INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG
Contents
1. Signature and stamp Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date __ Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 604 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 4 Periodic Inspection Log Type of inspection _ Periodic _ Battery change _ Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp Type of inspection _ Periodic _ Battery change _ Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 605 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 5 Periodic Inspection Log Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out2. INTRODUCTION The instructions in this manual provide the information necessary for the installation and the operation of KANNAD 406 AF AF H and AF 6D ELTs Servicing instructions Refer to SERVICING page 601 are normally performed by shop personnel For servicing and maintenance instructions refer to CMM 25 63 01 For regulatory requirements please consult your national aviation authority PAGE INTRO 1 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D PAGE INTENTIONALLY LEFT BLANK PAGE INTRO 2 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D SYSTEM OVERVIEW 1 COSPAS SARSAT System A Description Launched in the early eighties by the four founder countries Canada France Russia USA the COSPAS SARSAT system provides satellite aid to search and rescue SAR operations for maritime aeronautical and terrestrial vehicles anywhere in the world It uses distress beacons fitted on mobiles and a constellation of LEO and GEO satellites which relay the 121 5 243 MHz signals and process the 406 MHz signal to ground stations LUT where the beacon positions are determined with a precision of 10 NM with 121 5 243 signals and less than 2 NM with 406 signals Several types of beacons are designed to match the various applications of the COSPAS SARSAT system EPIRB Emergency Position Indicating Radio Beacon
3. INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D TABLE OF CONTENTS INSTALLATION REMOVAL RTCA FAR recommendations Registration and Programming Pin programming option Installation KANNAD 406 AF installation Fixed wings Helicopters KANNAD 406 AF H installation KANNAD 406 AF 6D installation First power up Removal Self test Periodicity Self test procedure ELT operational tests 302 Installation without programming dongle Installation with programming dongle RCP operational tests 406 and 121 5 MHz transmission test ELT Antenna link TROUBLESHOOTING General Faults on Self test Indicator lamp 3 1 flashes 3 2 flashes 3 3 flashes 3 4 flashes Other faults detected Buzzer does not operate Buzzer operates permanently when ELT in ARM mode SCHEMATICS amp DIAGRAMS Outline Dimensions Drilling Mask SERVICING TOC PAGE 2 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D TABLE OF CONTENTS Maintenance Schedule Periodic inspection Every 6 years Battery replacement Periodic Inspection Log Programming Log Pre delivery Inspection Log TOC PAGE 3 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D TABLE OF CONTENTS PAGE INTENTIONALLY LEFT BLANK TOC PAGE 4 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D
4. KANNAD 406 AF AF H AF 6D RECORD OF REVISIONS PAGE INTENTIONALLY LEFT BLANK ROR PAGE 2 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE Title Page FEB 01 2008 Record of Revisions FEB 01 2008 FEB 01 2008 List of Effective Pages FEB 01 2008 FEB 01 2008 Table of Contents FEB 01 2008 FEB 01 2008 FEB 01 2008 FEB 01 2008 Introduction FEB 01 2008 FEB 01 2008 System Overview FEB 01 2008 FEB 01 2008 FEB 01 2008 FEB 01 2008 FEB 01 2008 FEB 01 2008 System Functional Description and Operation FEB 01 2008 FEB 01 2008 LEP PAGE 1 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE 103 FEB 01 2008 104 FEB 01 2008 105 FEB 01 2008 106 FEB 01 2008 107 FEB 01 2008 108 FEB 01 2008 109 FEB 01 2008 110 FEB 01 2008 Installation Removal 201 FEB 01 2008 202 FEB 01 2008 203 FEB 01 2008 204 FEB 01 2008 205 FEB 01 2008 206 FEB 01 2008 207 FEB 01 2008 208 FEB 01 2008 209 FEB 01 2008 210 FEB 01 2008 301 FEB 01 2008 302 FEB 01 2008 303 FEB 01 2008 304 FEB 01 2008 Troubleshooting 401 FEB 01 2008 LEP PAGE 2 FEB 01 2008 AD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KAN KANNAD 406 AF AF H AF 6D LIST OF EFFECTIVE PAGES
5. for maritime applications ELT Emergency Locator Transmitter for aeronautical applications e PLB Personal Locator Beacon for land expeditions DNS N R C C RESCUE Figure 1 COSPAS SARSAT System PAGE 1 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D B World coverage with the COSPAS SARSAT system The major improvement is the use of the COSPAS SARSAT system for processing aeronautical emergencies The difference with the 121 5 243 MHz is that the 406 MHz transmission carries digital data which enable the identification of the aircraft in distress and facilitate SAR operation type of the aircraft number of passengers type of emergency The 406 MHz message is transmitted to the COSPAS SARSAT satellites This message is downloaded to one of the 64 ground stations 44 LEOLUTs and 20 GEOLUTS The aircraft is located by Doppler effect by the LEO satellites with a precision better than 2 NM 4 km at any point of the earth C Environmental improvements of ELTs The certification of an ELT includes a range of severe mechanical tests resistance to flame impact and crush tests resistance to 100 G and 500 G shocks watertightness antideflagration extreme temperatures 20 C to 55 C for more than 48 hours D G Switch shock detectors The shock detectors currently equipping automatic ELTs are the cause of a large number of false alarms Maj
