FCC ID: LYJADT406 ELT 406 MHz (Emergency Locator Transmitter)

 

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) 14 Place Marcel Dassault 31702 BLAGNAC France www.elta.fr Documentation P/N: 02E62356 Rev C Initial issue: Jun 30/02 Title Page Jul 30/03

86(56+$1%22. LIST OF UPDATES UPDATE No. A B C ISSUE INITIAL INSERTION DATE BY Jun 30/02 Apr 30/03 Jul 30/03 C.CRESP E.LABRIFFE E.LABRIFFE UPDATE No. ISSUE INSERTION DATE BY Page 1 Apr 30/03

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86(56+$1%22. LIST OF EFFECTIVE PAGES CHAPTER/

SECTION PAGE DATE CHAPTER/

SECTION PAGE DATE 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 Appendix A Appendix B 1 2 3 4 5 6 1 2 3 4 5 6 7 8 9 10 11 12 13 14 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 Page 3 Apr 30/03

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86(56+$1%22. TABLE OF ILLUSTRATIONS Figure 1 : COSPAS/SARSAT - System Principle Figure 2 : ELT ADT 406 AF / AP Presentation Figure 3 : ELT ADT 406 AF / AP Dimensions (Basic Configuration) Figure 4 : Tolerances on the Axis for Installation of the ELT ADT 406 AF / AP Figure 5 : Installation of the ELT ADT 406 AF / AP - Drilling Pattern Dimensions Figure 6 : ELT ADT 406 AF / AP Installation - Wiring Diagram Figure 7 : ELT ADT 406 AF / AP - Detailed Description Page 12 14 15 22 24 25 32 Page 5 Jun 30/02

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86(56+$1%22. LEADING PARTICULARS

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86(56+$1%22. TABLE OF CONTENTS 1. INTRODUCTION TO THE COSPAS-SARSAT SYSTEM A. The COSPAS-SARSAT system B. System organization C. The distress frequencies D. ELTA and the COSPAS-SARSAT system 2. GENERAL DETAILS OF THE ELT ADT 406 AF / AP A. Purpose of the ELT ADT 406 AF / AP B. Characteristics 3. DESCRIPTION OF THE ELT ADT 406 AF / AP AND OF THE AIRCRAFT COMPONENTS A. General description B. Detailed description 4. INSTALLATION OF THE ELT ADT 406 AF / AP A. General B. Installation of the beacon on the aircraft C. External antenna installation D. Remote control unit installation E. Installation and configuration of the beacon 5. UTILIZATION OF THE ELT ADT 406 AF / AP A. Automatic activation B. Manual activation C. Beacon shutdown D. Beacon self-test 6. MAINTENANCE OF THE ELT ADT 406 AF / AP A. Beacon self-test B. Maintenance periodicity table C. Battery replacement D. Battery discarding E. Test to do at the time of a beacon return in workshop PAGE 11 11 11 13 13 14 14 16 18 18 18 22 22 22 24 24 26 27 27 27 28 28 30 30 30 30 31 31 Page 9 Jun 30/02

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86(56+$1%22. 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 equipments 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 Page 11 Jun 30/02

86(56+$1%22. Legend :

ELT : (mergency /ocator 7ransmitter EPIRB : (mergency 3osition ,ndicating 5adio %eacon PLB : 3ersonal /ocator %eacon RCC : 5escue &oordination &enters

: 0ission &ontrol &enters MCC LUT : /ocal 8ser 7erminals COSPAS/SARSAT System Principle Figure 1 Page 12 Jun 30/02

86(56+$1%22. 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 its 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. Page 13 Jun 30/02

86(56+$1%22. 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. Metalic strap ELT ADT 406 AF / AP- Presentation Figure 2 Page 14 Apr 30/03

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4 7 ELT ADT 406 AF /AP - Overall Dimensions

(Other Back Up Antenna Configuration Are Available) Figure 3 Page 15 Apr 30/03

86(56+$1%22. 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 50W 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 -20C on 121.5&243 MHz. Voltage capacity ELTA type number lithium manganese dioxide (solid cathode), battery servicing kit available: 02N60052 kit for one ELT 02N60053 kit for 10 ELT

