700-00004-0XX-() Multi-function Display

Instructions for Continued Airworthiness

Part 23, Class I & II Installations

A VIDYNE
CORPORATION
55 Old Bedford Road
Lincoln, MA 01773

Document Number AVMFD-167 Control Category N/A

Revision Description ECO Date
00 Initial Release 03-244 09/24/03
01 FAA AEG comments (Section 6) 03-273 11/17/03
Added STC # & Engine Setup section from
02 ECO-04-010 01/23/04
the install manual
Added instructions for hour meter function
03 ECO-04-117 07/07/04
and PA-28 specific information
Draft 04-A Added part numbers for PA-46 Keirnan 2/28/05

Confidential property of Avidyne Corporation

Not to be disclosed without permission
700-00004-0XX-() Multi-function Display Instructions for Continued Airworthiness
Part 23, Class I & II Installations

Table of Contents
1. Introduction ........................................................................................... 6
1.1 Aircraft Description ......................................................................................................... 6

1.2 Scope.............................................................................................................................. 6

1.3 Applicability ..................................................................................................................... 6

1.4 Definitions and Abbreviations ......................................................................................... 6

1.5 Precautions ..................................................................................................................... 6

1.6 Units of Measure............................................................................................................. 6

1.7 Referenced Publications................................................................................................. 6

1.8 Distribution ...................................................................................................................... 6

2. Description............................................................................................. 7

3. Control, Operation Information ............................................................ 9

4. Servicing information.......................................................................... 10

5. Maintenance Instructions ................................................................... 11

5.1 Cleaning Cover Screen................................................................................................. 11

5.2 Recommended Periodic Scheduled Servicing Tasks................................................... 11

6. Troubleshooting Information ............................................................. 12

7. Removal and Replacement Information ............................................ 14

7.1 Removal........................................................................................................................14

7.1.1 Recorded Engine Time Function ..................................................................... 14

7.2 Installation..................................................................................................................... 15

7.3 System Setup and Checkout ........................................................................................ 15

7.3.1 Maintenance Mode Access ............................................................................. 15

7.3.2 GPS Interface, Setup and Checkout ............................................................... 16

7.3.2.1 GAMA 429 Graphics Setup (EX5000 only)............................................................. 17
7.3.2.2 Dual GPS setup with GAMA 429 (EX5000 only).................................................... 18

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Part 23, Class I & II Installations

7.3.2.3 RS-232 Setup ............................................................................................................ 18

7.3.2.4 FMS/GPS Communications Check (Messages)........................................................ 19
7.3.3 FMS/GPS Manufacturer Matrix ....................................................................... 20

Lightning Sensor Interface and Setup...................................................................... 21

7.3.4................................................................................................................................ 21
7.3.4.1 Lightning Sensor Checkout....................................................................................... 23
7.3.4.2 Lightning Sensor Strike Test .................................................................................... 24
7.3.4.3 Lightning Sensor Noise Mode .................................................................................. 24
7.3.5 Traffic Sensor .................................................................................................. 24
7.3.5.1 TAS (SkyWatch & Bendix/King) Setup ................................................................... 25
7.3.5.2 TAS (SkyWatch) Checkout ...................................................................................... 25
7.3.5.3 TAS (Bendix/King) Checkout .................................................................................. 26
7.3.5.4 TCAD (Optional) Setup............................................................................................ 26
7.3.5.5 TCAD Dual Display Setup ....................................................................................... 27
7.3.5.6 TCAD Checkout ....................................................................................................... 27
7.3.5.7 TIS (Optional) Setup................................................................................................. 28
7.3.5.8 TIS Checkout ............................................................................................................ 29
7.3.5.9 Traffic Communications Check (Messages)............................................................. 29
7.3.6 TAWS (Optional).............................................................................................. 30
7.3.6.1 TAWS Setup ............................................................................................................. 30
7.3.6.2 TAWS Checkout....................................................................................................... 30
7.3.6.3 TAWS Communications Check (Messages)............................................................. 31
7.3.7 Radar Sensor (700-00030-005 EX5000 only) ................................................. 32
7.3.7.1 RADAR System Calibration..................................................................................... 33
7.3.7.2 Calibration with AlliedSignal (Bendix/King) 2000 Radar Sensor ............................ 33
7.3.7.3 Roll Trim Adjustment ............................................................................................... 38
7.3.7.4 RADAR Checkout .................................................................................................... 38
7.3.7.5 RADAR Sensor Communications Troubleshooting ................................................. 39
7.3.8 Map Setup ....................................................................................................... 40

7.3.9 Engine Sensor Setup and Checkout (When EMax equipped) ........................ 40

7.3.10 Engine Sensor ................................................................................................. 40

7.3.10.1 Engine Sensor Setup ................................................................................................. 40
Fuel Quantity Calibration (Optional)........................................................................................... 42
7.3.10.2 Engine Sensor Checkout ........................................................................................... 43
7.3.11 Auxiliary Data (Optional).................................................................................. 43
7.3.11.1 Auxiliary Data Setup................................................................................................. 43
7.3.11.2 Auxiliary Data Checkout .......................................................................................... 44
7.3.12 Datalink (Optional) ........................................................................................... 44
7.3.12.1 Narrowcast Datalink Setup ....................................................................................... 44
7.3.12.2 Broadcast Datalink Setup.......................................................................................... 45
7.3.12.3 Narrowcast Datalink Checkout ................................................................................. 45
7.3.12.4 Narrowcast Datalink Satellite Reception Confirmation............................................ 45
7.3.12.5 Broadcast Datalink Checkout ................................................................................... 46
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7.3.12.6 Broadcast Datalink Satellite Reception Confirmation .............................................. 47

7.3.12.7 Radar Setup............................................................................................................... 48
8. Diagrams .............................................................................................. 49

9. Special Inspection Requirements ...................................................... 49

10. Application of Protective Treatments .............................................. 49

11. Data ..................................................................................................... 49

12. List of Special Tools .......................................................................... 49

13. For Commuter Category Aircraft ...................................................... 49

14. Recommended Overhaul Periods..................................................... 49

15. Airworthiness Limitation Section ..................................................... 50

16. Revision .............................................................................................. 51

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Part 23, Class I & II Installations

List of Figures
Figure 1. Avidyne 700-00004-0XX MFD .................................................................................................. 7
Figure 2 Avidyne MFD installation........................................................................................................... 8
Figure 3. MFD Installation....................................................................................................................... 14
Figure 4. MFD & Connector ................................................................................................................... 15
Figure 5. Maintenance Mode Page ......................................................................................................... 16
Figure 6. Engine Sensor Setup Page ...................................................... Error! Bookmark not defined.
Figure 7. Aircraft Setup Page ................................................................. Error! Bookmark not defined.
Figure 8. Datalink Info Table.................................................................. Error! Bookmark not defined.

List of Tables
Table 1. GPS/FMS Messages................................................................................................................... 12
Table 2. Traffic Messages ......................................................................................................................... 12
Table 3. Lightning Messages ................................................................................................................... 13
Table 4. Datalink Messages ..................................................................................................................... 13
Table 5. Recorded Engine Time Function Applicability...................................................................... 14

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Part 23, Class I & II Installations

1. Introduction
1.1 Aircraft Description
Make: Various
Model: Various
Make and models as listed in Avidyne Document, AVMFD-163, 700-00004-0XX MFD Approved Model
List STC #SA00191BO.
1.2 Scope
This document identifies the Instructions for Continued Airworthiness for the above referenced
aircraft modified to include installation of an Avidyne 700-00004-0XX Multi-function Display.
This ICA satisfies the requirements of 14 CFR 23.1529.
1.3 Applicability
Applies to aircraft altered by the installation of an Avidyne 700-00004-0XX Multi-function Display.

