DOC09078D
Ref. 0146257D
TP PAGE : 1
Date of rev.: JUN 20/2013
Revision 03
First issue: OCT 20/2010
Orolia S.A.S. - A Company of the Orolia Group
Emergency Locator Transmitters
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
With built-in GPS & Integral Antenna
© Orolia S.A.S. : This document is the property of Orolia S.A.S. and contains proprietary and confidential information.
The document is loaned on the express condition that neither the document itself nor the information contained therein shall be disclosed without the express consent of Orolia S.A.S. and that the information
shall not be used by the recipient without prior written acceptance by Orolia S.A.S.. Furthermore, the document shall be returned immediately to Orolia S.A.S. upon request.
Users are kindly requested to notify Orolia S.A.S of any discrepancy,
omission or error found in this manual.
Please report to our customer support:
E-mail: support.sar@orolia.com
Tel.: +33 (0)2 97 02 49 00
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
RECORD OF REVISIONS
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REV. Nb REVISION DATE INSERTION DATE BY
00 OCT 20/2010 OCT 20/2010 J.S.
01 MAY 09/2011 MAY 09/2011 J.S.
02 JAN 31/2012 JAN 31/2012 J.S.
03 JUN 20/2013 JUN 20/2013 J.S.
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Table of Contents
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Introduction
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System Overview
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System Functional Description and Operation
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Installation / Removal
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Check
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Troubleshooting
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Schematics and Diagrams 501 JUN 20/2013
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Servicing
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TABLE OF CONTENTS
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INTRODUCTION ..................................................................................... 1
WARRANTY ........................................................................................... 2
Scope .................................................................................................... 2
Exclusion ............................................................................................... 2
SYSTEM OVERVIEW ............................................................................. 1
COSPAS-SARSAT System ................................................................... 1
Description ............................................................................................................. 1
World coverage with the COSPAS-SARSAT system ............................................ 2
Operation ............................................................................................................... 2
Environmental improvements of ELTs ...................................................................2
KANNAD 406 ELT System Presentation .............................................. 3
LINE REPLACEABLE UNITS ............................................................... 5
Transmitter ............................................................................................................5
Bracket ..................................................................................................................6
External antenna ...................................................................................................6
SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION ..... 101
Transmitter Functional Description ................................................... 101
Transmission ..................................................................................................... 101
Controls & Connectors ......................................................................................101
Working mode information ................................................................................. 102
Off ................................................................................................................... 102
Self-Test .......................................................................................................... 102
Armed .............................................................................................................. 103
On ................................................................................................................... 103
VSWR Switch function (External / Integral antenna) ......................................... 104
GPS Strategy ..................................................................................................... 104
Basic Installation or portable use (without NAV Interface equipment) ............104
Installation including a NAV Interface equipment (Dongle IF GPS RS232) .... 105
Autonomy ..........................................................................................................105
Electrical interfaces ...........................................................................................106
Transmitter Technical Specifications ................................................................. 107
Equipment limitations ........................................................................ 108
Activation ........................................................................................... 108
Standby mode for automatic activation ..............................................................108
Manual activation ............................................................................................... 108
Off ..................................................................................................... 109
Self-Test ............................................................................................ 109
Compatibility list ................................................................................ 110
Mounting brackets ............................................................................................. 110
Remote control panels (RCP) ............................................................................ 110
Outside buzzer ..................................................................................................110
DIN-12 connector or programming dongles .......................................................110
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TABLE OF CONTENTS
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External antennas ............................................................................................. 111
INSTALLATION / REMOVAL ............................................................. 201
Registration ....................................................................................... 201
General .............................................................................................................. 201
Registration in USA ........................................................................................... 201
Registration in Canada ...................................................................................... 202
Programming .................................................................................... 203
"Pin programming" option .................................................................................. 203
ELT transmitter installation procedure .............................................. 204
ELT transmitter Connection .............................................................. 206
First power up ................................................................................... 206
Removal ............................................................................................ 207
CHECK ............................................................................................... 301
Self-test ............................................................................................. 301
Periodicity .......................................................................................................... 301
Self-test procedure ............................................................................................ 301
Operational tests ............................................................................... 302
ELT operational tests ........................................................................................ 302
Test of transmitted signals ................................................................................ 302
406 MHz Transmission tests ........................................................................... 302
121.5 MHz Transmission tests ........................................................................ 303
TROUBLESHOOTING ........................................................................ 401
General ............................................................................................. 401
Faults on Self-test ............................................................................. 401
3+1 flashes ..................................................................................................... 401
3+2 flashes ..................................................................................................... 401
3+3 flashes ..................................................................................................... 401
3+4 flashes ..................................................................................................... 401
3+5 flashes ..................................................................................................... 401
3+6 flashes ..................................................................................................... 401
SCHEMATICS & DIAGRAMS ............................................................ 501
Outline dimensions and weight with mounting bracket AF-COMPACT 501
Outline dimensions and weight with universal mounting bracket ...... 502
AF INTEGRA / AF INTEGRA (ER), axis of installation ..................... 503
AF-H INTEGRA / AF-H INTEGRA (ER), axis of installation ............. 504
SERVICING ................................................................................. 601
Maintenance Schedule ..................................................................... 601
Periodic inspection ............................................................................................ 601
Battery replacement .......................................................................................... 601
Battery replacement requirements .................................................... 602
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INTRODUCTION
INTEGRA ELTs are an extension of the range of KANNAD ELTs. The
development of this type of ELTs is based on the improvement of safety of
flights either for light aircraft, business aircraft or commercial aviation.
The safety of flights is strengthened thanks to a built-in GPS giving a more
accurate position transmitted within minutes following the distress and an
Integral Antenna which may replace the external antenna in case on
unavailability of this last one.
AF
(1)
INTEGRA is designed for fixed wing aircraft or helicopters, AF-H
INTEGRA is designed for flat installation on board helicopters only.
