ADAS/ADAS+ Upgrade Installation Manual TWIN-I-010-1 Rev O.pdf · 2009-03-11 · Pratt & Whitney Engine Services, Inc. 249 Vanderbilt Ave Norwood, MA 02062 249 Vanderbilt Ave., Norwood,

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+ Upgrade

Installation Manual

TWIN-I-010-1For Raytheon Model 200, 300, & 1900 Series

Manual Number: TWIN-I-010-1

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

Release Date: December 16, 2002 J Cipolla, Manager of QA

Revision Date: February 24, 2009 S Sackos, Manager ofManufacturing Services

Revision Ltr: O D Fetherston, Manager ofCustomer Solutions / Engineering

Total Pages: 103

Approvals:

P&W ENGINE SERVICES, INC. ADAS/ADAS+ Upgrade TWIN-I-010-1Raytheon Aircraft Company Model 200, 300, & 1900 Series

iTWIN-I-010-1 Pratt & Whitney Engine Services, Inc. Proprietary

PREFACE

Disclaimer

Like all instrumentation, the Pratt & Whitney Engine Services, Inc. ADAS+ requires knowledgeable interpretation by thepilot. Any recommendations and operating procedures contained in this manual shall not supersede the Aircraft or Enginemanufacturer recommendations, operating procedures, or limits. The Pratt & Whitney Engine Services, Inc. ADAS+ shouldnot be used as a primary guide monitoring the Aircraft and Engine manufacturers operating limits. Pratt & Whitney EngineServices, 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.


iiTWIN-I-010-1 Pratt & Whitney Engine Services, Inc. Proprietary

REVISION HISTORY

Rev O O O O O O O O O O O O O O O ORev Statusof Sheets Sheet i ii 1 2 3 4 5 6 7 8 9 10 11 12 13 14

Rev O O O O O O O O O O O O O O O OSheet 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30Rev O O O O O O O O O O O O O O O OSheet 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46Rev O O O O O O O O O O O O O O O OSheet 47 48 49 50 51 52 53 54 55 56 57 58 59 60 61 62Rev O O O O O O O O O O O O O O O OSheet 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78Rev O O O O O O O O O O O O O O O OSheet 79 80 81 82 83 84 85 86 87 88 89 90 91 92 93 94Rev O O O O O O O O OSheet 95 96 97 98 99 100 101 102 103

LOG OF REVISIONS

REV. NO ECO # DESCRIPTION DATE PAGES REVISED

A N/A Initial Release 12/16/2002

L 765 Add Revision Section. Revise Battery PowerConnection. Edit Vertical Accelerometer wiring.

05/20/2004 Cover, ii, 36, and55 – 62.

M 797 Edit wire schematic page 69, change parts list toreflect revised power connections.

11/04/2004 ii, 69, 94

N 869 Reformat and revise Pressure Bulkhead FeedThrough Instructions. Update parts list to includePressure Bulkhead Doubler.

07/01/2006 All

O 997 Complete update of the manual to include newcompany name and address. Formatted themanual, fixed typographical errors. Updated partnumbers in the lists and text. Added note that theVertical Accelerometer is no longer available.

02/24/2009 All

NOTE:If the ADAS/ADAS+ Upgrade Installation Manuals are revised, all operators will be provided witha copy of the applicable revision. If you have a subscription with TurbineTracker™, you will beinformed via email of new revisions to this manual. In addition to this, P&W Engine Servicesmaintains the latest versions of all manuals in the Support Section of TurbineTracker™.

If you are not a subscriber to TurbineTracker™, you may call Pratt & Whitney Engine ServicesCustomer Support at 781-762-8600 for the latest revision.


iiiTWIN-I-010-1 Pratt & Whitney Engine Services, Inc. Proprietary

TABLE OF CONTENTS

1 THE P&W ENGINE SERVICES TWIN ENGINE AIRCRAFT DATA ACQUISITION SYSTEMS..... 12 INSTALLATION ............................................................................................................................... 2

2.1. How to Use This Installation Manual............................................................................... 22.2. System Overview............................................................................................................... 32.3. Preparation ........................................................................................................................ 42.4. Mechanical Installation Instructions ............................................................................... 5

2.4.1. Mounting the System Processor............................................................................... 62.4.2. Pressure Bulkhead Fitting......................................................................................... 82.4.3. TREND Switches and Download Port FOR ADAS ................................................. 102.4.4. TREND Switches and Download Port FOR ADAS+ Upgrade ................................ 112.4.5. Torque Transducers ............................................................................................... 122.4.6. Aircraft Outside Air Temperature Probe ................................................................. 152.4.7. Pitot & Static Pressure Transducers....................................................................... 192.4.8. Aircraft Vertical Accelerometer ............................................................................... 23

2.5. Electrical Installation Instructions................................................................................. 242.5.1. J1 Harness (Power / Sensor).................................................................................. 252.5.2. J2 Harness (Engine 1) ............................................................................................ 262.5.3. J3 Harness (Engine 2) ............................................................................................ 282.5.4. Comm Harness (TREND Switch / Download Port)................................................. 302.5.5. Engine 1 & 2 Pre-Existing Torque Sensor .............................................................. 322.5.6. Engine 1 & 2 P&W Engine Services Supplied Torque Sensor ............................... 322.5.7. Engine N1 Speed Signals ....................................................................................... 332.5.8. Engine N2 Speed Signals ....................................................................................... 332.5.9. Voltage to Frequency Converter............................................................................. 342.5.10. Engine Fuel Flow Signals ....................................................................................... 352.5.11. Engine ITT Signals.................................................................................................. 362.5.12. Engine Bleed Signals.............................................................................................. 362.5.13. Ice Vane Signals ..................................................................................................... 362.5.14. Flap Position Signals .............................................................................................. 372.5.15. Weight On Wheels Signal....................................................................................... 372.5.16. Gear Extended Signal............................................................................................. 372.5.17. Pitot and Static Pressure Sensors .......................................................................... 382.5.18. Outside Air Temperature Sensor for adas .............................................................. 382.5.19. Outside Air Temperature Sensor for adas+............................................................ 392.5.20. Aircraft Accelerometer ............................................................................................ 392.5.21. Power and Ground Connections FOR ADAS ......................................................... 402.5.22. Power and Ground Connections FOR ADAS+ Upgrade ........................................ 41

2.6. Final Wiring Instructions:............................................................................................... 422.7. Initial Processor Test ...................................................................................................... 42

3 SYSTEM CONFIGURATION AND CALIBRATION....................................................................... 443.1. Definitions........................................................................................................................ 453.2. Processor (MLU) Configuration..................................................................................... 463.3. Pre-Calibration Sensor and Discrete Signal Test (Live Data Display) ....................... 463.4. Calibration Using Test Equipment ................................................................................ 483.5. Calibration Using Aircraft Cockpit Instruments........................................................... 50

4 AIRCRAFT TESTING .................................................................................................................... 534.1. Aircraft Ground Test ....................................................................................................... 534.2. Aircraft Flight Test .......................................................................................................... 574.3. Test Data Retrieval and Review ..................................................................................... 584.4. Continued Airworthiness Instructions.......................................................................... 584.5. Documentation ................................................................................................................ 58

5 AIRCRAFT CONNECTION TABLES ............................................................................................ 595.1. 1900 & 1900C ................................................................................................................... 595.2. 1900D................................................................................................................................ 60


ivTWIN-I-010-1 Pratt & Whitney Engine Services, Inc. Proprietary

5.3. 200 & 200T........................................................................................................................ 615.4. 200CT, A200, A200C, & A200CT..................................................................................... 625.5. B200C, B200CT, B200, B200T ........................................................................................ 635.6. 300 .................................................................................................................................... 645.7. B300.................................................................................................................................. 655.8. B300C & 300LW............................................................................................................... 66

6 WIRING DIAGRAMS ..................................................................................................................... 676.1. ADAS ................................................................................................................................ 67

6.1.1. Wiring Diagram No. 1 for ADAS: ............................................................................ 676.1.2. Wiring Diagram No. 2 for ADAS: ............................................................................ 686.1.3. Wiring Diagram No. 3 for ADAS: ............................................................................ 696.1.4. Wiring Diagram No. 4 for ADAS: ............................................................................ 70

6.2. ADAS+ UPGRADE ........................................................................................................... 716.2.1. Wiring Diagram No. 1 FOR ADAS+ UPGRADE: .................................................... 716.2.2. Wiring Diagram No. 2 FOR ADAS+ UPGRADE: .................................................... 726.2.3. Wiring Diagram No. 3 FOR ADAS+ UPGRADE: .................................................... 736.2.4. Wiring Diagram No. 4 FOR ADAS+ UPGRADE: .................................................... 74

7 HARNESS CONNECTOR SIGNAL PINOUTS.............................................................................. 757.1. ADAS Connector Signal Points ..................................................................................... 75

7.1.1. Harness J1, Connector “S” ..................................................................................... 757.1.2. Harness J2, Connector “SA”................................................................................... 767.1.3. Harness J3 Connector, “SB”................................................................................... 77

7.2. ADAS+ Upgrade Connector Signal Points ................................................................... 787.2.1. Harness J1, Connector “S” ..................................................................................... 787.2.2. Harness J2, Connector “SA”................................................................................... 797.2.3. Harness J3 Connector, “SB”................................................................................... 80

7.3. Harness “Comm” Connectors for ADAS ...................................................................... 817.3.1. (Cockpit TREND Switch Harness) – Single Display ............................................... 817.3.2. (Cockpit TREND Switch Harness) – Dual Display.................................................. 81

7.4. Harness “Comm” Connectors for ADAS+ Upgrade .................................................... 827.4.1. Cockpit TREND Switch Harness ............................................................................ 82

8 SYSTEM OPERATION OVERVIEW.............................................................................................. 838.1. Capabilities ...................................................................................................................... 83

8.1.1. Engine Run Logging ............................................................................................... 838.1.2. Cycle Logging ......................................................................................................... 838.1.3. Event Monitoring ..................................................................................................... 83

8.2. Functional Descriptions ................................................................................................. 848.2.1. Initialization ............................................................................................................. 848.2.2. SYSTEM MODES FOR ADAS ONLY..................................................................... 848.2.3. Run Mode FOR ADAS ONLY ................................................................................. 858.2.4. Lamp States in Run Mode FOR ADAS ONLY: ....................................................... 858.2.5. Configuration Mode FOR ADAS ONLY .................................................................. 868.2.6. Manual Self Test (Loopback Test) FOR ADAS ONLY............................................ 868.2.7. Run Mode FOR ADAS+ UPGRADE ONLY ............................................................ 868.2.8. LAMP STATES IN Run Mode FOR ADAS+ UPGRADE ONLY.............................. 87

9 PARTS LIST .................................................................................................................................. 889.1. Part Kits by Aircraft for ADAS ONLY: ........................................................................... 889.2. Part Kits By Aircraft for ADAS+ Upgrade ONLY: ......................................................... 919.3. Components for ADAS and ADAS+ Upgrade by Kit Number ..................................... 94

10 MAINTENANCE REQUIREMENTS............................................................................................... 9911 SERVICE...................................................................................................................................... 100

11.1. Customer Support......................................................................................................... 10011.2. Disclaimer ...................................................................................................................... 100

12 SPECIFICATIONS ....................................................................................................................... 10112.1. P&W Engine Services Twin Engine ADAS/ADAS+ Upgrade TWIN-K-010 ............... 101

APPENDIX A..................................................................................................................................... 103


vTWIN-I-010-1 Pratt & Whitney Engine Services, Inc. Proprietary

LIST OF FIGURES

FIGURE 1: SYSTEM PROCESSOR TO BRACKET MOUNTING .......................................................................................... 6FIGURE 2: BRACKET TO AVIONICS TRAY MOUNTING ................................................................................................... 7FIGURE 3: LOW PROFILE MOUNTING BRACKET........................................................................................................... 7FIGURE 4: TYPICAL CLEAR BAY AREAS OF FWD PRESSURE BULKHEAD (LOOKING AFT)................................................ 9FIGURE 5: SINGLE COCKPIT DISPLAY (CENTER CONSOLE MOUNT ASSEMBLY) .......................................................... 10FIGURE 6: DUAL COCKPIT DISPLAY (DISCRETE COMPONENT MOUNT)....................................................................... 10FIGURE 7: SINGLE COCKPIT DISPLAY (CENTER CONSOLE MOUNT ASSEMBLY) .......................................................... 11FIGURE 8: COCKPIT DISPLAY (DISCRETE COMPONENT MOUNT)................................................................................ 11FIGURE 9: STANDARD P&W ENGINE SERVICES TORQUE TRANSDUCER INSTALLATION............................................... 13FIGURE 10: P&W ENGINE SERVICES HIGH PRECISION TORQUE TRANSDUCER INSTALLATION .................................... 14FIGURE 11: OAT PROBE MOUNTING (NON-1900 SERIES AIRCRAFT) ........................................................................ 15FIGURE 12: OAT PROBE MOUNTING (1900, 1900C, 1900D SERIES AIRCRAFT, ONLY) .............................................. 17FIGURE 13: PITOT / STATIC TRANSDUCER MOUNTING............................................................................................... 19FIGURE 14: PITOT / STATIC BULKHEAD PRESSURE CONNECTIONS (NON-1900D) ...................................................... 21FIGURE 15: PITOT / STATIC BULKHEAD PRESSURE CONNECTIONS (1900D) .............................................................. 22FIGURE 16: ACCELEROMETER MOUNT AND ORIENTATION (VIEWED FROM ABOVE) .................................................... 23FIGURE 17: SINGLE OR DUAL WIRE SPLICE ............................................................................................................. 24FIGURE 18: SHIELD CONNECTION (OUTER HEAT SHRINK TUBING NOT SHOWN) ........................................................... 24FIGURE 19: FIREWALL WITH ADDITIONAL ADAS/ADAS+ UPGRADE CONNECTOR ..................................................... 27


1TWIN-I-010-1 Pratt & Whitney Engine Services, Inc. Proprietary

1 THE P&W ENGINE SERVICES TWIN ENGINE AIRCRAFT DATAACQUISITION SYSTEMS

This manual describes the installation of the P&W Engine Services’ ADAS/ADAS+ upgrade monitoringsystems.

Pratt & Whitney Engine Services, Inc. Aircraft Data Acquisition System has been designed to provide theoperator with engine and airframe electronic monitoring. Both the ADAS and the ADAS

+function with similar

monitoring requirements. The ADAS+

is our latest technology (generation III) and provides additional monitorcapability to the base ADAS system, as described below:

Engine Start Temperature Engine Start Length Minimum Start Voltage Event Time History Recording

The Pratt & Whitney Engine Services, Inc. Aircraft Data Acquisition System (ADAS / ADAS+) provides the

aircraft owner and operator with three types of detailed critical engine and aircraft operational information:

For the pilot, the ADAS/ADAS+ Upgrade provide a start-up warning system for a prior operation thatexceeded permissible ranges. The cockpit display indicates when an automatic trend sample is being taken,and allows the pilot to quickly take a manual sample at any time for either engine.

