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P&W ENGINE SERVICES, INC. Data Transmission Unit DTU-G-260-7Dassault Aviation Model Falcon 2000EX Revision E

This Document is Subject to the Restrictions Contained on Cover PageThe export control classification with respect to this document is contained on the first page

DTU-G-260-7, December 4, 2012 i of iv

REVISION HISTORY

Rev Status ofSheets

Rev E E E E B B B B B B B B ESheet i ii iii iv 1 2 3 4 5 6 7 8 9

Rev B E B B B B B B B B B B BSheet 10 11 12 13 14 15 16 17 18 19 20 21 22Rev B D D D DSheet 23 24 25 26 27

LOG OF REVISIONS

REV. NO ECO # DESCRIPTION DATE PAGES REVISED

A N/A Initial Release 09/06/2007 N/A

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

and schematic. Updated format.Corrected spelling and grammar.

04/09/2008 All

C 999 Updated DTU bus power connection.Updated Parts List. Updated wiring

schematic. Correct typographical errors.

05/26/2009 Cover, ii, 24 – 26

D 1020 Update Comm Port wiring in Schematic. 03/01/2010 Cover, ii, 26

E 1142 Change DTU Inspection Interval fromPhase “4A” to “B”

12/04/2012 Cover, i, ii, iii, iv, 9,11, 24, 25, 26, 27

Note: Revisions to this document shall be coordinated through the Boston Aircraft Certification Office,the Aircraft Evaluation Group, and the STC holder. If the DTU Instructions for ContinuedAirworthiness are revised, all operators will be provided with a copy of the applicable revision. Ifyou have a subscription with TurbineTracker, you will be informed via email of new revisionsto this manual. In addition to this, P&W Engine Services maintains the latest versions of allmanuals 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.



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TABLE OF CONTENTS

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

1.1 SCOPE ................................................................................................................................................ 11.2 APPLICABILITY................................................................................................................................... 11.3 DEFINITIONS AND ABBREVIATIONS .................................................................................................... 11.4 PRECAUTIONS .................................................................................................................................... 11.5 UNITS OF MEASURE ........................................................................................................................... 21.6 REFERENCED PUBLICATIONS .............................................................................................................. 21.7 DISTRIBUTION .................................................................................................................................... 21.8 WEIGHT AND BALANCE ...................................................................................................................... 2

2 DESCRIPTION ....................................................................................................................................... 3

2.1 DTU GENERAL DESCRIPTION ............................................................................................................. 32.2 SYSTEM PROCESSOR........................................................................................................................... 42.3 CONTROL COMPONENTS..................................................................................................................... 52.4 AIRFRAME COMPONENTS ................................................................................................................... 6

2.4.1 GSM / GPRS Antenna.................................................................................................................... 62.4.2 Shorting Plug................................................................................................................................. 7

3 CONTROL AND OPERATION INFORMATION................................................................................ 8

3.1 DTU FUNCTIONAL DESCRIPTION........................................................................................................ 83.2 INITIALIZATION .................................................................................................................................. 8

4 SERVICING INFORMATION............................................................................................................... 8

5 MAINTENANCE INSTRUCTIONS....................................................................................................... 8

5.1 RECOMMENDED PERIODIC SCHEDULED SERVICING TASKS ................................................................. 85.2 RECOMMENDED PERIODIC SCHEDULED PREVENTIVE MAINTENANCE TESTS/CHECKS ......................... 85.3 RECOMMENDED PERIODIC SCHEDULED INSPECTIONS ......................................................................... 9

5.3.1 Processor ...................................................................................................................................... 95.3.2 DTU RF Switch ............................................................................................................................. 95.3.3 Download Port .............................................................................................................................. 95.3.4 DTU Shorting Plug...................................................................................................................... 105.3.5 GSM Antenna .............................................................................................................................. 105.3.6 System Wiring.............................................................................................................................. 105.3.7 System Test.................................................................................................................................. 10

