INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG
Contents
1. 0143020 DOCO6330B Date of rev FEB 13 2008 KANNAD 406 AP H transmitter Mounting bracket 1 strap ANT100 auxiliarv antenna OPERATION MANUAL INSPECTION LOG KANNAD 406 AP H l lt lt O lt l lt V 51820502 04 S1820511 01 0124206 q 2 3 First issue OCT 18 2006 Revision 01 Jsanbas uodn oi AJSIBIPOLULWI eq JJEUS eu AQ eouejdeooe ay Aq pesn jou 11245 jeu pue Jo ssaJdxe y eq JIBUS peurejuoo BY JOU jeu 55 y SI 9U L pue pue Jo aui SI 5141 Users 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 433 0 2 97 02 49 00 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H RECORD OF REVISIONS REVISION DATE INSERTION DATE OCT 18 2006 OCT 18 2006 FEB 13 2008 FEB 13 2008 ROR PAGE 1 FEB 13 2008 INST2. 2 TSO C126 Paragraph D Requirements The conditions and tests required for TSO approval of this ELT are minimum performance standards It is the responsibility of those desiring to install this ELT on a specific type or class of aircraft to determine that the aircraft installation conditions are within the TSO standards The article may be installed only if further evaluation by the applicant documents an acceptable installation and it is approved by the Administrator 3 RTCA DO 182 Recommandations All ELT system components which must survive to a crash intact should be attached to the airframe in such a manner that the attachment system can support a 100g load in the plus and minus directions of the three principal axes of the aircraft 4 RTCA DO 204 Requirements The ELT shall be mounted to primary aircraft load carrying structures such as trusses bulkheads longerons spars or floor beams not aircraft skin The mounts shall have a maximum static local deflection no greater than 2 5 mm 0 1 inch when a force of 450 Newton 100 Ibf is applied to the mount in the most flexible direction Deflection measurements shall be made with reference to another part of the airframe not less than 0 3 meters 1 foot nor more than 1 0 meter 3 feet from the mounting location PAGE 203 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H B Bracket installation Determine the
3. 20 C Weight typical 1235 g max 1300 g 121 5 243 MHz TRANSMISSION including battery Frequencies Tightness O rings 121 5 MHz 6 kHz ENVIRONMENTAL CONDITIONS 243 0 MHz 12 kHz RTCA DO 160D EUROCAE 1 to 25 Output power 100 to 400 mW D1 XBA ED62 SYLMC AWXXXXZXXX 20dBm to 26 dBm ZWLI A1 A2 A3 XX XXA for each frequency QUALIFICATIONS Modulation type 3K20A3X JTSO 2C91a amp JTSO 2C126 EUROCAE Modulation rate between 85 and ED62 10096 TSO C91a amp TSO C126 RTCA DO183 amp Frequency of modulation signal DO204 1420 Hz to 490 Hz with decreasing COSPAS SARSAT TAC N 105 sweep Autonomy Over 48 hours at 20 CONTROLS ARM OFF ON switch Bright red visual indicator BNC antenna connector DIN12 connector for remote control panel RCP and pin programming option Buzzer PAGE 108 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 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 Switch to ARM Remote Control Panel Connector ARM OFF ON Switch Antenna connector To operate the ELT with the Remote Control Panel ensure that
4. The ELT switch is in the ARM position B Manual activation as fixed ELT Check that the outside antenna is correctly connected 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 MHz 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 H can be used outside the aircraft in survival version A tether is used to fix the transmitter to a liferaft in case of ditching PAGE 109 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H Switch to OFF Disconnect the outside antenna ANT and the Remote Control Panel RC Unfasten the Velcro strap Remove the transmitter and the auxiliarv antenna from the bracket Connect the auxiliarv antenna ANT Switch to 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 15 possible to stop the ELT in case of unintentional activation Regulations state that no transmission must be interrupted unless every means
5. extreme temperatures 20 to 55 for more than 48 hours D G Switch shock detectors The shock detectors equipping old automatic ELTs are the cause of a large number of false alarms Major work has consisted in studving 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 2 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 2 KANNAD 406 AP H Presentation The KANNAD 406 AP H belongs to the AP type of ELTs which are intended to be rigdly attached to the aircraft before the crash but readily removable from the aircraft after a crash The KANNAD 406 AP H is designed to be installed on helicopters only The KANNAD 406 AP H is composed of a transmitter a mounting bracket a remote control panel mandatory if ELT controls are not available from the pilot s position refer to RTCA DO 183 RTCA DO 204 EUROCAE 20 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 0 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 inst
