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User Manual INTEGRA AF.book

1. PAGE 303 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT PAGE INTENTIONALLY LEFT BLANK PAGE 304 OCT 20 2010 OPERATION MANUAL TROUBLESHOOTING 1 General Procedure for fault isolation onboard uses the indicator light red visual indicator of the EL T s front panel This indicator light is activated by a self test capability within the ELT 2 Faults on Self test When the self test is carried out the number of flashes on ELT or RCP s visual indicator gives an indication of the faulty parameter detected during the self test 1 3 1 flashes Low battery voltage Replace battery refer to CMM 25 63 06 for tests and repair 2 3 2 flashes Low RF power Check 406 MHz power refer to CMM 25 63 06 for tests and repair 3 3 3 flashes Faulty VCO locking faulty frequency Check frequencies refer to CMM 25 63 06 for tests and repair 4 344 flashes No identification programmed Check programming refer to CMM 25 63 06 for tests and repair 5 3 5 flashes VSWR Fault Check correct connection of antenna Perform a VSWR measurement 6 3 6 flashes GPS serial link fault Check GPS receiver refer to CMM 25 63 06 for tests and repair Note CMM 25 63 06 servicing instructions may be ordered to support sar kannad com PAGE 401 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT PAGE INTENTIONALLY LEFT BLANK PAGE 402 OCT 20 2010 OP
2. 1 long flash during ELT transmission on 406 MHz every 50 seconds Buzzer 1 5 Hz pulse signal recurrence 0 7 s during ELT transmission on 121 5 MHz except if the ELT has switched to internal antenna Refer to D VSWR Switch function External Integral antenna In case of accidental activation the ELT can be reset either by switching it to OFF or by switching to RESET on an optional Remote Control Panel when connected The number of 406 MHz bursts transmitted is recorded This information is available when the ELT is connected to a programming and test equipment PR600 D VSWR Switch function External Integral antenna During the 406 MHz burst the Voltage Standing Wave Ratio VSWR is measured After 5 bursts with wrong VSWR measurements the ELT switches from the external to the internal antenna in order to optimize transmitted signal In ON mode after 36 bursts the ELT decides to re switch or not according to the result of 2 new VSWR measurements NOTE when shifting from the external to the integral antenna the pulse signal of the buzzer shifts from one beep every 0 7 second to 2 beeps every 0 7 second Note The integral antenna has not been tested and approved by Cospas Sarsat E GPS Strategy To avoid consumption the GPS receiver is not power supplied in ARM mode After a crash automatic activation or manual activation the GPS will try to acquire a position in continuous mode during one hour
3. 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 and process the 406 MHz signal to ground stations LUT where the beacon positions are determined with a precision of less than 2 NM with the Doppler effect 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 PLB Personal Locator Beacon for land expeditions Figure 1 COSPAS SAHSAT System PAGE 1 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT B World coverage with the COSPAS SARSAT system The major improvement is the use of the COSPAS SARSAT system for processing aeronautical emergencies 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 LEOLUT
4. 66 Ib AF H typical 760 g 1 67 Ib Tightness O ring ENVIRONMENTAL CONDITIONS RTCA DO 160F EUROCAE ED14F Section 4 to 26 INTEGRA AF AF ER ED62A X ED62A A ED62A R C8C 1 X WXXXSZXXXZ ED62A B XXG33 XXA ED62A INTEGRA AF H AF H ER ED62A X ED62AJ A ED62A U G XWXX XSZXXXZ ED62A B XXG33 XXA ED62A QUALIFICATIONS ETSO 2C91a 4 ETSO 2C126 TSO C126a FOR USE OUTSIDE OF THE USA OR EASA RULES CONTACT YOUR LOCAL CIVIL AVIATION AUTHORITY PAGE 107 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 2 Equipment limitations Antenna ELT cable with maximum permitted attenuation 2db 400 MHz 3 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 off the ELT only when removed from the aircraft or when the aircraft is parked for a long period or for a maintenance operation Check that the antenna is correctly connected Switch to ARM To operate the ELT with an optional Remote Control Panel ensure that The ELT switch is the ARM position B Manual activation Check that the antenna is correctly connected Switch to ON either on the ELT or on an optional Remote Control Panel when connected The ELT starts with the self test sequence then after 50 sec transmits On 406 MHz one 406 MHz burst ev
5. 0 OCT 20 2010 OCT 20 2010 OCT 20 2010 LEP PAGE 3 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT LIST OF EFFECTIVE PAGES PAGE INTENTIONALLY LEFT BLANK LEP PAGE 4 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT TABLE OF CONTENTS INTRODUCTION WARRANTY Exclusion SYSTEM OVERVIEW COSPAS SARSAT System Description World coverage with the COSPAS SARSAT system Operation Environmental improvements of ELTs KANNAD 406 ELT System Presentation LINE REPLACEABLE UNITS Transmitter Bracket External antenna SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION Transmitter Functional Description Transmission Controls 4 Connectors Working mode information Self Test VSWR Switch function External Internal antenna Autonomy AF AF H INTEGRA ER P N 51851501 01 S1854501 01 AF AF H INTEGRA P N S1851501 02 S 1854501 02 Electrical interfaces Transmitter Technical Specifications Equipment limitations Activation Standby mode for automatic activation Manual activation Self Test Compatibility list Mounting brackets Remote control panels RCP DIN 12 connector or programming dongles External antennas INSTALLATION REMOVAL Registration TOC PAGE 1 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT TABLE OF CONTENTS General Registration in USA Registration in Canada Programming Pin programming option ELT transmitter installation
