Data Transmission Unit - TurbineTracker · Release Date: Ju ly 31 ,2 07 M i er a ngof H rdw re En...

Pratt & Whitney Engine Services, Inc.249 Vanderbilt Ave.Norwood, MA 02062

249 Vanderbilt Ave., Norwood, MA 02062, Phone 781-762-8600, Fax 781-762-2287

Data Transmission UnitInstallation InstructionsDTU-G-010-7

For Dassault Aviation Falcon 2000EX

Manual Number: DTU-G-010-7

Preparation Date: May 28, 2007 Prepared By: D Elsemiller

Release Date: July 31, 2007 J Miller, Manager of Hardware Engineering

Revision Date: August 24, 2011 S Sackos, Manager of Manufacturing

Revision Ltr: E

Pages: 50

P&W ENGINE SERVICES, INC. Data Transmission Unit DTU-G-010-7Dassault Aviation Model Falcon 2000EX

DTU-G-010-7 Pratt & Whitney Engine Services, Inc. Proprietary i

PREFACE

Proprietary Information Notice

This manual contains proprietary information that is protected by copyright, and all rights are reserved. No portion of thisdocument may be copied, photocopied, reproduced by any means, or translated into another language without the priorwritten permission of Pratt & Whitney Engine Services, Inc.


DTU-G-010-7 Pratt & Whitney Engine Services, Inc. Proprietary ii

REVISION HISTORY

Rev B E C C B B B B B B C B BRev Statusof Sheets Sheet i ii iii iv 1 2 3 4 5 6 7 8 9

Rev B B D C C C C C C C D C CSheet 10 11 12 13 14 15 16 17 18 19 20 21 22Rev C C C C C C C E C C C C CSheet 23 24 25 26 27 28 29 30 31 32 33 34 35Rev C D D D C C C C C C C C CSheet 36 37 38 39 40 41 42 43 44 45 46 47 48Rev C CSheet 49 50

LOG OF REVISIONS

REV. NO ECO # DESCRIPTION DATE PAGES REVISED

A N/A Initial Release 07/31/2007 N/A

B 954 Updated company name, address and logo.Added wire numbers to connection chart.Updated format. Corrected spelling and

grammar. Removed warranty information.

04/09/2008 All

C 999 Updated circuit breaker and wire routinginstructions. Updated Parts List. Updatedwiring schematic. Correct typographical

errors.

05/26/2009 Cover, ii – iv, 7, 13 – 50

D 1020 Update GSM Antenna InstallationInstructions and Notes. Update Comm

Port wiring in Schematic.

03/01/2010 Cover, ii, 12, 20, 37, 38,39

E 1093 Correct Typographical Error (from 2 AmpCB to 1 Amp CB)

08/24/2011 Cover, ii, 30

Note: If the DTU Installation Instructions are revised, all operators will be provided with a copy of theapplicable revision. If you have a subscription with TurbineTracker, you will be informed viaemail of new revisions to this manual. In addition to this, P&W Engine Services maintains thelatest versions of all manuals in the Support Section of TurbineTracker.

If you are not a subscriber to TurbineTracker, you may call P&W Engine Services CustomerSupport at 781-762-8600 for the latest revision.


DTU-G-010-7 Pratt & Whitney Engine Services, Inc. Proprietary iii

TABLE OF CONTENTS

1 INTRODUCTION ........................................................................................................................................... 1

1.1 DTU GENERAL DESCRIPTION............................................................................................................................. 11.2 SCOPE ................................................................................................................................................................ 11.3 ABOUT THIS MANUAL........................................................................................................................................ 21.4 SYSTEM DESCRIPTION........................................................................................................................................ 21.5 UNPACKING THE EQUIPMENT ............................................................................................................................. 31.6 PARTS LIST ........................................................................................................................................................ 31.7 WEIGHT AND BALANCE...................................................................................................................................... 3

2 INSTALLATION AND MAINTENANCE PROCEDURES ....................................................................... 4

2.1 STANDARD PRACTICES-AIRFRAME/POWERPLANT.............................................................................................. 42.1.1 Procedure for Wiring Connections .................................................................................................................... 42.1.2 Wiring Splices.................................................................................................................................................... 52.1.3 Maintenance ...................................................................................................................................................... 6

2.2 PARTS LIST ........................................................................................................................................................ 62.2.1 DTU by Parts Kits.............................................................................................................................................. 62.2.2 Components by Kit............................................................................................................................................. 6

3 INSTALLATION – MECHANICAL & ELECTRICAL ............................................................................. 8

3.1 SYSTEM PROCESSOR MOUNTING........................................................................................................................ 83.2 DTU RF SWITCH AND COMMUNICATIONS PORT .............................................................................................. 123.3 ANTENNA MOUNTING ...................................................................................................................................... 123.4 HARNESS INSTALLATION.................................................................................................................................. 13

3.4.1 J1 Harness Installation .................................................................................................................................... 133.4.2 GSM Antenna Cable Installation ..................................................................................................................... 15

3.5 SHORTING PLUG INSTALLATION....................................................................................................................... 163.5.1 Circuit Breaker Installation ............................................................................................................................. 17

4 HARNESS CONNECTOR SIGNAL PINOUTS......................................................................................... 18

4.1 ACS CABLE J1, 37 PIN “A” KEYED CONNECTOR ............................................................................................. 18

5 WIRING DIAGRAM .................................................................................................................................... 20

5.1 DTU – INTERCONNECT SCHEMATIC ................................................................................................................. 20

6 SYSTEM OPERATION OVERVIEW ........................................................................................................ 21

6.1 DTU FUNCTIONAL DESCRIPTION ..................................................................................................................... 216.1.1 Initialization..................................................................................................................................................... 21

7 SYSTEM CONFIGURATION ..................................................................................................................... 22

7.1 DEFINITIONS .................................................................................................................................................... 227.2 PROCESSOR CONFIGURATION........................................................................................................................... 22

8 AIRCRAFT TESTING ................................................................................................................................. 23

8.1 AIRCRAFT GROUND TEST................................................................................................................................. 238.1.1 Engine(s) Running: .......................................................................................................................................... 24

9 SERVICE ....................................................................................................................................................... 27

10 SPECIFICATIONS ....................................................................................................................................... 28

10.1 SYSTEM SPECIFICATIONS ................................................................................................................................. 2810.2 INTERFACE REQUIREMENTS FOR AIRCRAFT SENSORS ...................................................................................... 30

11 APPENDIX A ................................................................................................................................................ 31