: 6 VDC,

: 10.5 A/h,

:00E64191,

(c)Radio-electrical characteristics 1 406 MHz satellite transmitter Frequency transmitter power modulation transmission recurrence : 50 s, transmission duration

: 406.028 MHz,

: 5 W,

: "L" two-phase,

: 440 or 520 ms. Page 16 Apr 30/03

86(56+$1%22. 2 Associated homing transmitter Frequency 121.5 MHz transmitter power 243 MHz transmitter power modulation

: 121.5 MHz/243 Mhz or 121.5 MHz (selectable),

: > 100 or 200 mW (selectable),

: > 100 or 200 mW (selectable),

: AM (3K20A3X type) from, 1600 Hz to 300 Hz, up to four periods per second, antenna gain

: > 1 dBi.

(d)Environment characteristics Operating temperatures storage temperatures

: -20C to +55C,

: -55C to +85C.

(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 self-test

orange in conformity with the international distress signal, 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. Page 17 Apr 30/03

86(56+$1%22. 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). Page 18 Jun 30/02

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(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. JTSO-2C91a & 2C126

(X)

(b)Connectors use label This label gives indication on the electronic front face connectors use. Page 19 Apr 30/03

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(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. Homing power selection Homing pwr xx dBm Official 15 Hex.

(e)Batteries label This label indicates the batteries expiry date (next battery servicing). Page 20 Apr 30/03

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(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. Page 21 Jun 30/02

86(56+$1%22. 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 Page 22 Jun 30/02

86(56+$1%22. 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. 7KLVFDSVKDOOEHDVVLJQHGXSRQWKHLQLWLDOLQVWDOODWLRQDQGZLOONHHSWKLVSRVLWLRQLQPHPRU\IRU IXUWKHUEHDFRQUHSODFHPHQW 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.

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86(56+$1%22. 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 C. External antenna installation Figure 5 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. Page 24 Apr 30/03

86(56+$1%22. 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.

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86(56+$1%22. E. Installation and configuration of the beacon (Ref. Fig. 5)

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%((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.

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86(56+$1%22. 5. UTILIZATION OF THE ELT ADT 406 AF / AP (Ref. Fig. 7)

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,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.

:$51,1* ,QFDVHRIIDOVHDFWLYDWLRQWKHRSHUDWRUVKDOOVKXWGRZQWKH(/7DVGHVFULEHGLQ&$IWHU WKLVGHOD\WKH(/7ZLOOWUDQVPLWDFWXDOGLVWUHVVVLJQDOVRQWKHWKUHHDYDLODEOHVGLVWUHVVIUHTXHQFLHV 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. Page 27 Jun 30/02

86(56+$1%22. 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.

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/,0,7$7,212))$/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

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&203/(7(6(/)7(67 Place the beacons 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. Page 28 Apr 30/03

86(56+$1%22. 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.

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(2)Self-test by means of the remote control unit The beacons 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

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,)1275(027(&21752/:,//12723(5$7(7(675(6(721 Page 29 Apr 30/03

86(56+$1%22. 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.

&$87,217+(6(/)7(67352&(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

&$87,217+(%$77(5<3$&.6+$//%($33529(%<(/7$,)27+(53$&.$5(86((/7$

:,//&$1&(/:$55$17<$1:,//5()86($1<5(63216,%,/,7<217+( 3528&723(5$7,210,6)81&7,21

&$87,217+(%$77(5,(686(&$1127%(5(&+$5*(212775<7223(125 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. Page 30 Apr 30/03

86(56+$1%22. 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. Page 31 Jun 30/02

86(56+$1%22. X*X 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 Page 32 Apr 30/03

COSPAS-SARSAT TYPE APPROVAL CERTIFICATE Appendix A page 1 Apr 30/03

JTSO 2C91a AND JTSO 2C126 APPROVAL Appendix A page 2 Apr 30/03

Appendix A page 3 Apr 30/03

TSO C91a AND TSO C126 APPROVAL Appendix A page 4 Apr 30/03

Appendix A page 5 Apr 30/03

Crash Sensor Response Curve Appendix A page 6 Jun 30/02

/2*%22. FACTORY SETTING NEXT BATTERY SERVICING

../. (MM/YYYY) Appendix B page 1 Jun 30/02

/2*%22. FACTORY SETTING Appendix B page 2 Jun 30/02

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 3 Jun 30/02

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 4 Jun 30/02

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 5 Jun 30/02

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 6 Jun 30/02

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 7 Jun 30/02

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 8 Jun 30/02

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 9 Jun 30/02

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 10 Jun 30/02

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 11 Jun 30/02

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 12 Jun 30/02

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 13 Jun 30/02

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 14 Jun 30/02

 

 

86(56+$1%22. 86(56+$1%22.

