DESCRIPTION, OPERATION, INSTALLATION AND
DESCRIPTION, OPERATION, INSTALLATION ANDMAINTENANCE MANUALME406 ELT570-1600 Rev. GProprietary InformationThis document discloses subject matter in which Artex Aircraft Supplies, Inc. has proprietaryrights. Neither receipt nor possession thereof confers or transfers any right to reproduce ordisclose the document, any part thereof, any information therein, or any physical article ordevice, or practice any method or process except by written permission from or writtenagreement with Artex Aircraft Supplies, Inc.
ARTEX AIRCRAFT SUPPLIES, INC.570-1600Revision HistoryREVISIONCHANGEDATERELEASE06-30-05ADCN 267011-17-05BDCN 277705-01-06CDCN 284708-21-06DDCN 300705-21-07EDCN 307609-27-07FDCN 318203-03-08GDCN 322705-19-08GDCN 341303-30-09i
ARTEX AIRCRAFT SUPPLIES, INC.570-1600Table of Content1.Introduction, Description and Operation . 11.1Basic Information . 11.2Application . 11.3Description. 21.4Certification. 21.5Programming . 31.6Operation. 41.6.1 Accuracy . 51.6.2 Switch Operation . 51.6.3 Self-Test mode . 52.Installation for the United States. 72.1Introduction to Installation. 72.2Parts List. 8Table 1 – Parts List . 82.3Mount ELT . 92.4Mount Antenna. 142.4.1 ‘Whip’ Antenna – P/N 110-773 . 152.4.1.1Type of Aircraft . 152.4.1.2Location . 152.4.1.3Preparation . 152.4.1.4Installation . 152.4.1.5Composite Aircraft Installation . 162.4.2 Rod Antenna – P/N 110-338 . 162.4.2.1Location . 162.4.2.2Installation Preparation . 162.4.2.3Type of Aircraft . 162.4.2.4Installation . 162.4.2.5Composite Aircraft Installation . 172.5Mount Remote Switch . 172.6Mount Audio Indicator (“buzzer”) . 182.7Cable harness and Wiring. 182.7.1 Harness Wiring – Remote switch end . 192.7.2 Harness Wiring – ELT End . 192.7.3 Connect harness . 202.7.4 Connect RF Coaxial Cable . 252.7.5 Coax Cable Assembly (Optional) . 252.7.5.1Low Loss Coax Cable (Optional). 252.8Transmitter Test. 262.8.1 Self-Test. 262.8.2 Self-Test Schedule . 272.9Sealing Connectors in Wet Environments . 272.10 Helicopter installations . 28ii
ARTEX AIRCRAFT SUPPLIES, INC.570-16003.Registration . 303.1FAA Form 337 . 303.2Radio Station License - USA . 303.3U.S.A.A Registration . 313.4Canadian Registration . 333.5Other Country Registration. 334.Maintenance . 344.1Periodic Maintenance for the United States . 344.2Canadian Maintenance Requirements. 344.2.1 Regulations . 344.2.2 Performance Test. 354.2.2.1Peak Power Check . 354.2.2.2Frequency Check . 354.2.2.3Audio Modulation Check . 364.2.2.4Current Draw Check. 364.2.2.5Automatic Activation System Check. 364.3Periodic Maintenance – Other Countries . 364.4Maintenance Steps . 364.4.1 Remove ELT Connections . 364.4.2 Remove ELT . 364.4.3 Corrosion Inspection . 374.4.4 Battery Removal . 374.4.5 Battery replacement. 374.4.6 G-Switch Check. 414.4.7 Reinstall ELT. 424.4.8 Antenna Test . 424.4.9 Installed Transmitter Test (Self-Test) . 424.4.10Verification of Digital Message. 444.4.11Verify Registration . 454.4.12Logbook Entry. 454.4.13Shipping Instructions . 455.Troubleshooting Guide . 46Table 2 – Troubleshooting Guide . 46Table 3 – Troubleshooting Guide (continued) . 475.1Special Precautions for Electro-Static Discharges (ESD). 476.Specifications . 486.1Operating Frequencies . 486.2Output Power. 486.3Activation. 486.4Temperature . 486.5Input Power . 486.6Mechanical Characteristics. 496.7Electrical Characteristics. 496.8Coax . 49iii
ARTEX AIRCRAFT SUPPLIES, INC.6.96.106.116.127.iv570-1600Software . 49Weights . 49Table 4 – Weights. 49Electrical Loading of Aircraft System . 50Table 5 - Electrical Loading of Aircraft System . 50ME406 Series DO-160D Environmental Qualification Form. 58Table 6 – Environmental Qualification . 58Glossary . 59
