®

FlightMax
EX500-Series MFD

Installation Manual

P/N 600-00079-000
Rev 06
 Installation Manual
P/N 600-00079-000 Rev 06

Table of Contents

1. GENERAL INFORMATION .......................................................................................................................4

1.1. EQUIPMENT DESCRIPTION .....................................................................................................................5
1.2. TECHNICAL SPECIFICATIONS ..................................................................................................................5
2. INSTALLATION INSTRUCTIONS ............................................................................................................6
2.1. UNPACKING AND INSPECTION ................................................................................................................6
2.2. FLIGHTMAX EX500 MFD INSTALLATION ..............................................................................................7
2.2.1. EX500 Installation Considerations ............................................................................................7
2.2.2. Location and Viewing Angle .......................................................................................................7
2.2.3. Positioning and Mounting the EX500 Tray...............................................................................8
2.2.4. Electrical and Sensor Interface Wiring......................................................................................9
2.2.5. Electrical Load Analysis ............................................................................................................10
2.3. DATALINK ANTENNA INSTALLATION CONSIDERATIONS........................................................................10
2.3.1. Narrowcast Antenna Details.....................................................................................................10
2.3.2. Broadcast Antenna Details .......................................................................................................11
2.3.3. Weight and Balance ..................................................................................................................11
3. POST INSTALLATION CONFIGURATION GUIDE.............................................................................12
3.1. SYSTEM CONFIGURATION ....................................................................................................................12
3.1.1. Entering The Maintenance Mode ............................................................................................12
3.2. EX500 SENSOR INTERFACE SETUP ....................................................................................................13
3.2.1. EX500 Sensor Interface Provisioning Confirmation..............................................................13
3.2.2. Configuration Options................................................................................................................13
3.2.3. Configuration Selection .............................................................................................................19
3.3. GPS/FMS SYSTEM SETUP..................................................................................................................20
3.4. TRAFFIC SYSTEM SETUP ......................................................................................................................20
3.5. LIGHTNING SYSTEM SETUP ..................................................................................................................22
3.6. RADAR SYSTEM SETUP .....................................................................................................................23
3.6.1. RADAR System Calibration......................................................................................................26
3.6.2. Roll Trim Adjustment .................................................................................................................30
3.7. TAWS SYSTEM SETUP ........................................................................................................................30
3.8. NARROWCAST DATALINK SETUP .........................................................................................................30
3.9. BROADCAST DATALINK SETUP .............................................................................................................31
3.10. MAP HEADING SOURCE SETUP........................................................................................................31
3.11. BEZEL KEY DIMMING SETUP ............................................................................................................33
3.12. SYSTEM INFORMATION .....................................................................................................................34
4. EX500 MFD CHECKOUT.........................................................................................................................35
4.1. INITIAL INSTALLATION VALIDATION TEST..............................................................................................35
4.2. SENSOR COMMUNICATIONS CHECKOUT ..............................................................................................36
4.2.1. GPS/FMS Checkout ..................................................................................................................36
4.2.2. Lightning Sensor Checkout ......................................................................................................37
4.2.3. Traffic Sensor Checkout ...........................................................................................................38
4.2.4. TAWS Checkout.........................................................................................................................40
4.2.5. RADAR Checkout ......................................................................................................................41
4.2.6. Narrowcast Datalink Checkout.................................................................................................42
4.2.7. Broadcast Datalink Checkout...................................................................................................45
4.2.8. Broadcast Datalink Satellite Reception Confirmation ...........................................................45
4.2.9. Synchro Heading Checkout......................................................................................................46
4.3. POST INSTALLATION CHECK EMI CHECK ............................................................................................47
5. MFD DATA UPDATES .............................................................................................................................48
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5.1. MAP NAVDATA DATABASE UPDATES...................................................................................................48

5.1.1. To perform a data update .........................................................................................................48
5.2. CHART DATABASE UPDATES ................................................................................................................48
5.2.1. To perform a chart data update ...............................................................................................49
6. FACTORY SERVICE POLICIES.............................................................................................................50
6.1. TECHNICAL SUPPORT ...........................................................................................................................50
6.2. GENERAL SERVICE PROCEDURES .......................................................................................................50
6.3. AC 20-68B RECOMMENDED RADIATION SAFETY ...............................................................................50
APPENDIX A ENVIRONMENTAL QUALIFICATION FORMS ..................................................................................52
APPENDIX B STC EX500 PERMISSION ..........................................................................................................53
APPENDIX C INSTALLATION MECHANICAL: MFD, TRAY & PANEL DIMENSIONS ............................................54
APPENDIX D INSTALLATION MECHANICAL: TRAY SUPPORT STRUCTURE PANEL...........................................56
APPENDIX E INSTALLATION MECHANICAL: NARROWCAST DATALINK ANTENNA ............................................57
APPENDIX F EX500 W IRING: GENERAL .........................................................................................................58
APPENDIX G EX500 W IRING: GPS/FMS SUB-SYSTEM ................................................................................59
APPENDIX H EX500 W IRING: LIGHTNING AND BROADCAST DATALINK SENSORS ........................................60
APPENDIX I EX500 W IRING: TRAFFIC SENSORS............................................................................................61
APPENDIX J EX500 W IRING: TRAFFIC/TAWS SENSORS ..............................................................................62
APPENDIX K EX500 W IRING: DIGITAL RADAR .............................................................................................63
APPENDIX L EX500 W IRING: RDR-130/150/160 RADAR DIRECT CONNECT ............................................64
APPENDIX M EX500 W IRING: RDR-130/150/160 RADAR W/ ADAPTOR CABLE .......................................65
APPENDIX N EX500 W IRING: RDR-1100/1200 RADAR DIRECT CONNECT ..............................................66
APPENDIX O EX500 W IRING: RDR-1100/1200 RADAR W/ ADAPTOR CABLE ...........................................67
APPENDIX P EX500 W IRING: RDR-1300 RADAR DIRECT CONNECT ........................................................68
APPENDIX Q EX500 W IRING: RDR-1300 RADAR W/ ADAPTOR CABLE .....................................................69
APPENDIX R EX500 W IRING: WXR250/270/300 RADAR W/ ADAPTOR CABLE ........................................70

Table of Figures

Figure 1: Sample EX500 Panel Placements ...................................................................................... 7

Figure 2: Maintenance Mode Main Page (actual view depends on installed options) ........................ 12
Figure 3: Maintenance Mode Sensor Support .................................................................................. 13
Figure 4 Main Connector (P2) Pin Assignments.............................................................................. 15
Figure 5 ARINC Port Pinout Cross-Reference ................................................................................. 16
Figure 6 RS-232 Port Pinout Cross-Reference ................................................................................ 17
Figure 7: Main Connector Port Assignments .................................................................................... 18
Figure 8: GPS/FMS System Setup Page ......................................................................................... 19
Figure 9: Traffic System Setup Page ............................................................................................... 21
Figure 10: Lightning System Setup Page ......................................................................................... 23
Figure 11: Datalink Info Table.......................................................................................................... 31
Figure 12: Map System Setup Page ................................................................................................ 32
Figure 13: Aircraft Setup Screen...................................................................................................... 33
Figure 14: Port Info Table ................................................................................................................ 34
Figure 15: Platform Info Table ......................................................................................................... 34
Figure 16: Start-up Screen .............................................................................................................. 35

The latest revision of the FlightMax EX500-Series MFD Installation Manual is made available to
authorized Avidyne dealers on the web at www.avidyne.com.

Avidyne®, FlightMax® and FMX® are registered trademarks of Avidyne Corporation.

Stormscope, and Skywatch® are registered trademarks of Goodrich.

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1. General Information
This manual contains information about the physical, mechanical, and electrical characteristics of the
Avidyne FlightMax EX500-Series Multi-Function Display (MFD), and provides associated installation
instructions. While installation of the FlightMax EX500 is straightforward, it is best to carefully devise
a comprehensive installation strategy prior to commencing the installation effort. Follow the
installation instructions carefully to obtain maximum performance from the FlightMax EX500 MFD.

This installation manual applies to Avidyne 700-00007-XXX-() EX500-Series MFD’s with software
listed in Section 2.1 of this manual.

MFD operating information is contained in the FlightMax EX500-Series MFD Pilot's Guide, Avidyne
Manual 600-00078-000, which is supplied with the unit. It is recommended that avionics installers
review the Pilot’s Guide before operating the MFD. The most current version is available to installers
on the web at www.avidyne.com.

The conditions and tests required for TSO approval of this article are minimum performance
standards. It is the responsibility of those installing this article either on or within a specific type or
class of aircraft to determine that the aircraft installation conditions are within the TSO standards.
TSO articles must have separate approval for installation in aircraft. The article may be installed only
if performed under 14 CFR part 43 or the applicable airworthiness requirements.

CAUTION:

AC 20-68B, Recommended Radiation Safety, sets forth recommended radiation

safety precautions to be taken by personnel when operating airborne weather radar
on the ground. Dangers from ground operation of airborne weather radar include the
possibility of human body damage and ignition of combustible material by radiated
energy. The full text of this FAA Advisory Circular may be found on the web at
http://www1.faa.gov/RegulatoryAdvisory/ac_index.htm.

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1.1. Equipment Description

A complete FlightMax EX500-Series Multi-Function Display system consists of the following

components:

Avidyne FlightMax EX500-Series Multi-Function Display (MFD).

System installation kit including MFD tray assembly, and necessary connectors.

Optional radar interface cables connecting the MFD to the radar receiver/transmitter. These
cables provide a simplified connection to the pre-existing wiring.

User documentation including Pilot's Guide, Installation Manual, and Instructions for
Continued Airworthiness.

1.2. Technical Specifications

STANDARD FEATURES
Display High Brightness Sunlight Readable Color AMLCD
Diagonal size 5.5 inches
Interfaces RS-232, ARINC 429, ARINC 453, ARINC 407 & TTL
PHYSICAL CHARACTERISTICS
Weight with tray 7.2 lbs
Height 4.35 inches (Face Plate)
Width 6.25 inches (Face Plate)
Depth 12.8 inches (Tray incl. Rear connectors)
Viewing Angle Vertical: +30°, -10°
Horizontal: 60° left and right of center
OPERATING LIMITS
Voltage 18-32 VDC, negative ground
Current Maximum: 5 A at 28V
See Appendix A for Environmental Qualification Form

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2. Installation Instructions
2.1. Unpacking and Inspection

The shipping carton of the FlightMax EX500, Avidyne P/N 850-00010-XXX contains the following
components and parts:

Part Number Qty Description

700-00007-XXX 1 FlightMax EX500-Series Multi-Function Display
-XXX Description
-001 EX500, non-RADAR
-002 EX500, RDR1100/1200
-003 EX500, RDR1300
-004 EX500, RDR130/150/160
-005 EX500, RDS8X, RDR2XXX
-006 EX500, WXR250/270/300
600-00078-000 1 FlightMax EX500-Series MFD Pilot's Guide.

The shipping carton of the FlightMax EX500 Installation Kit, Avidyne P/N 850-00011-000 contains the
following components and parts:

Part Number Qty Description

700-00009-000 1 EX500 Tray Assembly
030-00181-000 1 Connector, D-Sub 78F, w/ backshell & Pins
150-00100-000 8 Screw, 4-40 x ¼ Flat, SS, 100 Degree
600-00079-000 1 FlightMax EX500-Series Multi-Function Display Installation Manual

Make sure that all the parts listed above were received and sustained no shipping damage. Where
evidence of shipping damage exists, save the shipping carton and packing material to help
substantiate your claim to the shipping company. Retain the original shipping carton and packing
material in case you need to ship the unit for service.

Locate the labels on the bottom of the MFD. Verify that the MFD has the ordered feature option set
marked on the label. During system checkout the installer will need to verify that one of the software
revisions listed below (or later) is installed in the unit.

Acceptable Software Revision Levels

Part Number Revision
530-00163-000 00
530-00120-000 01

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2.2. FlightMax EX500 MFD Installation

2.2.1. EX500 Installation Considerations

The EX500-Series MFD is intended for application as a supplementary situational awareness device.
The EX500 contains software developed in accordance with RTCA/DO-178B Level D requirements.
2.2.2. Location and Viewing Angle
FlightMax EX500 is designed for panel mounting using the mounting tray supplied with the unit
installation kit. Locate the MFD in a position on the panel where the pilot can easily reach the knobs
and controls to operate and view it from the proper viewing angle.

Viewing angle limits

Vertical Up 30º, Down 10º [+30º/-10º]
Horizontal Left and Right 60º [± 60º]

AUDIO PANEL

FLIGHTMAX TRANSPONDER
EX500

ADF OR OTHER AVIONICS

GPS/NAV/COM

GPS/NAV/COM

AUTOPILOT OR OTHER
AVIONICS

MFD PLACEMENT IN PANEL OF

SMALLER AIRCRAFT (TYPICAL)

AUDIO PANEL

FLIGHTMAX
EX500 TRANSPONDER

ADF OR OTHER
AVIONICS

GPS/NAV/COM

GPS/NAV/COM

AUTOPILOT

MFD PLACEMENT IN PANEL OF

LARGER AIRCRAFT (TYPICAL)

Figure 1: Sample EX500 Panel Placements

2.2.2.1. Cooling
The EX500 includes internal cooling provisions to maximize operational reliability. Care should be
taken not to obstruct the air vents located at the rear and sides of the unit/tray assembly.

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2.2.2.2. Heading Source Selection

The EX500 is capable of receiving aircraft heading from a variety of sources. Care should be taken
when selecting which heading source is to be used in the system installation. Heading source options
are listed below:
Source System Interface Source System Interface
Synchro ARINC 407 Synchro GPS/FMS GNC300XL ARINC 429
Lightning WX-500 RS-232 GPS 400/500 ARINC 429
Traffic Skywatch ARINC 429 GNS 430/530 ARINC 429
Skywatch HP ARINC 429 KLN-90B ARINC 429
KTA-870 ARINC 429 UNS-1B ARINC 429
KMH-880 ARINC 429 GNS-XLS ARINC 429
TCAS I ARINC 429

Selection of the synchro option is recommended and yields the best system reliability
(availability). Heading information supplied by the other referenced systems is typically sourced from
the synchro and may require interface converters between the synchro and the alternate heading
source. Refer to manufacturer’s installation manuals for guidance. Failure of these alternate sources
results in not only loss of that system but also heading related functionality on the EX500.
Specifically, this results in the loss of RADAR overlay capability and forces NORTH UP display of
other Map Mode data.

Refer to Appendix F and Section 3.9 of this document to select the active heading source.

2.2.3. Positioning and Mounting the EX500 Tray

As indicated in Section2.2.2, the EX500 location may vary depending upon instrument panel size,
control obstructions and other installed equipment. Four inches (4”) of clearance should be left behind
the tray to allow for connector clearance and permit air circulation through the EX500. A minimum of
1/8” clearance between the tray and other avionics should be maintained for air circulation purposes.
Avidyne mounting trays provide for a 0.125" clearance between the bezel and mounting tray (along
the sides and top of the tray) to allow for any panel thickness. Ensure that the mounting tray is
installed at the proper depth in the panel to allow the connectors of the EX500 to fully seat in the
connectors of the mounting tray. When properly installed the EX500 bezel should make contact with
the protruding lip on the bottom of the tray.
Structural aspects of the installation should be performed in accordance with AC43.13-2A, Chapter 1.
Appendix D contains details on tray mounting and support.

When installed, the EX500 when operated with any combination of other installed avionics must not
result in a deflection of the aircraft magnetic compass of greater than 10 degrees.

The entire back plate of the mounting tray may be removed (by removing the six screws which hold it
in place) to facilitate wiring. Both the connectors and the back plate may be installed or removed
when the tray is mounted in place. Complete system wiring per Section 2.2.4. With the wiring
complete and the tray installed, follow the initial installation validation test procedure provided in
Section 4.1of this manual and proceed to the configuration instructions in Section 3 of this manual.

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CAUTION

It is extremely important that the 0.125” panel thickness is not exceeded, or the
EX500 may not fully seat in the mounting tray. If communication between the EX500
and any of the sensor interfaces is not established, ensure that the EX500 is fully
seated in the tray, and then check all sensor connections.

