INSTALLATION MANUAL OPERATION MANUAL KANNAD 406 AP
Contents
1. LEP PAGE 3 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL LIST OF EFFECTIVE PAGES PAGE INTENTIONALLY LEFT BLANK LEP PAGE 4 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL 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 AP Presentation LINE REPLACEABLE UNITS Transmitter Bracket Remote Control Panel External antenna Design features General Mechanical design Compatibilitv list Remote control panels RCP DIN 12 connector or programming dongles ELT NAV Svstem Interface External antennas SVSTEM FUNCTIONAL DESCRIPTION AND OPERATION Transmitter Controls Autonomv Electrical characteristics Electrical interface Technical Specifications Activation Standbv mode for automatic activation Manual activation as fixed ELT Manual activation as survival ELT Manual reset Reset with Remote Control Panel Self Test INSTALLATION REMOVAL TOC PAGE 1 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP TABLE OF CONTENTS Registration and Programming Pin programming option ELT and bracket installation Installation recommandations FAA Recommendations TSO C126a Section 5 b Application Data Requirements RTCA DO 182 Recommandations RTCA DO 204a Requirements Bracket installation Fixed wings Helicopters Transmitter installation Ant2. 12 2008 INSTALLATION MANUAL OPERATION MANUAL INSTALLATION REMOVAL 1 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 AP is fully compatible with the four programming protocols defined by the COSPAS SARSAT C S G005 document Serialised Number Aircraft 24 bit Address the same as MODE S ATC or TCAS Aircraft Operator Designator serialised number up to 4096 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 in the shop with a programming and test equipment PR600 and KANNAD 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 programming equipment via the DIN 12 connector A Pin programming option The KANNAD 406 AP offers pin programming capabiliti
3. 2 0 08 3 ATTACHMENT HOLES DIA 5 5 0 22 CSK90 PAGE 506 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 7 ANT410 outline dimensions and drilling mask Note all dimensions are in milimeters inches in brackets 473 6 18 62 0 25 4 1 0 17 0 05 DIA THRU C SK 8 0 32 DIA x 100 DEGREE OPP SIDE 4 PLACES PAGE 507 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 8 ANT560 outline dimensions and drilling mask 129 5 5 10 139 7 5 50 Note dimensions are in millimeters inches in brackets 228 6 9 max 4 6 1 52 18 4 06 57 1 2 25 2 1 125 152 4 6 213 3 8 4 PAGE 508 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL SERVICING 1 Maintenance Schedule Periodic inspection and battery replacement can only be carried out by PART 145 FAR 145 avionics workshops or equivalent agreement according to local regulations 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 e G Switch activation Battery voltage 121 5 MHz 243 0 MHz 406 025 MHz transmission power 121 5 MHz 243 0 MHz 406 025 MHz frequency 121 5 MHz AM sweep monitoring with VHF receiver Number of 406 MHz transmissions optional programming kit req
4. 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 Major 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 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 2 KANN
5. HLIM aP WNWIXVW OL 31IWT1 SSOT 3144 Y WIA DAV pet Y S31339SID p NOLLVILHISSVIJ IIA H SIJANOS 48 NOILVILAISSVIJ RIM 3183 XvOO v SALYIIONI L A S310 ex NY wann anag YE g Le TONIC DNINNV3D23d ND JONDA deJ 3IONDI XL 379N00 XS IINOM SI 379N00 Xa 379N00 NO dod 31 dod AIZZNA doi NOWAOD dod 13S32 dI 113 ILIWSNVAL 4017901 a PAGE 503 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 4 ANT AV200 outline dimensions and drilling mask Note all dimensions are in milimeters inches in brackets Weight 85 g 0 19 Ibs rZ 9 609 712 7 0 500 13 0 515 12 1 047677 Cy B Mounting Hole Mounting Hole option 1 option 2 Moisture seal Outside of aircraft po ao Mounting hole through___ 5 aircraft skin Name plate 5 Lock washer o e Hex nut amp PAGE 504 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 5 ANT AV300 outline dimensions and drilling mask Note all dimensions are in milimeters inches in brackets Weight 255 g 0 56 A N N N 15 87 0 625 DIA Connector hole 5 56 0 21 9 DIA 34 14 1 344 3 Mounting holes PAGE 505 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KANNAD KANNAD 406 AP 6 ANT300 outline dimensions and drilling mask Note all dimensions are in millimeters inches in brackets GASKET _ DIA 45 35 aT TH