For maintenance personnel, the ADAS/ADAS+ Upgrade provide a data collection, storage, and analysistool for monitoring the overall health of the aircraft.

For management, the ADAS/ADAS+ Upgrade documents incidents of operation outside of permissiblelimits, useful in spotting patterns of misuse. It can provide computer downloadable data for reports of eachindividual flight or a complete aircraft history, covering all operational exceedances and the maintenanceactions taken in response.

While it does not replace the need for manual recording of data required by FAA approved operatingspecifications and maintenance programs, the P&W Engine Services ADAS/ADAS+ Upgrade are designed toprovide a powerful additional resource and warning system for improved aircraft maintenance, longevity, andsafety.

The P&W Engine Services twin engine ADAS consists of a central processor monitoring 24 aircraft sensorinputs. The processor records the date, time, duration, and maximum and average values of any excessivereading. It counts cycles, records flight times, identifies and measures hot starts and records the maximumvalue observed by each sensor during flight. All collected data is stored internally in non-volatile memory andcan be downloaded to a ground-based computer system for analysis and action.

The P&W Engine Services ADAS+ upgrade consists of a central processor monitoring aircraft sensor inputs.In addition to performing all of the functions of the ADAS, the ADAS+ upgrade also features a sizable buffermemory that dumps all engine parameters leading up to and following an exceedance event into non-volatilememory This data is then available for download and analysis.

With the exception of a trend sample activation button, the P&W Engine Services ADAS/ADAS+ Upgradereceive no inputs by the aircraft pilot or crew, and the recorded data cannot be altered from the cockpit panel.The twin engine Aircraft Data Acquisition System is a passive collector of information and does not participate inany command and control functions of the aircraft or its subsystems.

The P&W Engine Services twin engine ADAS/ADAS+ Upgrade conforms to the data collectionrequirements of Pratt & Whitney's ECTM trending program.



2 INSTALLATION

2.1. How to Use This Installation Manual

The main part of the installation manual consists of mechanical and electrical instruction sections, a set ofaircraft connection tables and a set of wiring diagrams. The mechanical and electrical sections are made up ofinstruction lists that take the following the form:

1.) A heading, which lists the applicable aircraft. Headings look like this:

For All Listed Aircraft Models:

2.) Caution notes, which present things to be aware of while performing the installation. Cautions look like this:

Installation Caution:

Excessive torque on the processor mounting studs can deform the shock mounts. The locking nut should be tightenedonly to the point of contact with the shock mount.

3.) Numbered assembly and wiring instructions, which include boxes for checking off steps as they areperformed. Instructions look like this:

Wiring Instructions:

Perform the following steps for each engine:

Engines1 2

010 Trim the engine ITT cable to length.

To perform the ADAS/ADAS+ Upgrade installation read the system overview. Complete the preparation sectionchecklist. Find the appropriate aircraft connection table and wiring diagram for your model aircraft, and thenfollow the steps for the mechanical and electrical assembly sections. Check off each instruction as it iscompleted. When finished proceed to post-Installation and testing sections of the manual.



2.2. System Overview

The P&W Engine Services twin engine Aircraft Data Acquisition System (ADAS/ADAS+ Upgrade) records andanalyzes 24 signals from locations on the airframe and both engines. The signals are obtained from acombination of aircraft and P&W Engine Services supplied sensors. The main system components and thesignals required are:

Processor (ADAS/ADAS+ Upgrade) - The twin engine processor is mounted in the avionics section ofthe aircraft. It does not require access during flight. The processor is mounted on a suppliedaluminum bracket with Lord Aerospace shock mounts. The processor bracket is mounted to theaircraft. Four connectors are used to join the processor to the system wiring harnesses.

Engine Torque (Engines 1 & 2) - The processor receives torque high and low-pressure signals throughtorque transducers located in each engine. Some aircraft models are equipped with factory-installedtorque transducers, while others require P&W Engine Services supplied torque transducers, which areincluded in the appropriate aircraft component kit. Refer to the Aircraft Connection Tables todetermine which transducers are used for your aircraft. The P&W Engine Services transducers areinserted into an engine’s high and low-pressure torque lines with “T” adapters.

N1 Speed (Engines 1 & 2) - The processor receives an N1 speed signal for each engine throughspliced electrical connections to the existing N1 tach generator gauge wiring.

N2 Speed (Engines 1 & 2) - The processor receives an N2 speed signal for each engine throughspliced electrical connections to the existing N2 tach generator gauge wiring.

Fuel Flow (Engines 1 & 2) - The processor receives a fuel flow rate signal for each engine throughconnections to the existing engine fuel flow gauges. Some aircraft model configurations require that aP&W Engine Services supplied voltage to frequency converter be installed between the processor andthe fuel flow signal source. The converters are included in the appropriate aircraft model componentkits.

ITT (Engines 1 & 2) – The processor receives a T5 temperature signal for each engine throughconnections to the Alumel and Chromel terminals of the existing ITT gauges.

Bleed Air (Engines 1 & 2) – The processor is wired to existing bleed air control switches to determinethe bleed air state.

Ice Vane (Engines 1 & 2) - The processor is wired to existing engine control switches to determine if theengine ice vanes are deployed.

Airspeed / Pitot Pressure – The processor calculates airspeed using a supplied P&W Engine Services0 – 3 PSID pressure transducer connected to the aircraft pitot pressure source.

Altitude / Static Pressure – The processor calculates altitude using a supplied P&W Engine Services 0- 15 PSIA pressure transducer connected to the aircraft static pressure source.

Outside Air Temperature – The processor receives an outside air temperature signal from a suppliedP&W Engine Services temperature sensor located underneath the aircraft adjacent to the nose gear.

Vertical Acceleration – The processor monitors a supplied P&W Engine Services +/- 5g accelerometerto record vertical acceleration loads during landings and flight maneuvers. The sensor is located aft ofthe wing main spar in the center of the fuselage.

Flap Down: Approach – The processor monitors the existing flap control to determine if the flaps areset to the approach configuration.



Flap Down: Final – The processor monitors the existing flap control to determine if the flaps are set inthe full down configuration.

Landing Gear Extended – The processor monitors the existing landing gear control switch to determineif the landing gear is extended.

Weight on Wheels (WOW) – The processor monitors the existing landing gear WOW switch todetermine if the aircraft is on the ground.

TREND Switch - The twin engine ADAS features dual cockpit TREND switches and status lamps whilethe ADAS+ Upgrade utilizes a single TREND switch and status lamp. The TREND switch enables thepilot to sample the engine(s) for trend analysis. On engine start, the lamps indicate whether anexceedance was recorded on a prior engine run. The lamps are also used to indicate a fault conditionin the system. The switch and lamp are installed in a convenient location in the aircraft cockpit.

Data Download Port - The processor uses a serial data download port for communication with a remotecomputer running the P&W Engine Services Monitor Link Program (MLP). The MLP handlesADAS/ADAS+ Upgrade configuration uploads, data downloads, and uploads to the Internet for dataanalysis.

2.3. PreparationThe Pratt & Whitney Engine Services, Inc. ADAS/ADAS+ Upgrade interfaces with many existing aircraft

and engine sensors. It is recommended (although not required) that you check the aircraft and engine functionand performance before and after the installation.

Airline: Planned Install date:

Aircraft Tail #: Left Engine S/N:

Aircraft S/N: Right Engine S/N:

Please complete the above information. The following is a list of items to be completed prior to the startof the ADAS/ADAS+ Upgrade installation.

Baseline Conditions:

1) Ground run and rigging check per “Beech” manual Checked by:(May be waived if performed recently. Provide results.)

2) Gear swing and horn check per “Beech” manual. Checked by:

3) Pitot & static leak check (co-pilot side) per “Beech” manual. Checked by:

4) Aircraft leaks check. Actual value: Checked by:(May be waived if performed recently. Provide results.)



Preliminary Mechanical Preparations:

5) Remove pilot and co-pilot seats. Checked by:

6) Remove both engine upper and lower cowlings. Checked by:

7) Remove partition behind both the pilot and co-pilot. Checked by:

8) Remove L/R wing leading edges adjacent to fuselage. Checked by:

9) Remove the first 3 floorboard panels from the entrance door. Checked by:

Notes:

2.4. Mechanical Installation Instructions

NOTE: All work to be done in accordance with FAAAdvisory Circular 43.13-1B "Acceptable Methods, Techniquesand Practices for Aircraft Inspection and Repair" and with FAAAdvisory Circular 43.13-2A "Acceptable Methods, Techniquesand Practices - Aircraft Alterations"

Please read all instructions completely before beginninginstallation. The P&W Engine Services ADAS/ADAS+ Upgradeinstallation is described in the following steps. It is assumedthat qualified mechanics or avionics technicians will performthe installation.

All aircraft systems interfacing with the P&W Engine Servicestwin engine Aircraft Data Acquisition Systems should bechecked for full functionality before installation begins.

Note: General supplies (solder, crimp splices, heat shrink, tape, etc.) are not includedwith the installation kit.



2.4.1. MOUNTING THE SYSTEM PROCESSOR



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

Assembly Note:

Some configurations of the Beech fuel flow circuit require mounting P&W Engine Services Voltage toFrequency Converters. They are:

Models 200 & 200T using Beech fuel flow configurations 1 & 2.

-and-

Models 200CT, A200, A200C, A200CT, B200 B200C, B200CT, & B200T using Beech fuel flowconfiguration 1.

P&W Engine Services converters are not used or supplied with other aircraft models andconfigurations.

Figure 1: System Processor to Bracket Mounting



Assembly Instructions:

The system processor is mounted in the aircraft avionics bay using mounting bracket, DPU-D-030-1.

Installation Note:

A low profile mounting bracket (DPU-D-094-1) is available if there is a space constraint inmounting the ADAS/ADAS+ Upgrade processor. The voltage to frequency converter cannot beused with this bracket. See Figure 3.

010 Assemble the system processor and P&W Engine Services Voltage to FrequencyConverter (if used) to the mounting bracket following Figure 1 and test fit in a convenientlocation within the avionics compartment. When the P&W Engine Services Voltage toFrequency Converter is used, the four mounting screws should be secured using Loctite®Blue or equivalent.

a. Mark the avionics tray for the location of the four mounting holes.

020 Drill and install the four supplied rivet nuts in the avionics tray.

030 Mount the system processor and bracket to the avionics tray using four screws and fourwashers as shown in Figure 2. Note: The processor may be mounted as shown orupside down (180 from the orientation shown).

Figure 2: Bracket to Avionics Tray Mounting

Figure 3: Low Profile Mounting Bracket



2.4.2. PRESSURE BULKHEAD FITTING


The twin engine ADAS+ uses a Raychem™ pressure bulkhead fitting for routing the harnesses into the aircraft.Depending on the aircraft and what equipment is installed you may or may not need a doubler. ReferenceFigure 4 for typical clear bay areas numbered 1 through 22.


No doubler is required if installing the feed through in bay 11, 12, 13, or 14. Any otherclear bay indicated in Figure 4 requires the supplied doubler. If a doubler already existson the bulkhead it may be used in place of the supplied doubler.

Maintain .25” edge distance between connector hole and structure (Bay 11, 12, 13, or 14).

Maintain .25” edge distance between doubler outer circumference and pressure bulkheadsupporting structure and/or pressure bulkhead bonded doublers (bay locations otherthen 11 through 14).

Ensure that connector is placed as close to lateral bay centerline as possible.

Ensure that the connector through hole does not exceed 1.34”.

Install fasteners and doubler (if applicable) with wet sealant as per Raytheon Aircraft,Beech Airliner Maintenance Manual, Chapter 20, Section 20-10-00.

Choose a location to install the pressure bulkhead connector that will be clear of anyobstructions. Because of possible aircraft alternate equipment the specific mountinglocation must be established by the installer. The position selected must not interferewith existing aircraft systems.



Figure 4: Typical Clear Bay Areas of Fwd Pressure Bulkhead (looking aft)

Pressure Bulkhead Connector Installation in Bay 11, 12, 13, or 14:

010 Drill a 1.34” hole into the pressure bulkhead in bay 11, 12, 13, or 14 specified in Figure 4or any other bay if a doubler already exists.

020 Install the Raychem™ fitting with the tapered end located in the cabin side of the pressurebulkhead. Then secure the fitting from the avionics bay side using the “B” nut provided,being careful not to dislodge, damage, or misplace the o-ring installed in the “B” nutgland.

Pressure Bulkhead Connector Installation in Any Bay Except 11, 12, 13, or 14 and doublerdoes not already exists:

010 Using the doubler as a guide, mark and drill 12 #21 holes through a clear bay on theforward pressure bulkhead.

020 Deburr all the holes in the forward pressure bulkhead and then reinstall doubler.

030 Using a Cherrymax Grip Gauge, measure the holes for the proper rivet grip length.

040 Install the CR3213-5-X Cherrymax rivets or equivalent (supplied by installer).

050 Install the Raychem™ pressure bulkhead fitting with the tapered end located in the cabinside of the pressure bulkhead. Then secure the fitting from the avionics bay side usingthe “B” nut provided, being careful not to dislodge, damage, or misplace the o-ringinstalled in the “B” nut gland.



2.4.3. TREND SWITCHES AND DOWNLOAD PORT FOR ADAS

TRENDENG 1

TRENDENG 2

ECTMPORT

Figure 5: Single Cockpit Display (Center Console Mount Assembly)

Figure 6: Dual Cockpit Display (Discrete Component Mount)



2.4.4. TREND SWITCHES AND DOWNLOAD PORT FOR ADAS+ UPGRADE

TREND

Figure 7: Single Cockpit Display (Center Console Mount Assembly)

Figure 8: Cockpit Display (Discrete Component Mount)




Configurations:

The twin engine ADAS/ADAS+ Upgrade TREND switch/fault lamp(s), download port, and connector areavailable in a pre-wired center-console mount assembly (P/N TWIN-A-064-1 for ADAS and P/N TWIN-A-064-2for ADAS+ Upgrade), or as a discrete component kit (P/N TWIN-K-045-1 for ADAS and P/N TWIN-K-045-2 forADAS+ Upgrade). These are referred to as a single and dual cockpit display, respectively.

The TREND switch/fault lamp assemblies consist of either one or two .80” x .80” square push-to-test lampsdepending on the system installed. The serial download port may be mounted away from the instrument panel,since it is not accessed in flight.

