TWIN-T-260-1 Rev H - Altair Avionics Ground Station Rev H.pdf · 2.1 AIRCRAFT DATA ACQUISITION SYSTEM ... TWIN-T-260-1 Pratt & Whitney Engine Services, Inc. Proprietary ... 72 16.14

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

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

ADAS/ADAS+ UpgradeInstructions for Continued Airworthiness

TWIN-T-260-1

For Raytheon Model 200, 300, and 1900 Series

Manual Number: TWIN-T-260-1

Preparation Date: November 13, 1999 Prepared By: D Desaulnier

Release Date: April 19, 2000 D Fetherston, Manager of Engineering

Revision Date: February 26, 2009 S Sackos, Manager of Manufacturing Services

Revision Ltr: H

Total Pages: 75

Approvals:

P&W ENGINE SERVICES, INC. ADAS/ADAS+ Upgrade TWIN-T-260-1Raytheon Aircraft Company Model 200, 300, & 1900 Series

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PREFACE

Disclaimer

Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADAS/ADAS+ Upgrade requires knowledgeableinterpretation by the pilot. Any recommendations and operating procedures contained in this manual shall not supersede theAircraft or Engine manufacturer recommendations, operating procedures, or limits. The Pratt & Whitney Engine Services,Inc. ADAS/ADAS+ Upgrade should not be used as a primary guide monitoring the Aircraft and Engine manufacturersoperating 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 Pratt & Whitney Engine Services, Inc.


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REVISION HISTORY

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

Rev H H H H H H H H H H H H H H H HSheet 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26Rev H H H H H H H H H H H H H H H H

Sheet 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42Rev H H H H H H H H H H H H H H H H

Sheet 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58Rev H H H H H H H H H H H H H H H H

Sheet 59 60 61 62 63 64 65 66 67 68 69 70 71 72 73 74Rev H

Sheet 75

LOG OF REVISIONS

REV. NO ECO# DESCRIPTION DATE PAGES REVISED

A Initial Release 04/19/00

C02120246

Incorporate models 200 and 300 Series aircraftinto the manual. Add Component Weights.

Revise Connection Charts and Signal Pin-outs.03/19/01

Sections 2.2 – 3.1 – 4.7 –4.8 – 4.9 – 4.10 – 4.11 –

4.16 – 4.17 - 4.18

D 0230Clerical changes to simplify manual

organization, improve ease of use, removeredundancy, and correct typographic errors.

05/15/01 All

E05220531

Add new fuse holder, DPU-C-057-1.Add description and drawing of a new highprecision, torque transducer. Change Adel

Torque sensor clamps to high temp WCJ series.Remove the PRC potting from kits.

06/27/01Sections 3.1.3 – 7.1 – 7.2 -

10

F 0540Revised connections to pins C and F on both J2

and J3 connectors.11/02/01 Section 5

G 765New ICA Format

Add Revision Section. Revise Battery PowerConnection.

07/22/05 All

H 997

Updated company name and address, format ofmanual, part numbers in the parts lists, text and

drawings, typographical errors, spelling andgrammar. Added notes indicating the Vertical

Accelerometer is no longer available.

02/26/09 All

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/ADAS+ Upgrade Instructions forContinued Airworthiness are revised, all operators will be provided with a copy of the applicablerevision. If you have a subscription with TurbineTracker™, you will be informed via email of newrevisions to this manual. In addition to this, P&W Engine Services maintains the latest versionsof all manuals in the Support Section of TurbineTracker.

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


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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

2.1 AIRCRAFT DATA ACQUISITION SYSTEM (ADAS/ADAS+ UPGRADE) GENERAL DESCRIPTION ............. 22.2 SYSTEM PROCESSOR................................................................................................................................ 42.3 INDICATING / CONTROL COMPONENTS ................................................................................................... 6

2.3.1 Trend Switch / Fault Lamp.............................................................................................................. 62.3.2 Circuit Breaker (+28 VDC) ............................................................................................................ 62.3.3 Fuse (+28 VDC).............................................................................................................................. 62.3.4 Communications (COMM) Port...................................................................................................... 6

2.4 AIRFRAME COMPONENTS ........................................................................................................................ 62.4.1 Outside Air Temperature (OAT) Probe........................................................................................... 62.4.2 Pitot/Static Pressure Transducers................................................................................................... 72.4.3 Vertical Accelerometer.................................................................................................................... 82.4.4 Firewall/Pressure Bulkhead Feedthru ............................................................................................ 82.4.5 Discrete Aircraft Signals................................................................................................................. 8

2.5 ENGINE INDICATING COMPONENTS ........................................................................................................ 82.5.1 Engine Temperature Sensors (T4, T4.5, ITT, EGT, MGT, TOT) .................................................... 82.5.2 Engine N1 (Ng) Speed Sensor ......................................................................................................... 82.5.3 Engine N2 Speed Sensor ................................................................................................................. 92.5.4 Propeller (Np) Speed Sensor........................................................................................................... 92.5.5 Engine Torque (Tq) Pressure.......................................................................................................... 9

3 CONTROL AND OPERATION INFORMATION........................................................................... 9

3.1 CAPABILITIES .......................................................................................................................................... 93.1.1 Engine Run Logging...................................................................................................................... 103.1.2 Cycle Logging ............................................................................................................................... 103.1.3 Event Monitoring........................................................................................................................... 103.1.4 Initialization .................................................................................................................................. 113.1.5 SYSTEM MODES .......................................................................................................................... 113.1.6 Run Mode FOR ADAS ONLY........................................................................................................ 123.1.7 Lamp States in Run Mode FOR ADAS ONLY:.............................................................................. 123.1.8 Configuration Mode FOR ADAS ONLY........................................................................................ 133.1.9 Manual Self Test (Loopback Test) FOR ADAS ONLY .................................................................. 133.1.10 Run Mode FOR ADAS+ UPGRADE ONLY.................................................................................. 133.1.11 LAMP STATES IN Run Mode FOR ADAS+ UPGRADE ONLY ................................................... 14

4 SERVICING INFORMATION......................................................................................................... 15

5 MAINTENANCE INSTRUCTIONS ................................................................................................ 15

5.1 RECOMMENDED PERIODIC SCHEDULED SERVICING TASKS.................................................................. 15


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5.2 RECOMMENDED PERIODIC SCHEDULED PREVENTIVE MAINTENANCE TESTS/CHECKS ........................ 155.3 RECOMMENDED PERIODIC SCHEDULED INSPECTIONS .......................................................................... 15

5.3.1 System Processor........................................................................................................................... 155.3.2 TREND Switch / Fault Lamp and Download Port ........................................................................ 165.3.3 Pitot / Static Transducers.............................................................................................................. 185.3.4 Outside Air Temperature Probe.................................................................................................... 195.3.5 Torque Transducer........................................................................................................................ 195.3.6 J1, J2, and J3 Harnesses............................................................................................................... 205.3.7 System Test .................................................................................................................................... 20

5.4 RECOMMENDED PERIODIC STRUCTURAL INSPECTIONS ........................................................................ 215.4.1 System Processor........................................................................................................................... 215.4.2 TREND Switch / Fault Lamp and Download Port ........................................................................ 215.4.3 Pitot / Static Transducers.............................................................................................................. 245.4.4 Outside Air Temperature Probe.................................................................................................... 255.4.5 Torque Transducer........................................................................................................................ 26

6 SYSTEM TROUBLESHOOTING.................................................................................................... 27

6.1 SYSTEM PROCESSOR.............................................................................................................................. 286.1.1 Processor Test ............................................................................................................................... 296.1.2 Download Port Test ...................................................................................................................... 306.1.3 Cockpit Fault Lamp Display Test.................................................................................................. 316.1.4 Torque Transducer and Channel Test........................................................................................... 326.1.5 Pitot / Static Transducer and Channel Test .................................................................................. 336.1.6 Outside Air Temperature Test ....................................................................................................... 346.1.7 P&W Engine Services Voltage to Frequency Converter............................................................... 366.1.8 Additional Aircraft Signals............................................................................................................ 36

7 REMOVAL AND REPLACEMENT INFORMATION................................................................. 37

7.1 PROCESSOR REMOVAL/REPLACEMENT ................................................................................................. 377.2 TREND SWITCH REMOVAL/REPLACEMENT ......................................................................................... 377.3 DOWNLOAD PORT REMOVAL/REPLACEMENT....................................................................................... 387.4 PITOT/STATIC TRANSDUCER REMOVAL/REPLACEMENT ...................................................................... 387.5 OAT REMOVAL/REPLACEMENT............................................................................................................ 397.6 TORQUE TRANSDUCER REMOVAL/REPLACEMENT ............................................................................... 39

8 SPECIAL INSPECTION REQUIREMENTS ................................................................................. 40

9 APPLICATION OF PROTECTIVE TREATMENTS.................................................................... 40

10 DATA................................................................................................................................................... 40

10.1 PARTS LIST ............................................................................................................................................ 4010.1.1 Part Kits by Aircraft for ADAS ONLY: ......................................................................................... 4010.1.2 Part Kits By Aircraft for ADAS+ Upgrade ONLY:....................................................................... 4310.1.3 Components for ADAS and ADAS+ Upgrade by Kit Number ...................................................... 46

11 LIST OF SPECIAL TOOLS.............................................................................................................. 51

12 FOR COMMUTER CATEGORY AIRCRAFT .............................................................................. 51

13 RECOMMENDED OVERHAUL PERIODS .................................................................................. 51


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14 AIRWORTHINESS LIMITATIONS ............................................................................................... 51

15 DIAGRAMS ........................................................................................................................................ 52

15.1 ADAS CONNECTOR SIGNAL POINTS ..................................................................................................... 5215.1.1 Power/ Sensor Cable J1, 15 Pin S Keyed Connector.................................................................... 5215.1.2 Sensor Cable J2, 15 Pin SA Keyed Connector .............................................................................. 5315.1.3 Cockpit Trend / Sensor Cable, J3, 37 Pin S Keyed Connector ..................................................... 5415.1.4 COMM CABLE HARNESS............................................................................................................ 55

15.1.4.1 COCKPIT TREND SWITCH HARNESS – SINGLE DISPLAY ........................................ 5515.1.4.2 COCKPIT TREND SWITCH HARNESS – DUAL DISPLAY ........................................... 55

15.2 ADAS+ UPGRADE CONNECTOR SIGNAL POINTS .................................................................................. 5615.2.1 Power/ Sensor Cable J1, 15 Pin S Keyed Connector.................................................................... 5615.2.2 Sensor Cable J2, 15 Pin SA Keyed Connector .............................................................................. 5715.2.3 Cockpit Trend / Sensor Cable, J3, 37 Pin S Keyed Connector ..................................................... 5815.2.4 COMM CABLE HARNESS............................................................................................................ 59

15.2.4.1 COCKPIT TREND SWITCH HARNESS – SINGLE DISPLAY ........................................ 5915.2.4.2 COCKPIT TREND SWITCH HARNESS – DUAL DISPLAY ........................................... 59

16 WIRING DIAGRAM ......................................................................................................................... 60

16.1 ADAS/ADAS+ UPGRADE CONNECTION CHART – 1900 & 1900C ....................................................... 6016.2 ADAS/ADAS+ UPGRADE CONNECTION CHART – 1900D.................................................................... 6116.3 ADAS/ADAS+ UPGRADE CONNECTION CHART – 200 & 200T ........................................................... 6216.4 ADAS/ADAS+ UPGRADE CONNECTION CHART – 200CT, A200, A200C, & A200CT........................ 6316.5 ADAS/ADAS+ UPGRADE CONNECTION CHART – B200C, B200CT, B200, & B200T ........................ 6416.6 ADAS/ADAS+ UPGRADE CONNECTION CHART – 300 ........................................................................ 6516.7 ADAS/ADAS+ UPGRADE CONNECTION CHART – B300...................................................................... 6616.8 ADAS/ADAS+ UPGRADE CONNECTION CHART – B300C & 300LW .................................................. 6716.9 ADAS - WIRING DIAGRAM NO. 1 ......................................................................................................... 6816.10 ADAS - WIRING DIAGRAM NO. 2 ......................................................................................................... 6916.11 ADAS - WIRING DIAGRAM NO. 3 ......................................................................................................... 7016.12 ADAS - WIRING DIAGRAM NO. 4 ......................................................................................................... 7116.13 ADAS+ UPGRADE - WIRING DIAGRAM NO. 1 ...................................................................................... 7216.14 ADAS+ UPGRADE - WIRING DIAGRAM NO. 2 ...................................................................................... 7316.15 ADAS+ UPGRADE - WIRING DIAGRAM NO. 3 ...................................................................................... 7416.16 ADAS+ UPGRADE - WIRING DIAGRAM NO. 4 ...................................................................................... 75

LIST OF FIGURES

FIGURE 1: CAPABILITIES OF DATA TRANSMISSION SYSTEM...................................................................................................... 3FIGURE 2: PROCESSOR .............................................................................................................................................................. 4FIGURE 3: TYPICAL AVIONICS COMPARTMENT SHOCK MOUNT DETAIL ................................................................................... 5FIGURE 4: TYPICAL ENGINE COMPARTMENT SHOCK MOUNT DETAIL ...................................................................................... 5FIGURE 5: TREND SWITCH/FAULT LAMP................................................................................................................................. 6FIGURE 6: COMMUNICATIONS PORT.......................................................................................................................................... 6FIGURE 7: OAT PROBE ............................................................................................................................................................. 7FIGURE 8: PITOT TRANSDUCER ................................................................................................................................................. 7FIGURE 9: STATIC TRANSDUCER ............................................................................................................................................... 7FIGURE 10: VERTICAL ACCELEROMETER .................................................................................................................................. 8FIGURE 11: TORQUE TRANSDUCER ........................................................................................................................................... 9FIGURE 12: BRACKET TO AVIONICS TRAY MOUNTING ........................................................................................................... 16