6. 50 Ohm coaxial cable RG58 for example ended with a BNC connector PAGE 4 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 4 Design features A General The KANNAD 406 AF AF H AF 6D belong to the AF type of ELTs which are permanently attached to an aircraft B Mechanical design The KANNAD 406 AF AF H AF 6D are made of moulded plastic with excellent mechanical resistance ASA PC light yellow colour The housing is designed with no sharp edges It can be easily taken in one hand Figure 3 KANNAD 406 AF AF H AF 6D with mounting bracket PAGE 5 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D PAGE INTENTIONALLY LEFT BLANK PAGE 6 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION 1 Transmitter The KANNAD 406 AF AF H AF 6D can be activated either automatically when the crash occurs thanks to a shock sensor or manually thanks to a switch on the transmitter itself or on a Remote Control Panel The KANNAD 406 AF AF H AF 6D are designed to transmit on three frequencies 121 5 243 and 406 MHz The two basic emergency frequencies 121 5 and 243 MHz are mainly used for homing in the final stages of the rescue operations The 406 MHz frequency is used by the COSPAS SARSAT satellites
7. AF 6D Typical 1110 g 2 47 Ibs 11120 g 2 469 Ibs 1190 g 2 623 Ibs Max 1180 g 2 60 Ibs 1190 g 2 623 Ibs 1260 g 2 778 Ibs B Electrical characteristics Transmitter power supply 3 x LiMnO D type cells C Electrical interface When installed on board the ELT has to be connected e to a Remote Control Panel via a DIN12 connector e to an outside antenna via a BNC connector The DIN12 connector is also used to connect a programming dongle a CS144 interface or a programming and test equipment PAGE 106 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 1 J1 This connector is dedicated for connection to the Remote Control Panel to the Programming or Maintenance Dongles to the CS144 interface and or to the programming equipment PR600 IMPORTANT Shielded cables are recommended The required wires are AWG24 J1 PIN Signal Name _ Destination Direction Jl A JRCP TEST RESET RCP J1 B DONGLE RX SMM PGM Viewed from J1 C DONGLE CS SMM Front Face J1 D DONGLE SK SMM J1 E DONGLE TX SMM PGM I KM DAY J1 F DONGLE ALE2P SMM x il G RCP COMMON RCP J1 H RCP BUZZER RCP J1 J IRCP LED RCP J1 K RCP ON RCP J1 L DONGLE GND SMM PGM J1 M_ N C Table 1 J1 connector pin out This wire is not used with some versions of Remote Control Panels For precise informati
8. equipment are required a Programming Dongle on each aircraft e a Maintenance Dongle on each ELT spare Figure 201 Maintenance Dongle PAGE 203 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 3 Installation Determine the location of the ELT on board according to FAR RTCA recommendations Determine the axis of the ELT according to the type of KANNAD 406 KANNAD 406 AF Refer to A KANNAD 406 AF installation page 206 KANNAD 406 AF H Refer to B KANNAD 406 AF H installation page 207 KANNAD 406 AF 6D Refer to C KANNAD 406 AF 6D installation page 208 Drill 4 holes 6 mm in the aircraft structure according to Drilling mask Holes 4 5 6 7 shall be preferred If the aircraft structure is not solid enough to withstand a 500 kg traction on the bracket a reinforcement plate not supplied should be installed as shown Figure 202 Bracket installation Fix the bracket with the 4 screws 8 washers and 4 nylstop nuts supplied IMPORTANT tighten to a torque between 4 and 5 Newton x meter Screw Tg Flight Direction Arrow Sp Washer small Mounting gar Washer large Reinforcement plate not supplied Nylstop nut Figure 202 Bracket installation PAGE 204 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D Verify that the ELT identification label matches the a
9. for precise pinpointing and identification of the aircraft in distress Once activated the transmitter operates continuously on 121 5 and 243 0 MHz with an output power of 100 mW on each frequency The modulation is an audio frequency sweeping downwards from 1420 Hz to 490 Hz with a repetition rate of 3 Hz The AM modulation factor is between 85 and 100 During the first 24 hours of operation a digital message is transmitted on 406 025 MHz every 50 seconds The output power on 406 MHz is 5 W The KANNAD 406 AF AF H and AF 6D can transmit two types of messages on 406 MHz 112 bits for a short message identification only e 144 bits for a long message identification aircraft position The long messages are generated by a separate interface module called CS144 connected to the ELT and either to a NAV equipment of the aircraft by RS232 RS422 or RS485 link Bi phase modulation at 400 bps enables to transmit all the relevant identification information to the COSPAS SARSAT satellites in 440 ms short message or 520 ms long message PAGE 101 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 2 Controls The following controls are to be found on the ELT front panel from left to right 3 position switch ARM OFF ON Visual indicator red DIN 12 connector for connection to Remote Control Panel CS144 interface module dongle or programming equipment BNC connect
10. frequency Check 406 MHz frequency refer to CMM 25 63 01 for repair see note 1 below 4 344 flashes No identification programmed Check programming see note 2 below NOTE 1 Only PART FAR 145 certified stations accredited by KANNAD can perform these repairs 2 Only accredited programming stations can perform programming 3 Other faults detected A Buzzer 1 Buzzer does not operate Refer to CMM 25 63 01 for repair See note 1 above 2 Buzzer operates permanently when ELT in ARM mode Refer to CMM 25 63 01 for repair See note 1 above PAGE 401 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D PAGE INTENTIONALLY LEFT BLANK PAGE 402 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D SCHEMATICS amp DIAGRAMS 1 Outline Dimensions N N cO N N sss ez Z8 100 3 937 Note all dimensions are in millimeters inches in brackets PAGE 501 FEB 01 2008 KANNAD 406 AF AF H AF 6D G O z O O LU Q O Z l lt 3 lt z O lt o Li a O l lt 3 lt z lt l lt n KAN 2 Drilling Mask 6 6 s n paua4aud 9 c s oH 1U9U30 dap ap suas uondavip 2U61 4 T WWTBT 6 0 WWOe eV ugo 247 WWE 6 0 Ue 6 0 Ue 6 0 WWO2 GENERAL TOLERANCES 0