5.4 RECOMMENDED PERIODIC STRUCTURAL INSPECTIONS ..................................................................... 115.4.1 Processor Mounting..................................................................................................................... 115.4.2 RF Switch .................................................................................................................................... 115.4.3 GSM Antennas............................................................................................................................. 125.4.4 DTU Shorting Plug...................................................................................................................... 12

6 SYSTEM TROUBLESHOOTING........................................................................................................ 13

6.1 SYSTEM PROCESSOR......................................................................................................................... 146.1.1 Processor Test ............................................................................................................................. 14

6.2 CONTROL COMPONENTS................................................................................................................... 156.2.1 RF Switch Test............................................................................................................................. 156.2.2 Communications Port Test ........................................................................................................... 16



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7 REMOVAL AND REPLACEMENT INFORMATION....................................................................... 17

7.1 PROCESSOR ...................................................................................................................................... 177.1.1 Processor Removal ...................................................................................................................... 177.1.2 Processor Replacement................................................................................................................ 17

7.1.2.1 System Configuration ........................................................................................................... 177.1.2.2 Aircraft Test ......................................................................................................................... 18

7.1.2.2.1 Engine(s) Off: ................................................................................................................. 187.1.2.2.2 Engine(s) Running: ......................................................................................................... 19

7.2 RF SWITCH ...................................................................................................................................... 217.2.1 RF Switch Removal...................................................................................................................... 217.2.2 RF Switch Replacement ............................................................................................................... 21

7.3 GSM ANTENNA................................................................................................................................ 227.3.1 GSM Antenna Removal ................................................................................................................ 227.3.2 GSM Antenna Replacement.......................................................................................................... 22

7.4 DTU SHORTING PLUG ...................................................................................................................... 227.4.1 DTU Shorting Plug Removal........................................................................................................ 227.4.2 DTU Shorting Plug Replacement ................................................................................................. 22

8 SPECIAL INSPECTION REQUIREMENTS ...................................................................................... 23

9 APPLICATION OF PROTECTIVE TREATMENTS......................................................................... 23

10 DATA ................................................................................................................................................. 23

10.1 PARTS LIST ...................................................................................................................................... 2310.1.1 DTU by Parts Kits ....................................................................................................................... 2310.1.2 Components by Kit....................................................................................................................... 23

11 LIST OF SPECIAL TOOLS ............................................................................................................. 24

12 FOR COMMUTER CATEGORY AIRCRAFT ............................................................................... 24

13 RECOMMENDED OVERHAUL PERIODS ................................................................................... 24

14 AIRWORTHINESS LIMITATIONS................................................................................................ 25

15 DIAGRAMS....................................................................................................................................... 26

15.1 HARNESS CONNECTOR SIGNAL PINOUTS ............................................................................... 2615.1.1 ACS Cable J1, 37 Pin “A” Keyed Connector ............................................................................... 26

15.2 DTU - INTERCONNECT SCHEMATIC .................................................................................................. 27



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FIGURES

FIGURE 1: DTU SIMPLIFIED BLOCK DIAGRAM ................................................................................................... 3FIGURE 2: PROCESSOR ....................................................................................................................................... 4FIGURE 3: BAGGAGE COMPARTMENT (VIEW LOOKING FORWARD) ..................................................................... 5FIGURE 5: DTU RF SWITCH AND COMMUNICATIONS PORT ................................................................................ 6FIGURE 7: GSM / GPRS ANTENNA..................................................................................................................... 7FIGURE 8: DTU SHORTING PLUG ....................................................................................................................... 7FIGURE 9: DTU RF SWITCH CONNECTOR WIRING ............................................................................................. 9FIGURE 10: DTU DOWNLOAD PORT CONNECTOR WIRING ................................................................................. 9FIGURE 11: DTU SHORTING PLUG CONNECTOR WIRING .................................................................................. 10FIGURE 12: DTU TO PROCESSOR MOUNTING BRACKET ................................................................................... 11FIGURE 13: GSM ANTENNA INSTALLATION ..................................................................................................... 12FIGURE 14: DTU SHORTING PLUGS.................................................................................................................. 12FIGURE 15: SYSTEM PROCESSOR TEST FLOW DIAGRAM................................................................................... 14FIGURE 16: RF SWITCH TEST FLOW DIAGRAM................................................................................................. 15FIGURE 17: COMMUNICATION PORT TEST FLOW DIAGRAM.............................................................................. 16FIGURE 18: COMMUNICATION PORT SOCKET – FRONT VIEW............................................................................ 16FIGURE 20: DTU WIRING SCHEMATIC ............................................................................................................. 27