6. 514 06 PAGE 109 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT E External antennas KANNAD Designation Manufacturer KANNAD Part Number ANT300 CHELTON 1327 82 0124220 WHIP ANT AV200 RAMI 200 0146150 ROD ANT AV300 RAMI 300 0146151 BLADE ANT500 SENSOR SYSTEMS 0124222 S65 8282 406 BLADE ANT560 DAYTON GRANGER 0145787 ELT10 696 1 BLADE ANT650 CHELTON 2624 82 0124251 N A CHELTON 21 41 N A PAGE 110 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT PAGE INTENTIONALLY LEFT BLANK PAGE 111 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT PAGE INTENTIONALLY LEFT BLANK PAGE 112 OCT 20 2010 OPERATION MANUAL INSTALLATION REMOVAL 1 Registration A General The ELT must be registered prior to installation onboard When 406 MHz ELT is installed in an aircraft it is imperative that the aircraft owner register the ELT Each 406 MHz ELT contains a unique identification code that is transmitted to the satellite This helps the Rescue Coordination Center RCC to determine whether an emergency has actually occurred The unique identification permits accessing a data base The registration card available from the local registration authority must be completed and returned to this authority The Programming Datasheet DIM00300 must be completed and returned to your distributor Any change of ownership shall also be declared and reg
7. C for INTEGRA ER ELTs As it is therefore preferable to keep the battery power for 121 5 MHz homing frequency transmission for the rescue operations in compliance with COSPAS SARSAT specifications the 406 MHz transmission is deliberately stopped after 24 hours to extend the 121 5 MHz transmission for as long as possible PAGE 105 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT G Electrical interfaces J1 DIN 12 socket J1 is dedicated for connection to an optional Remote Control Panel to a Programming or Maintenance Dongles or to a programming equipment PR600 IMPORTANT Shielded cables are recommended The required wires are AWG24 J1 PIN Signal Name Destination Direction J1 A RCP RESET RCP IN J1 B DONGLE RX SMM Viewed from J1 C DONGLE CS SMM OUT Front Face J1 D DONGLE SK SMM OUT 1 J1 E DONGLE TX SMM PGM OUT M KAN J1 F DONGLE ALE2P SMM OUT 14556 IG COMMON RCP OUT J1 H RCP BUZZER RCP OUT J1 J RCPLED RCP OUT J1 K RCP ON RCP OUT J1 L DONGLE GND SMM PGM OUT J1 M RCP 2W COMMON RCP OUT AK KAR Table 1 J1 connector pin out J2 BNC female connector J2 is used to connect the external antenna through a 50 coaxial cable IMPORTANT NOTICE The use of a low attenuation coaxial cable is recommended The maximum permitted attenuation in the coaxial is 2db 400 MHz PAGE 106 OCT 20 2010 A
8. DOC09078A 4 2 2 5 Ref 0146257A cC pu 9 C o he o p G l gt OPERATION MANUAL AF INTEGRA AF H INTEGRA ELT With built in GPS amp Integral Antenna A Company of the Orolia Group Revision 00 sanba uodn GYNNVA 01 J8 Ip uuuu pausnjas 245 jueuinoop ay Aq eouejdeo2e Juaidioas 94 Aq aq jou 5 aY jeu pue Jo juesuoo ssaJdxe y eq 5 paurejuos BY JOU JAS BY Jeujreu jeu ssejdxe ay uo SI ay Bguepyuoo pue pue Jo Kuedoad aui si 5141 O Date of rev OCT 20 2010 First issue OCT 20 2010 Users are kindly requested to notify KANNAD of 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 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT RECORD OF REVISIONS REVISION DATE INSERTION DATE OCT 20 2010 OCT 20 2010 ROR PAGE 1 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT RECORD OF REVISIONS PAGE INTENTIONA
9. ERATION MANUAL AF INTEGRA AF H INTEGRA ELT aviation KANNAD o 2 lt o O lt a YN o E lt LL I O 1 Outline dimensions and weight with mounting bracket AF COMPACT 2165 S6 1 988 VHO3LNI H AV v6 1 088 VHO3LNI AV Ssjexoeuq ui spunod sweu ybi9 Bununow uj 1 eoid 86876 86 YOO sjax9eJq ui SJo jeuul Iu ui SUOISUBWIP 9 ON PAGE 501 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 2 Outline dimensions and weight with universal mounting bracket Typical weight with mounting bracket Weight in grams pounds in brackets AF INTEGRA 905 1 99 AF H INTEGRA 910 2 00 RC O CO I Q YN lt O c Ant Arm Off On gt Sm CO gt o c E O O Oy 7 98 PAGE 502 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 3 AF INTEGRA AF INTEGRA ER axis of installation YAW Axis Front face connectors Roll Axis Direction of Flight Arrow DEREN KINO ASN ADNIOUIW O4 ISNVUL MOLVDOT ADN39 MALUWSNVUL YO 503 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 4 AF H INTEGRA AF H INTEGRA ER axis of
10. LLY LEFT BLANK ROR PAGE 2 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE Title Page OCT 20 2010 Record of Revisions OCT 20 2010 OCT 20 2010 List of Effective Pages OCT 20 2010 OCT 20 2010 Table of Contents OCT 20 2010 OCT 20 2010 OCT 20 2010 OCT 20 2010 Introduction OCT 20 2010 OCT 20 2010 System Overview OCT 20 2010 OCT 20 2010 OCT 20 2010 OCT 20 2010 OCT 20 2010 OCT 20 2010 System Functional Description and Operation OCT 20 2010 OCT 20 2010 LEP PAGE 1 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE 103 OCT 20 2010 104 20 2010 105 OCT 20 2010 106 OCT 20 2010 107 OCT 20 2010 108 OCT 20 2010 109 OCT 20 2010 110 OCT 20 2010 111 OCT 20 2010 112 OCT 20 2010 Installation Removal 201 OCT 20 2010 202 OCT 20 2010 203 OCT 20 2010 204 OCT 20 2010 205 OCT 20 2010 206 OCT 20 2010 207 OCT 20 2010 208 OCT 20 2010 301 20 2010 302 20 2010 303 20 2010 304 OCT 20 2010 Troubleshooting 401 20 2010 LEP PAGE 2 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE 402 20 2010 Schematics and Diagrams 501 OCT 20 2010 OCT 20 2010 OCT 20 2010 OCT 20 2010 Servicing OCT 20 2010 OCT 20 2010 OCT 20 201