11. transmission cumulated duration before or on the battery expiration date Only original battery pack included in battery kit KIT BAT 300 P N S1820516 99 supplied by KANNAD can be installed KANNAD refuse all responsibility and invalidate all warranty should other packs be installed PAGE 602 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 2 Periodic Inspection Log Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 603 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 3 Periodic Inspection Log Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station
12. 1 1587 WZ 16L 0 WWOe 1620 UOC ALE WIE PAGE 502 FEB 01 2008 KANNAD 406 AF AF H AF 6D G O z O LU Q O Z l lt 3 lt z O lt o Li a O l lt 3 lt z lt l lt n KANNAD Q 3 3 9 E SNId OL CIYITTOS NV DMA 30133NN02 2 NIQ 30ISNI CITIWLSND CADE LINOSIO CIINIYA TKS x GO JHL 40 WWADVIT ONIAIA DI 343429 dOY 40 NDISAJA SOS HLA CIS LON SI IMIA SIHL 19 OY JHL 40 WWADVIT ONIUIA OL 23430 CITIVISNI d33 ND SNIQN3d3 Sx DANI 39N3334338 SOLIGNNOD ONLLYN ix ATWA 009LNV YO OOSINY AO CODY 0OFLNY AD O0ELNY x if 3dAL do ND DNIGNAdA XX HLIA 2x 3dAL 173 NO ONITN3d30 p2 OL 8 XX HLIM dx l 3 SALN 2 Dl CALIN H1N31 ANSTVAINOS X0 XVII 3dAL 8S98 HLIM gp WOWIXWN DL CILINTI SS 3189 Y ZUIA DAY 24 Y ik SALROSID p NOLLYOLIISSYTO RA S339800S AW NOLLVOLHISSVIJ IIA un 18 TIEVI XVI SILVOTONI TONIC ONIKAVADOXA S410 20 TANYA mao iowa PT g ND 379N00 d237V 379N00 XL 379N00 XS FTONOT SI NOC Xi 3T9N00 ND dou 31 dad IZZNA did NOMACO ded 13S30 dI LTD 331INSNV31 301951 tea PAGE 503 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D PAGE INTENTIONALLY LEFT BLANK PAGE 504 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D SERVICING 1 Maintenance Schedu
13. ECTION LOG KANNAD 406 AF AF H AF 6D 3 LINE REPLACEABLE UNITS A Transmitter The KANNAD 406 AF AF H AF 6D is an ELT designed to be installed on board aircraft to transmit a distress signal on 3 frequencies e 406 MHz COSPAS SARSAT frequency for precise pinpointing and identification of the aircraft in distress e 121 5 and 243 MHz used for homing in the final stages of the rescue operations The KANNAD 406 AF AF H AF 6D are certified as Automatic Fixed AF ELTs and only work with a three frequency outside antenna B Bracket The bracket installed near the tail is designed to fix the ELT with a Velcro strap This enables quick removal of the ELT for maintenance or exchange C Remote Control Panel A remote control panel is available for installation in the cockpit in order to enable the pilot to monitor and control the ELT status The following controls are to be found on the panel e 3 position switch ON ARMED RESET amp TEST red or amber visual indicator beeper on certain versions The remote control panel is connected to the ELT via a 4 or 5 wire cable equipped with a Programming Dongle or a DIN 12 connector on the ELT side and the connector corresponding to the Remote Control Panel version on the other side D Outside antenna The outside antenna also installed near the tail can be either rod or blade type according to aircraft speed Connection to the ELT will be carried out with a
14. ERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 12 Programming Log Identification protocol TN ICAO AOD S N Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date __ __ Service station Signature and stamp PAGE 613 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 13 Programming Log Identification protocol TN ICAO AOD S N Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date _ __ Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp PAGE 614 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 14 Programming Log Identification protocol TN ICAO AOD S N Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date _ __ Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identificati
15. GE 209 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D PAGE INTENTIONALLY LEFT BLANK PAGE 210 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 1 Self test A Periodicity It is recommended by the manufacturer to test the ELT to detect any possible failure It is recommended to perform a self test once a month by pilot or maintenance personnel from the cockpit Remote Control Panel but it should not be done more than once a week However each self test consumes energy from the battery Should self tests be carried out more often than the maximum allowed the battery life time might be shorter than specified Do not perform Self test without the antenna connected B Self test procedure e Check that the antenna is correctly connected e Switch from position OFF to position ARM or press RESET amp TEST on the Remote Control Panel ensure that the ELT switch is in the ARM position The buzzer operates during the whole Self test procedure After a few seconds the test result is displayed with the visual indicator as follows One long flash indicates that the system is operational and that no error conditions were found e A series of short flashes See Remark below indicates the test has failed e Switch back to OFF If self test fails contact the distributor as soon as possible Unless a w