6. N A PAGE 7 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL PAGE INTENTIONALLY LEFT BLANK PAGE 8 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION 1 Transmitter The KANNAD 406 AP 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 AP is 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 frequencv is used bv the COSPAS SARSAT satellites 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 frequencv sweeping downwards from 1420 Hz to 490 Hz with a repetition rate of 3 Hz During the first 24 hours of operation a digital message is transmitted on 406 025 MHz everv 50 seconds The output power on 406 MHz is 5 W The KANNAD 406 AP can transmit two tvpes 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
7. NAV equipment of the aircraft by RS232 RS422 or RS485 link or to an ARINC429 bus PAGE 101 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 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 connector for the antenna Ant Arm Off On 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 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 3 Working mode information The KANNAD 406 AP has 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 On transmission Transmission is effective if the beacon is activated either manually on the ELT control panel remotely by the ON switch on
8. 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 DO 204a Requirements The ELT unit shall be mounted to primary aircraft load carrying structures such as trusses bulkheads longerons spars or floor beams not aircraft skin or a structure that meets the requirements of the following test The mounts shall have a maximum static local deflection no greater than 2 5 mm when a force of 450 Newtons 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 m or more than 1 0 m from the mounting location Typical approaches for adding shelf and rail platform mounting provisions to aircraft structure as shown an FAA Advisory circular 43 13 2 Chapter 2 PAGE 203 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP B Bracket installation e Determine the location of the ELT on board according to FAR RTCA recommendations CAUTION Do not install the ELT in a location directly exposed to the sun Determine the axis of the ELT according to the type of aircraft Fixed wing aircraft Refer to 1 Fixed wings page 205 Helicopter Refer to 2 Helicopters page 205 Drill 4 holes 6 mm in the aircraft structure according to Drilling mask Holes 4 5 6 7 shall be preferred
9. before switching the RCP to ON wait for the end of the self test PAGE 303 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 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 whereas a programmed message begins with FF FE 2F Example of message programmed in ELT FF FE 2F 53 C3 24 97 38 0B 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 P5 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 on the 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 or on the Remote Control Pan
10. readily removable from the aircraft after a crash B Mechanical design The KANNAD 406 AP is made of moulded plastic with excellent mechanical resistance ASA PC light yellow colour The housing is designed with no sharp edges Figure 3 KANNAD 406 AP with mounting bracket PAGE 5 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 5 Compatibilitv list A Remote control panels RCP KANNAD Designation RC100 KIT RC150 KIT RC200 RC200 NVG RC300 RC400 RC500 320 RC600 NVG Y RC600 NVG W RC800 B DIN 12 connector or programming dongles KANNAD Designation DIN 12 connector Programming dongle Programming dongle A320 Programming dongle A330 340 Programming dongle Assy C ELT NAV System Interface KANNAD Designation CS144 RS CS144 A Connecting cable for CS144 RS or CS144 A KANNAD Part Number S1820513 03 S1820513 07 S1820513 11 S1820513 14 S1820513 09 S1820513 05 S1820513 02 S1820513 12 S1820513 13 S1820513 15 KANNAD Part Number S1820514 03 S1820514 01 S1820514 04 S1820514 05 S1820514 06 KANNAD Part Number S1825502 01 S1825502 02 S1825502 03 PAGE 6 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL D External antennas KANNAD Designation Manufacturer KANNAD Part Number ANT560 DAYTON GRANGER 0145787 ELT 10 696 1 ANT410 DAYTON GRANGER 0145488 ELT 720063 ANT300 CHELTON 1327 82 0124220 ANT AV200 RAMI AV 200 0146150 ANT AV300 RAMI AV 300 0146151 N A ARTEX 110 340
