pratt & whitney engine services, inc. norwood, ma 02062 · p&w engine services, inc. adas+...

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

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

ADAS+Instructions for Continued Airworthiness

ADAS-G-260-1/A

For Cessna Caravan Model 208 Series

Manual Number: ADAS-G-260-1/A

Preparation Date: December 2, 2002 Prepared By: D Elsemiller

Release Date: December 16, 2002 S Sackos, Manager of Manufacturing Services

Revision Date: November 15, 2011 J Miller, Manager of Engineering

Revision Ltr: I

Total Pages: 37

Approvals:

P&W ENGINE SERVICES, INC. ADAS+ ADAS-G-260-1/ACessna Aircraft Company Model 208 Series

- i-ADAS-G-260-1/A Pratt & Whitney Engine Services, Inc. Proprietary

PREFACE

Disclaimer

Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADAS+ system requires knowledgeable interpretation bythe pilot. Any recommendations and operating procedures contained in this manual shall not supersede the Aircraft orEngine manufacturer recommendations, operating procedures, or limits. The Pratt & Whitney Engine Services, Inc. ADAS+system should not be used as a primary guide monitoring the Aircraft and Engine manufacturers operating limits. Pratt &Whitney Engine Services, Inc. is not liable for any damages resulting from the use of this product.

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 P&W Engine Services.


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REVISION HISTORY

Rev F I H I F F F H H F G H G H G HRev Statusof Sheets Sheet i ii iii iv v 1 2 3 4 5 6 7 8 9 10 11

Rev H H G G H H H H H H G G G G G GSheet 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27Rev H H H H H H I I I I

Sheet 28 29 30 31 32 33 34 35 36 37

LOG OF REVISIONS

REV. NO ECO# DESCRIPTION DATE PAGES REVISED

A Initial Release 12/16/02

B 735Change Processor Assembly Kit contents by

adding Ground Strap DPU-C-050-305/27/04 I and 1

C 812Reformat manual and add Split Lamp

Option. Correct Typos05/24/05 All

D 839Revise Connection Chart to show the correct

pin-out for the J2 Harness.09/12/05 Cover, I – iv, and 27

E 860Correct dimensions for Split

Lamp. Correct OAT Probe connections07/06/06 4, 29-32

F 957Update Split Lamp. Change UTC logo to

P&W logo. Update address. Correctspelling and grammar.

08/22/07 All

G 980Add Ice Vane Switch Kit to Parts List. AddContinued Airworthiness Instructions for Ice

Vane Switch.12/08/08 Cover, ii-iv, 7-33

H 994

Revise Parts List. Update Schematics.Revise OAT, Torque, Circuit Breaker, and

Download Port Instructions. CorrectTypographical Errors.

02/23/09Cover, ii–iv, 4, 5, 8, 10,

12-14, 17-22, 29-33

I 1103Add optional Garmin G620 Interface Cable

P/N ADAS-C-072-1 to Parts List. AddSchematics to support the interface cable

11/15/11Cover, ii, iv, v, 19, 22,

34 - 37

NOTE:Revisions to this document shall be coordinated through the Boston Aircraft Certification Office,the Kansas City AEG, and the STC holder. If the ADAS+ 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................................................................................................................................. 11.6 REFERENCED PUBLICATIONS .................................................................................................................. 11.7 DISTRIBUTION ......................................................................................................................................... 1

2 DESCRIPTION .................................................................................................................................... 2

3 CONTROL AND OPERATION INFORMATION........................................................................... 2

4 SERVICING INFORMATION........................................................................................................... 2

5 MAINTENANCE INSTRUCTIONS .................................................................................................. 3

5.1 RECOMMENDED PERIODIC SCHEDULED SERVICING TASKS.................................................................... 35.2 RECOMMENDED PERIODIC SCHEDULED PREVENTIVE MAINTENANCE TESTS/CHECKS.......................... 35.3 RECOMMENDED PERIODIC SCHEDULED INSPECTIONS............................................................................ 3

5.3.1 System Processor............................................................................................................................. 35.3.2 Standard TREND Lamp or Optional Split Lamp and Download Port............................................ 45.3.3 Pitot / Static Transducers................................................................................................................ 55.3.4 Outside Air Temperature Probe...................................................................................................... 75.3.5 Torque Transducer.......................................................................................................................... 75.3.6 Particle Separator Switch ............................................................................................................... 85.3.7 J1, J2, and J3 Harnesses................................................................................................................. 85.3.8 System Test ...................................................................................................................................... 8

5.4 RECOMMENDED PERIODIC STRUCTURAL INSPECTIONS .......................................................................... 95.4.1 System Processor............................................................................................................................. 95.4.2 Standard TREND Lamp or Optional Split Lamp and Download Port............................................ 95.4.3 Pitot / Static Transducers.............................................................................................................. 115.4.4 Outside Air Temperature Probe.................................................................................................... 125.4.5 Torque Transducer........................................................................................................................ 135.4.6 Particle Separator Switch ............................................................................................................. 14

6 SYSTEM TROUBLESHOOTING.................................................................................................... 15

7 REMOVAL AND REPLACEMENT INFORMATION................................................................. 15

7.1 PROCESSOR REMOVAL/REPLACEMENT................................................................................................. 157.2 TREND SWITCH OR ENGINE/TREND SPLIT LAMP REMOVAL/REPLACEMENT ................................. 157.3 DOWNLOAD PORT REMOVAL/REPLACEMENT....................................................................................... 167.4 PITOT/STATIC TRANSDUCER REMOVAL/REPLACEMENT ...................................................................... 167.5 OAT REMOVAL/REPLACEMENT............................................................................................................ 177.6 TORQUE TRANSDUCER REMOVAL/REPLACEMENT ............................................................................... 177.7 PARTICLE SEPARATOR SWITCH REMOVAL/REPLACEMENT .................................................................. 17

8 SPECIAL INSPECTION REQUIREMENTS ................................................................................. 19

9 APPLICATION OF PROTECTIVE TREATMENTS.................................................................... 19


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10 DATA................................................................................................................................................... 19

10.1 PARTS LIST ............................................................................................................................................ 1910.1.1 ADAS+ by Parts Kits .................................................................................................................... 1910.1.2 Components by Kit ........................................................................................................................ 19

11 LIST OF SPECIAL TOOLS.............................................................................................................. 23

12 FOR COMMUTER CATEGORY AIRCRAFT .............................................................................. 23

13 RECOMMENDED OVERHAUL PERIODS .................................................................................. 23

14 AIRWORTHINESS LIMITATIONS ............................................................................................... 23

15 DIAGRAMS ........................................................................................................................................ 24

15.1 POWER/ SENSOR CABLE J1, 15 PIN S KEYED CONNECTOR................................................................... 2415.2 SENSOR CABLE J2, 15 PIN SA KEYED CONNECTOR.............................................................................. 2515.3 COCKPIT TREND / SENSOR CABLE, J3, 37 PIN S KEYED CONNECTOR .................................................. 26

16 WIRING DIAGRAM ......................................................................................................................... 28