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FIGURE 13: ADAS TREND SWITCH AND DOWNLOAD PORT (DISCRETE MOUNT) ................................................................. 16FIGURE 14: ADAS TREND SWITCH / FAULT LAMP & DOWNLOAD PORT (CENTER CONSOLE MOUNT)................................. 16FIGURE 15: ADAS+ UPGRADE TREND SWITCH AND DOWNLOAD PORT (DISCRETE MOUNT) ............................................... 17FIGURE 16: ADAS+ UPGRADE TREND SWITCH / FAULT LAMP & DOWNLOAD PORT (CENTER CONSOLE MOUNT) .............. 17FIGURE 17: TREND SWITCH/FAULT LAMP CONNECTOR ........................................................................................................ 17FIGURE 18: DOWNLOAD PORT CONNECTOR ............................................................................................................................ 18FIGURE 19: PITOT / STATIC TRANSDUCER INSTALLATION ....................................................................................................... 18FIGURE 20: PITOT/STATIC WIRING.......................................................................................................................................... 19FIGURE 21: OAT PROBE WIRING ............................................................................................................................................ 19FIGURE 22: TORQUE TRANSDUCER WIRING ............................................................................................................................ 20FIGURE 23: PROCESSOR MOUNTING CONFIGURATION ............................................................................................................ 21FIGURE 24: ADAS TREND SWITCH AND DOWNLOAD PORT (DISCRETE MOUNT) ................................................................. 22FIGURE 25: ADAS TREND SWITCH / FAULT LAMP & DOWNLOAD PORT (CENTER CONSOLE MOUNT)................................. 22FIGURE 26: ADAS+ UPGRADE TREND SWITCH AND DOWNLOAD PORT (DISCRETE MOUNT) ............................................... 23FIGURE 27: ADAS+ UPGRADE TREND SWITCH / FAULT LAMP & DOWNLOAD PORT (CENTER CONSOLE MOUNT) .............. 23FIGURE 28: PITOT/STATIC INSTALLATION (SIDE VIEW) .......................................................................................................... 24FIGURE 29: OAT PROBE ILLUSTRATION ................................................................................................................................. 25FIGURE 30: TORQUE TRANSDUCER INSTALLATION CONFIGURATION...................................................................................... 26FIGURE 31: SYSTEM PROCESSOR START UP TEST FLOW DIAGRAM ........................................................................................ 28FIGURE 32: SYSTEM PROCESSOR TEST FLOW DIAGRAM ......................................................................................................... 29FIGURE 33: DOWNLOAD PORT TEST FLOW DIAGRAM ............................................................................................................. 30FIGURE 34: COCKPIT FAULT LAMP AND DOWNLOAD PORT WIRING ....................................................................................... 30FIGURE 35: COCKPIT FAULT LAMP TEST FLOW DIAGRAM ...................................................................................................... 31FIGURE 36: TORQUE TRANSDUCER TEST FLOW DIAGRAM...................................................................................................... 32FIGURE 37: TORQUE WIRING .................................................................................................................................................. 32FIGURE 38: PITOT / STATIC TRANSDUCER TEST FLOW DIAGRAM ........................................................................................... 33FIGURE 39: PITOT / STATIC WIRING ........................................................................................................................................ 33FIGURE 40: ADAS OAT PROBE TEST FLOW DIAGRAM .......................................................................................................... 34FIGURE 41: ADAS OAT WIRING ............................................................................................................................................ 34FIGURE 42: ADAS+ UPGRADE OAT PROBE TEST FLOW DIAGRAM........................................................................................ 35FIGURE 43: ADAS+ UPGRADE OAT WIRING ......................................................................................................................... 35FIGURE 44: VOLTAGE TO FREQUENCY CONVERTERS .............................................................................................................. 36FIGURE 45: ADAS – WITH TORQUE TRANSDUCERS AND WITHOUT VOLTAGE TO FREQUENCY CONVERTER .......................... 68FIGURE 46: ADAS – WITHOUT TORQUE TRANSDUCERS AND WITHOUT VOLTAGE TO FREQUENCY CONVERTER ................... 69FIGURE 47: ADAS – WITH TORQUE TRANSDUCERS AND WITH VOLTAGE TO FREQUENCY CONVERTER ................................ 70FIGURE 48: ADAS – WITH TORQUE TRANSDUCERS AND WITH VOLTAGE TO FREQUENCY CONVERTER ................................ 71FIGURE 49: ADAS+ UPGRADE – WITH TORQUE TRANSDUCERS AND WITHOUT VOLTAGE TO FREQUENCY CONVERTER ....... 72FIGURE 50: ADAS+ UPGRADE – WITHOUT TORQUE TRANSDUCERS AND WITHOUT VOLTAGE TO FREQUENCY CONVERTER. 73FIGURE 51: ADAS+ UPGRADE – WITH TORQUE TRANSDUCERS AND WITH VOLTAGE TO FREQUENCY CONVERTER.............. 74FIGURE 52: ADAS+ UPGRADE – WITHOUT TORQUE TRANSDUCERS AND WITH VOLTAGE TO FREQUENCY CONVERTER ....... 75

LIST OF TABLES

TABLE 1: PITOT TRANSDUCER SPECIFICATIONS ........................................................................................................................ 7TABLE 2: STATIC TRANSDUCER SPECIFICATIONS ...................................................................................................................... 8TABLE 3: TORQUE TRANSDUCER SPECIFICATIONS .................................................................................................................... 9


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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+ Upgrade. Any deviation from the proceduresdescribed within this document could result in a failure of the product to perform properly and couldpossibly result in damage to other systems of the aircraft.

1.2 Applicability

This document applies to aircraft that have P&W Engine Services’ ADAS/ADAS+ Upgrade monitorsinstalled.

1.3 Definitions and Abbreviations

ADAS – Aircraft Data Acquisition SystemICA – 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

TWIN-I-010-1 Installation Manual for Raytheon 200, 300, and 1900 Series aircraft

1.7 Distribution

These Instructions for Continued Airworthiness is to be furnished with ADAS/ADAS+ Upgrade enginetrend monitors for Raytheon Aircraft Model 200, 300, and 1900 Series aircraft and is to become part ofthe permanent aircraft record upon installation.



2 DESCRIPTION

2.1 Aircraft Data Acquisition System (ADAS/ADAS+ Upgrade) GeneralDescription

Aircraft and engine maintenance procedures are critical to flight safety and lower operating costs. P&WEngine Services has developed an aircraft data acquisition system known as the ADAS/ADAS+ Upgradeto perform three primary functions:

Exceedance Event Recording: The ADAS/ADAS+ Upgrade can monitor critical engine parametersand record instances where they have exceeded preset values (exceedances).

Engine Trend Monitoring: The ADAS/ADAS+ Upgrade can gather and store engine data samplesfor trend analysis.

Cockpit Indication: The ADAS/ADAS+ Upgrade can be configured to warn the pilot of a priorexceedance on start up or shutdown, and provide system self-test indication.

The ADAS+ Upgrade enables the operator to control, quantify, and manage engine maintenanceoperations and reduce direct operating costs.

In its data acquisition role, ADAS/ADAS+ Upgrade is a passive receiver of information. It can beconfigured to record data either manually or automatically.

Manual Operation: The pilot can quickly record a dataset from all sensors by pressing a cockpit-mounted trend button.

Automatic Operation: The system may be configured to automatically record exceedance eventsand trends. It may also be configured to record data samples when stable aircraft conditions areachieved. These conditions are configurable, and the data gathered may be used for engine trendanalysis.

Retrieving Data: Collected data is accessed through a download serial port. Communication withthe ADAS/ADAS+ Upgrade is achieved through P&W Engine Services’ Monitor Link Program(MLP), which can be used to download data and upload system configuration files. The MLP canalso be used to assist maintenance personnel in performing system diagnostics, calibrations, and real-time live sensor display.

System Configuration: The ADAS/ADAS+ Upgrade system is shipped with a predefined set ofsoftware sensor configurations, exceedance event specifications, cycle specifications, and enginestart/stop definitions. System configurations can be altered to reflect the customer’s operatingenvironment or requirements.



Figure 1: Capabilities of Data Transmission System



2.2 System Processor

The processor (Figure 2) collects and interprets data from airframe and engine mounted components.Data is retrieved by the operator through an RS485 cockpit interface connection. The processor does notrequire access during flight.

The processor measures 3.7” high by 6.9” long by 2.7” deep and weighs 2.3 lbs. An aluminum bracketwith Lord Aerospace shock mounts is used to mount the processor to the aircraft.

Figure 2: Processor

The system processor is mounted in a remote area of the aircraft using the P&W Engine Services suppliedmounting brackets (Figure 3 and Figure 4). Although the processor will not require access during normaloperation, care should be taken to install the processor in an area that complies with the environmentalrequirements of the system.



Figure 3: Typical Avionics Compartment Shock Mount Detail

Figure 4: Typical Engine Compartment Shock Mount Detail



2.3 Indicating / Control Components

Following are the descriptions and functions of the control components and indicators.

2.3.1 Trend Switch / Fault Lamp

The TREND switch / fault lamp (Figure 5) consists of a .75˝ x .75˝ square push-to-test combination lamp.The lamp is mounted on the console and is used to initiate a processor loop back test or initiate a manualtrend sample. Fault indications are displayed to the operator through the on/off or flashing status of thelamp

Figure 5: TREND Switch/Fault Lamp

2.3.2 Circuit Breaker (+28 VDC)

Automatically interrupts the electrical circuit under abnormal conditions. This connection is made toaircraft primary bus power that should be active whenever the aircraft battery switch is activated.

2.3.3 Fuse (+28 VDC)

Automatically interrupts the electrical circuit when the electrical current exceeds the specified amperage.This connection is made directly to the aircraft battery and must have power at all times.

2.3.4 Communications (COMM) Port

Used to interface with the processor. Data can be transferred and downloaded through this port (Figure6).

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 Outside Air Temperature (OAT) Probe

The temperature probe (Figure 7) is mounted on the underside of the aircraft to provide the processor withOAT data.



Figure 7: OAT Probe

2.4.2 Pitot/Static Pressure Transducers

Airspeed and altitude are calculated by installing a 5 VDC, 0-3 PSID transducer and 0-15 PSIAtransducer that can be mounted directly in-line with the existing pitot/static system. Illustrations in Figure8 and Figure 9 are typical representations of P&W Engine Services supplied Pitot/Static Transducers.Refer to Table 1 and Table 2 for transducer specifications.

Figure 8: Pitot Transducer

Table 1: Pitot Transducer Specifications

Pressure Range 0-3 PSID

Supply Current 5mA Max. @ 5VDC

Supply Voltage 5.00 VDC

Output Voltage 0.5 – 4.5 VDC

Range 0 PSID (0 Knots) to 3.00 PSID (340 Knots)

Hysteresis &Repeatability

+/- .05% of Span MAX

Weight 4.1 oz

Figure 9: Static Transducer



Table 2: Static Transducer Specifications

Pressure Range 0 – 15 PSIA

Supply Current 5mA Max @ 5 VDC



Range 3.4 PSIA (35000Ft) to 15.00 PSIA (-568 Ft)



Weight 2.7 oz

2.4.3 Vertical Accelerometer

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009.

The system uses a +/- 5g accelerometer (Figure 10), typically mounted aft of the spar, to monitorexceedances such as hard landings and/or excessive in-flight structural loads.

Figure 10: Vertical Accelerometer

2.4.4 Firewall/Pressure Bulkhead Feedthru

When the wiring from the engine compartment to the cockpit passes thru a firewall the wiring is routedthru a stainless steel feedthru and sealed with a high temperature resistant potting compound. When thewiring from the engine compartment to the cockpit passes a pressure bulkhead, a Raychem™ pressurebulkhead fitting is used.

2.4.5 Discrete Aircraft Signals

The ADAS/ADAS+ Upgrade comes equipped with thirteen discrete sensors that can be configured tomeasure bleed air position, particle separator position, weight on wheels, hour meter, landing gearposition, emergency power lever position, flap position, etc.

2.5 Engine Indicating Components

The following is a list of individual engine performance indicating components:

2.5.1 Engine Temperature Sensors (T4, T4.5, ITT, EGT, MGT, TOT)

The processor determines the temperature for each engine through a connection at the aircraft enginetemperature indicator. The ADAS/ADAS+ connects to the existing aircraft sensor by using the suppliedalumel and chromel terminal connectors.

2.5.2 Engine N1 (Ng) Speed Sensor

The processor determines engine N1 (Ng) speed(s) through spliced connections to the sensor inputs of theexisting N1 cockpit indicator or engine tachometer.



2.5.3 Engine N2 Speed Sensor

The processor determines engine N2 speed(s) through spliced connections to the sensor inputs of theexisting N2 cockpit indicator or engine tachometer.

2.5.4 Propeller (Np) Speed Sensor

The processor determines propeller (Np) speed(s) by way of a splice at either the cockpit indicator or theengine sensor input of the existing Np cockpit indicator or engine tachometer.

2.5.5 Engine Torque (Tq) Pressure

The processor has two ways of measuring aircraft torque. The first option is to install P&W EngineServices supplied pressure transducers (Figure 11) on the engine. The second option is to read the signaldirectly from the cockpit gauge. Refer to Table 3 for transducer specifications.

Figure 11: Torque Transducer

Table 3: Torque Transducer Specifications

Pressure Range 0-150 PSIG

Supply Current 5mA Max. @ 5VDC



Range 0.5 VDC at 0 PSI

4.5 VDC at Full Scale



Weight 2.7 oz

3 CONTROL AND OPERATION INFORMATION

3.1 Capabilities

For All Aircraft Models:

The ADAS/ADAS+ Upgrade is an instrument that gathers and records engine information from sensorsfor later retrieval. The ADAS/ADAS+ Upgrade are designed to perform the following functions:

Sensor Monitoring

Event Monitoring

Engine Run Logging

Trend Data Collection

Status Display

Operator Initiated Self-Test



Automatic Self-Test

Data Retrieval

Diagnostics Control

Calibration Parameter Control

Configuration Control

3.1.1 Engine Run Logging

The ADAS/ADAS+ Upgrade are capable of recording engine runs. For each run the following isrecorded for each engine:

Engine start date and time Engine run duration Maximum sensor value Cycle count

3.1.2 Cycle Logging

The ADAS/ADAS+ Upgrade can be configured for up to four different types of cycle count types duringeach engine run.