1.4 Definitions and Abbreviations

ICA – Instructions for Continued Airworthiness
STC – Supplemental Type Certificate
MFD – Multi-function Display
AEG – Aircraft Evaluation Group
CMOS – Complementary Metal Oxide Semiconductor
1.5 Precautions
This section is not applicable.

1.6 Units of Measure

This section is not applicable.

1.7 Referenced Publications

Document Title
Number
600-00105-000 FlightMax EX5000 Multi-function Display Pilot’s Guide
600-00073-000 FlightMax Installation Manual 700-00004-XXX-() Model EX3000
Series MFD EX5000 Series MFD

1.8 Distribution
These Instructions for Continued Airworthiness are to be furnished to the owner of an aircraft
modified in accordance with this STC, and is to become part of the permanent aircraft record.
A current revision of this ICA shall be available on the Avidyne website at www.avidyne.com
(Technical Publications).

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2. Description
The Avidyne 700-00004-0XX MFD is a panel mounted 10.4-inch diagonal situational awareness
display as shown in Figure 1.
The MFD provides the following display capabilities:
1. Moving Map
2. Traffic
3. Lightning
4. FMS-supplied Flight Plan
5. Obstacles
6. Datalink Weather (optional)
7. Engine Instruments (optional)
8. Outside Air Temperature (optional)
9. Recorded Engine Time

Dzus
FASTENER (4)
BRIGHTNESS
CONTROL

LINE DATALOADER
SELECT PORT
KEYS

L1 R1

L2 R2

L3 R3

L4 R4

L5 R5

LEFT RIGHT
KNOB KNOB

Figure 1. Avidyne 700-00004-0XX MFD

A block diagram of the Avidyne MFD interfaced in a fully equipped aircraft is presented in Figure 2.
Any particular installation may or may not incorporate certain external sensors.

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Engine Measurements (from probes)

MFD DL antenna
Engine
Data
Acquisition
Flight Data Source Unit
(PFD) (DAU)
RS232

VHF DL
RS-422 RS-422 Mag/OAT

static static dimmer circuit bezel dim

429 out 429 in

GNS430 #1 +28VDC power power

429 in
GPS Arinc Out 429 in
RS232/429 in
GNS430 #2
RS232
(optional) GPS Arinc Out

Traffic Sensor Stormscope

(optional) RS232/429 RS232
(optional)

Figure 2 Avidyne MFD installation

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3. Control, Operation Information

The MFD operation is controlled through 10 bezel keys, two rotary knobs, and a rocker switch. The
left knob selects the desired page, which is identified on the LCD above the knob. The particular page
that is currently selected defines the right knob’s function. The knob is appropriately labeled on the
LCD above the knob.
The rocker switch located in the top right corner of the bezel controls the display brightness, which is
adjusted manually by pushing the top portion of the switch to increase intensity and pushing the
bottom portion of the switch to decrease intensity. A pop-up window that presents the percentage of
full intensity, along with a bar graph representation, indicates the intensity setting of the display.
The functionality of the 10 bezel keys is defined by the page that is currently displayed, and are
labeled accordingly on the LCD adjacent to the key.
Refer to the FlightMax EX5000 Pilot’s Guide for more detail on MFD operation.

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4. Servicing information
This section is not applicable.

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5. Maintenance Instructions
Other than the periodic servicing task discussed below, maintenance of the Avidyne 700-00004-0XX
MFD is based on condition only; no other periodic maintenance is required.

5.1 Cleaning Cover Screen

If the PFD cover screen should become dirty due to finger prints, dust etc the following materials and
methods can be used to safely clean the screen.
• A soft lint free cloth
• Cleaning solution such as Optimax brand cleaner or water if Optimax is not available
• ALWAYS apply cleaning solution directly to the cloth and NEVER directly to the screen
• NEVER use products that contain ammonia, alcohol, acetone, ethyl alcohol, ethyl acid,
methyl chloride etc.

CAUTION: Using products with ammonia or other harmful ingredients or materials could void the
warranty.

NOTE: The cover screen is not glass, the surface is made of a soft film that is vulnerable to scratches,
damage by a sharp articles or improper cleaners. Use care when cleaning.

5.2 Recommended Periodic Scheduled Servicing Tasks

The Avidyne 700-00004-0XX MFD contains a 3-volt lithium battery that maintains CMOS memory on
an internal processor board and should be replaced after 10 years of service, or when CMOS memory
fails to retain configuration data, whichever occurs first. The Avidyne MFD must be returned to an
authorized FAA repair station to perform this maintenance function. Failure of the CMOS memory is
indicated by the message “WARNING: CMOS battery failure. Check database expiration date. Press
any bezel key to continue.” on a blue background prior to system boot up. After system boot up, the
MFD will function normally, but will not have retained the system date and time. If the system is
interfaced to the GNS 430 through ARINC 429, it will acquire current date and time from the GNS
430 when valid satellite data is received.

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6. Troubleshooting Information
The Avidyne MFD incorporates a message bar located at the bottom of the display. Messages are
generated by the system and displayed on the message bar and are helpful in troubleshooting system
problems. Table 1 and Table 2 present the messages that are generated by each application.
Note: For troubleshooting instructions recommending wiring checks, refer to the
Avidyne document, 600-00073-000, FlightMax Installation Manual 700-00004-
XXX-() Model EX3000 Series MFD EX5000 Series MFD for wiring diagram
information.

Table 1. GPS/FMS Messages

Message Meaning
Nav Source is Not Communicating No RS-232 or ARINC 429 GPS data is being received. Check wiring
and Comm port setting.
Nav Source Data is Not Valid Data is being received from the external GPS. However, insufficient
information is available to determine position. Aircraft could be in the
hangar or the GPS may not have determined its “fix” or location.
Nav Source Data is Valid The MFD is receiving valid position data from the GPS.
Nav Source Data Format Error Data is being received, however the MFD does not recognize the
data as the format selected. May indicate a baud rate or receiver
type error.
Nav Source: No Port selected The COMM port setting in the GPS setup dialog is set to NONE. To
correct this, choose the port to which the GPS is connected, typically
COM2.
Nav Source: Reconnecting This message is displayed when data between the MFD and the
GPS is being synchronized.
Nav Source: Can’t Open Port Another device is configured for the same port. Check the Setup
page for all devices. Typically the GPS is configured for RS-232 Port
2 or ARINC 429 port 1. A second GPS can only be configured for
ARINC port 2.
Heading Data is Not Valid Heading data is no longer available from the GPS. Will only appear if
the GPS is being used as the heading source.
Heading Data is Valid Heading data has been restored.

Table 2. Traffic Messages

Message Meaning
Traffic Sensor is (TAS) Not Communicating Traffic data is not being received.
Traffic Sensor is in Stand-By (TAS) The Skywatch sensor has been placed in Standby mode.
Traffic Sensor is in Self-Test (TAS) The Skywatch sensor has been placed in Self-Test mode.
Traffic Sensor is Operating Normally (TAS) Verification that Traffic data is valid.