6. KANNAD KANNAD 406 AP H LIST OF EFFECTIVE PAGES SUBJECT PAGE JDATE 402 13 2008 Schematics Diagrams 501 13 2008 502 13 2008 503 13 2008 504 13 2008 Servicing 601 JFEB 13 2008 602 13 2008 603 13 2008 604 13 2008 605 13 2008 606 13 2008 607 13 2008 608 13 2008 609 13 2008 610 13 2008 611 13 2008 612 13 2008 3 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H LIST OF EFFECTIVE PAGES PAGE INTENTIONALLY LEFT BLANK LEP PAGE 4 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H 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 H Presentation LINE REPLACEABLE UNITS Transmitter Bracket Remote Control Panel Outside antenna Design features SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION Transmitter Controls Working mode information Autonomy Technical characteristics Mechanical characteristics Material Overall Dimensions Electrical characteristics Electrical interface Technical Specifications Activation Standby mode for automatic activation Manual activation as fixed ELT Manual activation as survival EL
7. ELT 8 RCP buzzers modulated activation EST RESE 4 4 at least 1 sec then ARMED ELT transmission stops ELT amp RCP leds go out ELT Buzzer stops immediately RCP Buzzer stops after max 5 sec END OF TEST Figure 301 RCP LED and buzzer operation IMPORTANT 2 before switching the RCP to ON wait for the end of the self test PAGE 303 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 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 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 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 2 53 24 97 38 6 OF DO F5 20 Example of same message decoded by SARTECH ARG5410 FF FE 00 53 24 97 38 6 OF DO F5 20 C 121 5 MHz IMPORTANT this test must only be carried out between H and H 5 minutes Do not exceed 30 seconds of transmiss
8. 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 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 110 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H INSTALLATION REMOVAL Only PART FAR 145 certified service stations can install the KANNAD 406 AP H ELT 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 H is fully compatible with the four programming protocols defined by 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 Numb
9. found on the ELT front panel from left to right 3 position switch ARM OFF ON Red visual indicator 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 red visual indicator gives an indication on the working mode of the beacon after the self test a series of short flashes indicate the self test failed one long flash indicates a correct self test in operating mode periodic flashes during 121 5 243 transmission long flash during 406 transmission A buzzer gives audio information on the beacon working continuous tone during self test 2 beeps per second during 121 5 243 transmission Silence during 406 transmission PAGE 102 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 3 Working mode information The KANNAD 406 AP H has 4 different modes Off Self test temporary mode 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 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 w
10. location of the ELT on board according to FAR RTCA recommendations e 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 i Lower side Uppeszii ri Front face HH Lower side lt Upper side connectors ILLI Front face connectors U Label Direction of Flight Arrow Figure 202 KANNAD 406 AP H installation IMPORTANT The KANNAD 406 AP H is designed to be installed on board helicopters oniv The Direction of Flight arrow shall point towards the front or the bottom of the helicopter and not pointing 45 downwards e the KANNAD 406 AP H is installed with the Direction of Flight arrow pointing towards the front of the helicopter the ELT shall be mounted with the upper side pointing towards the top of the helicopter e the KANNAD 406 AP H is installed with the Direction of Flight arrow pointing towards the bottom of the helicopter the ELT shall be installed with the lower side pointing towards the front of the helicopter Drill 4 holes 2 6 mm in the aircraft structure according to Drilling mask Holes 4 5 6 7 shall be preferred If the aircraft structure is not solid enough to withstand a 500 kg traction on the bracket a reinforcement plate not supplied should be installed as shown Figure 203 Bracket installation Fix the bracket with the 4 s
