Latitude SkyNode S100 User manual

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INSTALLATION AND OPERATION MANUAL
FOR
SKYNODE® S100
TRACKING SYSTEM
P/N:S100-001
Document No.: S100-400
Creation: Jan 24, 2007
Revision: 2.01, Jun 17, 2014
LATITUDE TECHNOLOGIES CORPORATION
101-3375 Whittier Ave
Victoria, BC, Canada, V8Z-3R1
Tel: [phone]
Fax: [phone]
Email: [email protected]

SkyNode® S100 Installation and Operation Manual
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REVISION HISTORY
Revision
Editor
Revision
Date
Comments
2.01
CK
Jun 17, 2014
ECO10071 incorporated.
Corrected Figure 2 (S100 Outline
Drawing) Section 3.7.
Corrected Table 16, page
24;stated frequency was
1.616MHz –1.625MHz.
2.00
DS
Sep 13, 2010
Complete Revision
1.00
MI
Jan 24, 2007
First version
IMPORTANT NOTICES
Information in this document is subject to change without notice. Latitude
Technologies reserves the right to change or improve their products and
to make changes in the content of this material without obligation to
notify any person or organization of such changes or improvements.
No part of this manual may be reproduced in any form or by any means or used to make
a derivative work (such as translation, transformation, or adaptation) without written
permission from Latitude Technologies Corporation.
SkyNode is a trademark of Latitude Technologies Corporation.
Copyright 2007

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Limited Warranty
Latitude Technologies Corporation warrants products it manufactures against defects in
materials and workmanship for a period of one year from the date of factory sale. During
the warranty period, Latitude Technologies Corporation will, at its option, either repair or
replace products that prove to be defective.
Buyer shall prepay shipping charges for products returned to Latitude Technologies
Corporation for warranty service and Latitude Technologies Corporation shall pay for
return of products to Buyer. However, Buyer shall pay all shipping charges, duties, and
taxes for products returned to Latitude Technologies Corporation from outside of Canada.
This warranty shall not apply to damage resulting from:
Improper or inadequate maintenance from Buyer
Buyer-supplied software or interfacing
Unauthorized modification or misuse
Operation outside of the product environmental specifications
Improper installation, where applicable
No other warranty is expressed or implied. Latitude Technologies Corporation specifically
disclaims the implied warranties of merchantability and fitness for a particular purpose.
Remedies provided herein are Buyer’s sole and exclusive remedies. Latitude Technologies
Corporation shall not be liable for any direct, indirect, special incidental, or consequential
damages, whether based on contract, tort, or any other legal theory.

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Table of Contents
1. GENERAL INFORMATION.............................................................................. 6
1.1. INTRODUCTION ............................................................................................. 6
1.2. ACRONYMS AND ABBREVIATIONS ........................................................................ 6
1.3. EQUIPMENT PURPOSE ..................................................................................... 6
1.4. EQUIPMENT DESCRIPTION ................................................................................ 6
1.5. EQUIPMENT LIMITATIONS ................................................................................. 7
1.6. SAFETY PRECAUTIONS..................................................................................... 7
2. REFERENCED DOCUMENTS ........................................................................... 7
3. SPECIFICATIONS ......................................................................................... 8
3.1. DIMENSIONS................................................................................................ 8
3.2. ELECTRICAL SPECIFICATIONS ............................................................................ 8
3.3. PHYSICAL SPECIFICATIONS ............................................................................... 8
3.4. ENVIRONMENTAL SPECIFICATIONS ...................................................................... 8
3.5. PART NUMBERS............................................................................................. 8
3.6. OPTIONAL LATITUDE KITS PART NUMBERS ............................................................ 9
3.7. S100 DIMENSIONS...................................................................................... 10
4. INSTALLATION........................................................................................... 11
4.1. INTRODUCTION ........................................................................................... 11
4.2. UNPACKING ............................................................................................... 11
4.3. AIRWORTHINESS INTEGRITY-DESIGN CONSIDERATIONS .......................................... 11
4.3.1. Cable Routing.................................................................................................11
4.3.2. Grounding......................................................................................................11
4.3.3. Wiring Integrity ..............................................................................................11
4.3.4. Coax Cables ...................................................................................................12
4.3.5. Antenna(s) location.........................................................................................12
4.3.6. S100 location .................................................................................................12
4.3.7. Testing ..........................................................................................................12
4.3.8. General Guidelines for Installation ....................................................................12
4.4. S100 INSTALLATION .................................................................................... 12
4.4.1. Mounting .......................................................................................................12
4.4.2. Grounding and Bonding ...................................................................................12
4.4.3. Interfaces ......................................................................................................13
4.4.4. Antennas .......................................................................................................15
5. OPERATION................................................................................................ 17
5.1. CONFIGURATION SET-UP ............................................................................... 17
5.1.1. Edit GPS Interval ............................................................................................18
5.1.2. Edit Connection Interval ..................................................................................18
5.1.3. View/Reset Message Log..................................................................................19
5.2. SYSTEM CHECK AND DIAGNOSIS ...................................................................... 19
6. POST INSTALLATION TESTING................................................................... 20
6.1. PRE-TEST ................................................................................................. 20
6.2. FUNCTIONAL TEST-NO ENGINE ........................................................................ 20

