uAvionix Ping20S Manual

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Ping20S
User and Installation Guide

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© 2017 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
12/19/16
Initial release
B
5/25/17
Export Control

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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 not received a FAA transmit license and is
for development use only.
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 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
6.1 Markings.....................................................................................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
8Equipment Installation .......................................................................15
8.1 Unpacking and Inspecting...........................................................15
8.2 Mounting.....................................................................................15
8.3 Connections................................................................................16
8.4 Wiring Diagram...........................................................................17
Mating Connector: Molex 0436450200 ..................................................18
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.............................................................24
9.5 Aircraft Category.........................................................................25
9.6 ADS-B RX Capability..................................................................25
9.7 Programming..............................................................................26
10 Post Installation Checks.....................................................................27
11 Continued Airworthiness....................................................................27
12 Environmental Qualification Forms....................................................28

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5 Introduction
5.1 Description
The Ping20S is a TSO-C199 Class A, Mode S, 20W transponder with
support for ADS-B extended squitter. The Ping20S has a nominal power
output of 20W. 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

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5.2 Interfaces
The Ping20S has a single SMA antenna connection, a 4-pin Host interface
and a 5-pin FYXnav GPS interface.
Host Interface
Interface
Specification
Protocol
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)
FYXnav Interface
Interface
Specification
Protocol
FYXnav
COM 2
115200bps
GPS
Altitude Encoder
ICAO number
VFR Squawk Code
Callsign
Aircraft Maximum Speed
Aircraft Category
Aircraft Vso
Aircraft Length and Width
GPS Antenna Offset
ADS-B Rx Capability
MavLink

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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-1000xxx-001
A
1
Airborne Electronic Hardware
UAV-1000xxx-001
A
1
5.5 Supplied Accessories
Part
Part Number
Revision
Ping20S
UAV-1000xxx-001
A
Power Adapter –Battery Cable
A
FYXnav TSO GPS/Baro
UAV-1000568-001
A
Ping20S - FYXnav Cable
UAV-1000xxx-001
A
Wi-Fi Programmer
Dipole Antenna
UAV-1000653-001
A
Ping20S Mounting Tape
FYXnav Mounting Tape
Ping20S User Manual
UAV-1000xxx-001
A

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6 Technical Specifications
Specification
Characteristics
Compliance
TSO-C199 Class A
Level 2e 20W Class DO-181E
Class B1S DO-260B
Software
RTCA DO-178B Level D
Hardware
RTCA DO-254 Level D
Power
Requirements
11 –16VDC. Typical 2.4W On/Alt, 0.1W Standby.
Altitude
35,000ft
Operating
Temperature
-45°C to +70°C
Humidity
Tested to Category DO-160G Category B2
Transmit
Frequency
1090MHz ±1MHz
Transmit Power
20W nominal; 16W 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
15grams
Height
13mm
Length
40mm
Width
25mm

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6.1 Markings
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 apart
from output power.
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.

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This device meets the minimum performance and quality control standards
required by a technical standard order (TSO). Installation of this device
requires separate approval.
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.

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8 Equipment Installation
This section describes the installation of Ping20S 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 Ping20S 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 Ping20S 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 supplied mounting tape.
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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8.4 Wiring Diagram

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Power Interface
Pin
Type
Physical
1
Aircraft Power
11-16V
2
Ground
Mating Connector: Molex 0436450200
Host Interface
Pin
Type
Physical
Rate
Link
1
RX In
3.3V Serial
57600bps
Control
2
TX Out
3.3V Serial
57600bps
GDL 90
3
Power
5V Out
4
Ground
Mating Connector: JST ZHR-4, Pins: SZH-002T-P0.5
FYXnav Interface
Pin
Type
Physical
Rate
Link
1
NC
2
RX In
3.3V Serial
115200bps
MavLink
3
TX Out
3.3V Serial
115200bps
GDL 90
4
Power
5V Out
5
Ground
Mating Connector: JST ZHR-5, Pins: SZH-002T-P0.5
LEDs
LED
SOLID
FLASHING
RED
FAULT
Reply /
Transmit
GREEN
Powered
Receiving
Interrogation

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8.5 Cooling Requirements
Ping20S 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 Ping20S 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.
8.6 Wiring Considerations
The Ping20S 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 Ping20S and the power source is limited by the
impedance of the wire between them. The Ping20S is powered directly
from aircraft power, and, therefore, the acceptable voltage drop in the
power line is what limits the distance.
The Ping20S 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.
8.7 Antenna Installation
8.7.1 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.
8.7.2 Conventional OEM Monopole Antenna
The antenna should be installed according to the manufacturer’s
instructions.