11. 3 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 3 Wiring M EMERGENCY LOCATOR TRANSMITER ELT he pio FERITE RCP RESET RCP COMMON RCP BUZZER RCP LED RCP ON NOTES PROGRAMMING DONGLE INDICATES CABLE 7 B WIRE CLASSIFICATION 3 RF SOURCES D WIRE CLASSIFICATION 4 DISCRETES A 24 AWG WIRE CABLE LOSS LIMITED MAXIMUM 198 DONGLE SK WITH RG58 TYPE COAX OR EQUIVALENT DONGLE RX B DONGLE CS LENGTH LIMITED TO 2 METERS WITH XX 18 TO 24 DEPENDING ELT TYPE WITH XX DEPENDING ON RCP TYPE x3 ANT300 OR ANT400 ROD OR ANT500 OR ANT600 BALDE x4 MATING CONNECTOR REFERENCE INFO DEPENDING RCP INSTALLED REFER WIRING DIAGRAM OF THE RCP x6 THIS WIRE IS NOT USED WITH SOME VERSION OF RCP REFER TO WIRING DIAGRAM DF THE RCP xA SMALL PRINTED CIRCUIT BOARD CINSTALLED INSIDE DIN 12 CONNECTOR PLUG AND SOLDERED TO PINS B C D E F L DONGLE DONGLE ALE2P DONGLE GND L PAGE 503 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H PAGE INTENTIONALLY LEFT BLANK PAGE 504 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H SERVICING 1 Maintenance Schedule Periodic inspection and battery replacement can only be carried out by an accredited PART or FAR 145
12. ALLATION MANUAL OPERATION MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H RECORD OF REVISIONS PAGE INTENTIONALLY LEFT BLANK ROR PAGE 2 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE Title Page FEB 13 2008 Record of Revisions FEB 13 2008 FEB 13 2008 List of Effective Pages FEB 13 2008 FEB 13 2008 Table of Contents FEB 13 2008 FEB 13 2008 FEB 13 2008 FEB 13 2008 Introduction FEB 13 2008 FEB 13 2008 System Overview FEB 13 2008 FEB 13 2008 FEB 13 2008 FEB 13 2008 FEB 13 2008 FEB 13 2008 System Functional Description and Operation FEB 13 2008 FEB 13 2008 LEP PAGE 1 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H LIST OF EFFECTIVE PAGES SUBJECT PAGE DATE 103 FEB 13 2008 104 JFEB 13 2008 105 13 2008 106 JFEB 13 2008 107 13 2008 108 13 2008 109 13 2008 110 13 2008 Installation Removal 201 13 2008 202 FEB 13 2008 203 13 2008 204 13 2008 205 13 2008 206 13 2008 207 13 2008 208 13 2008 209 13 2008 210 13 2008 301 13 2008 302 13 2008 303 13 2008 304 13 2008 Troubleshooting 401 13 2008 2 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG
13. ATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 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 check that the Self Test result is OK one long flash B Installation with Programming Dongle connect the outside antenna to J2 switch the ELT from OFF to ARM check that the Self Test fails 3 4 flashes if not connect a maintenance dongle to J1 Switch the ELT from OFF to ARM Check that the Self Test fails 3 4 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 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 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 EST RESE then ARMED Self test Wait end of self test 7 sec max Cw ELT amp RCP leds flashing ELT amp RCP buzzers modulated activation 3 ELT continues to transmit ELT 4 RCP leds flashing
14. Inspection Log TOC PAGE 3 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H TABLE OF CONTENTS PAGE INTENTIONALLY LEFT BLANK TOC PAGE 4 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H INTRODUCTION The instructions in this manual provide the information necessary for the installation and the operation of KANNAD 406 AP H ELT Servicing instructions Refer to SERVICING page 601 are normally performed by shop personnel For servicing and maintenance instructions refer to CMM 25 63 01 For regulatory requirements please consult your national aviation authority PAGE INTRO 1 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H PAGE INTENTIONALLY LEFT BLANK PAGE INTRO 2 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H 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 satellites which relay the 121 5 243 MHz signals and process the 406 MHz signal to ground stations LUT where the beacon positions are dete
15. NSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H 10 Programming Log Identification protocol TN ICAO AOD S N Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp Identification protocol TN ICAO AOD 5 TEST Identification number Beacon identification 15 HEX 10 Aircraft Number Date _ __ Service station Signature and stamp 611 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 11 Pre delivery Inspection Log FIT DECAL HERE f 612 13 2008 Distributed Manufactured by KANNA KANNAD 2 1 des 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 DOCO06330B Ref 0143020B
16. T red or amber visual indicator beeper on certain versions The remote control panel is connected to the ELT via a 4 or 5 wire cable equipped with a Programming Dongle or a DIN 12 connector on the ELT side and the connector corresponding to the Remote Control Panel version on the other side D Outside antenna The outside antenna also installed near the tail can be either rod or blade type according to aircraft speed Connection to the ELT will be carried out with a 50 Ohm coaxial cable RG58 for example ended with a BNC connector PAGE 4 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 4 Design features The KANNAD 406 AP H is made of moulded plastic with excellent mechanical resistance ASA PC light yellow colour The housing is designed with no sharp edges It can be easily taken in one hand Figure 3 KANNAD 406 AP H with mounting bracket PAGE 5 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H PAGE INTENTIONALLY LEFT BLANK PAGE 6 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION 1 Transmitter The KANNAD 406 AP H 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