The AF INTEGRA (ER) and AF-H INTEGRA (ER) ELTs are evolutions of AF
INTEGRA and AF-H INTEGRA ELTs. The main evolution consists in the
extension to -40°C of temperature range.
The instructions in this manual provide the information necessary for the
installation and the operation of AF INTEGRA, AF-H INTEGRA, AF INTEGRA
(ER) and AF-H INTEGRA (ER) ELTs.
Servicing instructions of ELT are normally performed by shop personnel. For
detailed instructions , refer to Service & Support section of Kannad Aviation
Website.
For the initial installation, please refer to Initial Installation Manual supplied with
AF INTEGRA, AF-H INTEGRA, AF INTEGRA (ER) and AF-H INTEGRA (ER)
ELTs.
FOR REGULATORY REQUIREMENTS, PLEASE CONSULT YOUR
NATIONAL AVIATION AUTHORITY.
NOTE: (1) AF for Automatic Fixed
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WARRANTY
1. Scope
The equipment is warranted against all material or manufacturing defect for a
period of two years from the date of installation on the aircraft or thirty months
from the date of shipment from Orolia S.A.S. facilities whichever occur first.
Work carried out under the warranty shall not have the effect of extending the
warranty period.
In respect of this warranty, after a defect has been noted by our services, the
sole obligation incumbent upon us shall be the repair of the equipment or the
element identified as being defective by our services or possibly its
replacement free of charge, to the exclusion of all compensation or damages.
This warranty covers the cost of parts and labour in our factories.
The cost of transportation of the equipment replaced or repaired are the
purchaser's exclusive responsibility.
The risks shall be borne by the purchaser.
2. Exclusion
Defects and deterioration caused by natural wear of the product or by external
accident (poor maintenance, abnormal conditions of use, etc.) or by
modification of the equipment and tools not recommended nor specified by our
company, are excluded from the warranty.
Also the warranty shall not cover visible defects which the purchaser wouldn't
have formally notified Orolia S.A.S within 48 hours of receipt of the equipment.
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SYSTEM OVERVIEW
1. COSPAS-SARSAT System
A. Description
Launched in the early eighties by the four founder countries (Canada, France,
Russia, USA), the COSPAS-SARSAT system provides satellite aid to search
and rescue (SAR) operations for maritime, aeronautical and terrestrial vehicles
anywhere in the world.
It uses distress beacons fitted on mobiles and a constellation of LEO and GEO
satellites which relay and process the 406 MHz signal to ground stations (LUT)
where the beacon positions are determined with a precision of less than 2 NM
with the Doppler effect.
Several types of beacons are designed to match the various applications of the
COSPAS-SARSAT system:
• EPIRB (Emergency Position Indicating Radio Beacon) for maritime
applications.
• ELT (Emergency Locator Transmitter) for aeronautical applications.
• PLB (Personal Locator Beacon) for land expeditions.
Figure 1: COSPAS-SARSAT System
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B. World coverage with the COSPAS-SARSAT system
The major improvement is the use of the COSPAS-SARSAT system for
processing aeronautical emergencies.
The 406 MHz transmission carries digital data which enable the identification
of the aircraft in distress and facilitate SAR operation (type of the aircraft,
number of passengers, type of emergency).
The 406 MHz message is transmitted to the COSPAS-SARSAT satellites. This
message is downloaded to one of the 64 ground stations (44 LEOLUTs and 20
GEOLUTS).
The aircraft is located by Doppler effect by the LEO satellites with a precision
better than 2 NM (4 km) at any point of the earth.
Thanks to the built-in GPS receiver, the position (accuracy typically about 60
meters) will be transmitted by the ELT within minutes following the distress.
The 121.5 MHz frequency is no more processed by COSPAS-SARSAT system
but is still used by SAR services for homing in the final stage of rescue
operations.
C. Operation
In the event of a crash, the ELT activates automatically and transmits a sweep
tone on 121.5 MHz and the 406 MHz signal.
In a crash, a G-Switch (shock detector) turns the ELT "ON" when the ELT is
subjected to an important change of velocity (or deceleration).
Activation may also be accomplished by means of a Remote Control Panel
(RCP) from the cockpit or directly from a switch of the ELT’s front panel.
In the event the external antenna is unavailable due to the crash, the
integral antenna will replace it to transmit the 406 MHz signal to the
Cospas-Sarsat satellites.
Note: The integral antenna has not been tested and approved by CospasSarsat.
D. Environmental improvements of ELTs
The certification of an ELT includes a range of severe mechanical tests:
• resistance to flame;
• impact and crush tests;
• resistance up to 500 G shocks;
• watertightness;
• anti-deflagration;
• extreme temperatures .
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2. KANNAD 406 ELT System Presentation
AF INTEGRA and AF-H INTEGRA belong to the AF type of ELTs which are
permanently attached to an aircraft. AF INTEGRA and AF-INTEGRA (ER) are
designed to be installed on fixed wing aircraft or helicopters. AF-H INTEGRA
and AF-H INTEGRA (ER) are designed for flat installation on board helicopters
only.
The INTEGRA ELT system (Refer to Section Figure 2: ELT system description
page 4) is composed of:
1. the ELT transmitter:
• P/N S1851501-01 for AF INTEGRA (ER) or,
• P/N S1851501-02 for AF INTEGRA or,
• P/N S1852501-01 for AF-H INTEGRA (ER) or,
• P/N S1852501-02 for AF-H INTEGRA
2. a mounting bracket (P/N S1840502-01 or S1840502-02);
3. an external whip, rod or blade antenna;
4. A remote control panel
(1)
;
5. a DIN-12 connector, programming dongle or dongle IF GPS RS232
(2)
when the optional RCP is connected.
6. an outside buzzer (optional).
Note: (1) The RCP is optional only if the commands and controls of the
ELT are reachable and visible from the pilot seated position.
(RTCA DO-204A):
"Equipment control and indicator installed for in-flight use shall be readily
accessible from the cockpit crew position. The cockpit crew shall have an
unobstructed view of visual indicator when in the normal seated position."
Note: (2) GPS/NAV Interface with an on board RS232 GPS.