11. 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 or parked for a long period or for maintenance B Self Test The self test mode is a temporarv mode max duration 5 sec in which the ELT checks the main characteristics of the transmitter Batterv voltage Programming and enables digital communication with a programming and test equipment This mode is selected e when switching from OFF to ARM 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 e One long flash indicates valid test A series of short flashes indicates false test result The number of flashes indicates the type of failure e 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 e
12. 0 MHz must be used See Important notice D External antenna page 4 Fit both ends of coaxial cable with a waterproof Male BNC connector not supplied reference RADIALL R141007 or equivalent Connect one Male BNC connector to the antenna Female BNC socket PAGE 209 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 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 8 121 5 MHz transmission tests optional Refer to 4 406 and 121 5 MHz transmission test page 304 5 Removal Switch the ELT to OFF Refer to Figure 205 Installation controls and connectors Disconnect the Remote Control Panel or CS144 from the DIN12 connector Refer to Figure 205 Installation controls and connectors Disconnect the outside antenna from the BNC connector Refer to Figure 205 Installation controls and connectors Unfasten the self stripping strap Remove the auxiliary antenna Remove the transmitter from the bracket Figure 207 Removing the transmitter PAGE 210 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL 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
13. AD 406 AP Presentation The KANNAD 406 AP is composed of a transmitter a mounting bracket a remote control panel mandatorv 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 7 an auxiliary antenna for use as a survival beacon 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 AP is designed to be installed on fixed wing aircraft or helicopters PAGE 3 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 3 LINE REPLACEABLE UNITS A Transmitter The KANNAD 406 AP 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 It is certified as an Automatic Portable AP ELT and works with a three freq
14. DMA185J Ref 0139180J q 2 c G o G o l gt o c DI L I w LL INSTALLATION MANUAL OPERATION MANUAL KANNAD 406 AP transmitter Mounting bracket 1 strap KANNAD 406 AP P N S1820502 XX P N S1820511 01 Revision 08 jsenbas uodn GYNNYY 01 Ajajelpawu pawnjas aq JJEUS JUBWINJOP ay 10Wlayuny IVNNVM Aq 99UEJA899P u yum loud JNOLJHM Juaidioes ay Aq p sn aq jou JIBUS UOIJELWIOJUI ay Jey pue QVNNVX JO lu suo2 SS911X8 BY INOY IM POSOJSSIP aq JJBUS UI9 9U POLIEJUO9 UONEWLIOJUI By JOU JJOSJI JUBLUNDOP ay JOWJIBU ey UOIJIPUOD Ss idx AY uo PEUeO SI JUBLUNVOP ay UOIJBWJOJUI JBIJUBPIJUOD pue Mejaudoid SUIBJUOD pue GYNNYM JO Auadosd ay SI JUBLUNVOP siu AVNNVA O Date of rev APR 27 2010 First issue JUL 1999 Users are kindly request to notify KANNAD for any discrepancy omission or error found in this manual Please report to our customer support E mail support sar kannad com Tel 33 0 2 97 02 49 00 INSTALLATION MANUAL OPERATION MANUAL RECORD OF REVISIONS REVISION DATE INSERTION DATE MAR 18 2004 JAN 26 2005 JUN 28 2005 FEB 13 2008 SEP 12 2008 APR 27 2010 MAR 18 2004 JAN 26 2005 JUN 28 2005 FEB 13 2008 SEP 12 2008 APR 27 2010 ROR PAGE 1 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL RECORD OF REVISIONS PAGE INTENTIONALLY LEFT BLANK ROR PAGE 2 APR 27 2010 INSTALLA
15. 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 gg Flight Direction Arrow Washer small Mounting Racer 6 mm holes Aircraft structure ma Washer large Reinforcement plate not supplied Nylstop nut Figure 202 Bracket Installation PAGE 204 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL The G Switch axis shall be directed to sense the primary crash pulse along the longitudinal axis of the aircraft Reference to the G Switch is given by the arrow Sens du D placement Flight direction YAW Axis YAW Axis Front face ung connectors Z 45 di Label Direction of Flight Arrow Figure 203 KANNAD 406 AP fixed wings or helicopter installation 1 Fixed wings The G Switch sensor axis shall be pointed to sense the primary crash pulse along the longitudinal axis of the aircraft with maximum tolerance of 15 Consequently the KANNAD 406 AP shall be mounted with the arrow of the Direction of Flight label pointed towards the front of the aircraft 2 Helicopters The KANNAD 406 AP can be installed in its standard version on helicopter The ELT unit should be mounted with the front face connecto