2.2.4. Electrical and Sensor Interface Wiring

Refer to Appendix F through Appendix R for system and sensor wiring diagrams. Wiring is to be
performed in accordance with AC 43.13-1B. The following connectors, or equivalents, support the
EX500 tray installation.

Designation Vendor Part Number Description

P1 Positronic DD44M10G00 44-Pin High Density Male D-Sub Connector
P2 Positronic DD78F10G00 78-Pin High Density Female D-Sub Connector
J2 Delta Electronics 4205-018-N995 50 Ohm Blind Plug BNC Connector

The following notes apply to aircraft wiring to be used with the EX500 tray installation.

1. Power: P2- input: 5 A @ 28 vdc. Use 20 AWG for lengths greater than 3ft. Use 22 AWG
for P2 high-density sockets. Circuit breaker: 7.5 amp recommended. For 14 vdc
A/C, use 14 to 28 vdc converter (KGS Electronics RB-125, Ameri-King AK550-6 or
similar with TSO-C71, output 5 A min. @ 28 vdc.)
2. Dimming: P2- input: use 22 AWG, connect to a/c instrument dimming bus. Supports any
range 0-28 vdc. Connection to dimming-bus ground reference required.
3. ARINC 429: P2- wire: use 22 AWG twisted shielded pair, MS22759/18-22-2 or equivalent.
Connect shield to P2 connector metallic backshell grounding screw with solder or
crimp ring terminal.
4. ARINC 453: P2- wire: use 22 AWG twisted double shielded pair (Quadrax), (Bendix/King p/n
024-00064-0000) or equivalent. Connect outer shield to P2 connector metallic
backshell grounding screw with solder or crimp terminal ring. Connect inner and
outer shield to sensor connector metallic backshell grounding screw with solder or
crimp terminal ring.
5. RS-232: P2- wire: use 22 AWG shielded triple, MS22759/18-22-3 or equivalent. Connect
a dedicated RS-232 signal ground from the sensor to the MFD. Connect shield to
P2 connector metallic backshell grounding screw with solder or crimp ring
terminal.
6. Synchro input: P2- wire: use 22 AWG shielded double, MS22759/18-22-2 or equivalent, for REF
HI and REF LO. Use 22 AWG shielded triple, MS27500/18-22-3 or equivalent, for
X/Y/Z. Connect shield to P2 connector metallic backshell grounding screw with
solder or crimp ring terminal.
7. Synchro Valid: Use 22 AWG shielded single, MS22759/18-22-1 or equivalent. Valid low is less
than 1.4 vdc. Valid high is greater than 2.7vdc. Note: this input is optional. If not
used, no connection is required. See Section 3.9 for configuration details.
8. Narrowcast Datalink antenna:
J2- coax cable: use M17/128-RG400, (Thermax/CDT p/n RGS-400) high
temperature, 50 ohm, stranded core with 0.038 o.d., or equivalent. Terminate
antenna end with BNC series connector. See mechanical installation notes.

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9. Analog radar: P1- control and data lines: Use 22 AWG shielded single, MS22759/18-22-1 or
equivalent, for trigger and data lines. Use 22 AWG for all others. See wiring
appendices for particular radar system wiring.
10. Shield terminations: Shield terminations to be made as close to the protected signal wire
terminations as feasible.

2.2.5. Electrical Load Analysis

Prior to installation, an electrical load analysis should be performed specific to the aircraft. This
analysis should be in accordance with AC 43.13-1B, Chapter 11. The following values may be used
to support the analysis:

28 VDC Nominal 28 VDC

Unit
Load Maximum Load
EX500 2A 5A

The power input to the EX500 should be circuit protected in accordance with the guidelines of AC
43.13-1B, Chapter 11, Section 2. A 7.5 amp circuit breaker is recommend for use with the EX500.

2.3. Datalink Antenna Installation Considerations

The EX500 can operate with two different datalink systems simultaneously. Avidyne’s two-way
Narrowcast datalink system utilizes a built-in ORBCOMM transceiver to provide weather data tailored
for the aircraft’s current flight plan. The EX500 also supports the XMD076 XM WX Receiver from
Heads Up Technologies, which is a Broadcast datalink system providing larger amounts of weather
data, With both Narrowcast and Broadcast datalink systems installed, the EX500 will provide
Avidyne’s unique Multilink features, which include text messaging, flight tracking, and enhanced
weather coverage.

The Narrowcast datalink system is designed to work with a VHF antenna covering the band from 137
MHz to 151Mhz. If an existing comm antenna is in the preferred location for a datalink antenna,
consider using the Avidyne DC50 Datalink Coupler and replacing the existing comm antenna with a
combined VHF/datalink antenna. Please contact Avidyne for details.

The Broadcast datalink system operates in the S-band at 2.3 GHz. Several types of combination
antennas are available in addition to the standalone XM antenna. Contact Heads Up Technologies or
Comant, Inc. for details on the available antennas.

2.3.1. Narrowcast Antenna Details

To improve Narrowcast reception performance and minimize potential damage to the EX500
Narrowcast datalink transceiver, an antenna design with a DC-short between the antenna center
conductor and shield termination is required. The following commercially available antennas satisfy
the above requirement:

Manufacturer P/N Application

Comant CI 177-4 Max 210 kts indicated at 10,000 ft
CI 248-30 Max 210 kts indicated at 10,000 ft
CI 108-1 Max 600 kts TAS at 35,000 ft
CI 211-1 Max 600 kts TAS at 35,000 ft

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Sensor Systems S65-8280-10 Max 600 kts TAS

Refer to manufacturers for detailed performance specifications and aircraft applicability

Due to the low signal levels inherent with satellite communications, the following guidelines and
recommended practices should be adhered to :

Mount the Narrowcast antenna on the aircraft top-side, as high on the fuselage as practical.
Mount the antenna no closer than 36 inches to other transmitters. Relocation of other less
location-sensitive transmitters may be necessary to achieve optimal datalink performance.
On radar-equipped aircraft mount the antenna as far aft as possible, but no closer than 36
inches from vertical obstructions (ex. vertical stabilizer). Reflected radar energy may cause
damage to the datalink transceiver.
Install in accordance with the applicable portions of AC43.13 and antenna manufacturer
instructions.

Additional installation guidance is found in Appendix E of this installation manual.

NOTE:

This installation manual does not contain approved data for type specific aircraft
antenna installations.

2.3.2. Broadcast Antenna Details

Mount the antenna no closer than 36 inches to VHF-Comm transmitters of 15 Watts or less.
For more powerful transmitting antennas, separation should be a minimum of 48 inches.

If an XM/VHF-Comm combo antenna is being installed and is replacing the operation of an

existing approved antenna installation, the existing separations are acceptable.
SATCOM antennas transmit at 40 Watts and should be separated by the largest distance
possible. This distance must be a minimum of 36 inches.
When routing the XM antenna cable, the maximum possible separation from transmitter
antenna feed cables must be considered, especially with SATCOM and other high power
transmitters. Antenna feed cables of VHF transmitters of 15 Watts or less should require only
a minimal separation.
Receive-only antennas such as GPS and ADF do not produce interference and require little
separation. The XM antenna should be placed as close as possible to these types of
antennas to gain separation from transmitters.
For further details, including installation pre-testing, please refer to the Heads Up
Technologies XMD076 XM WX Receiver Installation Manual, document number XMD076-3.
2.3.3. Weight and Balance
A Weight and Balance calculation aircraft is required as part of installation approval process. Follow
the guidelines as established in AC 43.13-1B, Chapter 10, Section 2. The unit and installation kit
materials weight supplied below may be used.

Description Weight
EX500 Multi-Function Display with tray
7.2 lb (3.3kg)
and connectors

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3. Post Installation Configuration Guide

This section is intended as a guideline to post installation set up and configuration. For a complete
and detailed description of the unit functionality, refer to the latest revision of the Pilot Operating
Handbook, P/N 600-00078-000.
3.1. System Configuration
The following activities are to be completed during the EX500 configuration process:
Verify installed sensor option support
Verify installed software version number
Setup sensor port interfaces and associated operational options
Adjust the Bezel key backlighting level to match dimming range of other installed avionics
Confirm EX500 setup configuration.
3.1.1. Entering The Maintenance Mode
To configure the EX500 to the specific interface configuration of the installation, EX500
MAINTNANCE MODE must be accessed as follows (with the aircraft avionics master ON and circuit
breaker IN):
Press the PWR button to turn on the Display.
Allow the MFD to run through the initialization process. (approximately 1 minute)
You will be prompted to press any bezel key to continue.
Press any key to gain access to the normal operating mode.
The Page Indicator will have the Map box highlighted.
Rotate the Page knob to highlight “Aux”.
Simultaneously depress L1 (top left) and L3 (middle left) function keys. Hold them for
approximately 5 seconds until the Page indicator is removed from view.
The “Maintenance Mode” page should now be in view. Holding the L1 and L3 keys too long will cause
the unit to transfer into a Maintenance Mode sub-page. Press Cancel to return to the Maintenance
Mode Main page.

Once in the maintenance mode, follow the appropriate set up and configuration sheets of this guide.

L1 R1

L2 R2

L3 R3

L4 R4

L5 R5

Figure 2: Maintenance Mode Main Page (actual view depends on installed options)

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3.2. EX500 Sensor Interface Setup

The EX500 receives and transmits data via user configurable interface ports. To support the many
sensor types that are encountered in the typical aircraft installation, the installer must configure the
EX500 once the unit is installed. Port assignments may be made or modified for each sensor type
(GPS/FMS, Traffic, etc.) through the EX500 Maintenance Mode. The configuration activity includes:

Confirmation that the EX500 is provisioned for the sensor set installed on the aircraft,
Assignment of the interface port for each sensor, as wired by the installer,
Configuration of each sensor port for proper operation,
Selection of sensor specific operation settings*

* Selection of sensor operation settings should be performed under the guidance of the
manufacturer’s instructions for the specific sensor installed. The EX500 port configuration may be
viewed from the System Info utility.

The following section details setup procedures for these sensor interfaces.

3.2.1. EX500 Sensor Interface Provisioning Confirmation

Figure 1 depicts the Maintenance Mode main page. The left-hand column of buttons is dedicated to
initiating setup utilities for the sensor set that the EX500 is configured to support. The button legends
correspond to sensors supported by the EX500. Figure 3 depicts a unit, which supports GPS/FMS,
traffic and lightning sensors.

Verify that the sensor setup options conform to the sensors used in the installation.

Figure 3: Maintenance Mode Sensor Support

3.2.2. Configuration Options

To support the many sensor types encountered in the typical aircraft installation, the installer must
configure the EX500 for the sensor type and select the correct port configuration. Table 1 lists sensor
options and their associated port configurations. This data may be used when executing Maintenance
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Mode sensor setup utilities. Port selection must match the aircraft wiring. Default port assignments
must match the wiring instructions given in Appendices E through Q. Refer to Appendix F for
configurations with dual GPS/FMS inputs.

When the MFD is being used in conjunction with a digital radar system, ARINC 429 port 3 and ARINC
453 port 1 are default settings, which are not selectable via the procedures contained in this
document. Figure 7 provides a cross reference between port assignments and functional use.

Table 1: Sensor Port Configuration Options

Default Port
Sensor Type Sensor Option Port Type System Type
Port Configuration
GPS/FMS GAMA 429 ARINC 429 Garmin GPS 155XL, GNC Speed: Low
Format 300XL Speed: Low
1
Garmin GPS 400/500 Speed: Low
Garmin GNC 420 Speed: Low
Garmin GNS 430/530 (GAMA Speed: Low
429 Graphics w/INT)
Speed: High
Bendix/King KLN-90B
Speed: High
Universal UNS-1B
RS-232 Baud: 9600
King/Aviation Honeywell GNS-XLS
1 Baud: 9600
Format Garmin GNS 430/530
Baud: 9600
Bendix/King KLN-90B
Baud: 9600
Trimble 2000, 2101
Baud: 9600
UPSAT – all GPS units
RS-232 Baud: 9600
Northstar M3
RS-232 1 Baud: 4800
Northstar Format Garmin 150/250
1
NMEA 0183
Format
Traffic Not Installed
TCAD RS-232 Ryan 9900B, 9900BX N/A
2
TAS ARINC 429 L3 Skywatch, Skywatch HP N/A
2
TAS ARINC 429 Honeywell KTA-870, KMH-880 N/A
TIS-G ARINC 429 Garmin GTX330 N/A
2
TCAS ARINC 429 Goodrich TCAS 791 N/A
2
TCAS ARINC 429 Honeywell CAS-66A, KTA-970
2

Broadcast Not Installed RS-232 Heads Up Technologies N/A

Datalink 4 XMD076
XM Radio
Lightning Not Installed
WX-500 RS-232 3 WX500 N/A
RADAR The digital radar port is factory configured and requires no setup.
TAWS Not Installed
Honeywell ARINC 429/ 4 Honeywell EGPWS N/A
EGPWS ARINC 453 2
Map Heading Synchro N/A N/A N/A N/A

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Default Port
Sensor Type Sensor Option Port Type System Type
Port Configuration
{Source} FMS/GPS
Traffic
Stormscope
None (use GPS
Track)

Figure 4 Main Connector (P2) Pin Assignments

Pin Function Default Pin Function Default

1 TTL1 (R/T ON) 40 28 VDC

2 RESERVED 41 28 VDC

3 RESERVED 42 28 VDC

4 GND 43 ARINC 429 TX1 A

5 ARINC 429 RX1 A GPS A 44 RESERVED

6 ARINC 429 TX2 A 45 ARINC 429 RX2 A TRAFFIC

7 TTL2 (TAS) 46 ARINC 429 TX3 A RADAR

8 ARINC 429 RX3 A 47 TTL3 (TAS)

9 ARINC 429 TX4 A TAWS 48 ARINC 429 RX4 A

10 RS232 TX1 49 RS232 TX3 WX500

11 RS232 RX1 GPS A 50 RS232 RX3 WX500

12 RS232 RTN1 GPS A 51 RS232 RTN3 WX500

13 RESERVED 52 RESERVED

14 RESERVED 53 RESERVED

15 GND 54 SYNCHRO Z IN

16 SYNCHRO X IN 55 ARINC 453 TX3 A (UNUSED)

17 SYNCHRO REF LO 56 ARINC 453 RX2 A TAWS

18 DIMMING 57 GND

19 RESERVED 58 ARINC 453 TX3 B (UNUSED)

20 GND 59 ARINC 453 RX2 B TAWS

21 RESERVED 60 PWR GND

22 RESERVED 61 PWR GND

23 RESERVED 62 PWR GND

24 RESERVED 63 ARINC 429 TX1 B

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Pin Function Default Pin Function Default

25 ARINC 429 RX1 B GPS A 64 RESERVED

26 ARINC 429 TX2 B 65 ARINC 429 RX2 B TRAFFIC

27 RESERVED 66 ARINC 429 TX3 B RADAR

28 ARINC 429 RX3 B 67 RESERVED

29 ARINC 429 TX4 B TAWS 68 ARINC 429 RX4 B

30 RS232 TX2 TCAD 69 RS232 TX4 XM, GPS B

31 RS232 RX2 TCAD 70 RS232 RX4 XM, GPS B

32 RS232 RTN2 TCAD 71 RS232 RTN4 XM, GPS B

33 SYNCHRO VALID 72 RESERVED

34 RESERVED 73 RESERVED

35 SYNCHRO Y IN 74 SYNCHRO REF HI

36 GND 75 ARINC 453 RX1 A RADAR

37 GND 76 RESERVED

38 RESERVED 77 RESERVED

39 RESERVED 78 ARINC 453 RX1 B RADAR

Figure 5 ARINC Port Pinout Cross-Reference

ARINC 429 Ports ARINC 453 Ports

Port Signal Pin Port Signal Pin

1 TX A 43 1 TX A N/A

TX B 63 TX B N/A

RX A 5 RX A 75

RX B 25 RX B 78

2 TX A 6 2 TX A N/A

TX B 26 TX B N/A

RX A 45 RX A 56

RX B 65 RX B 59

3 TX A 46 3 TX A 55

TX B 66 TX B 58

RX A 8

RX B 28

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ARINC 429 Ports ARINC 453 Ports

4 TX A 9

TX B 29

RX A 48

RX B 68

Figure 6 RS-232 Port Pinout Cross-Reference

RS-232 Ports

Port Signal Pin

1 TX 10

RX 11

RTN 12

2 TX 30

RX 31

RTN 32

3 TX 49

RX 50

RTN 51

4 TX 69

RX 70

RTN 71

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P2
TAWS 453: ARINC 453 RX #2
RADAR 453:ARINC 453 RX #1
20 59
39 78
DIMMING 19 58
38 77
SYNCHRO 18 57
37 76
17 56
36 75
16 55
35 74
15 54
34 73
14 53
TRAFFIC 232: RS-232 #2 33 72
GPS A 232: RS-232 #1 13 52 LIGHTNING 232: RS-232 #3
32 71
GPS B 232 or XM WX
12 51
Broadcast Datalink:
31 70
11 50 RS-232 #4
30 69 TAWS 429: ARINC 429 RX #4
TAWS 429: ARINC 429 TX #4 10 49
29 68
ARINC 429 RX #3 9 48
28 67 RADAR 429: ARINC 429 TX #3
8 47
27 66 TRAFFIC 429: ARINC 429 RX #2
7 46
26 65
GPS A 429: ARINC 429 RX #1 6 45
25 64
5 44
24 63 AVIONICS POWER: RTN
4 43
23 62
3 42
22 61
2 41
21 60
1 40
AVIONICS POWER: 28 VDC
P2 - MAIN CONNECTOR
SERIAL DATA PORT
ASSIGNMENTS

NOTES:
1. AVAILABLE FOR GPS B WHEN TRAFFIC 429: ARINC 429 RX #2
PORT IS NOT WIRED
2. AVAILABLE FOR GPS B WHEN TAWS 429: ARINC 429 TX #4
PORT IS NOT WIRED

Figure 7: Main Connector Port Assignments

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3.2.3. Configuration Selection

To configure a specific sensor type, enter the appropriate setup utility by depressing the
corresponding bezel key. Figure 8 depicts the setup page for the GPS/FMS interface. Four operations
are supported for each sensor setup page.