For details of approved part number of INTEGRA ELT system, Refer to Section
6. Compatibility list page 110.
The transmitter and bracket are installed in the aircraft near the tail. The
external antenna is mounted on the fuselage near the tail. The remote control
panel is installed in the cockpit and connected to the ELT with a DIN-12
connector or a programming dongle and a 2, 3, or 4-wire bundle (not supplied)
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Figure 2: ELT system description
Note: Data position from an on board RS232 GPS only available if a dongle IF
GPS RS232 (5) is connected instead of programming dongle (5) or DIN-12
connector (5).
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3. LINE REPLACEABLE UNITS
A. Transmitter
The AF INTEGRA and AF-H INTEGRA are ELTs designed to be installed
onboard aircraft to transmit a distress signal on frequencies:
• 406 MHz (COSPAS-SARSAT frequency) for precise pinpointing and
identification of the aircraft in distress.
• 121.5 MHz used for homing in the final stages of the rescue operations.
The AF INTEGRA and AF-H INTEGRA are certified as Automatic Fixed (AF)
ELTs with the approved external antennas.
The housing of AF INTEGRA and AF-H INTEGRA transmitters are made of
molded plastic with excellent mechanical resistance.
The ELT housing is designed with no sharp edges.
Figure 3: ELT Transmitter
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B. Bracket
The bracket installed near the tail is designed to fix the ELT with a Velcro®
strap. This enables quick removal of the ELT for maintenance or exchange.
Figure 4: ELT Transmitter with Mounting Bracket
The transmitter may be installed on its standard mounting bracket
(P/N S1840502-01) or on an Universal Mounting Bracket (P/N S1840502-02)
to re-use existing drilling for retrofit (Refer to DOC09081, Initial Installation
Manual for drilling masks and outline dimensions of these brackets).
C. External antenna
Only approved antennas may be installed (Refer to Section 6.
Compatibility list page 110).
Connection to the ELT will be carried out with a 50 Ohm coaxial cable (RG58
for example) ended with a male BNC connector.
IMPORTANT NOTICE: Orolia S.A.S. recommends a cable with radio
electric properties similar or better to those of a RG58 cable.
Note: the 50 Ohm coaxial and the male BNC connector are not supplied
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SYSTEM FUNCTIONAL DESCRIPTION AND OPERATION
1. Transmitter Functional Description
A. Transmission
The transmitter can be activated either automatically when the crash occurs
(thanks to a shock sensor) or manually (thanks to a switch on the transmitter
itself or on a RCP).
The transmitter is designed to transmit on two frequencies (121.5 and 406
MHz). The 121.5 Mhz is mainly used for homing in the final stages of the rescue
operations. The 406 MHz frequency is used by the COSPAS-SARSAT
satellites for precise pinpointing and identification of the aircraft in distress.
Once activated, the transmitter operates continuously on 121.5 MHz.
During operations, a digital message is transmitted on 406.037 MHz every 50
seconds.
B. Controls & Connectors
The following controls are to be found on the ELT front panel (from left to right):
1. 3-position switch ARM/OFF/ON;
2. Visual indicator (red);
3. DIN 12 socket for connection to an optional Remote Control Panel, a
programming dongle, dongle IF GPS RS232 or a programming
equipment;
4. BNC connector for the external antenna.
Figure 1: Front Panel
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The red light gives an indication on the working mode of the beacon:
• after the self test:
- a series of short flashes indicates the self test failed;
- one long flash indicates a correct self test;
• in operating mode:
- periodic flashes during 121.5 transmission;
- long flash during 406 transmission.
A buzzer gives audio information on the beacon working:
• continuous tone during self test;
• 1 beep every 0.7 second during 121.5 transmission;
• silence during 406 transmission.
C. Working mode information
The ELT has 4 different modes:
• Off.
• Self-test (temporary mode).
• Armed (standby mode to enable automatic activation by the shock sensor
or by an optional remote control panel).
• On (transmission).
Transmission is effective if the beacon is activated (either manually on the ELT
control panel, automatically by the shock sensor, or remotely by the "ON"
switch of an optional remote control panel when connected).
(1)Off
The ELT is off when the switch is in position "OFF", no part of the ELT
is energized.
This mode must only be selected when the ELT is removed from the
aircraft or when the aircraft is parked for a long period or for
maintenance.
(2) Self-Test
The self-test mode is a temporary mode (max duration 15 sec) in which
the ELT checks the main characteristics of the transmitter (Battery
voltage, Programming...) and enables digital communication with
programming and test equipment.
This mode is selected:
• when switching from "OFF" to "ARM";
• when switching to "RESET / TEST" on an optional Remote Control
Panel (provided that the switch of the ELT is in position "ARM");
• when switching to "ON" prior to transmission.
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The buzzer operates during the self-test procedure.
After about 10 seconds, the test result is displayed on the visual
indicator as follows:
• One long flash indicates valid test.
• A series of short flashes indicates false test result.
The number of flashes indicates the type of failure:
• 3 + 1 = LOW BATTERY VOLTAGE.
• 3 + 2 = LOW TRANSMISSION POWER.
• 3 + 3 = FAULTY VCO LOCKING (FAULTY FREQUENCY).
• 3 + 4 = NO IDENTIFICATION PROGRAMMED.
• 3 + 5 = FAULTY VSWR (LINK TO EXTERNAL ANTENNA).
• 3 + 6 = INTERNAL GPS SERIAL LINK.
It is recommended to test the ELT regularly in order to detect any
possible failure (Refer to Section A. Periodicity page 301).
The number of self-tests carried out is recorded. This information is
available when the ELT is connected to a programming and test
equipment (PR600).
(3) Armed
In order to enable activation by the G-Switch or with an optional Remote
Control Panel, the ELT must be in standby mode with the switch in the
"ARM" position.
This mode is mandatory during flight. The ELT should remain in the
"ARM" position except when the aircraft is parked for a long period or for
maintenance.