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TCAD Altitude Unavailable (TCAD) Occurs when altitude data has been lost from the TCAD sensor.

Table 3. Lightning Messages

Message Meaning
Lightning Sensor is Operating Normally Verification that strike data to the MFD is valid.
Lightning Sensor in Demo Mode Demo mode has been selected as the operating mode from the
Lightning Setup Page.
Lightning Sensor is in Noise-Monitor Mode Noise-Monitor mode has been selected as the operating mode from
the Lightning Setup Page.
Lightning Sensor in Test Mode Test mode has been selected as the operating mode from the
Lightning Setup Page.
Lightning Sensor ERROR The sensor system has reported an error that may mean current
data is incomplete or erroneous. The error may clear.
Lightning Sensor has FAILED The sensor system has reported an error that may mean current
data is incomplete or erroneous. The error will not clear until power is
removed from and reapplied to the sensor system.
Lightning Sensor is Not Communicating Communication of strike data from the Lightning sensor to the MFD
has been lost.
Lightning Ahead The Lightning Ahead option has been checked on the Lightning
Setup page. Displayed when a Lightning Ahead condition exists.
Lightning Heading Source Failed Heading data is no longer available from the WX-500. Strike data
may still be valid. Will only appear if the WX-500 is being used as the
heading source.
Lightning Heading Source OK Heading data has been restored.
Stuck mic-PLEASE CHECK Check the comm transmitters for indication of a stuck mike.
Lightning Antenna Location Changed There may be an inconsistency between the antenna location jumper
setting and the software configuration. This message should only
appear during installation.

Table 4. Datalink Messages

Message Meaning/Action
Datalink Sensor Data Is Invalid The EX5000 has received unreadable satellite data.
Datalink Sensor Configuration Error The EX5000 is improperly configured for datalink.
o Requires factory servicing.
Datalink Sensor Is NOT Communicating The EX5000 is experiencing a communication failure with the
internal Satellite transceiver.
o Requires factory servicing.
NEW Messages???

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7. Removal and Replacement Information

7.1 Removal
Remove the Avidyne MFD from the instrument panel by turning four corner-mounted flat head Dzus
fasteners counter-clockwise and pulling the unit away from instrument panel. Remove the
signal/power connector located on the back of MFD by turning two jackscrews counter-clockwise
(see Figure 3). Disconnect the coax datalink antenna cable.

7.1.1 Recorded Engine Time Function

Specific MFDs manufactured by Avidyne are capable of recording engine run time and may be the
sole means of providing that function in a particular aircraft. The recorded engine time is provided
on the Maintenance page of the MFD. This value cannot be altered.
When removing and installing MFDs that provide the recorded engine time function, care must be
taken to note engine time prior to removal of the MFD. If a reconditioned, or new MFD is to be
reinstalled (in place of an originally installed MFD), the recorded engine time of the replacement
MFD must be reconciled in the aircraft records (airframe/engine logbooks).
Table 5 lists MFD software part numbers that are capable of providing recorded engine time.

Table 5. Recorded Engine Time Function Applicability

MFD Aircraft Type

S/W 530-00137-000, REV 01 PA-28R-201, PA-28-181, PA-28-161, PA-32R-301, PA-
32R-301T, PA-32-301, PA-32-301T

Figure 3. MFD Installation

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Part 23, Class I & II Installations

Figure 4. MFD & Connector

7.2 Installation
To install the MFD, secure the connector onto the MFD and tighten the two jackscrews. Rest the MFD
in the panel cutout and assure that the MFD cable is routed away from any moving parts behind the
instrument panel. Position the MFD. Secure the MFD to the instrument panel by turning four corner-
mounted flat head Dzus fasteners clockwise.
Upon reinstallation, a functional check should be performed in accordance with the System Setup
and Checkout procedures detailed in Section 7.3.

7.3 System Setup and Checkout

Any time the Avidyne MFD is removed and sent to the factory for service, or is replaced with another
unit, these system setup procedures should be performed to assure that the unit is properly
configured for the installation. This section should also be referenced if it is suspected that the unit
may be misconfigured.
Turn on the MFD by applying power to the aircraft battery and avionics bus master switches. The
green bezel key backlighting should illuminate to full intensity when the Instrument Lights dimmer
control is turned fully counterclockwise. As the dimmer control is turned clockwise, the bezel key
lighting should dim fully, and then increase in intensity.

7.3.1 Maintenance Mode Access

Upon initial system power-up, the MFD will execute a start-up sequence. During this time, the screen
will initially display the FlightMax logo, followed by a blank screen until a blue screen with the text
“Initializing-Please Wait…” is displayed. The startup sequence is finished when the text “Press any

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Part 23, Class I & II Installations

bezel key to Continue…” is displayed. The initialization screen displays the loaded software version,
along with NavData and Obstacle database expiration dates.
Apply power to all sensors that interface with the MFD such as GPS navigator, lightning sensor,
engine sensor, and traffic sensor. The MFD configuration is accomplished in the setup pages that are
accessed through the Maintenance Mode, which is accessed as follows:
1. Turn on the MFD by applying power to the aircraft
2. The system will begin its normal start up sequence
3. At the prompt, “Press any bezel key to continue”, press a line select key
4. Rotate the left knob clockwise until the Setup Page is displayed
5. Simultaneously press and hold the top left (L1), and 3rd down from the top left (L3), Line
Select keys for at least 5 seconds (See Figure 5).
1. A blue background “Maintenance Page” will appear Figure 5.

Figure 5. Maintenance Mode Page

NOTE: After changes are made in each setup page press the Save key to save and exit each setup
page. Press Cancel if you decide not to keep the changes. After all changes are made in Maintenance
Mode, the system must be restarted. Press Restart System. Changes will not take affect until the
MFD has been restarted. If no changes were made the Back to Map key exits Maintenance Mode.

7.3.2 GPS Interface, Setup and Checkout

The MFD is capable of interfacing with several FMS/GPS’s. There is a FMS/GPS Matrix
on page 20 that lists most of the FMS/GPS’s that interface with the MFD. The
matrix includes information about data formats available and GPS configurations.

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NOTE: Installers should use the matrix as a general guideline only. GPS
manufacturers are constantly improving and upgrading their products.
Installers should always refer to the Installation manuals that come with
their FMS/GPS to confirm configuration and setup parameters.

There are two possible data formats that the MFD uses to interface with the GPS:

• GAMA 429
• RS-232

Some GPS’s can only output in one format, while others are capable of outputs in either format.
EX3000 MFD’s support RS-232 interfaces only. EX5000 MFD’s support GAMA 429 and RS-232.
However, GAMA 429 Graphics is the only data format from the GPS capable of providing heading
information if the GPS is being used as the heading source (refer to Map Setup and Checkout section
on page Error! Bookmark not defined. for a complete explanation on setting up the various heading
configurations within the MFD).

7.3.2.1 GAMA 429 Graphics Setup (EX5000 only)

NOTE: Using 429 will allow for the display of curved segments and approach data,
if that data is available.