LIST OF TABLES

TABLE 1: SUMMARY OF DTU CAPABILITIES ...................................................................................................... 4TABLE 2: VHF FREQUENCY TABLE ................................................................................................................. 19TABLE 3: ELECTROMAGNETIC COMPATIBILITY TEST TABLE ........................................................................... 20



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1 INTRODUCTION

1.1 Scope

The purpose of this document is to provide users of this product with the P&W Engine Services approvedinstructions for continued airworthiness. Any deviation from the procedures described within this documentcould result in a failure of the product to perform properly and could possibly result in damage to other systemsof the aircraft.

These instructions are for aircraft associated with the FAA Type Certificate Data Sheet No. A50NM.

1.2 Applicability

This document applies to aircraft that have been altered by P&W Engine Services’ Data Transmission Unit(DTU), DTU-K-010-17.

1.3 Definitions and Abbreviations

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.

AML – Approved Model ListDTU – Data Transmission UnitEDU – Engine Diagnostic UnitGPRS – General Packet Radio ServiceGSM – Global System for Mobile CommunicationsICA – Instructions for Continued AirworthinessLAN – Local Area NetworkRF – Radio FrequencySTC – Supplemental Type Certificate

1.4 Precautions

Section 7.1.2 and 15.1.1

INSTALLATION CAUTION:

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

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.

Route wire in accordance with Dassault Model Falcon 2000EX Wiring Diagram Manual(Wiring – Maintenance Practices)



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1.5 Units of Measure

This section not applicable

1.6 Referenced Publications

GSS-T-301-1 Monitor Link Program (MLP)DTU-G-010-7 DTU Installation Manual for the Dassault Falcon 2000EXPub. 680/689 Falcon 2000EX Maintenance Manual, Maintenance Connector Engine 1, 2 – Section 45-77-00

1.7 Distribution

These Instructions for Continued Airworthiness are to be furnished with new production Data TransmissionUnits (DTU) for Dassault Falcon 2000EX aircraft and are to become part of the permanent aircraft record uponinstallation

1.8 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)

NOTE: Arm location is for typical installations only and should be verified at time of install. Refer toaircraft equipment list for actual measurements for weight and balance information.



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2 DESCRIPTION

2.1 DTU General Description

The DTU will connect to the existing left and right maintenance connectors (located in the baggagecompartment) of the PW308C engines to provide the communications system through which aircraft and engineperformance data can stream to the Internet without operator intervention. The source of this data will be fromthe PW308C Engine Diagnostic Unit (EDU). The destination will be the P&W Engine ServicesTurbineTracker™ Server.

The DTU passively monitors real-time engine data from the EDU while the aircraft is airborne by reading theEDU Status Message. Once the EDU Status Message is received, the DTU actively commands the EDU to goto the Maintenance Page of the EDU. The Maintenance Page will display the engine criteria to the DTU and theDTU will determine whether or not both engines are off. When the DTU ascertains that aircraft has landed andpowered down the DTU downloads the following engine data from the EDU and stores this data in non-volatilememory.

EDU Log Files Fault Codes Exceedances Events Trends

The DTU utilizes GSM Cellular Network “off the shelf” quad-band modem for transmission over 850MHz,900MHz, 1800MHz and 1900MHz for the automatic data transfer. The cellular telephone circuitry of the DTUis disabled during the time that the aircraft is airborne. The system will initiate a data transfer based on theengine parameters detailed in Section 3.1.

The DTU supports multiple communication modes to achieve data transfer. These will include hardwire,Cellular and Wireless LAN. The capabilities of the certified system are illustrated in Figure 1.

