ELTA ADT406 ELT 406 MHz (Emergency Locator Transmitter) User Manual

ELTA ELT 406 MHz (Emergency Locator Transmitter)

Contents

ADT 406 AF AP users handbook

86(5¶6+$1'%22.Documentation P/N: 02E62356 Rev C Initial issue: Jun 30/02 Title Page Jul 30/03 86(5¶6+$1'%22.,1&/8',1*,167$//$7,210$18$/$1'/2*%22. (0(5*(1&</2&$72575$160,77(502'(/$'7$)$3,17+(&263$66$56$76<67(0Issued by (/7$)14 Place Marcel Dassault 31702 BLAGNAC France www.elta.fr SERIAL NUMBER LABEL
86(5¶6+$1'%22.Page 1 Apr 30/03LIST OF UPDATES INSERTION INSERTION UPDATE No. ISSUE DATE BY UPDATE No. ISSUE DATE BY A B C INITIAL Jun 30/02 Apr 30/03 Jul 30/03 C.CRESP E.LABRIFFE E.LABRIFFE
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86(5¶6+$1'%22.Page 3 Apr 30/03LIST OF EFFECTIVE PAGES CHAPTER/ SECTION PAGE DATE CHAPTER/ SECTION PAGE DATE TITLE PAGE LISTE OF UPDATES LIST OF EFFECTIVE PAGE TABLE OF ILLUSTRATIONS LEADING PARTICULARS TABLE OF CONTENTS 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 Jul 30/03 Apr 30/03 BLANK Apr 30/03 BLANK Jun 30/02 BLANK Jun 30/02 BLANK Jun 30/02 BLANK Jun 30/02 Jun 30/02 Jun 30/02 Apr 30/03 Apr 30/03 Apr 30/03 Apr 30/03 Jun 30/02 Apr 30/03 Apr 30/03 Apr 30/03 Apr 30/03 Jul 30/03 Jun 30/02 Apr 30/03 Jun 30/02 Apr 30/03 Apr 30/03 Apr 30/03 Apr 30/03 Jun 30/02 Jun 30/02 Appendix A Appendix B 1 2 3 4 5 6 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Apr 30/03 Apr 30/03 Apr 30/03 Apr 30/03 Apr 30/03 Apr 30/03 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02 Jun 30/02
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86(5¶6+$1'%22. Page 5 Jun 30/02 TABLE OF ILLUSTRATIONS Page Figure 1 : COSPAS/SARSAT - System Principle 12 Figure 2 : ELT ADT 406 AF / AP Presentation 14 Figure 3 : ELT ADT 406 AF / AP – Dimensions (Basic Configuration) 15 Figure 4 : Tolerances on the Axis for Installation of the ELT ADT 406 AF / AP 22 Figure 5 : Installation of the ELT ADT 406 AF / AP - Drilling Pattern Dimensions 24 Figure 6 : ELT ADT 406 AF / AP Installation - Wiring Diagram 25 Figure 7 : ELT ADT 406 AF / AP - Detailed Description 32
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86(5¶6+$1'%22. Page 7 Jun 30/02 LEADING PARTICULARS &$87,21 7+,675$160,77(5,6$87+25,=(')2586(21/<'85,1*6,78$7,2162)*5$9($1',00,1(17'$1*(5&$87,21 ,7,6,03(5$7,9(7+$7($&+%($&212:1(55(*,67(567+(,5%($&21&217$&7(/7$25$33529('$*(17722%7$,17+(,1)250$7,215(/$7,9(727+,65(*,675$7,21&$87,21 7+(%($&210867,03(5$7,9(/<%(352*5$00(':,7+7+(5(/(9$17,'(17,),&$7,21$87+25,=('%<7+(/2&$/$,5:257+,1(66&$87,21 21&(7+(%($&21+$6%((1352*5$00(',7,6*(1(5$/<$66,*1('72$1$,5&5$)71$0($1','(17,),&$7,21,)7+,6%($&21,686('21$127+(5$,5&5$)7,7:28/'+$9(72%(5(352*5$00('1(:1$0($1','(17,),&$7,21&$87,21 %()25(,167$//,1*2586,1*7+,6(48,30(177+(9$/,',7<2)7+(,1)250$7,21217+(%($&21/$%(/0867,03(5$7,9(/<%(&+(&.('
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86(5¶6+$1'%22. Page 9 Jun 30/02 TABLE OF CONTENTS PAGE 1. INTRODUCTION TO THE COSPAS-SARSAT SYSTEM 11 A. The COSPAS-SARSAT system 11 B. System organization 11 C. The distress frequencies 13 D. ELTA and the COSPAS-SARSAT system 13 2. GENERAL DETAILS OF THE ELT ADT 406 AF / AP 14 A. Purpose of the ELT ADT 406 AF / AP 14 B. Characteristics 16 3. DESCRIPTION OF THE ELT ADT 406 AF / AP AND OF THE AIRCRAFT COMPONENTS 18 A. General description 18 B. Detailed description 18 4. INSTALLATION OF THE ELT ADT 406 AF / AP 22 A. General 22 B. Installation of the beacon on the aircraft 22 C. External antenna installation 24 D. Remote control unit installation 24 E. Installation and configuration of the beacon 26 5. UTILIZATION OF THE ELT ADT 406 AF / AP 27 A. Automatic activation 27 B. Manual activation 27 C. Beacon shutdown 28 D. Beacon self-test 28 6. MAINTENANCE OF THE ELT ADT 406 AF / AP 30 A. Beacon self-test 30 B. Maintenance periodicity table 30 C. Battery replacement 30 D. Battery discarding 31 E. Test to do at the time of a beacon return in workshop 31