If your GPS is capable of GAMA 429 Graphics output, wire it according to APPENDIX K – Wiring
Diagram 2, ARINC 429 Interface, and configure the following:
Receiver: Select GAMA 429 Graphics Format.
Port: There are 4 ARINC ports, the FMS/GPS is normally connected to ARINC1. Selecting None
indicates that a GPS is not connected to the MFD and the software will not look for one.
Speed: There are two speeds available, High and Low.
When the Receiver, Port, and Speed are set to the desired values, press the Save button. Press Cancel
if you decide not to keep the changes you made. Changes will not take affect until the MFD has been
restarted.

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7.3.2.2 Dual GPS setup with GAMA 429 (EX5000 only)

The EX5000 has the capability of receiving information from two GAMA 429 Graphics capable
GPS units. The GPS should be connected according to the wiring diagram in the appropriate
appendix.

7.3.2.3 RS-232 Setup

NOTE: Using an RS-232 interface does not provide for heading data from the FMS/GPS.

Wire the MFD according to APPENDIX J – Wiring Diagram, Power, Dimming Bus, DL antenna, and
RS-232 Interfaces, and configure the following:

Figure 6 GPS Setup, GAMA 429

Figure 7 GPS Setup, RS-232

Receiver: Use the FMS/GPS Manufacturer Matrix section on page 20 or refer to your FMS/GPS
Installation manual to determine the RS-232 output format of your receiver. Choose from the
following RS-232 formats: NMEA 0183, King/Aviation Format, or Northstar Format.
Port: There are 4 RS232 ports; the FMS/GPS is normally connected to RS232 1.
Baud: Choose the proper baud rate. Refer to the FMS/GPS Installation manual or see “FMS/GPS
Manufacturer Matrix” on page 20 for the maximum speed. The following speeds are available: 1200,
2400, 4800, 9600, 19200, or 38400.
When the Receiver, Port, and Baud rate are all set to the desired values, press the Save key to save
and complete the setup procedure. Press Cancel if you decide not to keep the changes you made.
Changes will not take affect until the MFD has been restarted.

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7.3.2.4 FMS/GPS Communications Check (Messages)

After the MFD has been restarted, any of the following messages may appear in the main viewing
screen or the message bar and Setup page.

Message Meaning
No RS-232 or ARINC 429 GPS data is being received. Check
Nav Source: Is Not Communicating
wiring and COM port setting.
Data is being received from the external GPS. However,
insufficient information is available to determine position.
Nav Source: Data is Not Valid
Aircraft could be in the hanger or the GPS may not have
determined its “fix” or location.

The MFD is receiving valid position data from the

Nav Source: Data is Valid
FMS/GPS.
Data is being received, however the MFD does not
Nav Source: Data Format Error recognize the data as the format selected. May indicate a
baud rate or receiver type error.
The RS232 port setting in the GPS setup dialog is set to
Nav Source: No Port selected NONE. To correct this, choose the port to which the GPS is
connected, typically RS232 1.
This message is displayed when data between the MFD
Nav Source: Reconnecting
and the GPS is being synchronized.
Another device is configured for the same port. Check the
Setup page for all devices. Typically the FMS/GPS is
Nav Source: Can't Open Port configured for Port1 (for RS-232) or ARINC1 (for ARINC
429). If a second FMS/GPS is being used it is configured
for Port2 or ARINC2.
Heading data is no longer available from the FMS/GPS.
Heading Data is Not Valid Will only appear if the FMS/GPS is being used as your
heading source.
Heading Data is Valid Heading data has been restored.

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7.3.3 FMS/GPS Manufacturer Matrix

RS-232 ARINC BAUD/DATA HEADING FMS/GPS DME

FMS/GPS RS232
FORMATS 429 RATE OUTPUT CONFIGURATION ARC

Flight
Plan ends
KLN-89B Yes King/Aviation No Serial - 9600 No
at entry
point
Flight
Serial – 9600 ARINC Plan ends
KLN-90B Yes King/Aviation Yes
ARINC - Low only at entry
point
The Northstar
default baud rate is
1200. Better
performance and
NorthStar extended data is
M1, M2, or Yes NorthStar No 1200 or 9600 No achieved by setting
M3 it to 9600 (1200 will
work). Refer to the
NorthStar manual to
change the baud
rate
Sends
Use RS-232 port 2 multiple
Trimble Some Not
Yes King/Aviation 9600 waypoints
2000, 2101 models Available No Parity, 8 bits around
arc
For the 250 DO
NOT use the W/O
150- GAMA mode, use
Garmin No Serial – 9600 ARINC
Yes King/Aviation the EFIS mode. If
150, 250 ARINC - Low only
250-No using the NMEA
format use the 2nd
channel.

Garmin
Yes King/Aviation No 9600 No
155, 165

For RS-232
With RS-
operation, set the
232 the
Garmin to Aviation
arc is
Garmin Serial – 9600 ARINC Output. With
Yes King/Aviation Yes depicted
400 Series ARINC - Low only ARINC 429
as a
operation use
straight
GAMA with
line.
Graphics
For RS-232 With RS-
Garmin Serial – 9600 ARINC operation, set the 232 the
Yes King/Aviation Yes
500 Series ARINC – Low only Garmin to Aviation arc is
Output. With depicted

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RS-232 ARINC BAUD/DATA HEADING FMS/GPS DME
FMS/GPS RS232
FORMATS 429 RATE OUTPUT CONFIGURATION ARC
ARINC 429 as a
operation use straight
GAMA with line.
Graphics

Universal ARINC –
No Yes Yes
UNS-1B High

For GNS-XLS
Configuration
Programming set as
The arc is
Honeywell ARINC – follows: GAMA
No Yes Yes depicted
GNS-XLS High or Low ARINC 329 Bus
as a gap
Data Set= 1. Basic
EFIS DME Arc
Style=1. Arc as Gap

II Morrow
Use the Moving
Apollo Yes King/Aviation No 9600 No
Map format.
GX-50

NOTE: Garmin Installation. Some Garmin units provide two RS-232 formats for GPS
data. One is an “aviation” format. The other is an RS232 “plotting” format. The
“aviation” format provides a “King” format 9600 baud output at a higher
repetition rate and is the preferred RS-232 output. Consult the specific Garmin GPS
installation manual for full details.

NOTE: Northstar Installations. Many Northstar units have a hidden setup screen to
change configuration parameters to make it difficult to change in flight. Carefully
refer to the Northstar installation manual for the specific codes to enter to set this
up correctly.

NOTE: Trimble 2000A Installations. This unit has a hidden setup screen documented in
the installation manual to change configuration parameters to make it difficult to
change in flight. Carefully refer to the Trimble Installation manual for the specific
codes to enter. Trimble units have been observed to sometimes lose configuration
when the aircraft battery is discharged

7.3.4 Lightning Sensor Interface and Setup

The L-3 Communications WX-500 Stormscope lightning sensor interface is optional.
Interconnect details are provided in the MFD installation (Section 1.7 Reference Publications).
The MFD communicates to and from the WX-500 using RS-232 communications. To
configure Lightning, access Maintenance Mode as described in Section 7.3.1 and select
Lightning Setup. Highlight each configuration item and select the appropriate MFD settings as
shown in the following table:
To configure Lightning, access Maintenance Mode and select Lightning Setup (Refer to Figure 8).