Mounting:

The ADAS/ADAS+ Upgrade single cockpit display assembly fastens to a standard center console opening withDzus™ fasteners.

To mount a dual cockpit display, perform the following steps:

010 Refer to Figure 5. Locate a suitable position for mounting the TREND switch/faultlamp(s). Mark and punch either one or two .75” square holes for mounting of the systemtrend lamps depending on the system installed. Caution should be taken when creatingthe holes to insure that the spacing between them will allow clearance for the installationof the two lamps.

020 Mark and drill out a 19/32” hole for the data download port.

030 Install the Trend Lamp(s) and Data Download Port into the instrument panel, usingLoctite® Blue on the threads of the Download Port.

2.4.5. TORQUE TRANSDUCERS

Note:Some models of aircraft use existing transducers and do not require the P&W Engine Services torquetransducers. Refer to the Aircraft Connection Table for your aircraft and configuration. When installing thesystem in aircraft models that do not require the P&W Engine Services torque transducers, skip the followingtransducer mounting instructions, and proceed to the OAT section.


Care should be taken to keep the pressure transducers forward of the engine hot section.

Note:Figure 9 and the description immediately below apply to the standard P&W Engine Services supplied torquetransducers. An optional P&W Engine Services High Precision torque transducer may have been supplied as analternate part with your kit. If so, see the High Precision Torque Transducer section further below for installationinstructions.


The twin engine ADAS/ADAS+ Upgrade obtain the engine torque level by using 0 - 5 volt transducers installed inthe high and low pressure lines, reference 7 or 8 (high precision transducers), as appropriate. Perform eachprocedure listed for each engine and check off the appropriate box.



P&W Engine Services Standard Torque Transducers (Kit TWIN-K-031-1, -2):

Figure 9: Standard P&W Engine Services Torque Transducer Installation

Engines1 2

010 Using Teflon® tape, install and torque each high and low pressure 0 - 150 PSIG

transducer (750-00003) into a swivel elbow adapter (960-00010).

020 Remove the aircraft torque high-pressure line from the manifold on the left side of theengine, leaving the existing elbow fitting.

030 Install the swivel end of the supplied “T” fitting (960-00003) onto the existing manifoldelbow fitting.

040 Install the aircraft torque high-pressure line on the opposite end of the “T” adapter.

050 Install the transducer/elbow assembly to the branch line of the “T” adapter. Orient thetransducer beneath and along the existing pressure line so these can be clampedtogether in the next step.

060 Using supplied clamp (MS21919WCJ12), clamp (MS21919WCJ16), screw (900-00014),washer (920-00005), spacer (940-00004), and lock nut (910-00017) secure transducer tothe existing pressure line.

070 Remove the aircraft torque low-pressure line from the manifold on the left side of theengine, leaving the existing elbow fitting.


090 Install the aircraft torque low-pressure line on the opposite end of the “T” adapter.


110 Using supplied clamp (MS21919WCJ12), clamp (MS21919WCJ16), screw (900-00014),washer (920-00005), spacer (940-00004), and lock nut (910-00017) secure transducer tothe existing pressure line.

120 Secure all lines and pressure transducers.



P&W Engine Services High Precision Torque Transducers (Kit TWIN-K-031-3, -4):

Figure 10: P&W Engine Services High Precision Torque Transducer Installation

Engines1 2

010 Install and torque each High Precision high and low pressure 0 - 100 PSIG transducer

(750-00005) into an “O” ring flare adapter (960-00015).

020 Install each transducer assembly onto a double swivel elbow (960-00014).

030 Remove the aircraft torque high-pressure line from the manifold on the left side of theengine, leaving the existing elbow fitting.


050 Install the aircraft torque high-pressure line on the opposite end of the “T” adapter.


070 Using supplied clamp (MS21919WCJ12), clamp (MS21919WCJ14 or MS21919WCH14),screw (900-00014), washer (920-00005), spacer (940-00004), and lock nut (910-00017)secure transducer to the existing pressure line.

080 Remove the aircraft torque low-pressure line from the manifold on the left side of theengine, leaving the existing elbow fitting.


100 Install the aircraft torque low-pressure line on the opposite end of the “T” adapter.


120 Using supplied clamp (MS21919WCJ12), clamp (MS21919WCJ14 or MS21919WCH14),screw (900-00014), washer (920-00005), spacer (940-00004), and lock nut (910-00017)secure transducer to the existing pressure line.

130 Secure all lines and pressure transducers.



2.4.6. AIRCRAFT OUTSIDE AIR TEMPERATURE PROBE

The OAT probe is installed differently for 1900 series aircraft than it is for the other listed aircraft models. 1900series aircraft require a honeycomb panel mounting procedure, while the other models mount through an area ofsheet metal skin. Refer to the appropriate instructions for your model below.

For All Listed Aircraft Models Except 1900, 1900C, and 1900D:

Figure 11: OAT Probe Mounting (Non-1900 Series Aircraft)


The OAT harness should be routed through the nose wheel housing into the avionics bay andspliced inside the avionics bay.

Care must be taken to clamp the OAT harness inside the nose wheel housing to preventchafing.

It is recommended that spiral wrap be use on the harness as added protection.




The twin engine Aircraft Data Acquisition Systems picks up its indication of outside air temperature using atemperature probe located on the underside of the aircraft near the nose gear housing. The temperature probeis mounted in the fairing and routed to the avionics bay through the nose wheel housing.

010 Gain access to the underside of the aircraft.

020 Refer to Figure 12. Locate a position for the OAT probe between aircraft stations 47 and79 on the starboard side. See the aircraft manufacturer's maintenance manual stationdiagram for your specific aircraft model. The position selected should be clear ofobstructions. Because of possible aircraft alternate equipment or modification in thisarea, the specific mounting location must be established by the installer. The positionselected must not interfere with existing aircraft systems.

030 Mark and drill the five # 40 holes through the aircraft skin using doubler DPU-D-047-1 asa template and increase the diameter of the holes using a # 20 / 21 drill bit.

040 Mark and drill a .5” dia. hole through the aircraft skin using doubler DPU-D-047-1 as atemplate.

050 Deburr all the holes in the aircraft skin and the doubler.

060 Coat all exposed surfaces of the doubler and the aircraft skin with zinc chromate primer.

070 Reinstall the doubler on the inside surface of the aircraft skin.

080 Using a Cherrymax™ grip gauge, measure the # 20 / 21 holes for the proper rivet griplength.

090 Coat the end of four CR3213-5-X Cherrymax™ rivets with zinc chromate primer

100 With the zinc chromate primer still wet, install the CR3213-5-X Cherrymax™ rivets. Fourrivets are to be installed 90 degrees apart from each other inserted from the outside ofthe aircraft.

110 Insert the temperature probe into the hole, from the inside of the aircraft, and installwashers (920-00009), “O” ring (990-00027) and jam nut (TWIN-D-061-1).

120 Install bolt (AN3-5A), washer (920-00005), and nut (910-00008) in the fifth hole drilledthrough the skin and doubler).

130 Tighten and safety wire the jam nut to the bolt (AN3-5A).



For 1900, 1900C and 1900D Models Only

Figure 12: OAT Probe Mounting (1900, 1900C, 1900D Series Aircraft, only)

010 Gain access to the underside of the aircraft. Refer to 10.

020 Drill a .50-inch hole in the proper location for the OAT Probe.

030 Remove the adjacent core material to a diameter of 1 inch. Make sure that the panelskins are not damaged.

040 Clean out all loose material.

050 Measure and mark a location for installing a safety bolt 1.5” away from the .50-inch hole.

060 Drill a #10 diameter hole at the marked location.

070 Remove core material in this location to a diameter of .4 - inches. Make sure the panelskins are not damaged.

080 Clean out all loose material.

090 Using Dexter / Hysol’s EA934NA epoxy paste adhesive, or equivalent, completely fill eachsection of panel where the honeycomb (core) was removed.

a. The requirements for a suitable equivalent paste adhesive are:

A pot life long enough to perform the assembly.

Sag resistance (thixotropic).

A room temperature cure.

An adhesive appropriate for aircraft structural metal bonding with mechanical properties equalto or greater than EA 934NA.



100 Allow the adhesive to cure.

110 Re-drill the .50-inch diameter hole.

120 Re-drill the #10 diameter hole.

130 Using Zinc Chromate Primer, coat all exposed surfaces of the aircraft skin and adhesive.

140 Refer to 10. From inside the aircraft, insert the temperature probe (TWIN-A-050-1 forADAS and TWIN-A-050-2 for ADAS+ Upgrade) with a washer (920-00009) through the.5” diameter hole.

150 Install a washer (920-00009), “O” ring (990-00027) and jam nut (TWIN-D-061-1) onto theprobe on the outside of the aircraft.

160 Install the safety bolt (AN3-5A), washer (920-00005), and nut (910-00008) in the # 10hole drilled in the skin.

170 Tighten the OAT nut and safety-wire the OAT nut to the safety bolt.



2.4.7. PITOT & STATIC PRESSURE TRANSDUCERS

Figure 13: Pitot / Static Transducer Mounting



Use Teflon® tape on all pipe threads.

For mounting areas where space is limited, P/N TWIN–D-014-1 is not required. A standoff(9230A232) is used with a bolt (900-00013) to secure the transducers.


The following steps refer to Figure 13:

010 Apply Teflon® tape to the male ¼” transducer threads (750-00001 and 750-00002) andpre-assemble pipe fittings and Tygon tube and brass hose insert (B-405-2) illustrated inFigure 13, above. The pitot and static port pressure hoses will be attached later whenthey are made up to length.



020 Attach the transducers to the transducer mounting bracket (TWIN-D-014-1).

030 Locate a position for the transducer assembly in the avionics compartment.

040 Using the transducer mounting bracket as a guide, mark and drill three #6 screw holesinto the aircraft angle support brackets.

050 Mount the transducer assembly in the avionics compartment using three screws (900-00012), three washers (920-00013), and three lock nuts (910-00016).

All Listed Aircraft Models Except 1900D:

Refer to Figure 14, below

060 Install “T” fittings (960-00037) onto the bulkhead pitot and static pressure ports. Theseports are located in the upper section of the avionics compartment on the co-pilot’s side.

070 Install pipe nipple fittings (960-00036) into the forward ends, and flare nipple fittings (960-00030) into the side branches of the “T” fittings.

1900D Model, Only:

Refer to Figure 15 below.

061 Install swivel “T” fittings onto the bulkhead pressure ports located in the avionicscompartment on the co-pilot’s side. The static “T” (960-00032) is larger than the pitot “T”(960-00003).

071 Install reducer (960-00031) onto the side branch of the static “T” fitting.

All Listed Aircraft Models, Including 1900D:

080 Install the original pitot and static inlet hoses onto the “T” fitting forward (run) ends.

090 Using hose (990-00028), and fittings (960-00027), fabricate pressure hoses. Connect thehoses between the ADAS AND ADAS+ pitot and static pressure transducers and the sidebranches of the respective “T” fittings.

100 Tighten and secure all hoses and fittings.



All Models Except 1900D:

Figure 14: Pitot / Static Bulkhead Pressure Connections (Non-1900D)



1900D Model Only:

Figure 15: Pitot / Static Bulkhead Pressure Connections (1900D)



2.4.8. AIRCRAFT VERTICAL ACCELEROMETER

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

Figure 16: Accelerometer Mount and Orientation (Viewed From Above)



The twin engine ADAS/ADAS+ Upgrade records vertical accelerations for hard landing and in-flight loads using a+/- 5g accelerometer mounted aft of the wing spar on the DC generator control panel. To mount theaccelerometer, perform the following steps:

010 Gain access to the wing main spar in the center of the fuselage.

020 Following Figure 16, find a convenient location and mount the accelerometer with thesupplied screws (900-00011) and lock nuts (910-00016).

030 Ensure that the vertical accelerometer is mounted so that the label with the Crossbowlegend and Model # is facing up and the label with the Serial # is facing towards theground. No other orientation is necessary.



2.5. Electrical Installation Instructions



Each wire is marked with a shrink-on label near the terminal end to indicate what it is. Whenyou shorten the wire behind the label, be sure to re-label it.

The twin engine Aircraft Data Acquisition Systems cables have shields that connect to the twinengine Aircraft Data Acquisition System chassis ground. When terminating the shieldedharness at the airframe connection, these shields must be trimmed back and insulated toprevent possible shorting with the signal wires.

Wiring Splices:

The use of Raychem™ hermetic style wire splices is recommended. When making connectionsbetween two shielded cables, the shields should also be maintained using Raychem™ or equivalent shieldsplices. The entire cable splice should be encased in heat shrink tubing when completed.

An example of shield and wire connection splices can be found in Figure 17 and Figure 18.

RAYCHEM D-436-37OR EQUIVALENT

Figure 17: Single or Dual Wire Splice

1. INSERT PREPARED CABLE

2. APPLY HEAT

RAYCHEMS01042OR EQUIVALENT

3. SPLICE WIRE ANDSHIELD PIGTAIL

Figure 18: Shield Connection (outer heat shrink tubing not shown)



2.5.1. J1 HARNESS (POWER / SENSOR)

ADAS Processor Only (For All Listed Aircraft Models):


Perform a continuity check on all wires before final connection.

Route all harnesses along existing harnesses wherever possible.

Each harness wire is marked with a shrink-on label near the terminal end to indicate what it is. Ifyou shorten the wire behind the label, be sure to re-label it.


010 Connect the harness to the J1 connector of the twin engine Aircraft Data AcquisitionSystem processor.

020 Split the harness and route the pitot / static cable to the transducer assembly in theavionics compartment.

030 Route the Outside Air Temperature cable to the OAT probe.

040 Route the flap digital cable to the cockpit connection location indicated in the appropriateAircraft Connection Table.

050 Route the gear extension digital cable to the cockpit connection location indicated in theappropriate Aircraft Connection Table.

060 Route the Weight On Wheels digital cable to the cockpit connection location indicated inthe appropriate Aircraft Connection Table.

070 Route the power and ground wires into the cockpit to the aircraft breaker panel as follows:

For 1900D models only: route to the primary bus located in the floor compartment aft ofthe center console (beneath panel 133ATC).

For all other models: route to the copilot's circuit breaker panel (located at zone 246).

080 Route the two conductor cable to the ice vane control panel location as indicated in theappropriate Aircraft Connection Table.

ADAS+ Upgrade Processor Only (For All Listed Aircraft Models):

010 Connect the harness to the J1 connector of the twin engine Aircraft Data AcquisitionSystem processor.

020 Split the harness and route the pitot / static cable to the transducer assembly in theavionics compartment.

030 Route the Outside Air Temperature cable to the OAT probe.

040 Route the flap digital cable to the cockpit connection location indicated in the appropriateAircraft Connection Table.