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86(5¶6+$1'%22. Page 11 Jun 30/02 1. INTRODUCTION TO THE COSPAS-SARSAT SYSTEM A. The COSPAS-SARSAT* system The purpose of the COSPAS-SARSAT satellite system is to detect and locate all distress signals transmitted by aeronautical, maritime or land-based beacons, for the search and rescue organizations. This program is the result of an international collaboration between the United States, Canada and France on the one hand (SARSAT project), and Russia on the other hand (COSPAS project). These two projects are fully compatible. Since the first results were obtained several countries have joined the program. Several other countries have shown an interest and will soon be joining the COSPAS-SARSAT system partners. ELTA in relation with CNES (French National Space Agency) has developed the complete range of products required for COSPAS-SARSAT system operation. Following an in-depth study phase, ELTA has arrived at highly conclusive technical results, and experimental and operational use of the "ground" equipment have proven this equipment’s reliability and ease-of-use. B. System organization (Ref. Fig. 1) In the COSPAS-SARSAT system, space equipment is placed on board several satellites in low near-polar orbit to capture transmissions from emergency transmitters and to retransmit these signals to specialized ground stations called /ocal 8ser 7erminals (LUT). These ground stations determine the position of the emergency transmitters and then retransmit the position data to the designated 0ission &ontrol &enters (MCC). The MCCs in turn retransmit these data to the appropriate 5escue &oordination &enters (RCC) so that they can start the search and rescue operations. * COSPAS-SARSAT : COSPAS = Kosmicheskaya Sistyema Poiska Avariynych Sudov SARSAT = Search and Rescue Satellite-Aided Tracking
86(5¶6+$1'%22. Page 12 Jun 30/02 Legend : ELT : (mergency /ocator 7ransmitter EPIRB : (mergency 3osition ,ndicating 5adio %eacon PLB : 3ersonal /ocator %eacon RCC : 5escue &oordination &enters MCC : 0ission &ontrol &enters LUT : /ocal 8ser 7erminals COSPAS/SARSAT – System Principle Figure 1
86(5¶6+$1'%22. Page 13 Jun 30/02 C. The distress frequencies There are several advantages to using the 406 MHz frequency : – Worldwide coverage: locating is not only possible in real-time within a radius of 2,500 km around the station, but also in global mode outside this zone since the satellites memorize the messages on the 406 MHz frequency. Location process uses Doppler effect. – Locating accuracy: 2 km as opposed to 10 to 15 km in the 121.5 MHz or 243 MHz frequencies. It should be noted however that the 406 MHz beacons also transmit 121.5 MHz and 243 MHz signals which enable the final approach of the rescue teams in homing mode. – Information reliability: the structure of the digital signal transmitted by these beacons makes it possible to be sure that there is actually a distress situation, as well as to identify automatically the mobile in distress which is vital for rescue operations. – Unique identification: each beacon has it’s own identification information. D. ELTA and the COSPAS-SARSAT system (1)406 MHz distress beacons: These beacons transmit to the satellites a digital message which identifies them and gives their position, as well as a signal that facilitates the final approach of the rescue teams. They are suitable for all types of use (maritime, aeronautical and land) and can, depending on the model, be activated manually or automatically. They are designed to function in the most extreme conditions with a high degree of reliability. (2)Satellites low earth orbiting: At least four satellites are permanently operational. Since their orbit is near-polar, in the worst case every point on Earth is overflown every two hours. In a ground station's visibility zone, the satellites directly transmit the messages captured in that zone, and also any messages from the zones not covered that they have stored in memory. (3)Geo-stationary satellites are now available in the system and offer faster detection capability (close to 5 minutes) but require a GPS receiver to supply location that is sent via C/S message. (4)Ground reception stations: The zone effectively covered (or visibility zone) is a circle with a radius of 2,500 km around the station. These stations receive (via the satellites) and process, in real time, the messages from the beacons activated in their visibility zone and, in batch mode, the messages from the 406 MHz beacons activated outside that zone and memorized by the satellites. Automatic processing of the 406 MHz digital messages allows the beacons to be located and the carrier mobile to be identified.