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Sensor: Select between the lightning sensor and a simulation program. The normal selection is
WX-500. The simulation setting is used in conjunction with the demo mode to simulate lightning
operations on the ground.
Operating Mode: The normal operating mode is weather. Demo is used in conjunction with
demo mode to simulate lightning operations. Noise Monitor mode is used during noise mapping
tests. Refer to the WX-500 installation manual for testing procedures.
Port: Set the MFD RS232 port that is connected to the WX500 to match the aircraft wiring.
Stab Type: Select the source of stabilization for use by the WX-500. Stabilization aids in correctly
positioning strikes when the aircraft is turning. The choices are:
• Synchro: a remote compass system that generates and transmits synchro signals
received by the WX500. This heading data can also be used by the MFD to orient the
map. See the Map Heading Setup section.
• Stepper: a remote compass system that generates and transmits stepper signals
received by the WX500. This heading data can also be used by the MFD to orient the
map. See the Map Heading Setup section.
• Use Map Heading/Track: The WX500 receives heading or track data from the MFD
via RS232. Heading will be sent from the MFD only if GPS/FMS is the heading
source via ARINC 429.
The best method of stabilization is a heading source (synchro or stepper input to the WX-500 or
Map Heading). The next best method is Track. The wiring and WX-500 jumpers must agree with
the setup on the MFD.
Enable Lightning Ahead Warning?: Enables display of the Lightning Ahead warning message in
the message bar when checked and disables it when not checked.
Antenna on Top?: Indicates that the sensor antenna is mounted on top of your aircraft when
checked and that it is mounted on the bottom of your aircraft when not checked.

NOTE: The antenna position setting and stabilization source agree with the
WX-500 jumper setting and the physical mounting location of the
antenna.

WX500 Diags: Allows access to the WX-500 diagnostic modes. Follow the guidance in the
WX-500 installation manual to verify WX-500 software versions, wiring configurations,
antenna environment, and fault log. (not available on all software releases)
Self Test: Runs the WX-500 self test and reports Pass or Fail. Follow the guidance in the WX-
500 installation manual to understand the testing and the interpretation of the results. (not
available on all software releases)

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Figure 8 Lightning Setup Page

7.3.4.1 Lightning Sensor Checkout

After the MFD has been restarted, any of the following messages may appear in the main
viewing screen or the message bar and Setup page.

Message Meaning

Verification that strike data to the MFD is

Lightning Sensor is Operating Normally
valid.

Demo mode has been selected as the

Lightning Sensor in Demo Mode operating mode from the Lightning Setup
Page.
Noise-Monitor mode has been selected as
Lightning Sensor is in Noise-Monitor
the operating mode from the Lightning
Mode
Setup Page.
Test mode has been selected as the
Lightning Sensor in Test Mode operating mode from the Lightning Setup
Page.
The sensor system has reported an error
Lightning Sensor ERROR that may mean current data is incomplete
or erroneous. The error may clear.
The sensor system has reported an error
that may mean current data is incomplete
Lightning Sensor has FAILED or erroneous. The error will not clear until
power is removed from and reapplied to
the sensor system.

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Message Meaning
Communication between the Lightning
sensor to the MFD has been lost. The
Lightning Sensor is Not Communicating wiring may be incorrect, the MFD setup
may not match the wiring or the sensor
may have an error.
The Lightning Ahead option has been
checked on the Lightning Setup page.
Lightning Ahead
Displayed when a Lightning Ahead
condition exists.
Heading data is no longer available from
the WX-500. Strike data may still be valid.
Lightning Heading Source Failed
Will only appear if the WX-500 is being
used as your heading source.

Lightning Heading Source OK Heading data has been restored.

Check your COM transmitters for

Stuck mic-PLEASE CHECK
indication of a stuck mike.

There may be an inconsistency between

the antenna location jumper setting and
Lightning Antenna Location Changed
the software configuration. This message
should only appear during installation.

7.3.4.2 Lightning Sensor Strike Test

Select the Setup page and press the Lightning Strike Test button. The MFD will switch to the
Map page and display a single strike at 15 mile range and 45 degrees relative bearing. If not
there may be an inconsistency with the heading source, wiring, or MFD setup.

7.3.4.3 Lightning Sensor Noise Mode

When operating the Lightning sensor in Noise Monitor mode, the Lightning button on the
Map page will display “Noise” as the current Lightning state. Do not press the button in this
state, or it may suppress lightning display unnecessarily. If no lightning strikes are shown at
all during noise testing, do press the button until it says Display Off, then press once more to
return to the proper Noise mode display.

7.3.5 Traffic Sensor

NOTE: Only the listed Traffic sensors are supported. If a non-listed traffic
sensor is connected to the MFD some of the data may display but its accuracy
and traffic sensor control functions may be incorrect or inoperable. Display of
traffic sensor data is not a guaranty of correct traffic sensor installation and
configuration.
Access Maintenance Mode and select Traffic Setup. Follow instructions for TAS, TCAD, or
TIS setup.

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7.3.5.1 TAS (SkyWatch & Bendix/King) Setup

SkyWatch uses an ARINC 429 data connection between the TRC (Transmitter/Receiver
Computer) and the MFD.
Sensor – Select TAS
Port- Select the MFD ARINC 429 port to which the TAS sensor is wired.
TAS Type- Select Skywatch or Bendix/King
External Controller? (SkyWatch only) - A check in this box indicates that control of
Standby/Operate and Self Test functions is not performed by the MFD but by the SkyWatch
display or a GPS. Only one device may control the Standby/Operate and the Self Test
functions thus they are NOT available on the MFD with external controller checked.
Heading Available? - Checking this field indicates that heading data is supplied to the TAS
sensor via synchro, stepper or ARINC 429 and is available to the MFD.

7.3.5.2 TAS (SkyWatch) Checkout

Self test can only be performed from the STANDBY mode and will return to the
STANDBY mode upon successful completion of the self test. To perform a Self test do the
following:
1. With Traffic in Stand By, rotate the left knob and select the Setup page.
2. Select Traffic Self Test.
3. The Map page will pop up.
4. The Sensor Status indicates that the sensor is in “Test” and a Traffic test pattern
appears on the display.
If the self test fails, an error message is generated and displayed on the MFD screen.
Refer to the SKY497 Installation manual for explanations and fault isolation
procedures.
Installation checkout - Once J1-80 (ALT_DISP1) is strapped to ground, the
Setup/Calibration menu is no longer available through the WX-1000 display or
MFD. To perform calibration and checkout, an external terminal or PC must be
connected. Once this configuration is saved, ARINC 429 communications to the MFD
will begin.
Use the alternate display procedure (Appendix E) in the SKY 497 Installation manual.
A terminal device using a RS-232 serial data cable is needed for these setup
procedures. Appendix D in the SKY497 Installation manual explains how to
configure the terminal device. Any computer with RS-232 terminal emulation
software (e.g., Procomm, HyperTerminal, etc.) may be used as the terminal device.

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Figure 9 TAS selection on Traffic Setup Page

7.3.5.3 TAS (Bendix/King) Checkout

Verify correct communication by monitoring the Message List on the Setup page for
normal message “Traffic Sensor Operating Normally”. The MFD does not command the
KTA870 into Self test mode. Use the KTA870 control panel if installed. Refer to the
KTA870 Installation Manual for fault isolation procedures.