16.1 ADAS+ CONNECTION CHART – CESSNA MODEL 208 SERIES .............................................................. 2816.2 ADAS+ INTERCONNECT SCHEMATIC – NO SUPPLIED TORQUE TRANSDUCERS................................... 3016.3 ADAS+ INTERCONNECT SCHEMATIC – SUPPLIED TORQUE TRANSDUCERS ......................................... 3116.4 ADAS+ INTERCONNECT SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS3216.5 ADAS+ INTERCONNECT SCHEMATIC (SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS..... 3316.6 ADAS+ SCHEMATIC (GARMIN G620 OPTION) – NO SUPPLIED TORQUE TRANSDUCERS..................... 3416.7 ADAS+ SCHEMATIC (GARMIN G620 OPTION) – SUPPLIED TORQUE TRANSDUCERS........................... 3516.8 ADAS+ SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS

.............................................................................................................................................................. 3616.9 ADAS+ SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS..... 37

LIST OF FIGURESFIGURE A- 1: ADAS+ MOUNTING ............................................................................................................................................ 3FIGURE A- 2: STANDARD TREND SWITCH OR OPTIONAL ENGINE/TREND SPLIT LAMP ......................................................... 4FIGURE A- 3: TYPICAL MOUNTING LOCATION FOR DOWNLOAD PORT...................................................................................... 4FIGURE A- 4: STANDARD TREND SWITCH/FAULT LAMP CONNECTOR WIRING ....................................................................... 5FIGURE A- 5: OPTIONAL ENGINE/TREND SPLIT LAMP CONNECTOR WIRING ........................................................................ 5FIGURE A- 6: DOWNLOAD PORT CONNECTOR WIRING ............................................................................................................. 5FIGURE A- 7: PITOT / STATIC TRANSDUCER INSTALLATION ...................................................................................................... 6FIGURE A- 8: PITOT/STATIC WIRING......................................................................................................................................... 6FIGURE A- 9: OAT PROBE WIRING ........................................................................................................................................... 7FIGURE A- 10: TORQUE TRANSDUCER WIRING ......................................................................................................................... 7FIGURE A- 11: PROCESSOR MOUNTING CONFIGURATION ......................................................................................................... 9FIGURE A- 12: STANDARD TREND SWITCH OR ENGINE/TREND SPLIT LAMP ...................................................................... 10FIGURE A- 13: TYPICAL MOUNTING LOCATION FOR DOWNLOAD PORT.................................................................................. 10FIGURE A- 14: PITOT/STATIC INSTALLATION (SIDE VIEW) ..................................................................................................... 11FIGURE A- 15: OAT PROBE ILLUSTRATION ............................................................................................................................ 12FIGURE A- 16: TORQUE TRANSDUCER INSTALLATION CONFIGURATION................................................................................. 13FIGURE A- 17: PARTICLE SEPARATOR SWITCH INSTALLATION ............................................................................................... 14FIGURE A- 18: PARTICLE SEPARATOR SWITCH (EXPLODED VIEW) ......................................................................................... 18FIGURE A- 19: WIRING SCHEMATIC– NO SUPPLIED TORQUE TRANSDUCERS.......................................................................... 30FIGURE A- 20: WIRING SCHEMATIC – SUPPLIED TORQUE TRANSDUCERS............................................................................... 31FIGURE A- 21: WIRING SCHEMATIC (SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS ..................................... 32


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FIGURE A- 22: WIRING SCHEMATIC (SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCER ............................................. 33FIGURE A- 23: WIRING SCHEMATIC (GARMIN G620 OPTION) – NO SUPPLIED TORQUE TRANSDUCERS ................................. 34FIGURE A- 24: WIRING SCHEMATIC (GARMIN G620 OPTION) – SUPPLIED TORQUE TRANSDUCERS ....................................... 35FIGURE A- 25: WIRING SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – NO SUPPLIED TORQUE TRANSDUCERS............ 36FIGURE A- 26: WIRING SCHEMATIC (GARMIN G620 / SPLIT LAMP OPTION) – SUPPLIED TORQUE TRANSDUCERS.................. 37

LIST OF TABLESTABLE A- 1: ADAS+ CONNECTION CHART ............................................................................................................................ 29


1ADAS-G-260-1/A Pratt & Whitney Engine Services, Inc. Proprietary

1 INTRODUCTION

1.1 Scope

The purpose of this document is to provide users of this product with P&W Engine Services approvedInstruction for Continued Airworthiness for the ADAS +. Any deviation from the procedures described withinthis document could result in a failure of the product to perform properly and could possibly result in damage toother systems of the aircraft.

1.2 Applicability

This document applies to aircraft that are altered by the installation of a P&W Engine Services’ ADAS+,EMU-A-010-3

1.3 Definitions and Abbreviations

ADAS+ – Aircraft Data Acquisition System PlusAML – Approved Model ListICA – Instructions for Continued AirworthinessMLP – Monitor Link ProgramSTC – Supplemental Type Certificate

1.4 Precautions

This section not applicable

1.5 Units of Measure

This section not applicable

1.6 Referenced Publications

ADAS-G-260-1 generic Instructions for Continued Airworthiness

1.7 Distribution

These Instructions for Continued Airworthiness are to be furnished with ADAS+ engine trend monitors forCessna Aircraft Model 208 Series aircraft and is to become part of the permanent aircraft record uponinstallation.



2 DESCRIPTION

A detailed description of the system can be found in ADAS-G-260-1, ADAS+ Instructions for ContinuedAirworthiness, Section 2.

3 CONTROL AND OPERATION INFORMATION

A detailed description of the control and operation of the system can be found in ADAS-G-260-1, ADAS+Instructions for Continued Airworthiness, Section 3.

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 ADAS+ has been designed with the latest solid-state technology. The onlycomponent that has a limited life span is the internal battery. This battery, under normal operating conditions, isexpected to last 10 years. If the battery is discharged, the processor must be returned to P&W Engine Servicesfor battery replacement.

5.2 Recommended Periodic Scheduled Preventive Maintenance Tests/Checks

None Required

5.3 Recommended Periodic Scheduled Inspections

The following information should be used to insure the continuous and trouble free operation of the ADAS +.These inspection steps should be followed during every 200-hour inspection.

These instructions describe general inspection methods. All inspections should look for general deterioration ofhoses, brackets, and any other component of the ADAS+ system. Other than the specific periodic inspections,maintenance is on-condition, and there is no other scheduled maintenance.

5.3.1 System Processor

The ADAS+ processor is located at approximately FS 70 in the engine compartment on the lower enginemounting tube. For the System Processor installation (Figure A- 1), 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 ADAS+ processor.

Figure A- 1: ADAS+ Mounting



5.3.2 Standard TREND Lamp or Optional Split Lamp and Download Port

The ADAS+ has a standard TREND switch / fault lamp or an optional Engine/Trend Split Lamp that is installedin the cockpit (Figure A- 5) and consist of a 75" x .75" square Push-to-test lamp for standard TREND switch /fault lamp or .68" x .68" for the optional Engine/Trend Split Lamp. The ADAS+ also has a download portinstalled in the cockpit (Figure A- 6) and consist of a 19/32" serial download connector.