16. ID Aircraft Tail Number Date _ __ Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp PAGE 610 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 10 Programming Log Identification protocol TN ICAO AOD SIN Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date __ __ Service station Signature and stamp PAGE 611 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 11 Programming Log Identification protocol TN ICAO AOD S N Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date _ __ Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp PAGE 612 FEB 01 2008 KANNAD INSTALLATION MANUAL OP
17. Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date __ Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 606 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 6 Periodic Inspection Log Type of inspection _ Periodic _ Battery change _ Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp Type of inspection _ Periodic _ Battery change _ Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 607 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 7 Periodic In
18. SUBJECT PAGE DATE 402 FEB 01 2008 Schematics and Diagrams 501 FEB 01 2008 502 FEB 01 2008 503 FEB 01 2008 504 FEB 01 2008 Servicing 601 JJUL 27 2007 602 JFEB 01 2008 603 FEB 01 2008 604 JFEB 01 2008 605 FEB 01 2008 606 FEB 01 2008 607 FEB 01 2008 608 JFEB 01 2008 609 JFEB 01 2008 610 JFEB 01 2008 611 FEB 01 2008 612 FEB 01 2008 613 JFEB 01 2008 614 FEB 01 2008 615 FEB 01 2008 616 JFEB 01 2008 LEP PAGE 3 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D LIST OF EFFECTIVE PAGES PAGE INTENTIONALLY LEFT BLANK LEP PAGE 4 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D TABLE OF CONTENTS INTRODUCTION SYSTEM OVERVIEW COSPAS SARSAT System Description World coverage with the COSPAS SARSAT system Environmental improvements of ELTs G Switch shock detectors KANNAD 406 ELTs Presentation LINE REPLACEABLE UNITS Transmitter Bracket Remote Control Panel Outside antenna Design features General Mechanical design SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION Transmitter Controls Working mode information Autonomy Technical characteristics Mechanical characteristics Material Overall Dimensions Technical Specifications Activation Standby mode for automatic activation Manual activation Manual reset Reset with Remote Control Panel Self Test TOC PAGE 1 FEB 01 2008
19. The document is loaned on the express condition that neither the document itself nor the information contained therein shall be disclosed without the express consent of KANNAD and that the information shall not be used by the recipient without prior written acceptance by kannad Furthermore the document shall be returned immediately to KANNAD upon request KANNAD This document is the property of KANNAD and contains proprietary and confidential information DMA174M NNAD Ref 0139162M INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D P N S1821502 02 KANNAD 406 AF transmitter P N S1822502 02 KANNAD 406 AF H transmitter P N S1821502 06 KANNAD 406 AF 6D transmitter P N S1820511 01 Mounting bracket 1 strap Revision 11 TP PAGE 1 First issue SEP 02 1999 Date of rev FEB 01 2008 Users are kindly requested to notify KANNAD for any discrepancy omission or error found in this manual Please report to our customer support E mail support sar kannad Tel 33 0 2 97 02 49 00 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D OF REVISIONS RECORD REVISION DATE INSERTION DATE OCT 14 2003 NOV 19 2003 APR 23 2004 JAN 24 2005 JUN 27 2005 FEB 01 2008 OCT 14 2003 NOV 19 2003 APR 23 2004 JAN 24 2005 JUN 27 2005 FEB 01 2008 ROR PAGE 1 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG
20. aver is granted flight should be cancelled Remark The number of flashes gives an indication of the faulty parameter detected during the self test 3 1 LOW BATTERY VOLTAGE 3 2 ILOW RF POWER 3 3 JFAULTV VCO LOCKING FAULTY FREQUENCY 3 4 NO IDENTIFICATION PROGRAMMED PAGE 301 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 2 ELT operational tests A Installation without programming dongle e connect RCP to J1 and outside antenna to J2 switch the ELT from OFF to ARM check that the Self Test result is OK one long flash B Installation with programming dongle connect the outside antenna to J2 switch the ELT from OFF to ARM check that the Self Test fails 3 4 flashes if not connect a maintenance dongle to J1 Switch the ELT from OFF to ARM Check that the Self Test fails 344 flashes Remove the maintenance dongle from J1 connect the programming dongle to J1 switch the ELT from OFF to ARM the buzzer operates during the whole self test procedure after a few seconds the LED displavs the result check that the Self Test result is OK one long flash PAGE 302 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 3 RCP operational tests Check correct operation of RCP LED and external buzzer by switching ELT and RCP as described in the sequential procedure hereun
21. der with ELT switch in the ARM position RCP SWITCH Self test when switching ELT from OFF to ARM START TEST EST RESE then ARMED Wait end of self test 7 sec max gt ELT amp RCP leds flashing ELT amp RCP buzzers modulated activation 3 ARMED ELT continues to transmit ELT amp RCP leds flashing ELT amp RCP buzzers modulated activation EST RESE 4 at least 1 sec then ARMED ELT transmission stops ELT amp RCP leds go out ELT Buzzer stops immediately RCP Buzzer stops after max 5 sec END OF TEST Figure 301 RCP LED and buzzer operation IMPORTANT 2 before switching the RCP to ON wait for the end of the self test PAGE 303 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 4 406 and 121 5 MHz transmission test A ELT Antenna link ELT Antenna link can be checked by testing VSWR KANNAD recommends the use of SWR3000 VSWR meter manufactured by PROCOM Refer to SWR3000 manufacturer s user manual for a VSWR measurement B 406 MHz This test must be carried out with a COSPAS SARSAT decoder Perform self test Press RESET and TEST on the RCP or switch ELT from OFF to ARM e Check with the COSPAS SARSAT decoder that except for the 5th and the 6th digits the decoded message is identical to the programmed message NOTE The message transmitted during self test sequence always begins with FF FE DO whe