11.1 DTU INSTALLATION......................................................................................................................................... 31


DTU-G-010-7 Pratt & Whitney Engine Services, Inc. Proprietary iv

11.2 GSM ANTENNA INSTALLATION ....................................................................................................................... 3711.3 CIRCUIT BREAKER INSTALLATION ................................................................................................................... 4011.4 SHORTING PLUG INSTALLATION....................................................................................................................... 4311.5 DTU WIRE ROUTING ....................................................................................................................................... 46

LIST OF FIGURESFIGURE 1: DTU SIMPLIFIED BLOCK DIAGRAM ......................................................................................................................... 1FIGURE 2: DATA TRANSMISSION UNIT (DTU) .......................................................................................................................... 2FIGURE 3: SINGLE OR DUAL WIRE SPLICES .............................................................................................................................. 5FIGURE 4: SHIELDED CONNECTION (OUTER HEAT-SHRINK TUBING NOT SHOWN) ................................................................... 5FIGURE 5: DTU PROCESSOR..................................................................................................................................................... 8FIGURE 6: BAGGAGE COMPARTMENT (VIEW LOOKING FWD) ................................................................................................. 8FIGURE 7: BRACKET ASSEMBLY WITH DOWNLOAD PORT, RF SWITCH, AND SHOCK MOUNTS ............................................... 10FIGURE 8: DOWNLOAD AND RF SWITCH CABLES SECURED.................................................................................................... 10FIGURE 9: DTU MOUNTING BRACKET (ADHY-026-1) .......................................................................................................... 11FIGURE 10: DTU MOUNTING LOCATION (VIEW LOOKING FWD)........................................................................................... 11FIGURE 11: GSM ANTENNA ................................................................................................................................................... 12FIGURE 12: GSM ANTENNA LOCATION.................................................................................................................................. 13FIGURE 13: GSM ANTENNA INSTALLATION ........................................................................................................................... 13FIGURE 14: AIRFRAME GROUND LOCATION (VIEW LOOKING STARBOARD) ........................................................................... 14FIGURE 15: FEED-THRU 751FT AND SPR 708 WIRING LOOM .................................................................................................. 15FIGURE 16: RH RADIO RACK ................................................................................................................................................. 15FIGURE 17: DTU SHORTING PLUG LOCATION ........................................................................................................................ 16FIGURE 18: DTU CIRCUIT BREAKER INSTALLED.................................................................................................................... 17FIGURE 19: DTU WIRING SCHEMATIC ................................................................................................................................... 20FIGURE 20: DTU RF SWITCH ................................................................................................................................................. 21FIGURE 21: DTU DATA RETRIEVAL MESSAGES ..................................................................................................................... 25FIGURE 22: DTU DATA TRANSMISSION MESSAGES ............................................................................................................... 25FIGURE 23: DTU DATA FLASH ERASED MESSAGES ............................................................................................................... 25

LIST OF TABLESTABLE 1: VHF FREQUENCY TABLE ....................................................................................................................................... 24TABLE 2: ELECTROMAGNETIC COMPATIBILITY TEST TABLE ................................................................................................. 26

APPENDIX AFIGURE A- 1: DTU INSTALLATION – SHEET 1 OF 6 ................................................................................................................. 31FIGURE A- 2: DTU INSTALLATION – SHEET 2 OF 6 ................................................................................................................. 32FIGURE A- 3: DTU INSTALLATION – SHEET 3 OF 6 ................................................................................................................. 33FIGURE A- 4: DTU INSTALLATION – SHEET 4 OF 6 ................................................................................................................. 34FIGURE A- 5: DTU INSTALLATION – SHEET 5 OF 6 ................................................................................................................. 35FIGURE A- 6: DTU INSTALLATION – SHEET 6 OF 6 ................................................................................................................. 36FIGURE A- 7: GSM ANTENNA INSTALLATION – SHEET 1 OF 3 ................................................................................................ 37FIGURE A- 8: GSM ANTENNA INSTALLATION – SHEET 2 OF 3 ................................................................................................ 38FIGURE A- 9: GSM ANTENNA INSTALLATION – SHEET 3 OF 3 ................................................................................................ 39FIGURE A- 10: CIRCUIT BREAKER INSTALLATION – SHEET 1 OF 3 .......................................................................................... 40FIGURE A- 11: CIRCUIT BREAKER INSTALLATION – SHEET 2 OF 3 .......................................................................................... 41FIGURE A- 12: CIRCUIT BREAKER INSTALLATION – SHEET 3 OF 3 .......................................................................................... 42FIGURE A- 13: SHORTING PLUG INSTALLATION – SHEET 1 OF 3 ............................................................................................. 43FIGURE A- 14: SHORTING PLUG INSTALLATION – SHEET 2 OF 3 ............................................................................................. 44FIGURE A- 15: SHORTING PLUG INSTALLATION – SHEET 3 OF 3 ............................................................................................. 45FIGURE A- 16: DTU WIRE ROUTING – SHEET 1 OF 5 .............................................................................................................. 46FIGURE A- 17: DTU WIRE ROUTING – SHEET 2 OF 5 .............................................................................................................. 47FIGURE A- 18: DTU WIRE ROUTING – SHEET 3 OF 5 .............................................................................................................. 48FIGURE A- 19: DTU WIRE ROUTING – SHEET 4 OF 5 .............................................................................................................. 49FIGURE A- 20: DTU WIRE ROUTING – SHEET 5 OF 5 .............................................................................................................. 50


DTU-G-010-7 Pratt & Whitney Engine Services, Inc. Proprietary 1

1 INTRODUCTION

This document contains the installation instructions for an airframe mounted Data Transmission Unit (DTU).The DTU provides two bi-directional data communication portals through which aircraft and engineperformance data can be transmitted, primarily via wireless techniques, to a remote data and application-processing server.

1.1 DTU General Description

A simplified block diagram of the DTU is shown in Figure 1 to clarify its interaction with all of its associatedelements.

Figure 1: DTU Simplified Block Diagram

The primary purpose of the DTU is to provide a portal between the on-aircraft measurement systems and aremote data and application server. This data communication shall typically occur with no human interventionwhen wireless communication is available at the aircraft destination point.

1.2 Scope

The purpose of this document is to provide users of this product with P&W Engine Services approvedinstallation instructions. Any deviation from the procedures described within this document could result in afailure of the product to perform properly and could possibly result in damage to other systems of the aircraft.

These instructions are for the Dassault Falcon 2000EX aircraft associated with the FAA Type Certificate DataSheet No. A50NM.