(4) On
This mode is selected:
• manually by switching the ELT to "ON";
• by switching an optional Remote Control Panel switch to "ON"
(provided that the ELT switch is in the "ARM" position);
• automatically when a crash occurs (provided that the ELT switch is in
the "ARM" position).
When this mode is selected, the ELT starts transmitting:
• after 50 seconds on 406 MHz (one 406 MHz burst every 50 seconds)
to the external antenna;
• after the GPS lock on 121.5 MHz (continous transmission between
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each 406 MHz burst). If GPS lock does not occur within 5 minutes, the
121.5 MHz will be activated.
The red visual indicator on the ELT (and on an optional remote control
panel when connected) flashes and the buzzer operates.
• Red visual indicator:
- 1 short flash during ELT transmission on 121.5 MHz (every 0.7
seconds);
- 1 long flash during ELT transmission on 406 MHz (every 50
seconds).
• Buzzer:
- 1.5 Hz pulse signal (recurrence 0.7 s) during ELT transmission on
121.5 MHz [except if the ELT has switched to internal antenna:
Refer to D. VSWR Switch function (External / Integral antenna)].
In case of accidental activation, the ELT can be reset either by switching
it to "OFF" or by switching to "RESET" on an optional Remote Control
Panel when connected.
The number of 406 MHz bursts transmitted is recorded. This information
is available when the ELT is connected to a programming and test
equipment (PR600).
D. VSWR Switch function (External / Integral antenna)
During the 406 MHz burst, the Voltage Standing Wave Ratio (VSWR) is
measured. After 5 bursts with wrong VSWR measurements, the ELT switches
from the external to the internal antenna in order to optimize transmitted signal.
In ON mode, after 36 bursts, the ELT decides to re-switch or not according to
the result of 2 new VSWR measurements.
NOTE: when shifting from the external to the integral antenna the pulse signal
of the buzzer shifts from one beep every 0.7 second to 2 beeps every 0.7
second.
Note: The integral antenna has not been tested and approved by CospasSarsat.
E. GPS Strategy
(1)Basic Installation or portable use (without NAV Interface equipment)
To avoid consumption, the internal GPS receiver is not power supplied in
ARM mode. After a crash (automatic activation) or manual activation, the
internal GPS will try to acquire a position in continuous mode during one hour
and by different sequences up to 24 hours of 406 MHz transmission. If the
internal GPS receiver acquires a valid position, then the message will contain
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the true position in the next 406 MHz burst. If the internal GPS receiver does
not acquire a valid position, then the message will contain the default value
(GPS position not valid).
(2) Installation including a NAV Interface equipment (Dongle IF GPS RS232)
When valid, the position of the internal GPS will always take priority, even if
a Dongle IF GPS RS232 is connected to the GPS equipment of the aircraft
(external GPS):
• If only the internal GPS acquires a valid position, then the message will
contain the true position of the internal GPS in the 406 MHz burst;
• If only the external GPS acquires a valid position, then the message will
contain the true position of the external GPS in the 406 MHz burst;
• If both internal and external GPS acquire a valid position, then the
message will contain the true position of the internal GPS acquire a valid
position;
• If neither the internal GPS, nor the external GPS acquire a valid position,
then the message will contain the default value (GPS position not valid).
According to § 4.5.5.2 of Cospas Sarsat C/S T001, if, after providing valid data,
the navigation input fails or is not available, the beacon message retains the
last valid position for 4 hours (± 5 min) after the last valid position data input.
After 4 hours the encoded position is set to the default values.
F. Autonomy
The energy is provided by a battery pack composed of a LiMnO2 two-element
battery (See pages page 107 & page 602 for Kit battery reference).
Battery shall be replaced according to the expiriy date indicated on the ELT.
NOTE: ELT Battery useful life: 6 years in service life (ETSO/TSO/COSPAS-
SARSAT margins included).
IMPORTANT: If the ELT has been activated for more than 1 hour, the
battery shall be replaced (See page 602 section 2, Battery replacement
requirements)
With new batteries, the duration of the 121.5 transmission is over 48 hours at
-20°C for INTEGRA ELTs and over 48 hours at -40°C for INTEGRA (ER) ELTs.
As it is therefore preferable to keep the battery power for 121.5 MHz homing
frequency transmission for the rescue operations, in compliance with
COSPAS-SARSAT specifications, the 406 MHz transmission is deliberately
Lithium cells, lithium batteries and equipment containing such
batteries are subjected to regulations and classified under class 9 as
from 1st of January 2003.
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stopped after 24 hours to extend the 121.5 MHz transmission for as long as
possible.
G. Electrical interfaces
J1
DIN 12 socket J1 is dedicated for connection to an optional Remote Control
Panel, to a Programming or Maintenance Dongles or to a programming
equipment (PR600).
IMPORTANT: Shielded cables are recommended. The required wires
are AWG24.
Table 1: J1 connector pin-out
J2
BNC female connector J2 is used to connect the external antenna through a
50 Ω coaxial cable.
IMPORTANT NOTICE:
The use of a low attenuation coaxial cable is recommended. The
maximum permitted attenuation in the coaxial is 1db@400 MHz.
J1 PIN Signal Name Destination Direction
Viewed from
Front Face
J1-A RCP RESET RCP IN
J1-B DONGLE RX SMM / PGM IN
J1-C DONGLE CS SMM OUT
J1-D DONGLE SK SMM OUT
J1-E DONGLE TX SMM / PGM OUT
J1-F DONGLE ALE2P SMM OUT
J1-G RCP COMMON RCP OUT
J1-H RCP BUZZER RCP OUT
J1-J RCP LED RCP OUT
J1-K RCP ON RCP OUT
J1-L DONGLE GND SMM / PGM OUT
J1-M RCP 2W COMMON RCP OUT
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H. Transmitter Technical Specifications
TYPE
• Two-frequency ELT
(121.5 / 406.037 MHz)
• Automatic Fixed
• COSPAS-SARSAT Class
INTEGRA AF (ER)/AF-H (ER):
Class I, -40°C to +55°C.