16. TALLATION MANUAL OPERATION MANUAL 4 Autonomy The energy is provided by a battery pack composed of 3 LiMnO D cells See pages 107 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 ofthe 121 5 243 transmission 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 subsequentiv updated if necessarv everv 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 deliberatelv 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 batterv lifetime it shall be replaced everv 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 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 5 Electrical characteristics Transmitter power supply 3 x LiMnO D type cells A Electrical interface When installed on board the ELT has t
17. TION MANUAL OPERATION MANUAL LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE Title Page APR 27 2010 Record of Revisions APR 27 2010 APR 27 2010 List of Effective Pages APR 27 2010 APR 27 2010 Table of Contents APR 27 2010 APR 27 2010 APR 27 2010 APR 27 2010 Introduction SEP 12 2008 SEP 12 2008 System Overview SEP 12 2008 SEP 12 2008 SEP 12 2008 SEP 12 2008 SEP 12 2008 SEP 12 2008 APR 27 2010 APR 27 2010 CON O O OI N System Functional Description and Operation LEP PAGE 1 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE 101 SEP 12 2008 102 SEP 12 2008 103 SEP 12 2008 104 SEP 12 2008 105 SEP 12 2008 106 SEP 12 2008 107 SEP 12 2008 108 SEP 12 2008 109 SEP 12 2008 110 SEP 12 2008 Installation Removal 201 APR 27 2010 202 APR 27 2010 203 APR 27 2010 204 APR 27 2010 205 APR 27 2010 206 APR 27 2010 207 APR 27 2010 208 APR 27 2010 209 APR 27 2010 210 APR 27 2010 301 SEP 12 2008 302 SEP 12 2008 303 SEP 12 2008 304 SEP 12 2008 LEP PAGE 2 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE Troubleshooting 401 APR 27 2010 402 SEP 12 2008 Schematics and Diagrams 501 SEP 12 2008 502 SEP 12 2008 503 SEP 12 2008 504 APR 27 2010 505 APR 27 2010 506 APR 27 2010 507 APR 27 2010 508 APR 27 2010 Servicing 601 APR 27 2010 602 SEP 12 2008
18. ed 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 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL PAGE INTENTIONALLY LEFT BLANK PAGE INTRO 2 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KANNAD KANNAD 406 AP 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 for maritime applications ELT Emergency Locator Transmitter for aeronautical applications e PLB Personal Locator Beacon for land expeditions kg 3 Ne A T R C C RESCUE COORDINATION CENTER Figure 1 COSPAS SARSAT System PAGE 1 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL
19. el press TEST and RESET the ELT shall be in the ARM position PAGE 304 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 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 Repair and battery replacement can only be carried out by PART 145 FAR 145 avionics workshops or equivalent agreement according to local regulations 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 frequency Check 406 MHz frequency refer to CMM 25 63 01 for repair see note 1 below 4 3 4 flashes No identification programmed Check programming see note 2 below NOTE 1 Only services 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 repa
20. enna Installation Antenna Installation Recommendations FAA Recommendations RTCA DO 204 Requirements for ELT location Antenna installation procedure First power up Self test Periodicity Self test procedure ELT operational tests 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 Visual indicator 3 1 flashes 3 2 flashes 3 3 flashes 3 4 flashes Other faults detected Buzzer does not operate Buzzer operates permanentiv when ELT in ARM mode TOC PAGE 2 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL TABLE OF CONTENTS SCHEMATICS amp DIAGRAMS Outline Dimensions Drilling Mask ANT AV200 outline dimensions and drilling mask ANT AV300 outline dimensions and drilling mask ANT300 outline dimensions and drilling mask ANT410 outline dimensions and drilling mask ANT560 outline dimensions and drilling mask SERVICING Maintenance Schedule Periodic inspection Every 6 years Battery replacement TOC PAGE 3 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KANNAD 406 AP TABLE OF CONTENTS TOC PAGE 4 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL INTRODUCTION The instructions in this manual provide the information necessary for the installation and the operation of KANNAD 406 AP ELT Servicing instructions Referto SERVICING page 601 are normally perform