Select: Change the highlighted parameter box. {knob rotation}

Change: Modify the parameter in the highlighted box. {knob rotation}
Save: Store any setup changes made since entering the page and return to the
Maintenance Mode Main page. {button press}
Cancel: Ignore any setup changes made since entering the page and return to the
Maintenance Mode Main page. {button press}

Figure 8: GPS/FMS System Setup Page

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3.3. GPS/FMS System Setup

Based upon tray wiring, Table 1 data, and sensor manufacturer’s instructions, configure the
GPS/FMS receiver input formats, port selections and port speeds for GPS/FMS avionics interfaced to
the EX500. Refer to Appendix G for Receiver B (GPS B) configuration guidance.

Note: Garmin GNS4xx and GNS5xx receivers must be configured for “GAMA 429 Graphics w/INT” if
interfaced via ARINC 429. Refer to Garmin installation manuals for details on changing this setting.

When complete, press Save to confirm changes made or press Cancel to retain previous system
settings and return to Maintenance Mode main page.

3.4. Traffic System Setup

Based upon tray wiring, Table 1 data, and sensor manufacturer’s instructions, configure the traffic
sensor input formats, and port selections for traffic sensor interfaced to the EX500.

System configuration options include (option availability depends on EX500 configuration ordered):

System Option Values Notes

TCAD Shields Terminal
Standard
Enroute
Range Terminal 0.5 – 1.5 nm
Standard 1 – 3 nm
Enroute 2 – 15 nm Limited to 6 nm max. by the 9900B sensor
Height Terminal 200 – 1000 ft
Standard 500 – 1500 ft
Enroute 1000 – 2000 ft
TAS External Controller Check/No Check Check this box if a dedicated external
Skywatch controller is installed. With this
box checked the EX500 will not initiate
Skywatch standby or Self Test functions.
TCAS Maximum Intruders Display All (31) Selects the maximum number of intruders
Specified by Sensor that can be simultaneously displayed on the
EX500.
Minimum (8)
Sensor Range 0 – 128 nm Sets the range limit of intruders displayed
on the EX500. This limit is independent of
limits set on the TCAS system.
External Mode Control (ABV/BLW/NRM) Check/No Check When checked, the EX500 will not control
the TCAS altitude mode.
External Range Control Check/No Check When checked, the EX500 will not control
the TCAS range setting.

When complete, press Save to confirm changes made or press Cancel to retain previous system
settings and return to Maintenance Mode main page.

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Figure 9: Traffic System Setup Page

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3.5. Lightning System Setup

Based upon tray wiring, Table 1 data, and sensor manufacturer’s instructions, configure the lightning
sensor input formats and port selections for the lightning sensor interfaced to the EX500. Refer to the
WX-500 manual for further lightning system operational details.

System configuration options include:

System Option Values Notes

WX-500 Operating Mode Weather Normal operating mode
Noise Monitor Supports noise mapping tests
(May require second button press to
advance from “Noise Monitor” to “Display
Off”)
Demo Used to learn lightning operations
Stab Type Synchro to WX-500 The WX-500 will use the synchro supplied
heading data connected directly to the
WX500.
Stepper to WX-500 The WX-500 will use stepper data from a
remote compass system.
Use Map Heading/Track The WX-500 will use orientation information
supplied by the EX500 based upon the “Map
Heading Configuration”
Enable Lightning Ahead Warning? Check/No Check When checked, the EX500 will issue
lightning ahead warning messages.
Antenna on Top? Check/No Check To be checked if the lightning sensor
antenna is located on top of the aircraft and
must correspond with the WX-500 jumper
settings.

Press Save to confirm changes made or press Cancel to retain previous system settings.

The EX500 is also able to report system data reported from the WX-500 via the WX500 Diags key
and initiate the WX-500 self-test function by activation of the WX500 Self Test key. These two
functions are only available when the WX-500 sensor is powered up and communicating with the
EX500. Refer to the WX-500 manual for details on reported system data and self-test operation.

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Figure 10: Lightning System Setup Page

3.6. RADAR System Setup

Table 2 lists the RADAR-types supported by the EX500-Series MFD. From the Radar Setup page,
select installed radar type, SAVE the selection and RESTART the system.
Table 2: EX500-Series Radar Support

EX500 Sensor EX500 Sensor

700-00007-001 Not Installed 700-00007-005 Bendix/King RS-181A
Bendix/King RS-181A-VP
700-00007-002 Bendix RT-131A/DA-1203A Bendix/King RS-811A
Bendix RT-1201A/DA-1203A Bendix/King RS-841A
Bendix/King RS-841A-VP
700-00007-003 Bendix RT-1301A/B /DA-1203A Bendix/King RS-861A
Bendix/King RS-861A-VP
700-00007-004 Bendix RT-131A/AT-133A AlliedSignal ART-2000
Bendix RT-131A/AT-133A (INV) AlliedSignal ART-2100
Bendix RT-131A/DA-144A
Bendix RT-131A/DA-144A (INV) 700-00007-006 Collins WXT-250A
Bendix ART-161A Collins WXT-250B/200mi
Collins WXT-250B/250mi

Configuration options are radar specific, presented as available per radar-type, and may be selected from the Radar
Setup page after the system restarts.

Table 3 describes option choices. Refer to the Radar installation and operations manuals for further
details.

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Option Value Notes

Park Position Last position Set the park/startup position for the radar antenna tilt angle.
Full up
Centered
Full down
Beam Width 0.0O – 19.5O Defines the Width and Height of the radar sweep graphical
depiction on the EX500 radar display. Typical beam widths are
Beam Height 0.0O – 19.5O
provided below.
Enable Gain Control Check/No Check Enables R/T variable gain control to be commanded from the
EX500.
Enable VP Check/No Check When checked, enables Radar Vertical Profile mode.
Enable Auto-Tilt Control Check/No Check When checked, enables Radar auto-tilt mode.
Primary Indicator (1) Check/No Check When checked, enables EX500 control of radar functions.
Disable Stabilization Check/No Check Disables EX500 display of the “Stab Off” annunciation
Enable Automatic Standby Check/No Check When checked, enables the EX500 to auto-command the radar to
standby when ground is sensed to be below 20 kts.

Table 3: Radar Configuration Options

Antenna Width Generic Beam Width Bendix/King Radars Collins Radar

10” 10° 10° 9.5°
12” 8° 8° 8°
18” 5° 5.6° 6°

Table 4: Radar Feature Matrix

Range Values

other than 0°
Roll Trim adj
Stabilization

Target Alert

Tilt settings
Multiple Ind

Stab on-off

Azim Lines
# of colors
supported
Scan Arcs

ARL/PAC
Auto-Tilt
control

VP

Bendix/King
RT-131A (RDR-150) 5, 10, 20, 90° 3 ±15°
[RT-131A/AT-133A] 40, 80, 160
[RT-131A/AT-133A
(INV)]
[RT-131A/DA-144A]
[RT-131A/DA-144A
(INV)]
RT-131A (RDR-1100) 10, 20, 40, 60°, 3 • • • ±15°
[RT-131A/DA1203A] 80, 160, 120°
240

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Range Values

other than 0°
Roll Trim adj
Stabilization

Target Alert

Tilt settings
Multiple Ind

Stab on-off

Azim Lines
# of colors
supported
Scan Arcs

ARL/PAC
Auto-Tilt
control

VP
ART-161A (RDR-160) 5, 10, 20, 90° 3 ±15°
[ART-161A] 40, 80, 160

RS-811A (RDS-81) 10, 20, 40, 90° 4 • • • • ±15°

[RS-811A] 80, 160,
240
RS-181A (RDS-82) 10, 20, 40, 90° 4 • • • • ±15°
[RS-181A] 80, 160,
240
RS-181A-VP (RDS- 10, 20, 40, 90° 4 • • • • • ±15°
82VP) 80, 160,
[RS-181A-VP] 240

RS-841A (RDS-84) 5, 10, 20, 120° 4 • • • ±15°

[RS-841A] 40, 80, 160,
240, 320
RS-841A-VP (RDS- 5, 10, 20, 120° 4 • • • • ±15°
84VP) 40, 80, 160,
[RS-841A-VP] 240, 320

RS-861A (RDS-86) 5, 10, 20, 120° 5 • • • • • ±15°

[RS-861A] 40, 80, 160,
240, 320
RS-861A-VP (RDS- 5, 10, 20, 120° 5 • • • • • • ±15°
86VP) 40, 80, 160,
[RS-861A-VP] 240, 320

ART-2000 (RDR- 10, 20, 40, 90°, 4 • • • • • • ±15°

2000) 80, 160, 100°
[ART-2000] 240

ART-2100 (RDR- 5, 10, 20, 60°, 5 • • • • • • • • ±15°

2100) 40, 80, 160, 90°,
[ART-2100] 240, 320 100°,
120°
RT-1201A (RDR- 10, 20, 40, 60°, 3 • • • ±15°
1100/1200) 80, 160, 120°
[RT-1201A/DA1203A] 240

RT-1301A/B (RDR- 10, 20, 40, 60°, 3 • • • ±15° ±15°,

1300) 80, 160, 120° ±30°
[RT-1301A/B 240
/DA1203A]

Collins

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Range Values

other than 0°
Roll Trim adj
Stabilization

Target Alert

Tilt settings
Multiple Ind

Stab on-off

Azim Lines
# of colors
supported
Scan Arcs

ARL/PAC
Auto-Tilt
control

VP
WXT-250A (WXR- 10, 25, 50, 120° 3 • • • ±15° ±30°
270) 100, 250
[WXT-250A]
WXT-250B (WXR- 10, 25, 50, 120° 4 • • • • ±15° ±30°
270A) 100, 200
[WXT-250B/200MI]
WXT-250B (WXR- 10, 25, 50, 120° 4 • • • • ±15° ±30°
270) 100, 250
[WXT-250B/250MI]
• Support native to R/T
Support provided by Avidyne software

NOTE: Features provided by software for ALL sensors:

- Beam Altitude display
- Beam Width display
- Bearing Line
- Hold (Freeze)
- Startup/Standby Tilt Parking

3.6.1. RADAR System Calibration

Calibration of the Radar R/T unit requires access to the radar calibration page on the FlightMax
EX500 unit. This section explains how to access the calibration page and complete the radar
calibration. Calibration of the radar R/T should be performed according to the procedures and
specifications for the specific unit installed in the aircraft.

Calibration can be performed after the Radar has been installed, setup and checked out per the radar
manufacturer’s instructions.

3.6.1.1. Calibration with Bendix/King RDS-8X Series Radars

NOTE:

In order to avoid recalibration of the R/T when upgrading from an ALREADY CALIBRATED
BENDIX/KING INDICATOR, it is suggested that the installer activate the Maintenance Page
of the original Bendix/King indicator BEFORE IT IS REMOVED and write down the value for
'Roll Trim'. This value may be entered in the EX500 to maintain the existing calibration.

To calibrate the system:

Enter the FlightMax EX500 Maintenance Mode per Section 3.1.1
Access the Calibration Mode
Perform the calibration according to the specifications in the R/T unit's manual.
Press Enter to accept new values.

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3.6.1.2. Calibration with AlliedSignal (Bendix/King) 2XXX Series Radars

This section describes Post-Installation System Configuration and Calibration of the Bendix/King
RDR-2000 and RDR-2100 Radar Systems using the FlightMax EX500 and replaces specific sections
of the Bendix/King Installation Manual that describe configuration and calibration using the
Bendix/King IN-182A Indicator.

To configure and calibrate the system, follow the original B/K Installation Manual substituting the
following two sections with the instructions provided herein.

2.4.1 CONFIGURATION PROCEDURE USING RADAR INDICATOR

2.4.4.1 STABILIZATION CALIBRATION WITH RADAR INDICATOR.

NOTE:

If the EX500 is replacing the indicator of currently installed and previously calibrated RDR
2000 series radar, this procedure may not be necessary. The calibration values are contained
in the configuration module of the R/T and should remain valid. Avidyne does recommend
that the installer check the calibration values after the Avidyne unit has been installed to
ensure that nothing has changed.

2.4.1 CONFIGURATION PROCEDURE USING A PERSONAL COMPUTER

The R/T Configuration Module must be configured using the Allied Signal KPA 900 Configuration Module Programmer Kit
(Part Number 050-03311-0000) in conjunction with a personal computer. Refer to the configuration module user data for
detailed setup instructions. Follow the instructions for the programmer.

2.4.1.1 Antenna Clearance Check

Complete the Antenna Clearance Check by performing the following steps:

A. Set the radar Function to SBY.

B. Set the radar Mode to GND.
C. Reduce the gain until the gain indicator shows the minimum setting.
D. Set the Antenna Tilt to full UP (U 15.0).
E. Set Range to 240 NM.
F. Set Function to TEST.
G. Set he radar mode to GND
H. Reduce the gain until the gain indicator in the upper left shows the minimum setting.
I. Set the Antenna Tilt to Full UP (U 15.0)
J. Set the Range to 240 NM
K. Navigate to the SETUP page and enter the Maintenance Mode.
L. Press the Radar Setup button.
M. Press the Calibration button to display the RT CALIBRATION DATA page. Upon display of the RT CALIBRATION
DATA page with the system in calibration mode, all fault fields will flash briefly. This verifies calibration mode is
entered.
N. Adjust the gain to obtain a value of –26.5 to –28 in the GAIN POT /2 field. This will initiate the antenna clearance
scan. The antenna will move to each of the extreme positions to determine that there is no interference with
antenna movement and all scan motors are working properly.