,1&/8,1*,167$//$7,210$18$/

$1/2*%22. SERIAL NUMBER LABEL

(0(5*(1&</2&$72575$160,77(5 02(/$7$3

,17+(&263$66$56$76<67(0

Issued by

(/7$

) 14 Place Marcel Dassault 31702 BLAGNAC France www.elta.fr Documentation P/N: 03E61013 Rev B Initial issue: Feb 15/03 Title Page Apr 17/03

86(56+$1%22. LIST OF UPDATES UPDATE No. ISSUE INSERTION DATE BY UPDATE No. ISSUE A B INITIAL Feb 15/03 Apr 17/03 E.LABRIFFE E.LABRIFFE INSERTION DATE BY Page 1 Apr 17/03

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86(56+$1%22. 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 33 34 Apr 17/03 Apr 17/03 BLANK Apr 17/03 BLANK Feb 15/03 BLANK Feb 15/03 BLANK Feb 15/03 BLANK Feb 15/03 Feb 15/03 Feb 15/03 Apr 17/03 Apr 17/03 Apr 17/03 Apr 17/03 Apr 17/03 Feb 15/03 Apr 17/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Apr 17/03 Feb 15/03 Apr 17/03 Apr 17/03 Apr 17/03 Apr 17/03 Feb 15/03 Feb 15/03 Apr 17/03 Appendix A Appendix B 1 2 3 4 5 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Feb 15/03 Page 3 Apr 17/03

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86(56+$1%22. TABLE OF ILLUSTRATIONS Figure 1 : COSPAS/SARSAT - System Principle Figure 2 : ELT ADT 406 AP Presentation Figure 3 : ELT ADT 406 AP Dimensions (Basic Configuration) Figure 4 : Tolerances on the Axis for Installation of the ELT ADT 406 AP Figure 5 : Installation of the ELT ADT 406 AP - Drilling Pattern Dimensions Figure 6 : ELT ADT 406 AP Installation - Wiring Diagram Figure 7 : ELT ADT 406 AP - Detailed Description Page 12 14 15 22 24 26 34 Page 5 Feb 15/03

86(56+$1%22. PAGE INTENTIONALLY LEFT BLANK Page 6 BLANK

86(56+$1%22. LEADING PARTICULARS

&$87,21 7+,675$160,77(5,6$87+25,=()2586(21/<85,1*6,78$7,2162)*5$9(

$1,00,1(17$1*(5

&$87,21 ,7,6,03(5$7,9(7+$7($&+%($&212:1(55(*,67(567+(,5%($&21&217$&7

(/7$25$33529($*(17722%7$,17+(,1)250$7,215(/$7,9(727+,6 5(*,675$7,21

&$87,21 7+(%($&210867,03(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%((1352*5$00(,7,6*(1(5$/<$66,*1(72$1

$,5&5$)71$0($1,(17,),&$7,21,)7+,6%($&21,686(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*2586,1*7+,6(48,30(177+(9$/,,7<2)7+(,1)250$7,21 217+(%($&21/$%(/0867,03(5$7,9(/<%(&+(&.( Page 7 Feb 15/03