11. NNAD aviation H Transmitter Technical Specifications OPERATION MANUAL AF INTEGRA AF H INTEGRA ELT TYPE Two frequency ELT 121 5 406 037 MHz Automatic fixed COSPAS SARSAT Class INTEGRA AF AF H ER Class 1 40 C to 55 lt INTEGRA AF AF H Class Il 20 C to 55 lt 406 MHz TRANSMISSION Frequency 406 037 MHz 1 kHz Output power 5W 37 dBm 2 dB Modulation type 16K0G1D Biphase L encoding Transmission duration 520ms long message every 50 s Autonomy INTEGRA 24 Hours 40 C INTEGRA 24 Hours 20 C 121 5 MHz TRANSMISSION Frequencies 121 5 MHz 6 kHz Output power 50 to 400 mW 17dBm to 26 dBm typical 100 mW Modulation type 3K20A3X Modulation rate 85 96 Frequency of modulation signal 1600 Hz to 300 Hz with decreasing sweep Autonomy INTEGRA ER over 48 hours 40 C INTEGRA over 48 hours 20 C G SWITCH SENSOR Mechanical G switch sensor compliant with EUROCAE ED62 specifications CONTROLS e ARM OFF ON switch DIN12 socket for RCP and pin programming option Bright red visual indicator Buzzer BNC antenna connector BATTERY KIT BAT200 P N S1840510 01 LiMnO two element battery for transmitter power supply Replacement interval 6 years after date of manufacture HOUSING Material Polycarbonate Color Yellow color compounded Transmitter dimensions 131 x 86 x 75 4 mm 5 157 x 3 385 x 2 968 inches Weight AF typical 755 g 1
12. Panel when connected Note switching to ON directly on the ELT front panel will also activate the ELT PAGE 206 OCT 20 2010 OPERATION MANUAL K NNAD AF INTEGRA AF H INTEGRA ELT 6 Removal Switch the ELT to OFF Disconnect the external antenna from the BNC connector of the ELT If connected disconnect the DIN 12 Connector of Remote Control Panel bundle from the DIN12 socket of the ELT Unfasten the self stripping strap Remove the transmitter from the bracket Figure 4 Removing the transmitter PAGE 207 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT PAGE INTENTIONALLY LEFT BLANK PAGE 208 OCT 20 2010 OPERATION MANUAL KANNAD AF INTEGRA AF H INTEGRA ELT 1 Self test A Periodicity EUROCAE ED 62A Recommendations 2 8 9 The battery source shall provide sufficient capacity for a self test to be conducted according to the period specified by the manufacturer or at least once a month according to Cospas Sarsat requirement 8 7 5 Check the self test function according to manufacturer s recommendation and that such a test shall occur at least once every six months Manufacturer Recommendations It is recommended by the manufacturer to test the ELT to detect any possible failure Operational check must be performed regularly by a pilot or maintenance personnel from the cockpit Remote Control Panel It is recommended to perform a self test at least once every si
13. 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 onboard When a maintenance dongle is connected Country code is 227 France Protocol is Test Identification number is SI 5 digits the last 5 digits of CSN number or 6 digits the 6 digits of the number If the pin programming option is selected by the owner the following equipment are required a Programming Dongle on each aircraft a Maintenance Dongle on each ELT spare Figure 1 Maintenance Dongle PAGE 203 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 3 ELT transmitter installation procedure NOTE Intial installation bracket installation and first wiring is described in Initial installation manual DOCO9081 also supplied with the transmitter 1 Mount the transmitter on the bracket For AF INTEGRA or AF INTEGRA ER with Flight direction arrow of the ELT pointed towards the front of the aircraft according to Section 3 AF INTEGRA AF INTEGRA ER axis of installation page 503 For AF H INTEGRA or AF H INTEGRA ER with Flight direction a
14. RA ELTs are an extension of the range of KANNAD ELTs The development of this type of ELTs is based on the improvement of safety of flights either for light aircraft business aircraft or commercial aviation The safety of flights is strengthened thanks to a built in GPS giving a more accurate position transmitted within minutes following the distress and an Integral Antenna which may replace the external antenna in case on unavailability of this last one AF INTEGRA is designed for fixed wing aircraft or helicopters INTEGRA is designed for flat installation on board helicopters only The AF INTEGRA ER and INTEGRA ER ELTs are evolutions of AF INTEGRA and AF H INTEGRA ELTs The main evolution consists in the extension to 40 C of temperature range The instructions in this manual provide the information necessary for the installation and the operation of AF INTEGRA AF H INTEGRA AF INTEGRA ER and AF H INTEGRA ER ELTs Servicing instructions of ELT are normally performed by shop personnel For detailed instructions and identification parts list refer to CMM 25 63 06 These servicing instructions may be ordered to support sar kannad com For the initial installation please refer to Initial Installation Manual supplied with AF INTEGRA AF H INTEGRA AF INTEGRA ER and AF H INTEGRA ER ELTs FOR REGULATORY REQUIREMENTS PLEASE CONSULT YOUR NATIONAL AVIATION AUTHORITY NOTE 1 AF for Automatic Fixed PAGE IN