1.3 About This Manual

This document contains general and specific information regarding mechanical and electrical hardware. In alldocuments, mechanical and electrical sections are made up of instruction lists that take the following form:

1. A heading that lists the applicable aircraft or engine. Headings appear as follows:

2. Cautions present things to be aware of while performing the installation. Cautions appear as follows:

INSTALLATION CAUTION:

Excessive torque on the processor-mounting studs can deform the shock mounts. Thelocking nut should be tightened only to the point of contact with the shock mount.

3. Numbered assembly and wiring instructions, which include boxes for checking off steps as they areperformed. Instructions appear as follows:

Wiring Instructions:

Perform the following steps:

Engines

1 2

010 Trim the cable to length

4. Notes present things that require specific attention to detail. Notes appear as follows:

1.4 System Description

A typical DTU (Figure 2) is depicted as follows:

Figure 2: Data Transmission Unit (DTU)



1.5 Unpacking the Equipment

Carefully remove each component from its original package. Place each component on a roll-away cart orsuitable workbench in the work area.

1.6 Parts List

Care must be taken when handling all parts and equipment. Before opening packages, perform an inventorycheck by comparing the receivables to the appropriate bill of materials.

1.7 Weight and Balance

Calculating weight and balance of the DTU after installation is the responsibility of the installer. Theinformation needed is shown below:

DTU Kit Weight lbs. ArmDTU-K-010-17 2.0 Frame 21 (11161)



2 INSTALLATION AND MAINTENANCE PROCEDURES


Use of any procedure (e.g. addendum) that does not apply to your specific applicationcould cause unnecessary damage to the aircraft and/or result in a system or productmalfunction.

2.1 Standard Practices-Airframe/Powerplant

Prior to installation, be sure that you have read all information contained in the documentation. Review allmanufacturer provided airframe and powerplant documentation in order to understand installation requirementsand technical capability of the system.

NOTE: General wiring supplies (solder, crimp splices, heat shrink, tape, grommets, cable ties and cabletie holders, etc) are not included with the installation kit.

Prior to installation, verify and follow each of the following instructions and guidelines:

1. All work to be done in accordance with FAA Advisory Circular 43.13-1B "Acceptable Methods,Techniques, and Practices for Aircraft Inspection and Repair" and with FAA Advisory Circular 43.13-2A "Acceptable Methods, Techniques and Practices - Aircraft Alterations"

2. All work to be done in accordance with applicable aircraft manufacturer’s standard practices. Refer tothe manufacture’s maintenance manuals for acceptable methods.

3. Read all instructions completely before beginning any installation. Only qualified mechanics oravionics technicians shall perform the installation.

4. All aircraft systems interfacing with the P&W Engine Services DTU must be checked for fullfunctionality before installation begins.

5. All illustrated mounting locations should be used as a general guide for mounting. Locations shown inillustrations may be altered to fit special individual installation requirements as needed, providedaccepted structural procedures and practices are followed.

6. Refer to the manufacturer’s manual for approved locations or cautions for clamping hoses and cables, ormodifying aircraft structure.

2.1.1 Procedure for Wiring Connections


The DTU cables have shields that connect to the processor chassis ground. Whenterminating the shielded harness at the airframe connection, these shields must betrimmed back and insulated to prevent possible shorting with the signal wires.



2.1.2 Wiring Splices

The use of Raychem™ hermetic style wire splices (Figure 3 and Figure 4) is recommended. When makingconnections between two shielded cables, the shields should also be maintained using Raychem™ or equivalentshield splices. The entire cable splice should be encased in heat shrink tubing when completed.

A general procedure for wire splices (See Figure 3 and Figure 4) is illustrated as follows:

RAYCHEM D-436-37

OR EQUIVALENT

Figure 3: Single or Dual Wire Splices

1. INSERT PREPARED CABLE

2. APPLY HEAT

RAYCHEM

S01-04-R

OR EQUIVALENT

3. SPLICE W IRE AND

SHIELD PIGTAIL

Figure 4: Shielded connection (Outer Heat-Shrink Tubing Not Shown)



2.1.3 Maintenance

The P&W Engine Services DTU has been designed with the latest solid-state technology. The only componentthat has a limited life span is the internal battery. This battery, under normal operating conditions, is expected tolast 10 years. If the battery is discharged, the DTU processor must be returned to P&W Engine Services forbattery replacement.

Should you suspect a problem, the unit should be returned to the factory for service.

Care of the processor under normal operation consists of general cleaning and inspection for bracket andconnector security at every major engine or aircraft inspection.

2.2 Parts List

For Dassault Aviation Falcon 2000EX:

The parts listed below consist of the installation kits for the DTU for the Dassault Aviation Falcon 2000EX.Assembly kit numbers are listed in section 2.2.1 and individual components are detailed by kit numbers insection 2.2.2.

2.2.1 DTU by Parts Kits

For Dassault Aviation Falcon 2000EX: Qty DTU-K-010-17

Processor Assembly 1 DTU-K-089-13Harness Kit 1 DTU-K-090-11Antenna Kit 1 DTU-K-092-2Additional Materials Installation Kit 1 DTU-K-093-17

2.2.2 Components by Kit

PROCESSOR ASSEMBLY KIT DTU-K-089-13

Mount, Miniature, Shock ADAS-D-067-1 Qty 4Washer, Processor Mount 920-00006 Qty 4Nut, Locking, Processor Mount MS21042-06 Qty 4Screw, #10-32 x 3/8” MS35207-261 Qty 6Strap, Ground DPU-C-050-1 Qty 1Mounting Bracket ADHY-D-026-1 Qty 1Washer, Flat 3/16” AN960-10 Qty 6Processor, Standalone DTU-A-012-1 Qty 1Nut, Elastic Stop, 10-32 AN365-1032A Qty 1Cover, Receptacle 990-00031 Qty 1Screw, #4-40 x ¼” 900-00003 Qty 1Clamp, Loop, Cush, ¼”, BLK MS21919DG4 Qty 1Assy., Split Lamp ADAS-A-011-1 Qty 1Cap, Lens - White 990-00127 Qty 1Assy., Port Download DPU-A-044-1 Qty 1Grommet Strip MS22529/2-3R-10PK Qty 4”Insert NAS1836-3-09 Qty 6



ENGINE HARNESS KIT DTU-K-090-11

Assembly Harness, J1, ACS, External DTU-C-150-1 Qty 1Cable DTU RF 2X Rt. Angle 1’ DTU-C-084-1 Qty 1