Incremental cycles (selectable sensor) Duration cycle (selectable sensor) Peak value cycle (one or two selectable sensors) Cumulative valley cycle (selectable sensor)

3.1.3 Event Monitoring

The ADAS/ADAS+ Upgrade can be configured to monitor and record airframe or engine exceedances orevents. Up to twenty basic AFM exceedances and operator specific events can be configured. Each eventrecord includes the date and time of the event, its duration and average and maximum sensor values.Events can be set to comprise inputs from either one or two sensors.



For All Listed Aircraft Models:

3.1.4 Initialization

When the system initializes, both TREND lamps indicate the various stages of the process. The processorinitialization sequence proceeds as follows:

When the processor’s power is first applied, each cockpit lamp will illuminate for approximately 2seconds while the system performs self-tests. The following self-tests are performed during initialization:

RAM Test PROM Test Temporary Memory Test Data Log Memory Test

If any of these tests fail, the lamp will remain on.

If the test passes, the lamp will extinguish and the processor will enter a system mode.

3.1.5 SYSTEM MODES

There are two system modes: Run Mode, and Configuration Mode.

For data collection it is normally operated in Run Mode.

For communication through the serial port with a laptop computer for the purposes of data transfer it isgenerally operated in Configuration Mode.

Configuration Mode is entered when a Communication cable is attached and the cable’s Run/Configureswitch is set to CONF. Run Mode is entered when the cable is not attached, or when it is attached and theRun/Configure Switch is set to RUN.

RUN is the default mode of operation. In this mode, the processor ignores all external serialcommands. The system is dedicated to monitoring sensors, exceedances, and cycles. During thisperiod a trend data sample can be stored manually by the pilot (if the cockpit is equipped with aTREND button) or by automatic sampling. No modifications of the processor settings arepossible in Run Mode. The ADAS/ADAS+ Upgrade may write records to system memory butcannot erase them while in this state. In Run Mode, the P&W Engine Services ADAS/ADAS+Upgrade can output a fixed format report of the current values of its sensors, along with otherflight information at a rate of 1 Hz through the serial port (Live Data Display). Run Mode isdefined by an ungrounded state of the Run/Configure input lines.

CONFIGURATION mode is the data transfer mode of operation. In this mode the ADAS/ADAS+Upgrade is dedicated to processing commands coming through the serial port from the MLP computer.The processor does not perform any monitoring of sensors, exceedances or cycles except in response to auser command. The ADAS/ADAS+ Upgrade does not write new records to system memory in this mode.Commands are available to retrieve or clear existing log data and configuration records while inCONFIGURATION Mode. It is defined by a grounded state on the Run/Configure input line.



The following section describes the condition of the cockpit lamps after initialization for:

Run Mode with the engine not running. Run Mode with the engine running. Configuration Mode.

3.1.6 Run Mode FOR ADAS ONLY

There are three possible states for the system in Run Mode. The states determine the lamp display.

1.) Normal2.) Warning3.) Error

Definitions:

In Normal state, the system is performing normally.

In Warning state, the system is indicating one or more of the following:

1. An exceedance was recorded2. The available data log memory is getting low3. The system has undergone a Factory Reset

In Error state, the system is indicating one or more of the following:

1. There is an internal program error2. There is a failed sensor channel3. There was a time slice (data) overflow4. The data log is full

3.1.7 Lamp States in Run Mode FOR ADAS ONLY:

While the engine is not running:

Lamp Out means Normal statusLamp Flashing means Warning statusLamp ON Continuously means Error status

Pressing the TREND switch with the lamp out will initiate a manual (“Loopback”) self test.Pressing the TREND switch with the lamp flashing will extinguish it IF in Warning state.

While the engine is running:

Lamp Flashing means a trend data sample is being taken, either automatically, or manuallyLamp Is Out for all other states.

Pressing the TREND switch with the lamp out will initiate a trend data sample.



3.1.8 Configuration Mode FOR ADAS ONLY

Lamp States in Configuration Mode

Lamp Out means Normal statusLamp Flashing means Warning statusLamp ON Continuously means Error status

While Flashing or On, Pressing the TREND switch will extinguish the lamp.While Off, Pressing the TREND switch will initiate a manual (Loopback) self test and send anacknowledgement of the button press to the serial communications port.

Note if the lamp is flashing, or ON, pressing the switch twice will accomplish bothof the above actions. It will extinguish the lamp and then perform a LoopbackTest. The lamp will remain off at the completion of the test.

3.1.9 Manual Self Test (Loopback Test) FOR ADAS ONLY

The Loopback test is a simple manual test that allows the user to check the operation of the lamp andCPU. It may be initiated in Configuration Mode, or in Run Mode when the engine is not running and thelamp is extinguished. Pressing the TREND switch initiates the Loop back Test.

Lamp Flashes for 5 Seconds means a Loopback Test was initiated, and is successful. The processorand lamp are functional.

3.1.10 Run Mode FOR ADAS+ UPGRADE ONLY

There are four possible states for the system in Run Mode. Each state determines the fault lamp display.

System States:

1. Normal

2. Maintenance

3. Caution

4. Fault

Definitions:

In Normal state, the system is performing normally OR recorded an input programmed toindicate Normal state.

In Maintenance state, the system recorded an input programmed to indicate Maintenancestate.

In Caution state, the system recorded an input programmed to indicate Caution state.

In Fault state, the system has failed OR the system recorded an input programmed toindicate Fault state.



3.1.11 LAMP STATES IN Run Mode FOR ADAS+ UPGRADE ONLY

While the Engine is Not Running Mode

Engine Not Running Mode is defined as anytime engine temperature is less than Engine Start Criteria(usually < 450 ºC).

Lamp Out means Normal state

Lamp Flashing means Maintenance state, if pressing the TREND switch stops the flashing

Lamp Flashing means Caution state, if pressing the TREND switch does not stop the flashing

Lamp Solid means Fault state

Pressing the TREND switch with the lamp out will initiate a manual (“Loopback”) self test.

Pressing the TREND switch with the lamp flashing will extinguish the lamp if in the Maintenance state.

While the Engine is Running Mode

Engine Running Mode is defined as anytime Ng is greater than Engine Run Criteria (usually > 55%).

Lamp Flashing means a trend data sample is being taken, either automatically, or manually

Lamp Is Out for all states. Lamp states are not allowed to report during Engine Running Mode.Pressing the TREND switch will initiate a trend data sample.



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/ADAS+ Upgrade has been designed with the latest solid-statetechnology. The only component that has a limited life span is the internal battery. This battery, undernormal operating conditions, is expected to last 10 years. If the battery is discharged, the processor mustbe returned to P&W Engine Services for battery replacement.

5.2 Recommended Periodic Scheduled Preventive Maintenance Tests/Checks

None Required5.3 Recommended Periodic Scheduled Inspections

The following information should be used to insure the continuous and trouble free operation of theADAS/ADAS+ Upgrade. These inspection steps should be followed during every other 100-hourinspection.

These instructions describe general inspection methods. All inspections should look for generaldeterioration of hoses, brackets, and any other component of the ADAS/ADAS+ Upgrade system. Otherthan the specific periodic inspections, maintenance is on-condition, and there is no other scheduledmaintenance.

5.3.1 System Processor

For the System Processor installation (

Figure 12), 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/ADAS+ Upgrade processor.



Figure 12: Bracket to Avionics Tray Mounting

5.3.2 TREND Switch / Fault Lamp and Download Port

The ADAS/ADAS+ Upgrade has a TREND switch / fault lamp that is installed in the cockpit and consistof a 75" x .75" square Push-to-test lamp. The ADAS/ADAS+ Upgrade also has a download port installedin the cockpit and consist of a 19/32" serial download connector.

For the TREND switch / fault lamp and download port installations (Figure 13, Figure 14, Figure 15 andFigure 16), perform the following inspections:

010 Verify that the proper connectors are in place. Refer to Figure 17 and Figure 18.

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.

TRENDENG 1

DOWNLOAD PORT

MOUNTING HOLE PATTERN

.75

.75

TRENDENG 2

.75

Figure 13: ADAS TREND Switch and Download Port (Discrete Mount)

TRENDENG 1

TRENDENG 2

ECTMPORT

Figure 14: ADAS TREND Switch / Fault Lamp & Download Port (Center Console Mount)



TREND

DOWNLOAD PORT


.75

.75

Figure 15: ADAS+ Upgrade TREND Switch and Download Port (Discrete Mount)

TREND

ECTMPORT

Figure 16: ADAS+ Upgrade TREND Switch / Fault Lamp & Download Port (Center Console Mount)

Figure 17: TREND Switch/Fault Lamp Connector



Figure 18: Download Port Connector

5.3.3 Pitot / Static Transducers

ADAS/ADAS+ Upgrade has the capability of measuring airspeed and altitude for event monitoring ortrend monitoring. Both pitot and static transducers are plumbed (Figure 19) into the aircraft’s existingpitot and static systems.

Figure 19: 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 20.






Figure 20: Pitot/Static Wiring

5.3.4 Outside Air Temperature Probe

The temperature probe is mounted on the underside of the aircraft to provide the processor with OATdata.

For the OAT probe installation (Figure 21) perform the following inspection:



Figure 21: 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 thetorque pressure lines.

010 Verify that the proper connectors are in place. Refer to Figure 22






Figure 22: Torque Transducer Wiring

5.3.6 J1, J2, and J3 Harnesses

010 Inspect harness for proper routing and security.

020 Inspect harness for signs of interference and wire chaffing.

5.3.7 System Test

010 With the aircraft battery connected and master switch on, verify that the TREND lamp or theoptional ENGINE/ETM Split Lamp illuminates, indicating system boot-up. After approximately5 seconds, the TREND lamp or the ENGINE/ETM Split Lamp will extinguish and either theTrend Lamp or the ETM Lamp will do one of 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 troubleshootthe system.

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 theADAS/ADAS+ Upgrade. These inspection steps should be followed during every other 100-hourinspection.

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

5.4.1 System Processor

For the System Processor installation (Figure 23), perform the following inspections:

010 Inspect processor for security to the mounting bracket.

020 Inspect mounting bracket for cracking.

Figure 23: Processor Mounting Configuration

5.4.2 TREND Switch / Fault Lamp and Download Port

For the TREND switch / fault lamp and download port installations (Figure 24, Figure 25, Figure 26, andFigure 27), perform the following inspections:

030 Inspect TREND Switch / Fault Lamp for proper mounting.

040 Inspect Download Port for proper mounting.



TRENDENG 1

DOWNLOAD PORT


.75

.75

TRENDENG 2

.75

Figure 24: ADAS TREND Switch and Download Port (Discrete Mount)

TRENDENG 1

TRENDENG 2

ECTMPORT

Figure 25: ADAS TREND Switch / Fault Lamp & Download Port (Center Console Mount)



TREND

DOWNLOAD PORT


.75

.75

Figure 26: ADAS+ Upgrade TREND Switch and Download Port (Discrete Mount)

TREND

ECTMPORT

Figure 27: ADAS+ Upgrade TREND Switch / Fault Lamp & Download Port (Center Console Mount)



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 28.

020 Inspect Adel™ clamps for deterioration.

030 Inspect fittings to make sure they are secure.

Figure 28: Pitot/Static Installation (Side View)



5.4.4 Outside Air Temperature Probe

For the OAT probe installation (Figure 29), 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 29: 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 thetorque pressure lines. The torque transducer installation is referenced in illustration Figure 30.

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

010 Inspect and make sure that transducer mounting is secure.

020 Inspect Adel™ clamps for deterioration.

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 30: Torque Transducer Installation Configuration



6 SYSTEM TROUBLESHOOTING

When the system does not function properly (or as you expect it to operate), the first thing that you mustdo is identify and isolate the problem. When you have accomplished this, you can effectively begin toresolve the problem.

The first step in troubleshooting is to isolate each system component and ensure that each componentfunctions properly when it is run independently. Using the Monitor Link Program (MLP), you caninterrogate the system to determine which function or component may have failed. Occasionally you mayhave to replace existing components to correct the problem. Determine if the problem is in the aircraft,ADAS/ADAS+ Upgrade processor, wiring or configuration of the processor.

Ask the question, can you repeat or recreate the problem? Random events may appear to be related, butthey are not necessarily contributing factors to your problem. You may be experiencing more than oneproblem. You must isolate and solve one problem at a time. Log (document) all testing and problemisolation procedures. You may need to review and consult this document later. This will also preventyou 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 the problem 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 ofthe ADAS/ADAS+ Upgrade Aircraft Data Acquisition System and its application provide answers to thefollowing questions:

Engine Type?

Airframe Type?

Processor Type?

Airframe Tail Number?

Processor Serial Number?

Is there a problem history?

Visual or computer indications?

Has the processor worked previously?

What activity was being performed when the failure occurred?

The ADAS/ADAS+ Upgrade will monitor and record system failures in a log that can be downloaded andreviewed. Status of the system can be obtained through the status/fault lamp.

Detailed troubleshooting for the system processor as well as for the various input channels can be foundin the topic-specific sections that follow.



6.1 System Processor

The first point of troubleshooting the ADAS/ADAS+ Upgrade is to be able to power up and communicateto the system processor.

During the initial power up phase, the system processor will perform self-test and display lampindications on the cockpit fault lamp (Figure 31). If the system powers up and will communicate with theMonitor Link Program (MLP), the download log will define any system faults. These faults can beinvestigated by following the troubleshooting methods in this section.

