ARTEX Cobham ME-183 NAV User manual

DESCRIPTION, INSTALLATION, OPERATION, AND
MAINTENANCE MANUAL
ME-183 NAV INTERFACE 453-0012
Docume t No.: 570-0001 Rev. -
Cobham Avio ics
Artex Products
Artex Aircraft Supplies, I c.
doi g busi ess as Cobham Avio ics
14405 Keil Road NE Aurora, Orego 97002 USA
Pho e 503-678-7929, Fax [phone]
E-mail i fo@artex. et
www.artex. et

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REVISION HISTORY
REVISION ENGINEERING CHANGE ORDER DATE
- RELEASE 07/14/09

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TABLE OF CONTENTS
1. INTRODUCTION................................................................................................................... 5
1.1 S YSTEM A DVA TAGES ...........................................................................................................5
1.2 S YSTEM D ESCRIPTIO ..........................................................................................................6
1.3 O PERATIO AL O VERVIEW ......................................................................................................6
1.4 C OMPATIBILITY ..................................................................................................................7
2. INTEGRATION...................................................................................................................... 8
2.1 D ATA O UTPUT R EQUIREME TS ................................................................................................8
2.2 MEA 0183 S E TE CE S TRUCTURE R EQUIREME TS .....................................................................8
3. OVERVIEW ........................................................................................................................... 9
3.1 R EGULATORY R EQUIREME TS .................................................................................................9
3.2 I STALLATIO ....................................................................................................................9
3.3 E LECTROSTATIC D ISCHARGE (ESD) P RECAUTIO S ........................................................................9
4. INSTALLATION .................................................................................................................. 10
4.1 I STALLATIO K IT .............................................................................................................10
4.2 ME406 ELT R EPROGRAMMI G .............................................................................................10
4.3 I STALLATIO I STRUCTIO S ...............................................................................................10
4.3.1 General Wiring and Grounding Considerations .......................................................10
4.3.2 Wiring Diagrams ................................................................................................11
4.3.3 GPS Data Output Interface with Remote Switch Harness ........................................12
4.3.4 DB15 Plug Replacement......................................................................................13
4.3.5 DB15 Plug Back Shell Sealing...............................................................................15
4.3.6 Final Installation ................................................................................................15
5. ME-183 NAV INTERFACE TESTING .................................................................................... 16
5.1 S ELF -T EST ......................................................................................................................16
5.1.1 Precautions .......................................................................................................16
5.1.2 Self-Test Procedure ............................................................................................16
5.2 P OSITIO D ATA V ERIFICATIO ..............................................................................................17
6. PERIODIC MAINTENANCE ................................................................................................. 18
6.1 I SPECTIO .....................................................................................................................18
6.2 T ESTI G .........................................................................................................................18
7. SPECIFICATIONS AND APPROVALS................................................................................... 19
7.1 E VIRO ME TAL R EQUIREME TS A D S PECIFICATIO S ................................................................19
7.2 P HYSICAL S PECIFICATIO S ...................................................................................................20
7.3 C OMMU ICATIO S S PECIFICATIO S ........................................................................................20
7.4 A PPROVALS .....................................................................................................................21
TABLES
T ABLE 4-1: ME-183 AV I STALLATIO K IT P ARTS L IST ...........................................................................10
T ABLE 5-1: ME406 ELT S ELF -T EST E RROR C ODES ...................................................................................16
T ABLE 7-1: RTCA DO-160F E VIRO ME TAL Q UALIFICATIO R EQUIREME TS .................................................19
T ABLE 7-2: E VIRO ME TAL S PECIFICATIO S .........................................................................................20
T ABLE 7-3: P HYSICAL S PECIFICATIO S ..................................................................................................20
T ABLE 7-4: C OMMU ICATIO S S PECIFICATIO S ........................................................................................20