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2.4.4.1 STABILIZATION CALIBRATION WITH FLIGHTMAX EX500

A. Set the radar Function to SBY.

B. Set the radar Mode to GND.
C. Reduce the gain until the gain indicator in the upper right shows the minimum setting.
D. Set the Antenna Tilt to full UP (U 15.0).
E. Set Range to 240 NM.
Note: Failure to perform steps A to E will prevent the ART from entering calibration mode. If more than one
radar indicator is installed in the system, all but one indicator must be in the OFF or SBY position in
order for the system to enter the calibration mode.
F. Enter the Maintenance Mode
G. Press the Radar Setup button
H. Press the Calibration button to display the RT CALIBRATION DATA page. See figure 2-5 in the Bendix/King
Installation Manual. Upon display of the RT CALIBRATION DATA page with the system in calibration mode, all
fault fields will flash briefly. Adjust Roll Trim with the outer knob to 0o.
I. If desired, copy all displayed values to a note pad in case there is a need to recall a value that is accidentally
changed.
J. 400 Hz REF GAIN
If an ARINC 429 gyro is being used, proceed to Step N.
1. Set the tilt table to 0 Deg. pitch and roll.
2. Use the GAIN controls to set the GAIN POT /2 setting between –28 and –30.
3. Adjust the TILT SETTING with the inner knob between 5 and 10 UP to increment the 400 HZ REF field to 0.0
±1.0 Deg. (adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon
reaching the desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure
2-11 in the Bendix/King Installation Manual.
4. Proceed to step K
Note: If the 400 Hz REF field is zero (0), and will not change when the TILT knob is adjusted, check that the
correct gyro has been selected when programming the Configuration Module.
K. PITCH GAIN
1. Set the tilt table for 10 Deg. pitch up.
2. Adjust the GAIN buttons for a GAIN POT setting between –24.5 and –26.5.
3. Adjust the TILT SETTING between 5 and 10 UP to increment the PITCH ANGLE field to 10.0 ±1.0 Deg.
(adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching the
desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11 in the
Bendix/King Installation Manual.
4. Set for 10 Deg. PITCH DOWN. Repeat steps 2 and 3.
5. Set the tilt table to 0 Deg. pitch and roll.
6. Proceed to step M.

L. PITCH OFFSET
1. Adjust the GAIN controls for a GAIN POT setting between –17.5 and –19.5.
2. Check that the tilt table is set for 0 Deg. pitch.
3. Adjust the TILT SETTING between 5 and 10 UP to increment the PITCH ANGLE field to 0.0 ±1.0
Deg.(adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching 0
Deg.±1.0o, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11 in the
Bendix/King Installation Manual.
4. Set the tilt table to 10 Deg. pitch up. The value should be 10.0U ±1.0o. If the value is out of range, repeat

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Step L.
Set the tilt table to 10 Deg. pitch down. The value should be 10.0D ±1.0o. If the value is out of range, repeat
5.
Step L.
6. Set the tilt table to 0 Deg. pitch. The value should be 0.0 ±1.0o. If the value is out of range, repeat Step M.
7. Proceed to Step N.
M. AHRS ARINC 429 PITCH OFFSET
1. Adjust the GAIN buttons for a GAIN POT setting between –10.5 and –12.5.
2. Check that the tilt table is set for 0 Deg. pitch.
3. Adjust the TILT SETTING between 5 and 10 UP to increment the PITCH ANGLE field to 0.0 ±1.0 Deg
(adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching 0
Deg.±1.0o, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11 in the
Bendix/King Installation Manual.
4. Set the tilt table to 10 Deg. pitch up. The value should be 10.0U ±1.0o. If the value is out of range, repeat
Steps 1, 2 and 3 of this section.
5. Set the tilt table to 10 Deg. pitch down. The value should be 10.0D ±1.0o. If the value is out of range, repeat
Steps 1, 2, 3 and 4 of this section.
6. Set the tilt table to 0 Deg. pitch. The value should be 0.0 ±1.0o.
7. Proceed to Step P.
N. ROLL GAIN
1. Set the tilt table for 10 Deg. roll right.
2. Adjust the GAIN buttons for a GAIN POT setting between –21.0 and –23.0.
3. Adjust the TILT SETTING between 5 and 10 UP to increment the ROLL ANGLE field to 10.0 ±1.0 Deg.
(adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching the
desired setting, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11 in the
Bendix/King Installation Manual.
4. Set the tilt table for 10 Deg .roll left. Repeat Steps 2 and 3 of this section.
5. Set the tilt table for 0 Deg. pitch and roll.
6. Proceed to Step O.
O. ROLL OFFSET
1. Adjust the GAIN buttons for a GAIN POT setting between –14.0 and –16.0.
2. Check that the tilt table is set for 0 Deg. roll.
3. Adjust the TILT SETTING between 5 and 10 UP to increment the ROLL ANGLE field to 0.0 ±1.0
Deg.(adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching 0
Deg.±1.0o, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11 in the
Bendix/King Installation Manual.
4. Set the tilt table to 10 Deg. roll right. The value should be 10.0R ±1.0o. If the value is out of range, repeat
Step N.
5. Set the tilt table to 10 Deg. roll left. The value should be 10.0L ±1.0o. If the value is out of range, repeat Step
N.
6. Set the tilt table to 0 Deg. roll. The value should be 0.0 ±1.0o. If the value is out of range, repeat Step O.
7. Proceed to Step P.

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P. AHRS ARINC 429 ROLL OFFSET

1. Adjust the GAIN controls for a GAIN POT setting between –7.0 and –9.0.
2. Check that the tilt table is set for 0 Deg. roll.
3. Adjust the TILT SETTING between 5 and 10 UP to increment the ROLL ANGLE field to 0.0 ±1.0 Deg.
(adjusting the TILT SETTING between 5 and 10 DOWN will decrement the numbers). Upon reaching 0
Deg.±1.0o, quickly adjust the TILT SETTING to above 10 to lock in the setting. See figure 2-11 in the
Bendix/King Installation Manual.
4. Set the tilt table to 10 Deg. roll right. The value should be 10.0R ±1.0o. If the value is out of range, repeat
Step P.
5. Set the tilt table to 10 Deg. roll left. The value should be 10.0L ±1.0o. If the value is out of range, repeat Step
P.
6. Set the tilt table to 0 Deg. roll. The value should be 0.0 ±1.0o.
7. Proceed to Step Q.
Q. SAVE CONFIGURATION
1. Adjust the GAIN controls for a GAIN POT setting between –3.5 and –5.5.
2. Set the TILT SETTING to 15.0D. The fault fields will flash indicating the save procedure is beginning. If the
save procedure is successful, the GYRO fault will disappear and the azimuth count will step.
3. If the GYRO fault remains, set TILT to 0 and repeat step 2 of this section.

3.6.2. Roll Trim Adjustment

For procedures that require the Roll Trim to be adjusted, the installer can access the Roll Trim
selection from the Maintenance Mode Radar Setup utility. When selected, the Roll Trim value
appears on the Radar screen and may be modified by the Roll Trim control knob. When all settings of
the Roll Trim have been accomplished, save the new setting by returning to the Radar Setup using
the Back button.

3.7. TAWS System Setup

Based upon tray wiring, Table 1 data, and sensor manufacturer’s instructions, configure the TAWS
sensor input formats and port selections for the TAWS sensor interfaced to the EX500 (option
availability depends on EX500 configuration ordered).

No additional system configuration options are required with the EX500 supported TAWS sensors.

Press Save to confirm changes made or press Cancel to retain previous system settings.

3.8. Narrowcast Datalink Setup

The EX500 is pre-configured for Narrowcast datalink operation. Avidyne recommends installing a
Narrowcast antenna even if Broadcast datalink is being installed, to provide the user with all the
features of the unique Multilink system.

If a Narrowcast datalink antenna is not being installed, select the Aircraft Setup page from
Maintenance Mode and set the Narrowcast selection to “Not Installed”. If this step is omitted, the
user will see a steady stream of Narrowcast error messages as the EX500 attempts to establish the
Narrowcast connection.

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Accessing the Datalink Info page from the System Info utility, which is entered from the Maintenance
Mode menu, gives details of the configuration.

Figure 11 depicts the Datalink Info table. Verify the presence of SC Serial Number and version
information on this screen.

Figure 11: Datalink Info Table

3.9. Broadcast Datalink Setup

The MFD supports the Heads Up XMD076 XM data receiver.
Confirm that the datalink setup fields on the Aircraft Setup page are configured for:
Broadcast– Select “XM Radio”. This will enable the datalink functionality and communication
with the satellite data receiver.
Port – Should be set to the serial port used for the satellite receiver, nominally RS232 4.
Save settings and restart MFD.

3.10. Map Heading Source Setup

Based upon tray wiring, Table 1 data, and sensor manufacturer’s instructions, configure the EX500
for the intended heading sensor input. Refer to section 2.2.2.2 of this manual.

System configuration options include:

System Source Values Notes

Aircraft Map Heading None (Use GPS Track) The GPS/FMS track will be used as the Map orientation
Heading reference.
Synchro – no Heading The EX500 will use ARINC 407 synchro input for heading
Valid input information. The synchro source does not supply a “heading
valid” signal, and the EX500 will assume the heading is valid
whenever an excitation input is detected.
Synchro – Heading The EX500 will use ARINC 407 synchro input for heading
Valid LOW information. The Heading Valid input is active when the
signal is LOW.

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System Source Values Notes

Synchro – Heading The EX500 will use ARINC 407 synchro input for heading
valid HIGH information. The Heading Valid input is active when the
signal is HIGH.
Stormscope The EX500 will use the lightning sensor input for heading
information. (WX500 must be configured for synchro)
Traffic The EX500 will use the traffic sensor input for heading
information. (only present with TAS/TCAS sensors)
GPS/FMS The EX500 will use the GPS/FMS sensor ARINC 429 input
for heading information. The GPS/FMS system may require
supplemental signal converters to generate heading
information usable to the EX500. Refer to GPS/FMS system
installation manuals for configuration options.

Press Save to confirm changes made or press Cancel to retain previous system settings.

Figure 12 depicts the factory default settings for the Map system setup.

Figure 12: Map System Setup Page

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3.11. Bezel Key Dimming Setup

From the Aircraft Setup page, the brightness of the EX500 bezel key backlighting can be balanced
to the other aircraft components. With the cockpit in a darkened environment, perform the following
procedure.

Adjust the aircraft panel lighting control to maximum brightness.

With the Brightest Dimming Voltage box highlighted, press Set
Adjust the aircraft panel lighting control to minimum useable nighttime panel brightness.
NOTE: This brightness level should be at the point where any other panel instruments
transition from dim (night) to bright (day) operation.
Select the Darkest Dimming Voltage box.
Press Set
Change the setting value until the EX500 bezel key lighting matches other display-based
instruments installed in the panel.
Press Save to confirm changes made or press Cancel to retain previous system settings.

Figure 13: Aircraft Setup Screen

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3.12. System Information

From the MAINTENANCE MODE main page the SYSTEM INFO pages may be accessed. Port
assignments, platform information and datalink operating status is presented.

Verify sensor port assignments with the Port Info table.

Figure 14 depicts the Port Info table.

Figure 14: Port Info Table

Figure 15 depicts the Platform Info table.

Figure 15: Platform Info Table

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4. EX500 MFD Checkout

The following MFD checkout aides are intended to assure proper EX500 installation and interfacing
with other aircraft sensors. Familiarize yourself with the Pilot's Guide for explanations of the various
functions and display controls. Refer to AC20-68B Recommended Radiation Safety provided with the
General Information section of this installation manual.

Any operational issues isolated to the EX500 MFD will require servicing of the unit by Avidyne
authorized personnel. Refer to the return procedures located at the back of this installation manual for
details.

4.1. Initial Installation Validation Test

Upon completion of aircraft wiring and tray installation, the following initial system validation should be
performed.
Check all power and airframe ground connections.
Verify that power is not present on any pins other than those specified in the wiring
diagrams section of this manual.
Slide the MFD into its mounting tray.
Verify that the MFD is properly seated in the mounting tray and secured into position.
Lock the unit in place with a size 3/32" Allen wrench. If you need to remove the unit, unlock
it with the Allen wrench, and slide the unit out of the tray.
Apply power to the MFD and all associated sensors.
The unit will go through a start-up sequence, which should end with the display as represented in
Figure 16.
Verify the software revision number matches (or higher) that on the Section 2.1.
Enter the Maintenance Mode per the procedure given in Section 3.1.1
Verify that the sensor setup options per Section 3.2.1.

Figure 16: Start-up Screen

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4.2. Sensor Communications Checkout

The following sections provide troubleshooting guidance when problems are encountered with EX500
MFD sensor interfaces. Please refer to the EX500-Series Multi-Function Display Pilot’s Guide on the
operation of each of these functions.

4.2.1. GPS/FMS Checkout

Turn on the GPS/FMS system and allow the time required to establish its present position.
Insure the GPS/FMS system is properly configured for use with an MFD.

GPS/FMS Sensor Communications Troubleshooting

If there is a communication or data error between the navigation source and the MFD, one of the
following messages will remain in the lower right corner of the screen.

Message Meaning/Action
Nav Source Is Not Communicating No RS 232 or ARINC 429 GPS data is being received.
o Verify wiring and Comm port setting.
o Verify that the EX500 is properly seated in its tray.
Nav Source Data Is Not Valid Data is being received from the external GPS. However, insufficient
information is available from the GPS to determine position.
o Verify that the GPS has determined its “fix” or location (relocating
the a/c outside of the hanger may assist reception)
o Verify GPS signal wiring within the harness.
Nav Source Data Format Error The MFD does not recognize the data being received from the GPS.
o Verify GPS data rate or MFD receiver type set-up.
Nav Source Can’t Open Port (err=x) The MFD is incorrectly setup with two devices on the same port.
2= Device Not found, means that somehow they selected a port that
doesn't exist. This may occur if they select an ARINC channel on
a system without a radar board.
5= Either another sensor was configured with the same port or that
ARINC1 was selected for the GPS on a non-ARINC 429 EX500.
997 = I/O error, interference is inhibiting the EX500’s ability to access
the assigned port.
o From the Setup page, verify port assignments for sensor inputs.
(Typically the GPS is configured for RS 232 Port 2 or ARINC 429 port 1)
Nav Source Reconnecting … The data between the MFD and the GPS is being synchronized. (no action)
Heading Data Is Not Valid When the GPS is being used as the heading source, heading data is no longer
available from the GPS.
o Verify that the GPS has determined its “fix” or location.
o Verify GPS reported heading matches aircraft heading.
o Verify heading into the GPS is valid

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4.2.2. Lightning Sensor Checkout

Perform a functional test of the lightning detection system in accordance with manufacturer’s
instructions. Refer to the MFD Pilot Guide for display operation.

Stabilization and heading location options must agree with the jumper settings on the WX500.

Lightning Sensor Communications Troubleshooting

If there is a communication or data error between the lightning sensor and the MFD, one of the
following messages will remain in the lower right corner of the screen.

Message Meaning/Action
Lightning Sensor Error The sensor system has reported an error.
o Use WX500 Diagnostics and Self Test utilities on the
EX500.
o Verify WX500 jumper wire configuration.
o Refer to lightning sensor installation and users manual to
troubleshoot.
Lightning Sensor Has Failed The sensor system has reported an error.
o Use WX500 Diagnostics and Self Test utilities on the
EX500
o Refer to lightning sensor installation and users manual to
troubleshoot.
Lightning Sensor Is Not Communicating Communication of strike data from the lightning sensor to the MFD
has been lost.
o Verify that the sensor is turned on and valid.
o Verify that the EX500 is properly seat in its tray.
o Verify system wiring.
Lightning Heading Source Failed When the lightning sensor is being used as the heading source,
heading data is no longer available from the sensor.
o Verify system wiring (incl. synchro).
o Use WX500 Diagnostics and Self Test utilities on the
EX500
o Refer to lightning sensor installation and users manual to
troubleshoot.
Lightning –Antenna Location Changed Present when the antenna installation configuration between the
MFD and the WX500 is different.
o Verify WX500 antenna location on the aircraft.
o Verify WX500 antenna location configuration (jumper).
o Verify (from EX500 Maintenance Mode) “Lightning Setup
Antenna on Top?” checkbox setting.
(All three should agree)

For details on other errors and parameters sent by the lightning sensor, refer to the lightning sensor
installation and users manuals.