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86(56+$1%22. TABLE OF CONTENTS 1. INTRODUCTION TO THE COSPAS-SARSAT SYSTEM A. The COSPAS-SARSAT system B. System organization C. The distress frequencies D. ELTA and the COSPAS-SARSAT system 2. GENERAL DETAILS OF THE ELT ADT 406 AP A. Purpose of the ELT ADT 406 AP B. Characteristics 3. DESCRIPTION OF THE ELT ADT 406 AP AND OF THE AIRCRAFT COMPONENTS A. General description B. Detailed description 4. INSTALLATION OF THE ELT ADT 406 AP A. General B. Installation of the beacon on the aircraft C. External antenna installation D. Remote control unit installation E. Installation and configuration of the beacon 5. UTILIZATION OF THE ELT ADT 406 AP A. Automatic activation B. Manual activation C. Beacon shutdown D. Beacon self-test 6. MAINTENANCE OF THE ELT ADT 406 AP A. Beacon self-test B. Maintenance periodicity table C. Battery replacement D. Battery discarding E. Test to do at the time of a beacon return in workshop PAGE 11 11 11 13 13 14 14 16 18 18 18 22 22 22 25 25 27 28 28 28 30 30 32 32 32 32 33 33 Page 9 Feb 15/03

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86(56+$1%22. 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 equipments 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 Page 11 Feb 15/03

86(56+$1%22. Legend :

ELT : (mergency /ocator 7ransmitter EPIRB : (mergency 3osition ,ndicating 5adio %eacon PLB : 3ersonal /ocator %eacon RCC : 5escue &oordination &enters

: 0ission &ontrol &enters MCC LUT : /ocal 8ser 7erminals COSPAS/SARSAT System Principle Figure 1 Page 12 Feb 15/03

86(56+$1%22. 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 its 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. Page 13 Feb 15/03

86(56+$1%22. 2. GENERAL DETAILS OF THE ELT ADT 406 AP A. Purpose of the ELT ADT 406 AP (Ref. Fig. 2) The ELT ADT 406 AP consists of a beacon that incorporates means of attachment. The ELT ADT 406 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 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 AP including country code assignation. Metalic stap ELT ADT 406 AP- Presentation Figure 2 Page 14 Apr 17/03

86(56+$1%22. ELT ADT 406 AP - Overall Dimensions

(Without optional protecting cover) Figure 3 Page 15 Apr 17/03

86(56+$1%22. B. Characteristics (Ref. Fig. 3)

(1)Approvals ADT 406 AP is COSPAS/SARSAT approved (TAC 131, dated July 2002) ADT 406 AP meets EUROCAE ED62 standard ADT 406 AP is JTSO 2C91a and JTSO 2C126 (JTSO N F.O. 0112 dated April 29, 2003) ADT 406 AP is TSO C91a and TSO C126 (TSO letter dated June 12, 2003)

(2)Physical characteristics

(a)Beacon with support Height : 101.3 mm Width : 188 mm Length : 329.3 mm Weight : 2.1 kg or 2.15 kg with the option of a protecting cover

(b)Beacon only Height : 101.3 mm Width : 188 mm Length : 234 mm (without back up antenna) Weight : 1.7 kg (with back up antenna) Back up antenna length : 375 mm (deployed)

(3)General characteristics

(a)External antenna Omnidirectionnal three-frequency antenna 50W 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 -20C on 121.5&243 MHz. Voltage capacity ELTA type number lithium manganese dioxide (solid cathode), battery servicing kit available: 02N60052 kit for one ELT 02N60053 kit for 10 ELT

: 6 VDC,

: 10.5 A/h,

:00E64191, Page 16 Apr 17/03

86(56+$1%22.

(c)Radio-electrical characteristics 1 406 MHz satellite transmitter Frequency transmitter power modulation transmission recurrence : 50 s, transmission duration

: 406.028 MHz,

: 5 W,

: "L" two-phase,

: 440 or 520 ms. 2 Associated homing transmitter Frequency 121.5 MHz transmitter power 243 MHz transmitter power modulation

: 121.5 MHz/243 Mhz or 121.5 MHz (selectable),

: 140 mW,

: 140 mW,

: AM (3K20A3X type) from, 1600 Hz to 300 Hz, up to four periods per second, antenna gain

: > 1 dBi.

(d)Environment characteristics Operating temperatures storage temperatures

: -20C to +55C,

: -55C to +85C.

