uAvionix Ping200S Manual

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Ping200S
User and Installation Guide

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© 2016 uAvionix Corporation. All rights reserved.
uAvionix Corporation
380 Portage Ave.
Palo Alto, CA 94306
http://www.uavionix.com
[e-mail]
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®is a registered trademark of uAvionix Corporation, and may not
be used without express permission of uAvionix.

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1 Revision History
Revision
Date
Comments
A
10/21/16
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 un-manned aircraft operating above
500ft AGL
This antenna used for this transmitter must installed to provide
a separation distance of at least 20cm from all persons.
!
!

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3 Limited Warranty
uAvionix products are warranted to be free from defects in material and
workmanship for one year from the installation in the aircraft. For the
duration of the warranty period, uAvionix, at its sole option, will repair or
replace any product which fails under 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.
This warranty does not apply to cosmetic damage, consumable parts,
damage caused by accident, abuse, misuse, water, fire or flood, damage
caused by unauthorized servicing, or product that has been modified or
altered.
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.

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4 Contents
1Revision History...................................................................................3
2Warnings / Disclaimers........................................................................4
3Limited Warranty..................................................................................5
5Introduction..........................................................................................8
5.1 Description....................................................................................8
5.2 Interfaces......................................................................................9
5.3 TABS..........................................................................................10
5.4 Software and Airborne Electronic Hardware Configuration. ........11
5.5 Supplied Accessories..................................................................11
6Technical Specifications ....................................................................12
6.1Markings.....................................................................................13
7Equipment Limitations .......................................................................13
7.1 Installation...................................................................................13
7.1.1 Modifications and Use Outside of Intended Scope ................13
7.1.2 Deviations .............................................................................13
7.1.3 Configurable Options.............................................................13
7.1.4 Approvals..............................................................................13
7.1.5 FAA Transmitter License and FCC Grant of Equipment
Authorization......................................................................................14
8Equipment Installation .......................................................................15
8.1 Unpacking and Inspecting...........................................................15
8.2 Mounting.....................................................................................15
8.3 Connections................................................................................16
8.4 Wiring Diagram...........................................................................17
8.5 Cooling Requirements ................................................................19
8.6 Wiring Considerations.................................................................19
8.7 Antenna Installation ....................................................................20
8.7.1 Supplied Dipole Antenna.......................................................20

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8.7.2 Conventional OEM Monopole Antenna..................................20
8.7.3 Antenna Cable ......................................................................22
9Configuration.....................................................................................24
9.1 ICAO Number.............................................................................24
9.2 VFR Squawk Code .....................................................................24
9.3 Callsign.......................................................................................24
9.4 Aircraft Maximum Speed.............................................................25
9.5 Aircraft Category.........................................................................25
9.6 Aircraft VSO..................................................................................25
9.7 Aircraft Size ................................................................................25
9.8 GPS Antenna Offset ...................................................................25
9.9 ADS-B Rx Capability...................................................................26
9.10 Programming..............................................................................27
10 Post Installation Checks.....................................................................28
11 Continued Airworthiness....................................................................28
12 Environmental Qualification Forms....................................................29

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5 Introduction
5.1 Description
The Ping200S is a TSO-C199 Class A, Mode S, level 2e transponder with
support for ADS-B extended squitter. The Ping200S 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.
This system will enable the aircraft to be visible to ATC and other aircraft
equipped with:
Traffic Advisory System (TAS) as defined in TSO-C174()
Traffic Alert and Collision Avoidance System I (TCAS I) as defined in
TSO-C188()
Traffic Alert and Collision Avoidance System II (TCAS II) as defined
in TSO-C119d
ADS-B In capability as defined in TSO-C154c, TSO-C166b and TSO-
C195b
This equipment has received a FAA transmit license for manned
aircraft and a license for un-manned aircraft operating above
500ft AGL
!