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6.3. FUNCTIONAL AND EMI TEST-ENGINE(S)RUNNING ................................................ 21
7. TROUBLESHOOTING ................................................................................... 22
7.1. LED BLINK PATTERN DESCRIPTION ................................................................... 22
7.1.1. LED Patterns during Startup.............................................................................22
7.1.2. LED Patterns during Regular Operation ..............................................................22
APPENDIX A- CONNECTOR PIN ASSINGMENTS .................................................. 23
APPENDIX B- INTERCONNECT INTERFACES ....................................................... 25
APPENDIX C- ENVIRONMENTAL TESTS TABLE ................................................... 30
List of Figures
Figure 1 - SkyNode S100 Tracker ............................................................................................... 6
Figure 2 - S100 Outline Drawing................................................................................................10
Figure 3 - S100 Startup Screen .................................................................................................17
Figure 4 - S100 Terminal Menu .................................................................................................18
List of Tables
Table 1- Latitude Technologies KT006 Kit ..................................................................................... 9
Table 2 - Latitude Technologies KT007 Kit..................................................................................... 9
Table 3 - S100 Input Interface...................................................................................................13
Table 4 - S100 Output Interface.................................................................................................13
Table 5 - S100 RS-232 Interface................................................................................................14
Table 6 - S100 Analog Input Interface .........................................................................................15
Table 7 - Combined Iridium/GPS Antenna Part Numbers ..................................................................15
Table 8 - GPS Antenna Part Numbers.........................................................................................16
Table 9 - Iridium Antenna Part Numbers ......................................................................................16
Table 10 - Pre-Test Checklist....................................................................................................20
Table 11 - Functional Test-No Engine Checklist .............................................................................20
Table 12 - Functional Test Checklist ...........................................................................................21
Table 13 - S100 Main Connector (P1) Pin Assignments....................................................................23
Table 14 - S100 P2 Pin Assignments. .........................................................................................24
Table 15 - GPS Connector.......................................................................................................24
Table 16 - SAT Connector .......................................................................................................24
Table 17 - Environmental Qualification Table.................................................................................32

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1. General Information
1.1. Introduction
The following information refers to the SkyNode S100 Iridium transceiver (henceforth referred to as the
“S100”) and tracking controller device; designed and manufactured by Latitude Technologies
Corporation. This information is intended solely for reference by End Users, Installers, and Application
Developers. Software or hardware changes may have occurred since the printing of this document.
Please contact Latitude Technologies Corporation for the most recent version.
1.2. Acronyms and Abbreviations
CPU Computer
EMI Electromagnetic Interface
LBS Pound
LBS-IN Pound/inch
MB Millibar
VDC Volt DC
OC Degrees Celsius
1.3. Equipment Purpose
The S100 device provides tracking (autonomous and host-polled asset positioning) including
messaging functions using the Iridium satellite network various Short Burst Data (SBD) mode of packet
data transmission.
1.4. Equipment Description
The S100 provides complete tracking and data telemetry in a small and light package.
Figure 1 - SkyNode S100 Tracker