Follow Cockpit DisplayTest Procedures

Connect the GroundStation and apply

system power.

Observe fault lamp

Fault lamp onduring power up?

Can processorcommunicate?

Observe fault lampafter system power up

Yes

Fault lamp onwhen pressed?

No

Fault lamp on solid Fault lamp flashing Fault lamp off

No

Yes Follow Processor TestProcedures

Follow Download PortTest Procedures

No

Normal Operation.Download Log and Review

Yes

Figure 31: System Processor Start Up Test Flow Diagram



6.1.1 Processor Test

This section defines the basic test to determine if the processor is powered and functioning. Follow theprocessor test flow diagram in Figure 32 to determine failure.

Check Aircraft SupplyVoltage

Measure aircraft supplyto system voltage at:

J1.F & GJ1.H & G

24V on bothF and H?

5V on J2.A?

With processorpowered measure

voltage at cockpit faultlamp connectorPin 4 (Conxall)

Pin 7 (15 Pin D-Sub)

Yes

No

Check wiring. If OK thenreplace processor

Replace ProcessorNo

Normal Operation. CheckDownload Port

Yes

24V on Pin 4? No


voltage at J2.A

Yes

Figure 32: System Processor Test Flow Diagram



6.1.2 Download Port Test

This section defines the basic test to determine if the communications port is functioning. Follow thedownload port test flow diagram in Figure 33 and connection diagram in Figure 34 to determine failure.Pratt & Whitney Engine Services, Inc. provides a test box (TWIN-A-075-1) that can be purchased toelectrically test the cockpit display and download port.

With processor poweredmeasure voltage at download

port connector pins:1 and 2(Conxall)

9 and 10 (15 Pin D-Sub)

1.5V measured?

With processorpowered measure forground at download

port connectorpin 3(Conxall)

Pin11 (15 Pin D-Sub)

Yes

No


Normal Operation. CheckCommunications Cable and

Computer

Ground on pin 3? No

Yes


Figure 33: Download Port Test Flow Diagram

FAULT LAMP CONN

WHT WIREWHT/BLU WIRE

WHT/GRN WIREWHT/ORG WIRE

SHRINK SLEEVING" Pull Back and Cover Shield "

4-COND"FAULT LAMP"ENGINE ONE

4-COND"DOWNLOAD PORT"

1234

4321

WHT WIRE

WHT/BLU WIRE

WHT/GRN WIREWHT/ORG WIRE

DOWNLOAD PORT CONN

FAULT LAMP CONN

WHT WIREWHT/BLU WIRE

WHT/GRN WIRE

WHT/ORG WIRE


4-COND"FAULT LAMP"ENGINE TWO

1243

Figure 34: Cockpit Fault Lamp and Download Port Wiring



6.1.3 Cockpit Fault Lamp Display Test

This section defines the basic test to determine if the cockpit fault lamp display is functioning. Follow thefault lamp test flow diagram in Figure 35 and connection diagram to determine failure. Note: for acomplete showing of the Fault Lamp and Download port connections refer to the InterconnectDiagrams.

With processor poweredmeasure voltage at fault

lamp connector pins:1 and 2(Conxall)

5 and 6 (15 Pin D-Sub)

24V measured?

Power cycle processorand measure voltage at

fault lamp connector pins:4 and 2(Conxall)

7and 6 (15 Pin D-Sub)

Yes

No


Normal Operation. Check FaultLamp Bulb

24V during power? No

Yes


Figure 35: Cockpit Fault Lamp Test Flow Diagram



6.1.4 Torque Transducer and Channel Test

This section defines the basic test to determine if the torque transducer is functioning and if the ADASprocessor is reading a signal from it. Follow the torque transducer test flow diagram in Figure 36 andconnection diagram in Figure 37 to determine failure.

With processorpowered measurevoltage at torque

transducer red andblack wires

5V measured?

Jumper the red andgreen wires at thetorque transducer

connector and observesensor reading

Yes

No


Replace Transducer

Did value goto full scale?

No

Yes


Figure 36: Torque Transducer Test Flow Diagram

Figure 37: Torque Wiring1

1Some models of aircraft do not require the P&W Engine Services Torque Transducers. For the

aircraft that do not require the P&W Engine Services Torque Transducers, refer to the ConfigurationChart for your model A/C and wiring interconnect diagram.



6.1.5 Pitot / Static Transducer and Channel Test

This section defines the basic test to determine if the pitot / static transducers are functioning and if theprocessor is reading signals from them. Follow the pitot / static transducer test flow diagram in Figure 38and connection diagram in Figure 39 to determine failure.

With processorpowered measurevoltage at pitot and

static transducer redand black wires

5V measured?

Jumper the red andgreen wires at the pitottransducer connectorand observe sensor

reading

Yes

No


Replace Transducer

Did value goto full scale?

No

Yes


Jumper the red andgreen wires at thestatic transducer

connector and observesensor reading


Replace Transducer

Did altitude gobelow sea level?

No

Yes

Figure 38: Pitot / Static Transducer Test Flow Diagram

STATIC TRANSDUCER

PITOT TRANSDUCER


GRN WIRES

BLK WIRE

BLK WIRE

RED WIRE

RED WIRE

WHT WIRE

WHT/BLU WIRE

WHT/GRN WIRE

WHT/ORG WIRE

Figure 39: Pitot / Static Wiring



6.1.6 Outside Air Temperature Test

This section defines the basic test to determine if the OAT probe is functioning and if the processor isreading a signal from it. Follow the OAT probe test flow diagram in Figure 40 and connection diagram inFigure 41 to determine failure for the ADAS and the OAT probe test flow diagram in Figure 42 andconnection diagram in Figure 43 to determine failure for the ADAS+ Upgrade.

Remove the J1connector and

measure voltage atpins C and E of the

cable

Voltagemeasured?

Manually heat probeand take note ofvoltage readings

Yes

No


Replace OAT ProbeDid voltage

change?No

Yes


Figure 40: ADAS OAT Probe Test Flow Diagram

OAT PROBE


RED WIRE

YELLOW WIRE

TIE SHIELDSTOGEHTHER

Figure 41: ADAS OAT Wiring




voltage at both sets ofwhite and red OAT

probe wire

Voltagemeasured?

Manually heat probeand take note ofvoltage readings

Yes

No


Replace OAT ProbeDid voltage

change?No

Yes


Figure 42: ADAS+ Upgrade OAT Probe Test Flow Diagram

OAT PROBE


WHT WIRES

RED WIRES

WHT WIRE

WHT/BLU WIRE

WHT/GRN WIRE

WHT/ORG WIRE

Figure 43: ADAS+ Upgrade OAT Wiring



6.1.7 P&W Engine Services Voltage to Frequency Converter

This section defines the basic test to determine if the P&W Engine Services Voltage to FrequencyConverters is functioning and if the processor is reading a signal from it. Follow the P&W EngineServices Voltage to Frequency Converters test flow diagram in Figure 44 to determine failure.

How Many Channelsare Non-Functional?

Check Continuity ofAffected Signal

Harness

ONE

Measure Voltage:Pin 3 vs. Pin 7 of ( Pin

VFC Connector

BOTH

Harness OKRepair Harness ToAltair Specifications

NO

Replace VFC

YES

Aircraft BusVoltage Detected

Check 2 ConductorVFC Power Harness

Check Continuity ofEngine 1 VFC Harness

Per WiringInterconnect Diagram

YES

Harness OKRepair Harness ToAltair Specifications

No

Replace VFC

YES

NO

Figure 44: Voltage to Frequency Converters

6.1.8 Additional Aircraft Signals

All sensor signals that are measured from aircraft sensors can be verified by simulating the aircraft signalsource. If equipment is not available for these tests you can also verify based on the operation of theaircraft instrument. Once wiring has been validated by resistance measurement you can simulate or runup the aircraft while monitoring the readings from the ADAS/ADAS+ Upgrade processor. If the wiringhas been validated and the system still does not read the sensor value then the processor must be replaced.



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, J3, and Comm wiring harnesses from the processor.

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

030 Disassemble the ADAS/ADAS+ Upgrade processor from the mounting bracket shown inFigure 23.

040 Assemble the ADAS/ADAS+ Upgrade processor to the mounting bracket shown in Figure 23.Ensure that the processor does not interfere with wiring or controls.

INSTALLATION CAUTION:

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.

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

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

070 Perform configuration and calibration per instructions in ADAS/ADAS+ Upgrade InstallationManual TWIN-I-010-1, System Configuration and Calibration.

7.2 TREND Switch Removal/Replacement

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

020 Disconnect TREND Switch ConXall™ connector under instrument panel.

030 Remove TREND Switch by squeezing locking springs on sides of switch and pushing theswitch thru the hole in the instrument panel.

040 Replace TREND switch 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 usingLoctite® 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 28. 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 (960-00029).

050 Remove the pitot and static transducers by removing the bolt, washer, and nut which securesthe two 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 (960-00029) from the Static Transducer if you are replacing theStatic Transducer.

070 Replace the appropriate transducer as necessary.

080 Apply Teflon® tape to the Pitot Transducer threads and install adapter (960-00002) or applyTeflon® tape to the Static Transducer threads and install “T” pipe (960-00029).

090 Attach the pitot and static transducers to the supplied plate (ADAS-D-018-1), clamp (ADAS-D-019-1, clamp (MS21919WDG26), bolt (910-00007), washer (920-00005) and lock nut (910-00008).

0100 Connect the Pitot hose (990-00028) to the adaptor (960-00002).

0110 Connect the Static hose (990-00028) to the “T” pipe (960-00029).

0120 Connect Tygon tubing to the Pitot Transducer.

0130 Secure and tighten all hoses and fittings.

0140 Perform Pitot/Static calibration per instructions in ADAS/ADAS+ Upgrade Installation ManualTWIN-I-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 (920-00009), “O” ring (990-00027) and jam nut (TWIN-D-061-1).

060 Tighten and safety wire the jam nut to the bolt (910-00007).

070 Apply a bead of sealant (ProSeal PR1422 or equivalent) around edge of doubler afterinstallation and smooth to produce a filleted profile.

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

090 Perform OAT calibration per instructions in ADAS/ADAS+ Upgrade Installation Manual TWIN-I-010-1, System Configuration 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 30, remove the “T” swivel (960-00012) 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 theadapter fitting (960-00015).

070 Connect the torque transducer / adapter fitting assembly to the “T” swivel (960-00012).

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

090 Perform Torque calibration per instructions in ADAS/ADAS+ Upgrade Installation ManualTWIN-I-010-1, System Configuration and Calibration.



8 SPECIAL INSPECTION REQUIREMENTS


9 APPLICATION OF PROTECTIVE TREATMENTS


10 DATA

10.1 Parts List

The parts listed in the sections below consist of the complete installation kit applied for under thesupplemental type certificate for the Raytheon (Beech) model aircraft specified. Assembly kit numbersare listed by aircraft model in section 10.1.1 and individual components are detailed by assembly kitnumbers in section 0.

10.1.1 Part Kits by Aircraft for ADAS ONLY:

1900 and 1900C Pedestal Display TWIN-K-010-1

ADAS Processor Assembly 1 TWIN-K-028-1Engine Harness Kit 1 TWIN-K-029-1Engine Torque Kit 1 TWIN-K-031-1

Hi Precision: TWIN-K-031-3Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-1Cockpit Trend Switch Kit 1 TWIN-K-027-1Additional Installation Materials Kit 1 TWIN-K-034-1

1900 and 1900C Individual Display TWIN-K-010-2

Processor Assembly 1 TWIN-K-028-1Engine Harness Kit 1 TWIN-K-029-1Engine Torque Kit 1 TWIN-K-031-1

Hi Precision: TWIN-K-031-3Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-1Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-1Additional Installation Materials Kit 1 TWIN-K-034-1

1900D UE1 to UE92 Pedestal Display TWIN-K-010-3


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-1Additional Installation Materials Kit 1 TWIN-K-034-2



1900D UE1 to UE92 Individual Display TWIN-K-010-4


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-1Additional Installation Materials Kit 1 TWIN-K-034-2

1900D UE93 and after Pedestal Display TWIN-K-010-5

Processor Assembly 1 TWIN-K-028-1Engine Harness Kit 1 TWIN-K-029-1Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-1Additional Installation Materials Kit 1 TWIN-K-034-2

1900D UE93 and after Individual Display TWIN-K-010-6

Processor Assembly 1 TWIN-K-028-1Engine Harness Kit 1 TWIN-K-029-1Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-1Additional Installation Materials Kit 1 TWIN-K-034-2

200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300C

Pedestal Display with Torque Kit TWIN-K-010-7


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-1Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

2

2The P&W Engine Services Voltage to Frequency Converters are not required for all aircraft

types or models. Refer to the Aircraft Configuration Charts for which aircraft require them.




Pedestal Display without Torque Kit TWIN-K-010-10

Processor Assembly 1 TWIN-K-028-1Engine Harness Kit 1 TWIN-K-029-1Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-1Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

3


Individual Cockpit Display with Torque kit TWIN-K-010-11


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-1Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

3


Individual Display without Torque kit TWIN-K-010-12

Processor Assembly 1 TWIN-K-028-1Engine Harness Kit 1 TWIN-K-029-1Aircraft Outside Air Temperature Probe Kit 1 TREND-K-040-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-1Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

3

3The P&W Engine Services Voltage to Frequency Converters are not required for all aircraft

types or models. Refer to the Aircraft Configuration Charts for which aircraft require them.