21. ertically polarized when the aircraft is in the normal flight attitude ELT antenna mounting surface should be able to whistand a static load equal to 100 times the antenna weight applied at the antenna mounting base in all directions The antenna should be mounted as close to the respective ELT as applicable The proximity of the ELT antenna to any vertically polarized communications antenna shall be such as to minimize radio frequency interference and radiation pattern distorsion of either antenna Coaxial cable connecting the ELT antenna installation should not cross the aircraft production breaks and should have vibrations proof RF connectors on each end The coaxial connecting the ELT transmitter to the external Antenna should be secured to the aircraft structure and when the coaxial cable is installed and the connectors are mated each end should have some slack B Antenna installation procedure The antenna must be mounted on the top of the aircraft to assure maximum visibility of satellites The upper aft portion of the fuselage should be preferred It should be mounted away from projections such as a propeller tail surfaces or the shadow of large antennas It is the responsibility of the installation agency to determine the appropriate and adequate antenna installation PAGE 208 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL Locate a position on the fuselage according to 8 2 RTCA DO 204a Requirements for ELT locat
22. es 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 EL T 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 201 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL 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 e Protocol is Test e Identification number is SI 5 digits the last 5 digits of CSN number or K 6 digits the 6 digits of the CSN number If the pin programming option is selected by the operator the following equipment are required a Programming Dongle on each aircraft e a Maintenance Dongle on each ELT spare Figure 201 Maintenance D
23. ether is used to fix the transmitter to a liferaft in case of ditching PAGE 108 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KANNAD KANNAD 406 AP Switch to OFF Disconnect the external antenna ANT and the Remote Control Panel RC Unfasten the Velcro strap Remove the transmitter and the auxiliary antenna from the bracket Connect the auxiliary antenna ANT Switch to ON Important Put the antenna in a vertical position The ELT starts with the self test sequence 121 5 243 MHz transmission starts immediately after the self test 406 MHz transmission starts after 50 seconds During transmission buzzer operates and visual indicator flashes periodically 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 Switch to RESET amp TEST on the remote control panel 9 Self Test Refer to 1 Self test page 301 PAGE 109 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL PAGE INTENTIONALLY LEFT BLANK PAGE 110 SEP
24. f the cable length exceeds 2 meters a low loss cable of attenuation less than 1 dB must be used 6 Technical Specifications TYPE Three frequency ELT 121 5 243 0 406 025 MHz e Automatic fixed e COSPAS SARSAT Class ll 20 C to 55 C 406 MHz TRANSMISSION Frequency 406 025 MHz 2 kHz Output power 5W 37 dBm 2 dB Modulation type 16K0G1D Biphase L encoding Transmission duration 440ms short message every 50 sec compatible with long message transmission 520ms Autonomy Over 24 hours at 20 C 121 5 243 MHz TRANSMISSION e Frequencies 121 5 MHz 6 kHz 243 0 MHz 12 kHz Output power 100 to 400 mW 20dBm to 26 dBm for each frequency Modulation type 3K20A3X Modulation rate between 85 and 100 Frequency of modulation signal 1420 Hz to 490 Hz with decreasing sweep Autonomy Over 48 hours at 20 C CONTROLS e ARM OFF ON switch e Red visual indicator e BNC antenna connector e DIN12 connector for remote control panel RCP and pin programming option e Buzzer G SWITCH SENSOR Mechanical G switch sensor compliant with EUROCAE ED62 specifications BATTERY KIT BAT300 P N S1820516 99 3 x LiMnO D type cells for transmitter power supply Replacement every 6 years HOUSING Material Molded plastic Color Yellow Transmitter dimensions 172 mm x 82 mm x 82 mm Overall dimensions max 290 mm x 115 mm x 95 mm Weight typical 1235 g max 1300 g including battery Tightness O r