For the TREND switch / fault lamp or the optional ENGINE/TREND Split Lamp and download portinstallations (Figure A- 2 and Figure A- 3), perform the following inspections:

010 Verify that the proper connectors are in place. Refer to Figure A- 4, Figure A- 5, and Figure A- 6.

020 Inspect electrical connectors for loose connections.

030 Inspect wiring for proper routing and security.

040 Inspect wiring for signs of interference and wire chaffing.

Figure A- 2: Standard Trend Switch or Optional ENGINE/TREND Split Lamp

Figure A- 3: Typical Mounting Location for Download Port



Figure A- 4: Standard TREND Switch/Fault Lamp Connector Wiring

Figure A- 5: Optional ENGINE/TREND Split Lamp Connector Wiring

Figure A- 6: Download Port Connector Wiring

5.3.3 Pitot / Static Transducers

ADAS + has the capability of measuring airspeed and altitude for event monitoring or trend monitoring. Bothpitot and static transducers are plumbed (Figure A- 7) into the aircraft’s existing pitot and static systems. Bothtransducers are mounted in tandem under the instrument panel on the co-pilots side. They are accessed from thecockpit by removing the control column cover assembly and glove compartment box.



Figure A- 7: Pitot / Static Transducer Installation

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

010 Verify that the proper connectors are in place. Refer to Figure A- 8.




Figure A- 8: Pitot/Static Wiring



5.3.4 Outside Air Temperature Probe

The temperature probe is mounted on the underside of the aircraft’s engine cowling to provide the processorwith OAT data.

For the OAT probe installation (Figure A- 9) perform the following inspection:



Figure A- 9: OAT Probe Wiring

5.3.5 Torque Transducer

The ADAS + obtains the engine torque level by using two (2) 0 – 150 PSIG transducers installed in the torquepressure lines.

010 Verify that the proper connectors are in place. Refer to Figure A- 10.




Figure A- 10: Torque Transducer Wiring



5.3.6 Particle Separator Switch

The Particle Separator Switch is installed onto the Particle Separator Actuating Rod controlled by the pilotinside the cockpit. The Particle Separator Switch is installed at Fuselage Station 77.0 on the left side of theengine compartment.

For the Particle Separator Switch Installation (Figure A- 17), perform the following inspection:

010 Inspect Particle Separator Switch wiring for proper routing and security.

020 Inspect Particle Separator Switch wiring for signs of interference and wire chaffing.

5.3.7 J1, J2, and J3 Harnesses

010 Inspect harness for proper routing and security.

020 Inspect harness for signs of interference and wire chaffing.

5.3.8 System Test

010 With the aircraft battery connected and master switch on, verify that the TREND lamp or the optionalENGINE/TREND Split Lamp illuminates, indicating system boot-up. After approximately 5 seconds,the TREND lamp or the ENGINE/TREND Split Lamp will extinguish and the TREND Lamp will do oneof the following:

Remain extinguished (NORMAL STATE)

Flash (MAINTENANCE OR CAUTION STATE)

Illuminate Solid (FAULT STATE)

If the processor does NOT go into NORMAL STATE, retrieve the log data, and troubleshoot thesystem.

020 Turn battery switch off.



5.4 Recommended Periodic Structural Inspections

The following information should be used to insure the continuous and trouble free operation of the ADAS +.These inspection steps should be followed during every 200-hour inspection.

These instructions describe general inspection methods. All inspections should look for general deterioration ofhoses, brackets, and any other component of the ADAS+ system. Other than the specific periodic inspections,maintenance is on-condition, and there is no other scheduled maintenance.

5.4.1 System Processor

For the System Processor installation (Figure A- 11), perform the following inspections:

010 Inspect processor for security to the mounting bracket.

020 Inspect mounting bracket for cracking.

Figure A- 11: Processor Mounting Configuration

5.4.2 Standard TREND Lamp or Optional Split Lamp and Download Port

For the Standard TREND switch / fault lamp or the optional ENGINE/TREND Split Lamp and download portinstallations (Figure A- 12 and Figure A- 13), perform the following inspections:

010 Inspect Standard TREND Switch / Fault Lamp or Optional ENGINE/TREND Split Lamp for propermounting.

020 Inspect Download Port for proper mounting.



Figure A- 12: Standard Trend Switch or ENGINE/TREND Split Lamp

Figure A- 13: Typical Mounting Location for Download Port



5.4.3 Pitot / Static Transducers

For the Pitot/Static transducer installation, perform the following inspection:

010 Inspect and make sure that transducer mountings are secure. Refer to Figure A- 14.

020 Inspect Adel™ clamps for deterioration.

030 Inspect fittings to make sure they are secure.

Figure A- 14: Pitot/Static Installation (Side View)



5.4.4 Outside Air Temperature Probe

For the OAT probe installation (Figure A- 15), perform the following inspection:

010 Inspect OAT probe assembly form proper mounting.

020 Inspect aircraft skin around OAT probe for signs of cracking.

030 Perform continuity test to ensure proper bonding with the aircraft skin.

Figure A- 15: OAT Probe Illustration



5.4.5 Torque Transducer

The ADAS + obtains the engine torque level by using two (2) 0 – 150 PSIG transducers installed in the torquepressure lines. The torque transducer installation is referenced in illustration Figure A- 16.

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

010 Inspect and make sure that transducer mounting is secure.


030 Inspect pressure lines for signs of deterioration.

040 Inspect fittings to make sure they are secure.

050 Inspect each transducer for signs of fluid leaking.

Figure A- 16: Torque Transducer Installation Configuration



5.4.6 Particle Separator Switch

For the Particle Separator Switch installation (Figure A- 17), perform the following inspection:

010 Inspect and make sure that Particle Separator Switch Mounting Plate is secure.

020 Inspect Particle Separator Switch Mounting and Support Plate for cracking.

030 Inspect and make sure that the Particle Separator Magnetic Switches are installed properly andsecure.


Figure A- 17: Particle Separator Switch Installation



6 SYSTEM TROUBLESHOOTING

Detailed troubleshooting for the system can be found in ADAS-G-260-1, ADAS+ Instructions for ContinuedAirworthiness, Section 6.

7 REMOVAL AND REPLACEMENT INFORMATION

7.1 Processor Removal/Replacement

NOTE: Insure that power is removed from the aircraft and the battery is disconnected

010 Disconnect the J1, J2, and J3 wiring harnesses from the processor.

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

030 Disassemble the ADAS+ processor from the mounting bracket shown in Figure A- 11.

040 Assemble the ADAS+ processor to the mounting bracket shown in Figure A- 11. Ensure that theprocessor does not interfere with wiring or controls.

INSTALLATION CAUTION:

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

050 Install ground strap between one of the processor mounting studs and the aircraft chassis.

060 Connect wiring harnesses J1, J2, and J3 to the processor.

070 Perform configuration and calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1,System Configuration and Calibration.

7.2 TREND Switch or ENGINE/TREND Split Lamp Removal/Replacement

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

020 Disconnect TREND Switch or ENGINE/TREND Split Lamp ConXall™ connector under instrumentpanel.

030 Remove TREND Switch or ENGINE/TREND Split Lamp by squeezing locking springs on sides ofswitch and pushing the switch thru the hole in the instrument panel.

040 Replace TREND switch or ENGINE/TREND Split Lamp and reconnect ConXall™ connector.



7.3 Download Port Removal/Replacement


020 Remove nut and washer from Download Port connector.

030 Disconnect Download Port ConXall™ connector. Remove Download Port.

040 Install Download Port into Instrument Panel and secure in place with washer and nut using Loctite®Blue on the threads of the download port.