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4.2.3. Traffic Sensor Checkout

4.2.3.1. TCAS I Checkout

Perform a functional test of the TCAS system in accordance with manufacturer’s instructions. Refer to
the MFD Pilot Guide for display operation.

If the self-test fails, test traffic displayed will not be visible or an error message is generated and
displayed on the EX500 display.

Refer to the TCAS installation manual for explanations and fault isolation procedures.

4.2.3.2. Skywatch TAS Checkout

Perform a functional test of the Skywatch TAS in accordance with manufacturer’s instructions. If a
WX-1000 display unit is not installed, refer to the MFD Pilot Guide for display operation.

If the self-test fails, an error message is generated and displayed on the EX500 display.
Refer to the Skywatch TAS installation manual for explanations and fault isolation procedures.

4.2.3.3. Honeywell TAS Checkout

Perform a functional test of the TAS system in accordance with manufacturer’s instructions. Refer to
the MFD Pilot Guide for display operation.

If the self-test fails, an error message is generated and displayed on the EX500 display.
Refer to the KTA-870 and KMH-880 installation manuals for explanations and fault isolation
procedures.

4.2.3.4. 9900BX TAS Checkout

Perform the checkout procedures of the 9900BX TAS in accordance with manufacturer’s instructions.
If a Ryan traffic display unit is not installed, refer to the MFD Pilot Guide for display operation.

If the self-test fails, an error message is generated and displayed on the EX500 display.
Refer to the 9900BX TAS installation manual for explanations and fault isolation procedures.

4.2.3.5. 9900B TCAD Checkout

Perform the checkout procedures of the 9900B TCAD in accordance with manufacturer’s instructions.
The EX500 does not display the TCAD self test function. If you wish to perform this test then you
must use the Ryan TCAD display unit.

If the self-test fails, an error message is generated and displayed on the EX500 display.
Refer to the 9900B TCAD installation manual for explanations and fault isolation procedures.

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Traffic Sensor Communications Troubleshooting

If there is a communication or data error between the traffic sensor and the MFD, one of the following
messages will remain in the lower right corner of the screen.

Message Meaning/Action
Traffic Sensor Is Not Communicating The traffic sensor is reporting a failure condition or not receiving valid
data.
o Verify that the EX500 is properly seat in its tray.
o Verify system wiring.
o Refer to traffic system installation and users manual to
troubleshoot.
Traffic Sensor has FAILED The EX500 RS232 ports are not configured correctly.
{TCAD} o Verify EX500 sensor ports do not conflict.
Traffic can’t connect The EX500 ARINC429 ports are not configured correctly.
{TCAS, TAS} o Verify EX500 sensor ports do not conflict.
TCAD Altitude Unavailable Altitude data is not being received from the traffic sensor.
{TCAD} o Verify that the sensor is turned on and valid.
o Verify system wiring (incl. alt. encoder).
o Refer to traffic sensor installation and users manual to
troubleshoot.
Traffic Heading Source Is Not Valid When the traffic sensor is being used as the heading source,
{TCAS, TAS} heading data is no longer available from the sensor.
o Verify system wiring (incl. synchro).
o Refer to traffic sensor installation and users manual to
troubleshoot.

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4.2.4. TAWS Checkout

4.2.4.1. EGPWS Checkout
With the EX500 selected to the TAWS page, perform a functional test of the EGPWS system in
accordance with manufacturer’s instructions. Refer to the MFD Pilot Guide for display operation.

The EGPWS software must support KC Picture Bus (KCPB) Phase 2. Consult the Honeywell
EGPWS documentation for applicable software configurations. Proper operation of the EGPWS
interface is noted by the absence of any system status messages. If the self-test fails, an error
message is generated and displayed on the EX500 display. Refer to the EGPWS system installation
manual for explanations and fault isolation procedures.

TAWS Communications Troubleshooting

If there is a communication or data error between the TAWS sensor and the MFD, the following
message will remain on the bottom of the screen.

Message Meaning/Action
TAWS Display Failed An incorrect system configuration or failure in one of the system components has
occurred.
o Verify that the sensor is turned on and valid.
o Verify system wiring.
TAWS Display Initializing If message does not clear within 60 seconds, communication between the
EX500 and the Terrain sensor has not been established.
o Verify that the sensor is turned on and valid.
o Verify system wiring.
o Refer to terrain sensor installation and user’s manual to troubleshoot.
TAWS Not Communicating Indicates that the EX500 is not receiving data from the Terrain sensor.
o Verify that the sensor is turned on and valid.
o Verify system wiring.
o Refer to TAWS sensor installation and user’s manual to troubleshoot.
TAWS Display Unavailable The TAWS Sensor has declared itself inoperative.
o Verify system wiring.
o Verify that the sensor inputs to the TAWS are turned on and valid.
o Refer to TAWS sensor installation and user’s manual to troubleshoot.
TAWS Sensor Self-Test The TAWS Sensor is performing a Self-Test. The message will remain until the
self-test is finished.
o Verify that the “Self-Test” mode has been not been selected at the
separate TAWS control panel.
o Verify system wiring.
o Refer to TAWS sensor installation and user’s manual to troubleshoot.
TAWS Display Inhibited The TAWS sensor is in the “Self-Test” mode.
o Verify that the “Self-Test” mode has been not been selected at the
separate TAWS control panel.
o Verify system wiring.
o Refer to TAWS sensor installation and user’s manual to troubleshoot.

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4.2.5. RADAR Checkout

Perform a functional test of the RADAR system in accordance with manufacturers instructions. Refer
to the MFD Pilot Guide for display operation.

4.2.5.1. RADAR Sensor Communications Troubleshooting

If there is a communication or data error between the RADAR sensor and the MFD, the following
message will remain on the bottom of the screen.

Message Meaning/Action
Radar Sensor Data Is Invalid Data received from the RADAR sensor system can not be used by
the EX500
o Cycle power on the EX500.
o Refer to RADAR Sensor installation and users manual to
troubleshoot.
Radar Sensor Has Failed The RADAR sensor system has reported an error.
o Check R/T configuration module error log.
o Refer to RADAR Sensor installation and users manual to
troubleshoot.
Radar Sensor Is Not Communicating Communication of return data from the RADAR sensor to the MFD
has been lost.
o Verify that the RADAR sensor is turned on and valid.
o Verify that the EX500 is properly seat in its tray.
o Verify system wiring.
Invalid GPS Data and Radar is ON The RADAR is ON and the EX500 has no ground speed data
available from the GPS/FMS.
o Verify the GPS/FMS is ON and valid.
o Verify system wiring.
o Refer to RADAR Sensor installation and users manual to
troubleshoot.
Radar Automatic Standby Disabled The RADAR is ON, the EX500 RADAR automatic standby mode is
disabled, and the EX500 has no ground speed data available from
the GPS/FMS.
o Verify the GPS/FMS is ON and valid.
o Verify system wiring.
o Refer to RADAR Sensor installation and users manual to
troubleshoot.

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4.2.6. Narrowcast Datalink Checkout

Refer to the MFD Pilot Guide for datalink related display configuration and operation.

4.2.6.1. Communications Troubleshooting

If there is an internal communication or data error between the satellite transceiver and the MFD main
processor, the following message will remain on the bottom of the screen.

Message Meaning/Action
Datalink Sensor Data Is Invalid The EX500 has received unreadable satellite data.
o Verify that the EX500 is properly seated in its tray.
Datalink Sensor Configuration Error The EX500 Comm Ports are improperly configured for datalink.
o Requires factory servicing. Refer to Factory Service
Policies section of this manual.
Datalink Sensor Is NOT Communicating The EX500 is experiencing a communication failure with the internal
Satellite transceiver.
o Requires factory servicing. Refer to Factory Service
Policies section of this manual.

4.2.6.2. Reception Troubleshooting

The ORBCOMM satellite network transmits very low power VHF signals that the EX500 must receive.
If the antenna is not properly installed or if there is excessive electromagnetic interference (such as
by nearby radio transmitter or inadequately grounded electronics) the system will not achieve
successful reception. The following steps may be taken to assess system performance.
Bring the aircraft to an area that has as few obstacles to line-of-sight viewing to the
southern horizon as possible and orient the aircraft heading south.
From Datalink Info table (see Figure 11), monitor for up to five minutes under the following
conditions; other avionics off, avionics on, engines at idle, engines at takeoff power. With a
satellite in view the signal strength and quality should peak above the following values.
- "Signal strength" is greater than -118 dBm
- "Estimated SNR (EbNo)" is greater than 10 dB
- “Segment errors” less than 10%
If the above reception levels are not achieved the following cause and corrective actions may apply.
• The antenna field of view is obstructed. Try moving or rotating the aircraft.
(if rotation works the antenna location on the aircraft may not be optimal.)
• There is a local source of electromagnetic interference.
- Try shutting off any nearby sources (such as VHF radios, alternators and magnetos).
- Relocated the aircraft away from potential nearby sources.
- Check electrical connections to ensure there is no improper grounding.
• There is poor satellite coverage. Try again after fifteen minutes.
• The antenna and cable are not properly installed.
- The antenna may not be properly connected to the ground plane. There must less
than 0.003 Ohms between the antenna mounting screw and the aircraft skin for proper
grounding.
The cable may not be properly connected to the antenna or EX500 tray.

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The following worksheet will assist in characterizing and troubleshooting the Narrowcast datalink
transceiver installation. The ORBCOMM satellite network transmits very low power VHF signals that
the EX500 must receive. If the antenna is not properly installed or if there is excessive
electromagnetic interference (such as by nearby radio transmitter or inadequately grounded
electronics) the system will not achieve successful reception.

The following steps may be taken to assess system performance.

Bring the aircraft to an area that has as few obstacles to line-of-sight viewing to the southern
horizon as possible and orient the aircraft heading south.
From the Maintenance Mode SYSTEM INFO page access the Datalink Info table (EX500
Installation Manual Section 3.8.1), monitor for up to fifteen minutes under the following conditions
and record the peak values indicated on the EX500.

Signal Strength Estimated SNR Segment Errors

> -118 dBm (EbNo) <10%
> 10 dB
- All avionics OFF __________ __________ __________

Estimated SNR Segment Errors

(EbNo) <10%
> 10 dB
- Electronic Instruments ON __________ __________

- Only Navigation Lights, Strobes and Beacons ON __________ __________

- Transponder ON (and in ALT mode when available) __________ __________

- COM 1 ON __________ __________

- COM 2 ON __________ __________

- Other Radios ON (ADF, DME, etc.) __________ __________

- Fuel Pumps ON (test individually when possible) __________ __________

- Pitot heat ON __________ __________

- Windshield Heat ON __________ __________

- Windshield Wipers ON __________ __________

- Engine ON and at IDLE __________ __________

- Left Magneto OFF __________ __________

- Right Magneto OFF __________ __________

- Engine at TAKEOFF POWER __________ __________

If the reception levels listed above are not achieved, troubleshoot the installation of the offending
system (ex. COM 2) and insure that proper shield terminations are made and adequate harness
separation exists on the aircraft. Additional shielding of the antenna coax cable will often improve
system reception performance. Excessive aircraft ignition noise may stem from Magnetos or Ignition
system wiring.
Consult www.avidyne.com for any additional guidance.

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Due to the weak signal levels of the satellite-based communication network, the datalink system is
very sensitive to electrical noise that may be present on the aircraft. These noise sources include:
Radio transmitters – VHF Communications, Transponders
Ignition/Electrical systems – Magnetos, Alternators
If the signal level, estimated SNR and segment error values achieve the recommended values listed
in Section 3.8 with no other equipment powered on the aircraft and engine not running, but fails in
one or more of the other test conditions, then aircraft noise interference is likely. With the datalink
system active, selectively turning on other equipment and systems one piece at a time can help
isolate the source of datalink interference. Once identified, the suspect system, and its associated
harnessing, should be inspected for proper electrical bonding (grounding). In some cases (ex.
magnetos), additional harness shielding may be required.

4.2.6.3. Interference Troubleshooting

The Narrowcast datalink transceiver is wired to its antenna with a double-shielded coax (RG400)
cable. This shielding design reduces the chances of interference between the datalink system and
other aircraft systems. Care should be taken when selecting where to route the cable from the
EX500 to the antenna. Placing the Narrowcast datalink coax cable away from non-shielded wires and
sensitive systems (ex. analog flight director signals, radio receivers, etc.) will reduce the chances of
interference. Additional shielding may prove necessary where the datalink system is seen to interfere
with other aircraft systems and cable routing modifications are not possible or prove ineffective.

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4.2.7. Broadcast Datalink Checkout

Start the MFD and select the Trip page. Press the Display button to view Broadcast Status (down
pointing arrow). If the MFD reports a Receiver ID the receiver is communicating with the MFD and
the RS-232 wiring is correct.

Position the aircraft in an area open to the sky. A Signal Quality of Good confirms the receiver is
detecting the satellite signals. A Signal Quality of Marginal or Weak may require repositioning the
aircraft to better location. A Signal Quality of None is an indication of a bad antenna, cable,
connection or receiver.

After the MFD has been restarted, any of the following messages may appear in the message bar on
any page and in the message list on the Setup page.

Message Meaning

Broadcast is Operating Normally Verification that the MFD is communicating with the
Broadcast receiver

Broadcast is Not Communicating

The MFD is not communicating with the Broadcast
(After 5 minutes of no communication)
receiver. Check power and wiring.

4.2.8. Broadcast Datalink Satellite Reception Confirmation

The broadcast satellite network transmits signals that are received by an external datalink receiver,
which sends the information on to the MFD through a serial connection. If the datalink antenna is not
properly installed or if there is excessive electromagnetic interference (such as a nearby radio
transmitter or inadequately grounded electronics), the system will not achieve consistent reception.
The following steps may be taken to assess system performance:

• Bring the aircraft to an area that has as few obstacles to line-of-sight viewing to the
southern horizon as possible.
• Select the Trip page on the MFD.
• Press the Display button until Broadcast (down-pointing arrow) Status is selected.
• The Signal Quality will be reported as Good, Marginal, Weak, or None. If the Broadcast
Receiver is working, the antenna and cabling are correct, and the aircraft is in view of at
least one Broadcast datalink satellite, the Signal Quality will be “Good” and the Receiver
ID will be reported.
• Make note of the Receiver ID for the aircraft owner, who will need it to begin Broadcast
datalink service.

If the Signal Quality is not reported as Good, the following cause and corrective actions may apply.
• The antenna field of view is obstructed. Try moving or rotating the aircraft.
Note: if rotation works, the antenna location on the aircraft may not be optimal
• There is a local source of electromagnetic interference.
- Try shutting off any nearby sources (such as VHF radios, alternators and magnetos).
- Relocate the aircraft away from potential nearby sources.
- Check electrical connections to ensure there is no improper grounding.
- The antenna and cable are not properly installed.
- The antenna may not be properly connected to the ground plane.

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- The cable may not be properly connected to the antenna or the EX5000.

Consult www.avidyne.com for any additional guidance.

4.2.9. Synchro Heading Checkout

With the EX500 powered and operating, and the EX500 heading source set to synchro (ref. Section
3.9), verify the heading displayed on the Map page matches the actual aircraft heading.

Important: The EX500 MUST be receiving GPS position in order to display heading. If GPS position
is not valid, magnetic heading will be display as three dashes (“---“).

4.2.9.1. Heading Source Troubleshooting

If there is a data error between the aircraft heading synchro source and the MFD, the following
message will remain on the bottom of the screen.

Message Possible Cause Action

Synchro Heading is NOT No 400 Hz excitation on REF HI Verify synchro excitation
Valid “Heading Valid” is inactive or incorrectly If a “Heading Valid” input is connected from the
specified heading source, ensure:
The proper active level has been selected (Section
3.9)
External series resistor R1 has been installed
(Appendix F)

*When using the EX500's direct synchro interface, the following table can be used to troubleshoot
and correct wiring errors. If it is determined that the X, Y, or Z lines are incorrectly connected, BE
SURE TO SWAP THE APPROPRIATE LINES AT THE EX500. Swapping lines at the synchro
source could result in unintentional heading problems with other devices connected to the aircraft
heading system.