ARTEX AIRCRAFT SUPPLIES, INC.570-1600Table of FiguresFigure 1 – ME406 Installed View . 4Figure 2 – ELT Front View. 6Figure 3 – Mounting Hole Diagram for Artex 110 Series and Narco ELT . 11Figure 4 – Mounting Hole Diagram for Artex 200 Series . 12Figure 5 – Mounting Hole Diagram for Pointer. 13Figure 6 – Antenna Ground Plane. 14Figure 7 – Remote Switch Placard . 17Figure 8 – ELT Connector (Front View of ELT). 21Figure 9 – Remote Switch Wiring . 22Figure 10 – Wiring Diagram: Metal Airframe . 23Figure 11 – Wiring Diagram: Metal Airframe . 23Figure 12 – Wiring Diagram: Composite Airframe . 24Figure 13 – Wiring Diagram: Composite Airframe . 24Figure 14 – ME406HM Helicopter Installation . 29Figure 15 – Spare Battery Pack Label . 39Figure 16 – ELT Battery Installation/Removal Exploded View . 40Figure 17 – Sample Battery Pack Labels . 40Figure 18 – Battery Pack 452-6499. 51Figure 19 – Audio Indicator (“buzzer”) 452-6505. 52Figure 20 – Remote Switch 345-6196-04 . 53Figure 21 – Whip Antenna 110-773 . 54Figure 22 – Rod Antenna 110-338. 55Figure 23 – Mounting Tray (452-3034) . 56Figure 24 – ME406 Series Outline Drawing . 57v
ARTEX AIRCRAFT SUPPLIES, INC.1.Introduction, Description and Operation1.1Basic Information570-1600This manual describes the operation, installation and maintenance of the Artex models ME406and ME406HM emergency locator transmitters (ELTs). The information is provided to ensureinitial and continued airworthiness. Information presented in this manual is accurate at time ofprinting, but is subject to change. Refer to the Artex web site at www.artex.net for the latestinformation and any updates to this manual.Web links provided in this manual were accurate at time of printing but may be subject tochange.Artex reserves the right to add approved components to the ELT installation system includingbut not limited to antennas, remote switches and coaxial cables. These changes are approvedas “minor changes” pursuant to FAR 21, Subpart O for TSO holders.Regulatory references are aimed at FAA and EASA requirements. Consult your national aviationauthority for requirements if you are located outside of a US or EASA member state.This edition contains information specific to installations in Canada.Application1.2This manual constitutes supporting data/documentation for installation.See section 3.1 of this manual (FAA Form 337) for a more detailed explanation of requireddocumentation.Canadian users must follow the requirements of Canadian Aviation Regulations Part V, CAR551.104. Other countries may have different requirements.The conditions and tests required for TSO approval of this article are minimum performancestandards. It is the responsibility of those installing this article either on or within a specific typeor class of aircraft to determine that the aircraft installation conditions are within the standardsapplicable to the TSO article including the integrated non-TSO function. TSO articles must haveseparate approval for installation in an aircraft. The article may be installed only if performedunder 14 CFR part 43 or the applicable airworthiness requirements.The ME406 or ME406HM ELT described in this manual was designed, tested and certified as acomplete system including the following components: ELTELTELTELTTransmitter w/ integral batteryMounting TrayAntennaRemote SwitchOnly Artex approved system components may be used for a TSO approved system.Page 1 of 60
ARTEX AIRCRAFT SUPPLIES, INC.570-1600Description1.3The ME406 and the ME406HM are type AF (automatic fixed) beacons.The ME406HM also features an additional 5 axis G-switch module that allows the ELT to beactivated in any of six axes. These 5 auxiliary “G” switches are a “non-TSO function” asdescribed in FAA Notice 8150.3. This “non-TSO” function has the following characteristics:1. The additional 5 auxiliary “G” switches provide crash sensing in the axes other than“forward” at a nominal 12 “G” threshold which may be encountered with rotor aircraft.There is no effect on any other performance specifications, software, hardware,environmental, or qualification levels.2. There are no additional interface requirements for the non-TSO function.3. There are no additional installation and operating instructions or limitations, or anyadditional instructions for continued airworthiness (ICA), for the non-TSO function.4. Artex has determined that there are no additional failure modes or hazards introducedby use of the non-TSO function.Inputs and outputs are protected against electrostatic discharge (ESD) and connections to 28Vor