10.1.2 Part Kits By Aircraft for ADAS+ Upgrade ONLY:

1900 and 1900C Pedestal Display TWIN-K-010-21

ADAS+ Upgrade Processor Assembly 1 TWIN-K-028-2Engine Harness Kit 1 TWIN-K-029-2Engine Torque Kit 1 TWIN-K-031-1

Hi Precision: TWIN-K-031-3Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-1Cockpit Trend Switch Kit 1 TWIN-K-027-2Additional Installation Materials Kit 1 TWIN-K-034-1

1900 and 1900C Individual Display TWIN-K-010-22


Hi Precision: TWIN-K-031-3Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-1Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-2Additional Installation Materials Kit 1 TWIN-K-034-1

1900D UE1 to UE92 Pedestal Display TWIN-K-010-23


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-2Additional Installation Materials Kit 1 TWIN-K-034-2

1900D UE1 to UE92 Individual Display TWIN-K-010-24


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-2Additional Installation Materials Kit 1 TWIN-K-034-2


44TWIN-T-260-1 Pratt & Whitney Engine Services, Inc. Proprietary

1900D UE93 and after Pedestal Display TWIN-K-010-25

ADAS+ Upgrade Processor Assembly 1 TWIN-K-028-2Engine Harness Kit 1 TWIN-K-029-2Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-2Additional Installation Materials Kit 1 TWIN-K-034-2

1900D UE93 and after Individual Display TWIN-K-010-26

ADAS+ Upgrade Processor Assembly 1 TWIN-K-028-2Engine Harness Kit 1 TWIN-K-029-2Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-2Additional Installation Materials Kit 1 TWIN-K-034-2

200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300, 300LW,B300, and B300C

Pedestal Display with Torque Kit TWIN-K-010-27


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-2Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

4


Pedestal Display without Torque Kit TWIN-K-010-30

ADAS+ Upgrade Processor Assembly 1 TWIN-K-028-2Engine Harness Kit 1 TWIN-K-029-2Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Trend Switch Kit 1 TWIN-K-027-2Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

5

4The P&W Engine Services Voltage to Frequency Converters are not required for all aircraft types or

models. Refer to the Aircraft Configuration Charts for which aircraft require them.5

The P&W Engine Services Voltage to Frequency Converters are not required for all aircraft types ormodels. Refer to the Aircraft Configuration Charts for which aircraft require them.




Individual Display with Torque kit TWIN-K-010-31


Hi Precision: TWIN-K-031-4Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-2Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

3


Individual Display without Torque kit TWIN-K-010-32

ADAS+ Upgrade Processor Assembly 1 TWIN-K-028-2Engine Harness Kit 1 TWIN-K-029-2Aircraft Outside Air Temperature Probe Kit 1 DPU-K-032-1Aircraft Vertical Accelerometer Kit 1 TWIN-K-032-1 (No longer Available)Pitot / Static Pressure Kit 1 TWIN-K-033-2Cockpit Fault Lamp and Download Port Kit 1 TWIN-K-045-2Additional Installation Materials Kit 1 TWIN-K-034-1Voltage to Frequency Converter Kit 1 TWIN-K-046-1

3



10.1.3 Components for ADAS and ADAS+ Upgrade by Kit Number

TWIN-K-027-1 COCKPIT TREND SWITCH KIT FOR ADAS

Cable, Cockpit Trend Switch TWIN-C-015-1 Qty 1Assy., Cockpit Trend Switch TWIN-A-064-1 Qty 1Connector, Hi-Density MS24308/2-11F Qty 1Backshell 400-00038 Qty 1Screw, Lock Post 900-00052 Qty 1

TWIN-K-027-2 COCKPIT TREND SWITCH KIT FOR ADAS+ UPGRADE

Cable, Cockpit Trend Switch TWIN-C-015-1 Qty 1Assy., Cockpit Trend Switch TWIN-A-064-2 Qty 1Connector, Hi-Density MS24308/2-11F Qty 1Backshell 400-00038 Qty 1Screw, Lock Post 900-00052 Qty 1

TWIN-K-028-1 PROCESSOR ASSEMBLY FOR ADAS

Processor TWIN-A-010-1 Qty 1Mounting Bracket DPU-D-030-1 Qty 1Shock Mounts, Lord 990-00020 Qty 4Washer, Processor Mount 990-00006 Qty 4Nut, Locking, Processor Mount 910-00009 Qty 4Nut, Rivet, #10 910-00026 Qty 4Screw, #10 900-00010 Qty 4Washer, Flat, #10 920-00007 Qty 4Strap, Ground DPU-C-050-1 Qty 1

TWIN-K-028-2 PROCESSOR ASSEMBLY FOR ADAS+ UPGRADE

Processor TWIN-A-010-2 Qty 1Mounting Bracket DPU-D-030-1 Qty 1Shock Mounts, Lord 990-00020 Qty 4Washer, Processor Mount 990-00006 Qty 4Nut, Locking, Processor Mount 910-00009 Qty 4Nut, Rivet, #10 910-00026 Qty 4Screw, #10 900-00010 Qty 4Washer, Flat, #10 920-00007 Qty 4Strap, Ground DPU-C-050-1 Qty 1

TWIN-K-029-1 ENGINE HARNESS KIT FOR ADAS

Cable Assembly, J1 TWIN-C-013-1 Qty 1Cable Assembly, Engine 1, J2 TWIN-C-011-1 Qty 1Cable Assembly, Engine 2, J3 TWIN-C-012-1 Qty 1

TWIN-K-029-2 ENGINE HARNESS KIT FOR ADAS+ UPGRADE

Cable Assembly, J1 TWIN-C-070-1 Qty 1Cable Assembly, Engine 1, J2 TWIN-C-011-1 Qty 1Cable Assembly, Engine 2, J3 TWIN-C-071-1 Qty 1



TWIN-K-031-1 ENGINE TORQUE KIT

Transducer, 0 – 150 PSIG 750-00003 Qty 4Alternate: 750-00004Alternate: *0 – 75 PSIG P01021

Elbow, Pipe to 37o

Flare 960-00010 Qty 4Fitting, “T”, Swivel 960-00003 Qty 4Clamp MS21919WCJ12 Qty 4Clamp MS21919WCJ16 Qty 4Screw 900-00014 Qty 4Nut 910-00017 Qty 4Spacer 940-00004 Qty 4Washer 920-00005 Qty 4Wall Mount Connector MS3450KT16S-8S Qty 2Alternate 400-00061Cable Connector MS3456KT16S-8P Qty 2Alternate 4000-00062Backshell M85049/41-10 Qty 4

Alternate M85049/41-8ACable 800-00016 Qty 60 ft.

TWIN-K-031-2 ENGINE TORQUE KIT

Transducer, 0 – 150 PSIG 750-00003 Qty 4Alternate: 750-00004Alternate: *0 – 75 PSIG P01021Elbow, Pipe to 37

oFlare 960-00010 Qty 4

Fitting, “T”, Swivel 960-00003 Qty 4Clamp MS21919WCJ12 Qty 4Clamp MS21919WCJ16 Qty 4Screw 900-00014 Qty 4Nut 910-00017 Qty 4Spacer 940-00004 Qty 4Washer 920-00005 Qty 4Cable 800-00016 Qty 60 ft.

TWIN-K-031-3 ENGINE HIGH PRECISION TORQUE KIT

Transducer, 0 – 100 PSIG 750-00005 Qty 4Elbow, Double Swivel, 37° Flare 960-00014 Qty 4Fitting, “T”, Swivel 960-00006 Qty 4Adapter, Boss O ring, 37° Flare 960-00015 Qty 4Clamp MS21919WCJ12 Qty 4Clamp MS21919WCJ14 Qty 4

Alternate: MS21919WCH14Screw 900-00014 Qty 4Nut 910-00017 Qty 4Spacer 940-00004 Qty 4Washer 920-00005 Qty 4Wall Mount Connector MS3450KT16S-8S Qty 2

Alternate 400-00061Cable Connector MS3456KT16S-8P Qty 2

Alternate 400-00062Backshell M85049/41-10A Qty 4

Alternate M85049/41-8ACable 800-00016 Qty 60 ft.



TWIN-K-031-4 ENGINE HIGH PRECISION TORQUE KIT

Transducer, 0 -- 100 PSIG 750-00005 Qty 4Elbow, Double Swivel, 37° Flare 960-00014 Qty 4Fitting, “T”, Swivel 960-00006 Qty 4Adapter, Boss O ring, 37° Flare 960-00015 Qty 4Clamp MS21919WCJ12 Qty 4Clamp MS21919WCJ14 Qty 4

Alternate: MS21919WCH14Screw 900-00014 Qty 4Nut 910-00017 Qty 4Spacer 940-00004 Qty 4Washer 920-00005 Qty 4Cable 800-00016 ` Qty 60 ft.

TWIN-K-032-1 AIRCRAFT VERTICAL ACCELEROMETER KIT

Accelerometer, 5g TWIN-D-035-1 Qty 1Screw 900-00011 Qty 2Nut 910-00016 Qty 2Washer 920-00013 Qty 2Connector 400-00026 Qty 1

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009.

TWIN-K-033-1 PITOT / STATIC PRESSURE KIT

Bracket, Transducer Mounting TWIN-D-014-1 Qty 1Nipple, Pipe 960-00036 Qty 2Tee, Pipe 960-00037 Qty 2Nipple, Flare 960-00038 Qty 2Hose, Inlet Pressure (990-00028) Qty 4 Ft.Fitting, Inlet Pressure Hose 960-00027 Qty 4Adapter, Pipe to 37° Flare 960-00002 Qty 1Tee, Pipe 960-00029 Qty 1Nipple, Flare 960-00030 Qty 1Bushing 920-00011 Qty 1Fitting, Male Nylo-Seal 960-00024 Qty 1Tubing, Tygon 990-00030 Qty 1 FtInsert B-405-2 Qty 1Transducer, 0 - 3 PSID 750-00001 Qty 1Transducer, 0 – 15 PSIA 750-00002 Qty 1Clamp, Inlet Pressure Hose MS21919WDG17 Qty 1Clamp, Inlet Pressure Transducer MS21919WDG26 Qty 1Screw, 6-32 900-00012 Qty 3Washer, Flat, #6 920-00013 Qty 3Nut, Locking, 6-32 910-00016 Qty 3Bolt, 10-32 900-00013 Qty 2Nut, Locking, 10-32 910-00008 Qty 2Washer, #10 920-00005 Qty 2Standoff 940-00003 Qty 1



TWIN-K-033-2 PITOT / STATIC PRESSURE KIT

Bracket, Transducer Mounting TWIN-D-014-1 Qty 1Hose, Inlet Pressure (990-00028) Qty 4 Ft.Fitting, Inlet Pressure Hose 960-00027 Qty 4Adapter, Pipe to 37° Flare 960-00002 Qty 1Tee, Pipe 960-00029 Qty 1Nipple, Flare 960-00030 Qty 1Bushing 920-00011 Qty 1Fitting, Male Nylo-Seal 960-00024 Qty 1Tubing, Tygon 990-00030 Qty 1 FtInsert B-405-2 Qty 1Transducer, 0 - 3 PSID 750-00001 Qty 1Transducer, 0 – 15 PSIA 750-00002 Qty 1Clamp, Inlet Pressure Hose MS21919WDG17 Qty 1Clamp, Inlet Pressure Transducer MS21919WDG26 Qty 1Screw, 6-32 900-00012 Qty 3Washer, Flat, #6 920-00013 Qty 3Nut, Locking, 6-32 910-00016 Qty 3Bolt, 10-32 900-00013 Qty 2Nut, Locking, 10-32 910-00008 Qty 2Washer, #10 920-00005 Qty 2Standoff 940-00003 Qty 1Reducer 960-00031 Qty 1Fitting, “T” Swivel 960-00032 Qty 1Fitting, “T” Swivel 960-00003 Qty 1

TWIN-K-034-1 ADDITIONAL INSTALLATION MATERIALS KIT

Grommet, Pressure Bulkhead 990-00035 Qty 1T5 Crimp Lug, Alumel 400-00034 Qty 2T5 Crimp Lug, Chromel 400-00035 Qty 2Fuse Holder, In-Line DPU-C-0571 Qty 2Fuse, 1 Amp 990-00033 Qty 2Terminal, End 990-00011 Qty 4Doubler, Pressure Bulkhead ADAS-D-059-1 Qty 1

TWIN-K-034-2 ADDITIONAL INSTALLATION MATERIALS KIT

Grommet, Pressure Bulkhead 990-00035 Qty 1Breaker, Circuit 1 Amp 990-00032 Qty 2T5 Crimp, Lug, Alumel 400-00034 Qty 2T5 Crimp, Lug, Chromel 400-00035 Qty 2Terminal, End 990-00011 Qty 4Doubler, Pressure Bulkhead ADAS-D-059-1 Qty 1

TREND-K-040-1 AIRCRAFT OUTSIDE AIR TEMPERATURE PROBE KIT

Probe, Temperature TWIN-A-050-1 Qty 1Nut, Jam TWIN-D-061-1 Qty 1Washer 920-00009 Qty 2Seal, “O” Ring 990-00027 Qty 1Screw, Drilled 910-00014 Qty 1Doubler, OAT Probe DPU-D-047-1 Qty 1



DPU-K-032-1 AIRCRAFT OUTSIDE AIR TEMPERATURE PROBE KIT FORADAS+ UPGRADE

Probe, Temperature TWIN-A-050-2 Qty 1Nut, Jam TWIN-D-061-1 Qty 1Washer 920-00009 Qty 2Washer 920-00005 Qty 1Nut 910-00008 Qty 1Seal, “O” Ring 990-00027 Qty 1Screw, Drilled 910-00014 Qty 1Doubler, OAT Probe DPU-D-047-1 Qty 1

TWIN-K-045-1 COCKPIT FAULT LAMP AND DOWNLOAD PORT KIT FORADAS

Assy., Cockpit Fault Lamp CYCLE-A-013-1 Qty 2Connector, 6 Pin Female 400-00026 Qty 2Assy., Download Port DPU-A-044-1 Qty 1Connector, 6 Pin, Male 400-00027 Qty 1Harness, Trend Switch TWIN-C-015-1 Qty 1Cover, Receptacle 990-00031 Qty 1LENS, CAP TWIN-D-022-1 Qty 1LENS, CAP TWIN-D-023-1 Qty 1

TWIN-K-045-2 COCKPIT FAULT LAMP AND DOWNLOAD PORT KIT FOR ADAS+UPGRADE

Assy., Cockpit Fault Lamp DPU-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 1Harness, Trend Switch TWIN-C-015-1 Qty 1Cover, Receptacle 990-00031 Qty 1LENS, CAP TWIN-D-041-1 Qty 1

TWIN-K-046-1 VOLTAGE TO FREQUENCY CONVERTER KIT

Voltage to Frequency Converter TWIN-A-042-1 Qty 1Cable harness Assemble TWIN-C-043-1 Qty 1Screw 900-00021 Qty 4



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 s): 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: ConXall Corporation,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/ADAS+ Upgrade has a current draw of 300 milliamps at 28V DC. TheADAS/ADAS+ Upgrade kit weighs 10.55 lbs.