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1. INTRODUCTION
This manual provides description, installation, operation, and maintenance information for
the ME-183 AV Interface (ME-183 AV). The ME-183 AV relays latitude and longitude
position data to the ELT for incorporation into the 406 MHz Search and Rescue (SAR)
satellite message. The ME-183 AV is designed as a retrofit accessory for Artex ME406
Series ELT installations.
1.1 System Adva tages
An ME406 ELT system, with the ME-183 AV interface retrofit kit installed, contains a
number of significant advantages over older technology ELT systems:
• Greater Position Accuracy (Figure 1-1)
• Position Data from a Single Beacon Transmission
• o Aircraft Power (power derived from GPS data output)
Figure
1
-
1
:
ELT Systems Accuracy Compariso

Page 6 of 21
1.2 System Descriptio
The ME-183 AV integrates with existing equipment, as illustrated in Figure 1-2.
Installation of the ME-183 AV requires an on-board navigation system (GPS)
supporting MEA 0183 output, in addition to an Artex ME406 ELT system. The GPS
receives satellite signal information, calculates latitude and longitude position, and sends
the position data to the ME-183 AV.
If the ELT is programmed with a short message (non-location protocol), it must be
reprogrammed to a long message (location protocol) in order to interface with the ME-
183 AV.
NOTE: The appropriate ME406 ELT user manual should be consulted for more detailed
information on ELT protocols and programming.
1.3 Operatio al Overview
The ME-183 AV receives power from the GPS receiver via its data output. Upon power
up, there is an initial 80-second charge time before the ME-183 AV can respond to an
ELT activation event.
The ME-183 AV periodically receives position data from the GPS receiver and converts
the position data to an ELT compatible format.
The ME-183 AV stores position data in RAM and waits for a signal from the ELT
indicating it has been:
• Activated automatically by the G-Switch, or
• Activated manually via the ELT local or cockpit remote switch.
As long as the ELT is activated and the GPS receiver continues to supply position data,
the ME-183 AV attempts to transmit current position data every 2 seconds; however,
the ELT locks position data upon activation and will only accept new data if it is reset
using the local or remote switch.
Figure
1
-
2
: ME
-
183 NAV
I terface System I tegratio
Block Diagram

Page 7 of 21
If the data link from the GPS to the ME-183 AV is lost, the ME-183 AV holds the last
known position data for 60 seconds, as required by C/S T.001 “Specification for
COSPAS-SARSAT 406 MHz Distress Beacons”, Subsection 4.5.5.4.
• The ELT must be activated within the 60-second timeframe for the ME-183 AV to
transmit position data to the ELT.
• After the 60-second timeframe has lapsed, the last known position is lost.
• The ELT transmits a default message if it does not receive valid position data.
1.4 Compatibility
The ME-183 AV is compatible with the following Artex ME406 Series ELTs:
• ME406 ELT – 453-6603
• ME406 HM ELT – 453-6604
• ME406P ELT – 453-6611

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2. INTEGRATION
This section describes GPS receiver and ME-183 AV integration requirements. Consult
your navigation system manufacturer’s user manual to determine if data output and
sentence structure formats are compatible with the following requirements.
The ME-183 AV is compatible with MEA 0183. Artex recommends the use of a
dedicated GPS data output channel for the ME-183 AV.
2.1 Data Output Requireme ts
In order to receive data, the ME-183 AV requires:
• Baud Rate (fixed): 4800
• Parity: one
• Data Bits: 8
• Stop Bits: 1
2.2 NMEA 0183 Se te ce Structure Requireme ts
The ME-183 AV accepts the following MEA 0183 sentences:
• GPRMC
• GPGLL