Turbine TrackerTM

Internet

CelluarWireless

LAN

CustomerCustomer Customer

ISP

Airport Hub

CellTower

Hand HeldController

Figure 1: DTU Simplified Block Diagram



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The capabilities of the DTU are detailed below in Table 1.

Bi-directional serial interface with P&W Engine Services engine monitors and OEM enginemonitorsMulti-mode GSM Cellular and 802.11 Wireless LAN RF communications for data retrieval andsystem configuration downloadBi-directional serial interface for hardwire data retrieval and system configuration downloadIndividual discrete digital outputs for system diagnosis and for control of P&W Engine Servicesengine monitorHardware and software for power control for the RF sections of the DTUSoftware for Internet protocol addressing and packet data transmissionBuilt-in test of interface and communication functions

Table 1: Summary of DTU Capabilities

2.2 System Processor

The processor (Figure 2) facilitates wireless connectivity between the PW308C EDU and P&W Engine ServicesTurbineTracker™ Server. This connectivity is bi-directional with the ability of the DTU to request engine statusfrom the EDU in near real time, and then retrieve data from the EDU when both engines have shut down. TheDTU processor then sends the engine data to the TurbineTracker™ website via the cellular network. The DTUsystem interfaces with only the aircraft power and the PW308C EDU and does not connect to any other aircraftsystems. The processor does not require access during flight.

The processor measures 3.7” high by 6.3” 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.

Figure 2: Processor

The system processor is mounted in the baggage compartment behind the lavatory panel (F2MB800838A2)where the maintenance connectors are located (Frame 21, Station 11161), as shown in Figure 3. The processorwill be mounted onto the ADHY-D-026-1 bracket, shown in Figure 4. Although the processor will not requireaccess during normal operation, care should be taken to install the processor in an area that complies with theenvironmental requirements of the system.

NOTE: For mounting instructions, refer to the DTU Installation Manual (DTU-G-010-7) for the DassaultAviation Falcon 2000EX aircraft.



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Figure 3: Baggage Compartment (view looking forward)

Figure 4: DTU Mounting Location

2.3 Control Components

Following are the descriptions and functions of the control components.

DTU RF Switch – The RF push-button switch is used to initiate actions internal to the DTU processor(manual upload transmission). The switch is mounted on the DTU bracket which is illustrated in Figure5.

MaintenanceConnectors


Lavatory PanelF2MB800838A2

DTU ProcessorLocationConnectors



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Figure 5: DTU RF Switch and Communications Port Communications (COMM) Port – Used to interface with the processor using the Monitor Link

Program (MLP). Configuration files can be loaded into the processor and data can be downloaded fromthe processor through this port (Figure 5 and Figure 6).

Figure 6: Communications Port

2.4 Airframe Components

A description of airframe components as well as their functions is described in the following:

2.4.1 GSM / GPRS Antenna

The GSM antenna (Figure 7) is mounted behind the baggage compartment wall (Frame 21) near the DTU.

RF switch andCommunications Port



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Figure 7: GSM / GPRS Antenna

2.4.2 Shorting Plug

The shorting plugs (DTU-C-151-1) are connected to the maintenance connectors (388 & 389) in the baggagecompartment. See Figure 8. When these shorting plugs are connected they will jumper the Engine DiagnosticUnit (EDU) transmit and receive wires (RS422) to the DTU wires.

Figure 8: DTU Shorting Plug



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3 CONTROL AND OPERATION INFORMATION

3.1 DTU Functional Description

The DTU operates as follows:

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

The DTU initiates the uploading of data by turning on the RF circuitry of the processor to establish acellular connection. The DTU uses an existing GSM/GPRS cellular network for data transmission. AnInternet Service Provider provides the Internet connectivity The DTU establishes a direct cellularconnection to the Access Point Network and performs an immediate upload to TurbineTracker.

All information downloaded from the aircraft system is 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 RF switch for the operator and maintenance personnel that will force the DTU totransmit the data to TurbineTracker™ (Figure 5).

