence hard landing etc or if this occur under any conditions other than an accident requiring immediate assistance pressing the RESET button on the Remote Switch Unit If the Aircraft is on the ground and the RESET button on the Remote Unit does not cause the Green ON light to extinguish the RESET button on the Main Unit should be pressed If airborne and the RESET button on the Remote unit does not cause the Green ON LIGHT to extinguish the main switch on the ELT should be set to the OFF position if the ELT 1s accessible If the ELT is not accessible in flight you should land at th
196. ssue 10 25 Feb 2008 Page 12 of 19 Table 1 EU states of Design powered aircraft fixed wing Design Production State of Design TC qo es Ez t and Comments Model 91 Safir Yes Yes Yes variants 772557 ___ 5 ______ ____ ______________ _ _ ___ _ _ _ _________ _______ Switzerland A Comte ACA Yes First Swissair Yes Yes Yes aircraft Consortium F W Doflug SWS D 3801 MS406 WWII Yes Yes Yes License from Morane Saulnier Datwyler Swiss Trainer R amp D special F33 05 Doflug Altenrhein B cker 131 WWII Significant for Yes Yes Yes LBA 717 illii the basis of all B cker 131 APM NEN F13 09 Annex II on B cker 133 WWII Significant for Yes Yes Yes Jungmeister Switzerland FFA Altenrhein AS202 32TP lt D lt D o R amp D special prototype only New Annex EASA list Issue 10 25 Feb 2008 Page 13 of 19 175 176 Table 1 EU states of Design powered aircraft fixed wing Historic Design Production State of Design TC event 1 1 55 lt 1 1 75 Comments F W Emmen license from DH DH 100 Mk 6 Yes Yes Yes Vampire EMEN 7 ____ mex o pP polo 2 Yes ves Dewoitine ol ol o 6 20 es 5 22 es 86 32 es CO 56 35 570 French SoD Swiss built Annex II for France WII DH 115 Mk 55 Vampire Trainer DH 112 Mk1 and Mk 4 Venom d 3605 K W Th
197. ssued by EASA acting in accordance with Regulation EC No 216 2008 on behalf of the European Community its Member States and of the European third countries that participate in the activities of EASA under Article 66 of that Regulation and in accordance with Commission Regulation EC No 1702 2003 to Niessler Handelsagentur Ferd Hanuschgasse 8 2345 BRUNN AM GEBIRGE AUSTRIA and certifies that the change in the type design for the product listed below with the limitations and conditions specified meets the applicable Type Certification Basis and environmental protection requirements when operated within the conditions and limitations specified below TC Holder SEE APPLICATION FOR LIST Model REFER TO LIST OF SMALL Model AIRPLANES IM THE 002 Model INSTALLATION INSTRUCTIONS Model AND ATTACHED TO APPLICATION EASA Certification Basis C5 23 Description of Design Change Installation of an Ameri King Corporation AK 451 ELT as replacement for a Pointer 3000 Associated Technical Documentation EON 002 Engineering Order dated 24 07 09 EONDO2 Installation Instructions dated 24 07 09 002 Maintenance Manual Supplement dated 24 07 08 Limitations None Conditions 1 Prior to installation of this modification the installer must determine that the interrelationship between this modification and any other previously installed modification will introduce no adverse effect upon the airworthiness of the product
198. t Satellite System Certificate Number 179 Manufacturer Ameri King Corporation USA Beacon Type ELT AF AP S and PLB Beacon Model s AK 451 AF AK 451 AP AK 451 S AK 451 PLB Test Laboratory Intespace Toulouse France Dates of Test June October 2006 June July 2007 Details of the beacon features and battery type are provided overleaf The Cospas Sarsat Council hereby certifies that the 406 MHz Distress Beacon Model identified above is compatible with the Cospas Sarsat System as defined in documents C S T 001 Specification for Cospas Sarsat 406 MHz Distress Beacon Issue 3 Rev 7 November 2005 C S T 007 Cospas Sarsat 406 MHz Distress Beacon Type Approval Standard Issue 4 Rev 1 October 2006 Date Originally Issued 24 September 2007 ee s D Levesque Head of Cospas Sarsat Secretariat NOTE HOWEVER 1 This certificate does not authorize the operation or sale of any 406 MHz distress beacon Such authorization may require type acceptance by national administrations in countries where the beacon will be distributed and may also be subject to national licensing requirements 2 This certificate is intended only as formal notification to the above identified manufacturer that the Cospas Sarsat Council has determined on the basis of test data of a beacon submitted by the manufacturer that 406 MHz distress beacons of the type identified herein meet the standards for use with the Cospas Sarsat S
