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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: (250) 475-0203 Fax: (250) 475-0204

Email: [email protected]

SkyNode® S100 Installation and Operation Manual

Page 2 of 32 S100-400, R2.01

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


Page 3 of 32 S100-400, R2.01

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.


Page 4 of 32 S100-400, R2.01

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 +1 (250) 475-0203 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


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


Page 14 of 32 S100-400, R2.01

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 +1 (250) 475-0203 and ask for technical support.

4.4.3.3 RS-232


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


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 +1 (250) 475-0203 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


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


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 . If the user presses 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 ___________________________


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6.3. Functional and EMI Test- Engine(s) running 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. This test is to be performed with the engine running, away from any building or structure.

TEST NOTES

With the aircraft outside, prior to engine(s) start, ensure to have visual access to the S100 indicator lights throughout the EMI testing including engine run.

Turn power “ON” to the aircraft and the S100. Ensure that the GPS input light (bottom of three) stops blinking prior to commencing the EMI tests.

Start the engine(s)

Turn all electrical and electronic equipment on the aircraft (Landing Lights, Taxi Lights, Blowers, XPDR, ADF, GPS, etc.). While performing the tests below, ensure that there is no noticeable disturbance in any of those systems.

Transmit on the following frequency, for 10 seconds while modulating (5,4,3, ...) on the No. 1 Com and, ensure that there is no “blinking” of the GPS light on the S100 for any of those transmitted frequencies: 121.12, 121.17, 121.22, 121.25, 131.20, 131.25, 131.30, 131.35 MHz Monitor all other instruments while performing this test.

Repeat above test on all COMS.

Turn the aircraft 90 Degrees Heading and repeat the tests above. Ensure that there is no “blinking” of the GPS light on the S100 for any of those transmitted frequencies: Monitor all other instruments while performing this test.

Transmit on any other installed Communication equipment on at least one frequency, and, ensure that there is no “blinking” of the GPS light on the S100.

Table 12 - Functional Test Checklist


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7. Troubleshooting

7.1. LED Blink Pattern Description

The S100 is equipped with three LEDs (light emitting diodes) located on the front panel, that can be used for visual troubleshooting. The top LED (“SAT”) provides information about the status of the SATCOM link. The middle LED (“SYS”) provides feedback about the state of the S100 (operational mode). The bottom LED (“GPS”) provides information about the health of the GPS link.

7.1.1. LED Patterns during Startup On startup, the system will enter its internal system check. During this time the system will cycle through the LEDs from top to bottom twice. Provided that all internal system diagnostics pass the SYS light will turn on and remain on solid.

7.1.2. LED Patterns during Regular Operation

Under normal operating conditions all three LEDs should be on solid. Other patterns that can be viewed: GPS LED blinks (1 second ON, 1 second OFF): No GPS satellite fix SAT LED blinks (1 second ON, 1 second OFF): No Iridium network, or SAT is not registered SAT LED blinks (2 seconds ON, 2 seconds OFF): System is in PassThru mode SYS LED blinks rapidly (200ms ON, 200ms OFF): System is in Emergency mode


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APPENDIX A- CONNECTOR PIN ASSINGMENTS

P1 (25 pin male D-sub):

Pin Name Type Function Range

1 RX AUX RS232 input Auxiliary serial data receive ±15 VDC

2 GND Ground Signal Ground return 0 VDC

3 TX AUX RS232 output Auxiliary serial data transmit ±5 VDC

4 GPS OUT RS232 output NMEA 0183 serial data transmit ±5 VDC


6 AIN2 IN Analog input As defined by application firmware

0 to +12 VDC (max 18 VDC)


8 IO-1 IN Discrete input As defined by application firmware

0 to +3.3 VDC (max)

9 GND Ground Power Ground return 0 VDC

10 BCKUP IN Aux Power input Backup Battery input (Optional)

+9 to + 36 VDC

11 PWR IN Power input Power Supply input +9 to + 36 VDC

12 5V OUT Power output Auxiliary Power Supply output (fused)

+5 VDC, Max 0.5A

13 OUT1 Discrete output Digital (full VDC) Output 0 to Vin, Max 150mA @ 12VDC

14 CTS AUX RS232 input Auxiliary serial data signal ±15 VDC

15 RTS AUX RS232 output Auxiliary serial data signal ±5 VDC


17 GPS IN RS232 input NMEA 0183 serial data receive (alternate GPS source input)

±15 VDC





20 V SENSE Analog input Voltage Sense input 0 to +12 VDC (max 33 VDC)

21 IO-2 IN Discrete input *As defined by application firmware

0 VDC to +3.3 VDC (max)




0 to +3.3 VDC (max)




0 to +3.3 VDC (max)

Table 13 - S100 Main Connector (P1) Pin Assignments

* Typical operation of discrete input is to sense either a Ground contact (0 VDC = logic LO) condition, or a open line condition (+3.3VDC = logic HI). The latter is due to internal weak pull-up resistors on all input lines. All interfaces except those in Bold are optional or for information only.