*In addition, only use the following table if heading is continuously present on the EX500 with
incorrect readings. If the heading display is intermittent or blank, then all five synchro lines should
first be checked for continuity and shorts.

*If no continuity errors or shorts are present in the system, use the manual slew feature of the
aircraft's compass system to position the H.S.I. at 0, 120, and 240 degrees.

Write down the corresponding EX500 heading readings and then use the following table to correct the
wiring.

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Compass System
EX500 Reading Error Amount Problem Solution
Reading
0 0 0
120 240 +120 X and Y Crossed Swap X and Y
240 120 -120
0 240 -120
120 120 0 X and Z Crossed Swap X and Z
240 0 +120
0 120 +120
120 0 -120 Y and Z Crossed Swap Y and Z
240 240 0
0 240 -120
Swap Y and Z,
120 0 -120 YZX Cross
then swap X and Y
240 120 -120
0 120 +120
Swap X and Y,
120 240 +120 ZXY Cross
then swap Y and Z
240 0 +120
0 180 180 Ref HI and Ref LO reversed Swap Ref HI and Ref LO

4.3. Post Installation Check EMI Check

The following procedure is performed to verify that no interference is noted through the use of the
EX500 MFD on other systems in the aircraft. The operation of the EX500 MFD shall not result in Nav
flags, constant location lightning strikes on any installed Stormscope, noise on COMM channels, or
other phenomena.

Comm Radios:
Scan through radio channels to ensure there is no interference caused by the EX500 or no
break in squelch due to the installation.
Check local ground and tower frequencies to ensure there is no break in squelch due to the
installation.
GPS:
Ensure that correct position is displayed
Verify no change in satellite signal strength on the GPS receiver with EX500 unit powered
ON or OFF.
Autopilot:
Ensure that autopilot self-test passes OK with EX500 powered on.

Other Instruments:
Verify that there is no adverse effect on other instruments with EX500 powered ON

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5. MFD Data Updates

5.1. Map NavData Database Updates
The Map NavData database may be updated periodically with data purchased from Jeppesen,
www.jeppesen.com.
All MFD units are shipped with the latest database pre-loaded. There are two places to check the
expiration date or version number:
• The Startup Screen
• The Setup Page
Updates are available via an optional Data Loader that connects to the Data Loader (USB) port on
the front of the MFD.

5.1.1. To perform a data update

1. Turn power OFF to the MFD.
2. Install data disk into the Data Loader drive.
3. Connect one end of the interconnect cable to the Data Loader and the other end to
the MFD data port on the front panel of the MFD.
NOTE: Ensure that the Data Loader is supported and not dangling by the cable. This
may cause an intermittent connection, which will result in an unsuccessful
data update.

4. Apply power to the MFD.

5. The Data Loader screen is displayed.
NOTE: If the regular MFD startup screen with the “Press Any Bezel Key” message is
displayed, the Data Loader was not detected by the MFD. Check the
connection between the Data Loader and the MFD. Cycle power to the MFD.

6. Press the “Proceed” button. Do not turn off the MFD or disconnect the interconnect
cable during a data load.
7. The data load is complete when the “Press Any Bezel Key” message is displayed.
8. Remove the Data Loader and interconnect cable and store in a safe place.

5.2. Chart Database Updates

The database of terminal procedure charts must be updated periodically with data purchased via
subscription from Jeppesen, www.jeppesen.com.

MFD units are shipped without any chart data pre-loaded. It is up to the user to obtain a valid
subscription from Jeppesen. Once the user has a valid Jeppesen subscription serial number, they
should visit www.myAvidyne.com to obtain an Avidyne Key number, which will allow use of that
subscription on a certain MFD. The user will have to register their MFD with myAvidyne.com if they
have not already done so. Both the Jeppesen subscription number and the Avidyne Key number are
required to complete a chart data load.

There are two places to check the expiration date of the chart data:
• The Startup Screen
• The Setup Page
Updates are loaded via an optional Data Loader that connects to the Data Loader (USB) port on the
front of the MFD.

Once the user has both a Jeppesen subscription number and Avidyne Key number, they can run the
Avidyne Data Extractor program on their PC to extract their chart data from the Jeppesen CD-ROM

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and save it onto a disk in the Avidyne Dataloader device. The Avidyne Dataloader is then ready to
complete the chart update.
NOTE: For more information on running Avidyne Data Extractor, consult Avidyne
600-00114-000, Avidyne CMax Data Update Guide

5.2.1. To perform a chart data update

1. Turn power OFF to the MFD.
2. Install data disk into the Data Loader drive.
3. Connect one end of the interconnect cable to the Data Loader and the other end to
the MFD data port on the front panel of the MFD.
NOTE: Ensure that the Data Loader is supported and not dangling by the cable. This
could cause an intermittent connection, which will result in an unsuccessful
data update. Cycle power to the MFD.

4. Apply power to the MFD.

5. The Data Loader screen is displayed.
NOTE: If the regular MFD startup screen with the “Press Any Bezel Key” message is
displayed, the Data Loader was not detected by the MFD. Check the
connection between the Data Loader and the MFD.

6. Press the “Proceed” button. Do not turn off the MFD or disconnect the interconnect
cable during a data load.
7. The data load is complete when the normal startup screen with the “Press Any Bezel
Key” message is displayed.
8. Remove the Data Loader and interconnect cable and store in a safe place.

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6. Factory Service Policies

6.1. Technical Support

Avidyne’s web site contains information that may assist the operator and installer with questions or
problems with their FlightMax EX500-Series Multi-Function Display.

www.avidyne.com

Technical support questions may be submitted, 24 hours per day, via the following:

Email: techsupport@avidyne.com

Fax: 781-402-7599

Voice: 888-723-7592

An Avidyne technical support representative will respond as soon as possible. Avidyne business
hours are 8:00 AM to 5:00 PM Eastern Time, Monday through Friday.

Please include the part number, revision number and serial number of the unit in all
correspondences. For problem reporting, please provide as many details associated with the problem
as possible.

6.2. General Service Procedures

Repair of the EX500 is performed at the factory, and includes a complete checkout and recalibration.

Prior to returning a unit for service, contact Avidyne at 888-723-7592 to obtain a Return Merchandise
Authorization (RMA) number.

Securely pack the unit in the original Avidyne shipping carton, write the RMA number on the outside
of the carton, and return it to the address provided by the Avidyne Customer Service Representative.

Include your name, complete shipping address, daytime telephone number, a complete description of
the problem, the desired return date, and shipping method.

If the original shipping carton or other suitable foam packing is not available, contact Avidyne to
arrange for packaging materials. Avidyne is not responsible for damage due to poorly packaged
returns.

6.3. AC 20-68B Recommended Radiation Safety

DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
WASHINGTON, D.C.

PURPOSE. This circular sets forth recommended radiation safety precautions to be taken by personnel when operating
airborne weather radar on the ground.

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1. CANCELLATION. AC20-68, dated April 11, 1975, is cancelled.

2. RELATED READING MATERIAL:

Barnes and Taylor, Radiation Hazard and Protection (London: George Newnes Limited, 1963), p.211.

U.S. Department of Health, Education and Welfare, Public Health Service, Consumer Protection and Environmental
Health Service, "Environmental health microwaves, ultraviolet radiation and radiation from lasers and television receivers
- An Annotated Bibliography," FS 2.300: RH-35, Washington, U.S. Government Printing Office, pp. 56-57.

Mumford. W.W., "Some technical aspects of microwave radiation hazards," Proceedings of the IRE, Washington, U.S.
Government Printing Office, February 1961, pp. 427-447.

1. BACKGROUND. Dangers from ground operation of airborne weather radar include the possibility of human body
damage and ignition of combustible material by radiated energy. Low tolerance parts of the body include the eyes and
testes.

2. PRECAUTIONS. Management and supervisory personnel should establish procedures for advising personnel of dangers
from operating airborne weather radars on the ground. Precautionary signs should be displayed in affected areas to alert
personnel of ground testing.

General.

Airborne weather radar should be operated on the ground only by qualified personnel.

1. Installed airborne radar should not be operated while the aircraft is in a hangar or other enclosure unless the radar
transmitter is not operating, or the energy is directed toward an absorption shield which dissipates the radio frequency
energy. Otherwise, radiation within the enclosure can be reflected throughout the area.
2. Body Damage. To prevent possible human body damage, the following precautions should be taken.
Personal should never stand nearby and in front of a radar antenna which is transmitting. When the antenna is not
scanning, the danger increases.

3. A recommended safe distance from operating airborne weather radars should be established. A safe distance can be
determined by using the equation in Appendix 1 or the graphs of figures 1 and 2. This criterion is now accepted by many
industrial organizations and is based on limiting exposure of humans to an average power density not greater than 10
milliwatts per square centimeter.
4. Personnel should be advised to avoid the end of an open waveguide unless the radar is turned off.
5. Personnel should be advised to avoid looking into the waveguide, or into the open end of a coaxial connector or line
connector to a radar transmitter output, as severe eye damage may result.
6. Personnel should be advised that when high power radar transmitters are operated out of their protective cases, X-rays
may be emitted. Stray X-rays may emanate from the glass envelope type pulser, oscillator, clipper, or rectifier tubes, as
well as magnetrons.
7. Combustible Materials. To prevent possible fuel ignition, an installed airborne weather radar should
not be operated while an aircraft is being refueled or defueled.

M.C. BEARD
Director of Airworthiness

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Appendix A Environmental Qualification Forms

RTCA/DO-160D ENVIRONMENTAL QUALIFICATION FORM

NOMENCLATURE: EX500 Multi-Function Display

PART NO: 700-00007-XXX-()
TSO NUMBER C113, C63c, C118, C110a, C147
MANUFACTURER: AVIDYNE CORPORATION
ADDRESS: 55 OLD BEDFORD ROAD, LINCOLN, MA 01773

RTCA/DO-160D CONDUCTED TEST

CONDITIONS
PARAGRAPH CATEGORY
TEMPERATURE 4.5 D1
INFLIGHT LOSS OF COOLING 4.5.4 V,D1
ALTITUDE 4.6.1 D1
DECOMPRESSION 4.6.2 D1
OVERPRESSURE 4.6.3 D1
TEMPERATURE VARIATION 5.0 B
HUMIDITY 6.0 A
OPERATIONAL SHOCK 7.2 B
CRASH SAFETY 7.3 B
VIBRATION 8.0 Cat. S Curves M
EXPLOSION 9.0 X (Not Tested)
WATERPROOFNESS 10.0 X (Not Tested)
FLUIDS SUSCEPTIBILITY 11.0 X (Not Tested)
SAND AND DUST 12.0 X (Not Tested)
FUNGUS 13.0 X (Not Tested)
SALT SPRAY 14.0 X (Not Tested)
MAGNETIC EFFECT 15.0 Z
POWER INPUT 16.0 B
VOLTAGE SPIKE 17.0 A
AUDIO FREQUENCY CONDUCTED SUSCEPTIBILITY 18.0 Z
INDUCED SIGNAL SUSCEPTIBILITY 19.0 A
RADIO FREQUENCY SUSCEPTIBILITY 20.0 V
EMISSION OF RADIO FREQUENCY ENERGY 21.0 M
LIGHTNING INDUCED TRANSIENT SUSCEPTIBILITY 22.0 A3E3
LIGHTNING DIRECT EFFECTS 23.0 X (Not Tested)
ICING 24.0 X (Not Tested)
ELECTROSTATIC DISCHARGE 25.0 A

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Appendix B STC EX500 Permission

Avidyne Corporation here by grants permission to all National Aviation Authority (FAA, CAA, JAA) approved
installers to use data from STC SA00161BO and amendments to modify aircrafts. The latest version of the
associated AVMFC-076 Avidyne 700-0007-XXX-() MFD (EX500) Approved Model List may be accessed by
authorized dealers at www.avidyne.com. Copies of the STC and amendments follow:

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Appendix C Installation Mechanical: MFD, Tray & Panel Dimensions

6.3 TRAY WIDTH

6.2 FACEPLACE WIDTH

4.35 4.4
FACEPLATE TRAY
HEIGHT HEIGHT

J2 - DATALINK P2 - MAIN
HDB-78 P1 - ANALOG RADAR
50 OHM COAX J1 - VIDEO INPUT
HDB-44
FRONT VIEW - MFD 75 OHM COAX
(NOT SUPPORTED - SHOWN
IN TRAY REAR VIEW - TRAY FOR REFERENCE ONLY

W/ CONNECTORS
ATTACHED
AFT FACING
PLANE OF PANEL

12.8 TRAY + CONNECTOR DEPTH

11.4 TRAY DEPTH

.7 6.3 CENTER OF GRAVITY

1.0

1.25

1.0 2.2

.60 .55

.48
9.5
COUNTERSUNK HOLES FOR
#6 FLATHEAD SCREWS
5 PLACES ON EACH SIDE OF TRAY
SIDE VIEW - MFD IN
TRAY
NOTES:
1. DIMENSIONS IN INCHES.
2 WEIGHT AND CENTER OF GRAVITY FOR MFD, TRAY, AND CONNECTORS.

AVIDYNE CORPORATION
EX500 INSTALLATION MECHANICAL
MFD, TRAY AND PANEL CUT-OUT
DIMENSIONS

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PANEL CUTOUT
TRAY INSTALLED FROM FRONT OF AIRCRAFT PANEL

PANEL CUTOUT
TRAY INSTALLED FROM REAR OF AIRCRAFT PANEL
ONLY!

NOTE: MAXIMUM INSTRUMENT PANEL

THICKNESS IS .125 IN

NOTES:
1. DIMENSIONS IN INCHES.
2 FOR ALL TYPES OF INSTALLATION, IF THE REAR FACE
OF THE EX500 BEZEL/FACEPLATE DOES NOT CONTACT THE
BOTTOM LIP OF THE TRAY, THE REAR CONNECTORS MAY NOT
BE FULLY ENGAGED, RESULTING IN POOR OR INTERMITTENT
CONTACT. AVIDYNE CORPORATION
EX500 INSTALLATION MECHANICAL
MFD, TRAY AND PANEL CUT-OUT
DIMENSIONS

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Appendix D Installation Mechanical: Tray Support Structure Panel

AUDIO PANEL OR OTHER AVIONICS

RPM RPM

AUTOPILOT OR OTHER AVIONICS

MAP MAP

OIL T OIL T

FLIGHTMAX
EX500
NAV/COM OR OTHER AVIONICS
OIL P OIL P

FF FF TRANSPONDER OR OTHER AVIONICS

GPS/NAV/COM OR OTHER AVIONICS

A
FRONT VIEW - RADIO PANEL
ALUMINUM 2024-T3
FASTEN ANGLE WITH PER AMS 4037 & AMS QQ-A-250/4
RIVETS MS20426A- ANGLE, 0.063 X 0.75 X 0.063" ATTACH TO EXISTING
BOTH SIDES STRUCTURE IF AVAILABLE

TAIL BRACE (TYPICAL)

INSTRUMENT OR
RADIO PANEL 2024-T3 ALUMINUM
PER AMS 4037 & AMS QQ-A-250/4
FLAT 0.75 MIN x 0.032 MIN
BOTH SIDES

#6-32 FLAT HEAD

SPACE TRAYS BY SCREWS AN510
0.05 3 PLACES, BOTH SIDES

AFT FACING
PLANE OF PANEL

MOMENT
6.25
NARROWCAST
DATALINK ANTENNA
WT =7.2 LBS

VIDEO INPUT
(NOT SUPPORTED - SHOWN
FOR REFERENCE ONLY)

SPACE TRAYS BY
0.05

A-A
SIDE VIEW - MFD IN
TRAY
AVIDYNE
NOTES:
1. DIMENSIONS IN INCHES. EX500 INSTALLATION MECHANICAL
2 WEIGHT AND MOMENT FOR MFD, TRAY, AND CONNECTORS. PANEL, TRAY SUPPORT STRUCTURE
3. REAR SUPPORT STRUCTURE REQUIRED.