199. t be within 20 degrees of vertical when the aircraft 15 in a normal flight altitude If the Antenna is mounted to a non metallic airframe a supplementary ground plane must be installed The installed Antenna must be able to withstand a static load of 100 times its weight applied to the base of the Antenna along the longitudinal axis of the aircraft The Antenna should be placed a minimum distance of 3 feet 1 meter from any vertically polarized communication Antennas 1 e Antennas radiating in the 118 137 MHz band The AK 451 15 certified to be used with any of the following antennas Whip antenna Model 451017 1B Rod antenna Model 451017 2A Blade antenna Model 451017 3A Whip antenna Model 451017 45 The ELT antenna must be mounted in accordance with the requirements of RTCA DO 204 Section 3 1 10 and RTCA DO 183 Section 3 1 10 Locate the antenna at least 30 inches away from other antennas wires vertical stabilizers etc to minimize distortion of the radiated field and interference with other equipments The antenna must be installed VERTICALLY within 15 of the vertical plane is acceptable Ameri King has no performance data for installations that deviate from the stated requirements 33 Each of the above listed antennas requires a ground plane On aircraft constructed with non conductive materials such as composite or fiberglass a ground plane must be added Ideally the ground plane should extend out from the antenna mount
200. ta Hi Tx Data Hi Tx Data Tx Data 17 78 FT 14 27 zr NIC Ground Ground AAC Ground NIC Ground AIC Ground ON LO audible Buzzer E 451018 ELT Model AK 451 Remote Una 451 004 5 232 Rxd Hi Gresnd Remote DC RESET Slo Remo Remote ON Lm Lo Remote DN 5W La Reri DN Light L 5 222 Tad Hi 3 inch T Adagter 451 0181 35 R 12 8 T Adapter 4510181 T Adapter 451 0181 Optional GPS connector OPTIONAL MULTI AXES G EWITCH 450 000 1 Remote Wiring Cable Assembly 450 0041 NOTE P N 450 0041M Optional Mil Spec M22759 18 35 AWG at specified length is available Figure 14 2d Wiring Diagram for AK 451 with GPS Position and 3 inch T adapter with Optional Multi axes G Switch with 2 wire interconnecting ELT Main Unit and Remote Switch Unit 113 APPENDIX QUICK OPERATION CHECK LEDs 1 ELT switch at ON position On continuously sec cr 99 sec cr 99 on 3 ELT switch at ARM position None for another 25 sec Self Test Mode NOTE If the LEDs flash there is a problem Self Test takes 25 sec Please refer to Installation and Operation manual paragraph 2 4 for details ELT hard Forward and Backward On continuously G Switch Test 5 Press RESET button 6 Press ON button On continuously on Remote Unit 7 Press RESET button Now the ELT switch
201. tery Replacement for ELT Remote 7 Figure 18 ELT Front Panels Main Unit and Remote Unit 78 Figure 19 ELT AP S complete assembly with 83 Figure 20 parameter e a 93 13 SECTION I GENERAL INFORMATION 11 SCOPE This manual contains information necessary for the installation test and operation of the model AK 451 Emergency Locator Transmitter manufactured by Ameri King Corporation California U S A 12 OVERVIEW 1 2 1 Description The Ameri King AK 451 Series is FAA TSO d approved EASA ETSO d approved 406 MHz ELT Emergency Locator Transmitter Types AF Automatic Fixed AP Automatic Portable S Survival It transmits aircraft GPS NAV position data immediately and accurately on triple 406 Satellite 243 Military 121 5 Civilian MHz frequencies The supreme advantage feature is the aircraft GPS NAV Latitude Longitude exact position shall be transmitted within 1 minute on the very first burst without waiting for a Polar Orbiting Satellite could be up to 4 hours Enhance the accuracy significantly for the ground search area from 1 2 kilometers non GPS NAV Position to 22 meters typical with GPS NAV Position Having a triple frequency insures your distress message reaches both NOAA Satellite Operation and US Air Force AFSR Ground Operation Search and Rescue Team with 100 fully confi