3.2 Initialization

When power is first applied, the DTU performs a series of self-tests that has no cockpit effect if it has a fault orif it passes. The following self-tests are performed during initialization:

Micro Controller Test

Temporary Memory Test

Data Log Memory Test

Program Integrity Test

4 SERVICING INFORMATION

This section is not applicable

5 MAINTENANCE INSTRUCTIONS

Scheduled Maintenance Program tasks are to be added to the aircraft operator’s appropriate maintenanceprogram as follows:

5.1 Recommended Periodic Scheduled Servicing Tasks

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 3 volt battery. The Poly-carbonmonofluoride Lithium Coin Battery isused for the real time clock and under normal operating conditions, is expected to last 10 years. If the internalbattery drops below 2.5 volts the date stamp on the DTU log file will default to 1997. If this occurs, theprocessor must be returned to P&W Engine Services for battery replacement.

5.2 Recommended Periodic Scheduled Preventive Maintenance Tests/Checks

None Required



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5.3 Recommended Periodic Scheduled Inspections

The following information should be used to insure the continuous and trouble free operation of the DTU.These inspection steps below should be followed during every “Phase B” inspection per the Dassault Model2000EX Maintenance Manual, Chapter 5.

These instructions describe general inspection methods. All inspections should look for general deterioration ofwiring, connectors, and any other component of the DTU system.

5.3.1 Processor

The DTU processor is mounted in the baggage compartment behind the lavatory panel (F2MB800838A2) wherethe maintenance connectors are located (Frame 21, Station 11161). For processor installation (Figure 4),perform the following inspections:

010 Inspect processor for security to the mounting bracket.

020 Inspect electrical ground strap for proper connection.

030 Inspect electrical connectors for proper connection to processor.

5.3.2 DTU RF Switch

010 Verify that the proper connector is in place (Figure 9).

020 Inspect connectors for loose connections.

Figure 9: DTU RF Switch Connector Wiring

5.3.3 Download Port

010 Verify that the proper connectors are in place (Figure 10).

020 Inspect connectors for loose connections.

Figure 10: DTU Download Port Connector Wiring



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5.3.4 DTU Shorting Plug

010 Verify that the proper connectors are in place (Figure 11).

020 Inspect maintenance connectors for loose connections.

Figure 11: DTU Shorting Plug Connector Wiring

5.3.5 GSM Antenna

The DTU incorporates a GSM (Global System for Mobile Communications) antenna that should be inspected.

To insure the integrity of the system, perform the following inspection: lowercase

010 Inspect antenna cable connections to make sure they are secure.

020 Inspect GSM antenna for security.

5.3.6 System Wiring

None of the wiring for the DTU is routed in metal or opaque conduits or in a high vibration area. A visualinspection is necessary to ensure the integrity of the wiring.

010 Inspect antenna cable for insulation cracking.

020 Inspect wire harness for insulation cracking and proper routing.

5.3.7 System Test

010 With the aircraft battery connected and master switch on, verify that you can communicate with theprocessor using the Monitor Link Program (MLP).

020 Once you establish communication with the processor “click” MLU –> MLU Status. This will show thesystem condition of the processor and should show a system condition of NORMAL. If the systemcondition of the processor is MAINTENANCE, CAUTION, or FAULT then retrieve the log data andtroubleshoot the system.

030 Turn battery switch off



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5.4 Recommended Periodic Structural Inspections

The following information should be used to insure the continuous and trouble free operation of the DTU.These inspection steps below should be followed during every “Phase B” inspection per the Dassault Model2000EX Maintenance Manual, Chapter 5.

These instructions describe general inspection methods. All inspections should look for general deterioration ofbrackets and any other component of the DTU system.

