uAvionix ping200XR Manual

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ping200XR
User and Installation Guide

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ECCN 7A994 Page 2 | 28
© 2020 uAvionix Corporation. All rights reserved.
uAvionix Corporation
300 Pine Needle Lane
Bigfork, MT 59911
http://www.uavionix.com
http://www.uavionix.com/support
Except as expressly provided herein, no part of this guide may be
reproduced, transmitted, disseminated, downloaded or stored in any
storage medium, for any purpose without the express written permission of
uAvionix. uAvionix grants permissions to download a single copy of this
guide onto an electronic storage medium to be viewed for personal use,
provided that the complete text of this copyright notice is retained.
Unauthorized commercial distribution of this manual or any revision hereto
is strictly prohibited.
uAvionix®and Ping®are registered trademarks of uAvionix Corporation and
may not be used without express permission of uAvionix.

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1 Revision History
Revision
Date
Comments
A
5/14/2020
Initial Release

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2 Warnings / Disclaimers
All device operational procedures must be learned on the ground.
uAvionix is not liable for damages arising from the use or misuse of this
product.
This equipment has received a FAA transmit license for manned
aircraft and a license for unmanned aircraft operating above
500ft AGL.
The antenna used for this transmitter must be installed to
provide a separation distance of at least 20cm from all persons.
This equipment is classified by the United States Department of
Commerce's Bureau of Industry and Security (BIS) as Export Control
Classification Number (ECCN) 7A994.
These items are controlled by the U.S. Government and authorized for
export only to the country of ultimate destination for use by the ultimate
consignee or end-user(s) herein identified. They may not be resold,
transferred, or otherwise disposed of, to any other country or to any person
other than the authorized ultimate consignee or end-user(s), either in their
original form or after being incorporated into other items, without first
obtaining approval from the U.S. government or as otherwise authorized by
U.S. law and regulations.
!
!

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3 Limited Warranty
uAvionix products are warranted to be free from defects in material and
workmanship for one year from purchase. For the duration of the warranty
period, uAvionix, at its sole option, will repair or replace any product which
fails in normal use. Such repairs or replacement will be made at no charge
to the customer for parts or labor, provided that the customer shall be
responsible for any transportation cost.
Restrictions: This warranty does not apply to cosmetic damage,
consumable parts, damage caused by accident, abuse, misuse, fire or
flood, theft, damage caused by unauthorized servicing, or product that has
been modified or altered.
Disclaimer of Warranty: IN NO EVENT, SHALL UAVIONIX BE LIABLE
FOR ANY INCIDENTAL, SPECIAL, INDIRECT OR CONSEQUENTIAL
DAMAGES, WHETHER RESULTING FROM THE USE, MISUSE OR
INABILITY TO USE THE PRODUCT OR FROM DEFECTS IN THE
PRODUCT. SOME STATES DO NOT ALLOW THE EXCLUSION OF
INCIDENTAL OR CONSEQUENTIAL DAMAGES, SO THE ABOVE
LIMITATIONS MAY NOT APPLY TO YOU.
Warranty Service: Warranty repair service shall be provided directly by
uAvionix. Proof of purchase for the product from uAvionix or authorized
reseller is required to obtain and better expedite warranty service.
Please contact uAvionix support with a description of the problem you are
experiencing. Also, please provide the model, serial number, shipping
address and a daytime contact number.
You will be promptly contacted with further troubleshooting steps or return
instructions. It is recommended to use a shipping method with tracking and
insurance.