15. 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 Cospas Sarsat Decoder FF FE DO 53 C3 24 97 38 0B A6 OF DO F5 20 NOTE for location protocol beacons the content of the encoded position data field of the self test message shall be the default values extract from C S T001 Cospas Sarsat 3 121 5 MHz Transmission tests This check shall only be conducted during the first five minutes of any UTC co ordinated universal time hour and restricted in duration to not more than five seconds Be sure to notify any nearby control tower of your intentions This test must be carried out with a VHF receiver Aircraft VHF receiver may be used Tune VHF receiver to 121 5 MHz e Start transmission Switch ELT to ON Only 2 sweep tones are heard after 5 seconds then the 121 5 MHz stops Stop transmission Switch to OFF continue to listen to 121 5 MHz for a few seconds to ensure that the ELT does not continue to transmit after the test is terminated IMPORTANT If the ELT operates for approximately 50 seconds a 406 MHz signal is transmitted and is considered valid by the satellite system Switch ELT to ARM
16. T 2 KANNAD 406 ELT System Presentation AF INTEGRA and AF H INTEGRA belong to the AF type of ELTs which are permanently attached to an aircraft AF INTEGRA and AF INTEGRA ER are designed to be installed on fixed wing aircraft or helicopters AF H INTEGRA and AF H INTEGRA are designed for flat installation on board helicopters only The INTEGRA ELT system Refer to Section Figure 2 ELT system description page 4 is composed of 1 the ELT transmitter P N S1851501 01 for AF INTEGRA ER or P N S1851501 02 for AF INTEGRA or P N S1852501 01 for AF H INTEGRA ER or P N S1852501 02 for AF H INTEGRA a mounting bracket P N S1840502 01 or 51840502 02 an external whip rod or blade antenna A remote control panel a DIN 12 connector or programming dongle when the optional RCP is connected Note 1 The RCP is optional only if the commands and controls of the ELT are reachable and visible from the pilot seated position RTCA DO 2044 Equipment control and indicator installed for in flight use shall be readily accessible from the cockpit crew position The cockpit crew shall have an unobstructed view of visual indicator when in the normal seated position For details of approved part number of INTEGRA ELT system Refer to Section 6 Compatibility list page 109 The transmitter and bracket are installed in the aircraft near the tail The external antenna is mounted on the fuselage near the tail The remote contro
17. TRO 1 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT WARRANTY 1 Scope The equipment is warranted against all material or manufacturing defect for a period of two years from the date of installation on the aircraft or thirty months from the date of shipment from KANNAD S A S facilities whichever occur first Work carried out under the warranty shall not have the effect of extending the warranty period In respect of this warranty after a defect has been noted by our services the sole obligation incumbent upon us shall be the repair of the equipment or the element identified as being defective by our services or possibly its replacement free of charge to the exclusion of all compensation or damages This warranty covers the cost of parts and labour in our factories The cost of transportation of the equipment replaced or repaired are the purchaser s exclusive responsibility The risks shall be borne by the purchaser 2 Exclusion Defects and deterioration caused by natural wear of the product or by external accident poor maintenance abnormal conditions of use etc or by modification of the equipment and tools not recommended nor specified by our company are excluded from the warranty Also the warranty shall not cover visible defects which the purchaser wouldn t have formally notified KANNAD within 48 hours of receipt of the equipment PAGE INTRO 2 OCT 20 2010 NA OPERATION MANUAL SYSTEM OVERVIEW
18. ails contact the distributor as soon as possible Unless a waver is granted flight should be cancelled refer to National Aviation Authorities 2 Operational tests These tests must be performed by maintenance personnel when performing the first power up procedure or to check the transmitter Refer to B Test of transmitted signals A ELT operational tests NOTE ELT operational tests only provide the aircraft operator with an indica tion that the ELT is transmitting however a positive result cannot be interpret ed as meaning that the ELT meets all operational parameters connect the outside antenna to J2 switch the ELT from OFF to ARM e check that the Self Test result is one long flash B Test of transmitted signals 1 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 Installed antenna performances The VSWR of the installed external antenna shall be checked at all working frequencies The value must be 3 1 Above this limit the beacon will consider that the installation is not enough optimized PAGE 302 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 2 406 MHz Transmission tests This test must be carried out with a COSPAS SARSAT decoder Perform self test switch ELT from OFF to ARM Check with the COSPAS
19. and by different sequences up to 24 hours of 406 MHz transmission If the GPS receiver acquires a valid position then the message will contain the true position in the PAGE 104 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT next 406 MHz burst If the GPS receiver does not acquire a valid position then the message will contain the default value GPS position not valid According to 4 5 5 2 of Cospas Sarsat C S T001 if after providing valid data the navigation input fails or is not available the beacon message retains the last valid position for 4 hours 5 min after the last valid position data input After 4 hours the encoded position is set to the default values F Autonomy The energy is provided by a battery pack composed of a LiMnO two element battery See pages page 107 amp page 604 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 Battery shall be replaced according to the expiriy date indicated on the ELT NOTE ELT Battery useful life 6 years in service life ETSO TSO COSPAS SARSAT margins included IMPORTANT If the ELT is actived the battery shall be replaced See page 604 section 2 Battery replacement requirements With new batteries the duration of the 121 5 transmission is over 48 hours at 20 C for INTEGRA ELTs and over 48 hours at 40