202. tion Note It 1s extremely important that the ELT GPS 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 may be followed after installing the ELT 3 4 10 4 24 Bit Address Installation Test mandatory for Installations reprogramming by Ameri King s authorized dealer Verify the 24 Bit Address by using the ELT Computer Test Set TS 451 or equivalent The 15 digit hex code shall be extracted by using the Computer Test Set or equivalent Realize that the AK 451 transmits 406 MHz test message which 15 encoded such that it will be ignored by the SAR satellite system This 15 digit number is used to register the ELT with the appropriate 406 MHz ELT registration authority In the US the National Oceanic and Atmospheric Administration NOAA maintains the database of registered ELT s Note Although a typical 15 digit hex code can contain position data the 15 digit ID used for registration purposes shall contain the default value of no position data instead this is indicated by the last 5 digits of the 15 digit hex code being FFBFF 92 3 4 10 5 GPS Position Test if equipped for using TS 451 Computer Test Set or equivalent Note Per FCC Regulation this test should be conducted inside a RF shielded room or an ELT RF shielded box
203. ttempt to distort aircraft structure to reduce gaps between the antenna base plate and aircraft mounting surface e Consider the factors of flutter vibration characteristics and drag load The approximate drag load an antenna develops may be determined by the formula D 0 000327 The formula includes 90 reduction factor for the streamline shape of the antenna D 15 the drag load on the antenna in 165 A 1s the frontal area of the antenna in sq ft V is the Vye of the aircraft in mph Example Antenna manufacturer specification frontal area 0 135 sq ft and of aircraft is 250 mph D 0 000327 x 135 250 0 000327 x 135 x 62 500 2 75 lbs f The above formula may be adapted to determine side load forces by substitution of the apparent frontal area value for A when the aircraft motion and antenna orientation are not the same 124 APPENDIX F REGISTERING A 406 MHz BEACON IN THE U S A Important Notice Please Read Before Completing Registration Registration 1s an important facet for all Cospas Sarsat 406 MHz emergency beacons Not only is it required by Federal Regulations but the information you furnish is used by Search And Rescue SAR agencies in the event of beacon activation The registration information is an important tool to assist the United States Coast Guard United States Air Force and other SAR agencies in locating and quickly responding to you your vessel or your aircraft Failure to register your
204. u m Schleicher Rhonbussard 52 777817 B niece OO 2 LLLI Ka es ___ _ __ ____ _ ____ _____ ___ 668 Experimental HO K cx C _____ ____ _____ res is __________ 7 ess __ ______ _________ _______ ______ 684 Experimental Siebert Sie 3B nS olo Rn wolf Hirth Goovier Ti e _ 21 experimental New Annex 11 list Issue 10 25 Feb 2008 Page 4 of 7 195 196 Table 3 Sailplanes and Powered Sailplanes EU and non EU Evaluation against Annex II criteria of Aviation force lt lt ang Comments Italy Caproni Antares A21SJCalif Yes Jet 278 powered ane Sailplanes All sailplanes designed Established before 1955 modern manufactured before sailplane 2 03 Ifjusag ___ _______ R 22 series Futar Super es es Hungary ea lt Netherlands okker w ty T D m e Pa D lt D __ a ae D lt D lt lt D NV Vliegtuigbouw Deventer es ________ es es LLL B wy c e PESTS z tu c lt lt D ea D gt N n 2 5 tu D v e lt x up to PZL Bielsko