86(5¶6+$1'%22. Page 14 Apr 30/03 2. GENERAL DETAILS OF THE ELT ADT 406 AF / AP A. Purpose of the ELT ADT 406 AF / AP (Ref. Fig. 2) The ELT ADT 406 AF / AP consists of a beacon that incorporates means of attachment. The ELT ADT 406 AF / AP is designed to transmit a digital distress signal to satellites that are part of the COSPAS/SARSAT SYSTEM. These satellites transmit the captured signal to the reception stations on the ground. This signal is transmitted on the 406.028 MHz frequency and is used to precisely locate and identify the ELT ADT 406 AF / AP. It also transmits a 121.5 MHz and 243 MHz signal to facilitate the final approach of the distress scene (homing). It can be triggered manually or automatically by means of an acceleration sensor (G.switch in accordance to EUROCAE ED-62 standard). This ELT meets the latest JAR OPS and ICAO recommendations. Any encoding protocol defined by COSPAS/SARSAT can be used with ELT ADT 406 AF / AP including country code assignation. ELT ADT 406 AF / AP- Presentation Figure 2 Metalic strap
86(5¶6+$1'%22. Page 15 Apr 30/03 ELT ADT 406 AF /AP - Overall Dimensions (Other Back Up Antenna Configuration Are Available) Figure 3 205 [8.07]74 [2.91]
86(5¶6+$1'%22. Page 16 Apr 30/03 B. Characteristics (Ref. Fig. 3) (1)Approvals ADT 406 AF / AP is COSPAS/SARSAT approved (TAC # 131, dated 15 July 2002, see Appendix A page 1) ADT 406 AF / AP meets EUROCAE ED62 standard ADT 406 AF / AP is JTSO 2C91a and JTSO 2C126 (JTSO N° F.O. 089 dated 03 Oct. 2002, see Appendix A page 2) ADT 406 AF / AP is TSO C91a and TSO C126 (TSO letter dated Febuary 24 2003, see Appendix A page 4) (2)Physical characteristics Height : 74 mm Width : 160 mm Length : 234 mm (without back up antenna) Weight : 1.6 kg maximum Back up antenna lenght : 200 mm max (3)General characteristics (a)External antenna – Omnidirectionnal three-frequency antenna 50Ω access, – conform to COSPAS/SARSAT and EUROCAE ED-62 specifications. (b)Power supply High energy batteries (2 series-connected packs), activable for 5 years. Autonomy 24 hours on 406.028 MHz and greater than 60 hours at -20°C on 121.5&243 MHz. – Voltage : 6 VDC, – capacity : 10.5 A/h, – ELTA type number :00E64191, – lithium manganese dioxide (solid cathode), – battery servicing kit available: 02N60052 kit for one ELT 02N60053 kit for 10 ELT (c)Radio-electrical characteristics 1 406 MHz satellite transmitter – Frequency : 406.028 MHz, – transmitter power : 5 W, – modulation : "L" two-phase, – transmission recurrence : 50 s, – transmission duration : 440 or 520 ms.