20. ery 50 seconds 121 5 MHz continous transmission between each 406 MHz burst During transmission the buzzer operates and the red visual indicator flashes 4 Off It is possible to stop the ELT in case of unintentional activation e Switch to 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 switched off within this delay no further radio contact will be necessary 5 Self Test Refer to Section 1 Self test page 301 PAGE 108 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 6 Compatibility list A Mounting brackets Designation Part Number COMPACT MOUNTING BRACKET KIT S1840502 01 COMPACT UNIVERSAL MOUNTING BRACKET KIT 51840502 02 B Remote control panels RCP KANNAD Designation RC100 KIT RC102 KIT RC200 RC300 RC300 NVG RC600 NVG Y RC600 NVG W C Outside buzzer KANNAD Designation OUTSIDE BUZZER KIT D DIN 12 connector or programming dongles Designation DIN 12 connector Programming dongle Programming A320 Programming dongle A320 A340 Programming dongle Assy Part Number S1820513 03 S1820513 21 S1820513 11 S1820513 09 S1820513 10 S1820513 12 S1820513 13 Part Number S1820515 06 Part Number S1820514 03 S1820514 01 S1820514 04 S1820514 05 S1820
21. his information is available when the ELT is connected to a programming and test equipment PR600 3 Armed In order to enable activation by the G Switch or with an optional 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 except when the aircraft is parked for a long period or for maintenance 4 On This mode is selected manually by switching the ELT to ON by switching an optional Remote Control Panel switch to ON provided that the ELT switch is in the ARM position e automatically when a crash occurs provided that the ELT switch is in the ARM position When this mode is selected the ELT starts transmitting after 50 seconds on 406 MHz one 406 MHz burst every 50 seconds to the external antenna on 121 5 MHz continous transmission between each 406 MHz burst Activation 5mn max after the Turn ON at the nominal power required PAGE 103 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT In case of a GPS lock before the 5mn max the 121 5 MHz will be activated Continuous transmission after the 406 MHz burst after switch if necessary The red visual indicator on the ELT and on an optional remote control panel when connected flashes and the buzzer operates Red visual indicator 1 short flash during ELT transmission on 121 5 MHz every 0 7 seconds
22. installation YAW Axis Upper side Front face Ed m Lower side Front face connectors Direction of Flight Arrow PAGE 504 OCT 20 2010 SERVICING 1 Maintenance Schedule Battery replacement carried out by an accredited PART 145 or FAR 145 or equivalent maintenance station Periodic inspection depending if the ELT is opened or not PART 145 or FAR 145 or equivalent may be required Refer to local regulations IMPORTANT Inspections must be recorded on the ELT LOG SHEET ref DIM08013 supplied with the ELT fields Periodic Inspection log page 2 2 A Periodic inspection Note if required by the relevant Civil Aviation Authority Some Civil Aviation Authorities may require the ELT be tested periodically In this case it is recommended to check the following parameters Proper installation Operation of the controls and crash sensor Transmitted signals Battery corrosion Note Due to the technology used for our beacon and battery pack any corrosions between two battery replacements is unlikely to happen However if this inspection is required by Civil Aviation Authority this check is detailed in CMM 25 63 06 page block CHECK page 5001 Note 1 As indicated in the Canadian operating rule Standard 625 the ELT shall be checked at intervals not exceeding 12 months in accordance with Appendix G of Chapter 571 of the Airworthiness Manual 1 Proper installat
23. ion Remove ELT from its mounting bracket Refer to 8 6 Removal page 207 Inspect the mounting bracket and the ELT Ensure the mounting bracket and the ELT are free of cracks or other obvious damage Inspect the connection Visually inspect all connector pins 2 Operation of the control crash sensor Referto CMM 25 63 06 page block TESTING AND FAULT ISOLATION PAGE 601 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 3 Transmitted signals Refer to Section B Test of transmitted signals page 302 4 Batteries corrosion Refer to CMM 25 63 06 page block CHECK 5 Check of 121 5 MHz frequency Re install the ELT Refer to 3 ELT transmitter installation procedure page 204 Check 121 5 MHz frequency using the aircraft tune receiver Refer to 8 3 121 5 MHz Transmission tests page 303 B 6 year inspection Replacement of battery pack is mandatory every 6 years Refer to S 2 Battery replacement requirements page 604 Testing of the following elements and parameters of the ELT is mandatory every 6 years together with the battery pack replacement Visual control of the housing and accessories Operation of the controls and crash sensor Measurement of 406 and 121 5 MHz output power and frequencies Verification of digital message coding 6 year inspection must be performed in the order listed below 1 Visual control of the housing and accessories Remove ELT from its mo