ANTENNA KIT DTU-K-092-2

GSM Antenna DTU-D-094-1 Qty 1Conn, Dust cap, SMA Male 400-00136 Qty 1

ADDITIONAL MATERIAL INSTALLATION KIT DTU-K-093-17

Terminal, Ring #10 400-00030 Qty 3Terminal, Ring #8 400-00139 Qty 3Terminal, Ring #6 400-00029 Qty 2Velcro® 990-00079 Qty 1Breaker, 1 Amp MS3320-1 Qty 1Assembly, Jumper Plug DTU-C-151-1 Qty 224 Gauge Wire M22759/16-24-9 Qty 10’Nut, Elastic Stop, 10-32 AN365-1032A Qty 1Screw, #10-32 x 1/2” MS35207-263 Qty 1Socket Contact M39029/56-351 Qty 8



3 INSTALLATION – MECHANICAL & ELECTRICAL

3.1 System Processor Mounting

NOTE: For Detailed DTU Installation Drawings, Refer to Appendix A, Section 11.1.

The processor (Figure 5) retrieves data (i.e. trends, faults, exceedances) from the Engine Diagnostic Unit (EDU)and transmits the data via cellular technology to TurbineTracker™.

The processor measures 3.7” high by 6.0” long by 2.7” deep and weighs 1.8 lbs. An aluminum bracket withLord Aerospace shock mounts is used to mount the processor to the aircraft.

The DTU is remotely mounted in the baggage compartment behind the lavatory panel (F2MB800838A2) wherethe maintenance connectors are located (Frame 21, Station 11161), as shown in Figure 6. The DTU will notrequire access during normal operation.

Figure 5: DTU Processor


The area chosen must allow full and free movement of any control system cables or tubes.The control mechanisms must be able to operate over their complete range of movement.

If another area is used to mount the DTU, the area must have sufficient structural integrityto support the unit. Sheet metal panels should be a minimum of .025” thick, with materialcomparable or stronger than 2024-T3 aluminum.

The area chosen must be inspected for any evidence of dents, contraction, cracking, anddeterioration of metal. Reference AC 43.13-2A, Chapters 1 & 2 for specific guidelines indetermining a mounting location.

The DTU processor is not certified to be mounted in the engine compartment.

Excessive torque on the processor-mounting studs can deform shock mounts. The lockingnut should be tightened to the point of contact with the shock mount.

Figure 6: Baggage Compartment (View Looking FWD)

MaintenanceConnectors

Lavatory PanelF2MB800838A2



The system processor shall be mounted in accordance with the following procedure:

010 Reference Figure 7 and assemble the download port (DPU-A-044-1), RF Switch (ADAS-A-011-1), andShock Mounts (990-00020) into the processor bracket (ADHY-D-026-1).

020 Secure the Download Port and RF Switch cables with provided clamp (MS21919DG4) and nut(AN365-1032A), as shown in Figure 8.

030 Install male SMA Dust Cap (400-00136) on the DTU LAN connector.

040 Assemble the DTU processor to the mounting bracket shown in Figure 9 and test fit in a proper

location Figure 10 within the aircraft to ensure that the processor does not interfere with wiring orcontrols.

050 When a location has been determined for the DTU, mark the location of the 6 mounting holes and drillto accommodate a potted-in style insert.

060 Remove a ¼ inch of the adjacent core material without damaging the panel skins.

070 Clean out all loose material.

080 Using Dexter / Hysol’s EA934NA epoxy paste adhesive, or equivalent, completely fill each section ofpanel where the honeycomb (core) was removed around the insert.

The requirements for a suitable equivalent paste adhesive are:

1. A pot life long enough to perform the assembly.2. Sag resistance (thixotropic).3. A room temperature cure.4. An adhesive appropriate for aircraft structural metal bonding with mechanical properties equal

to or greater than EA 934NA.

090 With the inserts installed allow the adhesive to cure.

100 Mount the system processor and bracket to the aircraft using the provided hardware.

110 Install ground strap DPU-C-050-1 between one of the processor mounting studs to the aircraftchassis. Remember to burnish the processor mounting bracket to ensure proper contact of thegrounding strap.

NOTE: Because the bracket is secured to a composite panel an additional wire is supplied to routefrom the mounting bracket to the airframe ground stud to ensure a proper grounding. For airframeground location see Figure 14.



Figure 7: Bracket Assembly with Download Port, RF Switch, and Shock Mounts

Figure 8: Download and RF Switch Cables Secured



Figure 9: DTU Mounting Bracket (ADHY-026-1)

Figure 10: DTU Mounting Location (View Looking FWD)


DTU ProcessorLocationConnectors



3.2 DTU RF Switch and Communications Port

The RF push-button switch is used to initiate actions internal to the DTU processor (manual uploadtransmission). The communication port is used to upload configuration files and download any log data that isneeded. The switch and download port are mounted in the mounting bracket, which is illustrated in Figure 7.

3.3 Antenna Mounting

NOTE: For Detailed GSM Antenna Installation Drawings, Refer to Appendix A, Section 11.2.

The DTU incorporates a GSM antenna that will be mounted internal to the airframe. The GSM antenna (Figure12) is mounted behind the baggage compartment wall (Frame 21) near the DTU (Figure 12).

Figure 11: GSM Antenna


If the antenna is not mounted per the instructions approved by the STC, the installer isresponsible for obtaining the necessary approval from the local Flight Standards DistrictOffice (FSDO). Any deviations must be noted on the FAA Form 337 as alternate locations.

If the antenna is mounted in the cabin of the aircraft they must be securely fastened to theaircraft to prevent their movement during a hard landing. The preferred method is to mountthe antenna in a secondary containment area.

The length of the coaxial cable for the GSM antenna (Figure 12 ) is six (6) feet. Ensure thatthe antenna location is no farther than this distance from the DTU processor.

The specific mounting location is important due to curvatures and uneven surfaces that canbe found on various aircraft. A flat surface is the desired GSM antenna mounting location.

The installer must ensure that the antennas are not mounted in a location totally bondencompassed by metal.

The antenna is not certified to be mounted external to the aircraft

010 The surface that will come in contact with the Velcro® tape must be free of paint, dust, oil, grease,and other contamination prior to antenna installation. Clean the aircraft surface thoroughly.

NOTE: You may need to remove a section of foam from the backside of the panel for theadhesive tape to bond.