205. ulations require that Transmitter tests only be done during the first 5 minutes of each hour and must not last for more than 3 Audio sweeps 1 5 seconds If you are at a location where there is an FAA Control Tower or other monitoring facility notify the facility before beginning the tests Never activate the ELT while airborne for any reason See Figure 18 for the ELT Front Panels for both ELT Main Unit and Remote Unit 71 O ELT REMOTE UNIT i E l s E I E 7 L Je T ELT le 7 mA 6 ON ON RESET Qj HORIZONTAL VERTIGAL GREE H LED LLUBINATE WHEN ELT 15 TRANSMITTING 9 RESET CN agp OFF MAIN e T SWITCH REMOTE AMERIE KIMG PART 450001 MADE LSA ELT MAIN UNIT Figure 18 ELT Front Panels Main Unit and Remote Unit 78 3 3 3 1 Monitor 121 5 MHz using the Aircraft Com Receiver or Portable Hand Held Receiver Turn the Squelch all the way up or ON 3 3 3 2 Ensure that the main switch on the ELT is on ARM position e Push the ON button on the Cockpit Remote Switch Unit Verify that both the Green ON lights located on the Main Unit and the Cockpit Remote Switch Unit are flashing Verify the Buzzer sound periodically Verify the ELT audio sweep tone can be heard on the Com Receiver e Push the RESET button on the Remote Switch unit Verify that the two Green ON lights are extinguished Verify the Buzzer sound cea
206. un itine D 26 lt b T N zn lt D Q UJ o m 79 79 C N lt ovo ouv ou Z Q 2 N a E y 5 2 de 3 d 9 lt Y Ww 2 3 0J er d lt I lt D D 79 n3 Walter Uetz Flugzeugbau lt New Annex list Issue 10 25 Feb 2008 Page 14 of 19 177 Table 1 EU states of Design powered aircraft fixed wing Design Production State of Design TC 1 1 55 lt 1 1 75 Comments S On basis of similarity with Jodel series ATL ATL 98 Carvair Yes Yes Development of Annex II DC 4 __ ST Lbs del LL ____________ _____ ___ we cs es es _________ ica es ves lt 5 __ _______ T Te Is ST 1 1 British Aircraft BASwalow2 _ ves 2 K e 1 5 Beagle B206 Bassett 25 5 es A109 Airedale ee note Yes Regarded as a development of the Auster series Beagle Beagle Auster A61 series 2 Y Yes Regarded as a direct development of Auster series New Annex Il EASA list Issue 10 25 Feb 2008 Page 15 of 19 178 Table 1 EU states of Design powered aircraft fixed wing State of Desi
207. upplied may be required Refer to FAA Advisory Circular 43 13 2B for guidance Look for Advisory Circulars under the Regulatory Advisory heading on the FAA home page www faa gov It 15 the responsibility of the installation agency to determine the appropriate and adequate antenna installation The 451017 3A Blade Antenna 15 designed to provide ELT transmissions from a single BNC Female Coaxial connector Location The 451017 3A must be mounted on the top of the aircraft to assure maximum visibility of satellites 406 MHz The best location is the upper aft portion of the fuselage The specific mounting location is very important flat surface 15 the best antenna mounting location Do not mount the antenna on the curvatures and uneven surface It should be mounted vertically and away from projections such as a propeller tail surfaces engine exhaust or the shadow of larger antennas Do not over torque the mounting screws in an attempt to reduce gaps between the antenna base plate and aircraft mounting surface If gaps over 0 020 appear between the base plate and mounting surface use of a mounting saddle is recommended Refer to Fig 8 for a drawing of the antenna Installation Preparation Prepare the surface for blade antenna installations in such a manner to ensure a ground contact of less than 0 0030 The electrical bonding between the antenna and the aircraft ground is very important If this bonding is not done properly the perform