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3. OVERVIEW
This section provides an installation overview and should be reviewed by personnel
performing the work.
3.1 Regulatory Requireme ts
TSO C126, Paragraph D
“The conditions and tests required for TSO approval of this article are minimum
performance standards. It is the responsibility of those desiring to install this article
on a specific type or class of aircraft to determine that the aircraft installation
conditions are within the TSO standards. The article may be installed only if further
evaluation by the applicant documents an acceptable installation and it is approved by
the administrator.”
FAA Requireme ts
In addition to the procedures outlined herein, the installer must adhere to the guidelines
established in FAA Advisory Circular (AC) 43.13 “Acceptable Methods, Techniques and
Practices Aircraft Alterations”, specifically Chapters 1 through 3, 11 and 13.
By signing the aircraft logbook or FAA Form 337, you are stating the installation has
been performed in accordance with current FAR requirements and the steps and
procedures outlined herein.
3.2 I stallatio
The ME-183 AV plugs into the ELT, between the remote switch harness DB15 plug and
the ELT.
• Data output from the GPS interfaces with the ME-183 AV at the DB15 plug.
• An installation overview is shown in Figure 3-1.
REMOTE SWITCH
HAR ESS
DB15 PLUG
ME406 ELT
ME-183 AV
THUMBSCREW (typ.)
Figure 3-1: I stallatio Overview
3.3 Electrostatic Discharge (ESD) Precautio s
The ME-183 AV is an electrostatic discharge sensitive (ESDS) device. As such, it must
be handled with care. If possible, wear a grounded wrist strap or ESD protective
footwear when handling the ME-183 AV during installation and maintenance activities.
Take particular care to avoid touching the exposed metal portion of the connectors and
exposed receptacle pins on the ME-183 AV and ELT.

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4. INSTALLATION
The following subsections provide detailed installation instructions for the ME-183 AV.
Consult AC 43.13 for general guidelines pertaining to installation, wiring, soldering, and
grounding.
4.1 I stallatio Kit
The ME-183 AV Installation Kit (455-0016) details are shown in Table 4-1.
Table 4-1: ME-183 NAV I stallatio Kit Parts List
PART NUMBER DESCRIPTION QTY
150-1127 D-Sub Housing, 15-Pin, Grommet 1
150-1130 Plug, D-Sub, 15-Pin 1
217-0001 Thumbscrew, ME-183 AV Interface 2
453-0012 Main Assembly, ME-183 AV Interface 1
570-0001 Manual, ME-183 AV Interface Description, Installation,
Operation, and Maintenance 1
850-0814 Sealant Strip, D-Sub Connector 4*
* 1 ea. provided as a spare
4.2 ME406 ELT Reprogrammi g
The ELT must be programmed with a long message (location protocol), if necessary,
before installing the ME-183 AV. ELT reprogramming may be accomplished by an
authorized service center or by using an Artex ME406 Reprogramming Adapter (455-
6600).
4.3 I stallatio I structio s
The following subsections provide installation guidelines and instructions. Differences in
shielded and unshielded installations are noted, where applicable.
4.3.1 Ge eral Wiri g a d Grou di g Co sideratio s
WARNING:
If ground or other connections are broken or otherwise damaged, the
ELT is still capable of automatic activation; however:
• The remote switch may be incapable of resetting the ELT,
• Operation may not be indicated on the remote switch LED, and/or
• The ME-183 AV may not receive position data.
WARNING: It is possible to inadvertently activate the ELT when working on the
remote switch wiring harness and/or installing the ME-183 AV. Always keep an AM
or aircraft radio tuned to 121.5 MHz during installation, such that an audible alert
(i.e., transmission sweeps) can be heard immediately.
The following wiring and grounding considerations are applicable.
• Minimum 24 AWG wire size.
• Shielding is recommended to help prevent EMI and RF interference.
• Use high quality conductor meeting MIL-W-16878, M22759, M27500, or a
commercial equivalent acceptable for use in aircraft applications.