5.4.1 Processor Mounting

For the System Processor installation (Figure 4), perform the following inspections:

010 Inspect the system processor for security to the mounting bracket. Refer to Figure 12.

020 Inspect mounting bracket for cracking.

Figure 12: DTU to Processor Mounting Bracket

5.4.2 RF Switch

For the DTU RF Switch installation Figure 5, perform the following inspections:

010 Inspect RF Switch for proper mounting.

020 Inspect mounting bracket for cracking.



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5.4.3 GSM Antennas

The DTU incorporates a GSM antenna is mounted behind the baggage compartment wall (Frame 21) near theDTU (Figure 13). To insure the integrity of the system, perform the following inspection:

010 Inspect and make sure that antenna mountings are secure.

Figure 13: GSM Antenna Installation

5.4.4 DTU Shorting Plug

The shorting plugs (DTU-C-151-1)) are connected to the maintenance connectors (388 & 389) in the baggagecompartment. See Figure 14. When these shorting plugs are connected they will jumper the Engine DiagnosticUnit (EDU) transmit and receive wires (RS422) over to the DTU wires. To insure the integrity of the system,perform the following inspection:

010 Inspect and make sure that DTU Shorting Plugs are secure.

Figure 14: DTU Shorting Plugs




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6 SYSTEM TROUBLESHOOTING

When the system does not function properly (or as you expect it to operate), the first thing that you must do isidentify and isolate the problem. When you have accomplished this, you can effectively begin to resolve theproblem.

The first step in troubleshooting is to isolate each system component and ensure that each component functionsproperly when it is run independently. Using the Monitor Link Program (MLP), you can interrogate the systemto determine which function or component may have failed. Occasionally you may have to replace existingcomponents to correct the problem. Determine if the problem is in the aircraft, DTU processor, wiring, theantenna or configuration of the processor.

Ask the question, can you repeat or recreate the problem? Random events may appear to be related, but they arenot necessarily contributing factors to your problem. You may be experiencing more than one problem. Youmust isolate and solve one problem at a time. Log (document) all testing and problem isolation procedures.You may need to review this document later. This will also prevent you from duplicating your testing efforts.

Once you have isolated a problem, take the necessary steps to resolve it. Refer to the problem solutionscontained in this document. If you cannot solve your system problems using this troubleshooting guide, or if theproblem persists, refer to Section 4 herein and contact P&W Engine Services Help Desk.

Before contacting the Help Desk, have someone from your organization with a technical understanding of theDTU and its application to provide answers on the following questions:

Engine Type? PW308C

Airframe Type? Dassault Model Falcon 2000EX

Processor Type? Data Transmission Unit (DTU)

Airframe Tail Number?

Processor Serial Number?

Is there a problem history?

Visual processor inspection?

Monitor Link Program (MLP) indications?

Has the processor worked previously?

What activity was being performed when the failure occurred?

The DTU will monitor and record system failures in a log that can be downloaded and reviewed. Status of thesystem can be obtained through MLP. Refer to the MLP user guide (GSS-T-301-1) for these procedures.

Detailed troubleshooting for the system processor as well as for the various input channels can be found in thetopic-specific sections that follow.



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6.1 System Processor

The first point of troubleshooting the DTU is to be able to power up and communicate to the system processor.

If the system powers up and will communicate with the Monitor Link Program (MLP), the download log willdefine any system faults. These faults can be investigated by following the troubleshooting methods in thissection.

6.1.1 Processor Test

This section defines the basic test to determine if the processor is powered and functioning properly. Follow theprocessor test flow diagram (Figure 15) to determine failure.

1Measure aircraftsupply to system

voltage at:J1.Pin 1 & 2J1.Pin 4 & 2

224V on both

1 and 4?

Yes

No

Check Aircraft SupplyVoltage.

Processor OK.

3Wiring Okay?

Yes

No Fix Wiring

Figure 15: System Processor Test Flow Diagram



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6.2 Control Components

6.2.1 RF Switch Test

This section defines the basic test to determine if the RF Switch is functioning. Follow the RF Switch test flowdiagram (Figure 16) and connection diagram to determine failure.

Disconnect J1 fromprocessor and checkfor continuity on J1

pins:2 and 23

Continuity?

While Pressing RFswitch check for

continuity on J1 pins:2 and 23

No

Yes

Check wiring. If OK thenreplace switch

Normal operation.