INTEGRA AF/AF-H:
Class II, -20°C to +55°C.
406 MHz TRANSMISSION
• Frequency: 406.037 MHz+/-1 kHz
• Output power: 5W (37 dBm +/- 2 dB)
• Modulation type: 16K0G1D
(Biphase L encoding)
• Transmission duration:
520ms (long message) every 50 s.
• Autonomy
INTEGRA (ER): 24 Hours @-40°C
INTEGRA: 24 Hours @-20°C
121.5 MHz TRANSMISSION
• Frequency:
121.5 MHz +/- 6 kHz
• Output power:
50 to 400 mW
(17dBm to 26 dBm), typical 100 mW
• Modulation type: 3K20A3X
• Modulation rate: > 85 %
• Frequency of modulation signal:
1600 Hz to 300 Hz with decreasing
sweep
•
Autonomy
INTEGRA (ER):
over 48 hours@-40°C
INTEGRA:
over 48 hours@-20°C.
G-SWITCH SENSOR
Mechanical G-switch sensor compliant
with EUROCAE ED62 specifications.
RF Fied strenght limits
INTEGRA (ER): 0.471 V/m
INTEGRA: 0.474 V/m
CONTROLS
• ARM / OFF / ON switch
• DIN12 socket for RCP and pin
programming option.
• Bright red visual indicator
• Buzzer
• BNC antenna connector
BATTERY
KIT BAT200, P/N: S1840510-01
LiMnO2 two-element battery for
transmitter power supply
Battery expiry date: 7 years from date of
cell manufacturing
HOUSING
Material: Polycarbonate
Color: Yellow (color compounded)
Transmitter dimensions:
131 x 86 x 75.4 mm
( 5.157 x 3.385 x 2.968 inches)
Weight:
• AF: typical 755 g. (1.66 lb).
• AF-H: typical 760 g. (1.67 lb).
Tightness: O-ring
ENVIRONMENTAL CONDITIONS
RTCA DO-160F / EUROCAE ED14F
Section 4 to 26:
INTEGRA AF / AF (ER)
[ED62A]X[ED62A]A[ED62A][R(C&C1)]X
WXXXSZXXXZ[ED62A]B[XXG33]XXA
[ED62A]
INTEGRA AF-H / AF-H (ER)
[ED62A]X[ED62A]A[ED62A][U(G)]XWXX
XSZXXXZ[ED62A]B[XXG33]XXA
[ED62A]
QUALIFICATIONS
ETSO-2C91a & ETSO-2C126 / TSOC126a
FOR USE OUTSIDE OF THE USA OR
EASA RULES, CONTACT YOUR
LOCAL CIVIL AVIATION AUTHORITY.
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 108
JUN 20/2013
2. Equipment limitations
Antenna - ELT cable with maximum permitted attenuation: 1db@400 MHz.
WARNING: ELTs are radio transmitters which emit radio frequency
radiation when activated. When transmitting, the user's minimum distance of
exposure is 0.20 meter.
For RF Fied strenght limits, please Refer to Section H. Transmitter
Technical Specifications page 107. RF Fied strenght limits have been
calculated according to Canadian RSS-102 Standard "Radio Frequency
(RF) Exposure Compliance of Radiocommunication Apparatus (All
Frequency Bands)".
For Canadian user, any information and/or contact on Radiofrequency (RF)
Energy and Health may be found on:
http://www.ic.gc.ca/eic/site/smt-gst.nsf/eng/sf08792.html.
3. Activation
A. Standby mode for automatic activation
In order to be automatically activated by the crash sensor, the ELT must be in
standby mode. This mode is mandatory during the flight. We recommend to
switch off the ELT only when removed from the aircraft or when the aircraft is
parked for a long period or for a maintenance operation.
• Check that the antenna is correctly connected.
• Switch to " ARM".
To operate the ELT with an optional Remote Control Panel, ensure that:
• The ELT switch is the "ARM" position .
B. Manual activation
• Check that the antenna is correctly connected.
• Switch to " ON " (either on the ELT or on an optional Remote Control Panel
when connected):
- The ELT starts with the self-test sequence then, after 50 sec., transmits
on:
• 406 MHz (one 406 MHz burst every 50 seconds);
• 121.5 MHz (continous transmission between each 406 MHz burst
after the GPS lock) .
- During transmission, the buzzer operates and the red visual indicator
flashes.
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AF INTEGRA / AF-H INTEGRA ELT
PAGE: 109
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4. Off
It is possible to stop the ELT in case of unintentional activation:
• Switch to " OFF ".
Important notice: As 406 MHz transmission is effective 50 seconds after
the ELT activation, if it is switched off within this delay, no further radio
contact will be necessary.
5. Self-Test
Refer to Section 1. Self-test page 301
Regulations state that no transmission must be interrupted unless
every means are used to contact and inform the Air Traffic Controller
of this action.
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 110
JUN 20/2013
6. Compatibility list
A. Mounting brackets
B. Remote control panels (RCP)
C. DIN-12 connector or programming dongles
Note (1): Fulfills functions of ELT to RCP cable, programming dongle and GPS/
NAV equipment interface when connected to an on board RS232 GPS.