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• Make a “Drip Loop” in the remote switch harness connection to the ME-183 AV
to divert moisture from the DB15 plug.
NOTE: A drip loop is an extra length of cable formed into a U-shaped bend just
before the plug. Water or other fluids flow down to the bottom of the loop and
drip off, diverting them away from the plug.
• GPS ground must be common to aircraft ground.
4.3.2 Wiri g Diagrams
The following wiring diagrams are applicable as noted:
• Figure 4-1 – Installation using a shielded harness in a metal airframe
• Figure 4-2 – Installation using an unshielded harness in a metal airframe with no
harness ground conductor
• Figure 4-3 – Installation using an unshielded harness in a metal airframe with a
harness ground conductor
• Figure 4-4 – Installation in a composite airframe
+14V
+28V
RED+ BLK -
HOR
452-6505
GPS TX
RESET 1
RESET 2
EXTER AL O
GSW0
GSW1
GROU D
LIGHT
AUDIO POWER
OTE: PI S 6 & 9
ARE I TER ALLY
TIED WITHI THE
REMOTE SWITCH
ASSEMBLY
SHIELD USED AS
GROU D WIRE
CABLE
SHIELD
U -SWITCHED
POWER
9
6
13
14
5
12
7
2
8
5
2
7
1
3
6
8
9
FROM GPS DATA OUTPUT
OTE: /C PI S
1, 3, 4, 10, 11, 13
OTE: GPS GROU D MUST BE
COMMO TO AIRCRAFT GROU D
DB15
PLUG
REMOTE SWITCH
MOLEX PLUG
+14V
+28V
RED+ BLK -
HOR
452-6505
GPS TX
RESET 1
RESET 2
EXTER AL O
GSW0
GSW1
GROU D
LIGHT
AUDIO POWER
OTE: PI S 6 & 9
ARE I TER ALLY
TIED WITHI THE
REMOTE SWITCH
ASSEMBLY
U -SWITCHED
POWER
9
6
13
14
5
12
7
2
8
FROM GPS DATA OUTPUT
OTE: /C PI S
1, 3, 4, 10, 11, 13
OTE: GPS GROU D MUST BE
COMMO TO AIRCRAFT GROU D
DB15
PLUG
REMOTE SWITCH
MOLEX PLUG
5
2
7
1
3
6
8
9
Figure
4
-
1
: Metal Airframe I stallatio w/Shielded Har ess
Shield Used as Grou d Co ductor
Figure
4
-
2
: Metal Airframe I
stallatio w/U shielded Har ess
No Har ess Grou d Co ductor

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+14V
+28V
RED+ BLK -
HOR
452-6505
GPS TX
RESET 1
RESET 2
EXTER AL O
GSW0
GSW1
GROU D
LIGHT
AUDIO POWER
OTE: PI S 6 & 9
ARE I TER ALLY
TIED WITHI THE
REMOTE SWITCH
ASSEMBLY
U -SWITCHED
POWER
9
6
13
14
5
12
7
2
8
FROM GPS DATA OUTPUT
OTE: /C PI S
1, 3, 4, 10, 11, 13
OTE: GPS GROU D MUST BE
COMMO TO AIRCRAFT GROU D
DB15
PLUG
REMOTE SWITCH
MOLEX PLUG
5
2
7
1
3
6
8
9
+14V
+28V
RED+
BLK-
HOR
452-6505
FROM GPS DATA OUTPUT
DB15
PLUG
REMOTE SWITCH
MOLEX PLUG
GPS RS-232 TX
RESET 1
RESET 2
EXTER AL O
GSW0
GSW1
GROU D
LIGHT
AUDIO POWER
OTE: PI S 6 & 9
ARE I TER ALLY
TIED.
SHIELD USED AS
GROU D WIRE
CABLE
SHIELD
U -SWITCHED
POWER
9
6
13
14
5
12
7
2
8
5
2
7
1
3
6
8
9
OTE: /C PI S
1, 3, 4, 10, 11, 13
OTE: GPS GROU D MUST BE
COMMO TO AIRCRAFT GROU D.
OTE: IF U SHIELDED HAR ESS IS I STALLED, A
GROU D CO DUCTOR BETWEE DB15 PLUG PI 7
A D MOLEX PLUG PI 6 IS REQUIRED
4.3.3 GPS Data Output I terface with Remote Switch Har ess
Referring to the wiring diagrams in Subsection 4.3.2, install a GPS data output
conductor as follows:
1. Run a minimum 24-AWG conductor from the GPS data output to the remote switch
harness DB15 plug.
2. Connect the GPS end of the data conductor in accordance with the GPS
manufacturer’s recommendations.
3. Disconnect the harness DB15 plug from the ELT.
4. Perform the following steps if the back shell of the DB15 plug has not been filled
with RTV or other potting compound. If the plug back shell is potted, proceed to
Step 5.
a) Strip the insulation from the conductor back approximately 1/8” (0.125”).
b) Solder the conductor into the Pin 9 solder cup of the plug in accordance with
the wiring diagrams shown in Subsection 4.3.2.
Figure
4
-
3
: Metal Airframe I stallatio w/U shielded Har ess
With Har ess Grou d Co ductor
Figure
4
-
4
: Composite Airframe w/Shielded Har ess
Shield Used as the Grou d Co ductor (See Diagram ote)