ground. If a terminal is inadvertently misconnected or a wire shorted, the ME406 will operatenormally after the condition has been corrected. The RF output is through a single BNCconnector.All functions of the ME406 or ME406HM are under microprocessor control. A self-test routinechecks ELT operation and installation, then presents the results as visual and auditory ‘errorcodes’ to aid in troubleshooting and to indicate status. Software is approved per therequirements of RTCA/DO-178B for Level D software.The battery pack consists of two D-size, lithium cells mounted in a cover assembly and is fieldreplaceable. Rated life is 6 years or one hour of use, which ever comes first, as specified by FAR91.207(c).Installation kits are available containing all major components needed to install the beacon.Certification1.4The ME406 (P/N 453-6603) and ME406HM (P/N 453-6604) are certified to the following: TSO C126TSO C91a in the 121.5/406 MHz configuration as referenced in TSO-C126, paragraph(e)FAR Part 91 – mandatory automatic ELT requirementsETSO 2C126Transport CanadaIndustry Canada (IC:121.5B-ME406AF)Page 2 of 60
ARTEX AIRCRAFT SUPPLIES, INC. Note:570-1600COSPAS-SARSAT T.001 and T.00747 CFR Part 87 (FCC requirements)Per FCC regulations 47 CFR § 2.902, the ELT is tested per “Verification” method,the FCC does not issue certificates for ELTs. The FCC identifier grantee code forArtex is H4K.Programming1.5The ME406 or ME406HM is pre-programmed at the factory using a short message format. Thefollowing User Protocols are supported: Serial NumberTail Number24-Bit Aircraft AddressAircraft Operator Designator/Serial NumberThe ME406 does not currently support long message format or Location Protocols. For acomplete discussion of ELT programming protocols please see COSPAS-SARSAT documentsG.005 and T.001 available at www.cospas-sarsat.org.The United States accepts the above listed protocols. For use outside of the US, contact yourlocal civil aviation authority for accepted or required programming protocols.Page 3 of 60
ARTEX AIRCRAFT SUPPLIES, INC.570-1600Figure 1 – ME406 Installed View1.6OperationIn the event of a crash, the ME406 or ME406HM activates automatically (automatic fixed “AF”configuration), and transmits the standard swept tone on 121.5 MHz lasting until battery poweris gone. This 121.5 MHz signal is mainly used to pinpoint the beacon during search and rescueoperations.Page 4 of 60
ARTEX AIRCRAFT SUPPLIES, INC.570-1600In addition, for the first 24 hours of operation, a 406 MHz signal is transmitting at 50-secondintervals. This transmission lasts 440 ms and contains identification data programmed into thebeacon and is received by COSPAS-SARSAT satellites. The transmitted data is referenced in adatabase (maintained by the national authority responsible for ELT registration) and used toidentify the beacon and owner.1.6.1AccuracyDoppler positioning is employed using both 121.5 MHz and 406 MHz signals. Position accuracyof the 121.5 MHz signal is within an area of approximately 15-20 km radius about thetransmitter. Due to the better signal integrity of the 406 MHz, its location accuracy is within a 3km radius.1.6.2Switch OperationIn a crash, an acceleration activated crash sensor (G-switch) turns the ELT ‘ON’ automaticallywhen the ELT experiences a change in velocity (or deceleration) of 4.5 fps 0.5 fps. Activationis also accomplished by means of the cockpit mounted remote switch or the switch on the ELT.To deactivate the ELT set either switch to the ‘ON’ position, then back to ‘ARM’.The ELT does not have an ‘OFF’ position. Instead, a jumper between two pins on the front Dsub connector must be in place for the G-switch to activate the unit. The jumper is installed onthe mating half of the connector so that when the connector is installed, the beacon is armed.This allows the beacon to be handled or shipped without ‘nuisance’ activation (front connectorremoved).NOTE:The ELT can still be manually activated using the local switch on the front of theELT. Care should be taken when transporting or shipping the ELT to not movethe switch or allow packing material to become lodged such