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5.2 Interfaces
The Ping200S has a single SMA antenna connection, a 6-pin Host
interface and a 4-pin FYXnav GPS interface.
Host Interface
Interface
Specification
Protocol
Power Input
46 –52V
COM1 RX
57600bps
VFR Squawk Code
Call sign
Squawk Code
IDENT
Transponder Mode
GDL 90 Compatible
Control Protocol
(See Appendix A)
COM1 TX
57600bps
Heartbeat
Ownship
Geometric Altitude
GDL 90
(See Appendix B)
COM2 RX
115200bps
Reserved for future use.
Mutual
Suppression
Input
Commonly used between
transponders and DME
systems, and between
transponders and collision
avoidance systems.
FYXnav Interface
Interface
Specification
Protocol
FYXnav
115200bps
GPS
Altitude Encoder
ICAO number
VFR Squawk Code
Callsign
Aircraft Maximum Speed
Aircraft Category
Aircraft Vso
uAvionix

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Aircraft Length and Width
GPS Antenna Offset
ADS-B Rx Capability
5.3 TABS
The intent of a Traffic Awareness Beacon System (TABS) is to increase
safety within the National Airspace System (NAS) by encouraging the
voluntary equipage of a low cost, compact, easy to install device that will
allow other aircraft equipped with collision avoidance systems and traffic
advisory systems to track and display the TABS aircraft. TABS are
intended to be used on aircraft that are exempt from carrying a transponder
or ADS-B equipment such as gliders, balloons and aircraft without electrical
systems.
A TABS will allow these exempted aircraft to be visible to other aircraft
equipped with:
Traffic Advisory System (TAS) as defined in TSO-C147().
Traffic Alert and Collision Avoidance System I (TCAS I) as defined in
TSO-C188().
Traffic Alert and Collision Avoidance System II (TCAS II) as defined
in TSO-C199d.
Aircraft with ADS-B In capability as defined in TSO-C154c, TSO-
C166b and TSO-195b.

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5.4 Software and Airborne Electronic Hardware
Configuration.
Part
Part Number
Revision
SDA
Software
UAV-1000704-001
A
1
Airborne Electronic Hardware
UAV-1000706-001
A
1
5.5 Supplied Accessories
Part
Part Number
Revision
Ping200S
UAV-1000706-001
A
Power Adapter
UAV-1000707-001
A
Ping200S –Power Adapter
Cable
Power Adapter –Battery Cable
A
FYXnav TSO GPS/Baro
UAV-1000568-001
A
Ping200S - FYXnav Cable
UAV-1000595-001
A
PingBuddy
UAV-1000525-001
A
Programmer
USB Micro Cable
Dipole Antenna
UAV-1000653-001
A
4S 800mAHr LiPo Battery
AC Charger
Fastener Set
FYXnav Mounting Tape
Ping200S User Manual
UAV-1000711-001
A
FYXnav Programming Manual
Case

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6 Technical Specifications
Specification
Characteristics
Compliance
TSO-C199 Class A
Level 2e Class 1 DO-181E
Class B1S DO-260B
FCC ID
2AFFTP200S
FAA Transmit
License
Manned aircraft. Un-manned operating above 500ft
AGL.
Software
RTCA DO-178B Level C
Hardware
RTCA DO-254 Level C
Power
Requirements
11 –33VDC. Typical 2W.
Altitude
35,000ft
Operating
Temperature
-45°C to +70°C
Humidity
Tested to Category DO-160G Category B2
Transmit
Frequency
1090MHz ±1MHz
Transmit Power
250W nominal; 125W minimum at antenna after
allowing for 0.5dB connector losses and 1.5dB cable
losses.
Transmitter
Modulation
6M75 V1D
Receiver
Frequency
1030MHz
Receiver
Sensitivity
-74dBm ±3dB
Weight
50grams
Height
17mm
Length
59mm
Width
57mm

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6.1 Markings
Ping200S, uAvionix Inc. TSO-C199 Class A
P/N: UAV-1000xxx-001 S/N: 10000001
DO-181E Class 2e Level 1 FCC ID: 2AFFTP200S
7 Equipment Limitations
7.1 Installation
7.1.1 Modifications and Use Outside of Intended Scope
This device has been designed and tested to conform to all applicable
standards in the original form and when configured with the components
shipped with the device. It is not permissible to modify the device, use the
device for any use outside of the intended scope, or use the device with
any antenna other than the one shipped with the device.
7.1.2 Deviations
There are no deviations from the MPS of TSO-C199 Class A Device.
7.1.3 Configurable Options
Accessing or altering configurable options not intended to be operated may
cause pilot distraction.
7.1.4 Approvals
Approvals do not cover adaptations to the aircraft necessary to
accommodate ancillary equipment such as power provisions, mounting
devices or external antennas; such items must still be approved under
existing minor modification/change processes applicable to the aircraft.
This device meets the minimum performance and quality control standards
required by a technical standard order (TSO). Installation of this device
requires separate approval.