Page 13 of 21
c) Provide adequate strain relief for the conductor.
d) Reassemble the back shell in accordance with Subsection 4.3.4, beginning with
Step 8.
NOTE: Artex recommends sealing the plug back shell in accordance with
Subsection 4.3.5.
5. Cut off the harness DB15 plug.
6. ote the conductor color coding and pin relationships using a multimeter or other
means of checking continuity.
7. Replace the DB15 plug following the instructions in Subsection 4.3.4.
4.3.4 DB15 Plug Replaceme t
Referring to the wiring diagrams in Subsection 4.3.2 and Figure 4-5, install a new
DB15 plug on the harness as follows:
1. Select a rubber grommet, supplied as part of the D-Sub housing kit (150-1127),
that fits snugly around the harness cable and other conductors.
2. Feed the cable and other conductors through the rubber grommet, such that the
raised collar end will fit inside the D-Sub housing, as shown in Figure 4-5 and
Figure 4-7.
3. Slide the grommet away from the cable and other conductor ends, such that it
does not interfere with soldering the conductors to the DB15 plug.
4. Strip insulation from the conductors back approximately 1/8” (0.125”).
5. Splice the horn ground conductor to the cable shield (Figure 4-1), or harness
ground conductor (Figure 4-3) near Pin 7 (Figure 4-6), such that one conductor is
terminated in Pin 7.
NOTE: For metal airframe installations with no conductor between Molex plug
Pin 6 and DB15 plug Pin 7, the horn ground conductor and DB15 plug Pin 7 are
grounded to the airframe (Figure 4-2).
Figure
4
-
5
:
DB15
Plug
Assembly
(Hor a d GPS co ductors ot show )
HOUSI G HALF (typ.)
HARDWARE (typ.)
DB15 PLUG
RAISED
COLLAR E D
THUMBSCREW (typ.)
BRACKET WASHER (typ.)
CABLE
GROMMET

Page 14 of 21
6. Solder a jumper between Pins 5 and 12 of the DB15 plug (Figure 4-6).
7. Solder the conductors into the solder cups of the DB15 plug (Figure 4-6).
NOTE: Check conductor color coding and pin relationships noted in Subsection 0,
Step 6, to ensure proper connection of the conductors.
8. Fit the plug into a housing half supplied as part of the D-Sub housing kit.
9. Position the grommet, such that it fits into the recess on the cable end of the D-
Sub housing, with the raised collar step against the housing inside face, as shown
in Figure 4-7.
10. Install the bracket washers, supplied as part of the D-Sub housing kit, onto the
thumbscrews (217-0001).
NOTE: The thumbscrews supplied with the housing kit are too short and are
replaced by the longer thumbscrews supplied as part of the ME-183 AV kit.
11. Set the thumbscrews in place on the housing half.
Figure
4
-
7
:
Cable Grommet Positio
HOUSI G
CABLE
GROMMET
RAISED
COLLAR E D
Figure
4
-
6
:
DB15
Plug
Pi Orie tatio
Pi positio umberi g is ide tical to that i scribed o the
fro t of the plug.
PI 9
PI 1
PI 8
PI 15