Designation Part Number
COMPACT MOUNTING BRACKET KIT S1840502-01
COMPACT UNIVERSAL MOUNTING BRACKET KIT S1840502-02
KANNAD Designation Part Number
RC100 KIT S1820513-03
RC102 KIT S1820513-21
RC200 S1820513-11
RC300 S1820513-09
RC300-NVG S1820513-10
RC310-NVG S1820513-26
RC600 NVG (Y) S1820513-12
RC600-NVG (W) S1820513-13
RC800 S1820513-15
RC810 S1820513-23
Designation Part Number
DIN-12 connector S1820514-03
Programming dongle S1820514-01
Programming dongle Assy S1820514-06
Programming dongle INTEGRA / LR S1820514-07
Dongle IF GPS RS232 S1820514-08
(1)
Programming dongle INTEGRA / SA S1820514-11
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 111
JUN 20/2013
D. Outside buzzer
E. External antennas
KANNAD Designation Part Number
OUTSIDE BUZZER KIT S1820515-06
KANNAD Designation Manufacturer KANNAD Part Number
ANT300 CHELTON 1327-82 0124220
WHIP ANT AV100 RAMI AV-100 0147444
WHIP ANT AV200 RAMI AV-200 0146150
ROD ANT AV300 RAMI AV-300 0146151
BLADE ANT500 SENSOR SYSTEMS
S65-8282-406
0124222
BLADE ANT560 DAYTON GRANGER
ELT10-696-1
0145787
BLADE ANT650 CHELTON 2624-82 0124251
N/A CHELTON 2632-82 N/A
N/A CHELTON 21-41 N/A
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INSTALLATION / REMOVAL
1. Registration
A. General
The ELT must be registered prior to installation onboard.
When a 406 MHz ELT is installed in an aircraft, it is imperative that the aircraft
owner register the ELT. Each 406 MHz ELT contains a unique identification
code that is transmitted to the satellite. This helps the “Rescue Coordination
Center” (RCC) to determine whether an emergency has actually occurred. The
unique identification permits accessing a data base.
The registration card available from the local registration authority must be
completed and returned to this authority.
Any change of ownership shall also be declared and registered with the local
registration authority.
B. Registration in USA
Mail or Fax your registration form to:
SARSAT BEACON REGISTRATION
NOAA
NSOF, E/SPO53
1315 East West Hwy
Silver Spring, MD 20910
or Save Time! Register your beacon online at:
www.beaconregistration.noaa.gov
All online registrations will be entered into the National 406 MHz Beacon
Registration Database on the same day of entry. Registration forms received
via postal mail will be entered within 2 business days of receipt. For online
registrations, a confirmation letter with your completed registration information
form will be sent immediately via e-mail or fax (if provided). Confirmation letters
sent via postal mail should arrive within two weeks. Once your registration
confirmation is received, please review all information. Any changes or updates
to your registration information can be done via the internet, fax, e-mail or
postal mail. If you do not receive your registration confirmation from NOAA on
the same day you submit it over the internet or within two weeks if you submit
it by postal mail, please call NOAA toll-free at: 1-888-212-SAVE (7283) or
301-817-4515 for assistance.
After initial registration (or re-registration) you will receive a NOAA Proof of
Registration Decal by postal mail. This decal is to be affixed to the beacon and
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 202
JUN 20/2013
should be placed in such a way that it is clearly visible. If for some reason you
do not receive the registration decal within two weeks, please call NOAA tollfree at: 1-888-212-SAVE (7283) or 301-817-4515.
Failure to register, re-register (as required every two years), or to notify NOAA
of any changes to the status of your 406 MHz beacon could result in penalties
and/or fines being issued under Federal Law. The owner or user of the beacon
is required to notify NOAA of any changes to the registration information at any
time. By submitting this registration the owner, operator, or legally authorized
agent declares under penalty of law that all information in the registration
information is true, accurate, and complete. Providing information that is
knowingly false or inaccurate may be punishable under Federal Statutes.
Solicitation of this information is authorized by Title 47 - Parts 80, 87, and 95 of
the U.S. Code of Federal Regulations (CFR). Additional registration forms can
be found on the NOAA-SARSAT website at:
www.sarsat.noaa.gov or at: www.beaconregistration.noaa.gov
C. Registration in Canada
Beacon information is held in the Canadian Beacon Registry maintained by the
National Search and Rescue Secretariat for use in search and rescue
operations. Online access to the Registry is available for all beacon owners to
register new beacons or to update their beacon information. You can add or
update your beacon information by accessing the registry directly, sending in a
completed registration form or by talking to one of our beacon registry
representatives.
You can access the registry:
• online: www.canadianbeaconregistry.com
• by email: CBR@Sarnet.dnd.ca
• by fax: 1-613-996-3746
• by telephone: 1-800-727-9414 or 1-613-996-1616
The registration information must be updated when the aircraft ownership
changes as per the Canadian Airworthiness Notice AN B029 (refer to following
link):
http://www.nss.gc.ca/site/Emergency_Beacons/canadian_beacon_registry_e.asp
Additional information and registration forms can be found on the Canadian
NSS website at:
http://www.nss.gc.ca/site/cospas-sarsat/INTRO_e.asp
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 203
JUN 20/2013
2. Programming
A. "Pin programming" option
The INTEGRA family offers pin-programming capabilities to facilitate
maintenance operations especially in the case of removals and/or
replacement.
A special DIN 12 connector with a Serial Memory Module (called "Programming
Dongle") is connected to the ELT when installed onboard. This Programming
Dongle contains the identification information of the aircraft and remains
onboard the aircraft. When an unprogrammed ELT is installed and connected
to this Programming Dongle and the "ELT" is switched to "ARM", it
automatically updates its own memory with the identification data contained in
the Programming Dongle memory.
When the ELT is removed from the aircraft, it keeps its identification data.
For maintenance purposes, it is possible to delete the identification information
of the ELT by connecting a "Maintenance Dongle" to the ELT. Any accidental
transmission with this "maintenance dongle" will not involve SAR operation as
the identification code transmitted is recognised by COSPAS-SARSAT as "not
onboard".
When a maintenance dongle is connected:
• Country code is 227 (France).
• Protocol is Test.
• Identification number is K + 6 digits (the 6 digits of the CSN number).
If the pin programming option is selected by the owner, the following equipment
are required:
• a "Programming Dongle" on each aircraft;
• a "Maintenance Dongle" on each ELT spare.
Figure 1: Maintenance Dongle
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 204
JUN 20/2013
3. ELT transmitter installation procedure
Refer to Figure 2: Installing the transmitter on the bracket page 205
NOTE: Intial installation (bracket installation and first wiring) is described in
Initial installation manual, DOC09081 also supplied with the transmitter.