25. ings ENVIRONMENTAL CONDITIONS RTCA DO 160D EUROCAE Ch1 to 25 D1 XBA ED62 YLMC AWXXXXZXXXZ WLI A1 A2 A3 XX XXA Note chapters 6 8 9 amp 10 according to DO160C QUALIFICATIONS ETSO 2C91a amp ETSO 2C126 FUROCAE ED62 TSO C91a 8 TSO C126 RTCA DO183 amp DO204 PAGE 107 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 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 Check that the antenna is correctly connected e Switch to ARM Remote Control Panel Connector i ARM OFF ON Switch Antenna connector To operate the ELT with the Remote Control Panel ensure that e The ELT switch is in the ARM position B Manual activation as fixed ELT Check that the external 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 transmission starts immediately after the self test 406 MHzZz starts after 50 seconds 406 burst every 50 sec during 24 hours During transmission buzzer operates and visual indicator flashes C Manual activation as survival ELT The KANNAD 406 AP can be used external the aircraft in survival version A t
26. ion A double plate may be necessary for the antenna to meet rigidity specifications in Section 2 RTCA DO 204a Requirements for ELT location page 208 A 9 Kilogram force 20 pound force applied in all direction should not cause an appreciable distorsion in the aircraft skin Each of the approved antennas requires a ground plane On fabric covered aircraft or aircraft with other types on nonmetallic skins a ground plane must be added This can be accomplished 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 The length of each foil radial should be at least equal to the antenna length and width atleast 1 inch due to the diameter of the antenna The ground plane must be connected to the shield of the antenna connector Antenna Metal foil under fabric or wood skin Figure 206 Antenna ground plane for non metallic aircraft According to the antenna to be installed use the appropriate outline drawings and drilling masks to determine the hole patern and drill size Refer to SCHEMATICS 8 DIAGRAMS page 501 Fabricate a 50 Ohms coaxial cable long enough to reach between the ELT installation location and the antenna location IMPORTANT The length of the coaxial cable should not exceed 2 7 meters 9 ft for a standard RG58 or equivalent coaxial cable If the cable length exceeds 2 7 meters a low loss cable of attenuation less than 1 dB 40
27. ir See note 1 above PAGE 401 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL PAGE INTENTIONALLY LEFT BLANK PAGE 402 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KANNAD 406 AP SCHEMATICS amp DIAGRAMS 1 Outline Dimensions Note all dimensions are in millimeters inches in bracket ITEMLIST x PART OF S18 20 51111 xx PART OF S18 21 512 11 WEIGHT TYPICAL 1235g MAX 1311g CENTER OF GRAVITY 5143 2 11 1 12 PAGE 501 SEP 12 2008 KANNAD 406 AP lt 3 lt z O lt cc LU a O lt 3 lt z O lt l lt n 2 Drilling Mask Qutline GENERAL TOLERANCES 01 10 66mm 1U9W320jdap ap SU9S U012294IP 1U01 4 sETL WWTBT 6 0 Wu0z 16L 0 WWO LE WWE Holes 4 prefered 3 6 2 PAGE 502 SEP 12 2008 lt p 2 lt ji coo us os lt DZ Z7 lt lt x e lt lt O KANNAD 04393010 8 SNId OL 3331 TS NV 5014 301393NND3 2 NIQ 30ISNI CITIYLSND AVDA LINONIO CIINIYA TIVWS x da JHL 40 WWADVIT ONISIA DI 33432 AI 40 NOISYIA 3WOS HLIM 3S0 LON SI IMIA SIHL 19 OY JHL 40 WYAOYIT ONINIA OL 33339 CITIVISNI dda NO 9NIQN3d30 Sx DINI 39N3333433 3D133NNU3 DNLLVN oe 30 Wa 0091NV AO QOGINV AD ADA O0PINY AD O0ELNY x 3dAl d33 NO DNIQN3d3 XX HLIA 12 3dAl 173 NO ONION3d30 2 OL 8 XX HIIA x SAILI 2 OL CILINI H15N31 INFIWAINGS YO XYOI 3HAL 8S93
28. o be connected e to a Remote Control Panel via a DIN12 connector e to an external 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 J1 This connector is dedicated for connection to the Remote Control Panel to the Programming or Maintenance Dongles to a 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 RCP TEST RESET RCP J1 B DONGLE RX SMM PGM Viewed from J1 C DONGLE CS SMM Front Face J1 D DONGLE SK SMM TIN Jl E DONGLE TX SMM PGM M DAY J1 F DONGLEALE2P SMM x WIG RCP COMMON RCP JIH RCPBUZZER JRCPC J1 J RCP LED RCP J1 K RCP ON RCP JI L JDONGLEGND SMM PGM JIM N C NG Table 1 J1 connector pin out This wire is not used with some versions of Remote Control Panels For precise information refer to Remote Control Panel technical description J2 Connector J2 is used to connect the external antenna through a 50 Q coaxial cable for use as fixed ELT or the auxiliarv antenna for use as survival ELT PAGE 106 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP IMPORTANT The length of the coaxial cable should not exceed 2 meters 6 ft for a standard RG58 or equivalent coaxial cable I