020 Cut the supplied Velcro® tape to the length of the GSM antenna and remove the release film.

030 Firmly press the tape to the front of the GSM antenna.

NOTE: The back of the GSM antenna is identified by the coaxial connector mounting and theidentification label. Figure 12 shows the back of the GSM antenna.

040 Mount the GSM antenna to the Velcro® tape installed on the backside of the baggage compartmentwall panel by firmly pressing the antenna to the tape (Figure 13).



Figure 12: GSM Antenna Location Figure 13: GSM Antenna Installation

3.4 Harness Installation

NOTE: For Detailed Wire Routing Drawings, Refer to Appendix A, Section11.5.


Route all cables to follow existing wiring harnesses. Ensure that all cables and individual wires do notinterfere with any control cables. Secure all connectors, cables, and wires with cable ties and wherenecessary, use spiral tubing to protect wires from chaffing and abrasion. Do not secure cables to anyexisting power cable.

Avoid sharp bends and routing RF cable near high energy sources.

Refer to Dassault Model Falcon 2000EX Wiring Diagram Manual (Wiring – Maintenance Practices)

3.4.1 J1 Harness Installation

010 Connect the J1 harness to the J1 connector on the DTU processor.

020 Route the AAV39E24 cable (6 Pin Female ConXall™ Connector) to the DTU RF Switch.

030 Route the AAB49B24 cable (6 Pin Male ConXall™ Connector) to the Communication Port.

040 Route the AAD09A24 and AA00A24N cables to an airframe ground (Figure 14).

050 Route the AAB48D24 cable to the Left Maintenance Connector (389) located on the lavatory panel(F2MB800838A2) in the baggage compartment, shown in Figure 10.

060 Route the AAB47D24 cable to the Right Maintenance Connector (388) on the lavatory panel(F2MB800838A2) in the baggage compartment, shown in Figure 10.



070 Route the AAV19A24 cable to the existing Dassault spare wire (91150737/20) located in the SPR708 wiring loom. Refer to Figure 15

NOTE: SPR 708 wiring loom is located in the baggage compartment near 751FT pressure bungon LH AFT pressure bulkhead, as shown in Figure 15. Another existing spare wire from SPR 708wiring loom can be used if 91150737/20 is unavailable.

NOTE: SPR 708 wiring loom is routed through the pressure bung and the Spare wire will needwill need to be pulled back from pressure bung and rerouted and spliced to AAV19A24.

080 Locate the other end of the spare wire in wiring loom SPR 700, located in the RH Radio Rackbehind co-pilot. Refer to Figure 16.

090 Route the spare wire to the overhead circuit breaker panel.

NOTE: If required, splice the supplied wire to the existing spare wire and route to the overheadcircuit breaker panel.

Figure 14: Airframe Ground Location (View Looking Starboard)



Figure 15: Feed-thru 751FT and SPR 708 wiring loom

Figure 16: RH Radio Rack

3.4.2 GSM Antenna Cable Installation

010 Connect the GSM antenna cable to the DTU processor GSM connection. Torque SMA Connector to5 inch pounds or 56 N-cm. The GSM antenna cable has a 90° connection on both ends.

020 Route the GSM cable (90° connector) to the GSM antenna. Torque SMA Connector to 5 inchpounds or 56 N-cm.

751FTPressure Bung

751FT SPR 708

SPR 700 bundlelocated here



3.5 Shorting Plug Installation

NOTE: For Detailed Shorting Plug Installation Drawings, Refer to Appendix A, Section 11.4.

The shorting plugs (388 & 389) are connected to the maintenance connectors in the baggage compartment. SeeFigure 17. When these shorting plugs are connected they will jumper the Engine Diagnostic Unit (EDU)transmit and receive wires (RS422) to the DTU wires.

010 Disconnect and remove Dust caps from the maintenance connectors (388 & 389).

020 Install DTU Shorting Plug in place of Dust Cap.

030 Install DTU Shorting Plug Lanyard in place of Dust Cap Lanyard.

Figure 17: DTU Shorting Plug Location




3.5.1 Circuit Breaker Installation

NOTE: For Detailed Circuit Breaker Installation Drawings, Refer to Appendix A, Section 11.3.


The “Bus” power is connected to the B2 Bus and is directly controlled by the aircraft“Battery Switch”

Ensure that any connection to aircraft power incorporates a minimal wire length from thepower source to the protection device, fuse or breaker. Recommended length is six (6)inches or less.

Ensure that the wire is protected from shorting out against the airframe or any other sharpobjects.

010 Locate a spare circuit breaker opening in the MISC section of the overhead circuit breaker panel inthe cockpit, as shown in Figure 18.

020 Install supplied 1 Amp circuit breaker into a spare opening and connect to the B2 Bus. Refer to thewiring schematic in 5.1

030 Secure all wiring.

Figure 18: DTU Circuit Breaker Installed

DTUBreaker



4 HARNESS CONNECTOR SIGNAL PINOUTS

4.1 ACS Cable J1, 37 Pin “A” Keyed Connector


Before making any wiring connections, verify all connection locations with the aircraftmanufacturer’s wiring diagram manuals.

Perform a continuity check on all wires before final connection.

Route all harnesses along existing harnesses wherever possible.

Cables may be marked with shrink-on labels near the terminal end. When you shorten a cablebehind a label, be sure to re-label it.

Refer to Falcon 2000EX Wiring Diagram Manual (Wiring – Maintenance Practices).

For Detailed Wiring Routing Drawings, Refer to Appendix A, Section 11.5.

Connector Harness WirePin Wire Color Number Signal Name Wired To

1 COND CABLEJ1-1 & 4 WHT AAV19A24 28V BUS 1 Amp Circuit Breaker (B2 Bus)

1 COND CABLEJ1-2 WHT/BLU AA00A24N 28V RTN Aircraft Ground

2 COND CABLEShield Shield AAB49B24 Shield 6 Pin Male Connector (Pin 5)J1-16, 19 WHT/BLU RS485A (–) 6 Pin Male Connector (Pin 2)J1-18, 17 WHT RS485B (+) 6 Pin Male Connector (Pin 1)

5 COND CABLEShield Shield AAV39E24 Shield 6 Pin Female Connector (Pin 6)J1-34 WHT/ORG LAMP 2 6 Pin Female Connector (Pin 5)J1-34 WHT/RED SWITCH 6 Pin Female Connector (Pin 4)J1-37 WHT/GRN LAMP 1 6 Pin Female Connector (Pin 3)J1-2 WHT/BLU GROUND 6 Pin Female Connector (Pin 2)J1-1 WHT LAMP PWR 6 Pin Female Connector (Pin 1)