as to toggle theswitch.In the ME406HM, activation is also accomplished by any of the 5 auxiliary “G” switches at anominal 12 “G” level.1.6.3Self-Test modeUpon turn-off, the ELT automatically enters a self-test mode that transmits a 406 MHz testcoded transmission that monitors certain system functions before returning to the ‘ARM’ mode.The transmission is ignored by any satellite that receives this signal, but the ELT requires it tocheck output power and correct frequency. If the ELT is left activated for approximately 50seconds or greater, a distress signal is generated that is accepted by the satellites.In addition to 121.5 and 406 MHz signal integrity, other operating parameters are checkedduring the self-test. Error codes are then generated if other problems are found. The errorcodes are displayed by a series of “blinks” of the ELT LED, remote LED and audio indicator. Seeparagraph 4.4.9, Installed Transmitter Test, for more details and a description of the errorcodes.Page 5 of 60
ARTEX AIRCRAFT SUPPLIES, INC.NOTE:Any time the ELT is activated, it is transmitting a 121.5 MHz distress signal.Therefore, all activations of the ELT should be kept to a minimum. Local ornational regulations may limit testing of the ELT or impose special requirementsor conditions to perform testing. For the “Self-Test,” Artex recommends the ELTbe “ON” for no more than 5 seconds. Testing should occur during the first 5minutes after the hour.Figure 2 – ELT Front ViewPage 6 of 60570-1600
ARTEX AIRCRAFT SUPPLIES, INC.2.Installation for the United States2.1Introduction to Installation570-1600Installations must be made by qualified personnel in accordance with FAA regulations.Duplicating a previous installation may not be acceptable. Refer to the following: FAA – Advisory Circular (AC) 43.13 (Acceptable Methods, Techniques, and Practices– Aircraft Alterations), specifically, Chapters 1 through 3, 11 and 13.Found at www.faa.gov, or specifically:http://www.airweb.faa.gov/Regulatory and Guidance 6256A54006E47B2?OpenDocumentTSO C126 paragraph D Requirements:“The conditions and tests required for TSO approval of this article are minimumperformance standards. It is the responsibility of those desiring to install thisarticle on a specific type or class of aircraft to determine that the aircraftinstallation conditions are within the TSO standards. The article may beinstalled only if further evaluation by the applicant documents an acceptableinstallation and it is approved by the administrator.”Found at www.faa.gov/certification/aircraft/ RTCA DO-182 recommends:“All ELT system components which must survive a crash intact, should beattached to the airframe in such a manner that the attachment system cansupport a 100g load in the plus and minus directions of the three principalaxes of the aircraft.”RTCA documents may be obtained from:RTCA, Inc.1828 L Street, NWSuite 805Washington, DC 20036Tel: 202-833-9339Fax: 202-833-9434Web site:www.rtca.orginfo@rtca.orgE-mail:NOTE 1: Installation in a pressurized aircraft constitutes a major modification. Consult theDepartment of Transportation Regional Officer before proceeding.NOTE 2: Aircraft manufacturers may also have guidance on ELT installation; refer to andfollow any applicable Type Approval or STC data for your aircraft. If locatedoutside of the US, follow all applicable regulations for your national authority.Page 7 of 60
ARTEX AIRCRAFT SUPPLIES, INC.2.2570-1600Parts ListInstallation kits offered for the ME406 include the necessary ELT-related components. Thetable below lists typical options. Parts can be ordered separately. Additional parts may also beavailable. Contact Artex at 1-800-547-8901 for details, pricing and availability.ItemOption / NotesP/NME406453-6603 (standard model)ME406HM453-6604 (helicopter model)Battery PackKit, see Battery Replacementsection of this manual455-0012Mounting trayOne option available452-3034Wire whip (15”)110-773 rev B (Figure 21,supersedes 110-773 rev A)Rod110-338 (Figure 22)Antenna cable, coaxial, BNCto BNC6’ (Other lengths availableupon request)611-6013-04ELT Installation Kit for usewith standard cock-pit remoteswitchMounting hardware &Connector kit455-7423ELT w/ battery packAntennaStandard Model CockpitRemote SwitchSwitch only345-6196-04 (Figures 9 & 20)Switch Installation kit455-6196Audio indicatorOne option available452-6505 (Figure 19)ManualLatest version available fordownload at www.artex.net570-1600Current measurement adapterAvailable to aid Canadianmaintenance requirements500-0057D-subminiature connector –15-pin, receptacleFor:- harness plug replacement- G-switch loop test fixture150-1130Table 1 – Parts ListPage 8 of 60