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Appendix E Installation Mechanical: Narrowcast Datalink Antenna

ACCEPTABLE UNACCEPTABLE

PREFERRED
DATALINK ANTENNA
LOCATION

UNACCEPTABLE
Ø 0.1285
ANTENNA MOUNTING 20 PLACES
SPACED 1.5 NOMINAL
LOCATION
Ø 0.75 Ø 0.177
4 PLACES

0.812

23
OVAL HEAD SCREW 18
NAS387-388
OR FLAT HEAD 0.812

COUNTERSUNK
LOCK WASHER MS35790
(FOR AV14)
1.00
1.00

GASKET (AV14)
NOT TO SCALE
RIVET NAS1097AD3-5
FOR NUTPLATE RIVET NAS1097AD4-3
FOR DOUBLER 20 PLACES ANTENNA DOUBLER PLATE
FUSELAGE SKIN
RIVET MS20470AD4-6
EXISTING STRUCTURE
DOUBLER PLATE WITH FLANGES OR JOGGLE
NUTPLATE MS21059-L08 FASTENED TO EXITING STRUCTURE (TYPICAL)
OR
SELF LOCKING NUT MS21044-N3

ANTENNA INSTALLATION
NOTES:
CROSS SECTION
1. ANTENNA: COMANT 177-4 (250 KNOTS) OR COMANT 248-30 (350 KNOTS).
2. INSTALL IN ACCORDANCE WITH AC 43.13, ANTENNA MFG GUIDANCE, AND TSO STANDARDS.
3. ANTENNA LOCATION: TOP OF AIRCRAFT. DISTANCE FROM TRANSMITTING ANTENNA: 36 IN. MIN. DISTANCE FROM VERTICAL
STABILIZER: 36 IN. MIN. ALLOWABLE HEIGHT OF VERTICAL STRAKE NEXT TO ANTENNA BASE: 2 IN MAX.
4. GROUND PLANE REQUIRED, 12 RADIUS MIN FOR NON METALLIC FUSELAGE.
5. ANTENNA DOUBLER PLATE FOR ALUMINUM FUSELAGE TYPICAL. DOUBLER SPANNING 2 STRINGERS, 0.125 MIN. DIA. RIVET SPACED 1.5
ON ALL EDGES OF DOUBLER. PREP AND COAT WITH CONDUCTIVE CHROMATE OR ALIDYNE.
6. ANTENNA GROUND CONNECTION MADE VIA INSIDE SURFACE OF FASTENER COUNTERSINK. REMOVE PAINT FROM COUNTERSINK
SURFACES AND COAT WITH CONDUCTIVE SEALANT OR INSTALL COUNTERSUNK LOCK WASHERS PER MFG GUIDANCE.
7. MOUNTING HARDWARE: TORQUE EVENLY. SEAL EXPOSED SURFACE AND COUNTERSINK SURFACE.
8. RESISTANCE: ANTENNA GROUND TO MOUNTING HARDWARE TO DOUBLER TO AIRFRAME/GROUND PLANE MAX < 0.5 OHM
9. ANTENNA CABLE: RG-400/U COAX, STRANDED CORE. ROUTE COAX ANTENNA CABLE TO MFD WITH NO KINKS OR BENDS GREATER THAN
2 IN. RADIUS. SECURE ALONG LENGTH, AVOID CHAFING.
10. FIBER REINFORCED PLASTIC (COMPOSITE) FUSELAGE INSTALLATION ONLY IN ACCORDANCE WITH AIRFRAME MFG GUIDANCE,
APPROPRIATE SIMILAR STC BASIS, OR DER APPROVAL.
11. AIRCRAFT PRESSURE VESSEL INSTALLATION ONLY IN ACCORDANCE WITH AIRFRAME MFG GUIDANCE, APPROPRIATE SIMILAR STC
BASIS, OR DER APPROVAL.
12. ANTENNA SPECIFICATIONS: FREQUENCY:137-151 MHz,
VSWR: 2.0 to 1 MAX, IMPEDANCE: 50 OHM, AVIDYNE CORPORATION
POLARIZATION PATTERN: VERTICAL OMNI-DIRECTIONAL,
TERMINATION:DC SHORT (ONLY) BETWEEN CENTER CONDUCTOR AND SHIELD EX500 INSTALLATION MECHANICAL
RF POWER: 5 W, HEIGHT:18 IN MAX,
TSO C37d, C38d, DATA LINK ANTENNA
RTCA/DO-160c, ENV.CAT. D2-AC SXSXDFSXXXXXXXXXX

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Appendix F EX500 Wiring: General

AVIDYNE
700-00007-XXX
EX500
P2 FLIGHTMAX MFD

20 AWG 22 AWG
AVIONICS POWER 28VDC 40 28 VDC
22 AWG
7.5 AMP 41 28 VDC
22 AWG
42 28 VDC
RTN 20 AWG 22 AWG
60 GND
22 AWG
61 GND
22 AWG
62 GND

A/C INSTRUMENT DIMMING 18 DIMMING

GROUND 37 GND
NOTE 4

AIRCRAFT
HEADING SOURCE NOTE 3 R2: 10K 1/4 W
SYNCHRO
R1: 10K 1/4 W
VALID 33 SYNCHRO VALID
NOTE 1
SYNCHRO X 16 SYNCHRO X
SYNCHRO Y 35 SYNCHRO Y
SYNCHRO Z 54 SYNCHRO Z
REF HI NOTE 2
74 REF HI
REF LO 17 REF LO
NOTE 4

NARROWCAST J2
RG 400 COAX ** NOTE 5 **
DATALINK ANTENNA 1 DL ANTENNA
2 GROUND

WIRING DIAGRAM SYMBOLS

OPTIONAL WIRING TWISTED TRIPLE SINGLE SHIELD

CHASSIS GROUND TWISTED PAIR DOUBLE SHIELD

NOTES:
1. THE SYNCHRO HEADING SOURCE IS THE PREFERRED EX500 HEADING
REFERENCE. THE UNIT WILL ALSO ACCEPT HEADING INFORMATION IF
SUPPLIED FROM CERTAIN FMS, TRAFFIC AND LIGHTNING DETECTION
SOURCES.
2. SIGNALS: REFERENCE HI AND LO SUPPLIED BY EXTERNAL SOURCE
(HEADING SOURCE OR A/C SUPPLY). 26 VAC RMS @ 400HZ, X/Y/Z
SIGNAL INPUTS = 11.8 VAC RMS SUPPLIED BY HEADING SOURCE.
REFERENCE AND SIGNAL INPUT WAVEFORMS MUST BE IDENTICAL,
E.I. EITHER BOTH SINE WAVES OR BOTH SQUARE WAVES.
3. WHEN USING SYNCHRO FOR THE HEADING SOURCE, INSTALL RESISTORS
WHEN REQUIRED AS FOLLOWS:
R1: SYNCHRO SOURCE HAS "VALID" OUTPUT SIGNAL AVAILABLE, AVIDYNE CORPORATION
R2: SYNCHRO SOURCE "VALID" SIGNAL WIRED TO THE EX500 ONLY.
4. TERMINATE SHIELD TO P2 CONNECTOR BACKSHELL (CHASSIS GROUND).
5. ** TO MINIMIZE POSSIBLE INTERFERENCE, THE DATALINK ANTENNA CABLE EX500 INSTALLATION WIRING DIAGRAM
SHOULD BE ROUTED AS TO AVOID CLOSE PROXIMITY WITH OTHER GENERAL EX500 WIRING
SENSITIVE AVIOINCS SYSTEM. ADDITIONAL CABLE SHIELDING MAY
REDUCE ANY DETECTED SYSTEM INTERFERENCE. **

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Appendix G EX500 Wiring: GPS/FMS Sub-system

GPS/FMS SOURCE A INTERCONNECT

(NOTE 1)
AVIDYNE
GARMIN
GPS/FMS GARMIN GARMIN BENDIX/KING UNIVERSAL HONEYWELL 700-00007-XXX
GNC 155XL/
429 OUTPUT GNS 430 GNS 530 KLN-90B UNS-1B GNS-XLS EX500
300XL
J101 P4001 P5001 J901 P5001 J101 P2 FLIGHTMAX MFD
429 TX A 16 46 46 24 J12 17 5 GPS A 429 RX A
429 TX B 15 47 47 23 K12 18 25 GPS A 429 RX B

OR
GARMIN
GPS NORTHSTAR GARMIN GARMIN TRIMBLE NOTE 4
GNC 155XL/
232 OUTPUT M3 GNS 430 GNS 530 2000/2000A
300XL
P15 J1 P4001 P5001 P1

232 TX 6 24 56 56 5 11 GPS A 232 IN

GND 5 GND GND GND GND 12 GPS A 232 RTN

GPS/FMS SOURCE B INTERCONNECT

(NOTE 2)
AVIDYNE
700-00007-XXX
GARMIN EX500
GPS/FMS GARMIN GARMIN BENDIX/KING UNIVERSAL HONEYWELL
GNC 155XL/
GNS 430 GNS 530 KLN-90B UNS-1B GNS-XLS P2 FLIGHTMAX MFD
429 OUTPUT 300XL
J101 P4001 P5001 J901 P5001 J101 45 TRAFFIC 429 A
429 TX A 65 TRAFFIC 429 B
16 46 46 24 J12 17
429 TX B 15 47 47 23 K12 18 48 GPS B 429 RX A
68 GPS B 429 RX B
OR SHIELDS NOT (SEE NOTE 3)
GARMIN SHOWN
GPS NORTHSTAR GARMIN GARMIN TRIMBLE
GNC 155XL/
232 OUTPUT M3 GNS 430 GNS 530 2000/2000A
300XL
P15 J1 P4001 P5001 P1

232 TX 6 24 56 56 5 70 GPS B 232 IN

GND 5 GND GND GND GND 71 GPS B 232 RTN

NOTE 4

NOTES:
1. GPS/FMS INPUTS MAY BE EITHER ARINC 429 OR RS-232. ARINC 429 IS THE
PREFERRED GPS/FMS INPUT. USE RS-232 IF ARINC 429 IS UNAVAILABLE.
2. GPS/FMS SOURCE B MAY BE INTERFACED TO ANY OF THE ABOVE
IDENTIFIED SERIAL INTERFACES, IF AVAILABLE. IF A SECOND ARINC 429
PORT IS UNAVAILABLE, USE GPS B 232 INPUT PORT. REFER TO THE
GPS/FMS CONFIGURATION SETUP GUIDE IN THIS MANUAL FOR SETUP
INSTRUCTIONS.
3. ARINC 429 DEFAULT SETTINGS: AVIDYNE CORPORATION
PORT #2: TRAFFIC SENSOR (MAY BE USED FOR GPS B WHEN NOT
WIRED FOR TRAFFIC)
PORT #4: TAWS (MAY BE USED FOR GPS B WHEN PINS 2 AND 29 ARE
EX500 INSTALLATION WIRING DIAGRAM
NOT WIRED GPS, FMS
4. TERMINATE SHIELD TO P2 CONNECTOR BACKSHELL (CHASSIS GROUND).

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Appendix H EX500 Wiring: Lightning and Broadcast Datalink Sensors

AVIDYNE
700-00007-XXX
EX500
FLIGHTMAX MFD

XM WX HEADS UP
DATALINK XMD076
P2
232 RX 4 69 XM WX 232 OUT

GND 23 71 XM WX 232 RTN

232 TX 22 70 XM WX 232 IN

LIGHTNING
SENSOR GOODRICH
WX500
P3
232 TX 20 P2
232 RX 8
P2
50 LIGHTNING 232 IN
GND 5 51 LIGHTNING 232 RTN
49 LIGHTNING 232 OUT

NOTE 1

NOTES:
1. TERMINATE SHIELD TO P2 CONNECTOR BACKSHELL (CHASSIS GROUND).

AVIDYNE CORPORATION
EX500 INSTALLATION WIRING DIAGRAM
LIGHTNING AND BROADCAST XM
DATALINK SENSORS

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Appendix I EX500 Wiring: Traffic Sensors

GOODRICH GOODRICH GOODRICH AVIDYNE

TAS/TCAS SKYWATCH SKYWATCH HP TCAS 791 700-00007-XXX
FLIGHTMAX EX500
TRC497 TRC899 TCAS791
MFD
J1 J1 P1 P2
429 TX A 34 42 7 (TX+) 45 TRAFFIC 429 A
429 TX B 33 43 8 (TX-) 65 TRAFFIC 429 B
NOTE 4 NOTE 1
SFTKEYx 85 19 7 TTL2
SFTKEY4 82 21 47 TTL3
PWRSWHI 11 5
PWRSWHI 3 4 NOTE 2 NOTE 3
ALT DISP 80 N/A

AVIDYNE
700-00007-XXX
TCAS I HONEYWELL FLIGHTMAX EX500
CAS-66A
MFD
P1A P1B P2
429 TX A 28 45 TRAFFIC 429 A
429 TX B 29 65 TRAFFIC 429 B
DISPLAY STATUS
NOTE 3
TA VALID #2 35
RA VALID #2 86

AVIDYNE
700-00007-XXX
TIS GARMIN FLIGHTMAX EX500
GTX-330
MFD
P3301 P2
429 OUT 2 A 30 45 TRAFFIC 429 A
429 OUT 2 B 28 65 TRAFFIC 429 B

NOTE 3

AVIDYNE
700-00007-XXX
FLIGHTMAX EX500
TCAD/TAS RYAN
MFD
9900B/9900BX
P2
P1
232 RX 19 30 TRAFFIC 232 OUT

GND GND 32 TRAFFIC 232 RTN

232 TX 17 31 TRAFFIC 232 IN

NOTE 3

NOTES: AVIDYNE CORPORATION

1. CONNECT TAS SOFTKEYS TO ONLY 1 CONTROLLER.
2. REFER TO GOODRICH INSTALL GUIDANCE FOR SKYWATCH EX500 INSTALLATION WIRING DIAGRAM
AND SKYWATCH HP ON/OFF CONTROL AND
CONFIGURATION FOR USE WITH AN ALTERNATE DISPLAY. TAS, TCAS, TCAD, TIS
3. TERMINATE SHIELD TO P2 CONNECTOR BACKSHELL (CHASSIS GROUND).
4. SFTKEY1 FOR SKYWATCH, SFTKEY2 FOR SKYWATCH HP

Page 61 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix J EX500 Wiring: Traffic/TAWS Sensors

AVIDYNE
700-00007-XXX
EX500
FLIGHTMAX MFD

TAWS/EGPWS HONEYWELL HONEYWELL

KTA 810 KMH 820 P2
429 TX #1 A 54 45 TRAFFIC 429 A
429 TX #1 B 55 65 TRAFFIC 429 B
429 RX #2 A 95 9 TAWS 429 TX A
429 RX #2 B 96 29 TAWS 429 TX B
453 TX A 103 56 TAWS 453 RX A
453 TX B 104 59 TAWS 453 RX B

NOTE 1

AVIDYNE
TAWS HONEYWELL HONEYWELL HONEYWELL BENDIX KING 700-00007-XXX
MK V MK VII MK VI/ MK VIII KGP-560 (GA) EX500
MIDDLE UPPER-J2 J2 J1 P2 FLIGHTMAX MFD

429 RX A 10A 13 37 47 9 TAWS 429 TX A

429 RX B 10B 14 36 66 29 TAWS 429 TX B
TOP LOWER-J1A J1 56 TAWS 453 RX A
59 TAWS 453 RX B
453 TX A 3A 15 58 30
453 TX B 3B 16 59 10

NOTE 1

AVIDYNE CORPORATION

NOTES: EX500 INSTALLATION WIRING DIAGRAM

1. TERMINATE SHIELD TO P2 CONNECTOR BACKSHELL (CHASSIS GROUND).
TRAFFIC/TAWS

Page 62 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix K EX500 Wiring: Digital RADAR