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4 Contents
1Revision History...................................................................................3
2Warnings / Disclaimers........................................................................4
3Limited Warranty..................................................................................5
4Contents..............................................................................................6
5System Information..............................................................................8
5.1 Certification Applicability...............................................................8
5.2TSO Performance.........................................................................8
5.3 Applicable P/Ns ............................................................................9
5.4 System Functions .........................................................................9
5.5 Intended TSO Deviations..............................................................9
5.6 FCC ID........................................................................................10
5.7 Device Marking...........................................................................11
5.8 Environmental Qualification Form...............................................11
5.9 Continued Airworthiness.............................................................12
5.10 System Limitations......................................................................12
6System Specifications........................................................................13
6.1 Specifications..............................................................................13
6.2 nano Control Head......................................................................14
6.2.1 nano Control Head Operation................................................16
6.2.2 Thumb Wheel Selection ........................................................16
6.3 Interfaces....................................................................................17
6.4 Serial Data Interfaces .................................................................17
7Installation .........................................................................................18
7.1 Part Numbers..............................................................................18
7.2 Unpacking and Inspecting...........................................................18
7.3 Mounting.....................................................................................18

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7.4 Connections................................................................................19
7.5 Wiring Diagram...........................................................................19
7.6 Cooling Requirements ................................................................20
7.7 Antenna Installation ....................................................................20
8Configuration.....................................................................................22
8.1 ICAO Address.............................................................................24
8.2 Aircraft Maximum Speed.............................................................24
8.3 Aircraft Stall Speed.....................................................................24
8.4 Aircraft Length / Width ................................................................24
8.5 Aircraft Registration ....................................................................25
8.6 GPS Antenna Lateral / Longitudinal Offset..................................25
8.7 Aircraft Emitter Type...................................................................25
8.8 ADS-B In Capability....................................................................26
8.9 Baro Altitude Source...................................................................26
8.10 Serial Port Baud Rate .................................................................26
8.11 SIL / SDA....................................................................................26
8.12 Default Control Mode..................................................................26
8.13 Default Squawk...........................................................................26
8.14 Baro Altitude Resolution..............................................................27
8.15 In / Out Protocols........................................................................27
8.16 Control........................................................................................27
9Post Installation Checks.....................................................................28
10 Support..............................................................................................28

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5 System Information
5.1 Certification Applicability
This installation manual provides mechanical and electrical information
necessary to install ping200XR. It is not equivalent to a regulator approved,
airframe-specific maintenance manual, installation design drawing, or
installation data package. The content of this manual assumes use by
competent and qualified personnel using standard maintenance procedures
in accordance with Title 14 of the Code of Federal Regulation and other
related accepted procedures. The conditions and tests required for
approval of this article are minimum performance standards. Those
installing this article either on or within a specific type or class of aircraft
must determine that the aircraft installation conditions are within the
standards which include any accepted integrated functions not specified by
the standards.
5.2 TSO Performance
The ping200XR is designed to meet the performance requirements of the
applicable Technical Standard Orders (TSOs) and Minimum Operational
Performance Specifications (MOPS) outlined below.
The ping200XR does not currently hold any TSOs. This manual will be
updated accordingly upon TSO Authorizations.
Function
TSO/RTCA
Class
AIR TRAFFIC CONTROL RADAR
BEACON SYSTEM/MODE SELECT
(ATCRBS / MODE S) AIRBORNE
EQUIPMENT
TSO-C112e
INCOMP
RTCA/DO-181E
Level 2els
Class 1
1090MHz EXTENDED SQUITTER
AUTOMATIC DEPENDENT
SURVEILLANCE – BROADCAST
(ADS-B)
TSO-C166b
RTCA/DO-260B
Class B1S
AUTOMATIC PRESSURE ALTITUDE
CODE-GENERATING EQUIPMENT
TSO-C88b