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12. Fit the other housing half into place, taking care to align the thumbscrews, bracket
washers, grommet, and plug.
13. Screw the housing halves together using the long, fully-threaded screws and nuts
supplied as part of the D-Sub housing kit.
14. Install the grommet clamp supplied as part of the D-Sub housing kit, around the
grommet.
15. Ring out the remote switch harness to verify correct pin to pin continuity.
Optionally, the system can be temporarily connected and operation checked via the
remote switch.
4.3.5 DB15 Plug Back Shell Seali g
Seal the plug back shell using Dow Corning
®
4 Electrical Insulating Compound, or an
equivalent meeting MIL-S-8660C.
1. Disassemble the D-Sub housing and remove a housing half.
2. Inject Dow Corning
®
4 into the back side of the plug, such that the insulating
compound surrounds the conductors and covers the back of the plug.
3. Reassemble the D-Sub housing (Subsection 4.3.4, Steps 8-14).
4.3.6 Fi al I stallatio
CAUTION
: When handling the ME-183 AV and ELT, take precautions in
accordance with Subsection 3.3, “Electrostatic Discharge (ESD) Precautions”.
Referring to Figure 4-8:
1. Install sealant strip (850-0814) in the
ELT DB15 receptacle as follows, if
one is not already installed from a
previous installation.
a) Peel a sealant strip off the plastic
sheet.
b) Press 2 sealant strips tacky side
against the male pins of the ELT
receptacle.
c) Peel the foam backing off the
sealant strip.
2. Plug the ME-183 AV into the ELT.
3. Install 1 sealant strip (850-0814) in the ME-183 AV DB15 receptacle, following
the procedures in Step 1.
4. Plug the harness into the ME-183 AV.
NOTE: Form a drip loop in the cable (Subsection 4.3.1).
5. Screw the thumbscrews into the ELT DB15 connector retaining nuts, making sure
the harness plug and ME-183 AV are seated properly in the receptacles.
Torque: 1 – 2 in-lbs
Figure
4
-
8
:
ME
-
183 NAV
Fi al
I stallatio

Page 16 of 21
5. ME-183 NAV INTERFACE TESTING
The purpose of this testing is to verify integrity of the ELT system after ME-183 AV
installation. This section also discusses the option of verifying position data transmission
using a beacon test set.
5.1 Self-Test
The following procedure initiates an ELT self-test routine to verify integrity of the ELT
system.
5.1.1 Precautio s
When the ELT is switched from O to ARM, it performs a self-test and a 406 MHz
signal is transmitted; however, the transmission is ignored by the SAR satellite system.
WARNINGS: Any time the ELT is activated, it is transmitting a 121.5 MHz signal.
Tests should be no longer than three audible sweeps (Subsection 5.1.2). Do OT
allow ELT activation to exceed 5 seconds.
After activation for approximately 50 seconds, the ELT transmits a 406 MHz signal,
which will be i terpreted as a actual emerge cy sig al.
CAUTION: Outside the United States, comply with local and/or national regulations
for testing of ELTs.
5.1.2 Self-Test Procedure
Initiate an ME406 ELT self-test as follows:
1. Tune a receiver, usually the aircraft radio, to 121.5 MHz.
2. Verify the on-board GPS is active and has acquired a valid position.
3. Allow 80 seconds after GPS activation for the ME-183 AV to charge.
4. Set the ELT remote switch to the O position and listen for 3 audio sweeps on the
radio, which takes approximately 1 second.
5. Set the switch back to the ARM (OFF) position and verify the switch panel LED
indicates a 1-pulse code (System OK).
• If multiple pulses (error codes) are displayed on the LED, refer to Table 5-1.
• Multiple error codes are displayed on the LED sequentially. For example, if a
3-pulse error and a 4-pulse error are detected, the LED will display the 3-
pulse code, followed by the 4-pulse code.
• Refer to the appropriate ME406 ELT user manual for a more detailed
explanation of error codes, their causes, and related troubleshooting
guidelines.
Table 5-1: ME406 ELT Self-Test Error Codes
PULSES PROBABLE CAUSE
1 System OK
3 Bad load detected
4 Low power detected

Page 17 of 21
PULSES PROBABLE CAUSE
5 o position data present or 406 MHz message not programmed
6 G-switch loop error
7 ELT battery usage over one hour
5.2 Positio Data Verificatio
Artex does not require this test be performed; any problem with received position data
will be indicated by the 5-pulse error (Table 5-1) during self-test (Subsection 5.1.2).
CAUTION: Artex only recommends this test be performed if the 406 MHz signal can
be properly shielded inside a screen room or container. If the 406 MHz “live” burst is
received by an SAR satellite, the sig al will be i terpreted as a actual
emerge cy sig al.
In order to read position data with a beacon test set, the following criteria must be met:
• The aircraft GPS system must be powered on for at least 80 seconds prior to ELT
activation, and
• The ELT must be active for at least 50 seconds, or until the first “live” 406 MHz
burst is transmitted and received by a beacon test set.
The “live” burst message will contain position data (i.e., latitude and longitude).