050 Reconnect ConXall™ connector.

7.4 Pitot/Static Transducer Removal/Replacement

NOTE: A Pitot/Static Leak test must be done after the replacement of a transducer


020 Refer to Figure A- 14. Disconnect Pitot hose (990-00028) from adaptor (960-00002).

030 Disconnect Tygon tubing from the Pitot Transducer.

040 Disconnect Static hose (990-00028) from “T” pipe (AN917-2D).

050 Remove the pitot and static transducers by removing the bolt, washer, and nut which secures thetwo transducers to the supplied plate (ADAS-D-018-1) and clamp (ADAS-D-019-1).

060 Remove the adapter, (960-00002) from the Pitot Transducer if you are replacing the PitotTransducer or the “T” pipe (AN917-2D) from the Static Transducer if you are replacing the StaticTransducer.

070 Replace the appropriate transducer as necessary.

080 Apply Teflon® tape to the Pitot Transducer threads and install adapter (960-00002) or apply Teflon®tape to the Static Transducer threads and install “T” pipe (AN917-2D).

090 Attach the pitot and static transducers to the supplied plate (ADAS-D-018-1), clamp (ADAS-D-019-1), clamp (MS21919WDG26), bolt (AN3-5A), washer (AN960-10) and lock nut (AN365-1032A).

100 Connect the Pitot hose (990-00028) to the adaptor (960-00002).

110 Connect the Static hose (990-00028) to the “T” pipe (AN917-2D).

120 Connect Tygon tubing to the Pitot Transducer.

130 Secure and tighten all hoses and fittings.

140 Perform Pitot/Static calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1,System Configuration and Calibration.



7.5 OAT Removal/Replacement


020 Remove safety wire from OAT jam nut (TWIN-D-061-1).

030 Remove OAT jam nut.

040 Remove temperature probe from hole.

050 Insert new temperature probe into the hole and install washers (AN960-816L), “O” ring (AN6227B-10) and jam nut (TWIN-D-061-1).

060 Tighten and safety wire the jam nut to the bolt P/N AN3-5A.

NOTE: Be sure not to over tighten the jam nut which could damage the O-Ring seal. 070 Apply a bead of sealant (ProSeal PR1422 or equivalent) around edge of doubler after installation

and smooth to produce a filleted profile.

080 Apply a bead of sealant (ProSeal PR1422 or equivalent) around the inner and outer edges of theOAT probe after installation and smooth to produce a filleted profile.

090 Perform OAT calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1, SystemConfiguration and Calibration.

7.6 Torque Transducer Removal/Replacement

NOTE: A Leak test must be done after the replacement of a transducer


020 Referring to Figure A- 16, remove the “T” swivel (960-00006) from the adapter fitting (960-00015).

030 Remove the adapter (960-00015) from the transducer.

040 Remove the transducer from the clamp (MS21919WCJ14).

050 Replace the transducer.

060 Using Teflon® tape, install and torque the 0 – 150 PSIG transducers (750-00005) into the adapterfitting (960-00015).

070 Connect the torque transducer / adapter fitting assembly to the “T” swivel (960-00006).

080 Secure / torque all lines and fittings per the manufacturer’s recommendations.

090 Perform Torque calibration per instructions in ADAS+ Installation Manual ADAS-G-010-1, SystemConfiguration and Calibration.

7.7 Particle Separator Switch Removal/Replacement


020 Remove the nuts (P/N 910-00001), washers (P/N AN960-4), and screws (P/N MS35206-220) fromthe clamps that attach the Magnetic Flange Sensor. Refer to Figure A- 18.

030 Remove Magnetic Flange Sensor (P/N 700-00016).

040 Remove the washers (P/N AN960-4) and screws (P/N MS35206-220) that attach the MagneticSensor Switch to the Switch Plate assembly.

050 Remove the clamps to where the wire splices into the wire bundle.

060 Disconnect the splices and remove the Magnetic Sensor Switch (P/N 700-00015) form the airplane.

070 Replace Magnetic Sensor Switch (P/N 700-00015) and connect to the wire splices.



080 Put the wire into the clamps and install the screws into the clamps.

090 Install the screws (P/N MS35206-220) and washers (P/N AN960-4) that attach the Magnetic SensorSwitch to the Switch Plate assembly.

100 Install the screws (P/N MS35206-220), washers (P/N AN960-4), and nuts (P/N 910-00001) into theclamps and attach the Magnetic Flange Sensor (P/N 700-00016).

NOTE: Additional washers may be installed between switch components and mounting structure asrequired achieving correct alignment. The “Must Operate” distance is 5.71mm and “Release”distance is 20.32mm.

Figure A- 18: Particle Separator Switch (Exploded View)



8 SPECIAL INSPECTION REQUIREMENTS


9 APPLICATION OF PROTECTIVE TREATMENTS


10 DATA

10.1 Parts List

For Cessna Aircraft Company Model Series 208 Series:

The parts listed below consist of the installation kits for the ADAS+ system for the Cessna Model 208 Series.Assembly kit numbers are listed in section 10.1.1 and individual components are detailed by kit numbers insection 10.1.2.10.1.1 ADAS+ by Parts Kits

For Cessna Aircraft Company Model Series 208: Qty P/N ADAS-K-010-2 Weight

Processor Assembly 1 ADAS-K-017-1 1.41 LbsWiring Harness Kit 1 ADAS-K-014-1 5.20 LbsEngine Torque Kit 1 ADAS-K-013-1 1.41 LbsAircraft OAT Kit 1 DPU-K-032-4 0.39 LbsAircraft Pitot Pressure Kit 1 DPU-K-034-4 0.77 LbsAircraft Static Pressure Kit 1 DPU-K-033-5 0.77 LbsCockpit Fault Lamp Assembly Kit 1 DPU-K-046-3 0.20 LbsCockpit Split Lamp and Download Port Kit (OPTIONAL) 1 ADAS-K-047-1 0.20 LbsParticle Separator Switch Kit 1 ADAS-K-070-1 1.04 ozAdditional Installation Materials Kit 1 EMU-K-023-4 0.40 Lbs*Cable Assy, ADAS+ to Garmin G620 (OPTIONAL) 1 ADAS-C-072-1

*Requires ADAS+ Software Version 5.1.0 or Greater*Requires G620 Software Version 6.10 or Greater

10.1.2 Components by Kit

For Cessna Aircraft Company Model Series 208:

PROCESSOR ASSEMBLY KIT ADAS-K-017-1

Processor EMU-A-010-3 Qty 1Mounting Bracket ADAS-D-029-1 Qty 1Clamp, Processor Mounting ADAS-D-030-1 Qty 2Shock Mounts, Lord 990-00020 Qty 4Washer, Processor Mount 920-00006 Qty 4Nut, Locking, Processor Mount MS21042-06 Qty 4Clamp, “U” Bolt NAS-3103-9-10 Qty 2

(Alternate: ADAS-D-016-1)Nut, Locking, Mount MS21042-3 Qty 4Washer, Mount AN960-10L Qty 4Strap, Ground DPU-C-050-3 Qty 1Terminal End, #10 400-00030 Qty 2Terminal End, #6 400-00029 Qty 2