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Function
TSO/RTCA
Class
AIRBORNE NAVIGATION SENSORS
USING THE GLOBAL POSITIONING
SYSTEM AUGMENTED BY THE
SATELLITE BASED
AUGMENTATION SYSTEM (SBAS)
TSO-C145e
INCOMP
RTCA/DO-229E
Beta 1
5.3 Applicable P/Ns
Description
P/Ns
skyBeacon PF007 Boot Program Firmware
UAV-1001758-001
ping200X PF007 Operating Program Firmware
UAV-1002393-001
ping200X FPGA
UAV-1002392-001
5.4 System Functions
System Function
DO-178C DAL
DO-254 DAL
Mode S Transponder
C
C
GPS/SBAS
C
C
Altitude Encoder
C
C
5.5 Intended TSO Deviations
The following deviations from TSO requirements, on this non-TSO device,
are noted. These deviations will be applied for on the TSO-certified
ping200XR.
TSO
Deviation
C112e
From TSO-C112e paragraphs 3.e and 6.f to use DO-178C
instead of DO-178B
C112e
Anticipating DO-181F for a Level 2 “Basic Transponder”, UM
field support is not implemented
C112e
Anticipating DO-181F for a Level 2 “Basic Transponder”,
Comm-A is not supported
C112e
Anticipating DO-181F for a Level 2 “Basic Transponder”,
broadcast interrogations are not supported

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TSO
Deviation
C112e
Anticipating DO-181F for a Level 2 “Basic Transponder”,
multisite message protocols, as they apply to Comm-B and
Level 2 transponders, are not supported
C112e
Anticipating DO-181F for a Level 2 “Basic Transponder”, Air-
Initiated Comm-B is not supported
C112e
Anticipating DO-181F, and in compliance with ICAO Annex 10
Volume IV requirements for equipment certified after January
1, 2020, ATCRBS/Mode S All-Calls interrogations (Long P4)
are not replied to
C166b
From TSO-C166b paragraph 3.e and 6.h to use DO-178C
instead of DO-178B.
C166b
Anticipating DO-260C, Airborne Velocity subtypes 3 and 4 are
not supported
C88b
From TSO-C88b paragraph 3.e and 6.h to use DO-178C
instead of DO-178B.
C88b
From TSO-C88b paragraph 3.d to use DO-150G instead of
DO-160E.
C145e
From RTCA/DO-229E section 2.1.1.10 to use a GPS antenna
that meets uAvionix minimum performance specifications
instead of DO-301 qualified antennas.
C145e
From TSO-C145e Paragraph 3.g to use RTCA/DO-160G in
place of RTCA/DO-160E.
TSO-C145e Class Beta 1 functionality is incomplete. ping200XR does not
implement LNAV approach mode, instead operating in En Route/Terminal
mode only, as appropriate for ADS-B Out applications.
5.6 FCC ID
Model
FCC ID
ping200XR
2AFFTP200S

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5.7 Device Marking
5.8 Environmental Qualification Form
Conditions
160G
Description of Conducted Tests
Temperature and Altitude
4.0
Equipment tested to Category B2
Low temperature ground survival
4.5.1
-55°C
Low Temperature Short-Time
Operating
4.5.1
-45°C
Low Temperature Operating
4.5.2
-45°C
High Temperature Operating
4.5.4
+70°C
High Temperature Short-Time
Operating
4.5.3
+70°C
High Temperature Ground Survival
4.5.3
+85°C
Loss of Cooling
4.5.5
Cooling air not required (+55°C operating
without cooling)
Altitude
4.6.1
60,000feet
Decompression
4.6.2
Equipment identified as Category B2 – no test
Overpressure
4.6.3
Equipment identified as Category B2 – no test
Temperature Variation
5.0
Equipment tested to Category B
Humidity
6.0
Equipment tested to Category A
Operation Shock and Crash Safety
7.0
Equipment tested to Category B
Vibration
8.0
Aircraft zone 2: type 5 Category S level M
Explosion
9.0
Equipment identified as Category X – no test
Waterproofness
10.0
Equipment identified as Category S
Fluids Susceptibility
11.0
Equipment identified as Category X – no test
Sand and Dust
12.0
Equipment identified as Category X – no test
Fungus
13.0
Equipment identified as Category X – no test
Salt Spray
14.0
Equipment identified as Category X – no test
Magnetic Field
15.0
Equipment identified as Category Z