Page 18 of 21
6. PERIODIC MAINTENANCE
The following subsections describe periodic maintenance and testing requirements and
procedures for the ME-183 AV. Comply with these requirements at the same time
periodic maintenance and testing is performed on the ELT system.
6.1 I spectio
WARNING:
It is possible to inadvertently activate the ELT when working around the
ELT and/or removing and installing the ME-183 AV. Always keep an AM or aircraft
radio tuned to 121.5 MHz during maintenance activities, such that an audible alert
(i.e., transmission sweeps) can be heard immediately.
CAUTION : When handling the ME-183 AV and ELT, take precautions in accordance
with Subsection 3.3, “Electrostatic Discharge (ESD) Precautions”.
Perform the following inspections:
1. Remove the ME-183 AV.
2. Inspect unit for visible damage.
3. Inspect electrical connections for corrosion, bent or broken pins, and other evidence
of damage.
4. Check security and condition of the GPS data output connection.
5. Correct any discrepancies found.
6.
Reinstall the ME-183 AV.
6.2 Testi g
Perform an ELT self-test in accordance with the procedure set forth in Subsection 5.1.
Position data verification is optional and may be performed at the aircraft operator’s
discretion. In order to read position data, the criteria set forth in Subsection 5.2 must
be met.

Page 19 of 21
7. SPECIFICATIONS AND APPROVALS
The following subsections provide specifications and approval information for the ME-183
AV.
7.1 E viro me tal Requireme ts a d Specificatio s
Table 7-1 lists the environmental conditions testing required by RTCA DO-160F,
“Environmental Conditions and Test Procedures for Airborne Equipment”. Table 7-2
provides the ME-183 AV environmental specifications.
Table 7-1: RTCA DO-160F E viro me tal Qualificatio Requireme ts
CATEGORY SECTION DESCRIPTION
[(C4)(D1)] 4.0 Temperature and Altitude
X 4.5.4 In Flight Loss of Cooling
B 5.0 Temperature Variation
A 6.0 Humidity
[DO-204] 7.0 Shock
[DO-204] 8.0 Vibration
X 9.0 Explosion Proofness
S 10.0 Waterproofness
X 11.0 Fluids Susceptibility
X 12.0 Sand & Dust
X 13.0 Fungus Resistance
X 14.0 Salt Spray
X 15.0 Magnetic Effect
X 16.0 Power Input
X 17.0 Voltage Spike
Z 18.0 Audio Frequency Conducted Susceptibility
AC 19.0 Induced Signal Susceptibility
T 20.0 Radio Frequency Susceptibility
M 21.0 Emission of Radio Frequency Energy
X 22.0 Lightning
X 23.0 Lightning Direct Effects
X 24.0 Icing
X 25.0 Electrostatic Discharge
[DO-204] 26.0 Fire, Flammability
Note: X = ot Applicable

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Table 7-2: E viro me tal Specificatio s
PARAMETER CHARACTERISTICS
Storage Temperature -55° C to +85° C (-67º F to +185º F)
Operating Temperature -40° C to +70° C (-40º F to +158º F)
Altitude 50,000 ft (15,240 m)
Vibration 10 G from 5 Hz to 2,000 Hz
Shock 500 G for 4 ms / 100 G for 23 ms
Humidity 95% for 50 hours
Overpressure -15,000 ft (-4,572 m)
Decompression 50,000 ft (15,240 m)
Flammability <1 second (UL 94, V-0)
7.2 Physical Specificatio s
Table 7-3 provides physical data for the ME-183 AV.
Table 7-3: Physical Specificatio s
PARAMETER CHARACTERISTICS
Weight <4 oz (113 g)
Dimensions 1.8 x 1.5 x 0.7 in. (46 x 38 x 18 mm)
7.3 Commu icatio s Specificatio s
Table 7-4 provides communications requirements for the ME-183 AV.
Table 7-4: Commu icatio s Specificatio s
PARAMETER REQUIREMENT
GPS Data Output (NMEA 0183 Compatible)
Speed (Baud Rate) 4800
Parity one
Data Bits 8
Stop Bits 1
Se te ce Formats (NMEA 0183)
Sentences Accepted GPGLL, GPRMC