29. ongle PAGE 202 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL 2 ELT and bracket installation A Installation recommendations The ELT shall not be installed within 60cm 2 ft of a compass or flux gate The distance between ELT and antenna shall be determined so that according to the coaxial cable choosen the cable lost should be lt 1dB at 400 MHz 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 1 FAA Recommendations Installation must be made by qualified personnel in accordance with FAA regulations Duplicating a previous installation may not be acceptable Refer to FAA Advisory Circular 43 13 2A Acceptable Methods Techniques and Practices Aircraft Alterations specifically Chapters 1 2 11 and 13 TSO C126a Section 5 b Application Data Requirements The conditions and tests for TSO approval of this article are minimum performance standards Those installing this article on or in a specific type or Class of aircraft must determine that the aircraft installation conditions are within the TSO standards TSO articles must have separate approval for installation in an aircaft The article may be installed only according to 14 CFR part 43 of the applicable airworthiness requirements RTCA DO 182 Recommandations All ELT system components which must survive to a crash intact should be
30. quipment PR600 PAGE 103 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 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 mandatorv during flight The ELT should remain in the ARM position all the time except when the ELT is removed from the aircraft or parked for a long period 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 manually by switching to position ON by switching the Remote Control Panel switch to position ON provided that the ELT switch is in the ARM position when a crash occurs provided that the ELT switch is in the ARM position When this mode is selected the ELT starts transmission on 121 5 MHz 8 243 MHz immediately continuous transmission 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 MHz bursts effectivelv transmitted is recorded This information is available when the ELT is connected to a programming and test equipment PR600 PAGE 104 SEP 12 2008 INS
31. rs pointing downwards at a 45 angle to the yaw axis with maximum tolerance of 159 e and with Direction of Flight arrow towards the front of the helicopter NOTE Should the KANNAD 406 AP be installed on board helicopter it will be necessary to make a special mounting base to install the ELT PAGE 205 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN odo KANNAD 406 AP C Transmitter installation Verifv that the ELT identification label matches the aircraft tail number e Mount the transmitter on the bracket Slide the self stripping strap thought the buckle and fasten it tightly Figure 204 Installing the transmitter on the bracket e Fold the antenna and slide it under the Velcro strap Connect the external antenna to the BNC connector Refer to Figure 205 Installation controls and connectors as shown Figure 2 ELT system description page 3 Note regarding the external antenna The specific installation tightening torque etc of the external antenna is not covered by this manual Refer to antenna manufacturer s instructions General instructions for an external antenna installation are detailed 3 Antenna Installation page 208 Connect the Remote Control Panel or CS144 to the DIN12 connector Refer to Figure 205 Installation controls and connectors as shown Figure 2 ELT system description page 3 PAGE 206 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP Set the 3 po
32. 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 A series of short flashes See Remark below indicates the test has failed If self test fails contact the distributor as soon as possible Unless a waver 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 LOW RF POWER 3 3 FAULTY VCO LOCKING FAULTY FREQUENCY 3 4 NO IDENTIFICATION PROGRAMMED PAGE 301 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 2 ELT operational tests A Installation without programming dongle connect RCP to J1 and outside antenna to J2 switch the ELT from OFF to ARM e check that the Self Test re