86(5¶6+$1'%22. Page 17 Apr 30/03 2 Associated homing transmitter – Frequency : 121.5 MHz/243 Mhz or 121.5 MHz (selectable), – 121.5 MHz transmitter power : > 100 or 200 mW (selectable), – 243 MHz transmitter power : > 100 or 200 mW (selectable), – modulation : AM (3K20A3X type) from, 1600 Hz to 300 Hz, up to four periods per second, – antenna gain : > 1 dBi. (d)Environment characteristics – Operating temperatures : -20°C to +55°C, – storage temperatures : -55°C to +85°C. (e)Miscellaneous characteristics – Automatic activation level in accordance with EUROCAE ED-62 (internal G-switch, see Appendix A page 6). Activation direction is selectable (4 possibe directions), – color : orange in conformity with the international distress signal, – self-test : transmission of one burst modulated with inverted frame synchronization and 5s transmission of 121.5 MHz , automation to off position (on remote control panel), – any COSPAS/SARSAT protocol available, . ELT S/N . A/C operator designator and S/N . A/C 24 bits address . A/C nationality and registration marking (recommended) . Test – any country code available, – can operate in short or long C/S message. For long message, location data (from on board GPS as exemple) is received from A/C data bus through an optional interface module, P/N 01N6593(x), – C/S identification stored in a transferable module to ease maintenance on ELT, – dual antenna access. Primary for external antenna and secondary for permanent back up antenna in case of failure detection on primary access.
86(5¶6+$1'%22. Page 18 Jun 30/02 3. DESCRIPTION OF THE ELT ADT 406 AF / AP AND OF THE AIRCRAFT COMPONENTS A. General description (1)The ELT ADT 406 essentially consists of : – an ADT 406 AF / AP beacon transmitter – a back up antenna, – labels, – an activation / identification module (2)The ELT ADT 406 AF / AP basic aircraft components consists of : – a remote control unit, – an external antenna. B. Detailed description (Ref. Fig. 7) (1)The ADT 406 AF / AP beacon The ADT 406 AF / AP beacon mainly consists of : – a power supply module, – an electronic assembly, – a mechanical assembly. The front face of the electronic assy is equipped with the following components : – a REMOTE CONTROL electrical SUB-D high density 15 pins female connector (7) for connecting up to the aircraft remote control panel or programming tools, – a BACK UP ANT. TNC female connector (10) for connecting up the antenna, – an EXT. ANT. BNC female connector (6) for connecting up the external antenna, – an ARMED/OFF/ON lockable toggle switch (9) for activating the beacon, – a TX indicator light (8) indicating beacon activation (real distress and self-test).
86(5¶6+$1'%22. Page 19 Apr 30/03 (2)The labels (a)Identification label This label indicates : – beacon name, manufacturer details, – the condition in which the beacon may be used (warning), – approval number, identification, part number, service bulletin, serial number and conditions on the use of the beacon. (b)Connectors use label This label gives indication on the electronic front face connectors use. (X)JTSO-2C91a & 2C126
86(5¶6+$1'%22. Page 20 Apr 30/03 (c)Connectors location label This label indicates the location of the connectors on the front face of the electronic assy. (d)Identification label This label indicates the axis according to which the ELT ADT 406 AF / AP must be installed on the aircraft (see paragraph. 4.B.) for automatic activation (G-switch). It is fixed to the activation / identification module. (e)Batteries label This label indicates the batteries expiry date (next battery servicing). Homing pwr xx dBmHoming powerselectionOfficial 15 Hex.
86(5¶6+$1'%22. Page 21 Jun 30/02 (3)ELT ADT 406 AF / AP aircraft components (a)Remote control unit The remote control unit integrated in the aircraft cockpit consists of : – a RESET/TEST pushbutton, – an ELT ON indicator light, – a two-position ON/ARMED switch with safety cover (flip guard). The safety cover forces the switch to ARMED position. This switch must always remain in this position, except in the case of manual distress triggering. The beacon is integrated in the aircraft as far aft as possible and so it must be connected to the remote control unit. This remote control unit enables beacon operation to be forced to ON, to be tested (TEST) or shutdown and restore in standby or ARMED mode (RESET) in the event of an untimely triggering of the ELT, from the aircraft cockpit. (b)External antenna An external antenna is recommended to be installed on the fuselage of the aircraft to maximize transmission of the distress signal to the satellites as required by JAR OPS. The cable lenght should remain as short as possible in order to keep RF losses as close as possible to 0.5 to 1 dB at each frequencies (121.5/243/406.028 MHz) and to reduce the probability of cable damage during the crash.