17. T Manual reset Reset with Remote Control Panel Self Test INSTALLATION REMOVAL TOC PAGE 1 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H TABLE OF CONTENTS Registration and Programming Pin programming option ELT Installation ELT and bracket installation recommendations FAA Recommendations TSO C126 Paragraph D Requirements RTCA DO 182 Recommandations RTCA DO 204 Requirements Bracket installation Transmitter and auxiliary antenna installation Antenna installation Antenna installation recommendations Antenna mounting location Antenna installation procedure RCP Installation if any ELT connection First power up Removal 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 Indicator lamp 3 1 flashes 3 2 flashes 3 3 flashes 3 4 flashes Other faults detected Buzzer does not operate Buzzer operates permanently when ELT in ARM mode SCHEMATICS amp DIAGRAMS TOC PAGE 2 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H TABLE OF CONTENTS Outline Dimensions Drilling Mask SERVICING Maintenance Schedule Periodic inspection Every 6 years Battery replacement Periodic Inspection Log Programming Log Pre delivery
18. acement mandatory date Date _ __ Service station Signature and stamp of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date _ __ Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 606 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AP H 6 Periodic Inspection Log Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date _ __ Service station Signature and stamp Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date _ __ Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 607 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 7 Programming Log Identification protocol TN ICAO AOD S N TEST Identification numbe
19. alled 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 Pd wW Bou Power Supply Nav System System with optional CS144 Figure 2 EL T system description 1 Note Only transmitter and auxiliary antenna are supplied with this manual PAGE 3 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 3 LINE REPLACEABLE UNITS A Transmitter The KANNAD 406 AP H is an ELT designed to be installed on board helicopters to transmit a distress signal on 3 frequencies 406 MHz COSPAS SARSAT frequency for precise pinpointing and identification of the aircraft in distress 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 frequency outside antenna when installed on board the aircraft or with a small whip antenna auxiliary 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 can be supplied 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 3 position switch ON ARMED RESET amp TES
20. crews 8 washers and 4 nylstop nuts supplied IMPORTANT tighten to a torque between 4 and 5 Newton x meter PAGE 204 FEB 13 2008 KANNAD Washer small Mounting bracke Washer large Nylstop nut INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AP H Flight Direction Arrow 2 9 Reinforcement plate not supplied Figure 203 Bracket installation PAGE 205 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H C Transmitter and auxiliary antenna installation e Verify that the ELT identification label matches the aircraft tail number 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 Fold the antenna and slide it under the Velcro strap PAGE 206 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H D Antenna installation 1 Antenna installation recommendations 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 3 11 and 13 RTCA DO 204 Requiremerents The antenna shall be mounted to provide either right hand circular or vertical
21. e following tests 1 ELT operational tests e connect RCP to J1 and outside antenna to J2 switch the ELT from OFF to ARM check that the Self Test result is OK one long flash RCP operational tests Refer to 3 RCP operational tests page 303 406 amp 121 5 MHz transmission tests optional Refer to 4 406 and 121 5 MHz transmission test page 304 At the end of the first power up procedure switch the ELT to ARM The ELT is now in stand by mode and to be activated either automatically by G Switch sensor if a crash occurs or manually by RCP if any Note switching to ON directly on the ELT front panel will also activate the ELT PAGE 209 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 4 Removal e Switch the ELT to OFF Refer to Figure 206 Installation controls and connectors Disconnect the Remote Control Panel 5144 from the DIN12 connector Refer to Figure 206 Installation controls and connectors Disconnect the outside antenna from the BNC connector Refer to Figure 206 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 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H 1 Self test A Periodicity It is recommended by the manufacturer to test