050 Route the gear extension digital cable to the cockpit connection location indicated in theappropriate Aircraft Connection Table.

060 Route the Weight On Wheels digital cable to the cockpit connection location indicated inthe appropriate Aircraft Connection Table.

070 Route the power and ground wires into the cockpit to the aircraft breaker panel as follows:

For 1900D models only: route to the primary bus located in the floor compartment aft ofthe center console (beneath panel 133ATC).

For all other models: route to the copilot's circuit breaker panel (located at zone 246).

2.5.2. J2 HARNESS (ENGINE 1)




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



010 Connect the harness to the J2 connector on the twin engine Aircraft Data AcquisitionSystem processor and route into the cockpit.

020 Split the harness and route the N1, N2, ITT and Fuel Flow cables behind the gauges inthe instrument panel. Refer to the Wiring Diagrams and the Aircraft Connection Tablesfor the proper wiring connection locations.

030 Route the accelerometer cable down fuselage to the accelerometer.

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009. Ifthe kit was purchased after March 1, 2009 and does not come with a VerticalAccelerometer, then cap and stow the wire as it will not be needed.

040 Route the P&W Engine Services torque transducer torque signal cable down fuselage tothe appropriate side wing root.

Note: Some aircraft models do not require P&W Engine Services Torque Transducers.For these installations, the torque signal cables should be routed to the aircraft’s existingtorque sensor connection locations listed in the Aircraft Connection Tables for youraircraft. In this case, skip Instructions (050) through (070) and continue with (080).

050 Trim the torque cable to length and splice it to five existing aircraft wing root spare pass-through wires, using the fifth wire for the cable shield.

060 Outside of the aircraft, splice the five aircraft pass-through wires to the remaining lengthof torque cable and route the cable along the wing spar to the engine nacelle.

070 Refer to Figure 19. Determine whether the existing aircraft engine bulkhead/firewallmounted connectors have enough spare pins to connect the torque signal cable. If theydo, utilize the existing connector to route the cable to the engine torque transducers. Ifnot, install the supplied MS3450KT16S-8S and MS3450KT16S-8P bulkhead connectors,



together with the M85049/41-10A backshells to route the wires to the torque transducers.Mount the connectors near the existing connector, but not so close as to interfere with it.

080 Route the “Bleed Eng 1” cable to the bleed hookup location as listed in the AircraftConnection Table.


Figure 19: Firewall With Additional ADAS/ADAS+ Upgrade Connector



2.5.3. J3 HARNESS (ENGINE 2)

ADAS Processor Only (For All Listed Aircraft Models):



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



010 Connect the harness to the J3 connector on the twin engine Aircraft Data AcquisitionSystem processor and route it into the cockpit.


030 Route the P&W Engine Services torque transducer signal cable down fuselage to theappropriate side wing root.




060 Refer to Figure 19. Determine whether the existing aircraft engine bulkhead/firewallmounted connectors have enough spare pins to connect the torque signal cable. If theydo, utilize the existing connector to route the cable to the engine torque transducers. Ifnot, install the supplied MS3450KT16S-8S and MS3450KT16S-8P bulkhead connectors,together with the M85049/41-10A backshells to route the wires to the torque transducers.Mount the connectors near the existing connector, but not so close as to interfere with it.




ADAS+ Upgrade Processor Only (For All Listed Aircraft Models):

010 Connect the harness to the J3 connector on the twin engine Aircraft Data AcquisitionSystem processor and route it into the cockpit.


030 Route the P&W Engine Services torque transducer signal cable down fuselage to theappropriate side wing root.




060 Refer to Figure 19. Determine whether the existing aircraft engine bulkhead/firewallmounted connectors have enough spare pins to connect the torque signal cable. If theydo, utilize the existing connector to route the cable to the engine torque transducers. Ifnot, install the supplied MS3450KT16S-8S and MS3450KT16S-8P bulkhead connectors,together with the M85049/41-10A backshells to route the wires to the torque transducers.Mount the connectors near the existing connector, but not so close as to interfere with it.


080 Route the two conductor cable to the ice vane control panel location as indicated in theappropriate Aircraft Connection Table.



2.5.4. COMM HARNESS (TREND SWITCH / DOWNLOAD PORT)




Route all harnesses along existing harnesses wherever possible.



The twin engine Aircraft Data Acquisition System TREND switches and download port may be mounted on eithera center console assembly (P/N TWIN-A-064-1 for the ADAS and P/N TWIN-A-064-2 for the ADAS+ Upgrade),or individually.

ADAS Only For Single Cockpit Display Option (Center Console Assembly):

010 Connect the COMM harness to the twin engine Aircraft Data Acquisition Systemprocessor and route it into the cockpit through the bulkhead fitting in the pressurebulkhead to the center console.

020 Trim back and crimp wires to the contacts (748610-4) of the 15 pin high-densityconnector (748565-1). Feed wires through backshell (400-00038) and insert intoconnector, connecting to the pins per section 7.3.1

030 Connect the harness to the console assembly.

040 Secure the wire harness to console assembly using slide latch (DE51224-1).

050 Install the panel assembly into the center console, secure by fastening four Dzus™fasteners.

ADAS Only For Dual Cockpit Display Option (Discrete Component Mount):

010 Connect the COMM harness to the twin engine Aircraft Data Acquisition Systemprocessor. Route the harness into the cockpit through the fitting in the pressure bulkheadto the desired location for the TREND switches and download port. Cut to length.

020 Install the two 6 Pin Female TREND switch circuit connectors (400-00026) onto theCOMM harness, connecting it per the pin out list in section 7.3.2

030 Connect the harness to the TREND switch assembly (TWIN-C-015-1).

040 Connect the single 6 Pin Male connector (400-00027) to the COMM harness, wiring asindicated in the pin out list in section 7.3.2

050 Connect the harness to the download port assembly (DPU-A-044-1)

060 Secure all wiring.



ADAS+ Upgrade Only For Single Cockpit Display Option (Center Console Assembly):

010 Connect the COMM harness to the twin engine ADAS+ Upgrade processor and route itinto the cockpit through the bulkhead fitting in the pressure bulkhead to the centerconsole.

020 Trim back and crimp wires to the contacts of the 15 pin high-density connector(M24308/2-11F). Feed wires through backshell (400-00038) and insert into connector,connecting to the pins per section 7.4.1

030 Connect the harness to the console assembly.

040 Secure the wire harness to console assembly using the screw lock post (900-00052).

050 Install the panel assembly into the center console, secure by fastening four Dzus™fasteners.

ADAS+ Upgrade Only For Cockpit Display Option (Discrete Component Mount):

010 Connect the COMM harness to the twin engine ADAS+ Upgrade processor. Route theharness into the cockpit through the fitting in the pressure bulkhead to the desiredlocation for the TREND switches and download port. Cut to length.

020 Install the 6 Pin Female TREND switch circuit connector (400-00026) onto the COMMharness, connecting it per the pin out list in section 7.3.2

030 Connect the harness to the TREND switch assembly (TWIN-C-015-1).

040 Connect the single 6 Pin Male connector (400-00027) to the COMM harness, wiring asindicated in the pin out list in section 7.3.2

050 Connect the harness to the download port assembly (DPU-A-044-1)



2.5.5. ENGINE 1 & 2 PRE-EXISTING TORQUE SENSOR

A/C NOT Requiring P&W Engine Services Transducers


Engines1 2

010 Perform the following steps for each engine. Trim the engine torque cables to length.Splice and terminate at the P119 and P120 connectors using the pin configuration listedin the appropriate Aircraft Connection Table. Note that there are four wires in each cable,but only two connections per engine. Insulate and tie back the unused wires (WHT andWHT/BLU).

Color P119 WHT/ORG (Engine 1 Torque +) WHT/GRN (Engine 1 Torque -)

Color P120 WHT/ORG (Engine 2 Torque +) WHT/GRN (Engine 2 Torque -)

2.5.6. ENGINE 1 & 2 P&W ENGINE SERVICES SUPPLIED TORQUE SENSOR

A/C Requiring P&W Engine Services Transducers:


If necessary, install firewall connectors in an appropriate location using connectors(MS3450KT16S-8S, MS3456KT16S-8P), backshell (M85049/41-10A), and cable (MS27500-20RC4S06) See Sections 2.5.2 and 2.5.3.



Engines1 2

010 Trim the engine torque cable to length. Splice to the engine transducer harness using thefollowing pin configuration:

Color Transducer WiresWHT/ORG GRN (High Pressure)WHT/BLU BLK (High and Low Pressure)WHT RED (High and Low Pressure)WHT/GRN GRN (Low Pressure)




2.5.7. ENGINE N1 SPEED SIGNALS




Engines1 2

010 Trim the engine N1 sensor cable to length. Splice and terminate at the connector usingthe pin configuration listed in Aircraft Connection Table for your model A/C.


2.5.8. ENGINE N2 SPEED SIGNALS




Engines1 2

010 Trim the engine N2 sensor cable to length. Splice and terminate at the connector usingthe pin configuration listed in Aircraft Connection Table for your model A/C.




2.5.9. VOLTAGE TO FREQUENCY CONVERTER

Only 200 & 200T with Beech fuel flow Configurations 1 & 2, and200CT, A200, A200C, A200CT, B200 B200C, B200CT, B200T with Beech fuel flowConfiguration 1


Refer to the appropriate wiring diagram and Aircraft Connection List. The Fuel Flow Voltage to FrequencyConverter harness consists of a nine-pin connector and five multi-conductor cables. The converter’s outputleads will be connected to the ADAS AND ADAS+ processor’s fuel flow signal input leads, which are part of theJ2 and J3 harnesses. The converter’s power leads will be spliced into the Processor’s J1 harness bus powerand ground connections. To reduce the length of cable runs, make all connections close to the processor,where practical.

010 Trim the converter’s “FUEL FLOW ENG 1 PROC” cable to length.

020 Trim the J2 harness “FUEL FLOW ENG1 INPUT” cable to length.

030 Splice the two cables together, maintaining the wire color code when making theindividual connections.

Processor Cable Converter Cable WHT WHT WHT/BLU WHT/BLU

010 Trim the converter’s “FUEL FLOW ENG 2 PROC” cable to length.

020 Trim the J3 harness “FUEL FLOW ENG 2 INPUT” cable to length.

030 Splice the two cables together, maintaining the wire color code when making theindividual connections.

Processor Cable Converter Cable WHT WHT WHT/BLU WHT/BLU

010 Trim the converter’s “CONV PWR” cable to length.

020 Cut the J1 “PROC PWR” cable where the converter’s power cable will be spliced in, nearthe processor. Label the processor side “PROC PWR, and the bus side “BUS PWR”.

030 Splice the converter cable to both the processor and bus power cables, maintaining thewire color code when making the individual connections.

Processor Cable Converter Cable Bus Power Cable WHT WHT WHT WHT/BLU WHT/BLU WHT/BLU

040 Secure all wiring. Proceed to Section 2.5.10, to connect the remaining converter cablesto the fuel flow sender signal.



2.5.10. ENGINE FUEL FLOW SIGNALS



The engine fuel flow connection will either be made from the J2 harness or the P&W Engine Services Voltage toFrequency Converter harness, depending on whether a converter was installed in the previous section. Performthe following steps:

For Aircraft With P&W Engine Services Voltage to Frequency Converters:

010 Trim the “FUEL FLOW SENSOR ENG 1” cable to length. Splice and terminate at theconnector using the pin configuration listed in Aircraft Connection Table for your modelA/C.

Harness LocationWHT Fuel flow gauge (see Aircraft Connection Table)WHT/BLU Wired direct to the fuel flow gauge.

020 Trim the “FUEL FLOW SENSOR ENG 2” cable to length. Splice and terminate at theconnector using the pin configuration listed in Aircraft Connection Table for your modelA/C.

Harness LocationWHT Fuel flow gauge (see Aircraft Connection Table)WHT/BLU Wired direct to the fuel flow gauge


For Aircraft Without P&W Engine Services Voltage to Frequency Converters:

010 Trim the “FUEL FLOW INPUT ENG 1” cable to length. Splice and terminate at theconnector using the pin configuration listed in Aircraft Connection Table for your modelA/C.

Harness LocationWHT Fuel flow gauge (see Aircraft Connection Table)WHT/BLU Wired direct to the fuel flow gauge.

020 Trim the “FUEL FLOW INPUT ENG 2” cable to length. Splice and terminate at theconnector using the pin configuration listed in Aircraft Connection Table for your modelA/C.

Harness LocationWHT Fuel flow gauge (see Aircraft Connection Table)WHT/BLU Wired direct to the fuel flow gauge




2.5.11. ENGINE ITT SIGNALS

For All Listed Aircraft Models:Wiring Instructions:


Engines1 2

010 Trim the engine ITT cable to length.

020 If the existing thermocouple wires connect to the gauge with wire lugs, attach the “CR” lugto the yellow wire and the “AL” lug to the red wire, and connect to the gauge.

030 If the existing thermocouple wires connect to the gauge with a connector, splice into thewires using the pin configuration listed in Aircraft Connection Table for your model A/C.