1. Mount the transmitter on the bracket
• For AF INTEGRA or AF INTEGRA (ER), with "Flight direction" arrow
of the ELT pointed towards the front of the aircraft according to
Section 3. AF INTEGRA / AF INTEGRA (ER), axis of installation page
503.
For AF-H INTEGRA or AF-H INTEGRA (ER), with "Flight direction"
arrow of the ELT pointed towards the front or downwards the
helicopter according to Section 4. AF-H INTEGRA / AF-H INTEGRA
(ER), axis of installation page 504.
2. Slide the self-stripping strap through the buckle. Ensure the buckle is
correctly positioned (indifferently on right or left side of ELT)
regarding the horizontal center line of ELT as shown Detail A.
3. Fasten the self-stripping strap tightly.
CAUTION:
AN INCORRECT TIGHTENING OF THE HOOK AND LOOP
FASTENER COULD LEAD TO AN UNSAFE SITUATION BY THE ELT
PREVENTING THE TRANSMISSION OF THE DISTRESS MESSAGE
IMPORTANT:
Once installed in the mounting bracket, the installer must be sure
that the transmitter is firmly attached in its bracket by trying to
extract it manually, thereby verifying there is no play and that it
remains attached when extraction from the bracket is attempted.
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
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JUN 20/2013
Figure 2: Installing the transmitter on the bracket
OPERATION MANUAL
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PAGE: 206
JUN 20/2013
4. ELT transmitter Connection
1. Connect the cable of the outside antenna to the BNC connector of the
front panel.
2. Set the 3-position switch of the front panel to ARM.
Figure 3: Installation, controls and connectors
• Perform the first power up procedure (see below).
5. First power up
Perform the following tests:
1. ELT operational tests:
• connect the external antenna to J2;
• switch the ELT from OFF to ARM;
• check that the Self-Test result is OK (one long flash).
2. 406 & 121.5 MHz transmission tests (optional):
Refer to Section B. Test of transmitted signals page 302.
At the end of the first power up procedure, switch the ELT to ARM.
The ELT is now in stand by mode and ready to be activated:
• either automatically by G-Switch sensor if a crash occurs;
• or manually by an optional Remote Control Panel (when connected).
Note : switching to ON directly on the ELT front panel will also
activate the ELT.
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 207
JUN 20/2013
6. Removal
1. Switch the ELT to OFF.
2. Disconnect the external antenna from the BNC connector of the ELT.
3. If connected, disconnect the DIN 12 Connector of Remote Control Panel
bundle from the DIN12 socket of the ELT.
4. Unfasten the self-stripping strap.
5. Remove the transmitter from the bracket.
Figure 4: Removing the transmitter
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AF INTEGRA / AF-H INTEGRA ELT
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JUN 20/2013
CHECK
1. Self-test
A. Periodicity
EUROCAE ED-62A Recommendations
§ 2.8.9 : "The battery source shall provide sufficient capacity for a self-test to
be conducted according to the period specified by the manufacturer or at least
once a month according to Cospas-Sarsat requirement."
§ 7.5 : "Check the self-test function according to manufacturer’s
recommendation and that such a test shall occur at least once every six
months."
Manufacturer Recommendations
It is recommended by the manufacturer to test the ELT to detect any possible
failure.
Operational check must be performed regularly by a pilot or maintenance
personnel from the cockpit (Remote Control Panel). It is recommended to
perform a self-test at least once every six months but it should not be done
more than once a month.
Each self-test consumes energy from the battery. Should self-tests be carried
out more often than the maximum allowed, the battery life-time might be shorter
than specified.
B. Self-test procedure
• Check that the antenna is correctly connected
Do not perform self-test without antenna connected.
• Tune aircraft radio to 121.5 MHz and ensure you can hear it.
• Switch from position "OFF" to position "ARM" or press RESET & TEST on
the Remote Control Panel (ensure that the ELT switch is in position
"ARM").
• Listen for the buzzer or watch the LED - it operates during the whole Selftest procedure. Close to the end of self-test a short (3 sweeps) 121.5
transmission is made - confirm this on the aircraft radio.
• 10 seconds after the beginning of the self test, the test result is displayed
with the red visual indicator and the buzzer will sound:
• One long flash (duration 1 seconds) indicates that the system is
operational and that no error conditions were found.
• A series of short flashes (200 ms) indicates the test has failed.
Remark: The number of flashes gives an indication of the faulty
parameter detected during the self-test.
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AF INTEGRA / AF-H INTEGRA ELT
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JUN 20/2013
If self-test fails, contact the distributor as soon as possible. Unless a
waver is granted, flight should be cancelled (refer to National Aviation
Authorities).
2. Operational tests
These tests must be performed by maintenance personnel when performing
the first power up procedure or to check the transmitter (Refer to B. Test of
transmitted signals).
A. ELT operational tests
NOTE: ELT operational tests only provide the aircraft operator with an indication that the ELT is transmitting; however, a positive result cannot be interpreted as meaning that the ELT meets all operational parameters.
• connect the outside antenna to J2;
• switch the ELT from OFF to ARM;
• check that the Self-Test result is OK (one long flash).
B. Test of transmitted signals
(1) 406 MHz Transmission tests
This test should be carried out with a COSPAS-SARSAT decoder.
Note: If a COSPAS-SARSAT decoder is not available, the coding sheet
supplied by the programmer for the beacon (or dongle) with the
corresponding CSN proves that the beacon (or dongle) is correctly
programmed. Skip to § (2) 121.5 MHz
• Perform self-test (switch ELT from OFF to ARM).
• Check with the COSPAS-SARSAT decoder that, except for the 5th and the
6th digits, the decoded message is identical to the programmed message.
NOTE:The message transmitted during self-test sequence always begins with
FF FE D0 whereas a programmed message begins with FF FE 2F.