OPTION 1
SINGLE RADAR DISPLAY

ARINC 708 BENDIX/KING BENDIX/KING BENDIX/KING

RADAR RDR 2000/2100 RDS 81/82 RDS 84/86 AVIDYNE
ART ART 2000/2100 RS 181A/811A RS 841A 700-00007-XXX
EX500
P5001 P1001 P1001 FLIGHTMAX MFD
P2

R/T ON #1 31 24 m 1 TTL1 (R/T ON)

429 RX 1A 2 19 a 46 RADAR 429 A
429 RX 1B 3 20 G 66 RADAR 429 B
75 RADAR 453 A
453 TX A 42 8 X 78 RADAR 453 B
453 TX B 43 9 A

R/T ON #2 32 12 p NOTE 1
429 RX 2A 4 18 C
429 RX 2B 5 5 Y

OPTION 2
DUAL RADAR DISPLAY
BENDIX/KING BENDIX/KING BENDIX/KING
RADAR
RDS 86 RDS 84 RDS 81/82
INDICATOR
IN 862A IN 842A IN 812A
P2001 P2001 P2001

n n 31 R/T ON #1
f f 27 429 TX A
L L 2 429 TX B

K K 1 453 RX A
e e 20 453 RX B

F F 8 IND STRAP
ARINC 708 BENDIX/KING BENDIX/KING BENDIX/KING
RADAR RDR 2000/2100 RDS 81/82 RDS 84/86
ART ART 2000/2100 RS 181A/811A RS 841A

P5001 P1001 P1001

AVIDYNE
R/T ON #1 31 24 m 700-00007-XXX
429 RX 1A 2 19 a EX500
429 RX 1B 3 20 G P2 FLIGHTMAX MFD
NOTE 2
453 TX A 42 8 X 75 RADAR 453 A
453 TX B 43 9 A 78 RADAR 453 B

R/T ON #2 32 12 p 1 TTL1 (R/T ON)

429 RX 2A 4 18 C 46 RADAR 429 A
429 RX 2B 5 5 Y 66 RADAR 429 B
SHIELD AS SHOWN IN
OPTION 1

NOTES: AVIDYNE CORPORATION

1. TERMINATE SHIELD TO P2 CONNECTOR BACKSHELL (CHASSIS GROUND).
2. HARNESS SPLICE TO BE MADE WITHIN CONNECTOR BACKSHELL OF ANY EX500 INSTALLATION WIRING DIAGRAM
ONE OF THE THREE UNITS.
DIGITAL RADAR, INDICATOR

Page 63 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix L EX500 Wiring: RDR-130/150/160 RADAR Direct Connect

RADAR ANTENNA BENDIX/KING BENDIX/KING

RDR-130/150 RDR-160 AVIDYNE
RECEIVER
RT-131A RT-161A 700-00007-004
TRANSMITTER
P1001 P1101 EX500
(ART)
P1 FLIGHTMAX MFD
GND E d 28,34 GND
RT ON/OFF G D 8 RT ON/OFF
TRIGGER N A 11 TRIGGER
TRG SHLD P Z 29 GND
TO RT-131
GAIN HI R H(N/C)
GAIN LO S(N/C) T TO RT-161 16 GAIN ADJ
RT-131 ONLY
VID INTG U N/C 25 VID_INTG
DATA2 V B 13 DATA2
DATA1 W C 12 DATA1
DATA SHLD Z F 30,31 GND
TEST Y E 7 TEST
+20 VDC H L 19 +20 VDC
-20 VDC M J 21 -20 VDC
ANTENNA
J1003
RT-131 ONLY
BORE SIGHT F N/C 1 BORE SIGHT
AZ DRV G R 9 AZ DRV
AZ DRV90 H P 10 AZ DRV90
TILT ADJ L K 14 TILT ADJ
+20 VDC B N/C
-20 VDC C N/C
GND Z N/C
POWER
P/O P1001
28 VDC IN A e 28VDC
28 VDC IN B S AVIONICS POWER NOTE 1
GND C h
GND D f GND

AVIDYNE CORPORATION
NOTES:
1. TERMINATE SHIELD TO P1 CONNECTOR BACKSHELL (CHASSIS GROUND).
EX500 INSTALLATION WIRING DIAGRAM
BENDIX/KING RADAR RDR-130/150/160

Page 64 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix M EX500 Wiring: RDR-130/150/160 RADAR w/ Adaptor Cable

AVIDYNE
100-00082-XXX
RADAR ANTENNA BENDIX/KING BENDIX/KING
RECEIVER RDR-130/150 RDR-160
FOR RT-131A USE P/N 100-00082-000 AVIDYNE
FOR RT-161A USE P/N 100-00082-001
TRANSMITTER RT-131A RT-161A 700-00007-004
P1001 P1101 EX500
(ART)
J1004 P2 P1 FLIGHTMAX MFD
GND E d B B 28,34 GND
RT ON/OFF G D D D 8 RT ON/OFF
TRIGGER N A K K 11 TRIGGER
TRG SHLD P Z L L 29 GND
TO RT-131
GAIN HI R H(N/C) M M 16 GAIN ADJ
TO RT-161
GAIN LO S(N/C) T N N
VID INTG U N/C R R RT-131 ONLY 25 VID_INTG
DATA2 V B S S 13 DATA2
DATA1 W C T T 12 DATA1
DATA SHLD Z F j j 30,31 GND
TEST Y E V V 7 TEST
+20 VDC H L E E 19 +20 VDC
-20 VDC M J J J 21 -20 VDC
ANTENNA
J1003
RT-131 ONLY
BORE SIGHT F N/C W W 1 BORE SIGHT
AZ DRV G R X X 9 AZ DRV
AZ DRV90 H P Y Y 10 AZ DRV90
TILT ADJ L K b b 14 TILT ADJ
+20 VDC B N/C
-20 VDC C N/C
GND Z N/C
NOTE 1
POWER
P/O P1001
28 VDC IN A e 28VDC
28 VDC IN B S
GND C h AVIONICS POWER
GND D f GND

NOTES:
1. P1 AND P2 SHIELDS TERMINATED TO CONNECTOR BACKSHELL AVIDYNE CORPORATION
(CHASSIS GROUND).

EX500 INSTALLATION WIRING DIAGRAM

BENDIX/KING RADAR RDR-130/150/160
WITH ADAPTER CABLE

Page 65 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix N EX500 Wiring: RDR-1100/1200 RADAR Direct Connect

RADAR ANTENNA BENDIX/KING AVIDYNE

RECEIVER RDR-1100/1200 700-00007-002
TRANSMITTER RT-1201A/131A EX500
P1
(ART) P1001 FLIGHTMAX MFD
RT FAULT T 2 RT FAULT
GND E 27,34 GND
RT ON/OFF G 8 RT ON/OFF
TRIGGER N 11 TRIGGER
TRG SHLD P
GAIN HI R 15 GAIN HI
GAIN LO S 16 GAIN LO
VID INT U 25 VID INT
DATA2 V 13 DATA2
DATA1 W 12 DATA1
DATA SHLD Z
TEST Y 7 TEST
+20 VDC H 19 +20 VDC
-20 VDC M 21 -20 VDC
ANTENNA
J1003
BORE SIGHT F 1 BORE SIGHT
AZ DRV G 9 AZ DRV
AZ DRV90 H 10 AZ DRV90
TILT ADJ L 14 TILT ADJ
+20 VDC B
-20 VDC C
GND Z
STAB DISABL A 6 STAB DISABL
TILT HI J 20 TILT HI
TILT LO K 22 TILT LO
FOR RT-131A ONLY
ROLL HI X 32 ROLL HI
ROLL LO Y 33 ROLL LO

NOTE 1
POWER
P/O P1001
28 VDC IN A 28VDC
28 VDC IN B
GND C AVIONICS POWER
GND D GND

NOTES:
1. TERMINATE SHIELD TO P1 CONNECTOR BACKSHELL (CHASSIS GROUND). AVIDYNE CORPORATION

EX500 INSTALLATION WIRING DIAGRAM

BENDIX/KING RADAR RDR-1100/1200

Page 66 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix O EX500 Wiring: RDR-1100/1200 RADAR w/ Adaptor Cable

AVIDYNE
100-00082-003

BENDIX/KING AVIDYNE
RADAR ANTENNA
RDR-1100/1200 700-00007-002
RECEIVER
RT-1201A/131A EX500
TRANSMITTER
P1001 J1004 P2 P1 FLIGHTMAX MFD
(ART)
RT FAULT T P P 2 RT FAULT
GND E B B 27,34 GND
RT ON/OFF G D D 8 RT ON/OFF
TRIGGER N K K 11 TRIGGER
TRG SHLD P L L
GAIN HI R M M 15 GAIN HI
GAIN LO S N N 16 GAIN LO
VID INT U R R 25 VID INT
DATA2 V S S 13 DATA2
DATA1 W T T 12 DATA1
DATA SHLD Z j j
TEST Y V V 7 TEST
+20 VDC H E E 19 +20 VDC
-20 VDC M J J 21 -20 VDC
ANTENNA
J1003
BORE SIGHT F W W 1 BORE SIGHT
AZ DRV G X X 9 AZ DRV
AZ DRV90 H Y Y 10 AZ DRV90
TILT ADJ L b b 14 TILT ADJ
+20 VDC B
-20 VDC C
GND Z
STAB DISABL A C C 6 STAB DISABL
TILT HI J Z Z 20 TILT HI
TILT LO K a a 22 TILT LO
ROLL HI X e e 32 ROLL HI
ROLL LO Y g g 33 ROLL LO

NOTE 1
POWER
P/O P1001
28 VDC IN A 28VDC
28 VDC IN B
GND C AVIONICS POWER
GND D GND

NOTES:
1. P1 AND P2 SHIELDS TERMINATED TO CONNECTOR BACKSHELL AVIDYNE CORPORATION
(CHASSIS GROUND).
EX500 INSTALLATION WIRING DIAGRAM
BENDIX/KING RADAR RDR-1100/1200
WITH ADAPTER CABLE

Page 67 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix P EX500 Wiring: RDR-1300 RADAR Direct Connect

AVIDYNE
RADAR ANTENNA BENDIX/KING 700-00007-003
RECEIVER RDR-1300 EX500
TRANSMITTER RT-1301A/B FLIGHTMAX MFD
P1
(ART) P1001
RT FAULT T 2 RT FAULT
GND E 27,34 GND
RT ON/OFF G 8 RT ON/OFF
TRIGGER N 11 TRIGGER
TRG SHLD P
GAIN HI R 15 GAIN HI
GAIN LO S 16 GAIN LO
M2 X 26 M2
M3 U 25 M3
DATA2 V 13 DATA2
DATA1 W 12 DATA1
DATA SHLD Z
TEST Y 7 TEST
+20 VDC H 19 +20 VDC
-20 VDC M 21 -20 VDC
ANTENNA
J1003
BORE SIGHT F 1 BORE SIGHT
AZ DRV G 9 AZ DRV
AZ DRV90 H 10 AZ DRV90
TILT ADJ L 14 TILT ADJ
+20 VDC B
-20 VDC C
GND Z
STAB DISABL A 6 STAB DISABL
TILT HI J 20 TILT HI
TILT LO K 22 TILT LO
ROLL HI X 32 ROLL HI
ROLL LO Y 33 ROLL LO

NOTE 1
POWER
P/O P1001
28 VDC IN A 28VDC
28 VDC IN B
GND C AVIONICS POWER
GND D GND

NOTES:
1. TERMINATE SHIELD TO P1 CONNECTOR BACKSHELL (CHASSIS GROUND). AVIDYNE CORPORATION

EX500 INSTALLATION WIRING DIAGRAM

BENDIX/KING RADAR RDR-1300

Page 68 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix Q EX500 Wiring: RDR-1300 RADAR w/ Adaptor Cable

AVIDYNE
100-00082-002

BENDIX/KING AVIDYNE
RADAR ANTENNA
RDR-1300 700-00007-003
RECIEVER
RT-1301A/B EX500
TRANSMITTER
P1001 J1004 P2 P1 FLIGHTMAX MFD
(ART)
RT FAULT T P P 2 RT FAULT
GND E B B 27,34 GND
RT ON/OFF G D D 8 RT ON/OFF
TRIGGER N K K 11 TRIGGER
TRG SHLD P L L
GAIN HI R M M 15 GAIN HI
GAIN LO S N N 16 GAIN LO
M2 X U U 26 M2
M3 U R R 25 M3
DATA2 V S S 13 DATA2
DATA1 W T T 12 DATA1
DATA SHLD Z j j
TEST Y V V 7 M1
+20 VDC H E E 19 +20 VDC
-20 VDC M J J 21 -20 VDC
ANTENA
J1003
BORESIGHT F W W 1 BORESIGHT
AZ DRV G X X 9 AZ DRV
AZ DRV90 H Y Y 10 AZ DRV90
TILT ADJ L b b 14 TILT ADJ
+20 VDC B
-20 VDC C
GND Z
STAB DISABL A C C 6 STAB DISABL
TILT HI J Z Z 20 TILT HI
TILT LO K a a 22 TILT LO
ROLL HI X e e 32 ROLL HI
ROLL LO Y g g 33 ROLL LO

NOTE 1
POWER
P/O P1001
28 VDC IN A 28VDC
28 VDC IN B
GND C AVIONICS POWER
GND D GND

NOTES:
1. P1 AND P2 SHIELDS TERMINATED TO CONNECTOR BACKSHELL AVIDYNE CORPORATION
(CHASSIS GROUND).
EX500 INSTALLATION WIRING DIAGRAM
BENDIX/KING RADAR RDR-1300
WITH ADAPTER CABLE

Page 69 of 70
 Installation Manual
P/N 600-00079-000 Rev 06

Appendix R EX500 Wiring: WXR250/270/300 RADAR w/ Adaptor Cable

RADAR ANTENNA COLLINS AVIDYNE AVIDYNE

RECEIVER WXT250A/B
TRANSMITTER 100-00081-000 700-00007-006
P1
(ART) EX500
DB-50S DB-50P FLIGHTMAX MFD
P1
RT FAULT d 5 5 2 RT FAULT
L/S t 46 46 3 L/S
TEST c 14 14 4 TEST
STC X 13 13 5 STC
RT STBY g 39 39 7 RT STBY
RT ON R 38 38 8 RT ON
MOD TMG G 17 17 11 MOD TMG
VIDEO 1 A 11 11 12 VIDEO 1
VIDEO 2 C 6 6 13 VIDEO 2
-6 db GAIN Y 1 1 23 GAIN 6
-12 db GAIN Z 2 2 24 GAIN 12
-18 db GAIN a 3 3 25 GAIN 18
-24 db GAIN b 4 4 26 GAIN 24
PRF CLOCK J 10 10 28 PRF CLOCK
PAC ALERT N 15 15 29 PAC ALERT
VIDEO 4 K 22 22 30 VIDEO 4
VIDEO 3 E 7 7 31 VIDEO 3
+15 VDC s 12 12 19 +15 VDC
-15 VDC k 16 16 21 -15 VDC
IND COMMON q 24 24 27 GND
IND COMMON r 31 31 34 GND
CTL COMMON H 18 18
COMMON F
COMMON D
COMMON B

-12 VDC S 27 27
ANTENNA 28 28
ANT-310/
30 30
32 32
312/318
P1
-12 VDC 15
STAB DISABL 6 40 40 6 STAB DISABL
A 9 45 45 9 AZ DRV A
B 1 48 48 10 AZ DRV B
TILT CTRL 12 47 47 14 TILT ADJ
TILT HI 11 42 42 20 TILT HI
TILT LO 4 44 44 22 TILT LO

NOTE 1
P/O P1
28 VDC IN i 28VDC
28 VDC IN j
GND h AVIONICS POWER
GND P GND

NOTES:
1. P1 AND P2 SHIELDS TERMINATED TO CONNECTOR BACKSHELL AVIDYNE CORPORATION
(CHASSIS GROUND).
2. IF JUNCTION BOSS IS USED ISOLATE EACH EX500 INSTALLATION WIRING DIAGRAM
SHIELD INDEPENDENTLY.
COLLINS RADAR WXR250/270/300
WITH ADAPTER CABLE

Page 70 of 70