208. ust be subjected to tests contained in the UN Manual of Tests and Criteria Additional Information International Maritime Dangerous Goods Code European Road Regulations ADR U S Hazardous Materials Regulations For more information please refer to the Transportation Regulations Page on Ultralife s Web Site http www ultralifebatteries com subcategory php ID 12 1 Product is shipped as Ground DOT Air WMate IMDO 2 No around transportation Lithium Battery Pack Only 3090 Lithium Battery Pack Only 3090 shipping requirement for Emergency Locator Transmitter 3072 Emergency Locator Transmitter 3072 placards Lithium Batteries Life Saving Appliances Not Self Inflating Lithium Batteries Life Saving Appliances Not Self Inflating 2 Special shipping information This battery has been tested to Section 38 3 of UN Manual of Tests and Criteria These batteries should be placarded and labeled as defined in DOT IATA and IMDG regulations based on mode of transportation These batteries cannot be shipped on passenger aircraft ULTRALIFE BATTERIES MSDS023 FA1284 Rev F OCT 01 2007 Page 5 of 6 Rev K Date OCT 31 2007 223 Section 15 Regulatory Information USA This MSDS meets exceeds OSHA requirements Canada This product has been classified in accordance with the hazard criteria of the Controlled Products Regulations and the MSDS contains all of the information required by those regul
209. ut Remote RESET SW Lo Remote ON SIW Lo 6 in Wiring Adapter with RJ12 8PBC Plug and Molex Amp Connector 4 pin Remote ON Light Lo Wiring between P1 and P2 must be as short as possible 12 max R5 232 Txd Hi to ensure damage upon crash Far crash safety p oF Figure 14 19 Wiring Diagram for retrofitting AK 451 with optional Multi axes G Switch 3 with 4 wire interconnecting ELT Main Unit and Remote Switch Unit Artex Pointer Kannad ACK Tech 110 BLACK onto Audible Buzzer 451 018 83 8 Vide T Adapter R 12 6PaC 451 0181 5 1 RJ12 6P6C 4 DC Ground 2 3 wc s 1 2 71 Remote Unit Remote ON 5 W Lo 1 451 004 R3 232 Rxd Hi OPTIONAL MULTI LIEU 3 2 DE Ground AXES G SWITCH 1 ___ 3 Remote RESET SW Lo 9090055 US 2 4 Remote ON SW Le 3 Lip 5 Remote ON Light Lo m J 4 m B Out A ELT RJ12 BPBC Madel 451 T Adapter 451 0181 5 232 Rxd Hi 1 IN Existing Aircraft 2 wire ELT Systems Joliet Narco D amp M etc pinout Pinout Remote RESET SVW Lo 3 aoe cena fo TP in rng Adopor with and MolaAmp Connector 290 4 Wiring between P1 P2 must be as short as possible 12 max RS 232 Txd Hi 5 to ensure no damage upon crash crash safety P1 3 i i h A Figure 14 1h Wiring Diagram for retrofittin
210. val 10026863 dated 8 18 2009 Approval EASA Minor Change Approval 10026866 dated 8 18 2009 Approval Austria for Historic Aircraft like PA 18 19 Series B cker T131 JOB 15 CSS13 dated 4 16 2010 Email Response from EASA to Ameri King regarding Acceptability of FAA Form 8130 3 Export Form in EU Europe Union dated 10 2 2009 Approval Japan Civil Aviation Board Approval dated 4 7 2010 Approval COSPAS SARSAT Type Approval Certificate No 179 dated 09 24 2007 147 Transport Airplane Directorat U S Department Transport Airplane Directorate Los Angeles Aircraft of Transportation pra Certification Office Federal Aviation Administration 19601 Paramount Boulevard Lakewood Califorma 96 071 2 313 7 JUL 2 4 2008 Ameri King Corporation Attn Keith Van 17881 Sampson Lane Huntington Beach CA 92648 Dear Mr Van Ameri King Corporation Technical Standard Order C91a and C126 This is reply to your letter dated June 28 2008 requesting Technical Standard Order TSO authorization for your Emergency Locator Transmitter ELT The statement of conformance to TSOs C91A C126 and the submitted data are accepted Effective the date of this letter you are authorized to identify the following ELT with the marking requirments defined in Title 14 Code of Federal Regulations 14 CFR part 21 607 d and in TSOs C91a and C126 PART NUMBER DESCRIPTION AK 451 AF 406 MHz ELT Emergency Locator Transmitter 406 121 5 243 0 MHz w