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Conditions
160G
Description of Conducted Tests
Power Input
16.0
Equipment identified as Category BX
Voltage Spike
17.0
Equipment identified as Category B
AF Conducted Susceptibility
18.0
Equipment identified as Category B
Induced Signal Susceptibility
19.0
Equipment identified as Category AC
RF Susceptibility
20.0
Equipment identified as Category TT
RF Emissions
21.0
Equipment identified as Category B
Lightening Induced Transient
Susceptibility
22.0
Equipment identified as Category A2G2L2
Lightening Direct Effects
23.0
Equipment identified as Category X – no test
Icing
24.0
Equipment identified as Category X – no test
Electrostatic Discharge
25.0
Equipment identified as Category A
Fire, Flammability
26.0
Equipment identified as Category X – no test
5.9 Continued Airworthiness
Maintenance of the ping200XR is "on condition" only. For regulatory
periodic functional checks, refer to the approved aircraft maintenance
manuals or manual supplements. The aircraft must be returned to service
in a means acceptable to the appropriate aviation authority.
5.10 System Limitations
This article meets the minimum performance and quality control standards
required by a TSO. If you are installing this article on or in a specific type or
class of aircraft, you must obtain separate approval for installation.

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6 System Specifications
ping200XR is a Mode S, Level 2els, Class 1 transponder with support for
ADS-B extended squitter, elementary surveillance and SI codes. The
ping200XR has a nominal power output of 250W and meets the power
output requirements for Class 1. The ADS-B function meets DO-260B class
B1S.
This transponder replies to both legacy Mode A/C interrogations and to
Mode S interrogations from both ground radar and airborne collision
avoidance systems. In all cases, the interrogations are received by the
transponder on 1030MHz and replies are transmitted on 1090MHz.
ping200XR integrates a RTCA/DO-229E SBAS GPS receiver.
6.1 Specifications
Specification
Value
Operating Altitude
unrestricted
Max Cruising Speed
unrestricted
Transmit Power (Max)
54dBm, 250W
1030 Receive Sensitivity
-74dBm ±3 dBm
RF Impedance
50Ω
Host Serial Communications
UCP
Export Compliance
ECCN 7A994
Input Voltage
11-34v (3S-8S LiPo)
Inrush Current Limit
1A See Note 1 below
TX Peak Current Limit
See Note 2 Below
Power Consumption (ON & ALT)
1.5W Continuous ON & ALT
4W Peak (8ms maximum)
Power Consumption (STBY)
0.4W
Transponder Performance Standard
RTCA DO-181E
Class
Class 1
Level
2els
ADS-B Performance Standard
RTCA DO-260B
Class
B1S
Certification
N/A
Environmental
RTCA DO-160G
FCC ID
2AFFTP200S
FAA Transmit License
Manned aircraft. Unmanned operating above 500ft AGL.
Software
RTCA DO-178C Level C
Hardware
RTCA DO-254 Level C
Operating Temperature
-45°C to +70°C
Storage Temperature
-55°C to +85°C
Transmitter Modulation
6M75 V1D
Weight
52grams
Height
10mm
Length
72mm
Width
47mm
RF Connector
SMA
GPS Connector
MMCX

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Note 1: Inrush and internal short-circuit protection is internally current limited to 1A. Note 2: Reply Transmission Peak
Current
Mode
Incremental Peak
Current @ 14V
Recovery
ATCRBS “7777” Reply
70mA
65us
Mode S Short
312mA
5.7ms
Mode S Long
312mA
9.4ms
1090ES DF17
312mA
9.4ms
6.2 nano Control Head
An optional nano control head is provided to allow squawk code
configuration without connecting to the configuration application.