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This device does not meet requirements for use in transponder rule
airspace as defined in 14 CFR § 91.215 and ADS-B rule airspace as
defined in 14 CFR § 91.225.
7.1.5 FAA Transmitter License and FCC Grant of Equipment
Authorization
This equipment has received a FAA transmit license for manned aircraft,
and for un-manned aircraft operating above 500ft AGL.
This equipment has been issued an FCC Grant of Equipment
Authorization.
The equipment contains FCC ID 2AFFTP200S and is marked on the
equipment nameplate.

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8 Equipment Installation
This section describes the installation of Ping200S and related accessories
in the aircraft, including mounting, wiring, and connections.
8.1 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.
8.2 Mounting
The Ping200S 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, remembering 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 Ping200S 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
holes. It should be mounted on a flat surface.

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8.3 Connections
Whenever power is supplied to the transponder, a 50ohm load
must be provided to the SMA connection. You can use the
supplied antenna or a commercially available 50ohm load.
!

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The following diagrams illustrate the setups using 48V and 14/28V Aircraft
power. Note that a power adapter will be required when installing with
14/28V Aircraft power.
48V (46-52V) Aircraft Power

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Host Interface
Pin
Type
Physical
Rate
Link
1
Ground
2
Aircraft Power
46-52V
3
COM1 TX
RS-232 Out
57600bps
GDL 90
4
COM1 RX
RS-232 In
57600bps
Control
5
COM2 RX
RS-232 In
115200bps
RFU
6
SURPRESS
3.3V IO
Mating Connector: Molex 0436450600, Pins: 0462350001
FYXnav Interface
Pin
Type
Physical
Rate
Link
1
RX In
3.3V Serial
115200bps
uAvionix
2
TX Out
3.3V Serial
115200bps
GDL 90
3
Power
5V Out
4
Ground
Mating Connector: JST ZHR-4, Pins: SZH-002T-P0.5
LEDs
LED
SOLID
FLASHING
RED
FAULT
Reply /
Transmit
GREEN
Powered
Receiving
Interrogation

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8.4 Cooling Requirements
Ping200S 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 Ping200S 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.
8.5 Wiring Considerations
The Ping200S was designed and tested using unshielded, untwisted wiring.
There may, however, be technical benefits of improved electromagnetic
emissions and susceptibility to and from the transponder system. Use of
twisted wire can reduce interference and break-through on adjacent audio
wiring if it is not possible to route them separately.
The distance between the Ping200S and the power adapter is limited by
the impedance of the wire between them. The Ping200S is powered from
the power adapter, not directly from aircraft power, and, therefore, the
acceptable voltage drop in the power line is what limits the distance.
The Ping200S needs an impedance of less than 0.5ohm in the power line
for satisfactory operation. The following table gives guidance for typical
aircraft hook-up wire. Note that different brands may vary –check your
supplier for details.
Gauge
ohm/km
Length for 0.5ohm
20 AWG
35
14.2m
22 AWG
64
7.8m
24 AWG
99
5.0m
An alternative to a harness built from individual wires, particularly for a long
cable run, is to use a multi-core cable. Aviation grade cables with 6 or more
cores are often more expensive than individual wires, and, therefore, are
not generally a good choice. For aircraft where those situations do not

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apply, an attractive alternative solution may be to use 3 or 4 pair data
cable.
Please note that not all data cable is suitable for this application. Cables
with solid cores should not be used. Cables should be selected based on
the wear characteristics of their insulation material, including temperature
rating, resistance to solvents and oils, and flammability. Most inexpensive
commercial data cables have poor flammability properties.
8.6 Antenna Installation
8.6.1 Supplied Dipole Antenna
The following considerations should be taken into account when siting the
antenna.
The antenna should be well removed from any projections, the
engine(s) and propeller(s). It should also be well removed from
landing gear doors, access doors or other openings which will break
the ground plane for the antenna.
The antenna should be mounted in a vertical position when the
aircraft is in level flight.
Avoid mounting the antenna within 1 meter of the ADF sense antenna
or any COMM antenna and 2 meters from the transponder to the
DME antenna.
Where practical, plan the antenna location to keep the cable lengths
as short as possible and avoid sharp bends in the cable to minimize
the VSWR.
Electrical connection to the antenna should be protected to avoid loss of
efficiency due to exposure to liquids and moisture. All Antenna feeders
shall be installed in such a way that a minimum of RF energy is radiated
inside the aircraft.
8.6.2 Conventional OEM Monopole Antenna
The antenna should be installed according to the manufacturer’s
instructions.
The following considerations should be taken into account when siting the
antenna.