22. er This identification consists of up to 7 alphanumeric characters Programming of the ELT can be carried out either or the distributor order must include programming details inthe shop with a programming and test equipment PC interface and DOS or Windows software on board the aircraft with a programming equipment or programming dongle This operation takes less than 2 minutes and does not need any hardware operation The identification is simply downloaded in the ELT when connected to the KANNAD programming equipment the DIN 12 connector A Pin programming option The KANNAD 406 AP H offers pin programming capabilities to facilitate maintenance operations especially in case of removals and or replacement A special DIN 12 connector with a Serial Memory Module called Programming Dongle is connected to the ELT when installed on board This Programming Dongle contains the identification information of the aircraft and remains on PAGE 201 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H board the aircraft When an unprogrammed ELT is installed and connected to this Programming Dongle and the ELT is switched to ARM it automatically updates its own memory with the identification data contained in the Programming Dongle memory When the ELT is removed from the aircraft it keeps its identification data For maintenance purposes it is possible t
23. hen the ELT is removed from the aircraft B Self Test The self test mode is a temporary mode max duration 5 sec in which the ELT checks the main characteristics of the transmitter Battery voltage Programming and enables digital communication with a programming and test equipment This mode is selected 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 when switching to ON prior to transmission The buzzer operates during the self test procedure After about 3 seconds the test result is displayed on the visual indicator as follows One long flash indicates valid test A series of short flashes indicates false test result The number of flashes indicates the type of failure e 3 1 LOW BATTERY VOLTAGE 3 2 LOW TRANSMISSION POWER 3 3 FAULTY VCO LOCKING FAULTY FREQUENCY 3 4 NOIDENTIFICATION 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 PAGE 103 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H when the ELT is connected to a programming and test equipment PR600 Armed In order to enable activation by the G Switch or with the Remote Control Panel the ELT mu
24. in out This wire is not used with some versions of Remote Control Panels For precise information refer to Remote Control Panel technical description 2 J2 Connector J2 is used to connect the outside antenna through 50 Q coaxial cable for use as fixed ELT or the auxiliary antenna for use as survival ELT IMPORTANT The length of the coaxial cable should not exceed 2 meters 6 ft for a standard RG58 or equivalent coaxial cable If the cable length exceeds 2 meters a low loss cable of attenuation less than 1 dB must be used PAGE 107 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 6 Technical Specifications TYPE G SWITCH SENSOR Three frequencv ELT Mechanical G switch sensor at 45 121 5 243 0 406 025 MHz compliant with EUROCAE ED62 Automatic fixed specifications COSPAS SARSAT Class II BATTERY 20 C to 55 C KIT BAT300 51820516 99 406 MHz TRANSMISSION 3 x D type cells for transmitter e Frequency 406 025 MHz 2 kHz power supply Output power 5W 37 dBm 2 dB Replacement every 6 years e Modulation type 16K0G1D Biphase I HOUSING L encoding Material Molded plastic Transmission duration Color Yellow color compounded 440ms short message every 50 Transmitter dimensions sec compatible with long message 172 mm x 82 mm x 82 mm transmission 520ms Overall dimensions Autonomy Over 24 hours at max 290 mm x 115 mm x 95 mm
25. ion This test must be carried out with a VHF receiver Tune VHF receiver to 121 5 MHz Start transmission either on ELT ON position or onthe RCP ON position the ELT shall be in the ARM position Listen to the 121 5 MHz sweep tone Stop transmission either on ELT OFF or ARM position oronthe Remote Control Panel press TEST and RESET the ELT shall be in the ARM position PAGE 304 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H TROUBLESHOOTING 1 General Procedure for fault isolation on board uses the visual indicator lof the ELT s front panel This visual indicator is activated by a self test capability within the ELT 2 Faults on Self test A Visual indicator When the self test is carried out the number of flashes gives an indication of the faulty parameter detected during the self test 1 3 1 flashes Low battery voltage Check battery refer to CMM 25 63 01 for repairSee note 1 below 2 342 flashes Low RF power Check 406 MHz power refer to CMM 25 63 01 for 566 note 1 below 3 343 flashes Faulty VCO locking faulty 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 566 note 2 below NOTE 1 Only PART FAR 145 certified stations accredited by KANNAD can perform these repairs 2 Onl