1 COND CABLEJ1-15 WHT AAD09A24 On-Ground Sw Aircraft Ground

4 COND CABLEShield Shield AAB48D24 Shield BackshellJ1-9 WHT ACS 2 TXHI Left Maintenance Connector (Pin *I)J1-10 WHT/BLU ACS 2 TXLO Left Maintenance Connector (Pin *H)J1-11 WHT/GRN ACS 2 RXHI Left Maintenance Connector (Pin *G)J1-12 WHT/ORG ACS 2 RXLO Left Maintenance Connector (Pin *F)



4 COND CABLEShield Shield AAV47D24 Shield BackshellJ1-13 WHT ACS 3 TXHI Right Maintenance Connector (Pin *I)J1-14 WHT/BLU ACS 3 TXLO Right Maintenance Connector (Pin *H)J1-21 WHT/GRN ACS 3 RXHI Right Maintenance Connector (Pin *G)J1-22 WHT/ORG ACS 3 RXLO Right Maintenance Connector (Pin *F)

Note: All shields are terminated to the backshell.

P&W ENGINE SERVICES, INC. Data Transmission Unit DTU-G-010-7Dassault Aviation Falcon 2000EX


5 WIRING DIAGRAM

5.1 DTU – Interconnect Schematic*NOTE 1: Reference Falcon 2000EX Maintenance Manual, Maintenance Connector Engine 1, 2 - Section 45-77-00

711TM91150737/2091150737/20

*NOTE 3: Locate existing Dassault spare wire (91150737/20) or alternate wire (see note 2) from SPR 700 wiring loomin RH Radio Rack behind co-pilo t. Route this wire to the overhead CB panel. If required, splice the suppliedM22759/16-24-9 wire to the existing spare wire so that you can route to the overhead CB panel.

SPR 700 *SEE NOTE 3

*NOTE 4: Route wire in accordance with Falcon 2000EXW iring Diagram Manual (W iring - Maintenance Practices)

Male Female

AA00A24N

J1.1J1.2J1.3J1.4J1.5J1.6J1.7J1.8J1.9

J1.10

WHT- RS485 - (A)123456

WHT/BLU - RS485 + (B)

WHT

WHT

123456

A/C GROUND

GROUND STRAP

DTU PROCESSORDTU-A-012-1

WHT/RED - DIAG SWITCH

WHT - LAMP PWRWHT/BLU - GND

WHT/ORG - LAMP 2 SW

WHT/GRN - LAMP 1 SW

FAULT LAMP ASSEMBLY

Comm Port

MICROSWITCH PTT Lamp 1 +Lamp 1 -SW1-NO

SW1-COMMSW1-NCSW2-NO

SW2-COMMSW2-NC

Lamp 2 +Lamp 2 -

SW3-NOSW3-COMM

SW3-NCSW4-NO

SW4-COMMSW4-NC

AAB47D24

AAB48D24

AAV39E24

AAV19A24

AAD09A24

AAB49B24

Bus B2

INDIC SW LAMP 1 -DIAG SWITCHINDIC SW LAMP 2 -

GROUND

A/C BUS +

A/C BAT -

A/C BAT +

DL PORT RS485A (-)DL PORT RS485B (+)

RS485A (-)

RS485B (+)

ON-GROUND SW

ACS2 - RXLOACS2 - RXHIACS2 - TXLOACS2 - TXHI

ACS3 - RXLOACS3 - RXHIACS3 - TXLOACS3 - TXHI

J1 - 37 S

13

222114

2334

2

4

3

37

1

171819

15

16

9101112

12

WHT

GSM ANTENNA

Download PortConXall

RF SwitchConXall

A/C Ground

123456

123456

MaleFemale

1 2

DTU SHORTINGPLUG

HICH B UART 1 IN

LOCH B UART 1 OUT

HI

LO

Breaker 1 AMP

Z*A*D*E

* F* G* H* I

Overhead CB Panel

WHT/ORG

WHTWHT/BLUWHT/GRN

RightMaintenanceConnector"388"

LeftMaintenanceConnector"389"

DTU SHORTINGPLUG

SPR 708 *SEE NOTE 2

Z*A*D*E

* F* G* H* I

A/C GROUND

*NOTE 2: Locate existing Dassault spare wire (91150737/20) in SPR 708 wiring loom in baggage compartment near 751FTpressure bung. 751FT is located on LH AFT pressure bulkhead. Splice the DTU wire (AAV19A24) to the spare wire.Another existing spare wire from SPR 708 wiring loom can be used if 91150737/20 is unavailab le.

*SEE NOTE 1Existing Aircraft Wiring

*SEE NOTE 1Existing Aircraft W iring

LO

WHT/BLUWHT/GRN

LOCH B UART 1 IN

WHT

WHT/ORG

HI

CH B UART 1 OUTHI

Z*A*D*E

* F* G* H* I

Z*A*D*E

* F* G* H* I

Figure 19: DTU Wiring Schematic



6 SYSTEM OPERATION OVERVIEW

6.1 DTU Functional Description

The DTU works as follows:

When the engines are shut off (N1 < 18%, ITT < 400°C and Wf < 200pph) after a flight or during pre-flightthe DTU will collect data from the aircraft system.

The DTU will establish a cellular connection. The DTU will utilize an existing GSM/GPRS cellular networkfor data transmission.

All information downloaded from the aircraft system will be transmitted to the Internet based data collectionmanagement service, TurbineTracker™.

P&W Engine Services’ TurbineTracker™ website has integrated Pratt & Whitney Canada’s WebECTM®program, so trend data uploaded is automatically processed and made available for WebECTM® analysis.

The transmission of data can occur after every flight or pre-flight while the engines are shut off (N1 < 18%,ITT < 400°C and Wf < 200pph).

The DTU incorporates a push-to-test switch for the operator that will force the DTU to transmit the data toTurbineTracker™ (Figure 21).

Figure 20: DTU RF Switch

6.1.1 Initialization

When power is first applied, the DTU performs a series of self-tests. The following self-tests are performedduring initialization:

Micro Controller Test

Temporary Memory Test

Data Log Memory Test

Program Integrity Test



7 SYSTEM CONFIGURATION

The DTU must be configured after installation. The installer, with the help of a computer and softwarecommunication tools, performs this configuration. Configuration requires a laptop computer connected to thesystem with a download cable and running P&W Engine Services Monitor Link Program (MLP).

7.1 Definitions

Configuration File: An MLP data file that contains cellular carrier information, aircraft subsystem (ACS)information for a specific aircraft. This information is transmitted to the processor during configuration.