211. w 1 flash Internal Data stored in Memory at fault 2 flashes Distress ID stored in Memory at fault 3 flashes Battery voltage 1s low Useful Life Battery Voltage setting 4 flashes Vcc supplies for F2 or F1 at fault 5 flashes RF power level 33 dBm 406 028 MHz 7 flashes 1 2 RF power level lt 17 dBm 121 5 243 MHz 9 flashes PLL locked in or F1 or F2 at fault Continuous flash no F3 F2 F1 RF output power ELT shuts down completely Note The self test mode that transmits a 406 MHz test code pulse monitors certain system functions before returning to the SELF TEST mode The 406 test pulse is ignored by any satellite that receives the signal but the ELT S uses this output to check output power and correct frequency Self test is 520 ms long message burst on the 406 MHz signal Synchronization pattern is 011 010 000 Self test is then 121 243 MHz VHF Continuous Wave during 15 During Self Test the ELT swept Tone is silent on the 121 5 MHz Radio The ELT S may accept GPS position input by connecting the external GPS to the Remote connector 82 PLB Transmits LED Flashing Sec On 4 Sec ON ANT PROGRAMMING SELF TEST for 25 sec AMERI KING CORP PART NO 450001 TSO 9 1a MADE IN U S A ELT S Top Label 16 25 in 3 in Figure 19 Automatic Portable ELT AP with integral antenna Survival ELT 5 83 FORWAR
212. w 406registration com to register online see Appendix G 4 1 6 Change of ownership or contact information It is the owner s responsibility to advise the National Authority of any change in the information on the registration form If the current owner of the ELT is transferring the to a new owner the current owner is required to inform the National Authority by Letter Fax or telephone of the name and address of the new owner The new owner of the ELT 15 required to provide the National Authority with all of the information requested on the Registration form This obligation transfers to all subsequent owners Registration forms are available from call 1 888 212 7283 101 4 1 7 Lost ELT s Inform NOAA immediately at 1 888 212 SAVE 7283 or your national authority that your ELT has been lost They will update your ELT registration information with the appropriate information 4 1 8 Stolen ELT s Things That You Need To Do e Report to your local police department that the ELT has been stolen Contact NOAA at 1 888 212 SAVE 7283 or your national authority with the following information so your registration information can be updated with the appropriate remarks Police Department Name Police Phone Number Police Case Number If your ELT was to activate the information you provide will be forwarded to the appropriate Search and Rescue Authorities who will ensure that your ELT gets back to you And if s
213. wept Tone must be heard on the VHF Radio 2121 5 MHz The 2 LEDs flashing 4 sec OFF 1 second ON synchronized with the Buzzer sound 4 sec OFF 1 sec ON 2 4 0 2 ELT Main Switch ARM position Both LED Lights and Buzzer must illuminate and sound for 4 sec then extinguish This 15 to make sure LED and Buzzer are properly powered Note Press RESET anytime to turn off unwanted transmission The ELT will then automatically enter Self test mode Self test takes 25 sec If ELT Self test is passed No light illuminate no buzzer sound If ELT malfunctions the LED Lights and buzzer will show 1 flash or 2 flashes or 3 flashes or 4 flashes etc Refer to Operation Manual paragraph 2 4 4 for details Next in order to check G Switch Throw the ELT forward and backward 2 3 times the ELT must activate ELT swept Tone must be heard on VHF Radio 2121 5 MHz The 2 LED lights flashing 4 sec OFF 1 sec ON synchronized with the Buzzer sound 4 sec OFF 1 sec ON Next Press either RESET Button no ELT swept tone heard on the 121 5 MHz VHF radio Both LED Lights and Buzzer must be extinguished Next Press the ON Switch on the Remote Switch Unit ELT swept Tone must be heard on VHF Radio 2121 5 MHz The 2 LED lights flashing 4 sec OFF 1 sec ON synchronized with the Buzzer sound 4 sec OFF 1 sec ON 2 4 0 3 For normal operation leave the ELT Main Switch ARM position at all times No ELT swept tone heard