2.5.12. ENGINE BLEED SIGNALS

For All Listed Aircraft Models:Wiring Instructions:


Engines1 2

010 Trim the Engine 1 and 2 bleed cables to length. Splice and terminate at the connectorsusing the pin configuration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT Bleed Air Signal, Engine 1 (see Aircraft Connection Table)WHT/BLU Bleed Air Signal, Engine 2 (see Aircraft Connection Table)


2.5.13. ICE VANE SIGNALS

For ADAS Only For All Listed Aircraft Models:


Engines1 2

010 Trim the Ice Vane cable to length. Splice and terminate at the connector using the pinconfiguration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT Ice Vane Signal, Engine 1 (see Aircraft Connection Table)WHT/BLU Ice Vane Signal, Engine 2 (see Aircraft Connection Table)




For ADAS+ Upgrade For All Listed Aircraft Models:


Engines1 2

010 Trim the Ice Vane cable to length. Splice and terminate at the connector using the pinconfiguration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT Ice Vane Signal, Engine 1 (see Aircraft Connection Table)WHT/BLU Ice Vane Signal, Engine 2 (see Aircraft Connection Table)


2.5.14. FLAP POSITION SIGNALS



010 Trim the Flap Position cable to length. Splice and terminate at the connector using thepin configuration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT Flaps – Approach (see Aircraft Connection Table)WHT/BLU Flaps – Full Down (see Aircraft Connection Table)


2.5.15. WEIGHT ON WHEELS SIGNAL



010 Trim the Weight on Wheels cable to length. Splice and terminate at the connector usingthe pin configuration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT Weight on Wheels (see Aircraft Connection Table)


2.5.16. GEAR EXTENDED SIGNAL

For ADAS Only For All Listed Aircraft Models:


010 Trim the Gear Extended cable to length. Splice and terminate at the connector using thepin configuration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT Gear Extended (see Aircraft Connection Table)




For ADAS+ Upgrade Only For All Listed Aircraft Models:


010 Trim the Gear Extended cable to length. Splice and terminate at the connector using thepin configuration listed in Aircraft Connection Table for your model A/C:

Harness LocationWHT/BLU Gear Extended (see Aircraft Connection Table)


2.5.17. PITOT AND STATIC PRESSURE SENSORS



010 Trim the Pitot/Static cable to length. Splice to the transducer harnesses. Refer to thewiring diagram and connect as follows:

Harness LocationWHT/ORG GRN Wire (Pitot Pressure Transducer)WHT RED Wire (Both Transducers)WHT/BLU BLK Wire (Both Transducers)WHT/GRN GRN Wire (Static Pressure Transducer)


2.5.18. OUTSIDE AIR TEMPERATURE SENSOR FOR ADAS



010 Trim the OAT cable to length. Splice with OAT Alumel / Chromel transducer wires. Referto the wiring diagram and connect as follows:

Harness LocationRED RED AlumelYEL YEL Chromel




2.5.19. OUTSIDE AIR TEMPERATURE SENSOR FOR ADAS+



010 Trim the OAT cable to length. Splice the harness wires with the transducer wires. Referto the wiring diagram and connect as follows:

Harness LocationWHT/ORG REDWHT REDWHT/BLU WHTWHT/GRN WHT


2.5.20. AIRCRAFT ACCELEROMETER


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.


010 Trim the Vertical Accelerometer cable to length. It will be wired to a supplied ConXall™connector (400-00026). This connector mates with the pre-wired transducer cableconnector. Refer to the wiring diagram and connect as follows:

Harness LocationWHT/BLU Pin 1 on mating ConXall™ connectorWHT/ORG Pin 2 on mating ConXall™ connectorWHT Pin 3 on mating ConXall™ connectorGround (Shield) Pin 6 on mating ConXall™ connector

020 Plug the two connectors together. Secure all wiring.



2.5.21. POWER AND GROUND CONNECTIONS FOR ADAS

For All Listed Aircraft Models Except 1900D:


The power connection points must be chosen to provide power to the ADAS through an entireengine’s running cycle.


010 Refer to the appropriate wiring diagram. Trim the processor power cable to length.Splice a supplied fuse into the PROC 1 and PROC 2 lines and connect to the respectiveengine primary bus power sources on the copilot’s circuit breaker panel located in theaircraft zone 246. Connect as follows:

Harness LocationWHT Aircraft Engine 1 Primary Bus Power (PROC 1)WHT/ORG Aircraft Engine 2 Primary Bus Power (PROC 2)WHT/BLU Aircraft Ground (GND)


For the 1900D Aircraft Model, Only:


The power connection points must be chosen to provide power to the ADAS through an entireengine’s running cycle.


010 Refer to the appropriate wiring diagram. Trim the processor power cable to length. Installthe supplied 1 amp circuit breakers in locations 60 and 61 of the primary bus, located inthe floor compartment aft of the center console. Connect the circuit breakers to therespective engine primary bus power sources. Connect as follows:

Harness LocationWHT Aircraft Engine 1 Primary Bus Power CB-61 (PROC 1)WHT/ORG Aircraft Engine 2 Primary Bus Power CB-60 (PROC 2)WHT/BLU Aircraft Ground (GND)




2.5.22. POWER AND GROUND CONNECTIONS FOR ADAS+ UPGRADE

For All Listed Aircraft Models Except 1900D:


The power connection points must be chosen to provide power to the ADAS+ Upgrade throughan entire engine’s running cycle.


010 Refer to the appropriate wiring diagram. Trim the processor power cable to length. Installthe supplied fuse into the BAT PWR IN and connect to the 28 VDC PWR source. Referto the appropriate connection chart in section 5. Splice a supplied fuse into the BUSPWR IN line and connect to the respective engine bus power source on the co-pilot’scircuit breaker panel located in aircraft zone 246. Connect as follows:

Harness LocationWHT Bus Power InWHT/ORG Battery Power InWHT/BLU Aircraft Ground


For the 1900D Aircraft Model, Only:


The power connection points must be chosen to provide power to the ADAS+ Upgrade throughan entire engine’s running cycle.


010 Refer to the appropriate wiring diagram. Trim the processor power cable to length.Splice a supplied fuse into the BAT PWR IN and connect to the 28 VDC PWR source.Refer to the appropriate connection chart in section 5. Install the 1amp circuit breaker inlocation 61 of the primary bus, located in the floor compartment aft of the center console.Connect the circuit breaker to the engine primary bus power source. Connect as follows:

Harness LocationWHT Bus Power InWHT/ORG Battery Power InWHT/BLU Aircraft Ground




2.6. Final Wiring Instructions:

For All Listed Engine Models:

Instructions:

010 Secure all wires making sure engine/aircraft control movements will not be affected by thewiring. Make sure wiring will not come in contact with hot sections of the engine. Makesure that wire harnesses will not be come in contact with sharp corners in the aircraft.

Note: final potting and heat shrinking of the Raychem™ pressure bulkhead fittinginstalled earlier (Section 2.4.2) will not be performed until after ground test is completed.

2.7. Initial Processor Test

For ADAS Only For All Aircraft Models:

Initial Test Instructions:

The TREND lamps may be used to monitor the system’s progress when first powered up. Two basictests can be performed. The second test requires a system Communication cable (TREND-C-033-1).The first test should be performed without the cable.

010 TEST 1: With the master battery switch off, turn the master battery switch on and verifythat the ADAS TREND lamps illuminate, indicating system boot-up. After approximately 2seconds, the lamps will extinguish for about 2 seconds and then either:

- Remains extinguished (NORMAL state)

- Flash (WARNING state)

- Remains on (ERROR state)

Note: if the lamps do not extinguish for about 2 seconds before indicating one of theabove states (including ERROR state) the system test for that processor has failed. It isimportant that the lamps both go out temporarily before entering a status display. (SeeSection 8.2.1 for detailed initialization description.)

Also note that the actual state displayed may vary and does not necessarily indicate aproblem. It is important at this stage only that the initialization sequence proceeds tocompletion properly. The states will have significance mainly after the sensors havebeen calibrated in the next section.

Did the lamps successfully complete the initialization sequence listed, (yes/no):

State indicated: Any Discrepancy?

Notes:

020 TEST 2: Plug the system Communication cable into the Communication Port and placethe “Run/Conf” switch in the cable to the “Conf” position. The lamps should indicate thesame state that they did earlier. If the lamps is ON or flashing press the button once toextinguish it.

030 With the lamps extinguished, press each TREND switch once. The lamp should flash forapproximately 5 seconds indicating a successful Loopback test.



040 Place the “Run/Conf” switch to the “Run” position. Both lamps should extinguish forapproximately 2 seconds and then return to the mode recorded in step 010. If theprocessor does not function exactly as described in the above steps, it has failed thepower-up test. Do not proceed to the Configuration and Calibration sections of themanual until the processor has been verified to be operational.

Notes:

For ADAS+ Upgrade Only For All Aircraft Models:

Initial Test Instructions:

The TREND lamp may be used to monitor the system’s progress when first powered up. Two basictests can be performed. The second test requires a system Communication cable (TREND-C-033-1).The first test should be performed without the cable.

010 TEST 1: With the master battery switch off, turn the master battery switch on and verifythat the ADAS+ Upgrade TREND lamp illuminates, indicating system boot-up. Afterapproximately 2 seconds, the lamp will extinguish for about 2 seconds and then either:

- Remain extinguished (NORMAL state)

- Flashing (CAUTION state if pressing the TREND switch does not stop the flashing)

- Flashing (MAINTENANCE state if pressing the TREND switch stops the flashing)

- Remains on (FAULT state)

Note: if the lamp does not extinguish for about 2 seconds before indicating one of theabove states (including ERROR state) the system test for that processor has failed. It isimportant that the lamp goes out temporarily before entering a status display. (SeeSection 8.2.1 for detailed initialization description.)

Also note that the actual state displayed may vary and does not necessarily indicate aproblem. It is important at this stage only that the initialization sequence proceeds tocompletion properly. The states will have significance mainly after the sensors havebeen calibrated in the next section.

Did the lamps successfully complete the initialization sequence listed, (yes/no):

State indicated: Any Discrepancy?

Notes:

020 TEST 2: Plug the system Communication cable into the Communication Port and placethe “Run/Conf” switch in the cable to the “Conf” position. The lamp should indicate thesame state that they did earlier. If the lamp is ON or flashing press the button once toextinguish it.

030 With the lamp extinguished, press the TREND switch once. The lamp should flash forapproximately 5 seconds indicating a successful Loopback test.

040 Place the “Run/Conf” switch to the “Run” position. The lamp should extinguish forapproximately 2 seconds and then return to the mode recorded in step 010. If theprocessor does not function exactly as described in the above steps, it has failed thepower-up test. Do not proceed to the Configuration and Calibration sections of themanual until the processor has been verified to be operational.

Notes:



3 SYSTEM CONFIGURATION AND CALIBRATION

The ADAS/ADAS+ Upgrade is a combination of hardware and software designed to have a wide range ofapplication. In order to correctly operate with the specific aircraft type it is installed in, the system must first beconfigured to expect the particular sensor and signal combinations available on that aircraft as well as theengine type and other necessary information.

When it has been properly configured, ADAS/ADAS+ Upgrade must then be calibrated to correctly compensatefor the precise range and level of the available sensor signals on that specific aircraft. This last function issimilar to the kind of calibration performed on aircraft instruments, and may use some of the same calibrationequipment. The system is also capable of being calibrated without such equipment, by utilizing the existingcockpit flight instruments as calibration standards. This option does however depend on the accuracy of thecockpit instruments (and their own calibration), and is more difficult to perform. It generally requires flying theaircraft to get a useful range of readings. Where conventional instrument test equipment is available, its use ispreferred for calibration.

Configuration and calibration are performed by the installer with the help of a computer and a softwarecommunication tool. Configuration and calibration require a laptop computer connected to the system via aCommunication cable and running P&W Engine Services’ Monitor Link Program (MLP). The MLP gives fieldpersonnel the ability to monitor the sensors in real time (Live Data Display) as well as to alter the configurationand calibration data stored by the system.

In addition to the MLP tool, P&W Engine Services offers an Internet based information management andanalysis system called TurbineTracker™. MLP and TurbineTracker™ make it possible to quickly transfer andmanage the aircraft’s configuration and calibration data, as well as operational data (log data) for fleetcomparison and analysis. The TurbineTracker™ website is located at www.turbinetracker.com. To obtain aTurbineTracker™ user account and password, contact P&W Engine Services Product Support.

Current software version manuals for both TurbineTracker™ and MLP are available through theTurbineTracker™ Website. The following sections and instructions for configuration and calibration of thesystem require familiarity with the MLP and TurbineTracker™ manuals and software. While this section of theInstallation Manual cannot replace the software manuals, a few of the special terms and concepts used in theconfiguration and calibration instructions are briefly defined on the following page. See the software manuals forfull descriptions and procedures for use of the applicable software product.



3.1. Definitions

Configuration File: An MLP data file that contains engine, sensor, and calibration information fora specific aircraft. This information is transmitted to the processor during configuration andcalibration.

Configuration Version: A number stored with a particular configuration file. The MLP andTurbineTracker™ both maintain version numbers of the current Configuration File in use. Thesemust match each other and correspond with the data stored by the system processor. When anew calibration is performed the version number is automatically incremented.

Live Data Display: An MLP mode of operation that presents periodically updated aircraft sensorreadings, as they occur. Live Data Display may be used in flight and on the ground whenadjusting the calibration or testing and troubleshooting the system.

Log Data: The stored operational aircraft exceedance, event, and sensor readings collected bythe processor. In normal aircraft use, the information gathering function of the system createsLog Data. This data is stored in relatively raw form (a Log File) and can be extracted and furtherprocessed into useful information through the MLP and TurbineTracker™.

One Point Offset Calibration (P2): A method that uses a single reading (or point) to correct(calibrate) a sensor signal. A One Point Offset Calibration is a less precise method of calibrationthan a Two Point Calibration. To increase the useful precision of the one point offset method, areading at the low end of a sensor’s signal range is preferred. For example, if a sensor reading issupposed to fall between 100 degrees and 800 degrees, a test reading at 150 degrees willcalibrate the system better than one at 500 degrees. See also One Point Slope Calibration.

One Point Slope Calibration (P1): A second method that uses a single reading (or point) tocorrect (calibrate) a sensor signal. A One Point Slope Calibration is a less precise method ofcalibration than a Two Point Calibration. To increase the useful precision of the one point slopemethod, a reading at the high end of a sensor’s signal range is preferred. For example, if asensor reading is supposed to fall between 0% and 100%, a test reading at 80% will calibrate thesystem better than one at 50%. If a reading at 0% has been attempted as a One Point SlopeCalibration, the system has not been usefully calibrated at all. See also One Point OffsetCalibration.

MLP (Monitor Link Program): P&W Engine Services’ communication program used for transfer ofoperational, configuration, and calibration data to and from the processor. It can also display liveoperational data.

MLU: (Monitor Link Unit): Another name for the system processor (not to be confused with MLP).As the function of processors becomes integrated with other aircraft systems and a variety ofcommunication methods, they may be thought of as data bridges, monitoring gathered signalsand linking this data to and from other systems.

Two Point Calibration (P1 & P2): The most accurate method of calibration, requiring both a lowand high value to correct (calibrate) a sensor signal. Readings far apart in value will producebetter results than those that are close together. For example, test readings of 0% and 80% willcalibrate the system better than readings at 20% and 40%. If two readings of 0% are entered as aTwo Point Calibration, the system has not been usefully calibrated at all, and may show spuriousresults.



3.2. Processor (MLU) Configuration

Configuration Notes:

These instructions require that the installer run the current version of the MLP on a laptop computer andthat the installer has created the required installation configuration file. The current version of the MLPand MLP manual are available from the TurbineTracker™ website.

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

When connecting the Communication Cable, be sure to properly align the cable plug’skey with the keyway in the Communication Port receptacle.

Processors1 2

010 Connect the Communication Cable provided to the ADAS/ADAS+ UpgradeCommunication Port. Connect the other end of the cable to the serial port on alaptop computer running the current version of the Monitor Link Program (MLP).