Configuration Version: A number stored with a particular configuration file. The MLP and TurbineTracker™both maintain version numbers of the current configuration file in use. These must match each other andcorrespond with the data collected and stored by the system processor. If the configuration file is changed, theversion number is automatically incremented.

MLP (Monitor Link Program): The P&W Engine Services communication program is used to transfer data toand from the processor.

7.2 Processor Configuration

These instructions require that the installer have a laptop computer with the current version of MLP and hascreated the required installation configuration file. The current version of the MLP and its manual are availablefrom the TurbineTracker™ website.

NOTE: Ensure that you have the correct copy of the Configuration File to be loaded.

010 Connect the download cable to the download port of the DTU to be configured. The cable can only beplugged in one way. Connect the other end of the cable to the serial port on a laptop computer withthe current version of the MLP.

020 Place the download cable “RUN/CONF” switch on the cable in the “CONF” position.

030 Establish connection to the processor using MLP. If unable to establish connection, proceed with theMLP Troubleshooting Procedure (See the MLP manual).

040 Select “Configure Unit” under the MLU Menu.

050 Follow the on-screen prompts and select the appropriate installation configuration file.

060 If you are prompted to retrieve the Log File, retrieve the log data by selecting ‘MLU’ under the MLUMenu and then click on ‘Retrieve Unit’s Data Log’.

070 Save the log file in the Log directory folder.

080 Select “Configure Unit” under the MLU Menu.

090 Follow the on-screen prompts and select the appropriate installation configuration file.



8 AIRCRAFT TESTING

While following the requirements of FAR 91.407, it is recommended that the aircraft be inspected forairworthiness prior to testing. If the ground test of the modified aircraft is not successfully completed, the aircraftshould be returned to the original aircraft configuration until the tests are completed and acceptable.

After installation of the DTU, it is recommended that ground tests be performed to verify the correct operation ofthe system in the aircraft. The following sections outline the suggested aircraft and system test procedures.

8.1 Aircraft Ground Test

010 With external power connected to aircraft, apply external power to the aircraft bus.

020 Power on all avionics.

030 Tune Comm 1 and Comm 2 VHF radios to the frequencies in Table 1 and verify that there is nointerference caused by the DTU. This can normally be conducted by checking for auto squelch breakon each listed frequency.

040 If interference is suspected at any particular frequency, pull the DTU circuit breaker to see if theinterference subsides.

050 If the aircraft is equipped with a GPS navigation receiver, display the satellite status page and cyclepower on the DTU.

060 Verify that the GPS signal strength is not affected by the operation of the DTU.

070 Tune the #1 and #2 VHF NAV receivers to receive a valid navigational signal from either a VOR ramptester or a locally tuned VOR navigation transmitter.

080 Verify that valid course deviation and a retracted NAV flag are displayed on the HIS or the VORcourse indicator.

090 Cycle power on the DTU and verify that there is no effect on the displayed NAV data.

100 Survey the aircraft for any other installed equipment that may be affected by interference from theDTU. Perform any additional tests as required to determine if the DTU creates objectionableinterference. This may be accomplished by pulling the DTU circuit breaker while observing thesubject equipment. List the additional equipment tested and any observed effects in theElectromagnetic Compatibility Testing Table (See Table 2).

110 Remove external power from aircraft and start engine(s).



Frequency Pass/Fail Frequency Pass/Fail

118.00 MHZ 127.00 MHZ

119.00 MHZ 128.00 MHZ

120.00 MHZ 129.00 MHZ

121.00 MHZ 130.00 MHZ

122.00 MHZ 131.00 MHZ

123.00 MHZ 132.00 MHZ

124.00 MHZ 133.00 MHZ

125.00 MHZ 134.00 MHZ

126.00 MHZ 135.00 MHZ

Table 1: VHF Frequency Table

8.1.1 Engine(s) Running:

010 Connect the download cable to the download port. The cable can only be plugged in one way.Connect the other end of the cable to the serial port on a laptop computer with the current version ofMLP.

020 Turn aircraft power on and establish a connection to the DTU processor using MLP. If unable toestablish a connection, proceed with the MLP Troubleshooting Procedure in the MLP Manual (P&WEngine Services Monitor Link Program – MLP User’s Guide).

030 “Click” on Expert –> Expert Command Mode.

040 “Click” on the Open Terminal button.

050 In the command line, type the following command and press enter: dtu.debug=on

Note: You may need to enter a couple of times for the system to accept the command. 060 Start engine.

070 With the engine running and the DTU operational, tune Comm 1 and Comm 2 VHF radios to thefrequencies in Table 1 and verify that there is no interference caused by the DTU. This can normallybe conducted by checking for auto squelch break on each listed frequency.

080 If interference is suspected at any particular frequency, pull the DTU circuit breaker to see if theinterference subsides.

090 If the aircraft is equipped with a GPS navigation receiver, display the satellite status page and cyclepower on the DTU.

100 Verify that the GPS signal strength is not affected by the operation of the DTU.

110 Tune the #1 and #2 VHF NAV receivers to receive a valid navigational signal from either a VOR ramptester or a locally tuned VOR navigation transmitter.

120 Verify that valid course deviation and a retracted NAV flag are displayed on the HIS or the VORcourse indicator.



130 Cycle power on the DTU and verify that there is no effect on the displayed NAV data.

140 Survey the aircraft for any other installed equipment that may be affected by interference from theDTU. Perform any additional tests as required to determine if the DTU creates objectionableinterference. This may be accomplished by pulling the DTU circuit breaker while observing thesubject equipment. List the additional equipment tested and any observed effects in theElectromagnetic Compatibility Testing Table (See Table 2).

150 Stop Engine(s) and leave aircraft power on for at least 15 minutes (data retrieval and upload time).This can be accomplished by having the APU running or by ground power.

160 Verify you receive the following messages shown in Figure 21 on the MLP screen within 2 minutesafter engine shut down.

NOTE: The amount of “2023232323232…” displayed in Figure 21 depends on how much datathe DTU needs to retrieve from the EDU. A normal engine run without errors or events shouldnot exceed one line of “2023232323232…”

170 Verify you receive the following messages shown in Figure 22 on the MLP screen within 2-3 minutesof completing step 160. Because we are uploaded three logs (Engine 1 EDU Log, Engine 2 EDU Log,and DTU log) you will see the messages shown in Figure 22 three times.