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 ADAS Connector Signal Points

15.1.1 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 16

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

3 COND CABLEJ1 G WHT/BLU Aircraft Ground Aircraft GroundJ1 F WHT Processor #1 Bus Power Bus Power, Supplied 1 Amp FuseJ1 M WHT/ORG Processor #2 Bus Power Bus Power, Supplied 1 Amp Fuse

THERMOCOUPLEJ1 C RED OAT (ALUMEL) RED Wire OAT ProbeJ1 E YEL OAT (CHROMEL) YEL Wire OAT Probe

2 COND CABLEJ1 J WHT Flaps, Approach Sig Cockpit Flap ControlJ1 H WHT/BLU Flaps, Final Sig Cockpit Flap Control

1 COND CABLEJ1 L WHT Gear Extended Sig Cockpit Gear Control

1 COND CABLEJ1 K WHT Weight on Wheels Sig Cockpit WOW Control

2 COND CABLEJ1 N WHT/BLU Ice Vane Sig Engine #1 Ice Vane ControlJ1 R WHT Ice Vane Sig Engine #2 Ice Vane Control

J1 P Shields



15.1.2 Sensor Cable J2, 15 Pin SA Keyed Connector







4 COND CABLEJ2 A WHT Eng1 Torque (5 VDC) RED Wire Both Torque TransducersJ2 B WHT/ORG Eng1 Torque (Signal +) GRN Wire High Torque TransducerJ2 C WHT/BLU Eng1 Torque (Ground) BLK Wire Both Torque TransducersJ2 F WHT/GRN Eng1 Torque (Signal –) GRN Wire Low Torque Transducer

1 COND CABLEJ2 D WHT Eng1 N1 “Spd 1” (Sig +) Eng1 N1 Instrument Gauge +

1 COND CABLEJ2 E WHT Eng1 N2 “Spd 2” (Sig +) Eng1 Np Instrument Gauge +

2 COND CABLEJ2 G WHT Eng1 Fuel Flow (Sig +) Eng1 Fuel Flow Instrument Gauge +J2 R WHT/BLU Eng1 Fuel Flow (Sig –) Eng1 Fuel Flow Instrument Gauge –

THERMOCOUPLEJ2 J RED Eng1 ITT (Alumel –) Eng1 ITT Instrument Gauge –J2 K YEL Eng1 ITT (Chromel +) Eng1 ITT Instrument Gauge +

3 COND CABLEJ2 M WHT/BLU Vertical Accl. (GND) Pin 1 ConXall™ Assy.J2 L WHT/ORG Vertical Accl. (Signal +) Pin 2 ConXall™ Assy.J2 H WHT Vertical Accl. (5 VDC) Pin 3 ConXall™ Assy.

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009. If the kit was purchasedafter March 1, 2009 and does not come with a Vertical Accelerometer, then cap and stow the wire as itwill not be needed.

1 COND CABLEJ2 N WHT Eng1 Bleed Air Cockpit Bleed Air Control

J2 P Shields



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













J3 P Shields

J3 H (Unused)J3 L (Unused)J3 M (Unused)



15.1.4 COMM CABLE HARNESS






15.1.4.1 COCKPIT TREND SWITCH HARNESS – SINGLE DISPLAY

Connector Harness Single Cockpit ConnectorPin Wire Color Signal Name 15 Pin

4 COND CABLE8 WHT Lamp – PTT V+ 19 WHT/BLU Lamp – Gnd 27 WHT/GRN Lamp – Switched V+ 32 WHT/ORG Pilot Trend Digital 0 4

4 COND CABLE8 WHT Lamp – PTT V+ 59 WHT/BLU Lamp – Gnd 66 WHT/GRN Lamp – Switched V+ 73 WHT/ORG Pilot Trend Digital 0 8

4 COND CABLE4 WHT/ORG Serial RS–485 +B 95 WHT/GRN Serial RS–485 –A 109 WHT/BLU System Gnd 111 WHT Run/Config Digital 1 12

9 Shields

15.1.4.2 COCKPIT TREND SWITCH HARNESS – DUAL DISPLAY

Connector Harness Individual Cockpit ConnectorsPin Wire Color Signal Name 6 Pin (3 Connectors)

4 COND CABLE8 WHT Lamp – PTT V+ 1 ENG2 6 Pin Female9 WHT/BLU Lamp – Gnd 27 WHT/GRN Lamp – Switched V+ 42 WHT/ORG Pilot Trend Digital 0 3

4 COND CABLE8 WHT Lamp – PTT V+ 1 ENG1 6 Pin Female9 WHT/BLU Lamp – Gnd 26 WHT/GRN Lamp – Switched V+ 43 WHT/ORG Pilot Trend Digital 0 3

4 COND CABLE4 WHT/ORG Serial RS–485 +B 1 DOWNLOAD 6 Pin Male5 WHT/GRN Serial RS–485 –A 29 WHT/BLU System Gnd 31 WHT Run/Config Digital 1 4

9 Shields



15.2 ADAS+ Upgrade Connector Signal Points

15.2.1 Power/ Sensor Cable J1, 15 Pin S Keyed Connector







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

3 COND CABLEJ1 G WHT/BLU Aircraft Ground Aircraft GroundJ1 F WHT Bus Power In Bus Power, Supplied 1 Amp FuseJ1 M WHT/ORG Battery Power In Battery Power, Supplied 1 Amp Fuse

4 COND CABLEJ1 C WHT OAT D RED Wire OAT ProbeJ1 E WHT/BLU OAT G WHT Wire OAT ProbeJ1 N WHT/ORG OAT R+ RED Wire OAT ProbeJ1 R WHT/GRN OAT R – WHT Wire OAT Probe

2 COND CABLEJ1 J WHT Flaps, Approach Sig Cockpit Flap ControlJ1 H WHT/BLU Flaps, Final Sig Cockpit Flap Control

1 COND CABLEJ1 L WHT Gear Extended Sig Cockpit Gear Control

1 COND CABLEJ1 K WHT Weight on Wheels Sig Cockpit WOW Control

Backshell Shields



15.2.2 Sensor Cable J2, 15 Pin SA Keyed Connector












3 COND CABLEJ2 M WHT/BLU Vertical Accl. (GND) Pin 1 ConXall™ Assy.J2 L WHT/ORG Vertical Accl. (Signal +) Pin 2 ConXall™ Assy.J2 H WHT Vertical Accl. (5 VDC) Pin 3 ConXall™ Assy.

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009. If the kit was purchasedafter March 1, 2009 and does not come with a Vertical Accelerometer, then cap and stow the wire as itwill not be needed.


J2 P (Unused)

Backshell Shields



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













2 COND CABLEJ3 M WHT Ice Vane Sig Engine #1 Ice Vane ControlJ3 L WHT/BLU Ice Vane Sig Engine #2 Ice Vane Control

J3 P (Unused)J3 H (Unused)

Backshell Shields



15.2.4 COMM CABLE HARNESS






15.2.4.1 COCKPIT TREND SWITCH HARNESS – SINGLE DISPLAY

Connector Harness Single Cockpit ConnectorPin Wire Color Signal Name 15 Pin

4 COND CABLE8 WHT Lamp + 19 WHT/BLU SW1 – COMM SW2 – COMM 27 WHT/GRN Lamp – SW1–ON 32 WHT/ORG SW2 – ON 4

4 COND CABLE4 WHT/ORG Serial RS–485 +B 95 WHT/GRN Serial RS–485 –A 109 WHT/BLU System Gnd 111 WHT Run/Config Digital 1 12

9l Shields

15.2.4.2 COCKPIT TREND SWITCH HARNESS – DUAL DISPLAY

Connector Harness Individual Cockpit ConnectorsPin Wire Color Signal Name 6 Pin (2 Connectors)

4 COND CABLE8 WHT Lamp + 1 Eng 1 6 Pin Female9 WHT/BLU SW1 – COMM SW2 – COMM 27 WHT/GRN Lamp – SW1-ON 32 WHT/ORG SW2-ON 4

4 COND CABLE8 WHT Lamp + 1 Eng 2 6 Pin Female9 WHT/BLU SW1 – COMM SW2 – COMM 23 WHT/GRN Lamp – SW1-ON 36 WHT/ORG SW2-ON 4

4 COND CABLE4 WHT/ORG Serial RS–485 +B 1 Download 6 Pin Male5 WHT/GRN Serial RS–485 –A 29 WHT/BLU System Gnd 31 WHT Run/Config Digital 1 4

9 Shields



16 Wiring Diagram

16.1 ADAS/ADAS+ Upgrade Connection Chart – 1900 & 1900C

RAYTHEON (BEECH) 1900 & 1900C

Signal Mfg.Config.

Connection Connection

Torque, Eng 1 All Supplied TorqueTransducers


N1, Eng 1 All P115 – Pin A




Fuel Flow, Eng 1* All P131 - Pin A (+) Pin I (-)

Fuel Flow, Eng 2* All P132 - Pin A (+) Pin I (-)

ITT, Eng 1 All M112 - CH (+) M112 - AL (-)


Bleed, Eng 1 All H131A20 (Bleed AirControl Switch)


Ice Vane, Eng 1 All H218A20 (Ice VaneControl Switch)


Flaps Approach All P194 Pin 14C

Flaps Final All P194 Pin 12C

Weight on Wheels All J-125 - Pin 2

Gear Extended All P200 - Pin 6

Battery Pwr(ADAS+ Upgrade)

All BUS BAR – HOT BATTERYW214

BUS Pwr All Circuit Breaker Panel Zone 246Primary Bus Source

Wiring Note:

Some configurations of Raytheon aircraft have the Foxboro Fuel Flow Indicator and/or Totalizer Systeminstalled. Please refer to the change in wiring for the fuel flow circuit if the following kits are installed:

Kit No. 114-9026-3 S

Kit No. 114-9026-5 S

Kit No. 114-9026-7 S

Fuel Flow, Eng 1 All P131 - Pin E (+) Pin F (-)

Fuel Flow, Eng 2 All P132 - Pin E (+) Pin F (-)



16.2 ADAS/ADAS+ Upgrade Connection Chart – 1900D

Note: Check the aircraft serial number to determine whether P&W Engine ServicesTorque transducers are required, or a wiring connection is made to the existing system,as indicated in the Torque entries in the table below

RAYTHEON (BEECH) 1900D

Signal Mfg. Config. Connection Connection

Torque, Eng 1 S/N UE1 thru UE92 Supplied TorqueTransducers

S/N UE93 & higher P119-S(+) P119-T(-)

Torque, Eng 2 S/N UE1 thru UE92 Supplied TorqueTransducers

S/N UE93 & higher P120-S(+) P120-T(-)

N1, Eng 1 S/N UE1 thru UE92 P115 – Pin A

S/N UE93 & higher P115 – Pin H







Fuel Flow, Eng 1 All P131 - Pin F (+) Pin E (-)

Fuel Flow, Eng 2 All P132 - Pin F (+) Pin E (-)

ITT, Eng 1 S/N UE1 thru UE92 M13 – Term E2 CHROMEL (+) Term E1 ALUMEL (-)

S/N UE93 & higher P237 – Pin H CHROMEL (+) Pin G ALUMEL (-)

ITT, Eng 2 S/N UE1 thru UE92 M12 – Term E2 CHROMEL (+) Term E1 ALUMEL (-)

S/N UE93 & higher P238 – Pin H CHROMEL (+) Pin G ALUMEL (-)





Flaps Approach All P194 Pin 14C

Flaps Final All P194 Pin 12C

Weight on Wheels All P542 - Pin M

Gear Extended All P200 - Pin 6


All P202 – Pin 11 or 12

BUS Pwr All Supplied Circuit BreakerPrimary Bus Source



16.3 ADAS/ADAS+ Upgrade Connection Chart – 200 & 200T

P&W Engine Services Voltage to Frequency Converters are required for BeechConfiguration 1 and 2 Fuel Flow systems for these model aircraft.

RAYTHEON (BEECH) 200 & 200T

Signal Mfg.Config.




N1, Eng 1 All P115 - Pin A




Fuel Flow, Eng 1 Config 1 P131 – Pin D (+) P131 – Pin C (-)

Config 2 P131 – Pin C (+) P131 – Pin B (-)

Fuel Flow, Eng 2 Config 1 P132 – Pin D (+) P132 – Pin C (-)

Config 2 P132 – Pin C (+) P132 – Pin B (-)







Flaps Approach All P194 - Pin 5C

Flaps Final All P194 - Pin 12C

Weight on Wheels All A100 - Pin 1

Gear Extended All A100 - Pin 6


All Bus Bar Panel Assy.W103




16.4 ADAS/ADAS+ Upgrade Connection Chart – 200CT, A200, A200C, & A200CT

P&W Engine Services Voltage to Frequency Converters are required for BeechConfiguration 1 Fuel Flow Indicator systems in these aircraft.

RAYTHEON (BEECH) 200CT, A200, A200C, & A200CT

Signal Mfg.Config.