22. e longitudinal axis of the aircraft with maximum tolerance of 157 Consequently the KANNAD 406 AF shall be mounted with the arrow of the Direction of Flight label pointed towards the front of the aircraft Helicopters The KANNAD 406 AF can be installed in its standard version on helicopter The ELT unit should be mounted with the front face connectors pointing downwards at a 45 angle to the yaw axis andwith Direction of Flight arrow towards the front of the helicopter NOTE Should the KANNAD 406 AF be installed on board helicopter it will be necessary to make a special mounting base to install the ELT PAGE 206 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D B KANNAD 406 AF H installation i Front f ere fs m U id ront tace Lower side pper siqe HE fa Front face connectors Lower side U Label Direction of Flight Arrow Figure 206 KANNAD 406 AF H installation IMPORTANT The KANNAD 406 AF H is designed to be installed on board helicopters oniv The Direction of Flight arrow shall point towards the front or the bottom of the helicopter and not pointing 45 downwards lf the KANNAD 406 AF H is installed with the Direction of Flight arrow pointing towards the front of the helicopter the ELT shall be mounted with the upper side pointing towards the top of the helicopter e If the KANNAD 406 AF H is installed with the Direct
23. ed position RTCA DO 183 PAGE 201 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 2 Registration and Programming The ELT must be registered prior to installation on board The registration card available from the local registration authority must be completed and returned to this authority The Programming Datasheet DIM0300 must be completed and returned to your distributor Any change of ownership shall also be declared and registered with the local registration authority and with the distributor The KANNAD 406 AF AF H AF 6D are fully compatible with the four programming protocols defined by the COSPAS SARSAT C S G005 document e Serialised Number Aircraft 24 bit Address the same as MODE S ATC or TCAS Aircraft Operator Designator serialised number up to 4096 e Aircraft Nationality and Registration marking Tail Number This identification consists of up to 7 alphanumeric characters Programming of the ELT can be carried out either e by KANNAD or the distributor order must include programming details e inthe shop with a programming and test equipment PC interface and DOS or Windows software on board the aircraft with a programming equipment or programming dongle This operation takes less than 2 minutes and does not need any hardware operation The identification is simply downloaded in the ELT when connected to the KANNAD program
24. eriod or for maintenance The Remote Control Panel is energized by the ELT when the ELT s Switch is in the ARM position D On This mode is selected e manually by switching to position ON e by switching the Remote Control Panel switch to ON provided that the ELT switch is in the ARM position e when a crash occurs provided that the ELT switch is in position ARM When this mode is selected the ELT starts transmission e on 121 5 MHz 8 243 MHz immediately continuous transmission e on 406 MHz after 50 seconds 406 burst every 50 sec during 24 hours The red visual indicator on the ELT and on the remote control panel if installed flashes and the buzzer operates In case of accidental activation the ELT can be reset either by switching it to OFF or by switching to RESET on the Remote Control Panel The number of 406 bursts effectively transmitted is recorded This information is available when the ELT is connected to a programming and test equipment PR600 PAGE 104 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 4 Autonomy The energy is provided by a battery pack composed of 3 LiMnO D cells See pages 108 amp 602 for Kit battery reference Lithium cells lithium batteries and equipment containing such batteries are subjected to regulations and classified under class 9 as from 1st of January 2003 The autonomy of the 121 5 243 trans
25. etermine that the aircraft installation conditions are within the TSO standards The ELT may be installed only if further evaluation by the applicant documents an acceptable installation and it is approved by the Administrator TSO C91a The ELT must be attached to the aircraft in such a manner that the probability of damage to the transmitter in the event of a crash impact is minimized FAR 91 207 The 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 inch when a force of 450 Newton 100 Ibf 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 meter 3 feet from the mounting location RTCA DO183 The ELT should not be installed at less than 60 cm 2 ft of a compass or flux gate Use cable of loss lt 1dB The ELT front panel should be easily accessible to connect the outside antenna and the remote control panel device and to check the ELT good operation controls and lights If no remote control is used ELT controls and displays installed for in flight use shall be readily accessible from the pilot s normal seated position The pilot shall have an unobstructed view of displayed data when in the normal seat