7.3.5.4 TCAD (Optional) Setup

The MFD supports Ryan 9900B and 9900BX TCAD sensors. Connect aircraft power to the
Ryan TCAD sensor per the Ryan Installation manual. The MFD does NOT provide power to
the Ryan sensor. TCAD is interfaced to the MFD via RS232.
Sensor: Select TCAD
Port: Select the MFD RS232 port to which the TCAD sensor is wired.
TCAD Type: Select either 9900B or 9900BX, corresponding to the installed TCAD sensor unit.
Note that 9900BX sensors are treated like TAS systems, so the TCAD Shield sizes are not
presented as adjustable. Note that some software versions may not present this option to
select TCAD type. If the option is not presented, all TCAD sensors will use the shield size
settings described below.

TCAD Shields: When interfaced with the TCAD 9900B, there are 3 shield sizes that can be
set: Terminal, Standard, and Enroute
Range: Sets the horizontal range of the shield. The range is in nautical miles and can be set
for a value between 0.0 and 10nm, in 0.1nm increments

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Height: Sets the vertical distance in feet with a value between 0 and 5000 ft. in 100 ft.
increments
Select the shield you wish to configure from the Shield drop down menu. Select the desired
Range and Height from the respective drop down lists. The following table gives the
suggested minimum and maximum values for the range and height of each shield.

Range (NM: 0.5) Height (feet: 100)

Min Max Min Max
Terminal 0.5 1.5 200 1000
Standard 1.0 3.0 500 1500
Enroute 2.0 6.0 1000 2000

NOTE: The max range values shown above are the largest values that the TCAD
processor will accept. Choosing larger values than those shown will cause the
processor to default to smaller shield sizes and is not recommended.

7.3.5.5 TCAD Dual Display Setup

When installing the MFD with the Ryan TCAD display unit, refer to the Ryan TCAD 9900
series Installation manual for wiring procedures. Reference Figure 2-15 Wiring Diagram for
Dual Displays and Section 7 in the Ryan manual for instructions.
7.3.5.6 TCAD Checkout

The MFD does not display the TCAD self test function. If you wish to perform this test, then
you must use the Ryan TCAD display unit.
On installations with the TCAD 9900 display unit, follow the checkout procedures given in
the 9900 series Installation Manual.
On installations without the TCAD 9900 display unit (MFD only), perform checkout
procedures listed in the 9900 series Installation Manual, with the exception of the display test.

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Figure 10 TCAD selection on Traffic Setup Page

7.3.5.7 TIS (Optional) Setup

EX5000 MFD supports the display of traffic information from a Garmin GTX-330 TIS-capable
Mode-S transponder.
Note: This option is available on 530-00148-000 and 530-00162-( ) software. This sensor is not
supported by the EX3000.

Wire power to the Garmin GTX -330 transponder per the Garmin Installation manual. The
MFD does NOT provide power to the GTX sensor. TIS uses an ARINC 429 data connection
between the transponder and the MFD. Make this connection after consulting the wiring
diagrams in the appendix of this document and the GTX-330 installation manual.
On the EX5000 Traffic Setup Page:
Sensor: Select TIS-G
Port: Select the MFD ARINC 429 port to which the TIS transponder is wired.

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Figure 11 TIS selection on Traffic Setup Page

7.3.5.8 TIS Checkout

Use a TIS transponder test set to test the combined installation of GTX-330 and the EX5000. If
no test set is available, conduct operations in an area supporting TIS data and verify that data
is received and traffic is displayed.

7.3.5.9 Traffic Communications Check (Messages)

After the MFD has been restarted, any of the following messages may appear in the main
viewing screen or the message bar and Setup page.

Message Meaning

Traffic Sensor is Not Communicating Traffic data is not being received.

The traffic sensor has been placed in

Traffic Sensor is in Stand-By (TAS/TIS)
Standby mode.
The traffic sensor has been placed in Self-
Traffic Sensor is in Self-Test (TAS)
Test mode.

Traffic Sensor is Operating Normally Verification that Traffic data is valid.

Occurs when altitude data has been lost

TCAD Altitude Unavailable (TCAD)
from the TCAD sensor.
The traffic sensor has reported an internal
Traffic Sensor has Failed fault, or the RS-232 ports are not
configured correctly (TCAD).

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NOTE: Upon completion of all configuration procedures, installers should
confirm that the MFD is configured for the correct Traffic sensor.

7.3.6 TAWS (Optional)

The MFD interfaces to the Honeywell Bendix/King EGPWS systems with Phase 2 software or
later.

7.3.6.1 TAWS Setup

To configure the MFD to interface to the TAWS, access Maintenance Mode and select TAWS
Setup.
Sensor: Select “Honeywell EGPWS”
ARINC 429 Port: Select “ARINC 429 4 – TAWS Default”
ARINC 453 Port: Select “ARINC 453 2 – TAWS Default”
Altitude Annunciation On: Selection of this feature will permit a visual annunciation of GPS
altitude on the TAWS display. A check mark in the adjacent box will appear if selection is
desired.
Upon completion of these settings, select “Save” and restart the MFD.

Figure 12 TAWS Sensor Setup Page

7.3.6.2 TAWS Checkout

Set the MFD to the TAWS page and perform a functional test of the GPWS system in
accordance with manufacturer’s instructions. Refer to the MFD Pilot Guide for display
operation.
The GPWS software must support KC Picture Bus (KCPB) Phase 2. Consult the Honeywell
GPWS documentation for applicable software configurations. Proper operation of the GPWS
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 MFD display. Refer to the EGPWS system
installation manual for explanations and fault isolation procedures.

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7.3.6.3 TAWS Communications Check (Messages)

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 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 Initializing If message does not clear within 60 seconds, communication
between the MFD 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 Indicates that the MFD is not receiving data from the Terrain
Communicating 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 The TAWS Sensor has declared itself inoperative.
Unavailable
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 Inhibited The TAWS sensor is in the “Inhibited” mode.
o Verify that the “Inhibit” mode has been not been selected at the
separate TAWS control panel.
o Refer to TAWS sensor installation and user’s manual to troubleshoot.

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7.3.7 Radar Sensor (700-00030-005 EX5000 only)

Radar support is provided by the Bendix/King RDR-2000 Radar system, including the
AlliedSignal ART-2000 sensor, and is an option only available on the 700-00030-005 EX5000.
The 530-00170-000 and 530-00170-001 software are the only software part numbers that will
support radar.

From the Radar setup page, select Radar Installed, save the selection, and restart the MFD.
The following table describes the configuration options offered by the ART-2000 sensor.
Further details are available in the Radar installation and operations manual.

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 EX5000 radar display. Typical beam
Beam Height 0.0O – 19.5O
widths are provided below.
Enable Gain Control Check/No Enables R/T variable gain control to be commanded from
Check the EX500.
Enable VP Check/No When checked, enables Radar Vertical Profile mode.
Check
Enable Auto-Tilt Check/No When checked, enables Radar auto-tilt mode.
Control Check
Primary Indicator (1) Check/No When checked, enables EX500 control of radar functions.
Check
Disable Stabilization Check/No Disables EX500 display of the “Stab Off” annunciation
Check
Enable Automatic Check/No When checked, enables the EX500 to auto-command the
Standby Check radar to standby when ground is sensed to be below 20
kts.

Beam width information is given in the table below.