86(5¶6+$1'%22. Page 22 Jun 30/02 4. INSTALLATION OF THE ELT ADT 406 AF / AP A. General System security and reliability obviously depends on the standard of installation. In order to ensure installation of the highest standard, the installation operations must be : – performed in conformity with this document, – performed in compliance with the current regulations, – performed by qualified personnel, – performed so that : . the aircraft's structural integrity is not affected, . it will not hinder the pilot in normal position, . it will not cause any damage in the event of an accident, . it will not prevent or modify operation of the other safety systems. If in doubt, contact the aircraft manufacturer or its representative, – inspected by representative authority. B. Installation of the beacon on the aircraft (Ref. Fig. 4) The beacon shall be installed in the rear of the aircraft in order to maximize the probability of ELT survival in case of crash. The activation / identification module DIRECTION OF FLIGHT must be parallel with the aircraft flight axis as indicated by the beacon's label. The activation / identification module direction and the A/C forward/aft directions must be respected to ensure correct acceleration sensor (G.switch) operation (See Fig. 4). NOTE : An angle of up to ± 8° from the aircraft flight axis could be allowed. An angle of up to ± 3° from the aircraft horizontal axis could be allowed. Tolerances on the Axis for Installation of the ELT ADT 406 AF / AP Figure 4
86(5¶6+$1'%22. Page 23 Jul 30/03 The beacon can be installed in any position (normal, upside down, right side, left side) with respect with the G-Switch activation direction stated on figure 4. The activation / identification assy of the beacon can be installed in four positions. Three alignment pins on the beacon board allow to set it in the required position. A cap is installed in one of the four holes of the activation / identification assy who is unused. 7KLVFDSVKDOOEHDVVLJQHGXSRQWKHLQLWLDOLQVWDOODWLRQDQGZLOONHHSWKLVSRVLWLRQLQPHPRU\IRUIXUWKHUEHDFRQUHSODFHPHQW After correct installation of the Activation/Identification module, it shall be attached to the A/C by means of the metalic strap in order to keep on board A/C the Cospas-Sarsat identification information related to the installed ELT. So these information will remain in the A/C upon transmitter exchange (for overhaul process as exemple). Unstowed objects must be not able to impact the beacon. Attach the beacon to the fuselage of the aircraft by means of four M4 bolts. Four 5 mm diameter holes at the corners of a 210 mm x 45 mm rectangle are drilled in the beacon. Particular care must be taken with this attachment. Standard industry means must be used to lock the screws. Use flat washer in order to avoid paint damage. &$87,21 7KLV(/7VKDOOEHIL[HGRQWKHSULPDU\$&VWUXFWXUHIRUFRUUHFW*6ZLWFKRSHUDWLRQGXULQJWKHFUDVK
86(5¶6+$1'%22. Page 24 Apr 30/03 The figure 5 shows the drilling pattern dimensions and determine the required area to access to the beacon controls and connectors. Installation of the ELT ADT 406 AF / AP - Drilling Pattern Dimensions Figure 5 C. External antenna installation ELTA recommend to use P/N 25988 (antenna model 2624-82 manufactured by CHELTON) Other external antenna may be used but at least shall be approved by Cospas-Sarsat and shall not have a capacitive input. Contact ELTA or one of its approved agent to chek if the antenna can be used with this ELT model. The external antenna must be installed on the upper part of the fuselage, as far aft as possible. Particular care must be taken with this attachment. Standart industry means must be used to lock the screws. The contact surface should be reinforced to prevent the antenna from tearing away at high speeds. The cable used shall be of a high quality with very low losses. RG 142 cable type is recommended with a length lower than 2 meters to keep losses close to 0.5 dB. Connect the connector to the antenna and to the EXT. ANT. access on ELT, and install the coaxial cable. This cable must be fixed to rigid aircraft structure all along its routing, and it should be as short as possible to avoid Radio Frequency losses and/or cable destruction in case of crash. D. Remote control unit installation The ELT ADT 406 AF / AP can be remotely controlled by using a remote control panel installed in the cockpit of the aircraft. The maximum length of this link is 200 meters and requires no grounded cable. The link requires 4 wires.