NOTE: The amount of “…” displayed, depends on how much data the DTU isuploading to TurbineTracker. A normal engine run without errors or events should not exceed5 lines of “…”

180 Verify you receive the following messages shown in Figure 23 on the MLP screen once step 170 hascompleted.

190 “Click” on the Close Terminal button and save output file if you want the data for future reference.

200 Shut aircraft power off.

210 Verify the engine run data has been uploaded to TurbineTracker™.

Figure 21: DTU Data Retrieval Messages

Figure 22: DTU Data Transmission Messages

Figure 23: DTU Data Flash Erased Messages



EquipmentProblem Found

Y/N?Comments

Ground TestCommentsFlight Test

Table 2: Electromagnetic Compatibility Test Table

Aircraft Make:

Aircraft Model:

Aircraft Registration Number:

Aircraft S/N:

Test Completed By:

Test Completed Date:



9 SERVICE

Customer Support:P&W Engine Services provides customer support in accordance with the product warranty detailed within thecustomer’s sales contract. If you have any questions concerning any P&W Engine Services product, please donot hesitate to contact us. Our Help Desk accepts calls Monday through Friday between 9:00 AM and 5:00 PMEST. Please have your model and serial number ready when you call.

Comments and findings should be forwarded to P&W Engine Services for inclusion in our continued productimprovement program.

In the event that the DTU must be returned for service, contact the P&W Engine Services Help Desk for aReturned Material Authorization (RMA) number. When you receive the RMA number, include it in the packageaddress and ship it, postage and insurance prepaid, to the address listed below.

When shipping an item for service, please include a complete detailed description of the symptoms you areexperiencing. This will greatly assist our technicians in rapidly identifying the problem. After service, theprocessor will be returned to you or your dealer with the shipping prepaid.

Pratt & Whitney Engine Services, Inc.Help Desk249 Vanderbilt AvenueNorwood, MA 02062Phone: (781) 762-8600Fax: (781) 762-2287E-mail:[email protected]



10 SPECIFICATIONS

10.1 System Specifications

GENERAL

Chassis Size (each): 3.7" x 2.7" x 6.0"

Kit Weight: Approximately 2 lbs.

POWER REQUIREMENTS

Voltage Range: 11 to 32 VDC

Current Draw < 1.0 A @ 11 VDC

Power Draw 8 Watts operating (Engine(s) OFF = RF ON)

4 Watts operating (Engine(s) ON = RF OFF)

20 mWatts standby

ENVIRONMENTAL (ALL TESTS TO RTCA/DO-160D)

Test Performed RTCA Section Level

Temperature & Altitude Section 4.0 Equipment tested to category D3

- Low Temperature Section 4.5.1 - 40 ºC Operating, -55 ºC Non-operational

- High Temperature Section 4.5.2 85 ºC

Operating

- In-Flight Loss of Cooling Section 4.5.4 Test not required

- Altitude Test Section 4.6.1 -1.000 to 55,000 Ft

- Decompression Test Section 4.6.2 Test not required

- Overpressure Test Section 4.6.3 Test not required

Temperature Variation Section 5.0 Equipment tested to category A, 10 ºC/Min

Humidity Section 6.0 Equipment tested to category B

Shock Section 7.0 Equipment tested to category B

- Operational Section 7.2 Equipment tested to category B

- Crash Safety Test Section 7.3 Equipment tested to category B

Vibration Section 8.0 Robust test performed to category R and U

Explosion Section 9.0 Equipment identified as category E

Waterproofness Section 10.0 Equipment identified as category R



Fluids Susceptibility Section 11.0 Equipment identified as category F

Sand and Dust Section 12.0 Equipment identified as category D

Fungus Section 13.0 Equipment identified as category F

Salt Spray Section 14.0 Equipment identified as category S

Magnetic Effect Section 15.0 Equipment identified as category Z

Power Input Section 16.0 Equipment tested to category B

Voltage Spikes Section 17.0 Equipment tested to category B

Audio Freq. Susceptibility Section 18.0 Equipment tested to category B

Induced Signal Susceptibility Section 19.0 Equipment tested to category Z

Radio Freq. Susceptibility Section 20.0 Equipment identified as category V

Radio Freq. Emission Section 21.0 Equipment tested to category L Lightning Induce

Transient Susceptibility Section 22.0 Equipment identified as category B3F3

Lightning Direct Effect Section 23.0Equipment identified as category X Test done inaccordance with HSER23/90 For PT6C-67C

Icing Section 24.0 Test Not Required

Electrostatic Discharge Section 25.0 Equipment identified as category A

DATA INTERFACE

Computer Interface: RS-485 Serial Interface or USB – 57,600 Baud

SYSTEM SOFTWARE

The DTU has been designed and tested to RTCA/DO-178B Level C

SAMPLE RATE

The DTU samples Engine Temperature and Engine Speed once per second.

DATA STORAGE

Flash Storage Memory: 32 MB



10.2 Interface Requirements for Aircraft Sensors

FAULT LAMP

The DTU may interface with an existing cockpit lamp.

The lamp shall have the following characteristics:

Nominal Voltage +28 VDC

Current 40 mA +/- 10%

Power Dissipation 1.24 Watts

Average Rated Life (0°C) 1,500 Hours

DIAGNOSTIC SWITCH

The diagnostic switch is part of the status/fault lamp assembly. The input shall have the following characteristics:

Parameter Specification Comments

Input Threshold 0 VDC

> 0 VDC

Switch Depressed

Switch Disengaged

POWER INPUT +28 VDC

The DTU requires power via a 1 Amp Circuit Breaker. The input shall be as follows:

Parameter Specification Comments

Nominal +28 VDC

Typical 20 – 30 VDC

Minimum 11 VDC

Maximum 32 VDC



11 Appendix A

11.1 DTU Installation

Figure A- 1: DTU Installation – Sheet 1 of 6



11.2 GSM Antenna Installation

Figure A- 7: GSM Antenna Installation – Sheet 1 of 3



11.3 Circuit Breaker Installation

Figure A- 10: Circuit Breaker Installation – Sheet 1 of 3



11.4 Shorting Plug Installation

Figure A- 13: Shorting Plug Installation – Sheet 1 of 3



11.5 DTU Wire Routing

Figure A- 16: DTU Wire Routing – Sheet 1 of 5

Data Transmission Unit - TurbineTracker · Release Date: Ju ly 31 ,2 07 M i er a ngof H rdw re En...

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Transcript of Data Transmission Unit - TurbineTracker · Release Date: Ju ly 31 ,2 07 M i er a ngof H rdw re En...