020 Place the Communication cable “Run/Conf” switch on the cable in the “Conf”position.

030 Establish connection to the processor using MLP. If unable to establishconnection, proceed with MLP troubleshooting procedures (See the MLP manual).

040 Select “Configure Unit” under the MLU Menu.

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

060 Select “Open”. (If you are prompted to retrieve the Log File, retrieve the log datafrom the processor first and then select “Open.”)

3.3. Pre-Calibration Sensor and Discrete Signal Test (Live Data Display)

After configuration and before calibrating the sensors, it is suggested that a Live Data Display check beperformed to make sure that all the sensors are operating. The Live Data Display will also be used hereto test the discrete (switched) aircraft signal channels. The discrete signals are are: Flaps, Engine Bleeds,Ice Vane / Particle Separator, Gear Extended, and Weight on Wheels.

These instructions require that the installer run the current version of the MLP on a laptop computer andthat the installer has created the required installation configuration file. The current version of the MLPand MLP manual are available from the TurbineTracker™ website

Although the data will be viewed in real time, the data is stored in a file for futurereference.

Live data updates once every second. This rate may appear as lag in the readings whencompared to aircraft instrumentation.


Testing the Gear Extended and Weight on Wheels discrete channels will require jackingthe aircraft

010 Connect the Communication Cable provided to the Communication Port. Connectthe other end of the cable to the serial port on a laptop computer running the currentversion of the Monitor Link Program (MLP).



020 Place the Communication cable Run/Configure switch in the “CONF” position.

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

040 Select “Live Data” then “Text View”. Follow the on-screen prompts and select“Save”.

050 When prompted by MLP, place the Run/Configure switch in the “Run” position andclick “OK.”

060 When the sensors are displayed on the screen and the system clock at the top isincrementing, check each sensor channel for proper operation. A faulted sensorchannel will display as “9999.9999.” Faulted sensor channels should beinvestigated using the Instructions for Continued Airworthiness manual. Actualsensor readings will vary, and the Airspeed, Altitude, ITT, OAT, Torque, and VerticalAccelerometer readings will have more significance after performing calibration inthe next section.

070 To the check the Flaps discrete channel, cycle the flaps to Landing and Approachwhile noting the change on the Live Data Display. It should go from 0 to 1.

080 To the check the Engine Bleed discrete channels, cycle the Left and Right EngineBleeds while noting the change on the Live Data Display. It should go from 0 to 1for each.

090 To the check the Ice Vane / Particle Separator discrete channels, cycle the Left andRight Engine Ice Vane / Particle Separators while noting the change on the LiveData Display. It should go from 0 to 1 for each.

100 To the check the Gear Extended discrete channel, you will need to check the livedata display both before and after jacking the aircraft and retracting the wheels.You will also need to read the signal before and after jacking for the Weight onWheels discrete channel.

To proceed:

a.) Check the Live Data display while the aircraft is on its gear. The Gear Extendedchannel should display 1. The Weight on Wheels channel should display 0.

b.) Jack the aircraft. The Weight on Wheels channel display should change to 1.

c.) Retract the landing gear. The Gear Extended channel display should change to0.

d.) Extend the landing gear, and remove the jacks.

110 Click “Stop Live Data” to stop viewing live data.

120 When prompted, place the “Run/Conf” switch in the “CONF” position and click “OK.”



3.4. Calibration Using Test Equipment

Calibration Notes:


The same test equipment that is used to check cockpit instruments can be used for calibrating the ADASAND ADAS+ system. You can calibrate the torque sensors using a dead weight tester, the ITT (T5) usinga Barfield tester, the pitot and static pressure sensors using a pitot/static tester, and the OAT sensor usinga calibrated thermometer -- or equivalent testers. This test equipment should be verified to be accurate.

Example Calibration of Engine Torque Channel:

We will use a generic torque signal calibration as an example. The torque figures below are used forillustration only. Use the appropriate instructions and manufacturer’s manual torque figures for an actualcalibration.

a.) To calibrate the torque channel we will first locate the appropriate step for calibrating torquefrom the Calibration Instruction steps listed below. The torque channel is listed in step 080.The instruction calls for a two point calibration of the torque sensors.

b.) To determine the minimum system requirements for the two points we look in Appendix A inthis manual. For two point calibration we must choose two calibration settings that have at leastthe minimum spread listed in the table. In our example for calibrating a torque signal, the tablespecifies a minimum required spread of 30%, or 22.5 PSI, or 1900 ft-lb. This is the minimumdifference between the two points we need to set our calibration test equipment to.

c.) To pick two specific points we refer to the aircraft manufacturer’s maintenance manual andlook up the signal being calibrated. For the torque calibration, we find in the manual a list ofsettings for a dead weight tester used to calibrate the torque instrument. That list includessettings of say 0, 10, 20, 30, 40, and 50 psi. From Appendix A, we already found we need atleast 22.5 psi spread between the points for setting the dead weight tester. We decide to useconvenient points of 10 and 50 pounds. This provides a 40 pound spread – which is better thanthe minimum required 22.5 psi.

d.) For the first point we pressurize the dead weight tester and torque high pressure line to 10pounds.

e.) We then check the cockpit indicator and find that the instrument reads, say 850 ft-lbs. Wecompare this to the manufacturer’s maintenance manual and find that the ideal reading is, say,836 ft-lbs, and that the acceptable range of tolerance is, say, 735 to 935 ft-lbs. The cockpitinstrument (at 850 lbs.) is therefore within manufacturer’s range of tolerance.

f.) Using MLP we set the monitor’s torque sensor calibration for the first point to 850 lbs. (thecockpit instrument reading).

We calibrate to the cockpit instrument reading, rather than the ideal reading (836 ft-lbs) so thatthe pilot’s readings and the monitor’s recordings will correlate. It is therefore important that thecockpit instrument reading comply with the manufacturer’s tolerance range. If it does not fit themanufacturer’s tolerance range (for example, if it read 950 lbs.), the cockpit instrument willhave to be calibrated before using it to set the monitoring system.

g.) To complete the calibration we repeat steps 4 through 6 for the 50 psi second calibration point.



Other calibration types: If instead of a two point calibration we had wanted to perform a single pointoffset or single point slope calibration, Appendix A would be consulted for the requirements for the singlepoint to be entered. The appendix contains three tables, one for each type of calibration.

In use, although the monitor is calibrated to cockpit instrument readings, even a properly calibratedmonitoring system may not absolutely agree with the cockpit indicators because of signal lag and humanfactors while setting, and normal signal fluctuation and system tolerances. The cockpit instrument fromwhich the system is calibrated may also be near one end of the acceptable range of error, and the monitorsystem’s range of tolerance may be additional to that difference. Where the difference between monitoror calibration equipment and the cockpit instrument reading is great, the cockpit instrument should beverified to be accurate.

Calibration Cautions:

Opening MLP for a calibration session will increment the Configuration File Version byone. Any number of sensors may be calibrated during this session without increasing theversion number further. Opening and closing and reopening MLP for calibration multipletimes however will increment the Configuration File Version each time it is opened, andthis should be avoided.


Calibration Instructions:

010 Connect the Communication Cable provided to the Communication Port. Connectthe other end of the cable to the serial port on a laptop computer running the currentversion of the Monitor Link Program (MLP).



040 Select “Sensor Calibration” under the MLU Menu. You will see a dropdown list ofsensors available for calibration.

NOTE: for the subsequent steps, only the following entries should be selected forcalibration in an ADAS AND ADAS+ system:

ITT (Engine 1 & 2)

Torque (Engine 1 and 2)

OAT (Processor 1 only -- this will actually calibrate both processors)

Vertical Accelerometer -- NOTE: The Vertical Accelerometer is no longeravailable as of March 1, 2009.

Airspeed (Processor 1 only -- this will actually calibrate both processors)

Altitude (Processor 1 only -- this will actually calibrate both processors)

Do not calibrate other signals, even though they are available through MLP aschoices.

Also note: although Pitot and Static are available, these entries won’t be chosenfrom the list. The pitot and static signals are more easily calibrated by selectingAirspeed and Altitude from the list.



050 Select Engine 1’s ITT entry and perform a Two Point Calibration using testequipment and referring to Appendix A for the requirements for minimumpermissible point spread.

060 Select Engine 2’s ITT entry and perform a Two Point Calibration using testequipment and referring to Appendix A for the requirements for minimumpermissible point spread

070 Select Processor 1’s OAT entry and perform a One Point Offset Calibration usingtest equipment and referring to Appendix A for the requirements for an offset pointvalue.

080 Select Engine 1’s Torque entry and perform a Two Point Calibration using testequipment and referring to Appendix A for the requirements for minimumpermissible point spread.

090 Select Engine 2’s Torque entry and perform a Two Point Calibration using testequipment and referring to Appendix A for the requirements for minimumpermissible point spread.

100 Select Processor 1’s Airspeed entry and perform a Two Point Calibration using testequipment and referring to Appendix A for the requirements for minimumpermissible point spread.

110 Select Processor 1’s Altitude entry and perform a Two Point Calibration using testequipment and referring to Appendix A for the requirements for minimumpermissible point spread.

120 Select the Vertical Accelerometer entry and perform a Two Point Calibration usingthe following procedure:

a.) Remove the vertical accelerometer from the center section.

b.) Have an assistant invert it by hand and note the contents of the grayed box inthe MLP computer’s calibration window – it should go to -1. Enter –1 in the whiteentry window.

c.) Have the assistant return the accelerometer to the right side up position andnote the contents of the grayed box in the MLP computer’s calibration window – itshould go to 1. Enter 1 in the white entry window.

130 After calibration, upload the new Configuration File version to yourTurbineTracker™ account. It is important to keep both the MLP andTurbineTracker™ configuration versions in sync.

3.5. Calibration Using Aircraft Cockpit Instruments

Calibration Notes:


This procedure is generally less precise than using calibration equipment standards and requires bothcalibration on the ground and in the air to obtain instrument readings. Two separate one point calibrationswill be performed in this procedure – one on the ground, and one in flight. This will approximate a twopoint calibration for the sensors, though it will actually be composed of one point calibrations. The singlepoint calibrations for each sensor will be entered as an Offset point (P2) on the ground, and a Slope point(P1) in the air.



Opening MLP for a calibration session will increment the Configuration File Version byone. Any number of sensors may be calibrated during this session without increasing theversion number further. Opening and closing and reopening MLP for calibration multipletimes however will increment the Configuration File Version each time it is opened, andthis should be avoided. The same session should be open for both the ground readingand the in flight reading to maintain a single Configuration File Version.


Calibration of the Vertical Accelerometer cannot be accomplished by reference toaircraft instruments. Calibration should be performed through the method described inSection 3.4.

010 Connect the Communication Cable provided to the Communication Port for theengine processor to be configured. Connect the other end of the cable to the serialport on a laptop computer running the current version of the Monitor Link Program(MLP).



040 Select “Sensor Calibration” under the MLU Menu. You will see a dropdown list ofsensors available for calibration.

NOTE: for the subsequent steps, only the following entries should be selected forcalibration in an ADAS/ADAS+ Upgrade:

ITT (Engine 1 & 2)

Torque (Engine 1 and 2)

OAT (Processor 1 only -- this will actually calibrate both processors)

Airspeed (Processor 1 only -- this will actually calibrate both processors)

Altitude (Processor 1 only -- this will actually calibrate both processors)

It is recommended that you do not calibrate other signals, even though they areavailable through MLP as choices.

050 Select Engine 1's ITT entry and perform a One Point Offset calibration adjustingthe value to the current engine temperature. If the engine is cold assume outsideair temperature for the value.

060 Select Engine 2's ITT entry and perform a One Point Offset calibration adjustingthe value to the current engine temperature. If the engine is cold assume outsideair temperature for the value.

070 Select Processor 1’s OAT entry and perform a One Point Offset calibrationadjusting the value to the current outside air temperature instrument reading.

080 Select Engine 1's Torque entry and perform a One Point Offset calibration adjustingthe value to the current engine torque. If the engine is not running, this valueshould be zero.

090 Select Engine 2's Torque entry and perform a One Point Offset calibration adjustingthe value to the current engine torque. If the engine is not running, this valueshould be zero.



100 Select Processor 1’s Airspeed entry and perform a One Point Offset calibration.On the ground (protected from wind and prop wash) this value should be zero.

110 Select Processor 1’s Altitude entry and perform a One Point Offset calibration. Toobtain actual “Pressure Altitude” adjust the barometric pressure in the aircraftaltimeter to 29.92 In Hg. Use the altitude value from the aircraft altimeter as thecalibration value.

120 Start the aircraft.

130 Take off and establish a steady state cruise flight condition.

140 Select Engine 1's ITT entry and perform a One Point Slope calibration adjusting thevalue to the current engine temperature shown by the aircraft instrument.

150 Select Engine 2's ITT entry and perform a One Point Slope calibration adjusting thevalue to the current engine temperature shown by the aircraft instrument.

160 Select Engine 1's Torque entry and perform a One Point Slope calibration adjustingthe value to the current engine torque shown by the aircraft instrument.

170 Select Engine 2's Torque entry and perform a One Point Slope calibration adjustingthe value to the current engine torque shown by the aircraft instrument.

180 Select Processor 1’s Airspeed entry and perform a One Point Slope calibrationadjusting the value to the current airspeed shown by the aircraft instrument.

190 Select Processor 1’s Altitude entry and perform a One Point Slope calibration. Toobtain actual “Pressure Altitude” adjust the barometric pressure in the aircraftaltimeter to 29.92 In. Hg. Use the value represented in the aircraft altimeter for thecalibration value.

200 After calibration, upload the new Configuration File version to yourTurbineTracker™ account. It is important to keep both the MLP andTurbineTracker™ configuration versions in sync.



4 AIRCRAFT TESTING

Following the requirements of FAR 91.407 it is recommended that the aircraftshould be inspected for airworthiness. If the ground and/or flight testing of themodified aircraft is not satisfactorily completed it should be returned to the originalaircraft configuration until the tests are completed and acceptable.

After installation and calibration, of the ADAS/ADAS+ Upgrade, it is recommended, though not required,that ground and flight tests be performed to verify the correct operation of the installed system. Thefollowing sections outline the suggested aircraft and system test procedures.

4.1. Aircraft Ground Test

For ADAS Only For all Listed Aircraft

010 With the aircraft battery connected and master switch on and breaker pulled, pushin the breaker and verify that the ADAS/ ADAS+ Upgrade TREND lamp(s)illuminate, indicating system boot-up. After approximately 2 seconds, the lamps willextinguish for about 2 seconds and then either:



- Come back on and remain on (ERROR state)

If the processor does NOT go into NORMAL state, retrieve the log data, andtroubleshoot the system.