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1.5. Equipment Limitations
Although there is no specific equipment limitation, the installer should refer to the installation
recommendations of Section 4 and the Environmental Qualification Table of Appendix C.
1.6. Safety Precautions
There is no specific safety precaution as such, associated with this equipment.
2. Referenced Documents
a) RTCA DO-160E, Environmental Conditions and Test Procedures for Airborne Equipment,
2004-12-09
b) FAA AC43.13-1B, Acceptable Methods, Techniques, and Practices - Aircraft Alterations,
2008-03-03

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3. SPECIFICATIONS
3.1. Dimensions
See Figure 2 below.
3.2. Electrical Specifications
Power requirement: +12.0 VDC or +28VDC nominal
Input Current: 0.050 A Standby
(at 28VDC) 0.160 A Transmit/Receive (Average)
0.500 A Transmit (Peak)
3.3. Physical Specifications
Length: 6.80 inches (17.3cm)
Width: 4.00 inches (10.2cm)
Height: 1.10 inches (2.8 cm)
Weight: 0.94 lbs (426 g)
Mounting: Any direction. Provide access for visibility of Status Indicators
for Troubleshooting.
Material/Finish: Chassis and cover are 5052-H32 brushed aluminum with black
textured powder coat finish.
Cooling: Convection cooling only. No forced cooling required.
3.4. Environmental Specifications
See Appendix C
3.5. Part Numbers
The following Part Numbers are applicable to this Installation Manual
S100 Tracker P/N S100-001

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3.6. Optional Latitude Kits Part Numbers
The following Optional Part Numbers Kits can be ordered from Latitude Technologies Corp.
The KT006 Kit is comprised of the following parts:
QTY
LATITUDE
PART NUMBER
DESCRIPTION
1
CN054
DB25 Backshell, plastic
25
CN057
DB25-F 22 AWG crimp socket pins, machined, 109 series
1
CN058
DB25-F connector, crimp socket housing, 109 series
1
CN046
SMA plug, straight crimp for RG-400 cable (M39012/55-4502)
1
CN048
TNC, straight, plug, for RG400 cable (M39012/30-0503)
1
550-0101
Ziploc bag, 2" x 3"
1
550-0103
Ziploc bag, 4" x 6"
Table 1- Latitude Technologies KT006 Kit
The KT007 Kit is comprised of the following parts:
QTY
LATITUDE
PART NUMBER
DESCRIPTION
1
CN054
DB25 Backshell, plastic
25
CN057
DB25-F 22 AWG crimp socket pins, machined, 109 series
1
CN058
DB25-F connector, crimp socket housing, 109 series
1
CN047
SMA plug, right angle, crimp for RG-400 cable (M39012/56-
4502)
1
CN049
TNC, right angle, plug, for RG400 cable (M39012/26-0503)
1
550-0101
Ziploc bag, 2" x 3"
1
550-0103
Ziploc bag, 4" x 6"
Table 2 - Latitude Technologies KT007 Kit

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3.7. S100 Dimensions
Dimensions are provided in inches.
Figure 2 - S100 Outline Drawing

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4. Installation
4.1. Introduction
This section provides information regarding the installation of the S100. Close adherence to these
suggestions will assure optimum performance of the system. It is the responsibility of the installer to
design the installation on or within the limits specified in this manual. The installation approval by the
relevant certification authority is the responsibility of the installer.
4.2. Unpacking
Following verification of shipping documents, move the case to a clean area. Remove packing material
and keep ready. Remove the unit carefully and place it on a flat clean surface. Verify that the part and
serial numbers on the shipping invoice matches the part and serial numbers on the unit label. In case
of mismatch, contact Latitude Technologies for details. Perform a visual inspection of the unit to
ensure that it was not damaged during shipment. If you ordered the installation kit ensure that all
connectors are in the package.
4.3. Airworthiness Integrity-Design Considerations
It is mandatory that, during the design of the installation airworthiness, considerations be taken into
account as to not change the airworthiness integrity of the aircraft being modified. Special attention
should therefore be taken in the following areas:
4.3.1.Cable Routing
While installing the additional wiring required for integrating the system into the aircraft it is important
that the existing cable routing and system separation established by the aircraft OEM be respected and
remain unchanged.
4.3.2.Grounding
While installing the additional wiring and grounds required to integrate the system into the aircraft it is
important to install grounding point at proper locations. If existing grounding point are to be used
ensure that the number of grounds on that location is not exceeded and always follow the aircraft OEM
Maintenance Manual guide. Always attach the power ground for this system to grounds designated or
used by the OEM as DC Grounds (as opposed to AC or shields or signal grounds). It is highly
recommended to bring the power ground to a DC ground in close proximity to the circuit breaker that
feeds the S100.(See Appendix A)
4.3.3.Wiring Integrity
Ensure you follow the guidelines of this Installation Manual as to the size and quality of the wiring and
associated components. Any deviation may require more data and analysis from the local approval
authority for the modifications required to install the S100. (See Appendix A). Ensure that all added
wiring is clamped in accordance with FAA AC43.13-1B, Chapter 11.