26. 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 frequency is used by 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 frequency sweeping downwards from 1420 Hz to 490 Hz with a repetition rate of 3 Hz The AM modulation factor is between 85 and 100 During the first 24 hours of operation a digital message is transmitted on 406 025 MHz every 50 seconds The output power on 406 MHz is 5 W The KANNAD 406 AP H can transmit two types of messages on 406 MHz 112 bits for a short message identification only 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 NAV equipment of the aircraft by RS232 RS422 or RS485 link modulation at 400 bps enables to transmit all the relevant identification information to the COSPAS SARSAT satellites in 440 ms short message or 520 ms long message PAGE 101 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 2 Controls The following controls are to be
27. ithium batteries and equipment containing such batteries are subjected to regulations and classified under class 9 as from 1st of January 2003 The autonomy of the 121 5 243 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 subsequently updated if necessary every 2 hours As it is therefore preferable to keep the battery power for 121 5 243 MHz homing frequency transmission for the rescue operations the 406 MHz transmission is deliberately stopped after 24 hours to extend the 121 5 243 transmission for as long as possible The transmitter battery expiry date is fixed at 6 years after manufacturing If no activation of the ELT occurs during the battery lifetime it shall be replaced every 6 years see note below NOTE The useful life time of batteries is twelve 12 years To be in compliance with FAR regulations they have to be replaced every 6 years when 50 percent of their useful life has expired PAGE 105 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 5 Technical characteristics A Mechanical characteristics The housing is to be installed on a Mounting Bracket P N 51820511 01 1 Material Material Plastic ASA PC LURAN SKR2867 CWU Treatment Light yellow colour RAL 1028 Fire classification MO 2 Overall Dimensions Refer to 1 O
28. load ELT weight x 100 The interconnecting antenna to ELT cable should have sufficient slack on both ends that it will not be subjected to any tensile load and should be tied loosely to the tether PAGE 207 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 3 Antenna installation procedure Ensure that the antenna mounting location meets the requirements as described 2 Antenna mounting location page 207 A double plate will most likely be necessary for the antenna to meet rigidity specifications in 2 Antenna mounting location page 207 A 9 Kilogram force 20 pound force applied in all direction should not cause an appreciable distorsion in the aircraft skin On fabric covered aircraft or aicraft 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 Metal foil under fabric M TEENS or wood skin Figure 205 Antenna ground plane for non metallic aircraft Use the outline drawings and drilling masks supplied by your antenna manufacturer to determine the hole patern and drill size Fabricate a 50 Ohms coaxial cable long enough to reach between the ELT installation location and the antenna location IMPORTANT The le
29. maintenance station with valid agreement for KANNAD ELT maintenance A Periodic inspection Note if required by the relevant Civil Aviation Authority Some Civil Aviation Authorities may require the ELT is tested periodically In this case KANNAD recommends to check the following parameters Battery voltage 121 5 MHz 243 0 MHz 406 025 MHz transmission power 121 5 MHz 243 0 MHz 406 025 MHz frequency VCO lock 121 5 MHz AM decoding sweep monitoring with VHF receiver Number of 406 MHz transmissions optional programming kit required Number of self tests carried out optional programming kit required Programmed data optional programming kit required NOTE This functioning check can be carried out without opening the ELT but requires specific equipment Refer to CMM 25 63 01 page block SPECIAL TOOLS FIXTURES AND EQUIPMENT B Every 6 years Testing of the various elements of the ELT is mandatory every 6 years together with the battery replacement Visual control of the housing and accessories Refer to CMM 25 63 01 Orring battery and desiccant capsule replacement Refer to CMM 25 63 01 Beacon Tightness CMM 25 63 01 Testing and Fault Isolation procedure as described in CMM 25 63 01 PAGE 601 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H C Battery replacement Battery replacement is mandatory after more than 1 hour of real transmissio