ARTEX AIRCRAFT SUPPLIES, INC.570-1600Additional items required. In addition to the kit, the following are examples of parts andtools that may be required, but are not provided: Miscellaneous tools: Drill, Phillips screwdriver (#2 bit), center punch, wire stripper,wrenches for aircraft disassembly/assemblySoldering iron & solderMetal & fabricating tools/equipment to fabricate ELT and audio indicator mounts1/2 A slow-blow fuse and holder (or comparable circuit breaker) for cockpit remoteindicatorShielded cable for remote switch harnessHarness securing fasteners / materialsMiscellaneous hookup wire – 22 AWG (typical)Molex connector pin crimp tool P/N HTR1719C (generic P/N 11-01-0008) orequivalentTerminal extraction tool – Molex P/N 11-03-0002 or equivalentElectronics grade RTV for sealing connector pinsTools to install antenna, ELTMounting bracketsMount ELT2.3Three separate mounting-hole patterns are provided so that, if the ME406 or ME406HM isreplacing an existing ELT indicated on the list below, the original mounting holes can be used.Remove the old ELT holder or tray and install the ME406 mounting tray in its place. Use the 832 X 5/8” Phillips, pan-head screws, nuts and flat washers provided. You may provide yourown hardware so long as the correct size and type is used. Mounting screws are English 8-32or M4 x length as required. Stainless steel hardware is recommended. Use hardwareconforming to an accepted standard such as AN or Mil-Spec.Compatible patterns include: Artex 100/110, G406, C406 and B406 series and Narco ELT-910, ELT-10Artex ELT-200 seriesPointer model ELT 3000-seriesIf this is a new installation or if the current installation is unacceptable, find a location per thefollowing: RTCA suggests the aft section of the fuselage. Statistically, this is least likely toreceive damage in a crash. It is also near the antenna connection, minimizing cablelength between the transmitter and antenna.Maintain access for maintenance.If possible, avoid locating the ELT where it will be subjected to chemical fluids suchas deicing compounds, cleaning fluids, etc. Over time, these chemicals may attackthe plastic and metal components.Page 9 of 60
ARTEX AIRCRAFT SUPPLIES, INC.570-1600The mounting location must conform to the requirements of RTCA DO-204 and AC 43.13. DO204 Sec 3.1.8 states:“The ELT shall be mounted to primary aircraft load carrying structures such astrusses, bulkheads, longerons, spars, or floor beams (not aircraft skin). Themounts shall have a maximum static local deflection no greater than 2.5 mm(0.1 in.) when a force of 450 Newtons (100 lbs) is applied to the mount in themost flexible direction. Deflection measurements shall be made with referenceto another part of the airframe not less than 0.3 meters (1-foot) nor more than1.0 m (three feet) from the mounting location.”Mount the ELT so that the longitudinal axis of the ELT (the ax
The ME406 or ME406HM ELT described in this manual was designed, tested and certified as a complete system including the following components: ELT Transmitter w/ integral battery ELT Mounting Tray ELT Antenna ELT Remote Switch Only Artex approved system components may be used for a TSO approved system. Page 1 of 60
5.3. STAFInst Uninstall 6. Platform Installation Notes 6.1. Linux installation 6.2. AIX installation 6.3. HP-UX IA64 64-bit installation 6.4. IBM i 32-bit (previously known as i5/OS or OS/400) installation 6.5. z/OS installation 6.6. FreeBSD installation 6.7. Mac OS X installation 6.8. Solaris installation 7. Environment Variable Settings 7.1.
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