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4.3.4.Coax Cables
The length of the coaxial cables to both the GPS and Iridium antennas (or combination) is paramount to
the performance of the S100 system. Both should be kept to a strict minimum, and this factor should be
taken into consideration when planning the installation.
4.3.5.Antenna(s) location
The antenna(s) should be located with an unobstructed view of the sky when the aircraft is in level
flight. Any obstruction will reduce the system capabilities. On helicopters, and if possible, avoid
installation of the antennas under the rotor. Although, many “under the rotor” installations have proven
satisfactory, it is also best to keep the antenna(s) as horizontal as possible in relation to the standard
line of flight.
4.3.6.S100 location
The S100 can be located anywhere in the airframe as long as the location is compatible with the
Environment that the S100 was qualified to (See Appendix C). It is also mandatory that the S100 be
installed so that the side of the unit that shows the status lights can be accessible on the ground, with
power “ON”, for maintenance and troubleshooting.
4.3.7.Testing
The installation of the S100 does require ground testing. The guidelines for such tests are outlined in
Section 6.0 of this Installation Manual.
4.3.8.General Guidelines for Installation
When installing the S100, follow the guidelines provided in the following document and the correct
Chapter and Section as appropriate for the installation performed:
FAA AC43.13-1B, Chapter 11
4.4. S100 Installation
4.4.1. Mounting
The S100 may be mounted in any orientation. The S100 is designed to be hard mounted using four #8
or #10 screws and associated waved (lock) washers. No shock mounts are necessary unless the unit
is mounted outside the vibration limits outlined in Appendix C.
4.4.2.Grounding and Bonding
The S100 is bonded to the airframe through pin connections. There is no need for special bonding
requirements.

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4.4.3.Interfaces
Note: For electrical Characteristics see Appendix A
4.4.3.1 Discrete Inputs
Function
Port Name
Pin #
IO-1 IN
P1
8
IO-2 IN
P1
21
IO-3 IN
P1
22
IO-4 IN
P1
23
IO-5 IN
P1
24
IO-6 IN
P1
25
Table 3 - S100 Input Interface
The S100 has 6 discrete inputs that, when configured, can be used to trigger events or alter the
device’s behaviour. For example, one input could be configured as an emergency or “mayday” switch;
when asserted the S100 would send an emergency message and begin sending position reports every
10 seconds. Another input could be configured to disable flight following while asserted. They can also
be configured to trigger position messages for specific events such as “Down & Clear,” “Mark Target,”
“Weight On/Off Wheels” (when wired to a squat switch), “Engine On/Off” (when connected to the
engine hours meter), or many other possibilities.
Configuring discrete inputs is done remotely by Latitude Technologies Corporation; for assistance, call
[phone] and ask for technical support.
Discrete inputs have the following possible states:
Asserted (“On”) Input is connect to aircraft ground
Deasserted (“Off”) Input is “floating” (open circuit)
NOTE: Voltage should NEVER be applied to a discrete input on the S100. Doing so will cause damage
to the device.
4.4.3.2 Discrete Output
Function
Port Name
Pin #
OUT1
P1
13
Table 4 - S100 Output Interface
The S100 has one fused discrete output that can be used for driving a low current load at the same
S100’s supply voltage.
An example application of this function is simple signaling; when configured, the discrete output can be
turned-on by sending a message from a Web Sentinel account. For example, if the output is wired to a
light in the flight deck, a ground dispatcher could send a message to turn-on the light; when the pilot