(e)Miscellaneous characteristics Automatic activation level in accordance with EUROCAE ED-62 (internal G-switch). Activation direction is selectable (4 possibe directions), color self-test

orange in conformity with the international distress signal, 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 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 back up antenna in case of failure detection on primary access. Page 17 Apr 17/03

86(56+$1%22. 3. DESCRIPTION OF THE ELT ADT 406 AP AND OF THE AIRCRAFT COMPONENTS A. General description

(1)Introduction This beacon from the ADT406 family derives from the ADT 406 AF/AP model. Consequently, this beacon features the functional capabilities of the AF/AP besides its flotation gear, the attachment interface and its flexible antenna entirely compatible with Cospat/Sarsat.

(2)The ELT ADT 406 essentially consists of :

an ADT 406 AP beacon transmitter a whip antenna, labels, an activation / identification module, a support.

(3)The ELT ADT 406 AP basic aircraft components consists of :

a remote control unit, an external antenna. Note : this beacon can be used in survival mode without these elements. B. Detailed description (Ref. Fig. 7)

(1)The ADT 406 AP beacon The ADT 406 AP beacon mainly consists of :

a whip antenna, a power supply module, an electronic assembly, a mechanical assembly, a float. The front face of the electronic assy is equipped with the following components :

a REMOTE CONTROL electrical high density 15 pins female connector (10) for connecting up to the aircraft remote control panel or programming tools, a BACK UP WHIP ANT. TNC female connector (13) for connecting up the antenna, an EXT. ANT. BNC female connector (9) for connecting up the external antenna, an ARMED/OFF/ON lockable toggle switch (12) for activating the beacon, a TX indicator light (11) indicating beacon activation (real distress and self-test). Page 18 Apr 17/03

86(56+$1%22.

(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. Page 19 Feb 15/03

86(56+$1%22.

(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 AP must be installed on the aircraft

(see paragraph. 4.B.) for automatic activation (G-switch). It is fixed to the activation / identification module. Homing power selection Homing pwr xx dBm Official 15 Hex.

(e)Batteries label This label indicates the batteries expiry date (next battery servicing). Page 20 Apr 17/03

86(56+$1%22. ELT ADT 406 AP aircraft components

(f)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.

(g)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. The cable lenght should remain as short as possible in order to RF keep losses as close as possible to 0.5 to 1 dB at each frequencies (121.5/243/406.028 MHz). Page 21 Feb 15/03

86(56+$1%22. 4. INSTALLATION OF THE ELT ADT 406 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) In the case of use in automatic mode, the beacon shall be installed in the rear of the aircraft in order to maximize the probability of ELT survival in case of crash. However, it can be installed in another position in survival mode. 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 AP Figure 4 Page 22 Feb 15/03

86(56+$1%22. 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. 7KLVFDSVKDOOEHDVVLJQHGXSRQWKHLQLWLDOLQVWDOODWLRQDQGZLOONHHSWKLVSRVLWLRQLQPHPRU\IRU IXUWKHUEHDFRQUHSODFHPHQW 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. The attachment points are similar to those of the ADT 406 AF/AP beacon. Page 23 Feb 15/03

86(56+$1%22. The figure 5 shows the drilling pattern dimensions and determine the required area to access to the beacon controls and connectors. ELTA Recommendation Optional for Other Beacon Retrofit Installation of the ELT ADT 406 AP - Drilling Pattern Dimensions Figure 5 Page 24 Feb 15/03

86(56+$1%22. C. External antenna installation This antenna should be approved by ELTA. ELTA recommend to use P/N 25988 (antenna model 2624-82 manufactured by CHELTON) 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 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. Page 25 Feb 15/03

86(56+$1%22. The following simplified diagram shows the wiring between the ELT ADT 406 AP and its peripherals :

The Remote Control Panel (in cockpit) identified as "RCP", the external antenna noted as "EA", the whip antenna noted as "BA". The EA is connected to the ELT ADT 406 AP BNC female connector (5). The BA is connected to the ELT ADT 406 AP TNC female connector (1). The RCP is connected to the ELT ADT 406 AP high density 15 pins female connector (3). ELTA recommend to use P/N 16243 for RCP connector and P/N 231 plus 232 for ELT. A three position guarded switch (2) controls the ELT ADT 406 AP. A red indicator (4) displays the ELT ADT 406 AP state.