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P2 (9 pin female D-sub):

Pin Name Type Function Range 1 CD RS232 output Serial data signal ±5 VDC

2 RX RS232 output DCE serial data transmit ±5 VDC

3 TX RS232 input DCE serial data receive ±15 VDC

4 DTR RS232 input Serial data signal ±15 VDC


6 DSR RS232 output Serial data signal ±5 VDC

7 RTS RS232 input Serial data signal ±15 VDC

8 CTS RS232 output Serial data signal ±5 VDC

9 RI / +5V * RS232 output * Serial data signal * ±5 VDC

* Factory option to set P2, Pin 9 to a fixed +5V, 100mA supply.

Table 14 - S100 P2 Pin Assignments.

GPS (SMA female):

Impedance 50 Ohm

RF input frequency 1575 MHz

RF Input Level -130 dBW and –163 dBW

Active bias voltage +3 Vdc

Active Bias Current Maximum 70 mA (center conductor)

Table 15 - GPS Connector

SAT (TNC female):

Impedance 50 Ohm

Frequency 1616 MHz – 1625 MHz

RF transmit power 7W max per slot, Average 0.6W per frame typical

RF receive sensitivity -118.5 dBm

Table 16 - SAT Connector


Page 25 of 32 S100-400, R2.01

APPENDIX B- INTERCONNECT INTERFACES


Page 26 of 32 S100-400, R2.01

TABLE B1 –WIRING INSTALLATION NOTES

ITEM PART NUMBER or EXPLANATION

DENOTES COAX CONNECTOR (SMA OR TNC)

Single Wires ALL WIRES PER AWG22 UNLESS OTHERWISE SPECIFIED, M22759/41-22-9 OR EQUIVALENT

Connector P1 DB25

Connector P2 DB9

GPS Antenna Connector

M39012/30-0503 (Straight) or M39012/20-0007 (90°)

Iridium Antenna Connector

M39012/30-0503 (Straight) or M39012/20-0007 (90°)

RECOMMENDED CIRCUIT BREAKERS 2 OR 3 AMPS MS22073-3 OR MS26574-3


Page 27 of 32 S100-400, R2.01

TABLE B2 –IRIDIUM COAX CABLES CHART

PIC= PIC WIRE AND CABLE, N53W24747 S. Corporate Circle, P.O. Box 330, Sussex, WI, 53089-0330, Ph. 262-246-0500 ECS= ECS 5300 W. Franklin Drive Franklin, WI 53132 USA Ph: 414.421.5300 or 800.327.9473

Max. Cable length (feet)

Coaxial Cable Type or supplier (see below)

P/N Cable OD (inches)

Min. Bend Radius (inches)

Matching Connectors

TNC- male straight plug (P/N)

TNC- male 90° plug (P/N)

≤ 10 MIL-C-17 RG400 0.195 1.00 M39012/30-0503 M39012/20-0007

≤ 12 MIL-C-17 RG400 0.195 1.00 M39012/30-0503 M39012/20-0007

≤ 12 MIL-C-17 RG142 0.195 1.00 M39012/30-0503 M39012/20-0007

≤ 12 PIC S44191 0.195 1.00 190108 190109

≤ 15 ECS 311901 0.195 1.00 CTS722 CTR722

≤ 20 ECS 311601 0.229 1.15 CTS922 CTR922, CTRE922 (extended), CTRL922 (long)

≤ 25 ECS 311501 0.229 1.20 CTS922 CTR922, CTRE922 (extended), CTRL922 (long)

≤ 25 PIC S33141 0.270 1.40 190308 190309

≤ 30 ECS 311201 0.317 1.59 CTS122 CTR122

≤ 40 PIC S22089 0.435 2.50 190408 190409

≤ 50 ECS 310801 0.452 2.26 CTS022 CTR022


Page 28 of 32 S100-400, R2.01

TABLE B3 –GPS COAX CABLES CHART

Cable length (feet)

Coaxial Cable Type

P/N Cable OD (inches)