WIRING HARNESS KIT ADAS-K-014-1

Cable Assembly, J1 EMU-C-025-1 Qty 1Cable Assembly, J2 ADAS-C-011-1 Qty 1Cable Assembly, J3 ADAS-C-012-1 Qty 1

ENGINE TORQUE KIT EMU-K-013-1

Transducer, 0 - 100 PSIG 750-00005 Qty 2Adapter, “O” Ring / 37 Flare 960-00015 Qty 2Fitting, “T” Swivel 960-00006 Qty 2Hose, Pressure, 12” AE3663162E0120 Qty 2Clamp MS21919WCJ14 Qty 2Clamp MS21919WCJ16 Qty 2Transducer Harness 750-00006 Qty 2

AIRCRAFT OAT PROBE KIT DPU-K-032-4

Probe, Temperature TWIN-A-050-2 Qty 1Nut, Jam TWIN-D-061-1 Qty 1Washer AN960-816L Qty 2Seal, “O” Ring AN6227B-10 Qty 1Bolt, Drilled AN3H-4A Qty 1Doubler, OAT Probe DPU-D-047-1 Qty 1Washer AN960-10 Qty 1Nut, Fiber Lock AN365-1032A Qty 1Connector, ConXall™ 400-00026 Qty 1Connector, ConXall™ 400-00027 Qty 1

AIRCRAFT PITOT PRESSURE KIT DPU-K-034-4

Transducer, 0-3 PSID 750-00001 Qty 1Clamp, Inlet Pressure Transducer MS21919WDG26 Qty 1Bolt, 10-32 AN3-5A Qty 1Nut, Locking, 10-32 AN365-1032A Qty 1Washer, #10 AN960-10 Qty 2Plate, Mounting ADAS-D-018-1 Qty 1Clamp ADAS-D-019-1 Qty 1Feed Through ADAS-D-033-1 Qty 1Adapter, Pipe – 37 Flare 960-00002 Qty 1Hose, 306 990-00028 Qty 1Fitting, Hose ¼” 960-00027 Qty 1“T”, Barbed ¼” 960-00028 Qty 1



AIRCRAFT STATIC PRESSURE KIT DPU-K-033-5

Transducer, 0-15 PSIA 750-00002 Qty 1Clamp, Nacelle Static Transducer MS21919WDG16 Qty 1Bolt, 10-32 AN3-5A Qty 1Nut, Locking, 10-32 AN365-1032A Qty 1Washer, #10 AN960-10 Qty 1Fitting, ¼ ″ Tube to 1/8 ″ Male thrd 960-00024 Qty 1Tubing, Tygon 1/8 ″ 990-00030 Qty 1 FtInsert 920-00010 Qty 1Bushing ¼ - 1/8 AL AN912-1D Qty 1“T”, 1/4'” Thread AL AN917-2D Qty 1Nipple, Flared Tube ¼” Tube AN816-4-4D Qty 1Hose, 306 990-00028 Qty 1Fitting, Hose ¼” 960-00027 Qty 1“T”, Barbed ¼” 960-00028 Qty 1

COCKPIT FAULT LAMP ASSEMBLY DPU-K-046-3

Assy., Cockpit Fault Lamp DPU-A-043-1 Qty 1Lens TREND-D-041-1 Qty 1Connector, 6 Pin Female 400-00026 Qty 1Assy., Download Port DPU-A-044-1 Qty 1Cover 990-00031 Qty 1Connector, 6 Pin, Male 400-00027 Qty 1Screw, Pan Head, 4-40 900-00009 Qty 1Washer AN960-4 Qty 1Nut, Fiber Lock 910-00001 Qty 1

COCKPIT SPLIT LAMP AND DOWNLOAD PORT KIT (OPTIONAL) ADAS-K-047-1

Assy., Cockpit Split Lamp ADAS-A-043-1 Qty 1Connector, 6 Pin Female 400-00026 Qty 1Assy., Download Port DPU-A-044-1 Qty 1Connector, 6 Pin, Male 400-00027 Qty 1Cover, Receptacle 990-00031 Qty 1Screw, Pan Head, 4-40 900-00009 Qty 1Washer AN960-4 Qty 1Nut, Fiber Lock 910-00001 Qty 1

PARTICLE SEPARATOR SWITCH KIT ADAS-K-070-1

Sensor Magnetic SPST/NO Flange 700-00015 Qty 1Magnet flange Mount 700-00016 Qty 1Screw, #4-40 X 7/8L MS35206-220 Qty 4Mtg Plate, Particle Separator Switch ADAS-D-069-1 Qty 1Clamp, Loop, Cush, 0.25” BLK MS21919WDG8 Qty 2Nut, LCKG, SS, 4-40” 910-00001 Qty 4Washer #4, Flat AN960-4 Qty 20



ADDITIONAL MATERIAL INSTALLATION KIT EMU-K-023-4

Crimp Lug, Alumel 400-00031 Qty 1Crimp Lug, Chromel 400-00032 Qty 1Breaker, 1 Amp 990-00032 Qty 1Fuse, 1.0 Amp 990-00033 Qty 1Holder, Fuse DPU-C-057-1 Qty 1Terminal, ½” 400-00033 Qty 2

*CABLE ASSY, ADAS+ TO GARMIN G620 (OPTIONAL) ADAS-C-072-1

*Requires ADAS+ Software Version 5.1.0 or Greater*Requires G620 Software Version 6.10 or Greater



11 LIST OF SPECIAL TOOLS

ConXall™ connectors are installed in this system. The following tools are recommended by the vendor for usewith these connectors (vendor P/Ns): Insertion Bit (356-20), Pin Removal Bit (356-201), Socket Removal Bit(356-202), Handle (356-1), Crimp Tool (359-21), Locator (357-122). The vendor address is: ConXallCorporation., 601 East Wildwood, Villa Park, IL 60181.

12 FOR COMMUTER CATEGORY AIRCRAFT

For Commuter Category Aircraft, electrical load data applicable for each system and aircraft weight and balancemust be identified. The ADAS+ has a current draw of 300 milliamps at 28V DC. The ADAS+ kit weighs 10.55lbs.

13 RECOMMENDED OVERHAUL PERIODS


14 AIRWORTHINESS LIMITATIONS

The Airworthiness Limitations section is FAA approved and specifies maintenance required under §§ 43.16 and91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are noairworthiness limitations for this equipment.



15 DIAGRAMS

15.1 Power/ Sensor Cable J1, 15 Pin S 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 acable behind a label, be sure to re-label it.

Connector Harness Wired ToPin Wire Color Signal Name Refer to Section 6

4 COND CABLEJ1 A WHT/ORG Pitot (Signal +) GRN Wire Pitot TransducerJ1 B WHT Pitot/Static (5 VDC) RED Wire Pitot/Static TransducerJ1 N WHT/BLU Pitot/Static (Ground) BLK Wire Pitot/Static TransducerJ1 D WHT/GRN Static (Signal +) GRN Wire Static Transducer

1 COND CABLEJ1 F WHT 28 VDC Bus Power Bus Power, Supplied 1 Amp Breaker

2 COND CABLEJ1 H WHT 28 VDC Battery Power Battery Power, 1 Amp Fuse

J1 G WHT/BLU System Ground Aircraft Ground

J1 J UnusedJ1 K UnusedJ1 C UnusedJ1 E UnusedJ1 L UnusedJ1 M UnusedJ1 R UnusedJ1 P Unused



15.2 Sensor Cable J2, 15 Pin SA Keyed Connector




Route all harnesses along existing harnesses wherever possible.