86(5¶6+$1'%22. Page 25 Apr 30/03 The following simplified diagram shows the wiring between the ELT ADT 406 AF / AP and its peripherals : – The Remote Control Panel (in cockpit) identified as "RCP", – the external antenna noted as "EA", – the back up antenna noted as "BA". The EA is connected to the ELT ADT 406 AF / AP BNC female connector (5). The BA is connected to the ELT ADT 406 AF / AP TNC female connector (1). The RCP is connected to the ELT ADT 406 AF / AP high density 15 pins female Sub-D connector (3). ELTA recommend to use P/N 16243 (or Type 8525-16R 14SN- or equivalent) for RCP connector and reference 8635 15 P (Sub-D HD plug) + 8635 4100 (pins) from FCI manufacturer or equivalent. A three position guarded switch (2) controls the ELT ADT 406 AF / AP. A red indicator (4) displays the ELT ADT 406 AF / AP state. ADT 406 AF / AP Beacon Installation Figure 6
86(5¶6+$1'%22. Page 26 Jun 30/02 E. Installation and configuration of the beacon (Ref. Fig. 5) &$87,2172%(23(5$7,21$/7+(%($&216+$//%(,1$50('326,7,2121&(,7+$6%((1&255(&7/<,167$//('Connect the antenna cable to the EXT. ANT. connector. Connect the back up antenna to ELT. Switch the Remote Control ON/ARMED lockable toggle switch to "ARMED" on remote control panel. Connect the remote control unit cable to the REMOTE CONTROL connector on ELT and lock it. Connect the remote control unit cable rear of the remote control panel and lock it. Switch the Beacon ARMED/OFF/ON lockable toggle switch to ARMED (pull and slide), the system is ready for use. &$87,21$66221$67+(%($&21,6,1$50(',7&$1%($8720$7,&$//<$&7,9$7('%<7+(,17(51$/*6:,7&+
86(5¶6+$1'%22. Page 27 Jun 30/02 5. UTILIZATION OF THE ELT ADT 406 AF / AP (Ref. Fig. 7) &$87,21,17+((9(172)817,0(/<%($&21$&7,9$7,216+87'2:17+(%($&21$1',1)2507+(&/26(676($5&+$1'5(6&8(6$525$,53257&21752/72:(5,00(',$7(/<The ELT ADT 406 can be activated in two modes : – automatic when the acceleration sensor is triggered, – manual. A. Automatic activation The acceleration sensor has detected an impact sufficient to trigger it. The indicator light (8) and the aural indicator indicate beacon activation. Otherwise do not do anything and leave the beacon in operation until the rescue team arrives. Upon automatic activation the ELT enter directly in a waiting condition for about 30s (self test is not performed). This state is displayed by flasing on indicator light (8) 1.75s ON, 0.25s OFF. :$51,1* ,QFDVHRIIDOVHDFWLYDWLRQWKHRSHUDWRUVKDOOVKXWGRZQWKH(/7DVGHVFULEHGLQ&$IWHUWKLVGHOD\WKH(/7ZLOOWUDQVPLWDFWXDOGLVWUHVVVLJQDOVRQWKHWKUHHDYDLODEOHVGLVWUHVVIUHTXHQFLHV B. Manual activation There are two cases in which a distress signal may be triggered manually : – the acceleration sensor (G.switch) has not been triggered but a distress signal must be sent (injured passengers, aircraft out of operation ...), – the aircraft is on the ground and must be evacuated. (1)First case, from the Remote Control Raise the safety cover (guard) on the remote control unit and place the switch in the ON position (lever upwards). An automatic self-test sequence is performed. Then the indicator light (8) and the aural indicator indicate beacon activation. This signal is permanently displayed on the Remote Control LED. Do not do anything and leave the beacon in operation until the rescue team arrives. (2)Second case, from the beacon Place the beacon switch (9) in the ON position (pull and slide). An automatic self-test sequence is performed. Then the beacon enter in a waiting condition for about 30s. This state is displayed by flashing on indicator light (8) 1.75 s ON, 0.25 s OFF. This delay will avoid unwanted activation (false manoeuvre). Then the indicator light (8) and the aural indicator indicate beacon activation. The actual distress signal is transmitted. This state is displayed by flashing on indicator light : 0.5 s ON, 0.5 s OFF.