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#76 ADT 406 AP Beacon Installation Figure 6 Page 26 Apr 17/03

5 8

86(56+$1%22. E. Installation and configuration of the beacon (Ref. Fig. 5)

(1)Installation in automatic mode

&$87,2172%(23(5$7,21$/7+(%($&216+$//%(,1$50(326,7,2121&(,7+$6

%((1&255(&7/<,167$//( Connect the antenna cable to the EXT. ANT. connector. 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. Note : the beacon can be used in automatic mode with neither RCP nor external antenna.

&$87,21$66221$67+(%($&21,6,1$50(,7&$1%($8720$7,&$//<$&7,9$7(%< 7+(,17(51$/*6:,7&+

(2)Installation in survival mode Connect the whip back up antenna to ELT. The switch shall be on OFF.

Page 27 Feb 15/03

86(56+$1%22. 5. UTILIZATION OF THE ELT ADT 406 AP (Ref. Fig. 7)

&$87,21,17+((9(172)817,0(/<%($&21$&7,9$7,216+872:17+(%($&21$1

,1)2507+(&/26(676($5&+$15(6&8(6$525$,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 (11) and the aural indicator indicate beacon activation. If the aircraft has to be evacuated, refer paragraph B.(2) second case. Otherwise do not do anything and leave the beacon in operation until the rescue team arrives. 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 (11) 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 (12) 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 (10) 1.75 s ON, 0.25 s OFF. This delay will avoid unwanted activation (false manoeuvre). Then the indicator light (11) 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. Page 28 Apr 17/03

86(56+$1%22. If the aircraft has to be evacuated, Follow the instructions :

- unfasten the strap (and the cable if relevant),

- remove the beacon from its bracket, pull firmly to brake the retaining metallic strap (14, Ref. Fig. 7).

- extend the antenna and take the beacon with you. Page 29 Apr 30/03

86(56+$1%22. 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.

&$87,217+(%($&210867%(6+872:1%()25($1<0$,17(1$1&(23(5$7,216$5( 3(5)250( 7+(%($&210867%(&203/(7(/<6+872:1%()25(,7,65(029($1,76

$50(2))2172**/(6:,7&+6+$//%(,12))326,7,21 D. Beacon self-test

&$87,217+(6(/)7(676+$//%(3(5)250(:,7+,17+(),567012)$1<+285

%(&$86(7+((/7,66(1,1*0+=6,*1$/)25685,1*7+,6352&(66

/,0,7$7,212))$/6($/(57 The ELT ADT 406 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 listen on any VHF receiver.

(1)Self-test on the beacon

&$87,217+,66(/)7(67352&(666+$//127%(,17(5837(

,)7+,6352&(66,6127&203/(7()25$1<5($6213(5)250$1(:

&203/(7(6(/)7(67 Note : in case of use in survival mode without external antenna, the self-test will indicate an antenna failure, but the beacon will transmit normally on its emergency antenna. Place the beacons ARMED/OFF/ON toggle switch (12) in ON position. After two short blinks and a delay of 3 s, check that the indicator light (11) comes ON and the beacons buzzer sounds during 6s. After a brief blink the self-test report is display :

10 s permanent illumination of the indicator light (11) for correct operation, 10 s blinking condition of the indicator light (11) 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. Page 30 Apr 17/03

86(56+$1%22. Then the beacon enter in a waiting condition for 30 s (rate : 1.75s ON; 0.25s OFF). During this state return the switch (12) to ARMED position.

&$87,2123(5$7256+$//6:,7&+2))25$50(7+((/7:,7+,16$)7(56(/)7(67 5(325772$92,5($/,675(6675$160,66,21

(2)Self-test by means of the remote control unit The beacons ARMED/OFF/ON toggle switch (12) must be in ARMED position. The Remote Control ARMED/ON must be in ARMED position. Press the RESET/TEST pushbutton until the two acknowlegment blink on LED. Then, after a delay of approximately 6 second, the self test 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. 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. NOTE : On the beacon, after the two short blinks, the indicator light (11) comes ON and the buzzer sounds

&$87,217+((/76+$//%(,1$50(326,7,21,)1275(027(&21752/:,//127 23(5$7(7(675(6(721 Page 31 Apr 17/03

86(56+$1%22. 6. MAINTENANCE OF THE ELT ADT 406 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.