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sees the light, they can press an “Acknowledge” button (wired into a properly configured discrete input;
see Section 4.4.3.1) to turn-off the light and send an “acknowledged” message back to dispatch.
Configuring the discrete output is done remotely by Latitude Technologies Corporation; for assistance,
call [phone] and ask for technical support.
4.4.3.3 RS-232
Function
Port Name
Pin #
RX_AUX
P1
1
TX_AUX
P1
3
RTS_AUX
P1
15
CTS_AUX
P1
14
Signal GND
P1
2
GPS_IN
P1
17
GPS_OUT
P1
4
Signal GND
P1
16
RX
P2
2
TX
P2
3
DSR
P2
6
DTR
P2
4
RTS
P2
7
CTS
P2
8
GND
P2
5
Table 5 - S100 RS-232 Interface.
The S100 has 3 sets of RS-232 lines for communication. The main RS-232 port is P2, the DB9 9-pin
serial port on the front of the device; this port outputs all the debug information and can also be used
with Latitude API devices. This is also the port used for upgrading the S100’s firmware.
Port setting for P2:
Baud 19200 (for upgrading firmware, use 57600)
Data Bits 8 bit
Parity None
Stop Bits 1 bit
Flow Control None
There is an auxiliary RS-232 port available on P1; with select firmware versions, this is can be also be
used to output debug data or communicate with Latitude API devices, but not for upgrading firmware.
Port settings are the same as for P2.
P1 also contains a GPS RS-232 port; this can be set to either output a stream of raw position data from
the internal GPS module, or accept GPS position data from an external source to be used instead of
the internal module.
Port setting for the GPS In/Out port:
Baud 9600
Data Bits 8 bit

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Parity None
Stop Bits 1 bit
Flow Control None
Specification NMEA0183
NOTE: Serial ground lines should be connected through the S100; do not connect serial ground lines
directly to the airframe ground.
4.4.3.4 Analog Inputs
Function
Port Name
Pin #
AIN1_IN
P1
18
AIN2_IN
P1
6
AIN3_IN
P1
19
Table 6 - S100 Analog Input Interface
The S100 has 3 analog inputs that can be used with some firmware versions to measure analog
voltage levels and trigger events at specific values. For example, the S100 can be configured to read
values from a strain-gauge sensor connected to one of the analog inputs and send a message when
the weight decreases a certain amount (i.e., if the aircraft releases a load).
The analog inputs can measure DC voltage levels from ~0V to +28V.
You may be required to change the firmware version on your S100 in order to use the analog inputs;
call Latitude Technologies at [phone] and ask for technical support.
4.4.4.Antennas
The following antennas are known to be compatible with the S100.
4.4.4.1 Combined Iridium/GPS Antenna
Latitude
P/N
Manufacture’s P/N
Description
MD006
S5GIR1516RR-A2P-XTT-1
or
5G1516RR-A2P-XTT-1
Antcom Dual Iridium/GPS antenna. TNC jacks, active
GPS LNA 20dB, white.
MD007
S5GIR1516RR-AP-XTT-1
or
5G1516RR-AP-XTT-1
Antcom Dual Iridium/GPS antenna. TNC jacks, active
GPS LNA 33dB, white.
MD020
S5GIR1516RR-AP-XTT-4
or
5G1516RR-AP-XTT-4
Antcom Dual Iridium/GPS antenna. TNC jacks, active
GPS LNA 33dB, black.
Table 7 - Combined Iridium/GPS Antenna Part Numbers

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4.4.4.2 GPS Antenna
Latitude
P/N
Manufacture’s P/N
Description
MD019
3G15A2-XT-1
Antcom GPS Antenna 3.5" dia, active LNA 20dB, white
MD24
S67-1575-109
Sensor Systems antenna, 3.5” dia, passive GPS antenna,
TNC jack, white.
Table 8 - GPS Antenna Part Numbers
4.4.4.3 Iridium Antenna
Latitude
P/N
Manufacture’s P/N
Description
MD015
S3IR16RR-P-XTB-1
Antcom Iridium Antenna 3.5" dia, white
MD24
S67-1575-109
Sensor Systems antenna, 3.5” dia, Iridium antenna, TNC
jack, white.
MD022
S67-1575-165
Sensor Systems dual Iridium/Iridium (or passive GPS)
antenna, TNC jacks, white.
Table 9 - Iridium Antenna Part Numbers