30. n cumulated duration before or on the battery expiration date Only original battery pack included in battery kit KIT BAT 300 P N S1820516 99 supplied by KANNAD can be installed KANNAD refuse all responsibility and invalidate all warranty should other packs be installed PAGE 602 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 2 Periodic Inspection Log Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date _ __ Service station Signature and stamp Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date _ __ Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 603 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG 406 3 Periodic Inspection Log Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp T
31. ngth of the coaxial cable should not exceed 2 meters 6 ft for a standard RG58 or equivalent coaxial cable If the cable length exceeds 2 meters a low loss cable of attenuation less than 1 dB must be used Fit one end of coaxial cable with a waterproof connector matching with the antenna connector the other end ELT side with a waterproof Male BNC connector not supplied reference RADIALL R141007 Connect the cable to the antenna socket E RCP Installation if any The Remote Control Panel shall be readily accessible from the pilot s normal seated position Refer to the manual provided with your RCP and to 3 Wiring page 503 PAGE 208 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H F ELT connection Connect the outside antenna to 42 BNC connector Refer to Figure 206 Installation controls and connectors as shown Figure 2 ELT system description page 3 Connect the Remote Control Panel CS144 to J1 DIN12 connector Refer to Figure 206 Installation controls and connectors as shown Figure 2 ELT system description page 3 Set the 3 position switch Refer to Figure 206 Installation controls and connectors to ARM J2 ARM OFF ON Antenna RCP Switch Connector Connector Ant Arm Off On RC Figure 206 Installation controls and connectors Perform the first power up procedure Refer to 3 First power up page 209 3 First power up Perform th
32. o 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 Country code is 227 France Protocol is Test Identification number is SI 5 digits the last 5 digits of CSN number If the pin programming option is selected by the operator the following equipment are required a Programming Dongle on each aircraft e a Maintenance Dongle on each ELT spare Figure 201 Maintenance Dongle PAGE 202 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 2 ELT Installation A ELT and bracket installation recommendations The ELT should not be installed at less than 60 cm 2 ft of a compass or flux gate Use cable of loss lt 198 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
33. polarization when the aircraft is in the normal flight attitude The antenna shall be installed as close to the unit as possible 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 The antenna mounting surface shall be able to whistand a static load equal to 100 times the antenna s weight applied at the antenna mounting base along the longitudinal axis of the aircraft Antenna mounting location 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 Locate a position on the fuselage where the antenna can be installed vertically with at least 0 75 meter 29 52 inches clearance from other antennas specially VHF mounted on the aircraft when installed the coaxial cable of the antenna will not cross any major structural sections in the aircraft so that in the event of a crash the ELT and the antenna are in the same section placing the antenna directly above the ELT unit being the best solution the ELT transmitter and outside antenna are on opposite sides of an airframe production break the components should be secured to each other by a tether that can support a 100 G
34. r Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp Identification protocol ICAO AOD 5 TEST Identification number Beacon identification 15 HEX ID Aircraft Tail Number Date Service station Signature and stamp PAGE 608 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H 8 Programming Log Identification TN ICAO AOD S N Identification number Beacon identification 15 HEX 10 Aircraft Number Date Service station Signature and stamp Identification protocol TN ICAO AOD 5 TEST Identification number Beacon identification 15 HEX 10 Aircraft Number Date _ __ Service station Signature and stamp PAGE 609 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 9 Programming Log Identification protocol TN ICAO AOD SN TEST Identification number Beacon identification 15 HEX 10 Aircraft Tail Number Date _ __ Service station Signature and stamp Identification protocol ICAO AOD 5 LITEST Identification number Beacon identification 15 HEX 10 Aircraft Tail Number Date Service station Signature and stamp PAGE 610 FEB 13 2008 I