214. ws the beacon to be handled or shipped without nuisance activation Care should be taken when transporting or shipping the ELT not to move the switch or to allow packing material to become lodged such as to toggle the switch Main switch alternate positions e ON ELT transmits immediately Both Green ON lights on the main unit and remote switch unit flash and the buzzer sound at rate of 1 second ON 4 seconds OFF The ELT swept Tone must be heard on the 121 5 MHz VHF Radio OFF The ELT is turned off ARM ELT self test is confirmed after 24 seconds If the self test is passed the 2 Green ON lights and the buzzer sound must be extinguished The ELT swept Tone must be silent on the 121 5 MHz VHF Radio e The ELT system is then in the ARM mode 3 3 2 Transmitter ID Programming and Self Test Turn the main switch from the OFF position to the ARM position The Buzzer sound and the 2 Green ON lights shall illuminate for 4 seconds then extinguish This is to allow coding programming during the next 20 seconds window and self test for 1 second thereafter 76 Note The ELT may be ID coding programming during the aforementioned 20 seconds window period If no programming happened the ELT will then enter the Self Test Mode for 1 second thereafter Self Test takes 25 sec Self test results after 25 seconds are If the self test is Passed the Green ON light 1s steadily extinguished and there s no buzzer soun
215. yond its intended purpose 1 e to assist SAR agencies in carrying out their mission Public reporting burden for the collection of this information is estimated to average 15 minutes per response including the time for reviewing instructions searching existing data sources and completing and reviewing the collection of information Comments regarding this burden or any other aspect of this collection of information including suggestions for reducing this burden should be sent to NOAA SARSAT NSOF E SP3 423 Suitland Road Suitland MD 20746 Or call 1 888 212 SAVE 7283 or 301 817 4515 Finally false alerts remain a chief concern for SAR agencies We ask that you carefully refer to the beacon s user manual for instructions on properly operating installing testing performing required maintenance and or stowage of your beacon We find that these are important factors in reducing the number of false alerts Please use the utmost care at all times 126 Mall Fax t AQUA SAR SAT NSOF ESPJ 4231 Suitland Road Suitland MD 20748 rax 301 817 4565 Official 406 MHz ELT Registration Form Beacon ID LE Identifier LI ELT Manufacturer Model No ELT Information ELT Registration New ELT Registration L Renewal of ELT Registration Replacement of ELT Decal Check here if this ELT is a replacement for a previously registered ELT Change of ELT Information or Ownership Please enter the old ELT u
216. ystem 3 Although the manufacturer has formally stated that all beacons identified with the above model saane s will meet the Cospas Sarsat specification referenced above this certificate 15 not a warranty and Cospas Sarsat hereby expressly disclaims any and all liability arising out of or in connection with the issuance use or misuse of the certificate 4 This certificate 15 subject to revocation by the Cospas Sarsat Council should the beacon type for which it is issued cease to meet the Cospas Sarsat specification new certificate may be issued after satisfactory corrective action has been taken and correct performance demonstrated in accordance with the Cospas Sarsat Type Approval Standard 5 Cospas Sarsat type approval testing requirements only address the electrical performance of the beacon at 406 MHz Conformance of the beacon to operational and environmental requirements is the responsibility of national administrations an Certificate Number 179 Dated 24 September 2007 Operating temperature range 20 C to 55 C Operating lifetime 24 hours Transmit frequency 406 028 MHz Battery details battery pack of 4 four D type cells Lithium Sulphur Dioxide SAFT LO26SXC or Lithium Manganese Dioxide SAFT LM33600 or Lithium Manganese Dioxide Ultralife U10014 Beacon model features 121 5 243 MHz auxiliary radio locating device 100 mW homer duy cycle 40 96 Interface to external navigation devic

- Ameri-King Corporation

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