Continuityr? No

Yes

Check wiring. If OK thenreplace switch

Figure 16: RF Switch Test Flow Diagram



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6.2.2 Communications Port Test

This section defines the basic test to determine if the communications (COMM) port is functioning. Follow thedownload port test flow diagram (Figure 17) and connection diagram to determine failure.

With processorpowered measure

voltage at downloadport connector pins:

1 and 2

1.5V measured?

Yes

No

Normal Operation. CheckCommunications Cable and

Computer

Disconnect 6 pinConXall connector

and measure 1.5V atpins 1 and 2 (Male

side).

Replace Comm PortAssembly.

Note: Pin 1 on the COMM Port is identified below(Figure 17).

1.5V measured?

Yes

No Check Wiring. If OKreplace processor

Figure 17: Communication Port Test Flow Diagram

Figure 18: Communication Port Socket – Front View



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7 REMOVAL AND REPLACEMENT INFORMATION

7.1 Processor

7.1.1 Processor Removal

010 Insure that power is removed from the aircraft and the battery is disconnected.

020 Pull collar and tag DTU circuit breaker.

030 Disconnect J1 and cap with an ESD cap.

040 Disconnect GSM Coaxial cable from the processor.

050 Remove the DTU mounting bracket from the panel by removing the 6 screws (MS35207-261) andthe 6 washers (AN960-10).

060 Disconnect the ground strap between the processor mounting stud and the aircraft chassis.

070 Disassemble the DTU from the mounting bracket by removing the 4 nuts (MS21042-06) and 4washers (920-00006), shown in Figure 12.

7.1.2 Processor Replacement

010 Assemble the DTU to the mounting bracket by installing the 4 nuts (MS21042-06) and 4 washers(920-00006), shown in Figure 12. Torque nuts to 8 inch pounds


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

020 Reinstall ground strap between the processor mounting stud and the aircraft chassis.

030 Reinstall DTU mounting bracket to the panel by securing the 6 screws (MS35207-261) and the 6washers (AN960-10). Torque screws to 15 inch pounds.

040 Connect GSM Coaxial cable to the processor. Torque SMA Connector to 5 inch pounds.

050 Remove ESD cap from J1 and connect to processor.

060 Ensure proper bonding by making sure that the resistance is less than 0.7 ohms from the groundstrap to airframe ground.

070 Remove tag on DTU circuit breaker and push circuit breaker back in.

080 Reconnect aircraft battery and turn aircraft power on.

090 Configure and test the processor per section 7.1.2.1 and 7.1.2.2.

7.1.2.1 System 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.



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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.

7.1.2.2 Aircraft Test

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, theaircraft should 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 operationof the system in the aircraft. The following sections outline the suggested aircraft and system test procedures.

7.1.2.2.1 Engine(s) Off:

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 2 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 3).

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



DTU-G-260-7, December 4, 2012 19 of 27

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 2: VHF Frequency Table

7.1.2.2.2 Engine(s) Running:

010 Start engine.

020 With the engine running and the DTU operational, tune Comm 1 and Comm 2 VHF radios to thefrequencies in Table 2 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

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

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

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

060 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

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

080 Cycle power on the DTU (this can be done by disconnecting the J1 connector) and verify that there isno effect on the displayed NAV data.

090 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 3)

100 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.

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



DTU-G-260-7, December 4, 2012 20 of 27

EquipmentProblem Found

Y/N?Comments

Ground TestCommentsFlight Test

Table 3: Electromagnetic Compatibility Test Table

Aircraft Make:

Aircraft Model:

Aircraft Registration Number:

Aircraft S/N:

Test Completed By:

Test Completed Date:



DTU-G-260-7, December 4, 2012 21 of 27

7.2 RF Switch

7.2.1 RF Switch Removal



030 Remove the DTU processor mounting bracket from the panel by removing the 6 screws (MS35207-261) and the 6 washers (AN960-10). Gain access to the underside of the bracket shown in Figure19.