N1, Eng 1 Config 1 P115 - Pin A

Config 2 P115 - Pin H







Fuel Flow, Eng 1 Config 1 P131 – Pin C (+) P131 – Pin B (-)

Config 2 P131 – Pin F (+) P131 – Pin E (-)





ITT, Eng 1 Config 1 M112 - CH (+) M112 - AL (-)

Config 2 M112 - CH (+) M112 - AL (-)

Config 3 P237 - Pin H (+CH) P237 - Pin G (-AL)


Config 2 M113 - CH (+) M113 - AL (-)











All A228 Panel Assy. – Battery Bus PwrW103




16.5 ADAS/ADAS+ Upgrade Connection Chart – B200C, B200CT, B200, & B200T

P&W Engine Services Voltage to Frequency Converters are required for BeechConfiguration 1 Fuel Flow Indicator systems in these aircraft.

RAYTHEON (BEECH) B200C, B200CT, B200, & B200TSignal Mfg.

Config.Connection Connection

Torque, Eng 1 Config 1 Supplied TorqueTransducers

Config 2 P119-S(+) P119-T(-)


Config 2 P120-S(+) P120-T(-)
















Config 2 M112 - CH (+) M112 - AL (-)



Config 2 M113 - CH (+) M113 - AL (-)











All A228 Panel Assy. – Battery Bus PwrW103




16.6 ADAS/ADAS+ Upgrade Connection Chart – 300

RAYTHEON (BEECH) 300

Signal Mfg.Config.








Fuel Flow, Eng 1 All P131 – Pin E (+) P131 – Pin C (-)

Fuel Flow, Eng 2 All P132 – Pin E (+) P132 – Pin C (-)












All A1 Circuit Breaker Box Assy.W1




16.7 ADAS/ADAS+ Upgrade Connection Chart – B300

RAYTHEON (BEECH) B300Signal Mfg.



Config 2 Supplied TorqueTransducers


Config 2 Supplied TorqueTransducers









Fuel Flow, Eng 1 Config 1 P131 – Pin E (+) P131 – Pin C (-)

























16.8 ADAS/ADAS+ Upgrade Connection Chart – B300C & 300LW

RAYTHEON (BEECH) B300C & 300LWSignal Mfg.


Torque, Eng 1 Config 1 Supplied Torque Transducers

Config 2 Supplied Torque Transducers

Config 3 P119 - Pin H (+) P119 - Pin G (-)

Torque, Eng 2 Config 1 Supplied Torque Transducers

Config 2 Supplied Torque Transducers

Config 3 P120 – Pin H (+) P120 – Pin G (-)





















Bleed, Eng 1 All H119A22 (Bleed Air ControlSwitch)

Bleed, Eng 2 All H124A22 (Bleed Air ControlSwitch)

Ice Vane, Eng 1 All H208A22 (Ice Vane ControlSwitch)

Ice Vane, Eng 2 All H211A22 (Ice Vane ControlSwitch)










16.9 ADAS - Wiring Diagram No. 1

Configuration: With P&W Engine Services Torque Transducers, and No P&W Engine Services Voltage to Frequency Converter

Transducer

TD2

RED

BLKGRN

Transducer

TD1

RED

BLKGRN

Transducer

TD4 - LOW

RED

BLKGRN

Sig +

Sig -

Sig +

Sig -

Sig +

Sig +

Transducer

TD3 - HIGH

RED

BLKGRN

Sig +

Sig +

Sig +

Sig -

Sig +

Sig -

Transducer

TD6 - LOW

RED

BLKGRN

Transducer

TD5 - HIGH

RED

BLKGRN

GFKEJ

GFKEJ

GFKEJ

GFKEJ

Weight-on-Wheels

Gear Extended

Sig +

Sig +

Proc 1 28VDC In

GND

Proc 2 28VDC In

OAT Probe

AL - REDCH - YEL

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

MICROSWITCH PTTLamp +Lamp -SW1-ONSW1-COMMSW1-OFFSW2-ONSW2-COMMSW2-OFF


1 2

1 2

123456

123456Vertical Accl

SIG

PWRGND

ADAS

System

Processor

J1.AJ1.BJ1.C

J1.L

J1.DJ1.EJ1.FJ1.GJ1.HJ1.JJ1.K

J1.MJ1.NJ1.RJ1.P

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

J3.AJ3.BJ3.CJ3.DJ3.EJ3.FJ3.GJ3.HJ3.JJ3.KJ3.LJ3.MJ3.NJ3.RJ3.P


68

75

9

68

75

9

12

34

12

34

101112

101112

Flaps - Approach

Flaps - Final

Ice Vane ENG 1

Ice Vane ENG 2

1

4

2

3

(1) REFER TO THE CONFIGURATION CHART FOR ALLWIRING CONNECTIONS TO THE AIRCRAFT.

(2) STANDARD INSTALLATION USES A SINGLE COCKPIT DISPLAY

WITH A 15 PIN CONNECTOR. IF THE OPTION TO USE TWO

SEPERATE DISPLAYS AND DOWNLOAD PORT IS CONFIGURED THEN

REFER TO THE CENTER PIN CALLOUT.

NOTES:

TORQUEENG 1

TREND ENG 1

TREND ENG 2

DOWNLOAD PORT

TORQUEENG 2

N1 ENG 1

N2 ENG 1

FUEL FLOWSENSOR ENG 1

ITT ENG 1

N1 ENG 2

N2 ENG 2

AC PITOT

AC STATIC

ENGINE FIREWALL CONN

LEFT ENGINE WING ROOTSPARE WIRE SPLICES

ITT ENG 2

RIGHT ENGINE WING ROOTSPARE WIRE SPLICES



WHT/ORG

WHT/BLU

WHT/GRN

WHT

WHT/ORG

WHT/GRN

WHT/BLU

WHT

WHT/ORGWHT/BLU

WHT

WHT/BLU

RED

YEL

WHT

WHT

WHT

WHT

WHT

WHT

WHT/BLU

RED

YEL

WHT/ORG

WHT

WHT/BLU

WHT/GRN

REDYEL

WHT/BLU

WHT

WHT

WHT

COCKPIT 15 PIN CONNSHOWN - STANDARD

WHT/ORG

WHT/GRNWHT

WHT/BLU

WHT/ORGWHT/GRNWHT

WHT/BLU

WHT/BLUWHT

WHT/GRNWHT/ORG

BLEED ENG 1

1 AMP BREAKERS INSTALLED

WHT

WHT/ORG

WHT/BLU

3

4

1

2

4

3

2

1

1

4

2

3

OPTIONAL COCKPITCONNECTORS

COCKPIT DISPLAY ASSEMBLY

OAT

BLEED ENG 2

WHT/BLU

WHT

ACCL CONN

PROC PWR

Figure 45: ADAS – With Torque Transducers and Without voltage to Frequency Converter




Configuration: With No P&W Engine Services Torque Transducers, And With No P&W Engine Services Voltage to Frequency Converter

PROC PWR

NOTE: INSULATE AND TIEBACK UNUSED WIRES

1

4

2

3

3

4

1

2

Sig +

Sig -

Transducer

TD1

RED

BLKGRN

Transducer

TD2

RED

BLKGRN

Sig +

Sig +

Sig +

Sig +

Sig -

Flaps - Approach

Flaps - FinalSig +

Sig -

Sig +

Sig -

Sig + Proc 1 28VDC In

GND

Proc 2 28VDC In

Sig +

Sig +

Weight-on-Wheels

Gear Extended

Ice Vane ENG 1

Ice Vane ENG 2

OAT Probe

AL - REDCH - YEL

68

75

9

68

75

9

12

34

12

34

101112

101112

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

1 2

1 2



Sig +

Sig -

Vertical Accl

SIG

PWRGND

ADASSystemProcessor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




123456

123456

Sig +

Sig -

TORQUE ENG 1

DOWNLOAD PORT

TREND ENG 2

TREND ENG 1

FUEL FLOWSENSORENG 1

N2 ENG 1

N1 ENG 1

N1 ENG 2

ITT ENG 1

AC STATIC

AC PITOT

N2 ENG 2

WHT/ORG

FUEL FLOWSENSORENG 2

ITT ENG 2

WHT

WHT/BLU

YEL

RED

WHT/BLU

WHT

WHT

WHT

WHT

WHT

RED

WHT/BLU

WHT

WHT

WHT/ORG

YEL

WHT/GRN

WHT/BLU

YELRED

WHT

WHT/BLU

WHT

WHT

COCKPIT 15 PIN CONN

SHOWN - STANDARD

WHTWHT/GRN

WHT/ORG

WHT/ORG

WHT/BLU

WHT/BLUWHT

WHT/GRN

WHT/GRN

WHTWHT/BLU

BLEED ENG 1

WHT/ORG

WHT


WHT/ORG

WHT/BLU

OPTIONAL COCKPIT

CONNECTORS

1

4

2

3

4

3

2

1





OAT


BLEED ENG 2

NOTES:

WHT/BLUACCL CONN

WHT

WHT/BLUWHT/ORG

WHT/GRN


WHT

WHT/ORG

WHT/GRN

TORQUE ENG 2WHT

WHT/BLU

(1) REFER TO THE CONFIGURATION CHART FOR ALL

WIRING CONNECTIONS TO THE AIRCRAFT.

Figure 46: ADAS – Without Torque Transducers and Without voltage to Frequency Converter




Configuration: With P&W Engine Services Torque Transducers, And With P&W Engine Services Voltage to Frequency Converter

Transducer

TD4 - LOW

RED

BLKGRN

Sig +

Sig -

Transducer

TD3 - HIGH

RED

BLKGRN

Sig +

Sig +

Sig -

Transducer

TD6 - LOW

RED

BLKGRN

Transducer

TD5 - HIGH

RED

BLKGRN

GFKEJ

GFKEJ

Weight-on-Wheels

Gear Extended

OAT Probe

AL - REDCH - YEL

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



1 2

68

75

9

68

75

9

12

34

12

34

101112

101112

Flaps - Approach

Flaps - Final

Sig +

Sig -

Sig +

Sig -

Sig +

Sig +

1 2

594837261

Transducer

TD1

RED

BLKGRN

Transducer

TD2

RED

BLKGRN

Proc 1 28VDC In

GND

Proc 2 28VDC In

Ice Vane ENG 1

Ice Vane ENG 2

Sig +

Sig +

Sig +

GFKEJ

GFKEJ

ADASSystemProcessor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




123456

123456Vertical Accl

SIG

PWRGND

1

4

2

3

(1) REFER TO THE CONFIGURATION CHART FOR ALLWIRING CONNECTIONS TO THE AIRCRAFT.





NOTES:

TORQUEENG 1

TREND ENG 1

TREND ENG 2

DOWNLOAD PORT

TORQUE ENG 2

N1 ENG 1

N2 ENG 2


ITT ENG 1

N2 ENG 2

AC PITOT

AC STATIC

ENGINE FIREWALLCONN

ITT ENG 2

RIGHT ENGINE WING ROOTSPARE WIRE SPLICES


WHT/ORG

WHT/BLU

WHT/GRN

WHT

WHT/ORG

WHT/GRN

WHT/BLU

WHT

WHT/ORG

RED

YEL

WHT

WHT

WHT

WHT/BLU

WHT/ORG

WHT

WHT/BLU

WHT/GRN

REDYEL

WHT/BLU

WHT

WHT

WHT

COCKPIT 15 PIN CONNSHOWN - STANDARD

WHT/ORG

WHT/GRNWHT

WHT/BLU

WHT/ORGWHT/GRNWHT

WHT/BLU

WHT/BLUWHT

WHT/GRNWHT/ORG

BLEED ENG 1


WHT

WHT/ORG

WHT/BLU

3

4

1

2

4

3

2

1

1

4

2

3

OPTIONAL COCKPITCONNECTORS


OAT

BLEED ENG 2

WHT/BLU

WHT

WHT/BLU

WHT

FUEL FLOWCONVERTER


WHT

WHT

N1 ENG 2

WHT

WHT/BLU

WHT WHT/BLUWHT

WHT

WHT

YEL

RED

WHTWHT/BLU

LEFT ENGINEWING ROOTSPARE WIRESPLICES

FUEL FLOWENG 2 PROC

WHT/BLUFUEL

FLOW

ENG

2INPUT

FUEL

FLOW

ENG1

PROC

FUEL FLOWENG 1 INPUT

CONV PWR

WHT/BLU

ACCL CONN

WHT

PROC PWR

Figure 47: ADAS – With Torque Transducers and With Voltage to Frequency Converter




Configuration: With No P&W Engine Services Torque Transducers, And With P&W Engine Services Voltage to Frequency Converter

Sig +

Sig -

Transducer

TD1

RED

BLKGRN

Transducer

TD2

RED

BLKGRN

Sig +

Sig +

Sig +

Flaps - Approach

Flaps - Final

Sig +

Sig -

Sig +

Proc 1 28VDC In

GND

Proc 2 28VDC In

Sig +

Sig +

Weight-on-Wheels

Gear Extended


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

Ice Vane ENG 1

Ice Vane ENG 2

OAT Probe

AL - REDCH - YEL

1 2

1 2

Vertical Accl

SIG

PWRGND

123456

123456

68

75

9

68

75

9

12

34

12

34

101112

101112


Sig +

Sig -

Sig +

Sig -

ADAS

System

Processor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




TORQUE ENG 1

FUEL

FLOW

ENG

1PROC

FUEL FLOW ENG 1INPUT

N1 ENG 1

TREND ENG 2

TREND ENG 1

N2 ENG 1

DOWNLOAD PORT

ITT ENG 1

AC PITOT

N2 ENG 2

N1 ENG 2

ITT ENG 2

AC STATIC

WHT/BLUWHT/ORG

RED

WHT

WHT

YEL

WHT

WHT

WHT

WHT/ORG

YEL

RED

WHT/BLU

WHT

YELRED

WHT/GRN

WHT

WHT

WHT

WHT/BLU

WHT/BLUWHT/GRN

COCKPIT 15 PIN CONN

SHOWN - STANDARD

WHT

WHT/ORG

WHTWHT/GRN

WHT/ORG

WHT/GRNWHT/ORG

WHT/BLU

WHT/BLUWHT

WHT/GRN

WHTWHT/BLU


BLEED ENG 1

WHT/ORG

PROC PWRWHT/ORG

WHT

1

4

2

3

4

3

2

1

WHT/BLU

OAT


OPTIONAL COCKPIT

CONNECTORS

BLEED ENG 2





WHT

WHT/BLU

NOTES:

WHT/ORG

WHT/GRN

ACCL CONN

WHT

WHT/BLU

TORQUE ENG 2



3

4

1

2

1

4

2

3


594837261

Sig +

Sig -

Sig +

Sig -

FUEL FLOWSENSOR ENG 1 WHT/BLU

WHT/BLU

WHT

WHT


FUEL FLOWCONVERTER

WHT/BLU

WHT/BLU

WHTWHT

WHT

WHT/BLU

WHT

WHT


CONV PWR

FUEL

FLOW

ENG

2INPUT

FUEL FLOWENG 2 PROC

Figure 48: ADAS – With Torque Transducers and With Voltage to Frequency Converter



16.13 ADAS+ Upgrade - Wiring Diagram No. 1

Configuration: With P&W Engine Services Torque Transducers, and No P&W Engine Services Voltage to Frequency Converter

LEFT ENGINE WING ROOTSPARE WIRE SPLICES



RIGHT ENGINE WING ROOT

SPARE WIRE SPLICES

Transducer

TD4 - LOW

RED

BLKGRN

Transducer

TD1

RED

BLKGRN

Transducer

TD2

RED

BLKGRN

Sig +

Sig -

Sig +

Sig -

Sig +

Transducer

TD3 - HIGH

RED

BLKGRN

Sig +

Sig +

Sig -

Sig +

Sig +

Transducer

TD6 - LOW

RED

BLKGRN

Sig +

Sig -

.

.

.

.

.

.

.

.

.

.

.

.

.

.

.

.

.

.

.

.

Transducer

TD5 - HIGH

RED

BLKGRN

Sig +

Weight-on-Wheels

Gear Extended

Flaps - Approach

Flaps - Final

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

Sig +


1 2

1 2

68

75

9

68

75

9

12

34

12

34

101112

101112

Vertical Accl

SIG

PWRGND

123456

123456

Eng 1 Ice Vane

Eng 2 Ice VaneADAS

System

Processor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




Bus Power In

GND

Batt Power In

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

WHT

WHT/BLU


WITH A 15 PIN CONNECTOR. IF THE OPTION IS TO USE A

SEPERATE DISPLAY AND DOWNLOAD PORT CONFIGURATION THEN


COCKPIT 15 PIN CONN

SHOWN - STANDARDNOTES:



NOTE: MODELS 1900C,

200, & 300 USE TWO

(2) FUSES. MODEL

1900D USES 1 FUSE

& 1 CIRCUIT BREAKER

WHT/BLUWHT

WHT/GRNWHT/ORG

DOWNLOAD PORT

ENG1TREND LAMP

ENGINE ONETORQUE

AC PITOT

ENGINE TWO N2

ENGINE TWO N1

ENGINE ONE ITT

ENGINE ONE Wf

ENGINE ONE N2

ENGINE ONE N1

ENGINE TWOTORQUE

WHT/ORG

WHT

WHT/GRN

WHT/BLU

WHT/ORG

ENGINE TWO Wf

ENGINE TWO ITT

AC STATIC

RED

WHT/BLU

WHT

WHT/BLUWHT/ORG

WHT

WHT/BLU

WHT/GRN

WHT/BLU

WHT

WHT

WHT

WHT

WHT

WHT

YEL

WHT/GRN

WHT/BLU

WHT

WHT/ORG

YEL

RED

WHT/ORG

WHT/BLU

WHT

WHT

WHT/BLU

WHT/BLU

WHT/BLUWHT

WHT/GRNWHT/ORG

WHT/BLU

WHTWHT/GRN

WHT


ENGINE ONE BLEED

WHT/ORGWHT/GRN

WHT


OPTIONAL COCKPIT

CONNECTORS

1

4

2

3

4

3

2

1

3

4

1

2

WHT/BLU

WHT/ORG

ACCL CONN

1

4

2

3

ENGINE TWO BLEED

OAT

PROC PWR

Figure 49: ADAS+ Upgrade – With Torque Transducers and Without voltage to Frequency Converter




Configuration: With No P&W Engine Services Torque Transducers, And With No P&W Engine Services Voltage to Frequency Converter

Transducer

TD1

RED

BLKGRN

Transducer

TD2

RED

BLKGRN

Sig +

Sig -

Sig +

Sig -

Sig +

Sig +

Sig +

Sig -

Sig +

Sig +

Sig +

Sig -

Sig +

Weight-on-Wheels

Gear Extended

Flaps - Approach

Flaps - Final

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

Sig +

1 2

1 2


68

75

9

68

75

9

12

34

12

34

101112

101112

Vertical Accl

SIG

PWRGND

123456

123456

Eng 1 Ice Vane

Eng 2 Ice Vane

ADAS

System

Processor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




Bus Power In

GND

Batt Power In

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

ENGINE ONE Wf

ENGINE ONE N2

ENGINE ONE N1

ENGINE TWOTORQUE

DOWNLOAD PORT

ENG 1TREND LAMP

ENGINE ONETORQUE

ENGINE TWO ITT

AC STATIC

AC PITOT

ENGINE TWO N2

ENGINE TWO N1

ENGINE ONE ITT

WHT/ORG

WHT

WHT/GRNWHT/BLUWHT/ORG

ENGINE TWO Wf

RED

WHT/BLU

WHT

WHT/BLUWHT/ORG

WHT

WHT/BLUWHT/GRN

WHT/BLU

WHT

WHT

WHT

WHT

WHT

WHT

YEL

WHT/GRN

WHT/BLU

WHT

WHT/ORG

YEL

RED

WHT/BLU

WHT

WHT

WHT/BLU

WHTWHT/GRNWHT/ORG

WHT/BLU

WHTWHT/GRN

WHT/ORG

COCKPIT 15 PIN CONN

SHOWN - STANDARD

1 AMP BREAKERS/FUSES INSTALLED

ENGINE ONE BLEED

WHT/ORGWHT/GRN

WHTWHT/BLU

WHT/BLU

1

4

2

3

4

3

2

1

3

4

1

2

WHT/BLU

WHT/ORG

WHT

1

4

2

3

ENGINE TWO BLEED

OAT


OPTIONAL COCKPIT

CONNECTORS

PROC PWR

ACCL CONN

NOTE: INSULATE AND TIE

BACK UNUSED WIRES

WHT/BLU

WHT

Sig +

Sig -


BACK UNUSED WIRES

NOTE: MODELS 1900C,

200, & 300 USE TWO

(2) FUSES. MODEL

1900D USES 1 FUSE

& 1 CIRCUIT BREAKER

WHTWHT/BLU





WHT/GRNWHT/ORG



NOTES:

Sig +

Sig -

Figure 50: ADAS+ Upgrade – Without Torque Transducers and Without voltage to Frequency Converter




Configuration: With P&W Engine Services Torque Transducers, And With P&W Engine Services Voltage to Frequency Converter

NOTE: MODELS 1900C,

200, & 300 USE TWO

(2) FUSES. MODEL

1900D USES 1 FUSE

& 1 CIRCUIT BREAKER

PROC PWR

FREQ 1 +

Sig +

Transducer

TD3 - HIGH

RED

BLKGRN

Sig +

Sig -

Transducer

TD4 - LOW

RED

BLKGRN

Transducer

TD6 - LOW

RED

BLKGRN

Sig +

Sig -

.

.

.

.

.

.

.

.

.

.

Transducer

TD5 - HIGH

RED

BLKGRN

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

Weight-on-Wheels

Gear Extended

Flaps - Approach

Flaps - Final

68

75

9

68

75

9

12

34

12

34

101112

101112

1 2

Sig +

Sig +

Sig +

Sig -

Sig +

Sig -

Transducer

TD2

RED

BLKGRN

Transducer

TD1

RED

BLKGRN

594837261

1 2

Sig +

Sig +

123456

123456

ADAS

System

Processor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




.

.

.

.

.

.

.

.

.

.

Sig +

Vertical Accl

SIG

PWRGND

ENG1TREND LAMP

TORQUEENG 1

1

4

2

3

AC PITOT

N2 ENG 2

ITT ENG 1

FUEL FLOWENG 1

N2 ENG 1

N1 ENG 1

TORQUE ENG 2

DOWNLOAD PORT

WHT/GRN

WHT/BLU

WHT/ORG


RIGHT ENGINE WING ROOT

SPARE WIRE SPLICES

ITT ENG 2

ENGINE FIREWALLCONN

AC STATIC

YEL

RED

WHT/ORG

WHT/BLU

WHT/GRN

WHT

WHT/GRN

WHT/BLU

WHT

WHT/ORG

WHT/BLU

WHT

WHT

WHT

WHT/ORG

FREQ 1 -

WHT/GRNWHT/ORG

WHT/BLU

WHTWHT/GRN

FUEL

FLOW

CONVERTER

FUEL FLOWENG 2

WHTN1 ENG 2

WHT

WHT

WHT

WHT/BLU

WHT/BLUWHT

WHT

WHT





COCKPIT 15 PIN CONN

SHOWN - STANDARDNOTES:



WHT/BLU

WHT/BLU

WHT

WHT

Bus Power In

GND

Batt Power In

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

RED

YEL


Eng 1 Ice Vane

Eng 2 Ice Vane

WHT

WHT/BLU

WHT/BLUWHT

LEFT ENGINEWING ROOTSPARE WIRESPLICES

FREQ 2 -

WHT/BLU

FREQ

2+

WHT/BLUWHT

WHT/GRNWHT/ORG

WHT/BLUWHT

WHT/GRN

WHTWHT/BLU


BLEED ENG 1

WHT/ORG

WHT/ORG

WHT

4

3

2

1

3

4

1

2

WHT/BLU


OPTIONAL COCKPIT

CONNECTORS

1

4

2

3BLEED ENG 2

OAT

WHT/BLU

WHT

CONV PWR

WHT/BLU

WHT

ACCL CONN

WHT

WHT/ORG

Figure 51: ADAS+ Upgrade – With Torque Transducers and With voltage to Frequency Converter




Configuration: With No P&W Engine Services Torque Transducers, And With P&W Engine Services Voltage to Frequency Converter

TORQUE ENG 1

FREQ 1 +

FREQ 1 -

N1 ENG 1

N2 ENG 1

DOWNLOAD PORT

ITT ENG 1

AC PITOT

N2 ENG 2

N1 ENG 2

ITT ENG 2

AC STATIC

WHT/BLUWHT/ORG

RED

WHT

WHT

YEL

WHT

WHT

WHT

WHT/ORG

YEL

RED

WHT/BLU

WHT

WHT/GRN

WHT

WHT

WHT

WHT/BLU

WHT/BLUWHT/GRN

COCKPIT 15 PIN CONN

SHOWN - STANDARD

WHT/BLU

WHT/ORG

WHTWHT/GRN

WHT/ORG

WHT/GRNWHT/ORG

WHT/BLU

WHT/BLUWHT

WHT/GRN

WHTWHT/BLU

1 AMP BREAKERS/FUSES INSTALLED

BLEED ENG 1

WHT/ORG

PROC PWR

WHT/ORG

WHT

1

4

2

3

4

3

2

1

WHT/BLU

OAT


OPTIONAL COCKPIT

CONNECTORS

BLEED ENG 2





NOTES:

WHT/GRN

ACCL CONN

WHT/BLU

TORQUE ENG 2



3

4

1

2

1

4

2

3


BACK UNUSED WIRES

Sig +

Sig +

Sig -

Transducer

TD1

RED

BLKGRN

Transducer

TD2

RED

BLKGRN

Flaps - Approach

Flaps - FinalSig +

Sig -

Sig +

Sig +

Sig +

Sig +

Weight-on-Wheels

Gear Extended

1 2

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


Vertical Accl

SIG

PWRGND

123456

123456

1 2

Sig +

Sig -

Sig +

Sig -

ADAS

System

Processor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




68

75

9

68

75

9

12

34

12

34

101112

101112

Sig +

Sig -

Sig +

594837261

Sig +

Sig -

WHTWHT/ORG

OAT Probe

OAT-GWHT

OAT-R+RED

OAT-DRED

OAT R-WHT

FREQ 2 -

Bus Power In

GND

Batt Power In

NOTE: MODELS 1900C,

200, & 300 USE TWO

(2) FUSES. MODEL

1900D USES 1 FUSE

& 1 CIRCUIT BREAKER

Eng 1 Ice Vane

Eng 2 Ice Vane

WHT

WHT/BLU

WHT

WHT/ORGWHT/BLU

WHT/GRN

FUEL FLOWENG 1 WHT/BLU

WHT/BLU

WHT

WHT

FUEL FLOWENG 2

FUEL

FLOW

CONVERTER

WHT/BLU

WHT/BLU

WHTWHT

WHT

WHT/BLU

WHT

WHT

ENG 1TREND LAMP


BACK UNUSED WIRES

CONV PWR

FREQ 2+

Figure 52: ADAS+ Upgrade – Without Torque Transducers and With voltage to Frequency Converter

Documents

TWIN-T-260-1 Rev H - Altair Avionics Ground Station Rev H.pdf · 2.1 AIRCRAFT DATA ACQUISITION SYSTEM ... TWIN-T-260-1 Pratt & Whitney Engine Services, Inc. Proprietary ... 72 16.14