020 Start the engines. Monitor the engine torque lines for oil leaks. If leaks are foundshut down and correct the leak.

030 With both engines running and the system operational, verify operation of all radios.All radios (VHF, AM, SATCOM, SELCAL, FLT PHONE, ETC.) should be checked onat least three frequencies (LOW, MED, HIGH) using a long count of 1 to 10. Allradios should perform normally.

040 With the aircraft running and the system operational, verify operation of allnavigation equipment. All navigation equipment (ILS, VOR, NDB, GPS, LORAN,ETC.) should be checked. All navigation equipment should perform normally.

050 With the aircraft running and the system operational verify the normal operation ofall other equipment (NITESUN, FLIR, etc.).

060 Record the results in the Electromagnetic Compatibility Testing table.



For ADAS+ Upgrade Only For all Listed Aircraft

010 With the aircraft battery connected and master switch on and breaker pulled, pushin the breaker and verify that the ADAS/ ADAS+ Upgrade TREND lamp illuminates,indicating system boot-up. After approximately 5 seconds, the lamps will extinguishand then either:



- Come back on and remain on (ERROR state)

If the processor does NOT go into NORMAL state, retrieve the log data, andtroubleshoot the system.

020 Start the engines. Monitor the engine torque lines for oil leaks. If leaks are foundshut down and correct the leak.

030 With the both engines running and the system operational, verify operation of allradios. All radios (VHF, AM, SATCOM, SELCAL, FLT PHONE, ETC.) should bechecked on at least three frequencies (LOW, MED, HIGH) using a long count of 1to 10. All radios should perform normally.

040 With the aircraft running and the system operational, verify operation of allnavigation equipment. All navigation equipment (ILS, VOR, NDB, GPS, LORAN,ETC.) should be checked. All navigation equipment should perform normally.

050 With the aircraft running and the system operational verify the normal operation ofall other equipment (NITESUN, FLIR, etc.).

060 Record the results in the Electromagnetic Compatibility Testing table.



Electromagnetic Compatibility Test Table

EQUIPMENTPROBLEMFOUND?

Y/NCOMMENTS

GROUND TESTCOMMENTS

FLIGHT TEST



070 On the runway, stabilize the engine at a convenient partial power setting.

080 Once the engine readings are stabilized, write down the cockpit instrument values inthe data table, below, including airspeed and altitude data.

090 As soon as the data is written down, push once on the Engine 1 TREND switch foran ADAS or once on the TREND switch for an ADAS+ Upgrade. Take care not todisturb the running conditions while the fault lamp is flashing and the processor isrecording data.

100 Repeat for the Engine 2 TREND Switch for ADAS and the TREND switch for theADAS+ Upgrade.

110 After successful completion of all ground tests, pot the processor harnessRaychem™ bulkhead connector (see Section 2.4.2) with PRC (MC236 B-1/2) andheat shrink the fitting.

The ADAS/ADAS+ Upgrade stored data will be retrieved at the conclusion of the ground and/orflight-testing. Once retrieved this data will also be inserted into the data table below and compared to theaircraft instrumentation.

GROUND TEST DATA TABLE

GroundTest 1

Eng. #1 Eng. #2 Comments

Cockpit ADAS/ADAS+

Upgrade

Delta Cockpit ADAS/ADAS+

Upgrade

Delta

TQ (ft lb.)

NP (rpm)

ITT (C)

Ng (%)

Wf (lb./hr)

Ice Vane

Bleed

OAT (C) *********

Alt (ft) *********

IAS (kts) *********



4.2. Aircraft Flight Test

For All Listed Aircraft:

010 Take off and climb to cruise altitude.

020 During the enroute phase of the flight, check all radios and navigation equipment fornormal performance. Ensure the absence of electromagnetic interference betweenthe ADAS/ADAS+ Upgrade and the rest of the aircraft systems. Record the resultsof all tests in the Electromagnetic Compatibility Test Table.

030 Check all other aircraft equipment and controls and verify normal operation.

040 Once the engine readings are stabilized, record the cockpit instrument values in theFlight Test Data Table, below.

050 As soon as the data is recorded, push once on the Engine 1 TREND switch. Takecare not to disturb the running conditions while the fault lamp is flashing and theprocessor is recording data.

060 Repeat for the engine 2 TREND Switch.

The system stored data will be retrieved at the conclusion of the ground and/or flight-testing. Onceretrieved this data will also be inserted into the data table below and compared to the aircraftinstrumentation.

FLIGHT TEST DATA TABLE

FlightTest 1

Eng. #1 Eng. #2 Comments

Cockpit ADAS/ADAS+

Upgrade

Delta Cockpit ADAS/ADAS+

Upgrade

Delta

TQ (ft lb.)

NP (rpm)

ITT (C)

Ng (%)

Wf (lb./hr)

Ice Vane

Bleed

OAT (C) *********

Alt (ft) *********

IAS (kts) *********



4.3. Test Data Retrieval and Review

After the ground and/or flight test(s) have been completed perform the following:

010 Retrieve the ADAS/ADAS+ Upgrade trend data for each engine to a laptopcomputer running the P&W Engine Services Monitor Link Program (MLP).

020 Fill in the Ground and/or Flight Test Tables with the trend data.

030 Review the tables for any discrepancies between the system data and the aircraftinstrument readings.

4.4. Continued Airworthiness Instructions

010 See Continued Airworthiness Instructions (TWIN-T-260-1) for trouble shooting ofsystem.

4.5. Documentation

010 Complete all FAA Form 337 paperwork and log book entries.

020 Complete and return the installation card to Pratt & Whitney Engine Services, Inc.at:

Pratt & Whitney Engine Services, Inc.Customer Service Department249 Vanderbilt Ave.Norwood, MA 02062



5 AIRCRAFT CONNECTION TABLES

5.1. 1900 & 1900C

RAYTHEON (BEECH) 1900 & 1900C

Signal Mfg.Config.

Connection Connection

Torque, Eng 1 All P&W E.S. Torque Transducers


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 Air ControlSwitch)


Ice Vane, Eng 1 All H218A20 (Ice Vane ControlSwitch)


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 TotalizerSystem installed. Please refer to the change in wiring for the fuel flow circuit if the following kitsare 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 (-)



5.2. 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 P&W E.S. TorqueTransducers

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

Torque, Eng 2 S/N UE1 thru UE92 P&W E.S. 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 (-)

Bleed, Eng 1 All H131A20 (Bleed AirControl Switch)

Bleed, Eng 2 All H143A20 (Bleed AirControl Switch)

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

Ice Vane, Eng 2 All H125A20 (Ice VaneControl Switch)

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 P&W E.S. Supplied Circuit BreakerPrimary Bus Source



5.3. 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




5.4. 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




5.5. 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, & B200T

Signal Mfg.Config.


Torque, Eng 1 Config 1 P&W E.S. Torque Transducers

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




5.6. 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




5.7. B300

RAYTHEON (BEECH) B300

Signal Mfg.Config.



Config 2 P&W E.S. Torque Transducers











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

























5.8. B300C & 300LW

RAYTHEON (BEECH) B300C & 300LW

Signal Mfg.Config.




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



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


































6 WIRING DIAGRAMS

6.1. ADAS

6.1.1. WIRING DIAGRAM NO. 1 FOR ADAS:

Configuration: With Supplied Torque Transducers, and No Supplied 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

ADASSystemProcessor

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




Configuration: With No Supplied Torque Transducers, And With No Supplied Voltage to Frequency Converter

Transducer

TD2

RED

BLKGRN

Transducer

TD1

RED

BLKGRN

Sig +

Sig -

Sig +

Sig -

Sig +

Sig +

Sig +

Sig +

Sig +

Sig -

Sig +

Sig -Flaps -Approach

Flaps - Final

Weight-on-Wheels

GearExtended

Sig +

Sig +

Proc 128VDCIn

GND

Proc 228VDCIn

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


68

75

9

68

75

9

12

34

12

34

101112

101112

ADASSystemProcessor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




IceVaneENG1

IceVaneENG2

Sig +

Sig -

Sig +

Sig -

TORQUE ENG 1

TREND ENG 1

TREND ENG 2

DOWNLOAD PORT

N1 ENG 1

N2 ENG 1

FUEL FLOWSENSORENG 1

ITT ENG 1

N1 ENG 2

N2 ENG 2

AC PITOT

AC STATIC

ITT ENG 2

FUEL FLOWSENSORENG 2

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


WHT/ORG

WHT/GRNWHT

WHT/BLU

WHT/ORGWHT/GRNWHT

WHT/BLU

WHT/BLUWHT

WHT/GRNWHT/ORG

BLEED ENG 1


WHT

WHT/ORG

WHT/BLU

4

3

2

1

1

4

2

3



OAT





BLEED ENG 2

NOTES:

WHT/BLU

WHT

ACCL CONN

WHT/GRN

WHT/ORGWHT/BLU

WHT

NOTE: INSULATE AND TIEBACK UNUSED WIRES

TORQUE ENG 2WHT/GRN

WHT/ORGWHT/BLU

WHT


1

4

2

3

3

4

1

2


PROC PWR




Configuration: With Supplied Torque Transducers, And With Supplied 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






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


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



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




Configuration: With No Supplied Torque Transducers, And With Supplied Voltage to Frequency Converter

Transducer

TD2

RED

BLKGRN

Transducer

TD1

RED

BLKGRN

Sig +

Sig -

Sig +

Sig +

Sig +

Sig +

Sig -

Flaps - Approach

Flaps - Final

Weight-on-Wheels

Gear Extended

Sig +

Sig +

Proc 128VDCIn

GND

Proc 228VDCIn

OAT Probe

AL- REDCH- YEL

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


1 2

1 2

123456

123456Vertical Accl

SIG

PWRGND


68

75

9

68

75

9

12

34

12

34

101112

101112

ADASSystem

Processor

J1.AJ1.BJ1.C

J1.L


J1.MJ1.NJ1.RJ1.P




Sig +

Sig -

Sig +

Sig -

594837261Sig +

IceVaneENG1

IceVaneENG2

Sig +

Sig -

Sig +

Sig -

TREND ENG 1

TREND ENG 2

DOWNLOAD PORT

N2 ENG 1

ITT ENG 1

N1 ENG 2

N2 ENG 2

AC PITOT

AC STATIC

ITT ENG 2

WHT/ORGWHT/BLU

WHT

RED

YEL

WHT

WHT

WHT

WHT

RED

YEL

WHT/ORG

WHT

WHT/BLU

WHT/GRN

REDYEL

WHT/BLU

WHT

WHT

WHT


WHT/ORG

WHT/GRNWHT

WHT/BLU

WHT/ORGWHT/GRNWHT

WHT/BLU

WHT/BLUWHT

WHT/GRNWHT/ORG

BLEED ENG 1


WHT

WHT/ORG

WHT/BLU

4

3

2

1

1

4

2

3



OAT





BLEED ENG 2

NOTES:

WHT/BLU

WHT

ACCL CONN

WHT/GRN

WHT/ORGWHT/BLU

WHT

TORQUE ENG 2


1

4

2

3

3

4

1

2



WHT

WHT/BLU

WHT/BLU

FUEL FLOWCONVERTER


WHTWHT/BLU

WHT/BLUWHT

WHTWHT/BLU

WHT

WHT

WHT


CONV PWR

FUEL FLOWENG 2 PROC

FUELFLOW

ENG2INPUT

TORQUE ENG 1

FUELFLOW

ENG1PROC

FUEL FLOW ENG 1INPUT

N1 ENG 1

WHT

WHT/GRNWHT/BLUWHT/ORG

PROC PWR



6.2. ADAS+ UPGRADE

6.2.1. WIRING DIAGRAM NO. 1 FOR ADAS+ UPGRADE:

Configuration: With Supplied Torque Transducers, and No Supplied 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 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

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:

(1) REFER TO THE CONFIGURATION CHART FOR ALL

WIRING CONNECTIONS TO THE AIRCRAFT.

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




Configuration: With No Supplied Torque Transducers, And With No Supplied 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 -




Configuration: With Supplied Torque Transducers, And With Supplied 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




Configuration: With No Supplied Torque Transducers, And With Supplied 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+



7 HARNESS CONNECTOR SIGNAL PINOUTSInstallation Caution:

Refer to the Aircraft Connection Tables and Wiring Diagrams for your model A/C for allconnections.

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

7.1. ADAS Connector Signal Points

7.1.1. HARNESS J1, CONNECTOR “S”

(Power/Aircraft Harness)

Connector HarnessPin Wire Color Signal Name

4 COND CABLEA WHT/ORG Pitot/Static - Pitot SigB WHT Pitot/Static - VccD WHT/GRN Pitot/Static - Static SigG WHT/BLU Pitot/Static - Gnd

3 COND CABLEG WHT/BLU Aircraft GroundF WHT Processor #1 PowerM WHT/ORG Processor #2 Power

THERMOCOUPLE CABLEC RED Thermocouple - AlumelE YEL Thermocouple - Chromel

2 COND CABLEJ WHT Flaps, Approach SigH WHT/BLU Flaps, Final Sig

1 COND CABLEL WHT Gear Extended Sig

1 COND CABLEK WHT Weight on Wheels Sig

2 COND CABLEN WHT Ice Vane Sig, Engine 1R WHT/BLU Ice Vane Sig, Engine 2

P Shields



7.1.2. HARNESS J2, CONNECTOR “SA”

(Engine No. 1 Harness)

Connector HarnessPin Wire Color Signal

4 COND CABLEA WHT Torque - VccB WHT/ORG Torque - Sig – HighC WHT/BLU Torque - GndF WHT/GRN Torque - Sig - Low

1 COND CABLED WHT RPM Sig (N1)

1 COND CABLEE WHT RPM Sig (N2)

2 COND CABLEG WHT Fuel Flow - Sig +R WHT/BLU Fuel Flow - Sig –

3 COND CABLEM WHT Vertical Accl. - VccL WHT/BLU Vertical Accl. - GndH WHT/ORG Vertical Accl. - Sig

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009. If the kit waspurchased after March 1, 2009 and does not come with a Vertical Accelerometer, then cap andstow the wire as it will not be needed.