Example of message programmed in ELT:
3+1 LOW BATTERY VOLTAGE
3+2 LOW RF POWER
3+3 FAULTY VCO LOCKING (FAULTY FREQUENCY)
3+4 NO IDENTIFICATION PROGRAMMED
3+5 FAULTY VSWR (EXT. ANTENNA)
3+6 INTERNAL GPS SERIAL LINK
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AF INTEGRA / AF-H INTEGRA ELT
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FF FE 2F 96 E3 AF 0F 0F 7F DF FF 62 60 B7 83 E0 F6 6C
Example of same message decoded by Cospas-Sarsat Decoder:
FF FE D0 96 E3 AF 0F 0F 7F DF FF 62 60 B7 83 E0 F6 6C
NOTE: for location protocol beacons, the content of the encoded position data
field of the self-test message shall be the default values (extract from C/S T001
Cospas Sarsat.
(2) 121.5 MHz Transmission tests
This test must be carried out with a VHF receiver either with the aircraft VHF
receiver or with a not on-board VHF receiver.
IMPORTANT: Aircraft VHF receiver may be used only if 406 MHz test was
carried out with a Cospas-Sarsat decoder, otherwise check 121.5 MHz
using a VHF receiver (not the on-board VHF receiver) several dozens
meters away from the antenna. This ensures to validate the antenna.
• Tune VHF receiver to 121.5 MHz;
• Start transmission:
- Switch ELT to ON.
• Only 2 "sweep tones" are heard after 5 seconds, then the 121.5 MHz
stops.
• Stop transmission:
- Switch to OFF;
- continue to listen to 121.5 MHz for a few seconds to ensure that the ELT
does not continue to transmit after the test is terminated.
IMPORTANT: If the ELT operates for approximately 50 seconds, a 406
MHz signal is transmitted and is considered valid by the satellite system.
Switch ELT to ARM.
This check shall only be conducted during the first five minutes of any UTC,
(co-ordinated universal time) hour, and restricted in duration to not more than
five seconds. Be sure to notify any nearby control tower of your intentions.
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JUN 20/2013
TROUBLESHOOTING
1. General
Procedure for fault isolation onboard uses the indicator light (red visual
indicator) of the ELT’s front panel. This indicator light is activated by a self-test
capability within the ELT.
2. Faults on Self-test
When the self-test is carried out, the number of flashes on ELT or RCP’s visual
indicator gives an indication of the faulty parameter detected during the selftest.
(1)3+1 flashes
- Low battery voltage:
Replace battery: refer to relevant CMM for tests and repair.
(2) 3+2 flashes
- Low RF power:
Check 406 MHz power: refer to relevant CMM for tests and repair.
(3) 3+3 flashes
- Faulty VCO locking (faulty frequency):
Check frequencies: refer to relevant CMM for tests and repair.
(4) 3+4 flashes
- No identification programmed
Check programming:refer to relevant CMM for tests and repair.
(5) 3+5 flashes
- VSWR Fault
Check correct connection of antenna
Perform a VSWR measurement
(6) 3+6 flashes
- Internal GPS serial link fault
Check GPS receiver: refer to relevant CMM for tests and repair.
Note: for CMM download and other servicing instructions, refer to Service &
Support section of Kannad Aviation website.
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SCHEMATICS & DIAGRAMS
1. Outline dimensions and weight with mounting bracket AF-COMPACT
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
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JUN 20/2013
2. Outline dimensions and weight with universal mounting bracket
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
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JUN 20/2013
3. AF INTEGRA / AF INTEGRA (ER), axis of installation
OPERATION MANUAL
AF INTEGRA / AF-H INTEGRA ELT
PAGE: 504
JUN 20/2013
4. AF-H INTEGRA / AF-H INTEGRA (ER), axis of installation
OPERATION MANUAL
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JUN 20/2013
SERVICING
1. Maintenance Schedule
A. Periodic inspection
Note: (if required by the relevant Civil Aviation Authority).
Some Civil Aviation Authorities may require the ELT be tested periodically.
In this case, refer to Service Letter SL S1840501-25-05 "Guidelines for periodic
inspection" available on the Service & Support section of Kannad Aviation
Website.
B. Battery replacement
Testing of various elements and parameters of the ELT is mandatory when the
battery is replaced.
• For battery replacement interval, Refer to § 2. Battery replacement
requirements, page 602.
• The testing procedure associated with the battery replacement is
described in the relevant CMM
For CMM download and other servicing instructions, refer to Servcie & Support
section of Kannad Aviation Website.
Battery replacement:
carried out by an accredited PART 145 or FAR 145 (or equivalent)
maintenance station.
Periodic inspection:
depending if the ELT is opened or not, PART 145 or FAR 145 (or
equivalent) may be required. Refer to local regulations
OPERATION MANUAL
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JUN 20/2013
2. Battery replacement requirements
Battery replacement is mandatory:
• after more than 1 hour of real transmission (cumulated duration);
• before or on the battery expiration date;
• after use in an emergency;
• after an inadvertant activation of unknown duration.
Battery available from any Kannad Aviation distributor or dealer.
List of distributor available on our Web site: http://www.kannadaviation.com
Orolia S.A.S.
Z.I. des Cinq Chemins CS10028
56520 GUIDEL - FRANCE
Telephone: +33 (0)2 97 02 49 49 Fax: +33 (0)2 97 65 00 20
Web: http://www.kannadaviation.com
E-mail: contact@kannadaviation.com
Support: support.sar@orolia.com Tel.: +33 (0)2 97 02 49 00
Only original and approved battery pack included in battery KIT
BAT200 (P/N S1840510-01) supplied by Orolia S.A.S. can be installed.
[SAFT-FRIWO , Lithium Manganese Dioxide, 2 x M20 (D-type) cells]
PLEASE CONTACT YOUR LOCAL DISTRIBUTOR
Orolia S.A.S. refuse all responsibility and invalidate
all warranty should other packs be installed.
DOC09078D
Ref:0146257D
Distributed by
Manufactured by
Orolia S.A.S.
Z.I. des Cinq Chemins CS10028
56520 GUIDEL - FRANCE
Tél. / Phone : +33 (0) 2 97 02 49 49
Fax : +33 (0) 2 97 65 00 20
A Company of the Orolia Group
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