4 COND CABLEJ2 A WHT Eng Torque (5 VDC) RED Wire Both Torque TransducersJ2 B WHT/ORG Eng Torque (Signal +) GRN Wire High Torque TransducerJ2 C WHT/BLU Eng Torque (Ground) BLK Wire Both Torque TransducersJ2 F WHT/GRN Eng Torque (Signal -) GRN Wire Low Torque Transducer

2 COND CABLEJ2 D WHT Eng Ng Spd (Sig +) N1 Tachometer +J2 H WHT/BLU Eng Ng Spd (Sig –) N1 Tachometer –

2 COND CABLEJ2 E WHT Eng Np Spd (Sig +) Np Tachometer +J2 N WHT/BLU Eng Np Spd (Sig –) Np Tachometer –

THERMOCOUPLEJ2 J RED Eng ITT (Alumel –) ITT Engine Mounting Pad –J2 K YEL Eng ITT (Chromel +) ITT Engine Mounting Pad +

2 COND CABLEJ2 G WHT Fuel Flow (Sig +) Fuel Flow Transmitter +J2 R WHT/BLU Fuel Flow (Sig –) Fuel Flow Transmitter –

J2 P Unused



15.3 Cockpit Trend / Sensor Cable, J3, 37 Pin S Keyed Connector




Route all harnesses along existing harnesses wherever possible. Do not connect to enginescavenge lines.



1 COND CABLE-- WHT SW PWR 2 Aircraft Bus Power, Supplied 1 Amp

Breaker

1 COND CABLEJ3 3 WHT Digital 2 Bleed Air – S53

1 COND CABLEJ3 4 WHT Digital 3 EPL (Emergency Power Lever) – S91

1 COND CABLEJ3 5 WHT Digital 4 Particle Separator Switch

4 COND CABLE-- WHT IND SW (VCC) Lamp ConXall™ Pin 1J3 19 WHT/ORG IND SW (Switched) Lamp ConXall™ Pin 4J3 18 WHT/BLU IND SW (GND) Lamp ConXall™ Pin 2J3 1 WHT/GRN IND SW (TREND Switch) Lamp ConXall™ Pin 3

1 COND CABLE (Using Standard Trend Lamp)J3 37 WHT IND SW Open Cap, Coil, and Stow (Near Lamp ConXall™)

1 COND CABLE (Using Optional ENGINE/TREND Split Lamp)J3 37 WHT IND SW Open (Switched) Lamp ConXall™ Pin 5

4 COND CABLEJ3 16 WHT Download Port (RS485+) Download ConXall™ Pin 1J3 17 WHT/ORG Download Port (RS485-) Download ConXall™ Pin 2J3 18 WHT/BLU Download Port (GND) Download ConXall™ Pin 3J3 2 WHT/GRN Download Port (Run/Conf) Download ConXall™ Pin 4



4 COND CABLEJ3 21 WHT Air Temp (“D”) OAT ConXall™ Pin 1J3 22 WHT/BLU Air Temp (“G”) OAT ConXall™ Pin 2J3 23 WHT/ORG Air Temp (“R+”) OAT ConXall™ Pin 3J3 24 WHT/GRN Air Temp (“R–”) OAT ConXall™ Pin 4

4 COND CABLEJ3 31 WHT Vertical Accl. + Terminate and Tie Back (near download port)J3 32 WHT/ORG Vertical Accl. – Terminate and Tie Back (near download port)J3 33 WHT/BLU Vertical Accl. + Terminate and Tie Back (near download port)J3 34 WHT/GRN Vertical Accl - Terminate and Tie Back (near download port)

2 COND CABLEJ3 35 WHT Digital 1 + Hour Meter –J3 36 WHT/BLU Digital 1 - Aircraft Ground

4 WIRE JUMPER7 GRN Configuration Ground Set at Factory11 GRN Configuration ID 0 Set at Factory14 GRN Configuration ID 1 Set at Factory15 GRN Configuration ID 2 Set at Factory

6 Unused8 Unused9 Unused10 Unused13 Unused20 Unused25 Unused26 Unused27 Unused28 Unused29 Unused30 Unused



16 Wiring Diagram

16.1 ADAS+ Connection Chart – Cessna Model 208 Series

Sensor WireNumber

Caravan withElectric Torque System

Caravan withWet Torque System

Aircraft Component ADAS+ Connector Aircraft Component ADAS+ Connector

Aircraft SensorsEngine Assy. Block J2 Engine Assy. Block J2RED Pin J Alumel Red RED Pin J Alumel Red

Engine ITT AAA10B22

YEL Pin K Chromel Yel YEL Pin K Chromel YelJ134 J2 J134 J2Pin B BLK Pin D WHT Pin B BLK Pin D WHT

Engine N1 (Ng) AAP10B22

Pin A WHT Pin H WHT/BLU Pin A WHT Pin H WHT/BLUJ211 J2 P&WES Transducers J2

Pin A WHT Torque RED Wire Pin A WHTPin C Pin B WHT/ORG Torque GRN Wire Pin B WHT/ORG

Pin C WHT/BLU Torque BLK Wire Pin C WHT/BLU

Engine Torque(Tq)Model 208S/N 00007 thru00096

AAA20D22

Pin D Pin F WHT/GRN Torque GRN Wire Pin F WHT/GRNJ211 J2 P&WES Transducers J2

Pin A WHT Torque RED Wire Pin A WHTPin A Pin B WHT/ORG Torque GRN Wire Pin B WHT/ORG

Pin C WHT/BLU Torque BLK Wire Pin C WHT/BLU

Engine Torque(Tq)Model 208S/N 00097 thru00199Model 208BS/N 0001 ANDON

AAA20D22

Pin B Pin F WHT/GRN Torque GRN Wire Pin F WHT/GRN

J34 J2 J34 J2Pin A BLK Pin E WHT Pin A BLK Pin E WHT

Propeller Speed(Np)

AAP11B22

Pin B WHT Pin N WHT/BLU Pin B WHT Pin N WHT/BLUJ5 J2 J5 J2Pin A WHT Pin G WHT Pin A WHT Pin G WHT

Fuel Flow (Wf) AAP00B22

Pin B BLK Pin R WHT/BLU Pin B BLK Pin R WHT/BLUS53 J3 S53 J3Bleed Air AAD11A24NO Pin 3WHT NO Pin 3WHTS91 J3 S91 J3Emergency Power

LeverS/N 00001 Thru00140

AAD18A24C – WH1 Pin 4 WHT C – WH1 Pin 4 WHT

S91 J3 S91 J3Emergency PowerLeverS/N 00141 AND >

AAD18A24C - WH4 Pin 4 WHT C - WH4 Pin 4 WHT

IND12 (Hour Meter) J3 IND12 (Hour Meter) J3J305 – DF7 Pin 35 WHT J305 – DF7 Pin 35 WHT