Antenna Width Generic Beam Width Bendix/King Radars

10” 10 O 10 O
12” 8O 8O
18” 5O 5.6 O

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The following table describes the features provided by the ART-2000 sensor.

Values
Range

supported
Scan Arcs

# of colors

Multiple Ind

Stabilization
control
Stab on-off

Auto-Tilt

VP

Roll Trim adj

ARL/PAC

Target Alert

Tilt settings
other than 0°
Azim Lines
ART-2000 10, 20, 90°, 4 • • • ∇ • • • ±15°
(RDR-2000) 40, 80, 100°
160, 240
[ART-
2000]
• 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

7.3.7.1 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.

7.3.7.2 Calibration with AlliedSignal (Bendix/King) 2000 Radar Sensor

This section describes Post-Installation System Configuration and Calibration of the

Bendix/King RDR-2000 Radar System using the EX5000 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

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2.4.4.1 STABILIZATION CALIBRATION WITH RADAR INDICATOR.

NOTE
If the EX5000 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.

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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 EX5000

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.

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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 Step L.
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 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
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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.

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.

7.3.7.3 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
setting of the Roll Trim has been accomplished, save the new setting by returning to the
Radar Setup using the Back button.

7.3.7.4 RADAR Checkout

Perform a functional test of the RADAR system in accordance with manufacturers

instructions. Refer to the MFD Pilot Guide for display operation.

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7.3.7.5 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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7.3.8 Map Setup

The Avidyne MFD has the capability to overlay Traffic and Lightning information onto the
Map display. To utilize this feature, Map requires Heading or Track information.
The MFD can receive HEADING data from one of following sources:
Garmin 400 series GPS (via ARINC 429).
L-3 Communications Stormscope (via RS-232). This is the most common method.
L-3 Communications Skywatch (via ARINC 429) with software level 1.6 or higher.
Honeywell (Bendix/King) KTA-870 or KMH-880
TRACK is the actual direction the aircraft is moving relative to the earth’s surface, and is
obtained from the GPS.
To configure the Map heading source, access Maintenance Mode as described in Section 7.3.1
and select Map Setup. Use the right hand knob to cycle through the selections: None (Use GPS
Track), FMS/GPS, Stormscope, and SkyWatch. When the appropriate setting is selected,
press the Save bezel key. The MFD must be restarted for the setting to take effect.

7.3.9 Engine Sensor Setup and Checkout (When EMax equipped)

7.3.10 Engine Sensor

The MFD supports engine display on Cirrus, Diamond, Lancair, and Piper Aircraft by
receiving data via RS232 and/or ARINC422 from an engine sensor interface unit specifically
designed for each aircraft. Not all display functions are available on all aircraft.
NOTE: The Engine Instruments Setup may only be activated for those aircraft specifically
included under Avidyne Service Bulletin or STC or TC authorization. Do not set up the MFD
Engine Sensor interface for any unapproved aircraft installation.

7.3.10.1 Engine Sensor Setup

To configure the MFD for interface with the optional Avidyne Engine Sensor Interface Unit
(SIU), Data Acquisition Unit (DAU) or a Vision System DPU, access Maintenance Mode and
select Engine Setup (See Figures 11 & 12). Highlight each configuration item and select the
appropriate MFD settings as shown below. When instructed, proceed to the Aircraft Setup
Page to complete the Engine Instruments page setup.

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Figure 13 Engine Setup Page Figure 14 Engine Setup Page

with Fuel Cal with Electrical

NOTE: Upon completion of all configuration procedures, installers should

confirm that the MFD is communicating properly with the corresponding
engine interface unit. This can be verified following the sensor setup
procedure.

NOTE: Figures 11 & 12 depict representative Engine Instruments Setup pages.

This page will contain different selectable options depending on MFD
software configuration installed.

The MFD uses an RS-232 data connection to receive data from the Engine Sensor Unit. An
ARINC 429 connection is also used for specific aircraft.
Sensor Type - Select “Avidyne SIU”, “Vision DPU”, or “Avidyne DAU” as appropriate.
Port – Select the MFD RS232 port to which the Engine interface unit is wired
Aircraft Model- Use the appropriate selection from the Aircraft Model pull down list
DAU ARINC Port – Select the ARINC port to which the Engine interface unit is wired.
DAU Fuel Quantity Port – Select the RS232 port from which fuel quantity will be received.
Electrical/Rudder Trim Port – Select the RS232 port from which electrical and rudder trim
information will be received.
Vacuum System Installed (Optional) - If the MFD software version supports a display of
vacuum system pressure on the Engine Page, a checkbox will also be displayed on the Engine
Setup page. Select this checkbox and use the knob to check the box, if a vacuum system with
compatible vacuum pressure sensor is installed in the aircraft.
Electrical (Optional) – Select Single Bus, Single Alternator; Single Bus, Dual Alternator; or
Dual Bus, Dual Alternator. (Note that some selections are not available with some aircraft.)
Voltage (Optional) – Select 14V or 28V, as appropriate, for the aircraft installation.
Determines only Engine Page display ranges for electrical system information.
Units – Select display of fuel information in English or metric units.

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NOTE: The data box at the bottom of the page shows the configuration
of the SIU and whether data is being properly received. If the Engine Setup
settings do not match with the configuration settings of the SIU/DAU, you
will see a yellow annunciation alerting you to recheck configuration of this
page and/or the configuration settings of the SIU/DAU. If the SIU/DAU
was off or not properly connected when the Engine Setup page was
entered, but subsequently is properly selected and operating correctly, the
Engine Setup Page status box may not be properly refreshed to reflect this.
The installer should confirm the correct Engine Setup options are selected,
press Save, and restart the MFD. Confirm after restart that the MFD is
receiving the engine data from the SIU/DAU.

Fuel Quantity Calibration (Optional)

Note: Option not available on all aircraft. This option only available with software part
number 530-00137-000, 530-00137-001, 530-00170-000, and 530-00170-002.
Fuel quantity indicator calibration is used to compensate for aircraft-to-aircraft variations
in the fuel quantities reported by the Engine Data Acquisition Unit (DAU).
The fuel quantity indicator calibration is accessed from the Engine Setup page. Provided
the DAU is communicating with the MFD and sending valid fuel quantity data, the fuel
quantity indicator calibration may be accomplished. If the DAU is not communicating
with the MFD, a DAU failure screen is displayed when the fuel cal page is selected. The
only operator selection available in that situation is to exit the page.
The fuel quantity indicator calibration page provides a display of the current fuel
quantity indicator calibration values. Different options are available depending on the
state of the fuel quantity indicator calibration. The three states of the fuel quantity
indicator calibration are: (1) Not Calibrated; (2) Calibration Underway; and (3)
Calibrated.
Procedure (for 530-00137-() and 530-00170-002 software):
1. From the Not Calibrated state, the operator may “Begin Cal” or “Exit” the fuel
calibration page.
2. If the operator chooses “Begin Cal”, the state of fuel calibration changes to Underway
and the fuel quantity indicator can be calibrated.
a. If “Exit” is pressed, the operator is returned to the Engine Setup page with
the calibration state remains in the previous state.
3. Use the right knob to select the current calibration point. The selected calibration
point is highlighted and the value displayed is the current reported quantity from the
DAU. A message at the bottom of the screen prompts the operator to add the
appropriate amount of fuel and then to select “Accept Value” once the value
reported from the SIU has stabilized.
a. If the SIU reported value is not within 2 gallons of the test point value, a
message “DAU Reported Fuel Quantity Out Of Tolerance” will be presented
and the value will not be accepted.
4. This process is then repeated for all the calibration points.