&$87,217+(6(/)7(67352&(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

&$87,217+(%$77(5<3$&.6+$//%($33529(%<(/7$,)27+(53$&.$5(86((/7$

:,//&$1&(/:$55$17<$1:,//5()86($1<5(63216,%,/,7<217+( 3528&723(5$7,210,6)81&7,21

&$87,217+(%$77(5,(686(&$1127%(5(&+$5*(212775<7223(125 5(&+$5*(7+(0 Next battery servicing date is indicated on a label stuck on the back face of ADT 406 AP. The old batteries must be replaced with new batteries of a model approved by ELTA P/N 02N60052 (battery servicing for one ELT) or 02N60053 (battery servicing for ten ELTs). ELTA recommends that the ELT ADT 406 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. Page 32 Feb 15/03

86(56+$1%22. 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 AP beacon, RF test on the operational frequencies 121.5 243 406 MHz. Page 33 Feb 15/03

86(56+$1%22. 14 1 BACK UP ANTENNA (BASIC CONFIGURATION) 2 FRONT FACE 3 ACTIVATION/IDENT ASSY 4 BACK FACE 5 MACHINED SECTION 6 STRAP 7 FLOAT 8 SUPPORT 9 EXT. ANT. BNC CONNECTOR (FEMALE) 10 REMOTE CONTROL CONNECTOR(FEMALE HD 15 PINS) 11 TX LED 12 ARMED/OFF/ON TOGGLE AND GUARDED SWITCH 13 BACK UP ANT. TNC CONNECTOR (FEMALE) 14 METALIC STRAP. ELT ADT 406 AP Detailed Description Figure 7 Page 34 Apr 17/03

COSPAS-SARSAT TYPE APPROVAL CERTIFICATE Appendix A page 1 Feb 15/03

JTSO 2C91a AND JTSO 2C126 APPROVAL Appendix A page 2 Feb 15/03

TSO C91a AND TSO C126 APPROVAL Appendix A page 3 Feb 15/03

Appendix A page 4 Feb 15/03

Crash Sensor Response Curve Appendix A page 5 Feb 15/03

/2*%22. FACTORY SETTING NEXT BATTERY SERVICING

../. (MM/YYYY) Appendix B page 1 Feb 15/03

/2*%22. FACTORY SETTING Appendix B page 2 Feb 15/03

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 3 Feb 15/03

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 4 Feb 15/03

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 5 Feb 15/03

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 6 Feb 15/03

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 7 Feb 15/03

/2*%22. ELT SERIAL NUMBER:

ENCODING UPDATE FORM ELT S/N

(MM/DD/YYYY) A/C REG. MARK A/C 24 Bit Address A/C OR A/P TYPE:

A/C OP-DESIGNATOR + S/N REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. REGISTRATION COUNTRY:

PROTOCOL:

C/S 15 HEX:

SIMPLIFIED DEC:

A/C MSN:

ISSUED BY:

DATE: //

SIGNATURE AND STAMP:

NOTE : Attach the encoding update sheet issued from the ELTA encoding tool. A/C OP-DESIGNATOR + S/N A/C OR A/P TYPE:

A/C 24 Bit Address A/C REG. MARK

(MM/DD/YYYY) ELT S/N ELT SERIAL NUMBER:

FINAL OPERATOR:

CONTACT (PHONE, email):

TEST TEST FINAL OPERATOR:

CONTACT (PHONE, email):

Appendix B page 8 Feb 15/03

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 9 Feb 15/03

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 10 Feb 15/03

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 11 Feb 15/03

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 12 Feb 15/03

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 13 Feb 15/03

/2*%22. MAINTENANCE TASKS RF TEST

(MM/YYYY)

(MM/DD/YYYY) BATTERY SERVICING FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. FINAL OPERATOR:

TYPE OF MAINTENANCE:

TASK DESCRIPTION:

NEXT BATTERY SERVICING: /

DATE: //

REPAIR STATION:

SIGNATURE AND STAMP:

NOTE : Attach the RF test sheet issued from the ELTA test tool. BATTERY SERVICING

(MM/DD/YYYY)

(MM/YYYY) RF TEST INSPECTION REPAIR INSPECTION REPAIR Appendix B page 14 Feb 15/03