Hour Meter AAD10B24

Ground Pin 36 WHT/BLU Ground Pin 36 WHT/BLU



Sensor WireNumber




Relay K 3 J1 Relay K 3 J1A2 Pin H WHT A2 Pin H WHT

Battery Power AAV00B22

Ground Pin G WHT/BLU Ground Pin G WHT/BLURelay K 3 J1 Relay K 3 J1Bus Power AAV10A22A1 Pin F WHT A1 Pin F WHT

Sensor WireNumber




P&W Engine Services Supplied Sensors

Oat Probe J3 Oat Probe J3Red Wire Pin 21 WHT Red Wire Pin 21 WHTWht Wire Pin 22 WHT/BLU Wht Wire Pin 22 WHT/BLURed Wire Pin 23 WHT/ORG Red Wire Pin 23 WHT/ORG

OAT Probe AAA00D24

Wht Wire Pin 24 WHT/GRN Wht Wire Pin 24 WHT/GRNTransducers J1 Transducers J1Pitot Grn Wire Pin A WHT/ORG Pitot Grn Wire Pin A WHT/ORGPitot/Static Red Wire Pin B WHT Pitot/Static Red Wire Pin B WHTPitot/Static Blk Wire Pin N WHT/BLU Pitot/Static Blk Wire Pin N WHT/BLU

Airspeed /Altitude Sensor

AAA22D22

Static Grn Wire Pin D WHT/GRN Static Grn Wire Pin D WHT/GRNParticle SeparatorSwitch

J3 Particle SeparatorSwitch

J3

BLK Wire Pin 5 WHT BLK Wire Pin 5 WHTParticle SeparatorSwitch Sensor

AAD16A24

BLK Wire Aircraft Ground BLK Wire Aircraft Ground

Table A- 1: ADAS+ Connection Chart

P&W ENGINE SERVICES, INC. ADAS+ ADAS-G-260-1/ACessna Caravan Model 208 Series

- 30 -ADAS-G-260-1/A Pratt & Whitney Engine Services, Inc. Proprietary

16.2 ADAS+ Interconnect Schematic – No Supplied Torque Transducers

AAV30D24

AAB40D24

123456

123456

AAD18A24

DOWNLOAD PORT ASSEMBLY

Female

N/C

OEM SUPPLIED TRANSDUCER OPTION

WHT/GRN - TREND

SwitchBLKMagnetic ReedBLK

PARTICLE SEPARATOR

AAA24D24

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD

WHTAAD16A24

TRQ 5 VDCTRQ HI SIGTRQ GNDTRQ LO SIG

N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K Transducer

REDBLKGRN

FUSE 1 AMP

1 2

CIRCUIT BREAKER 1 AMP

1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

NP TACH +NP TACH -

AB

FUEL FLOW +FUEL FLOW -

AB

ITT- (AL)ITT+ (CH) .

.

123456

123456

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

J1.10

123456

MICROSWITCH PTT Lamp 1 +Lamp 1 -SW1-NO

SW1-COMMSW1-NCSW2-NO

SW2-COMMSW2-NC

123456

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

Transducer

0-5 VDC

SIG -

SIG +

S53.

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2

CONG GNDCONG ID1CONG ID2CONG ID4

OAT DOAT GOAT R+OAT R-

EPL SIG

HOURMETER +HOURMETER -

BLEED SIG

P/S SIG

Vertical Accl +Vertical Accl SIGVertical Accl -Vertical Accl

J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

(DIRECT BATTERY)

(SWITCHED POWER)

AIRCRAFT PITOT

AIRCRAFT STATIC

ADAS+ PROCESSOREMU-A-010-3

WHT

WHT

WHT

WHT/BLU

WHT/BLU

WHT/BLU

YELRED

N/C

N/C

CONFIGID = 7

WHT/GRN - RUN/CONF

WHT/ORG - RS485 - (A)

CONNECTORCOMM PORT

WHT - LAMP PWR

WHT - RS485 + (B)

WHT/BLU - GND

WHT/ORG - LAMP 1 SW

WHT/BLU - GND

WHT - LAMP 2 SW

WHTWHT/BLU

ENGINE T/C

BLOCK

AIRCRAFT

CONN J134

AIRCRAFT

CONN J34

AIRCRAFT

CONN J5

ESSENTIAL BUS

GROUND STRAPAIRCRAFT

CONN J211

AIRCRAFT BLEED VALVE

BATTERYRELAYK3

WHT

WHT

WHT

WHTWHT/BLU

WHT/BLU

WHT/GRNWHT/ORG

WHT/ORG

WHTWHT/BLU

WHT/GRN

WHT

AIRCRAFT EPL

AAV00B22

AAV10A22

To Bus Breaker

AAP11B22

AAP10B22

AAA22D22

AAA10B22

AAP00B22

AAD10B24

AAA20D22

AAD11A24

AAV32A24

AAA00D24

WHT/BLUWHT/ORG

WHT

WHT/GRN

Male

Female

Female

Male

FAULT LAMP ASSEMBLY Male

CONNECTORFAULT LAMP

WHT

WHT/BLUWHT/ORG

WHT/GRN

N/C

Figure A- 19: Wiring Schematic– No Supplied Torque Transducers



16.3 ADAS+ Interconnect Schematic – Supplied Torque Transducers

123456

DOWNLOAD PORT ASSEMBLY

Female

LOW

HIGH

N/C


AAV30D24

PARTICLE SEPARATOR

AAD16A24

WHT

WHT/GRN - TREND

AAA24D24


N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD


1 2

FUSE 1 AMP

1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

Transducer

REDBLKGRN

NP TACH +NP TACH -

AB

123456


.


AB

123456

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

J1.10

123456

123456

MICROSWITCH PTT Lamp 1 +Lamp 1 -SW1-NO

SW1-COMMSW1-NCSW2-NO

SW2-COMMSW2-NC

S53.

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2



EPL SIG


BLEED SIG

P/S SIG


J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

AIRCRAFT STATIC

AIRCRAFT PITOT

(DIRECT BATTERY)

(SWITCHED POWER)

WHT/GRNWHT/BLU


WHTWHT/ORG

WHT

YELRED

WHT/BLU

WHT/BLU

WHT/BLU

WHT

WHT

CONFIGID = 7

WHT - RS485 + (B)

WHT/BLU - GNDWHT/GRN - RUN/CONF


CONNECTORCOMM PORT

WHT - LAMP 2 SWWHT/ORG - LAMP 1 SW

WHT/BLU - GNDWHT - LAMP PWR

AIRCRAFT

CONN J5

ENGINE T/C

BLOCK

WHT/BLUWHT

WHT


BATTERYRELAYK3

ESSENTIAL BUS

GROUND STRAP

AIRCRAFT

CONN J134

AIRCRAFT

CONN J34 WHT/GRNWHT/ORG

WHTWHT/BLU

WHT/BLUWHT

WHT

WHT/GRNWHT/ORG

WHTWHT/BLU

AIRCRAFT EPL

WHT

AAV00B22

AAV10A22

To Bus Breaker

AAB40D24

AAD10B24

AAA20D22

AAA10B22

AAP00B22

AAP11B22

AAP10B22

AAA22D22

AAA00D24

AAD18A24

AAD11A24

AAV32A24

WHTWHT/BLUWHT/ORGWHT/GRN

Transducer

RED

GRNBLK

Male

Transducer

RED

BLKGRN

Female

FemaleMale

N/C

ENGINETORQUE

FAULT LAMP ASSEMBLY

CONNECTORFAULT LAMP

Male

123456

Figure A- 20: Wiring Schematic – Supplied Torque Transducers



16.4 ADAS+ Interconnect Schematic (Split Lamp Option) – No Supplied Torque Transducers

AAV30D24

OEM SUPPLIED TRANSDUCER OPTION

WHT/GRN - TREND

AAA24D24

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD


N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K Transducer

REDBLKGRN

FUSE 1 AMP

1 2


1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

NP TACH +NP TACH -

AB


AB


.