33. sition switch Refer to Figure 205 Installation controls and connectors to ARM Remote Control Panel Connector ARM OFF ON Switch Antenna connector Figure 205 Installation controls and connectors e Perform the first power up procedure Refer to 4 First power up page 210 PAGE 207 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 3 Antenna Installation The external antenna can be either of whip rod or blade type according to aircraft speed Use only approved antennas Connection to the ELT will be carried out with a 50 Ohm coaxial cable RG58 for example ended with two male BNC connectors A Antenna Installation Recommendations 1 FAA Recommendations Installation must be made by qualified personnel in accordance with FAA regulations Duplicating a previous installation may notbe acceptable Methods for installing antenna are outlined in AC43 13 12 refer to FAA Advisory Circular 43 13 2A Acceptable Methods Techniques and Practices Aircraft Alterations specifically Chapters 1 3 11 and 13 2 RTCA DO 204a Requirements for ELT location ELT antennas should be located away from other antennas to avoid disruption of antenna radiation patterns Idealisticallv for the 121 5 MHz ELT antenna 2 5 meter separation is sufficient separation from VHF communications and navigation receiving antennas to minimize unwanted interferences ELT antennas should be v
34. sult 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 displays the result check that the Self Test result is OK one long flash PAGE 302 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL KAN KANNAD 406 AP 3 RCP operational tests Check correct operation of RCP LED and external buzzer by switching ELT and RCP as described in the sequential procedure hereunder with ELT switch in the ARM position RCP SWITCH Self test when switching ELT from OFF to ARM START TEST i EST RESE then ARMED Self test 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 8 RCP leds flashing ELT 8 RCP buzzers modulated activation EST RESE 4 atleast 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
35. uencv outside antenna when installed on board the aircraft or with a small whip antenna auxiliarv antenna when used as a survival ELT 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 External antenna The external 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 50 Ohm coaxial cable RG58 for example ended with a BNC connector IMPORTANT NOTICE KANNAD recommends a cable with radio electric properties similar or better to those of a RG58 cable PAGE 4 SEP 12 2008 INSTALLATION MANUAL OPERATION MANUAL 4 Design features A General The KANNAD 406 AP belongs to the AP type of ELTs which are intended to be rigdly attached to the aircraft before the crash but
36. uired 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 These tests are described in Service Letter SL S18XX502 25 12 B Everv 6 vears Testing of the various elements of the ELT is mandatorv everv 6 vears together with the batterv replacement e Visual control of the housing and accessories Refer to CMM 25 63 010r CMM 25 63 05 e O ring battery and desiccant capsule replacement Refer to CMM 25 63 01 or CMM 25 63 05 Beacon Tightness CMM 25 63 01 or CMM 25 63 05 Testing and Fault Isolation procedure as described in CMM 25 63 01 NOTE e CMM 25 63 01 level 3 CMM reserved for KANNAD service stations only e CMM 25 63 05 level 2 CMM available upon request or on KANNAD Website PAGE 601 APR 27 2010 INSTALLATION MANUAL OPERATION MANUAL C Battery replacement Battery replacement is mandatory after more than 1 hour of real 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 Battery available from any KANNAD distributor or dealer KANNAD Z I des Cinq Chemins BP23 56520 GUIDEL FRANCE Telephone 33 0 2 97 02 49 49 Fa
37. x 33 0 2 97 65 00 20 Web http www kannad com E mail contact aviation kannad com Support support sar kannad com Tel 33 0 2 97 02 49 00 List of distributor available on our Web site http www kannad com PAGE 602 SEP 12 2008 Distributed by Manufactured by KANNA KANNAD Z I des Cinq Chemins BP 23 56520 GUIDEL FRANCE T l Phone 33 0 2 97 02 49 49 Fax 33 0 2 97 65 00 20 www kannad com DMA185P Ref 0139180P
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