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a. If the operator needs to pause the calibration process and turn off power to
the MFD, the “Save” button is used to save the interim calibration values.
5. Once all points have been calibrated, the operator presses “Calibration Complete” to
cause calibration factors to be computed and applied to DAU reported fuel quantity.
6. Other options from the Underway state are to “Restore Last Cal” and “Clear Cal”.
a. Pressing “Restore Last Cal” causes the calibration values from the last
completed calibration to be restored and the state to change to Calibrated.
b. Pressing “Clear Cal” causes all calibration values to be cleared and the state
to change to Not Calibrated. An “Are You Sure?” prompt will give the
operator a chance to reconsider the decision to either “Restore Last Cal” or
“Clear Cal”.
NOTE: Pressing “Cancel” from the Underway state causes the current calibration session
to be aborted with any unsaved interim calibration values being discarded.
For the fuel calibration procedure for the 530-00170-000 software, refer to the Piper
Process Specification document PPS60185.

7.3.10.2 Engine Sensor Checkout

After the MFD has been restarted, view the Engine page to verify data communication.
Operate the aircraft engine to confirm correct operation of all sensors. Aircraft Setup
(below) will have to be completed for Percent Power function to correctly operate on
some models.

7.3.11 Auxiliary Data (Optional)

The MFD may be configured to receive pressure altitude and outside air data from the PFD
via a ARINC 429 interface. Note: Option not available on all aircraft.

7.3.11.1 Auxiliary Data Setup

To configure the MFD for Aux Data access Maintenance Mode and select Aircraft Setup.
Aux Data– Select ‘Avidyne PFD”. This action will result in the receipt of ARINC 429 data
from the PFD for input to the % Power calculations.
Port – Select MFD ARINC port to which the PFD is wired.
Once settings are made, press the “Save” button to return to the Maintenance Mode
screen and restart the MFD by pressing “Restart System”. After restart, proceed with
system checkout.

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Figure 15 Aircraft Setup Page with Datalink

7.3.11.2 Auxiliary Data Checkout

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

PFD is Operating Normally Verification that pressure altitude and

OAT data received by the MFD is valid

PFD is Not Communicating Pressure altitude or OAT data are not being
received by the MFD

7.3.12 Datalink (Optional)

Note: Option not available on all models. MFDs may be equipped with no Datalink, either
Narrowcast or Broadcast datalink, or both Datalink types.
To configure the MFD for Datalink access Maintenance Mode and select Aircraft Setup.

7.3.12.1 Narrowcast Datalink Setup

Confirm that the datalink setup fields on the Aircraft Setup page are configured for:
Datalink – Select “Quake SC”. This will enable the datalink functionality communication
with the internal Datalink transceiver.
Port – Should only be set to RS232 port 6, the Datalink Default.

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7.3.12.2 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 RS-232 port wired to the XM receiver, nominally RS232 4.
Save settings and restart MFD.

7.3.12.3 Narrowcast Datalink Checkout

Access the MFD Maintenance Mode. Select System Info. Select Datalink Info.
When the optional narrowcast datalink function is enabled, and the proper port is selected on
the Aircraft Setup maintenance mode page, the EX5000 is pre-configured for datalink
operation. Accessing the Datalink Info page from the System Info utility, which is entered
from the Maintenance Mode menu, gives details of the configuration.
Figure 20 depicts the Datalink Info page. Verify the presence of SC Serial Number and
version information on this screen.

Figure 16 Narrowcast Datalink Info Page

7.3.12.4 Narrowcast Datalink Satellite Reception Confirmation

ORBCOMM satellite network transmits very low power VHF signals that the EX5000 must
receive. If the antenna is not properly installed or if there is excessive electromagnetic
interference (such as a nearby radio transmitter, ground power cart, or inadequately
grounded avionics), the system will not achieve successful reception. The following steps
may be taken to assess system performance.
• Bring the aircraft to an area with the clearest view of the sky to the horizon.
• From Datalink Info table (see Figure 20), monitor for up to five minutes under the
following conditions; other avionics off, avionics on, engines at idle, engines at

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takeoff power. With a satellite in view, the signal strength and quality should peak
above the following values:

Maintenance Mode, System Info, Trip Page, Narrowcast (2 arrows) Status

Datalink/Narrowcast Info
"Signal strength" is greater than -118 dBm Signal Strength > 4, (scale of 1-10)
(-130 is lowest, -100 is highest)
"Estimated SNR (EbNo)" is greater than 10 dB Signal Quality > 4, (scale of 1-10)
“Segment errors: less than 10% Message Quality = 10, (scale of 1-10)

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 the aircraft.
• There is a local source of electromagnetic interference.
- Try shutting off any nearby sources (such as VHF radios, alternators, magnetos,
ground power cart).
- Relocated the aircraft away from potential nearby sources.
- Check electrical connections and grounds.
- There is poor satellite coverage. Try again after fifteen minutes.
- Check the antenna and cable for proper installation.
- Check the connection between the antenna and its ground plane.
Consult www.avidyne.com for any additional guidance.

7.3.12.5 Broadcast Datalink Checkout

Power up the MFD and XM Receiver 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.
Refer to the Heads Up Technology, XMD076 XM Receiver Installation Manual and Activation
Instructions. Contact Heads Up Technologies at service@heads-up.com or www.heads-
up.com.

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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 XM Receiver

Broadcast is Not Communicating

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

7.3.12.6 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.

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

Consult www.avidyne.com for any additional guidance.

7.3.12.7 Radar Setup

When Radar is installed select the appropriate MFD settings as shown in the following table:

Configuration Item MFD Setting Comment

Radar Sensor Allied Signal ART 2100 is also an
ART2000 available sensor
Park Position Centered
Beam Width 7 degrees
Beam Height 7 degrees
Enable Gain Control Checked
Enable VP Checked
Enable Auto Ztilt Unchecked
Control
Primary Indicator Checked
Disable Stabilization Unchecked
Enable Automatic Unchecked
Standby

Press the Save bezel key. The MFD must be restarted by pressing the “Restart System” bezel
key for the settings to take effect.

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8. Diagrams
This section is not applicable.

9. Special Inspection Requirements

This section not applicable.

10. Application of Protective Treatments

This section is not applicable.

11. Data
This section is not applicable.

12. List of Special Tools

This section is not applicable.

13. For Commuter Category Aircraft

This section is not applicable.

14. Recommended Overhaul Periods

This section is not applicable.

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15. Airworthiness Limitation Section

The Airworthiness Limitations section is FAA approved and specifies maintenance required
under §43.16 and §91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.
There are no additional airworthiness limitations as a result of this modification.

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16. Revision
Revisions to this document shall be coordinated through the Boston Aircraft Certification
Office, the Kansas City AEG, and the STC holder. Inquiries relating to the ICA should be
made to Avidyne Corporation. If you would like to be notified of future revisions to this
manual please furnish the information listed below:

Name
Address
City, State, and Zip Code
Part Number of Manual
Current Revision Status of Manual

Please submit this information to:

Avidyne Corporation
55 Old Bedford Road
Lincoln, MA 01773

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