26. ion of Flight arrow pointing towards the bottom of the helicopter the ELT shall be installed with the lower side pointing towards the front of the helicopter PAGE 207 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D C KANNAD 406 AF 6D installation UI Label Direction of Flight Arrow Figure 207 KANNAD 406 AF 6D installation For fixed wings aircraft and helicopters the KANNAD 406 AF 6D shall be mounted in roll or pitch plane either parallel or perpendicular to the aircraft flight direction 4 First power up Perform the following tests ELT operational tests Refer to 2 ELT operational tests page 302 RCP operational tests Refer to 3 RCP operational tests page 303 406 amp 121 5 MHz transmission tests optional Refer to 4 406 and 121 5 MHz transmission test page 304 PAGE 208 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 5 Removal e Switch the ELT to OFF Refer to Figure 204 Installation controls and connectors Disconnect the Remote Control Panel or CS144 from the DIN12 connector Refer to Figure 204 Installation controls and connectors Disconnect the outside antenna from the BNC connector Refer to Figure 204 Installation controls and connectors Unfasten the self stripping strap Remove the transmitter from the bracket Figure 208 Removing the transmitter PA
27. ircraft tail number e Mount the transmitter on the bracket Slide the self stripping strap thought the buckle and fasten it tightly Figure 203 Installing the transmitter on the bracket e Connect the outside antenna to the BNC connector Refer to Figure 204 Installation controls and connectors as shown Figure 2 ELT system description page 3 Note regarding the outside antenna The installation of the outside antenna is not covered by this manual Refer to antenna manufacturer s instructions If the aircraft is not metallic the antenna should be mounted on a metallic counterpart e Connect the Remote Control Panel or CS144 to the DIN12 connector Refer to Figure 204 Installation controls and connectors as shown Figure 2 ELT system description page 3 Set the 3 position switch Refer to Figure 204 Installation controls and connectors to ARM DIN12 Connector ARM OFF ON Switch BNC connector Figure 204 Installation controls and connectors e Perform the first power up procedure Refer to 4 First power up page 208 PAGE 205 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D A KANNAD 406 AF installation YAW Axis YAW Axis Front face 24 connectors AT 45 UI Label Direction of Flight Arrow Figure 205 KANNAD 406 AF installation 1 Fixed wings The G Switch sensor axis shall be pointed to sense the primary crash pulse along th
28. le Periodic inspection and battery replacement can only be carried out by an accredited PART or FAR 145 maintenance station with valid agreement for KANNAD ELT maintenance A Periodic inspection Note if required by the relevant Civil Aviation Authority Some Civil Aviation Authorities may require the ELT is tested periodically In this case KANNAD recommends to check the following parameters Battery voltage 121 5 MHz 243 0 MHz 406 025 MHz transmission power 121 5 MHz 243 0 MHz 406 025 MHz frequency VCO lock 121 5 MHz AM decoding sweep monitoring with VHF receiver Number of 406 MHz transmissions optional programming kit required Number of self tests carried out optional programming kit required Programmed data optional programming kit required NOTE This functioning check can be carried out without opening the ELT B Every 6 years Testing of the various elements of the ELT is mandatory every 6 years together with the battery replacement e Visual control of the housing and accessories Refer to CMM 25 63 01 O ring battery and desiccant capsule replacement Refer to CMM 25 63 01 Beacon Tightness CMM 25 63 01 Testing and Fault Isolation procedure as described in CMM 25 63 01 PAGE 601 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D C Battery replacement Battery replacement is mandatory after more than 1 hour of real
29. ming equipment via the DIN 12 connector A Pin programming option The KANNAD 406 AF AF H AF 6D offer pin programming capabilities to facilitate maintenance operations especially in case of removals and or replacement A special DIN 12 connector with a Serial Memory Module called Programming Dongle is connected to the ELT when installed on board This Programming Dongle contains the identification information of the aircraft and remains on board the aircraft When an unprogrammed ELT is installed and connected to this Programming Dongle and the ELT is switched to ARM it automatically updates its own memory with the identification data contained in the PAGE 202 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D Programming Dongle memory When the ELT is removed from the aircraft it keeps its identification data For maintenance purposes it is possible to delete the identification information of the ELT by connecting a Maintenance Dongle to the ELT Any accidental transmission with this maintenance dongle will not involve SAR operation as the identification code transmitted is recognised by COSPAS SARSAT as not on board When a maintenance dongle is connected e Country code is 227 France Protocol is Test Identification number is SI 5 digits the last 5 digits of CSN number If the pin programming option is selected by the operator the following