24. istered with the local registration authority and with the distributor B Registration in USA Mail or Fax your registration form to NOAA SARSAT NSOF E SP3 4231 Suitland Road Suitland MD 20746 or Save Time Register your beacon online at www beaconregistration noaa gov All online registrations will be entered into the National 406 MHz Beacon Registration Database on the same day of entry Registration forms received via postal mail will be entered within 2 business days of receipt For online registrations a confirmation letter with your completed registration information form will be sent immediately via e mail or fax if provided Confirmation letters sent via postal mail should arrive within two weeks Once your registration confirmation is received please review all information Any changes or updates to your registration information can be done via the internet fax e mail or postal mail If you do not receive your registration confirmation from NOAA on the same day you submit it over the internet or within two weeks if you submit it by postal mail please call NOAA toll free at 1 888 212 SAVE 7283 or 301 817 4515 for assistance After initial registration or re registration you will receive a NOAA Proof of PAGE 201 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT Registration Decal by postal mail This decal is to be affixed to the beacon and should be placed in such a way that it is clearly visib
25. l panel is installed in the cockpit and connected to the ELT with a DIN 12 connector or a programming dongle and a 2 3 or 4 wire bundle not supplied PAGE 3 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT Figure 2 ELT system description Antennas not to scale Coaxial cable Connector lt 23 or 4 wire bundle WG 24 PAGE 4 OCT 20 2010 NA OPERATION MANUAL KANNAD AF INTEGRA AF H INTEGRA ELT 3 LINE REPLACEABLE UNITS A Transmitter The AF INTEGRA and AF H INTEGRA are ELTs designed to be installed onboard aircraft to transmit a distress signal on frequencies 406 MHz COSPAS SARSAT frequency for precise pinpointing and identification of the aircraft in distress 121 5 MHz used for homing in the final stages of the rescue operations The AF INTEGRA and AF H INTEGRA are certified as Automatic Fixed AF ELTs with the approved external antennas The housing of AF INTEGRA and AF H INTEGRA transmitters are made of molded plastic with excellent mechanical resistance The ELT housing is designed with no sharp edges Figure 3 ELT Transmitter PAGE 5 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT B Bracket The bracket installed near the tail is designed to fix the ELT with a Velcro amp strap This enables quick removal of the ELT for maintenance or exchange Velcro strap Bracket Figure 4 ELT Transmitter with Mounting Bracket The transmi
26. le If for some reason you do not receive the registration decal within two weeks please call NOAA toll free at 1 888 212 SAVE 7283 or 301 817 4515 Failure to register re register as required every two years or to notify NOAA of any changes to the status of your 406 MHz beacon could result in penalties and or fines being issued under Federal Law The owner or user of the beacon is required to notify NOAA of any changes to the registration information at any time By submitting this registration the owner operator or legally authorized agent declares under penalty of law that all information in the registration information is true accurate and complete Providing information that is knowingly false or inaccurate may be punishable under Federal Statutes Solicitation of this information is authorized by Title 47 Parts 80 87 and 95 of the U S Code of Federal Regulations CFR Additional registration forms can be found on the NOAA SARSAT website at www sarsat noaa gov or at www beaconregistration noaa gov C Registration in Canada Beacon information is held in the Canadian Beacon Registry maintained by the National Search and Rescue Secretariat for use in search and rescue operations Online access to the Registry is available for all beacon owners to register new beacons or to update their beacon information You can add or update your beacon information by accessing the registry directly sending in a completed registration for
27. m or by talking to one of our beacon registry representatives You can access the registry online www canadianbeaconregistry com by email CBROSarnet dnd ca by fax 1 613 996 3746 by telephone 1 800 727 9414 or 1 613 996 1616 The registration information must be updated when the aircraft ownership changes as per the Canadian Airworthiness Notice AN B029 refer to following link http www nss gc ca site Emergency Beacons canadian beacon registry e asp This information must be recorded on the ELT LOG SHEET ref DIM08013 supplied with the ELT fields Programming Log Additional information and registration forms can be found on the Canadian NSS website at http www nss gc ca site cospas sarsat INTRO e asp PAGE 202 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 2 Programming A Pin programming option The INTEGRA family offers pin programming capabilities to facilitate maintenance operations especially in the 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 onboard This Programming Dongle contains the identification information of the aircraft and remains onboard 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