86(5¶6+$1'%22. Page 28 Apr 30/03 C. Beacon shutdown In the event of a false manoeuvre or untimely operation, shutdown the beacon. The beacon is shutdown by pressing the RESET/TEST pushbutton on the remote control unit. This control is not active during the self test sequence or if the ON/ARMED switch is in ON position. NOTE : Stopping distress signal transmission by means of the remote control unit does not switch the beacon OFF. It is restored in ARMED mode. Acknowledgment of the control is displayed by 2 short blink on LED and buzzer. &$87,217+(%($&210867%(6+87'2:1%()25($1<0$,17(1$1&(23(5$7,216$5(3(5)250('7+(%($&210867%(&203/(7(/<6+87'2:1%()25(,7,65(029('$1',76$50('2))2172**/(6:,7&+6+$//%(,12))326,7,21  D. Beacon self-test &$87,217+(6(/)7(676+$//%(3(5)250(':,7+,17+(),567012)$1<+285%(&$86(7+((/7,66(1',1*0+=6,*1$/)256'85,1*7+,6352&(66/,0,7$7,212))$/6($/(57The ELT ADT 406 AF / AP is designed to perform a self-test, from the remote control unit, or as soon as the beacon is started up manually. Actual test transmission on 121.5 MHz for 5 s can be listened on any VHF receiver. (1)Self-test on the beacon &$87,217+,66(/)7(67352&(666+$//127%(,17(5837(',)7+,6352&(66,6127&203/(7()25$1<5($6213(5)250$1(:&203/(7(6(/)7(67Place the beacon’s ARMED/OFF/ON toggle switch (9) in ON position. After two short blinks there is a delay of approximately 3 seconds, then the indicator light (8) comes ON and the buzzer sounds for approximately 6 seconds. After a brief blink the self-test report is display : – 10 s permanent illumination of the indicator light (8) for correct operation, – 10 s blinking condition of the indicator light (8) for failure detection. Blinking rate indicates the failure source detection as follow : . 125 ms ON, 125 ms OFF (Frequency 4 Hz), ELT Check Sum failure (software problem) . 250 ms ON, 250 ms OFF (Frequency 2 Hz), ELT power failure (UHF and/or VHF) . 500 ms ON, 500 ms OFF (Frequency 1 Hz), Ext. Antenna connection failure or signal identification missing.
86(5¶6+$1'%22. Page 29 Apr 30/03 Then the beacon enter in a waiting condition for 30 s (rate : 1.75s ON; 0.25s OFF). During this state return the switch (9) to ARMED position. &$87,2123(5$7256+$//6:,7&+2))25$50('7+((/7:,7+,16$)7(56(/)7(675(325772$92,'5($/',675(6675$160,66,21(2)Self-test by means of the remote control unit The beacon’s ARMED/OFF/ON toggle switch (9) must be in ARMED position. The Remote Control ARMED/ON must be in ARMED position. Press the RESET/TEST pushbutton until the two acknowledgment blinks on LED. Then, after a delay of approximately 6 seconds, the self-test report is displayed on the Remote Control Unit LED : – 10 s permanent illumination for correct operation, – 10 s blinking condition for failure detection. Blinking rate indicates the failure source detection as follow : . 125 ms ON, 125 ms OFF (Frequency 4 Hz), ELT Check Sum failure (software problem) . 250 ms ON, 250 ms OFF (Frequency 2 Hz), ELT power failure (UHF and/or VHF) . 500 ms ON, 500 ms OFF (Frequency 1 Hz), Ext. Antenna connection failure or signal identification missing. NOTE: On the beacon, after the two short blinks, the indicator light (8) comes ON and the buzzer sounds during 6 seconds. This is the self-test process. Then the self-test report is indicated as it is done for the Remote Control Unit LED &$87,217+((/76+$//%(,1$50('326,7,21,)1275(027(&21752/:,//12723(5$7(7(675(6(721
86(5¶6+$1'%22. Page 30 Apr 30/03 6. MAINTENANCE OF THE ELT ADT 406 AF / AP A. Beacon self-test The manufacturer recommends that a beacon self-test should be performed regularly. The highest rate is one per day. Normally this task is added to other periodic maintenance task such a “A” check. In all events the user must comply with the applicable regulations in the country concerned governing the self-test period. The self-test must only be performed when the order to do so is given or by the competent authorities. A higher rate of self-test will reduce the 5 years battery servicing. &$87,217+(6(/)7(67352&('85(3$5$*5$3+'0867%(5(63(&7('72$92,'817,0(/<%($&21$&7,9$7,21 B. Maintenance periodicity table Periodicity Operations Operator 5 years Replacement of batteries ELTA or approved agent/airline 5 years General overhaul in specialized workshop ELTA or approved agent/airline C. Batteries replacement &$87,217+(%$77(5<3$&.6+$//%($33529('%<(/7$,)27+(53$&.$5(86('(/7$:,//&$1&(/:$55$17<$1':,//5()86($1<5(63216,%,/,7<217+(352'8&723(5$7,210,6)81&7,21&$87,217+(%$77(5,(686('&$1127%(5(&+$5*(''212775<7223(1255(&+$5*(7+(0 Next battery servicing date is indicated on a label stuck on the back face of ADT 406 AF / AP. The old batteries must be replaced with new batteries of a model approved by ELTA P/N 02N60052 (kit for battery servicing for one ELT) or 02N60053 (kit for battery servicing for ten ELTs). ELTA recommends that the ELT ADT 406 AF / AP should undergo a general overhaul on its test and programming bench at this occasion. Refer to CMM 25-60-10 for detail of operation.