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5. Operation
5.1. Configuration Set-up
All S100 units are factory pre-configured to standard default settings. However, should the need arise
to modify them, the following steps describe how to use the menu to view and configure the reporting
parameters of the S100 device.
Diagnostic test routines are also available in the menu and are described in Section 5.2. System Check
& Diagnosis. It is highly recommended that all changes be double checked and verified whenever
changes are made.
To determine what firmware version is currently installed and the unit’s serial number power up the
S100 and observe the serial port data output display. This screen is only displayed on power up, and
lasts about 15 seconds while system initialization is performed. Communication settings are 19200, 8,
N, 1.
Figure 3 - S100 Startup Screen
Upon completion of the startup initialization process, if the user wishes to enter the system Menu, they
should press any key on the keyboard except <ESC>. If the user presses <ESC> or does not press
any key for 15 seconds, the S100 will enter its normal program mode.
If the user enters the menu, the following screen will appear.

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Figure 4 - S100 Terminal Menu
The lower half of the screenshot above shows the options that the S100 Menu provides. Each of the
options shown can be accessed by pressing the number or letter to the immediate left of the option
(e.g. Press ‘2’ to Enter a new GPS Interval).
Immediately above the options are the current settings of the S100. Accessing any of the provided
Menu options will result in explicit instructions on how the option is used.
The following sections provide a brief description of what the modifiable settings indicate.
5.1.1. Edit GPS Interval
The GPS Interval is the length of time between the S100’s processing and storing of a GPS position.
The setting is provided in seconds. Note –this value cannot be set to a greater value than the
Scheduled Report Interval.
5.1.2. Edit Connection Interval
The Connection Interval is the length of time between regularly scheduled transmissions of GPS data.
This setting is provided in seconds. Note –this value must be a multiple of GPS Intervals and must be
greater than the configured GPS Interval. (e.g. If the GPS Interval is 60 s, the Scheduled Report
Interval can be 60s, 120s, 180s, etc.).

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5.1.3. View/Reset Message Log
The Message Log contains all relevant position messages that have been stored locally. There are two
operations that can be performed on the position message log: viewing and clearing. Viewing the
messages will display all logged position messages that have not been transmitted successfully.
Deleting (Resetting) the log will clear any untransmitted position messages. Deleting the log cannot be
undone. The user should verify that this operation is required before performing it.
5.2. System Check and Diagnosis
There are three internal diagnostic checks (Test Satcom, Test GPS, Test Mainboard) that can be
performed on the S100. Accessing the appropriate menu option will begin these internal self-tests.

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6. Post Installation Testing
The following test must be performed after each installation. This test is to ensure system functionality
as well as EMI compatibility with existing aircraft systems.
6.1. Pre-Test
TEST
CHECK
Verify that each component of the installed system is
properly installed and properly fastened.
Verify that primary power connections have no short
circuit in the input power wiring.
Verify that all electrical connectors are properly
mated and tightened.
With the system ON, check illumination of all three
green LED’s
Pull the Circuit Breaker and ensure that all LED’s are
off on the S100.
Table 10 - Pre-Test Checklist
6.2. Functional Test-No Engine
This test requires a facility to monitor the availability of the aircraft on the Latitude web site. Prior to
performing this test an account must have been established with Latitude. Communication with the
person monitoring the web site is required.
TEST
CHECK
NOTES
With the aircraft outside, ensure proper
communication with the person monitoring the web
site. (Web Sentinel). Also ensure that the three
Green lights are ON prior to check.
Verify that position, speed (0) and altitude details are
accurate to the current aircraft situation as seen on
Web Sentinel.
Table 11 - Functional Test-No Engine Checklist
Note: LAT on Web Sentinel _____________________________
LONG on Web Sentinel____________________________
Altitude on Web Sentinel ___________________________