28. procedure ELT transmitter Connection First power up Self test Periodicity Self test procedure Operational tests ELT operational tests Test of transmitted signals ELT Antenna link 406 MHz Transmission tests 121 5 MHz Transmission tests TROUBLESHOOTING General Faults on Self test Visual Indicator 341 flashes 3 2 flashes 3 3 flashes 344 flashes 3 5 flashes 3 6 flashes SCHEMATICS amp DIAGRAMS ELT Outline Dimensions with Mounting Bracket AF COMPACT ELT Outline dimension with Universal Mounting Bracket AF INTEGRA AF INTEGRA ER axis of installation AF H INTEGRA AF H INTEGRA ER axis of installation SERVICING Maintenance Schedule Periodic inspection Proper installation Operation of the control crash sensor Transmitted signals Batteries corrosion Check of 121 5 MHz frequency 6 year inspection TOC PAGE 2 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT TABLE OF CONTENTS Visual control of the housing and accessories Operation of the controls and crash sensor Measurement of output powers frequencies and verification of digital message 602 Current draw measurement in ARM and ON positions optional Battery pack replacement Check of 121 5 MHz frequency Battery replacement requirements TOC PAGE 3 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT TABLE OF CONTENTS PAGE INTENTIONALLY LEFT BLANK TOC PAGE 4 OCT 20 2010 OPERATION MANUAL INTRODUCTION INTEG
29. rrow of the ELT pointed towards the front or downwards the helicopter according to Section 4 AF H INTEGRA AF H INTEGRA ER axis of installation page 504 Slide the self stripping strap through the buckle Ensure the buckle is correctly positioned indifferently on right or left side of ELT regarding the horizontal center line of ELT as shown Detail A PAGE 204 OCT 20 2010 OPERATION MANUAL KANNAD AF INTEGRA AF H INTEGRA ELT 3 Fasten the self stripping strap tightly Figure 2 Installing the transmitter on the bracket PAGE 205 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 4 ELT transmitter Connection 1 Connect the cable of the outside antenna to the BNC connector of the front panel 2 Setthe 3 position switch of the front panel to ARM Figure 3 Installation controls and connectors Perform the first power up procedure see below 5 First power up Perform the following tests 1 ELT operational tests connect the external antenna to J2 switch the ELT from OFF to ARM check that the Self Test result is OK one long flash 406 amp 121 5 MHz transmission tests optional Refer to Section B Test of transmitted signals page 302 At the end of the first power up procedure switch the ELT to ARM The ELT is now in stand by mode and ready to be activated either automatically by G Switch sensor if a crash occurs or manually by an optional Remote Control
30. s 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 Thanks to the built in GPS receiver the position accuracy typically about 120 meters will be transmitted by the ELT within minutes following the distress The 121 5 MHz frequency is no more processed by COSPAS SARSAT system but is still used by SAR services for homing in the final stage of rescue operations C Operation In the event of a crash the ELT activates automatically and transmits a sweep tone on 121 5 MHz and the 406 MHz signal In a crash a G Switch shock detector turns the ELT ON when the ELT is subjected to an important change of velocity or deceleration Activation may also be accomplish by means of a Remote Control Panel RCP from the cockpit or directly from a switch of the ELT s front panel In the event the external antenna is unavailable due to the crash the integral antenna will replace it to transmit the 406 MHz signal to the Cospas Sarsat satellites Note The integral antenna has not been tested and approved by Cospas Sarsat D Environmental improvements of ELTs The certification of an ELT includes a range of severe mechanical tests resistance to flame impact and crush tests resistance up to 500 G shocks watertightness anti deflagration extreme temperatures 2 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA EL
31. t is mandatory after more than 1 hour of real transmission cumulated duration before or on the battery expiration date after use in an emergency after an inadvertant activation of unknown duration Only original and approved battery pack included in battery KIT BAT200 P N 51840510 01 supplied by KANNAD can be installed SAFT FRIWO Lithium Manganese Dioxide 2 x M20 D type cells PLEASE CONTACT YOUR LOCAL DISTRIBUTOR KANNAD refuse all responsibility and invalidate all warranty should other packs be installed Battery available from any KANNAD distributor or dealer List of distributor available on our Web site http www kannad com KANNAD 2 1 des Cinq Chemins BP23 56520 GUIDEL FRANCE Telephone 33 0 2 97 02 49 49 Fax 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 PAGE 604 OCT 20 2010 Distributed by Manufactured by ANNAD aviation KANNAD 2 1 des Chemins BP23 56520 GUIDEL FRANCE T l Phone 33 0 2 97 02 49 49 Fax 33 0 2 97 65 00 20 A Company of the Orolia Group DOCO09078A Ref 0146257A
32. t of the ELT is energized This mode must only be selected when the ELT is removed from the aircraft or when the aircraft is parked for a long period or for maintenance 2 Self Test The self test mode is a temporary mode max duration 15 sec in which the ELT checks the main characteristics of the transmitter Battery voltage Programming and enables digital communication with programming and test equipment This mode is selected when switching from OFF to ARM when switching to RESET TEST on an optional Remote Control Panel provided that the switch of the ELT is in position ARM when switching to ON prior to transmission The buzzer operates during the self test procedure PAGE 102 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT After about 10 seconds the test result is displayed on the visual indicator as follows 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 1 LOW BATTERY VOLTAGE 3 2 LOW TRANSMISSION POWER 343 FAULTY VCO LOCKING FAULTY FREQUENCY 3 4 NO IDENTIFICATION PROGRAMMED 3 5 FAULTY VOLTAGE STANDING WAVE RATIO LINK TO EXTERNAL ANTENNA 3 6 GPS SERIAL LINK It is recommended to test the ELT regularly in order to detect any possible failure Refer to Section A Periodicity page 301 The number of self tests carried out is recorded T