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

Transducer

0-5 VDC

SIG -

SIG +

S53.

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2



EPL SIG


BLEED SIG

P/S SIG


J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

DIRECT BATTERY

SWITCHED POWER

AIRCRAFT PITOT

AIRCRAFT STATIC


WHT

WHT

WHTWHT/BLU

WHT/BLU

YELRED

WHT/BLU

N/C

N/C

CONFIGID = 7

WHT/GRN - RUN/CONF

WHT/ORG - RS485 - (A)WHT - RS485 + (B)

WHT/BLU - GND

WHT/ORG - LAMP 1 SW

WHT/BLU - GNDWHT - LAMP PWR

WHT - LAMP 2 SW

WHTWHT/BLU

ENGINE T/C

BLOCK

AIRCRAFT

CONN J134

AIRCRAFT

CONN J34

AIRCRAFT

CONN J5

GROUND STRAPAIRCRAFT

CONN J211

AIRCRAFT BLEED VAVE

BATTERYRELAYK3

ESSENTIAL BUS

WHT

WHT

WHT

WHT/BLU

WHT/BLU

WHT/GRNWHT/ORG

WHT

WHT/ORG

WHTWHT/BLU

WHT/GRN

WHT

AIRCRAFT EPL

AAV00B22

AAV10A22

To Bus Breaker

AAP10B22

AAA22D22

AAA10B22

AAP00B22

AAP11B22

AAD10B24

AAA20D22

AAD11A24

AAV32A24

AAA00D24

AAD18A24

WHT/ORG

WHT

WHT/GRN

WHT/BLU

FemaleMale

WHT/BLUWHT/ORGWHT

WHT/GRN

123456

123456

AAB40D24

COMM PORT

123456

123456

J1.10J1.9J1.8J1.7J1.6J1.5J1.4J1.3J1.2J1.1

SPLIT LAMP

123456

123456

MICROSWITCH PTTLamp +Lamp -

SW1-NOSW1-COMM

SW1-NCSW2-NO

SW2-COMMSW2-NCLamp 2 +Lamp 2 -

Female Male

Male Female

CONNECTOR

COMM PORT

CONNECTOR

SPLIT LAMP


PARTICLE SEPARATOR

WHTAAD16A24

N/C

Figure A- 21: Wiring Schematic (Split Lamp Option) – No Supplied Torque Transducers



16.5 ADAS+ Interconnect Schematic (Split Lamp Option) – Supplied Torque Transducers


PARTICLE SEPARATOR

HIGH

LOW

123456

AAV30D24

WHT/GRN - TREND

123456

Male

AAA24D24

28 VDC PWR

28 VDC BATTGND

P/S 5 VDCP/S GND

PITOT SIGSTATIC SIG

J1 - 15 S

F

HG

BNAD


N2 SPD -

FUEL FLOW -

N1 SPD -N1 SPD +

N2 SPD +

ITT- (AL)

FUEL FLOW +

ITT+ (CH)

J2 - 15 SA

ABCF

E

D

N

GR

J

H

K Transducer

REDBLKGRN

FUSE 1 AMP

1 2


1 2

Transducer

REDBLKGRN

N1 TACH +N1 TACH -

AB

NP TACH +NP TACH -

AB


AB


.

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

S53.

S91

AC HOURMETER IND12

+ -

RUN/CONF SW

RS-485+ (B)RS-485- (A)GND

TREND SW

VCCGND

LAMP 1LAMP 2



EPL SIG


BLEED SIG

P/S SIG


J3 - 37 S

2

161718

119

78910

37

21222324

4

3536

3

5

3433

3132

AAV31A22

AAV31A22

(SWITCHED POWER)

(DIRECT BATTERY)

AIRCRAFT PITOT

AIRCRAFT STATIC


WHT/BLUWHT/GRN

WHT/ORGWHT

WHT

WHT

WHT

WHT/BLU

WHT/BLU

WHT/BLU

REDYEL

CONFIGID = 7


WHT/GRN - RUN/CONFWHT/BLU - GND

WHT - RS485 + (B)

WHT - LAMP PWR

WHT - LAMP 2 SW

WHTWHT/BLU

ENGINE T/C

BLOCK

AIRCRAFT

CONN J5

AIRCRAFT

CONN J34

AIRCRAFT

CONN J134

GROUND STRAP

ESSENTIAL BUS

BATTERYRELAYK3


WHT

WHT

WHTWHT/BLU

WHT/BLUWHT

WHT/ORGWHT/GRN

WHT/BLUWHT

WHT/ORGWHT/GRN

WHT

AIRCRAFT EPL

To Bus Breaker

AAV10A22

AAV00B22

AAA22D22

AAP10B22

AAP11B22

AAP00B22

AAA10B22

AAA20D22

AAD10B24

AAV32A24

AAD11A24

AAD18A24

AAA00D24

AAD16A24

WHT

WHT

WHT/ORGWHT/BLU

WHT/GRN

Transducer

RED

GRNBLK

Transducer

RED

BLKGRN

Female

ENGINETORQUE

WHT/BLU - GND

AAB40D24

COMM PORT

123456

123456

J1.10J1.9J1.8J1.7J1.6J1.5J1.4J1.3J1.2J1.1

SPLIT LAMP

123456

123456

MICROSWITCH PTTLamp +Lamp -

SW1-NOSW1-COMM

SW1-NCSW2-NO

SW2-COMMSW2-NCLamp 2 +Lamp 2 -

N/C

WHT/ORG - LAMP 1 SW

MaleFemale

FemaleMale

CONNECTOR

COMM PORT

CONNECTOR

SPLIT LAMP

Figure A- 22: Wiring Schematic (Split Lamp Option) – Supplied Torque Transducer



16.6 ADAS+ Schematic (Garmin G620 Option) – No Supplied Torque Transducers

Figure A- 23: Wiring Schematic (Garmin G620 Option) – No Supplied Torque Transducers



16.7 ADAS+ Schematic (Garmin G620 Option) – Supplied Torque Transducers

Figure A- 24: Wiring Schematic (Garmin G620 Option) – Supplied Torque Transducers



16.8 ADAS+ Schematic (Garmin G620 / Split Lamp Option) – No Supplied Torque Transducers

Figure A- 25: Wiring Schematic (Garmin G620 / Split Lamp Option) – No Supplied Torque Transducers



16.9 ADAS+ Schematic (Garmin G620 / Split Lamp Option) – Supplied Torque Transducers

Figure A- 26: Wiring Schematic (Garmin G620 / Split Lamp Option) – Supplied Torque Transducers

pratt & whitney engine services, inc. norwood, ma 02062 · p&w engine services, inc. adas+...

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