040 Remove Adel Clamp (MS21919DG4) and nut (AN365-1032A), shown in Figure 19.

050 Remove the RF Switch by squeezing locking springs on the sides of switch and pushing the switchthru the hole in the panel/bracket (Figure 19).

060 Disconnect RF Switch ConXall™ connector and remove RF Switch.

7.2.2 RF Switch Replacement

010 Install RF Switch.

020 Install Adel Clamp (MS21919DG4) and nut (AN365-1032A). Torque nut to 15 inch pounds.

030 Reconnect ConXall™ connector.

040 Reinstall DTU mounting bracket to the panel by securing the 6 screws (MS35207-261) and the 6washers (AN960-10). Torque screws to 15 inch pounds.


060 Reconnect aircraft battery and turn aircraft power on.

070 Establish communication with the processor via the download port using the Monitor Link program(MLP). Refer to section 5.3.7 of this manual.

080 Once communication is established, “click” on the Expert Menu then “click” Expert Command Mode.

090 “Click” on the Open Terminal button.

100 In the command window, type the following: dtu.debug=on. Then press enter.

110 Press and hold RF Switch for greater than 5 seconds and confirm that MLP displays the followingmessage, “DTU> Enter Maintenance Mode!”.

120 Close MLP and remove download port.

Figure 19: RF Switch

Adel ClampRF Switch



DTU-G-260-7, December 4, 2012 22 of 27

7.3 GSM Antenna

7.3.1 GSM Antenna Removal



030 Disconnect antenna cable at antenna connector.

040 Remove antenna from aircraft by pulling on Velcro®.

7.3.2 GSM Antenna Replacement

010 Replace Velcro® if needed and attach antenna to aircraft.

020 Connect antenna cable at antenna connector. Torque SMA Connector to 5 inch pounds.



7.4 DTU Shorting Plug

7.4.1 DTU Shorting Plug Removal



030 Disconnect and remove DTU Shorting Plug and lanyard (Figure 14).

7.4.2 DTU Shorting Plug Replacement

010 Connect DTU Shorting Plug and lanyard.





DTU-G-260-7, December 4, 2012 23 of 27

8 SPECIAL INSPECTION REQUIREMENTS


9 APPLICATION OF PROTECTIVE TREATMENTS


10 Data

10.1 Parts List

The parts listed below consist of the installation kits for the DTU. Assembly kit numbers are listed in section10.1.1 and individual components are detailed by kit numbers in section 10.1.2.

10.1.1 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

10.1.2 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



DTU-G-260-7, December 4, 2012 24 of 27

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

11 LIST OF SPECIAL TOOLS

Raychem crimp tool – AD-1377Raychem splices – D436-XXDaniels crimper – M22520/1-XXDaniels positioner – M22520/1-XXInsertion/removal tool – M81969/14-XXP&W Engine Services Serial Download Cable – TREND-C-033-1P&W Engine Services USB Download Cable – ADAS-C-053-1

Minimum System RequirementsWindows™ operating system 98 or higherInternet AccessRS232 or USB port

12 FOR COMMUTER CATEGORY AIRCRAFT

For Commuter Category Aircraft, electrical load data applicable for each system and aircraft weight and balancemust be identified. The DTU has a current draw of 300 milliamps at 28V DC intermittently (during RFtransmission), and 150 milliamps at 28V DC continuously.

13 RECOMMENDED OVERHAUL PERIODS




DTU-G-260-7, December 4, 2012 26 of 27

15 DIAGRAMS

15.1 HARNESS CONNECTOR SIGNAL PINOUTS

15.1.1 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.

Route wire in accordance with Dassault Model Falcon 2000EX Wiring Diagram Manual(Wiring – Maintenance Practices)

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.



DTU-G-260-7, December 4, 2012 27 of 27

15.2 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-pilot. 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 2000EXWiring Diagram Manual (Wiring - 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 unavailable.

*SEE NOTE 1Existing Aircraft Wiring

*SEE NOTE 1Existing Aircraft Wiring

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 20: DTU Wiring Schematic

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