THERMOCOUPLE CABLEJ RED Thermocouple - AlumelK YEL Thermocouple - Chromel

1 COND CABLEN WHT Bleed Air Sig, Engine 1

P Shields



7.1.3. HARNESS J3 CONNECTOR, “SB”



4 COND CABLEA WHT Torque - VccB WHT/ORG Torque - Sig - HighC WHT/BLU Torque - GndF WHT/GRN Torque - Sig - Low



2 COND CABLEG WHT Fuel Flow - Sig +R WHT/BLU Fuel Flow - Sig -

THERMOCOUPLE CABLEJ RED Thermocouple – AlumelK YEL Thermocouple - Chromel


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

P Shields



7.2. ADAS+ Upgrade Connector Signal Points

7.2.1. HARNESS J1, CONNECTOR “S”

(Power/Aircraft Harness)


4 COND CABLEA WHT/ORG Pitot/Static - Pitot SigB WHT Pitot/Static - VccD WHT/GRN Pitot/Static - Static SigG WHT/BLU Pitot/Static - Gnd

3 COND CABLEG WHT/BLU Aircraft GroundF WHT Bus Power InM WHT/ORG Battery Power In

4 COND CABLEC RED OAT-DE WHITE OAT-GN RED OAT-R+R WHT OAT R

2 COND CABLEJ WHT Flaps, Approach SigH WHT/BLU Flaps, Final Sig

1 COND CABLEL WHT Gear Extended Sig

1 COND CABLEK WHT Weight on Wheels Sig

P Shields



7.2.2. HARNESS J2, CONNECTOR “SA”


Processor ConnectorPin Wire Color Signal

4 COND CABLEA WHT Torque - VccB WHT/ORG Torque - Sig – HighC WHT/BLU Torque - GndF WHT/GRN Torque - Sig - Low



2 COND CABLEG WHT Fuel Flow - Sig +R WHT/BLU Fuel Flow - Sig –

3 COND CABLEM WHT Vertical Accl. - VccL WHT/BLU Vertical Accl. - GndH WHT/ORG Vertical Accl. - Sig

NOTE: The Vertical Accelerometer is no longer available as of March 1, 2009. If the kit waspurchased after March 1, 2009 and does not come with a Vertical Accelerometer, then cap andstow the wire as it will not be needed.



P Shields



7.2.3. HARNESS J3 CONNECTOR, “SB”



4 COND CABLEA WHT Torque - VccB WHT/ORG Torque - Sig - HighC WHT/BLU Torque - GndF WHT/GRN Torque - Sig - Low



2 COND CABLEG WHT Fuel Flow - Sig +R WHT/BLU Fuel Flow - Sig -



2 COND CABLEM WHT Ice Vane Sig, Engine 1L WHT/BLU Ice Vane Sig, Engine 2

H (Unused)

P Shields



7.3. Harness “Comm” Connectors for ADAS

7.3.1. (COCKPIT TREND SWITCH HARNESS) – SINGLE DISPLAY

Connector Harness to: Single Cockpit ConnectorPin Wire Color Signal 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

7.3.2. (COCKPIT TREND SWITCH HARNESS) – DUAL DISPLAY

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

4 COND CABLE8 WHT Lamp - PTT V+ 1 ENG 1 Female9 WHT/BLU Lamp - Gnd 2 6 Pin7 WHT/GRN Lamp - Switched V+ 32 WHT/ORG Pilot Trend Digital 0 4

4 COND CABLE8 WHT Lamp - PTT V+ 1 ENG 2 Female9 WHT/BLU Lamp - Gnd 2 6 Pin3 WHT/GRN Lamp - Switched V+ 36 WHT/ORG Pilot Trend Digital 0 4

4 COND CABLE4 WHT/ORG Serial RS-485 +B 1 DOWNLOAD Male5 WHT/GRN Serial RS-485 -A 2 6 Pin9 WHT/BLU System Gnd 31 WHT Run/Config Digital 1 4

9 Shields



7.4. Harness “Comm” Connectors for ADAS+ Upgrade

7.4.1. COCKPIT TREND SWITCH HARNESS

Connector Harness to: Single Cockpit ConnectorPin Wire Color Signal 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

9 Shields



8 SYSTEM OPERATION OVERVIEW

8.1. Capabilities

For All Aircraft Models:

The ADAS/ADAS+ Upgrade is an instrument that gathers and records engine information fromsensors for 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

8.1.1. ENGINE RUN LOGGINGThe ADAS/ADAS+ Upgrade are capable of recording engine runs. For each run the following is

recorded for each engine:

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

8.1.2. CYCLE LOGGINGThe ADAS/ADAS+ Upgrade can be configured for up to four different types of cycle count types

during each engine run.

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

8.1.3. EVENT MONITORING

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



8.2. Functional Descriptions


8.2.1. INITIALIZATION

When the system initializes, both TREND lamps indicate the various stages of the process. Theprocessor initialization 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.

8.2.2. SYSTEM MODES FOR ADAS ONLY

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 datatransfer it is generally operated in Configuration Mode.

Configuration Mode is entered when a Communication cable is attached and the cable’sRun/Configure switch is set to CONF. Run Mode is entered when the cable is not attached, or when it isattached and the Run/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. Duringthis period a trend data sample can be stored manually by the pilot (if the cockpit is equipped witha TREND 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 toa user command. The ADAS/ADAS+ Upgrade does not write new records to system memory in thismode. 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.

8.2.3. RUN MODE FOR ADAS ONLY

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

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

8.2.4. 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.



8.2.5. 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 an acknowledgement of the button press to the serial communications port.

Note if the lamp is flashing, or ON, pressing the switch twice will accomplish both of theabove actions. It will extinguish the lamp and then perform a Loopback Test. The lampwill remain off at the completion of the test.

8.2.6. MANUAL SELF TEST (LOOPBACK TEST) FOR ADAS ONLY

The Loopback test is a simple manual test that allows the user to check the operation ofthe lamp and CPU. It may be initiated in Configuration Mode or in Run Mode when the engine isnot running and the lamp is extinguished. Pressing the TREND switch initiates the Loop backTest.

Lamp Flashes for 5 Seconds means a Loopback Test was initiated, and issuccessful. The processor and lamp are functional.

8.2.7. RUN MODE FOR ADAS+ UPGRADE ONLY

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

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.



8.2.8. 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 StartCriteria (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 Maintenancestate.

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.



9 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 9.1 and individual components are detailed by assembly kit numbersin section 9.3.

9.1. 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 B300CPedestal 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

1

1The 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.



200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300CPedestal 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

2

200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300CIndividual 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

2

200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300CIndividual 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

2


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



9.2. 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



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 B300CPedestal 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

3

200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300CPedestal 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

4


types or models. Refer to the Aircraft Configuration Charts for which aircraft require them.4

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



200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300CIndividual 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

2

200, 200T, 200C, 200CT, A200, A200C, A200CT, B200, B200C, B200T, B200CT, 300,300LW, B300, and B300CIndividual 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

2



9.3. 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 2

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

Alternate 4000-00062Backshell M85049/41-10A 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 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 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 FORADAS+ 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



10 MAINTENANCE REQUIREMENTS

The Pratt & Whitney Engine Services, Inc. twin engine Aircraft Data Acquisition System EngineMonitor has been designed with the latest in solid-state technology. The only component that has a limitedlife span is the internal battery. This battery is anticipated under normal operation to last over 10 years. Ifthe battery is discharged, the twin engine ADAS/ADAS+ Upgrade processor must be returned to P&WEngine Services for battery replacement.

The only (non-LRU) field-replaceable component in the P&W Engine Services ADAS/ADAS+Upgrade is the incandescent lamp in the TREND switch indicator. This lamp can be purchased at anyaircraft supply or by calling Pratt & Whitney Engine Services, Inc. Should you suspect a problem, the unitshould be returned to the factory for service.

The calibration of the system should remain within documented specifications under normaloperation. It is suggested that operators initially monitor the calibration of the twin engine Aircraft DataAcquisition Systems every other 100-hour inspection. If the calibration does not change after 2 - 3inspections the calibration check period can be increased to every 1000 hours to coincide with the plannedaircraft instrument schedule.

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

Comments and findings should be forwarded to Pratt & Whitney Engine Services, Inc. forinclusion in our continued product improvement program.

In the event that the twin engine ADAS/ADAS+ Upgrade must be returned for service, contact theP&W Engine Services Customer Service Department for an RMA number. When you receive the RMAnumber, include it in the package address and ship it, postage and insurance prepaid, to the addresslisted below.

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

Pratt & Whitney Engine Services, Inc.Customer Service Department249 Vanderbilt Ave.Norwood, MA 02062(781) 762-8600



11 SERVICE

11.1. Customer SupportPratt & Whitney Engine Services, Inc. provides customer support in accordance with the product

warranty detailed within the customer’s sales contract. If you have any questions concerning any P&WEngine Services product, please do not hesitate to call us. Our Customer Service department acceptscalls Monday through Friday between 9:00 AM and 5:00 PM EST. Please have your model and serialnumber ready when you call.

Pratt & Whitney Engine Services, Inc.Customer Service Department249 Vanderbilt Ave.Norwood, MA 02062(781) 762-8600

11.2. DisclaimerLike all instrumentation, the Pratt & Whitney Engine Services, Inc. twin engine ADAS/ADAS+

Upgrade requires knowledgeable interpretation by the pilot. Any recommendations and operatingprocedures contained in this installation manual (TWIN-I-010-1) shall not supersede the aircraft or enginemanufacturers’ recommendations, operating procedures, requirements, or limits. The Pratt & WhitneyEngine Services, Inc. twin engine Aircraft Data Acquisition Systems should not be used as a primary guidefor monitoring the aircraft and engine manufacturers’ operating limits. Pratt & Whitney Engine Services,Inc. is not liable for any damages resulting from the use of this product.



12 SPECIFICATIONS

12.1. P&W Engine Services Twin Engine ADAS/ADAS+ Upgrade TWIN-K-010

GENERALChassis Size: 3.5" x 2.7" x 6"Weight (whole system): 12.6 - 14.75 lbs.

Total added airborne weight of the P&W Engine Services twin engine ADAS or ADAS+ Upgrade isapproximately 14.75 pounds for aircraft requiring P&W Engine Services torque transducers. Totaladded weight is approximately 12.6 pounds for aircraft not requiring P&W Engine Services torquetransducers.

SYSTEM COMPONENT WEIGHTSADAS or ADAS+ Upgrade Processor 2.03 lbsProcessor Mounting Bracket 0.2 lbsHarness, J1 1.6 lbs

1

Harness, J2 2.63 lbsHarness, J3 2.0 lbsHarness, COMM 1.6 lbs.Pitot/Static Kit 1.54 lbsOAT Kit 0.39 lbs.Engine Torque Kit 2.16 lbsRaychem™ Press Bulkhead Fitting 0.4 lbsVoltage to Frequency Converter 0.2 lbs

2

POWER REQUIREMENTSVoltage Range: 8 to 35VDCCurrent Draw: < 700 mAPower Draw: 12 Watts, operating

20 mWatts, standby

ENVIRONMENTAL(All tests to RTCA/DO-160C)Operating Temperature Range: -40

oC to +70

oC

Storage Temperature Range: -55o

C to +85o

COperating Ceiling (Pressure Altitude): 55,000 FeetHumidity Rating: Category B - SevereShock Rating: 12 G

DATA INTERFACEComputer Interface: RS-485 Serial Interface

SYSTEM SOFTWAREAll tests to RTCA/DO-178B Level C.

1The weight for the harness is from the kit. Any wire cut from the harness during installation will reducethe harness weight.

2The P&W Engine Services Voltage to Frequency Converter is not required for all aircraft types or

models.



SENSOR CHANNEL RANGE AND ACCURACYEngine 1 & 2 Temperature Measurement Range: 0

oC to 1200

oC

Accuracy: +/- 5o

CEngine 1 & 2 N1 Speed Measurement Range: 0 - 150%

Accuracy: +/- .1 %Engine 1 & 2 N2 Speed Measurement Range: 0 - 150%

Accuracy: +/- .1 %Engine 1 & 2 Torque Measurement Range: 0 –150 PSI

Accuracy: +/- 2 %(High Precision Torque Option) Measurement Range 0-100 PSI

Accuracy +/- 1%

Engine 1 & 2 Fuel Flow Measurement Range: 10 – 30,000 HzAccuracy: +/- 2 Hz

Altitude Measurement Range: -1000 to + 32,000 Ft.Accuracy: +/- 75 FtAccuracy (>32,000Ft): +/- 150 Ft

Airspeed Measurement Range: 0 - 350 KnotsAccuracy: +/- 5 Knots

Outside Air Temperature Measurement Range: -55o

C to +100o

CAccuracy: +/- 5

oC

Aircraft Vertical Acceleration Measurement Range: +/- 5gAccuracy: +/- .06g

SAMPLE RATEAll inputs are sampled five times per second.

DATA STORAGESystem Data: Eight text fields for storage of Tail Number, Serial Number

and Engine Module Serial Numbers

Engine Run Data: Engine Run DateEngine Run TimeMax. Sensor Values ObservedCycles Counted

Exceedance Data: Exceedance DateExceedance TimeExceedance DurationExceedance TypeMaximum Value ObservedAverage Value Observed

Trend Sample: Trend Type (Auto/Manual)Trend Time,Sensor Max Value ObservedSensor Average Value Observed

Number of Records: Depending on type, up to 300 Engine Runs with oneTrend Sample per flight



APPENDIX A

Two Point Calibration Minimum RequirementsSensor Type Minimum Requirements for point selection

Engine Temperature* If any point is less then 400 degC, the calibration points mustdiffer by 400 degC

Engine Temperature* If all points are above 400 degC, the calibration points mustdiffer by 200 degC

Thermocouple OATSensor* (ADAS)

Calibration points must differ by 30 degC

Torque* Calibration points must differ by 30%, or 22.5 PSI or 1900 ft-lbAltitude* Calibration points must differ by 4000 ft

* A value pair is either the two values specified by the user or the two values read fromthe unit.

One Point Slope (P1) Calibrations Minimum Requirements

Sensor Type Minimum Requirements for point selection

Engine Temperature Values must be greater than 400 degCTorque Values must be greater than 25%, or 18.75 PSI or 1550 ft-lbStatic Pressure Must be less than 5.3 in Hg, or 2.6 PSIAAltitude Must be less than 40500 ftAirspeed Must be greater than 80 knots

One Point Offset (P2) Calibrations Minimum Requirements

Sensor Type Minimum Requirements for point selection

TemperatureSensors

Values must be less than 70 degC

Torque Values must be less than 25%, or 18.75 PSI or 1550 ft-lbStatic Pressure Must be less than 5.3 in Hg, or 2.6 PSIAAltitude Must be less than 40500 ftRTD OAT Sensor (ADAS+) Must be less than 145 degCPitot Must be less than 0.075 PSIDAirspeed Must be less than 60 knots

Documents

ADAS/ADAS+ Upgrade Installation Manual TWIN-I-010-1 Rev O.pdf · 2009-03-11 · Pratt & Whitney Engine Services, Inc. 249 Vanderbilt Ave Norwood, MA 02062 249 Vanderbilt Ave., Norwood,