33. tter may be installed on its standard mounting bracket P N S1840502 01 or on an Universal Mounting Bracket P N 51840502 02 to re use existing drilling for retrofit Refer to DOCO9081 Initial Installation Manual for drilling masks and outline dimensions of these brackets C External antenna Only approved antennas may be installed Refer to Section 6 Compatibility list page 109 Connection to the ELT will be carried out with a 50 Ohm coaxial cable RG58 for example ended with a male BNC connector IMPORTANT NOTICE KANNAD recommends a cable with radio electric properties similar or better to those of a RG58 cable Note the 50 Ohm coaxial and the male BNC connector are not supplied PAGE 6 OCT 20 2010 OPERATION MANUAL SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION 1 Transmitter Functional Description A Transmission The transmitter 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 RCP The transmitter is designed to transmit on two frequencies 121 5 and 406 2 The 121 5 Mhz is mainly used for homing in the final stages of the rescue operations The 406 MHz frequency is used by the COSPAS SARSAT satellites for precise pinpointing and identification of the aircraft in distress Once activated the transmitter operates continuously on 121 5 2 During operations a digital message is transmitted on 406 037 MHz ever
34. unting bracket Refer to 6 6 Removal page 207 Inspect the mounting bracket and the ELT Ensure the mounting bracket and the ELT are free of cracks or other obvious damage Inspect the connection Visually inspect all connector pins 2 Operation of the controls and crash sensor Refer to CMM 25 63 06 page block TESTING AND FAULT ISOLATION 3 Measurement of output powers frequencies and verification of digital message Refer to CMM 25 63 06 page block TESTING AND FAULT ISOLATION PAGE 602 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 4 Current draw measurement in ARM and ON positions optional This test is required by Canadian Regulation according to CAR571 Appendix G c 3 d Refer to CMM 25 63 06 page block TESTING AND FAULT ISOLATION 5 Battery pack replacement CAUTION USE ONLY ORIGINAL AND APPROVED BATTERY PACK see 2 Battery replacement requirements Refer to CMM 25 63 06 page block DISASSEMBLY and page block ASSEMBLY 6 Check of 121 5 MHz frequency Re install the ELT Refer to 8 3 ELT transmitter installation procedure page 204 Check 121 5 MHz frequency using the aircraft tune receiver Refer to 8 3 121 5 MHz Transmission tests page 303 Note CMM 25 63 06 servicing instructions may be ordered to support sar kannad com PAGE 603 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 2 Battery replacement requirements Battery replacemen
35. x months but it should not be done more than once a month 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 B Self test procedure Check that the antenna is correctly connected Do not perform self test without antenna connected Tune aircraft radio to 121 5 MHz and ensure you can hear it Switch from position OFF to position ARM or press RESET amp TEST on the Remote Control Panel ensure that the ELT switch is in position ARM Listen for the buzzer it operates during the whole Self test procedure Close to the end of self test a short 3 sweeps 121 5 transmission is made confirm this on the aircraft radio After a few seconds the test result is displayed with the red visual indicator and the buzzer will sound One long flash indicates that the system is operational and that error conditions were found A series of short flashes indicates the test has failed Remark The number of flashes gives an indication of the faulty parameter detected during the self test PAGE 301 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT 3 1 LOW BATTERY VOLTAGE 3 2 LOW RF POWER 3 3 FAULTY VCO LOCKING FAULTY FREQUENCY 3 4 NO IDENTIFICATION PROGRAMMED 345 FAULTY VOLTAGE STANDING WAVE RATION EXT ANTENNA 346 GPS SERIAL LINK If self test f
36. y 50 seconds B Controls amp Connectors 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 socket for connection to an optional Remote Control Panel a programming dongle or a programming equipment BNC connector for the external antenna 4 2 1 3 Figure 201 Front Panel The red light gives an indication on the working mode of the beacon PAGE 101 OCT 20 2010 OPERATION MANUAL ANNAD AF INTEGRA AF H INTEGRA ELT e after the self test aseries of short flashes indicate the self test failed one long flash indicates a correct self test in operating mode periodic flashes during 121 5 transmission long flash during 406 transmission A buzzer gives audio information on the beacon working continuous tone during self test 1 beep every 0 7 second during 121 5 transmission silence during 406 transmission C Working mode information The ELT has 4 different modes Off Self test temporary mode Armed standby mode to enable automatic activation by the shock sensor or by an optional remote control panel On transmission Transmission is effective if the beacon is activated either manually on the ELT control panel automatically by the shock sensor or remotely by the ON switch of an optional remote control panel when connected 1 Off The ELT is off when the switch is in position OFF no par

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