35. rmined 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 PLB Personal Locator Beacon for land expeditions Figure 1 COSPAS SARSAT System PAGE 1 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 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 bv Doppler effect bv the LEO satellites with a precision better than 2 NM 4 km at anv 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
36. st be in standby mode with the switch in the ARM position This mode is mandatory during flight The ELT should remain in the ARM position all the time except when the aircraft is parked for a long period or for maintenance The Remote Control Panel is energized by the ELT when switched to ARM 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 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 amp 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 effectively transmitted is recorded This information is available when the ELT is connected to a programming and test equipment PR600 PAGE 104 FEB 13 2008 INSTALLATION MANUAL MANUAL INSPECTION 06 KANNAD KANNAD 406 AP H 4 Autonomy The energy is provided by a battery pack composed of 3 LiMnO D cells See pages 108 amp 602 for Kit battery reference Lithium cells l
37. the ELT to detect any possible failure It is recommended to perform a self test once a month by pilot or maintenance personnel from the cockpit Remote Control Panel but it should not be done more than once a week However each self test consumes energy from the battery Should self tests be carried out more often than the maximum allowed the battery life time might be shorter than specified Do not perform Self test without the antenna connected B Self test procedure Check that the antenna is correctly connected 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 Switch back to OFF 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 INO IDENTIFICATION PROGRAMMED PAGE 301 FEB 13 2008 INSTALL
38. utline Dimensions page 501 Transmitter outline dimensions 172 x 82 x 82 mm Outline dimensions with auxiliary antenna and mounting bracket 290 x 115 x 95 mm 8 Weight Typical 1235 g max 1300 g including battery and auxiliary antenna B Electrical characteristics Transmitter power supply x LiMnOs D type cells C Electrical interface When installed on board the ELT has to be connected to a Remote Control Panel via a DIN12 connector to an outside antenna via a connector The DIN12 connector is also used to connect a programming dongle a CS144 interface or a programming and test equipment PAGE 106 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 1 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 J1 A TEST RESET J1 B DONGLE RX SMM PGM Viewed from J1 C DONGLE CS SMM Front Face J1 D JDONGLE SK SMM PES J1 E DONGLE TX SMM PGM M 9 DONGLE ALE2P SMM J LC J1 G RCP COMMON RCP J1 H BUZZER RCP J1 J RCPLED RCP J1 K RCPON RCP J1 L DONGLE GND SMM PGM J1 M Table 1 J1 connector p
39. y accredited programming stations can perform programming 3 Other faults detected A Buzzer 1 Buzzer does not operate Refer to CMM 25 63 01 for 56 note 1 above 2 Buzzer operates permanently when ELT in ARM mode Refer to CMM 25 63 01 for 56 note 1 above PAGE 401 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H PAGE INTENTIONALLY LEFT BLANK PAGE 402 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H SCHEMATICS amp DIAGRAMS 1 Outline Dimensions Note all dimensions are in millimeters inches in bracket ITEMLIST IDENT DESCRIPTION PARTNUMBER ELT MODEL KANNAD 416 2 MOUNTING BRACKET 5629581 3 VELROSTR P 52524 amp AUXILIARY ANTENNA x PART OF S18 21 511 11 xx PART OF S18 21 512 14 WEIGHT TYPICAL 12359 MAX 1311g CENTER GRAVITY 51 3 12 11 1 12 PAGE 501 FEB 13 2008 406 2 O O 0 lt 5 2 lt O lt lt 5 2 lt O lt l lt n KANNAD 2 Drilling Mask GENERAL TOLERANCES 01 10 gt SU9S U012294IP 4461 4 4418 f WW68 6 70 610 LE WWE Holes 4 7 prefered 3 6 J PAGE 502 FEB 1
40. ype of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 604 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD 406 AP H 4 Periodic Inspection Log Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date _ __ Service station Signature and stamp Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery replacement mandatory date Date Service station Signature and stamp 9 note complete P N of replaced components if battery pack has been changed also note Batch Number Tester Name and Date of Manufacture PAGE 605 FEB 13 2008 INSTALLATION MANUAL OPERATION MANUAL INSPECTION LOG KANNAD KANNAD 406 AP H 5 Periodic Inspection Log Type of inspection Periodic Battery change Repair Other Operations carried out Next recommended inspection date Next planned battery repl
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