Min. Bend Radius (inches)

Matching Connectors

TNC- male straight plug (P/N)

TNC- male RA plug (P/N)

5 MIL-C-17/113 RG316 0.098 0.50 M39012/55-4502 M39012/56-4502 10 MIL-C-17/113 RG316 0.098 0.50 M39012/55-4502 M39012/56-4502 15 MIL-C-17/113 RG142 0.195 1.00 M39012/55-4502 M39012/56-4502 15 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 20 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 25 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 30 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 40 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 50 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 60 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502 70 MIL-C-17/128 RG400 0.195 1.00 M39012/55-4502 M39012/56-4502


Page 29 of 32 S100-400, R2.01

Figure B1 – Typical Wiring Installation

COMBINED GPS/IRIDIUM

ANTENNA

GPS ANTENNA

IRIDIUM ANTENNA

Skynode® S100 Installation and Operation Manual

Page 30 of 32 S100-400, R2.01

APPENDIX C- ENVIRONMENTAL TESTS TABLE


Page 31 of 32 S100-400, R2.01

TABLE C1 – ENVIRONMENTAL TESTS TABLE

NOMENCLATURE: SKYNODE S100 ______ TYPE/MODEL/PART NO: S100-001 TSO NUMBER: N/A MANUFACTURER’S SPECIFICATION AND/OR OTHER APPLICABLE SPECIFICATION: N/A MANUFACTURER: LATITUDE TECHNOLOGIES CORPORATION ADDRESS: 101-3375 Whittier Ave Victoria, BC, Canada, V8Z-3R1 REVISION & CHANGE NUMBER OF DO-160E: DATES TESTED: February-March 2007 and July 2010

Condition Section Description of tests conducted

Temperature and Altitude Low Temperature Ground Survival Low Temperature Short Time Low Temperature High Temperature Ground Survival High Temperature Short Time High Temperature Altitude Decompression Overpressure

4.0 4.5.2 4.5.1 4.5.1 4.5.4 4.5.3 4.5.3 4.6.1 4.6.2 4.6.3

Equipment tested to Categories A4 Operating: -40

oC

Non-Operating: -55oC

Operating: -40oC

Operating: +60oC

Short time high temperature: +85oC

Operating: +60oC

50,000 feet 8000 feet to 50000 feet -15000 feet

Temperature Variation 5.0 Equipment tested to Category B +/- 5

oC/min.

Humidity 6.0 Equipment tested to Category A 95% RH for 48 Hours

Operational Shock and Crash Safety Operational Shock Crash Safety

7.0 7.2.1 7.3.1

Equipment tested to Category B 6 G for 11ms in all axes 20 G for 11ms in all axes

Vibration 8.0 8.5.1 8.8.3

Equipment tested to Categories SM and U2FF1 Sinusoidal: 0.1” from 5 to 15 Hz 0.01” from 15 to 55 Hz 1.5G from 55 to 500 Hz Unknown Helicopter Frequencies Vibration Profile F- Random Vibration Profile F1-Random

Explosion 9.0 Equipment identified as Category X, no test performed

Waterproofness 10.0 Equipment identified as Category X, no test performed

Fluids Susceptibility 11.0 Equipment identified as Category X, no test performed

Sand and Dust 12.0 Equipment identified as Category X, no test performed

Fungus 13.0 Equipment identified as Category X, no test performed

Salt Spray 14.0 Equipment identified as Category X, no test performed

Magnetic Effect 15.0 Equipment tested to Category Z


Page 32 of 32 S100-400, R2.01

Condition Section Description of tests conducted

Power Input 16.0 Equipment tested to Category B Tests performed for both 14VDC and 28VDC systems

Voltage spike 17.0 Equipment tested to Category B 56Vpk for 10µs

Audio Frequency Susceptibility 18.0 Equipment identified as Category X, no test performed

Induced Signal Susceptibility 19.0 Equipment identified as Category X, no test performed

Radio Frequency Susceptibility 20.0 Equipment identified as Category X, no test

performed

Emission of Radio Frequency Energy 21.0 Equipment tested to Category B

Lightning Induced Transient Susceptibility 22.0 Equipment identified as Category X, no test

performed

Lightning Direct Effects 23.0 Equipment identified as Category X, no test

performed

Icing 24.0 Equipment identified as Category X, no test

performed

Electrostatic Discharge 25.0 Equipment identified as Category X, no test

performed

Fire, Flammability 26.0 Equipment identified as Category X, no test

performed

Table 17 - Environmental Qualification Table