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6.2.1 nano Control Head Operation
MODE
STBY
Standby and Programming Mode
ON
ADS-B and Mode S Active, altitude (Mode C) reporting
disabled
ALT
ADS-B and Mode S Active, altitude reporting enabled
ADSB
Mode S disabled, ADS-B active (Development Only)
Mode S Activity
Flashing – Mode S activity
Health
Flashing – Communications Healthy
Flashing – Communications Healthy and GPS locked
6.2.2 Thumb Wheel Selection
The nanoHead Control unit is controlled and configured via the thumb
wheel at the bottom of the device. Move your thumb across the wheel to
select the desired character you would like to change. Once you reach the
desired character, press the thumb wheel to select the character. Once you
have selected the character, move your thumb across the thumb wheel to
cycle through character options to choose. Once you have the character
you want, click the thumb wheel once more to set the character.

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6.3 Interfaces
The ping200XR has a single SMA antenna connection and a 4-wire power
and data interface. A MMCX connection provides connectivity to an
external GPS antenna, and the baro port provides connection to the pitot-
static system if available.
Ping200XR
CONTROL and
CONFIGURATION
POWER (9-30.3V)
ANTENNA
RS232 Serial
RS232 Serial
GPS
ANTENNA
6.4 Serial Data Interfaces
Protocol
Message Type
CONTROL and
CONFIGURATION
2400 - 115200bps
UCP RX
[0x2B] Transponder Configuration
[0x2C] Message Request
[0x2D] Transponder Control
[0x2E] GNSS Data
UCP TX
[0x00] Heartbeat
[0x0A] Ownship
[0x25] Identification
[0x0B] Geo Alt Ownship
[0x28] Sensor, Barometer
[0x2B] Transponder Configuration
[0x2F] Transponder Status
Note:
Details of the UCP packets can be found in UAV-1002375-001 uAvionix GDL90 Plus
Transponder ICD.
ping200XR

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7 Installation
7.1 Part Numbers
Part
Part Number
Rev
ping200XR
UAV-1003772-001
A
RS232-USB adapter
UAV-1002374-001
A
ping200XR User and Installation Manual
UAV-1004178-001
A
7.2 Unpacking and Inspecting
Carefully unpack the device and make a visual inspection of the unit for
evidence of any damage incurred during shipment. If the unit is damaged,
notify the shipping company to file a claim for the damage. To justify your
claim, save the original shipping container and all packing materials.
7.3 Mounting
The ping200XR is designed to be mounted in any convenient location in
the cockpit, the cabin, or an avionics bay.
The following installation procedure should be followed, taking care to allow
adequate space for installation of cables and connectors.
•Select a position in the aircraft that is not too close to any high
external heat source. The ping200XR is not a significant heat source
itself and does not need to be kept away from other devices for this
reason.
•Avoid sharp bends and placing the cables too near to the aircraft
control cables.
•Secure the transponder to the aircraft via the three (3) mounting
brackets. It should be mounted on a flat surface.

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7.4 Connections
Whenever power is supplied to the transponder, a 50 Ohm load
must be provided to the SMA connection. You can use the
supplied antenna or a commercially available 50 Ohm load.
Powering the transponder without an attached load will result in
damage to the device not covered under warranty.
7.5 Wiring Diagram
Ping200XR
CONTROL and
CONFIGURATION
POWER (9-30.3V)
ANTENNA
Control Input
(Control Head or
Autopilot)
GPS
ANTENNA
Control Interface
Pin
Type
Physical
Rate
Black
Ground
Red
Aircraft
Power
9-30.3V
Grey
COM TX
RS-232 Out
Programmable
Orange
COM RX
RS-232 In
Programmable
!
ping200XR

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7.6 Cooling Requirements
ping200XR is designed to meet all applicable TSO requirements without
forced-air cooling.
Attention should, however, be given to the incorporation of cooling
provisions to limit the maximum operating temperature if ping200XR is
installed in close proximity to other avionics. The reliability of equipment
operating in close proximity in an avionics bay can be degraded if adequate
cooling is not provided.
7.7 Antenna Installation
The following considerations should be taken into account when siting the
antenna.
•The RF antenna should be mounted in a vertical position when the
aircraft is in level flight. See figure below for proper orientation.