86(5¶6+$1'%22. Page 31 Jun 30/02 D. Batteries discarding The batteries must be discarded in compliance with the applicable regulations in the country concerned. NOTE : The type of battery used is not dangerous for the environment provided that it is completely discharged. Contact ELTA for getting additional discarding information. E. Test to do at the time of a beacon return in workshop Perfoms the following tests described in CMM 25-60-10 : – visual check, – test of acceleration sensor automatic triggering, – functional test of ADT 406 AF / AP beacon, – RF test on the operational frequencies 121.5 – 243 – 406 MHz.
86(5¶6+$1'%22. Page 32 Apr 30/03 1 – BACK UP ANTENNA (BASIC CONFIGURATION) 2 – FRONT FACE 3 – ACTIVATION/IDENT ASSY 4 – BACK FACE 5 – MACHINED SECTION 6 – EXT. ANT. BNC CONNECTOR (FEMALE) 7 – REMOTE CONTROL CONNECTOR (SUB-D HD FEMALE 15 PINS) 8 – TX LED 9 – ARMED/OFF/ON TOGGLE AND GUARDED SWITCH 10 – BACK UP ANT. TNC CONNECTOR (FEMALE) 11 – METALIC STRAP ELT ADT 406 AF / AP – Detailed Description Figure 7
Appendix A page 1 Apr 30/03COSPAS-SARSAT TYPE APPROVAL CERTIFICATE
Appendix A page 2 Apr 30/03JTSO 2C91a AND JTSO 2C126 APPROVAL
Appendix A page 3 Apr 30/03
Appendix A page 4 Apr 30/03 TSO C91a AND TSO C126 APPROVAL
Appendix A page 5 Apr 30/03
Appendix A page 6 Jun 30/02Crash Sensor Response Curve
/2*%22.Appendix B page 1 Jun 30/02FACTORY SETTING NEXT BATTERY SERVICING ……../……………. (MM/YYYY)
/2*%22.Appendix B page 2 Jun 30/02FACTORY SETTING
/2*%22.Appendix B page 3 Jun 30/02ENCODING UPDATE FORM REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: ……/……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool.
/2*%22.Appendix B page 4 Jun 30/02ENCODING UPDATE FORM REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool.
/2*%22.Appendix B page 5 Jun 30/02ENCODING UPDATE FORM REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool.
/2*%22.Appendix B page 6 Jun 30/02ENCODING UPDATE FORM REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool.
/2*%22.Appendix B page 7 Jun 30/02ENCODING UPDATE FORM REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool.
/2*%22.Appendix B page 8 Jun 30/02ENCODING UPDATE FORM REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY: ELT SERIAL NUMBER: PROTOCOL: ELT S/N A/C OP-DESIGNATOR + S/N A/C 24 Bit Address A/C REG. MARK TEST C/S 15 HEX: SIMPLIFIED DEC: A/C MSN: A/C OR A/P TYPE: FINAL OPERATOR: CONTACT (PHONE, email…): ISSUED BY: DATE: …… /……/…… …… (MM/DD/YYYY) SIGNATURE AND STAMP: NOTE : Attach the encoding update sheet issued from the ELTA encoding tool.
/2*%22.Appendix B page 9 Jun 30/02MAINTENANCE TASKS FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool.
/2*%22.Appendix B page 10 Jun 30/02MAINTENANCE TASKS FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool.
/2*%22.Appendix B page 11 Jun 30/02MAINTENANCE TASKS FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool.
/2*%22.Appendix B page 12 Jun 30/02MAINTENANCE TASKS FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool.
/2*%22.Appendix B page 13 Jun 30/02MAINTENANCE TASKS FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool.
/2*%22.Appendix B page 14 Jun 30/02MAINTENANCE TASKS FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR: TYPE OF MAINTENANCE: BATTERY SERVICING INSPECTION REPAIR RF TEST TASK DESCRIPTION: NEXT BATTERY SERVICING: ……/……… … (MM/YYYY) DATE: …… /……/…… …… (MM/DD/YYYY) REPAIR STATION: SIGNATURE AND STAMP: NOTE : Attach the RF test sheet issued from the ELTA test tool.

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