30. mission is close to 100 hours at 20 C with new batteries In the worse conditions possible a distress is pinpointed 5 5 hours maximum after the ELT activation and the position is subsequently updated if necessary every 2 hours As it is therefore preferable to keep the battery power for 121 5 243 MHz homing frequency transmission for the rescue operations the 406 MHz transmission is deliberately stopped after 24 hours to extend the 121 5 243 transmission for as long as possible The transmitter battery expiry date is fixed at 6 years after manufacturing If no activation of the ELT occurs during the battery lifetime it shall be replaced every 6 years see note below NOTE The useful life time of batteries is twelve 12 years To be in compliance with FAR regulations they have to be replaced every 6 years when 50 percent of their useful life has expired PAGE 105 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 5 Technical characteristics A Mechanical characteristics The housing is to be installed on a Mounting Bracket P N S1820511 01 1 Material Material Plastic ASA PC LURAN SKR2867 CWU Treatment Light yellow colour RAL 1028 Fire classification MO 2 Overall Dimensions Refer to 1 Outline Dimensions page 501 Transmitter outline dimensions 172 x 82 x 82 mm Outline dimensions with mounting bracket 181 x 100 x 94 mm 3 Weight AF AF H
31. on refer to Remote Control Panel technical description 2 J2 Connector J2 is used to connect the outside antenna through a 50 02 coaxial cable IMPORTANT The length of the coaxial cable should not exceed 2 meters 6 ft for a standard RG58 or equivalent coaxial cable If the cable length exceeds 2 meters a low loss cable of attenuation less than 1 dB must be used PAGE 107 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 6 Technical Specifications TYPE G SWITCH SENSOR Three frequency ELT Mechanical G switch sensor compliant 121 5 243 0 406 025 MHz with EUROCAE ED62 specifications e Automatic fixed 6 G switch assembly in ELT KANNAD e COSPAS SARSAT Class Il 406 AF 6D S1821502 06 20 C to 55 C BATTERY 406 MHz TRANSMISSION KIT BAT300 P N S1820516 99 Frequency 406 025 MHz 2 kHz 3 x LiMnO D type cells for transmitter Output power 5W 37 dBm 2 dB power supply Modulation type 16K0G1D Biphase Replacement every 6 years L encoding HOUSING Transmission duration Material Molded plastic 440ms short message every 50 Color Yellow sec compatible with long message Transmitter dimensions transmission 520ms 172 mm x 82 mm x 82 mm Autonomy Over 24 hours at Overall dimensions 20 C max 181 mm x 100 mm x 94 mm 121 5 243 MHz TRANSMISSION Weight typical 1110 g max 1260 g e Frequencies including battery 121 5 MHz 6 kHz Tightness O ring
32. on number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp PAGE 615 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 15 Pre delivery Inspection Log FIT DECAL HERE f Y PAGE 616 FEB 01 2008 Distributed by Manufactured by KANNA MARTEC Serpe lesm Z I des Cinq Chemins 56520 GUIDEL FRANCE T l Phone 33 0 2 97 02 49 49 Fax 33 0 2 97 65 00 20 DMA174M Ref 0139162M
33. or for the antenna 1 Ant ArmOffOn RC Figure 101 Front Panel The visual indicator gives an indication on the working mode of the beacon e after the self test a series of short flashes indicate the self test failed one long flash indicates a correct self test in operating mode periodic flashes during 121 5 243 transmission long flash during 406 transmission A buzzer gives audio information on the beacon working continuous tone during self test 2 beeps per second during 121 5 243 transmission silence during 406 transmission PAGE 102 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 3 Working mode information The KANNAD 406 AF AF H AF 6D have 4 different modes e Off Self test temporary mode e Armed standby mode to enable automatic activation by the shock sensor or by the remote control panel e On transmission Transmission is effective if the beacon is activated either manually on the ELT control panel remotely by the ON switch on the remote control panel or automatically by the shock sensor A Off The ELT is off when the switch is in position OFF No part of the ELT is energized This mode must only be selected when the ELT is removed from the aircraft B Self Test The self test mode is a temporary mode max duration 5 sec in which the ELT checks the main characteristics of the transmitter Battery
34. or work has consisted in studying aircraft crashes study made by the Crash Research Institute and evaluating the acceleration amplitudes involved As a consequence G Switch specifications have been modified to optimize the accuracy of the crash detection PAGE 2 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 2 KANNAD 406 ELTs Presentation The KANNAD 406 AF AF H AF 6D are composed of a transmitter a mounting bracket a remote control panel mandatory if ELT controls are not available from the pilot s position refer to RTCA DO 183 RTCA DO 204 EUROCAE ED 62 an outside antenna a Programming Dongle for pin programming function option CS144 Interface Module option The transmitter bracket Programming Dongle and CS144 Interface Module are installed in the aircraft near the tail The outside antenna is mounted on the fuselage near the tail The remote control panel is installed in the cockpit and connected to the ELT with a 4 or 5 wire bundle Coaxial cable Max cable loss 1 dB i e 2 mtrs with RG 58 4 wire bundle AWG 24 Power Supply Nav System System with optional CS144 Figure 2 ELT system description The KANNAD 406 AF and AF 6D are designed to be installed on fixed wing aircraft or helicopters The KANNAD 406 AF H is to be installed only on helicopters PAGE 3 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSP
35. reas a programmed message begins with FF FE 2F Example of message programmed in ELT FF FE 2F 53 C3 24 97 38 OB A6 OF DO F5 20 Example of same message decoded by SARTECH ARG5410 FF FE DO 53 C3 24 97 38 0B A6 OF DO F5 20 C 121 5 MHz IMPORTANT this test must only be carried out between H and H 5 minutes Do not exceed 30 seconds of transmission This test must be carried out with a VHF receiver e Tune VHF receiver to 121 5 MHz Start transmission either on ELT ON position or onthe RCP ON position the ELT shall be in the ARM position Listen to the 121 5 MHz sweep tone Stop transmission either on ELT OFF or ARM position oronthe Remote Control Panel press TEST and RESET the ELT shall be in the ARM position PAGE 304 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG TROUBLESHOOTING 1 General Procedure for fault isolation on board uses the visual indicator of the ELT s front panel This visual indicator is activated by a self test capability within the ELT 2 Faults on Self test A Visual indicator When the self test is carried out the number of flashes gives an indication of the faulty parameter detected during the self test 1 3 1 flashes Low battery voltage Check battery refer to CMM 25 63 01 for repair See note 1 below 2 3 2 flashes Low RF power Check 406 MHz power refer to CMM 25 63 01 for repair see note 1 below 3 343 flashes Faultv VCO locking faultv
36. s 243 0 MHz 12 kHz ENVIRONMENTAL CONDITIONS Output power 100 to 400 mW RTCA DO 160D EUROCAE Chi to 25 20dBm to 26 dBm D1 XBA ED62 SYLMC AWXXXXZXXX for each frequency ZWLI A1 A2 A3 XX XXA Modulation type 3K20A3X QUALIFICATIONS Modulation rate between 85 and JTSO 2C91a 8 JTSO 2C126 EUROCAE 100 ED62 Frequency of modulation signal TSO C91a amp TSO C126 RTCA DO183 8 1420 Hz to 490 Hz with decreasing DO204 sweep Autonomy Over 48 hours at 20 C CONTROLS e ARM OFF ON switch Red visual indicator BNC antenna connector DIN12 connector for remote control panel RCP and pin programming option Buzzer PAGE 108 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 7 Activation A Standby mode for automatic activation In order to be automatically activated by the crash sensor the ELT must be in standby mode This mode is mandatory during the flight We recommend to switch the ELT off only when the aircraft is parked for a long period or for a maintenance operation e Check that the antenna is correctly connected e Switch to ARM To operate the ELT with the Remote Control Panel ensure that e The ELT switch is in the ARM position B Manual activation e Check that the antenna is correctly connected e Switch to ON either on the ELT or on the Remote Control Panel The ELT starts with the self test sequence 121 5 243 MHZ transmi
37. spection Log Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp Type of inspection _ Periodic _ Battery change _ Repair _ Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date __ Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 608 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D 8 Programming Log Identification protocol TN ICAO AOD SIN Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp Identification protocol TN ICAO AOD SIN TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date __ __ Service station Signature and stamp PAGE 609 FEB 01 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AF AF H AF 6D 9 Programming Log Identification protocol TN ICAO AOD S N TEST Identification number Beacon identification 15 HEX
38. ssion starts immediately after the self test 406 MHz starts after 50 seconds 406 burst every 50 sec during 24 hours During transmission buzzer operates and visual indicator flashes 8 Reset It is possible to stop the ELT in case of unintentional activation Regulations state that no transmission must be interrupted unless every means are used to contact and inform the Air Traffic Controller of this action Important notice As 406 MHz transmission is effective 50 seconds after the ELT activation if it is reset within this delay no further radio contact will be necessary A Manual reset e Switch to OFF B Reset with Remote Control Panel The switch has to be in the ARM position on the ELT e Switch to RESET amp TEST on the remote control 9 Self Test Refer to 1 Self test page 301 PAGE 109 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D PAGE INTENTIONALLY LEFT BLANK PAGE 110 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D INSTALLATION REMOVAL Only PART FAR 145 certified service stations can install the KANNAD 406 AF AF H AF 6D ELT 1 RTCA FAR recommendations The conditions and tests required for TSO approval of this ELT are minimum performance standards It is the responsibility of those desiring to install this ELT on a specific type or class of aircraft to d
39. voltage Programming and enables digital communication with a programming and test equipment This mode is selected e when switching from OFF to ARM e when switching to RESET TEST on the Remote Control Panel provided that the switch of the ELT is in the ARM position e when switching to ON prior to transmission The buzzer operates during the self test procedure After about 3 seconds the test result is displayed on the visual indicator as follows One long flash indicates valid test Aseriesof short flashes indicates false test result The number of flashes indicates the type of failure 3 1 LOW BATTERY VOLTAGE e 3 2 LOW TRANSMISSION POWER e 3 3 FAULTY VCO LOCKING FAULTY FREQUENCY e 3 4 NO IDENTIFICATION PROGRAMMED It is recommended to test the ELT regularly in order to detect any possible failure Refer to A Periodicity page 301 The number of self tests carried out is recorded This information is available when the ELT is connected to a programming and test equipment PR600 PAGE 103 FEB 01 2008 KANNAD INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AF AF H AF 6D C Armed In order to enable activation by the G Switch or with the Remote Control Panel the ELT must be in standby mode with the switch in the ARM position This mode is mandatory during flight The ELT should remain in the ARM position all the time except when the aircraft is parked for a long p
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